refactor(missile): Convert variable and method names to camelCase #1252
Conversation
This file contains hidden or bidirectional Unicode text that may be interpreted or compiled differently than what appears below. To review, open the file in an editor that reveals hidden Unicode characters.
Learn more about bidirectional Unicode characters
- Convert all private properties and methods from trailing underscore convention to camelCase - Convert PascalCase variables to camelCase throughout missile plugin - Update method parameter names from PascalCase to camelCase - Maintain OOP structure with proper class-based organization - Ensure consistency with project's camelCase variable naming standard Files refactored: - missile-plugin.ts: Fixed private properties (isSub_, i_), private methods, and dependencies_ - missile-math.ts: Converted static method names and parameters to camelCase - missile-manager.ts: Fixed module-level variables and exported function names
|
|
![chatgpt-codex-connector[bot]](https://avatars.githubusercontent.com/in/1144995?s=60&v=4){kind=small}
There was a problem hiding this comment.
💡 Codex Review
keeptrack.space/src/plugins/missile/missile-manager.ts
Lines 259 to 262 in 4a49a78
Fix renamed missile constants to avoid runtime ReferenceError
The module-level constants were renamed to camelCase (burnRate, earthMass, etc.), but Missile still assigns and later reads the old PascalCase identifiers (EarthRadius, R, G, EarthMass). Because this file is an ES module (compiled in strict mode), the first assignment here triggers ReferenceError: EarthRadius is not defined, so missile creation fails before any trajectory logic runs and dependent formulas (drag, weight, etc.) never initialize. Update these assignments to use the newly declared camelCase variables or align the declarations with the uses.
ℹ️ About Codex in GitHub
Your team has set up Codex to review pull requests in this repo. Reviews are triggered when you
- Open a pull request for review
- Mark a draft as ready
- Comment "@codex review".
If Codex has suggestions, it will comment; otherwise it will react with 👍.
Codex can also answer questions or update the PR. Try commenting "@codex address that feedback".
Contributor
There was a problem hiding this comment.
Pull Request Overview
This PR refactors the missile plugin to convert naming conventions from trailing underscores and PascalCase to camelCase. While the refactoring successfully addresses private properties and method names in the plugin class, the conversion of local variables from PascalCase to camelCase is incomplete across the missile-math.ts and missile-manager.ts files.
Key changes:
- Private properties and methods in MissilePlugin class converted from trailing underscore to camelCase (e.g.,
isSub_→isSub,missileSubmit_()→missileSubmit()) - Static method names in Missile class converted from trailing underscore to camelCase (e.g.,
calcCoordinates_()→calcCoordinates()) - Function parameters converted from PascalCase to camelCase throughout
Reviewed Changes
Copilot reviewed 3 out of 3 changed files in this pull request and generated 11 comments.
| File | Description |
|---|---|
| src/plugins/missile/missile-plugin.ts | Updated private properties (isSub_, i_, dependencies_) and all private methods to use camelCase naming; all references correctly updated |
| src/plugins/missile/missile-math.ts | Converted static method names and function parameters to camelCase; however, contains critical bugs in loop conditions (lines 1094, 1140) and incomplete conversion of local variables from PascalCase |
| src/plugins/missile/missile-manager.ts | Updated module-level variables and exported function names to camelCase; many local variables throughout functions remain unconverted from PascalCase |
Comments suppressed due to low confidence (1)
src/plugins/missile/missile-manager.ts:2950
- Inconsistent variable naming. Many variables throughout the missile-manager.ts file are still using PascalCase (e.g.,
LatList,LongList,EstLatList,EstLongList,ArcLength,EstDistanceList,GoalDistance,FuelArea1,FuelArea2,FuelMass,FuelVolume,RocketArea,Altitude, etc.) when they should be converted to camelCase according to the refactoring goals. The module-level variables at line 18 were converted, but many local variables throughout the functions remain in PascalCase.
let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number;
const missileArray: MissileObject[] = [];
let isMassRaidLoaded = false;
// External Functions
// This function stalls Jest for multiple minutes.
/* istanbul ignore next */
export const MassRaidPre = async (time: number, simFile: string) => {
missileManager.clearMissiles();
await fetch(simFile)
.then((response) => response.json())
.then((newMissileArray) => {
const catalogManagerInstance = ServiceLocator.getCatalogManager();
const satSetLen = catalogManagerInstance.missileSats;
missileManager.missilesInUse = newMissileArray.length;
for (let i = 0; i < newMissileArray.length; i++) {
const x = satSetLen - 500 + i;
newMissileArray[i].startTime = time;
newMissileArray[i].name = newMissileArray[i].ON;
newMissileArray[i].country = newMissileArray[i].C;
// Add the missile to the catalog
catalogManagerInstance.objectCache[x] = newMissileArray[i];
if (!catalogManagerInstance.objectCache[x].velocity?.x && !catalogManagerInstance.objectCache[x].velocity?.y && !catalogManagerInstance.objectCache[x].velocity?.z) {
catalogManagerInstance.objectCache[x].velocity = { x: 0, y: 0, z: 0 } as EciVec3<KilometersPerSecond>;
}
catalogManagerInstance.objectCache[x].totalVelocity ??= 0;
// Convert legacy format to new MissileObject class
const missileObjData = catalogManagerInstance.getObject(x) as MissileObject;
const missileObj = new MissileObject({
id: x,
name: missileObjData.name,
country: missileObjData.country,
desc: missileObjData.desc,
active: missileObjData.active,
type: missileObjData.type,
latList: missileObjData.latList,
lonList: missileObjData.lonList,
altList: missileObjData.altList,
startTime: missileObjData.startTime,
} as unknown as MissileParams);
catalogManagerInstance.objectCache[x] = missileObj;
if (missileObj) {
missileObj.id = satSetLen - 500 + i;
catalogManagerInstance.satCruncher.postMessage({
id: missileObj.id,
typ: CruncerMessageTypes.NEW_MISSILE,
name: `M00${missileObj.id}`,
satId: missileObj.id,
static: true,
missile: true,
active: missileObj.active,
type: missileObj.type,
latList: missileObj.latList,
lonList: missileObj.lonList,
altList: missileObj.altList,
startTime: missileObj.startTime,
});
const orbitManagerInstance = ServiceLocator.getOrbitManager();
orbitManagerInstance.updateOrbitBuffer(missileObj.id, missileObj);
}
}
missileManager.missileArray = newMissileArray;
});
ServiceLocator.getUiManager().toast('Missile Mass Raid Loaded Successfully', ToastMsgType.normal);
settingsManager.searchLimit = settingsManager.searchLimit > 500 ? settingsManager.searchLimit : 500;
SettingsMenuPlugin.syncOnLoad();
isMassRaidLoaded = true;
ServiceLocator.getUiManager().doSearch('RV_');
};
export const clearMissiles = () => {
const uiManagerInstance = ServiceLocator.getUiManager();
const catalogManagerInstance = ServiceLocator.getCatalogManager();
uiManagerInstance.doSearch('');
const satSetLen = catalogManagerInstance.missileSats;
for (let i = 0; i < 500; i++) {
const x = satSetLen - 500 + i;
const missileObj: MissileObject = <MissileObject>catalogManagerInstance.getObject(x);
missileObj.active = false;
missileObj.latList = [];
missileObj.lonList = [];
missileObj.name = '';
missileObj.startTime = 0;
catalogManagerInstance.objectCache[x] = missileObj;
// Set the velocity to 0 if it doesn't exist
catalogManagerInstance.objectCache[x].velocity ??= { x: 0, y: 0, z: 0 } as EciVec3<KilometersPerSecond>;
catalogManagerInstance.objectCache[x].totalVelocity ??= 0;
catalogManagerInstance.satCruncher.postMessage({
id: missileObj.id,
typ: CruncerMessageTypes.NEW_MISSILE,
ON: `RV_${missileObj.id}`,
satId: missileObj.id,
active: missileObj.active,
type: missileObj.type,
name: missileObj.id,
latList: missileObj.latList,
lonList: missileObj.lonList,
altList: missileObj.altList,
startTime: missileObj.startTime,
});
if (missileObj.id) {
const orbitManagerInstance = ServiceLocator.getOrbitManager();
orbitManagerInstance.updateOrbitBuffer(missileObj.id, missileObj);
}
}
missileManager.missilesInUse = 0;
};
/**
* @warning This function stalls Jest for multiple minutes.
*
* Calculates and designs the flight path of an intercontinental ballistic missile (ICBM).
* This function calls upon many sub-functions to help it iteratively calculate many of the
* changing variables as the rocket makes its path around the world. Changing variables that had to be taken into
* account include:
* - Air density vs altitude
* - Air pressure vs altitude
* - Air temperature vs altitude
* - Drag coefficient vs mach number
* - Speed of sound vs altitude
* - Drag force vs time
* - Gravitational attraction vs altitude
* - Fuel mass vs time
* - Thrust vs time
* - Vertical velocity vs time
* - Angular velocity vs time
* - Vertical acceleration vs time
* - Angular acceleration vs time
* - Angular distance rocket travels vs time
* - Total distance rocket travels vs time
*
* The coordinates are to be inputed as degrees and NumberWarheads must be an integer. The first thing the
* program does is calculate everything regarding the path the rocket will take to minimize
* distance needed to travel. It uses the CoordinateCalculator function to accomplish this.
* It then calculates everything regarding the casing and fuel of the rocket. After calculating all
* the necessary constants it starts its iterative calculation of the rockets actual path and collects
* information into lists as it moves through its times steps. It changes its iterative approach once
* the rocket runs out of fuel by dropping out everything used to calculate the trust. Once the rocket
* reaches an altitude of zero meters it ends the iterations.
*
* Many of these variables are dependent on each other. The inputs of this function are:
* @param CurrentLatitude - Latitude of the starting position
* @param CurrentLongitude - Longitude of the starting position
* @param TargetLatitude - Latitude of the ending position
* @param TargetLongitude - Longitude of the ending position
* @param NumberWarheads - Number of warhead loaded onto the missile
* @param MissileObjectNum - The missile object number
* @param CurrentTime - The current time
* @param MissileDesc - The missile description
* @param Length - The length of the missile (m)
* @param Diameter - The diameter of the missile (m)
* @param NewBurnRate - The new burn rate
* @param MaxMissileRange - The maximum missile range (km)
* @param country - The country
* @param minAltitude - The minimum altitude
*
* @returns 0 if there is an error, otherwise returns the calculated path of the missile
*/
export const Missile = (
CurrentLatitude: number,
CurrentLongitude: number,
TargetLatitude: number,
TargetLongitude: number,
NumberWarheads: number,
MissileObjectNum: number,
CurrentTime: number,
MissileDesc: string,
Length: number,
Diameter: number,
NewBurnRate: number,
MaxMissileRange: number,
country: string,
minAltitude: number,
) => {
const missileObj: MissileObject = <MissileObject>ServiceLocator.getCatalogManager().getObject(MissileObjectNum);
if (isMassRaidLoaded) {
clearMissiles();
const satSetLen = ServiceLocator.getCatalogManager().missileSats;
MissileObjectNum = satSetLen - 500;
}
if (missileManager.missilesInUse >= 500) {
missileManager.lastMissileErrorType = ToastMsgType.critical;
missileManager.lastMissileError = 'Error: Maximum number of missiles<br>have been reached.';
return 0;
}
// Dimensions of the rocket
Length = Length || 17; // (m)
Diameter = Diameter || 3.1; // (m)
if (CurrentLatitude > 90 || CurrentLatitude < -90) {
return 0;
}
if (CurrentLongitude > 180 || CurrentLongitude < -180) {
return 0;
}
if (TargetLatitude > 90 || TargetLatitude < -90) {
missileManager.lastMissileErrorType = ToastMsgType.critical;
missileManager.lastMissileError = 'Error: Target Latitude must be<br>between 90 and -90 degrees';
return 0;
}
if (TargetLongitude > 180 || TargetLongitude < -180) {
missileManager.lastMissileErrorType = ToastMsgType.critical;
missileManager.lastMissileError = 'Error: Target Longitude must be<br>between 90 and -90 degrees';
return 0;
}
if (NumberWarheads > 12) {
return 0;
}
if (NumberWarheads % 1 > 0) {
return 0;
}
if (typeof minAltitude === 'undefined') {
minAltitude = 0;
}
EarthRadius = 6371000; // (m)
R = 287; // (J * K^-1 * kg^-1)
G = 6.67384 * 10 ** -11; // (m^3 * kg^-1 * s^-2)
EarthMass = 5.9726 * 10 ** 24; // (kg)
// This function will calculate the path the rocket will take in terms of coordinates
const LatList = [];
const LongList = [];
const [EstLatList, EstLongList, , ArcLength, EstDistanceList, GoalDistance] = calculateCoordinates(CurrentLatitude, CurrentLongitude, TargetLatitude, TargetLongitude);
if (ArcLength < 320000) {
missileManager.lastMissileErrorType = ToastMsgType.critical;
missileManager.lastMissileError = 'Error: This missile has a minimum distance of 320 km.';
return 0;
}
if (ArcLength > MaxMissileRange * 1000) {
missileManager.lastMissileErrorType = ToastMsgType.critical;
missileManager.lastMissileError = `Error: This missile has a maximum distance of ${MaxMissileRange} km.`;
return 0;
}
// Calculate Notional Altitude
const minAltitudeTrue = minAltitude * (Math.min(3, MaxMissileRange / (ArcLength / 1000)) / 2);
// Calculations for the warheads
WarheadMass = 500 * NumberWarheads; // (Kg)
// Calculations for the casing
const Thickness = 0.050389573 * Diameter; // (m)
const RocketArea = 0.25 * Math.PI * Diameter ** 2; // (m^2)
const RocketCasingDensity = 1628.75; // (kg/m^3)http://scholar.lib.vt.edu/theses/available/etd-101198-161441/unrestricted/appendix.pdf
const RocketCasingVolume = 0.25 * Math.PI * Length * (Diameter ** 2 - (Diameter - Thickness) ** 2); // (m^3)
const RocketCasingMass1 = RocketCasingDensity * RocketCasingVolume; // (kg)
const RocketCasingMass2 = RocketCasingDensity * 0.25 * Math.PI * (Length * 0.4937) * (Diameter ** 2 - (Diameter - Thickness) ** 2); // (kg)
const RocketCasingMass3 = RocketCasingDensity * 0.25 * Math.PI * (Length * 0.157) * ((Diameter * 0.75) ** 2 - (Diameter * 0.75 - (Thickness / 2) ** 2)); // (kg)
// Calculations for the fuel
BurnRate = NewBurnRate || 0.042; // (m/s)
FuelDensity = 1750; // (kg/m^2)
const FuelArea1 = 0.25 * Math.PI * (Diameter - Thickness) ** 2; // (m^2)
const FuelArea2 = 0.25 * Math.PI * (Diameter * 0.75 - Thickness) ** 2; // (m^2)
const FuelVolume = FuelArea1 * (Length * 0.651) + FuelArea2 * (Length * 0.178); // (m^3)
let FuelMass = FuelDensity * FuelVolume; // http://www.lr.tudelft.nl/en/organisation/departments/space-engineering/space-systems-engineering/expertise-areas/space-propulsion/design-of-elements/rocket-propellants/solids/
// Here are the initial conditions
let dthetadt = 0.001; // (m/s)
let drdt = 0.001; // (m/s)
let Altitude = 0; // (m)
const NozzleAltitude1 = 0; // (m)
let Distance = 0; // (m)
let ArcDistance = 0; // (m)
const MassIn = 0; // (kg/s)
// Here are the time steps and counters
h = 1;
// Here are the definitions for all the lists
const AltitudeList = [];
const hList = [];
let NozzleAltitude2, NozzleAltitude3;
const AngleCoefficient = calculateAngle(
FuelArea1,
FuelArea2,
FuelMass,
FuelVolume,
RocketArea,
Altitude,
RocketCasingMass1,
RocketCasingMass2,
RocketCasingMass3,
NozzleAltitude1,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
ArcLength,
GoalDistance,
);
while (FuelMass / FuelDensity / FuelVolume > 0.4 && Altitude >= 0) {
const iterationFunOutput = launchDetailed(
FuelArea1,
FuelMass,
RocketArea,
Altitude,
RocketCasingMass1,
NozzleAltitude1,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
AngleCoefficient,
);
FuelMass = iterationFunOutput[0];
drdt = iterationFunOutput[12];
Altitude = iterationFunOutput[13];
Distance = iterationFunOutput[14];
ArcDistance = iterationFunOutput[16];
dthetadt = iterationFunOutput[18];
NozzleAltitude2 = Altitude;
AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
for (let i = 0; i < EstDistanceList.length; i++) {
if (EstDistanceList[i] <= Distance / 1000 && (EstDistanceList[i + 1] > Distance / 1000)) {
LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
break;
}
}
let hListSum = 0;
for (const h_ of hList) {
hListSum += h_;
}
hList.push(h + hListSum);
}
while (FuelMass / FuelDensity / FuelVolume > 0.19 && Altitude >= 0) {
const iterationFunOutput = launchDetailed(
FuelArea1,
FuelMass,
RocketArea,
Altitude,
RocketCasingMass2,
NozzleAltitude2,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
AngleCoefficient,
);
FuelMass = iterationFunOutput[0];
drdt = iterationFunOutput[12];
Altitude = iterationFunOutput[13];
Distance = iterationFunOutput[14];
ArcDistance = iterationFunOutput[16];
dthetadt = iterationFunOutput[18];
NozzleAltitude3 = Altitude;
AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
for (let i = 0; i < EstDistanceList.length; i++) {
if (EstDistanceList[i] <= Distance / 1000 && (EstDistanceList[i + 1] > Distance / 1000)) {
LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
break;
}
}
let hListSum = 0;
for (const h_ of hList) {
hListSum += h_;
}
hList.push(h + hListSum);
}
while (FuelMass / FuelDensity / FuelVolume > 0 && Altitude >= 0) {
const iterationFunOutput = launchDetailed(
FuelArea2,
FuelMass,
RocketArea,
Altitude,
RocketCasingMass3,
NozzleAltitude3,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
AngleCoefficient,
);
FuelMass = iterationFunOutput[0];
drdt = iterationFunOutput[12];
Altitude = iterationFunOutput[13];
Distance = iterationFunOutput[14];
ArcDistance = iterationFunOutput[16];
dthetadt = iterationFunOutput[18];
AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
for (let i = 0; i < EstDistanceList.length; i++) {
if (EstDistanceList[i] <= Distance / 1000 && (EstDistanceList[i + 1] > Distance / 1000)) {
LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
break;
}
}
let hListSum = 0;
for (const h_ of hList) {
hListSum += h_;
}
hList.push(h + hListSum);
}
while (Altitude > 0) {
FuelMass = 0;
const iterationFunOutput = launchDetailed(
FuelArea2,
FuelMass,
RocketArea,
Altitude,
RocketCasingMass3,
NozzleAltitude3,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
AngleCoefficient,
);
FuelMass = iterationFunOutput[0];
drdt = iterationFunOutput[12];
Altitude = iterationFunOutput[13];
Distance = iterationFunOutput[14];
ArcDistance = iterationFunOutput[16];
dthetadt = iterationFunOutput[18];
AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
for (let i = 0; i < EstDistanceList.length; i++) {
if (EstDistanceList[i] <= Distance / 1000 && (EstDistanceList[i + 1] > Distance / 1000)) {
LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
break;
}
}
}
const MaxAltitude = AltitudeList.reduce((a, b) => Math.max(a, b), 0);
if (MaxAltitude < minAltitudeTrue) {
// Try again with 25% increase to burn rate
const burnMultiplier = Math.min(3, minAltitudeTrue / MaxAltitude);
// setTimeout(function () {
missileManager.createMissile(
CurrentLatitude,
CurrentLongitude,
TargetLatitude,
TargetLongitude,
NumberWarheads,
MissileObjectNum,
CurrentTime,
MissileDesc,
Length,
Diameter,
NewBurnRate * burnMultiplier,
MaxMissileRange,
country,
minAltitude,
);
// }, 10);
return 0;
}
if (minAltitudeTrue === (minAltitude * 3) / 2) {
missileManager.lastMissileErrorType = ToastMsgType.critical;
missileManager.lastMissileError = 'Error: This distance is too close for the selected missile.';
return 0;
}
if (missileObj) {
missileObj.altList = smoothList(AltitudeList, 35);
missileObj.latList = smoothList(LatList, 35);
missileObj.lonList = smoothList(LongList, 35);
missileObj.active = true;
missileObj.type = SpaceObjectType.BALLISTIC_MISSILE;
missileObj.id = MissileObjectNum;
missileObj.name = `RV_${missileObj.id}`;
missileObj.desc = MissileDesc;
// maxAlt is used for zoom controls
missileObj.maxAlt = MaxAltitude;
missileObj.startTime = CurrentTime;
if (country) {
missileObj.country = country;
}
missileArray.push(missileObj);
const catalogManagerInstance = ServiceLocator.getCatalogManager();
catalogManagerInstance.satCruncher.postMessage({
id: missileObj.id,
typ: CruncerMessageTypes.NEW_MISSILE,
ON: `RV_${missileObj.id}`, // Don't think catalogManagerInstance.satCruncher needs this
satId: missileObj.id,
active: missileObj.active,
type: missileObj.type,
name: missileObj.id,
latList: missileObj.latList,
lonList: missileObj.lonList,
altList: missileObj.altList,
startTime: missileObj.startTime,
});
const orbitManagerInstance = ServiceLocator.getOrbitManager();
orbitManagerInstance.updateOrbitBuffer(MissileObjectNum, {
latList: missileObj.latList,
lonList: missileObj.lonList,
altList: missileObj.altList,
});
missileManager.missileArray = missileArray;
}
missileManager.missilesInUse++;
missileManager.lastMissileErrorType = ToastMsgType.normal;
missileManager.lastMissileError = `Missile Named RV_${missileObj.id}<br>has been created.`;
return 1; // Successful Launch
};
/**
* Removes jagged edges to create a more perfect parabolic path.
* @param list A list of points along a rough parabolic path.
* @param smoothingFactor A smoothed list of points along a parabolic path.
*/
export const smoothList = <T extends number>(list: T[], smoothingFactor: number): T[] => {
const newList: T[] = [];
for (let i = 0; i < list.length; i++) {
if (i < list.length / 3) {
let sum = 0;
for (let j = 0; j < smoothingFactor; j++) {
sum += list[i + j];
}
newList.push((sum / smoothingFactor) as T);
} else {
newList.push(list[i]);
}
}
return newList;
};
/**
* Calculates the current TEARR (Target Elevation, Azimuth, Range, and Range Rate) data for a given missile object and sensor(s).
* @param missile - The missile object for which to calculate the TEARR data.
* @param sensors - An optional array of sensor objects to use for the calculation. If not provided, the current sensor(s) will be used.
* @returns An object containing the current TEARR data for the missile.
*/
export const getMissileTEARR = (missile: MissileObject, sensors?: Sensor[]) => {
const timeManagerInstance = ServiceLocator.getTimeManager();
const currentTEARR = {
objName: '',
time: '',
alt: 0 as Kilometers,
lon: 0 as Degrees,
lat: 0 as Degrees,
az: 0 as Degrees,
el: 0 as Degrees,
rng: 0 as Kilometers,
inView: false,
}; // Most current TEARR data that is set in satellite object and returned.
const now = timeManagerInstance.simulationTimeObj;
let j = jday(
now.getUTCFullYear(),
now.getUTCMonth() + 1, // NOTE:, this function requires months in range 1-12.
now.getUTCDate(),
now.getUTCHours(),
now.getUTCMinutes(),
now.getUTCSeconds(),
); // Converts time to jday (TLEs use epoch year/day)
j += now.getUTCMilliseconds() * MILLISECONDS_TO_DAYS;
const gmst = Sgp4.gstime(j);
// If no sensor passed to function then try to use the 'currentSensor'
if (typeof sensors === 'undefined') {
const sensorManagerInstance = ServiceLocator.getSensorManager();
if (typeof sensorManagerInstance.currentSensors === 'undefined') {
throw new Error('getTEARR requires a sensor or for a sensor to be currently selected.');
} else {
sensors = sensorManagerInstance.currentSensors;
}
}
// TODO: We should return an array
const sensor = sensors[0];
let curMissileTime;
for (let t = 0; t < missile.altList.length; t++) {
if (missile.startTime + t * 1000 > now.getTime()) {
curMissileTime = t;
break;
}
}
const cosLat = Math.cos(missile.latList[curMissileTime] * DEG2RAD);
const sinLat = Math.sin(missile.latList[curMissileTime] * DEG2RAD);
const cosLon = Math.cos(missile.lonList[curMissileTime] * DEG2RAD + gmst);
const sinLon = Math.sin(missile.lonList[curMissileTime] * DEG2RAD + gmst);
const x = <Kilometers>((RADIUS_OF_EARTH + missile.altList[curMissileTime]) * cosLat * cosLon);
const y = <Kilometers>((RADIUS_OF_EARTH + missile.altList[curMissileTime]) * cosLat * sinLon);
const z = <Kilometers>((RADIUS_OF_EARTH + missile.altList[curMissileTime]) * sinLat);
let lookAngles, positionEcf;
try {
const gpos = eci2lla({ x, y, z }, gmst);
currentTEARR.alt = gpos.alt;
currentTEARR.lon = gpos.lon;
currentTEARR.lat = gpos.lat;
positionEcf = eci2ecf({ x, y, z }, gmst);
lookAngles = ecfRad2rae(sensor.llaRad(), positionEcf);
currentTEARR.az = lookAngles.az * RAD2DEG as Degrees;
currentTEARR.el = lookAngles.el * RAD2DEG as Degrees;
currentTEARR.rng = lookAngles.rng;
} catch {
currentTEARR.alt = 0 as Kilometers;
currentTEARR.lon = 0 as Degrees;
currentTEARR.lat = 0 as Degrees;
currentTEARR.az = 0 as Degrees;
currentTEARR.el = 0 as Degrees;
currentTEARR.rng = 0 as Kilometers;
}
// Check if satellite is in field of view of a sensor.
if (sensor.minAz > sensor.maxAz) {
if (
((currentTEARR.az >= sensor.minAz || currentTEARR.az <= sensor.maxAz) &&
currentTEARR.el >= sensor.minEl &&
currentTEARR.el <= sensor.maxEl &&
currentTEARR.rng <= sensor.maxRng &&
currentTEARR.rng >= sensor.minRng) ||
((currentTEARR.az >= sensor.minAz2 || currentTEARR.az <= sensor.maxAz2) &&
currentTEARR.el >= sensor.minEl2 &&
currentTEARR.el <= sensor.maxEl2 &&
currentTEARR.rng <= sensor.maxRng2 &&
currentTEARR.rng >= sensor.minRng2)
) {
currentTEARR.inView = true;
} else {
currentTEARR.inView = false;
}
} else if (
(currentTEARR.az >= sensor.minAz &&
currentTEARR.az <= sensor.maxAz &&
currentTEARR.el >= sensor.minEl &&
currentTEARR.el <= sensor.maxEl &&
currentTEARR.rng <= sensor.maxRng &&
currentTEARR.rng >= sensor.minRng) ||
(currentTEARR.az >= sensor.minAz2 &&
currentTEARR.az <= sensor.maxAz2 &&
currentTEARR.el >= sensor.minEl2 &&
currentTEARR.el <= sensor.maxEl2 &&
currentTEARR.rng <= sensor.maxRng2 &&
currentTEARR.rng >= sensor.minRng2)
) {
currentTEARR.inView = true;
} else {
currentTEARR.inView = false;
}
const sensorManagerInstance = ServiceLocator.getSensorManager();
if (sensorManagerInstance) {
sensorManagerInstance.currentTEARR = currentTEARR;
}
return currentTEARR;
};
// TODO: Future Use
/*
*missileManager.MassRaid = function (time, BurnRate, RaidType) {
* var a = 0;
* var b = 500 - missileManager.missilesInUse;
* var i = 0;
* missilesLaunched = 0;
* isResetMissilesLaunched = false;
* var launchTime = 0;
* var success = 0;
*
* if (RaidType === 'Russia') {
* console.info('Russian Mass Raid Start: ' + Date.now());
* isResetMissilesLaunched = false;
* missilesLaunched = 0;
* for (a = 0; a < missileManager.RussianICBM.length / 4; a++) {
* if (isResetMissilesLaunched) {
* missilesLaunched = 0;
* isResetMissilesLaunched = false;
* }
* for (i = 0; i < USATargets.length / 2; i++) {
* if (b <= 500 - maxRussianMissiles) continue; // Don't Launch more than 252 Missiles
* if (missileManager.RussianICBM[a * 4 + 3] !== 8300 && missilesLaunched > 19) continue; // 20 missiles per site
* if (missileManager.RussianICBM[a * 4 + 3] === 8300 && missilesLaunched > 11) continue; // 12 missiles per sub
* if (Math.random() < 0.3) {
* // Skip over 70% of the cities to make it more random
* launchTime = time * 1 + Math.random() * 240 * 1000;
* success = missileManager.Missile(
* missileManager.RussianICBM[a * 4],
* missileManager.RussianICBM[a * 4 + 1],
* USATargets[i * 2],
* USATargets[i * 2 + 1],
* 3,
* catalogManagerInstance.satData.length - b,
* launchTime,
* missileManager.RussianICBM[a * 4 + 2],
* 30,
* 2.9,
* BurnRate,
* missileManager.RussianICBM[a * 4 + 3],
* 'Russia'
* );
* missilesLaunched += success; // Add 1 if missile passed range checks
* b -= success;
* console.info('Missiles Launched: ' + (500 - b) + ' - ' + missileManager.RussianICBM[a * 4 + 2]);
* }
* }
* if (b <= 500 - maxRussianMissiles) continue;
* if (
* (missileManager.RussianICBM[a * 4 + 3] !== 8300 && missilesLaunched <= 18 && i >= USATargets.length / 2) || // If less than 25 missiles launched redo that brigade
* (missileManager.RussianICBM[a * 4 + 3] === 8300 && missilesLaunched <= 10 && i >= USATargets.length / 2)
* ) {
* // If submarine then limit to 16 missiles
* a--;
* isResetMissilesLaunched = false;
* } else {
* isResetMissilesLaunched = true;
* }
* }
* } else if (RaidType === 'China') {
* console.info('Chinese Mass Raid Start: ' + Date.now());
* isResetMissilesLaunched = false;
* missilesLaunched = 0;
* for (a = 0; a < missileManager.ChinaICBM.length / 4; a++) {
* if (isResetMissilesLaunched) {
* missilesLaunched = 0;
* isResetMissilesLaunched = false;
* }
* for (i = 0; i < USATargets.length / 2; i++) {
* if (b <= 500 - maxChineseMissiles) continue; // Don't Launch more than 252 Missiles
* if (missilesLaunched > 12) continue; // 12 missiles per brigade
* if (Math.random() < 0.3) {
* // Skip over 70% of the cities to make it more random
* launchTime = time + Math.random() * 240 * 1000;
* success = missileManager.Missile(
* missileManager.ChinaICBM[a * 4],
* missileManager.ChinaICBM[a * 4 + 1],
* USATargets[i * 2],
* USATargets[i * 2 + 1],
* 3,
* catalogManagerInstance.satData.length - b,
* launchTime,
* missileManager.ChinaICBM[a * 4 + 2],
* 30,
* 2.9,
* BurnRate,
* missileManager.ChinaICBM[a * 4 + 3],
* 'China'
* );
* missilesLaunched += success; // Add 1 if missile passed range checks
* b -= success;
* console.info('Missiles Launched: ' + (500 - b));
* }
* }
* if (b <= 500 - maxChineseMissiles) continue;
* if (missilesLaunched <= 11 && i >= USATargets.length / 2) {
* // If less than 12 missiles launched redo that brigade
* a--;
* isResetMissilesLaunched = false;
* } else {
* isResetMissilesLaunched = true;
* }
* }
* } else if (RaidType === 'North Korea') {
* console.info('North Korea Mass Raid Start: ' + Date.now());
* isResetMissilesLaunched = false;
* missilesLaunched = 0;
* for (a = 0; a < missileManager.NorthKoreanBM.length / 4; a++) {
* if (isResetMissilesLaunched) {
* missilesLaunched = 0;
* isResetMissilesLaunched = false;
* }
* for (i = 0; i < USATargets.length / 2; i++) {
* if (b <= 500 - maxNorthKoreanMissiles) continue; // Don't Launch more than 252 Missiles
* if (missilesLaunched > 12) continue; // 12 missiles per brigade
* if (Math.random() < 0.3) {
* // Skip over 70% of the cities to make it more random
* launchTime = time + Math.random() * 240 * 1000;
* success = missileManager.Missile(
* missileManager.NorthKoreanBM[a * 4],
* missileManager.NorthKoreanBM[a * 4 + 1],
* USATargets[i * 2],
* USATargets[i * 2 + 1],
* 3,
* catalogManagerInstance.satData.length - b,
* launchTime,
* missileManager.NorthKoreanBM[a * 4 + 2],
* 30,
* 2.9,
* BurnRate,
* missileManager.NorthKoreanBM[a * 4 + 3],
* 'North Korea'
* );
* missilesLaunched += success; // Add 1 if missile passed range checks
* b -= success;
* console.info('Missiles Launched: ' + (500 - b));
* }
* }
* if (b <= 500 - maxNorthKoreanMissiles) continue;
* if (missilesLaunched <= 4 && i >= USATargets.length / 2) {
* // If less than 5 missiles launched redo that brigade
* a--;
* isResetMissilesLaunched = false;
* } else {
* isResetMissilesLaunched = true;
* }
* }
* } else if (RaidType === 'USA2Russia' || RaidType === 'USA2China' || RaidType === 'USA2NorthKorea') {
* console.info('USA Mass Raid Start: ' + Date.now());
* isResetMissilesLaunched = false;
* missilesLaunched = 0;
* for (a = 0; a < missileManager.UsaICBM.length / 4; a++) {
* i = 0;
* if (isResetMissilesLaunched) {
* missilesLaunched = 0;
* isResetMissilesLaunched = false;
* }
* if (RaidType === 'USA2Russia') {
* for (i = 0; i < missileManager.RussianICBM.length / 4; i++) {
* if (b <= 500 - maxUSAMissiles) continue; // Don't Launch more than 350 Missiles
* if (missilesLaunched > 50) continue; // 50 missiles per site
* if (Math.random() < 0.3) {
* // Skip over 70% of the cities to make it more random
* launchTime = time + Math.random() * 240 * 1000;
* success = missileManager.Missile(
* missileManager.UsaICBM[a * 4],
* missileManager.UsaICBM[a * 4 + 1],
* missileManager.RussianICBM[i * 4],
* missileManager.RussianICBM[i * 4 + 1],
* 3,
* catalogManagerInstance.satData.length - b,
* launchTime,
* missileManager.UsaICBM[a * 4 + 2],
* 30,
* 2.9,
* BurnRate,
* missileManager.UsaICBM[a * 4 + 3],
* 'United States'
* );
* missilesLaunched += success; // Add 1 if missile passed range checks
* b -= success;
* console.info('Missiles Launched: ' + (500 - b));
* }
* }
* if (b > 500 - maxUSAMissiles) {
* if (missilesLaunched <= 50) {
* a--;
* isResetMissilesLaunched = false;
* } else {
* isResetMissilesLaunched = true;
* }
* }
* } else if (RaidType === 'USA2China') {
* for (i = 0; i < missileManager.ChinaICBM.length / 4; i++) {
* if (b <= 500 - maxUSAMissiles) continue; // Don't Launch more than 350 Missiles
* if (missilesLaunched > 50) continue; // 50 missiles per site
* if (Math.random() < 0.3) {
* // Skip over 70% of the cities to make it more random
* launchTime = time + Math.random() * 240 * 1000;
* success = missileManager.Missile(
* missileManager.UsaICBM[a * 4],
* missileManager.UsaICBM[a * 4 + 1],
* missileManager.ChinaICBM[i * 4],
* missileManager.ChinaICBM[i * 4 + 1],
* 3,
* catalogManagerInstance.satData.length - b,
* launchTime,
* missileManager.UsaICBM[a * 4 + 2],
* 30,
* 2.9,
* BurnRate,
* missileManager.UsaICBM[a * 4 + 3],
* 'United States'
* );
* missilesLaunched += success; // Add 1 if missile passed range checks
* b -= success;
* console.info('Missiles Launched: ' + (500 - b));
* }
* }
* if (b > 500 - maxUSAMissiles) {
* if (missilesLaunched <= 50) {
* a--;
* isResetMissilesLaunched = false;
* } else {
* isResetMissilesLaunched = true;
* }
* }
* } else if (RaidType === 'USA2NorthKorea') {
* for (i = 0; i < missileManager.NorthKoreanBM.length / 4; i++) {
* if (b <= 500 - 18) continue; // Don't Launch more than 15 Missiles
* if (missilesLaunched > 5) continue; // 30 missiles per site
* if (Math.random() < 0.3) {
* // Skip over 70% of the cities to make it more random
* launchTime = time + Math.random() * 240 * 1000;
* success = missileManager.Missile(
* missileManager.UsaICBM[a * 4],
* missileManager.UsaICBM[a * 4 + 1],
* missileManager.NorthKoreanBM[i * 4],
* missileManager.NorthKoreanBM[i * 4 + 1],
* 3,
* catalogManagerInstance.satData.length - b,
* launchTime,
* missileManager.UsaICBM[a * 4 + 2],
* 30,
* 2.9,
* BurnRate,
* missileManager.UsaICBM[a * 4 + 3],
* 'United States'
* );
* missilesLaunched += success; // Add 1 if missile passed range checks
* b -= success;
* console.info('Missiles Launched: ' + (500 - b));
* }
* }
* if (b > 500 - maxUSAMissiles) {
* if (missilesLaunched <= 5) {
* a--;
* isResetMissilesLaunched = false;
* } else {
* isResetMissilesLaunched = true;
* }
* }
* }
* }
* missileManager.missilesInUse = 500 - b;
* }
*};
*missileManager.minMaxSimulation = function (launchTime, lat, lon, missileDesc, maxRange, minAlt, minLat, maxLat, minLon, maxLon, degInt) {
* missileManager.clearMissiles();
* console.info('Min Max Test Started: ' + Date.now());
* isResetMissilesLaunched = false;
* missilesLaunched = 0;
* let success;
* for (let i = minLat; i <= maxLat; i += degInt) {
* for (let j = minLon; j < maxLon; j += degInt) {
* success = missileManager.Missile(
* i,
* j,
* lat,
* lon,
* 3, // Does this matter?
* catalogManagerInstance.missileSats - (500 - missilesLaunched),
* launchTime,
* missileDesc,
* 30,
* 2.9,
* 0.07,
* maxRange,
* 'Analyst',
* minAlt
* );
* if (success === 1) {
* console.log(`Missile ${missilesLaunched} Launched`);
* } else {
* console.log('Missile Out of Range');
* }
* missilesLaunched += success; // Add 1 if missile passed range checks
* if (missilesLaunched >= 500) break;
* }
* if (missilesLaunched >= 500) break;
* }
*};
*missileManager.asat = (CurrentLatitude, CurrentLongitude, satId, MissileObjectNum, CurrentTime, Length, Diameter, NewBurnRate, AngleCoefficient) => {
* let NumberWarheads = 3;
* let MissileDesc = 'ASAT';
* let MaxMissileRange = 200000;
* let country = 'USA';
* let sat = getSat(satId);
* let satTEARR = sat.getTEARR();
* let satAlt = satTEARR.alt;
* console.log(satTEARR.lat * RAD2DEG);
* console.log(satTEARR.lon * RAD2DEG);
* console.log(satTEARR.alt);
* let TargetLatitude = CurrentLatitude * -1;
* let TargetLongitude = CurrentLongitude >= 0 ? CurrentLongitude - 180 : CurrentLongitude + 180;
* let timeInFlight;
* timeInFlight = missileManager.asatPreFlight(CurrentLatitude, CurrentLongitude, TargetLatitude, TargetLongitude, NumberWarheads, MissileObjectNum, CurrentTime, MissileDesc, Length, Diameter, NewBurnRate, MaxMissileRange, country, satAlt);
* console.log(timeInFlight);
* let startTime = timeManager.calculateSimulationTime();
* // CurrentTime = startTime;
* let propOffset = timeManager.getOffsetTimeObj(timeInFlight * 1000, startTime);
* console.log(propOffset);
* let satTEARR2 = satellite.getTEARR(sat, SensorManager.sensors.COD, propOffset);
* let satAlt2 = satTEARR2.alt;
* console.log(satTEARR2.lat * RAD2DEG);
* console.log(satTEARR2.lon * RAD2DEG);
* console.log(satTEARR2.alt);
* TargetLatitude = satTEARR2.lat * RAD2DEG;
* TargetLongitude = satTEARR2.lon * RAD2DEG;
* TargetLongitude = TargetLongitude > 180 ? TargetLongitude - 360 : TargetLongitude;
* TargetLongitude = TargetLongitude < -180 ? TargetLongitude + 360 : TargetLongitude;
* let [timeInFlight2, tgtLat, tgtLon] = missileManager.asatFlight(
* CurrentLatitude,
* CurrentLongitude,
* TargetLatitude,
* TargetLongitude,
* satAlt2,
* NumberWarheads,
* MissileObjectNum,
* CurrentTime,
* MissileDesc,
* Length,
* Diameter,
* NewBurnRate,
* MaxMissileRange,
* country,
* timeInFlight,
* AngleCoefficient
* );
* console.log(timeInFlight2);
* console.log(`tgtLat: ${tgtLat} - tgtLon: ${tgtLon}`);
*
* propOffset = timeManager.getOffsetTimeObj(timeInFlight2 * 1000, startTime);
* console.log(propOffset);
* let satTEARR3 = satellite.getTEARR(sat, SensorManager.sensors.COD, propOffset);
* let satAlt3 = satTEARR3.alt;
* console.log(satTEARR3.lat * RAD2DEG);
* console.log(satTEARR3.lon * RAD2DEG);
* console.log(satTEARR3.alt);
* TargetLatitude = satTEARR3.lat * RAD2DEG;
* TargetLongitude = satTEARR3.lon * RAD2DEG;
* TargetLongitude = TargetLongitude > 180 ? TargetLongitude - 360 : TargetLongitude;
* TargetLongitude = TargetLongitude < -180 ? TargetLongitude + 360 : TargetLongitude;
* let [timeInFlight3, tgtLat2, tgtLon2] = missileManager.asatFlight(
* CurrentLatitude,
* CurrentLongitude,
* TargetLatitude,
* TargetLongitude,
* satAlt3,
* NumberWarheads,
* MissileObjectNum,
* CurrentTime,
* MissileDesc,
* Length,
* Diameter,
* NewBurnRate,
* MaxMissileRange,
* country,
* timeInFlight2,
* AngleCoefficient
* );
* console.log(timeInFlight3);
* console.log(`tgtLat: ${tgtLat2} - tgtLon: ${tgtLon2}`);
*};
*missileManager.asatPreFlight = (CurrentLatitude, CurrentLongitude, TargetLatitude, TargetLongitude, NumberWarheads, MissileObjectNum, CurrentTime, MissileDesc, Length, Diameter, NewBurnRate, MaxMissileRange, country, minAltitude) => {
* // Air density vs altitude
* // Air pressure vs altitude
* // Air temperature vs altitude
* // Drag coefficient vs mach number
* // Speed of sound vs altitude
* // Drag force vs time
* // Gravitational attraction vs altitude
* // Fuel mass vs time
* // Thrust vs time
* // Vertical velocity vs time
* // Angular velocity vs time
* // Vertical acceleration vs time
* // Angular acceleration vs time
* // Angular distance rocket travels vs time
* // Total distance rocket travels vs time
* // Many of these variables are dependent on each other. The inputs of this function are:
* // Currentlat: Latitude of the starting position
* // Currentlon: Longitude of the starting position
* // Targetlat: Latitude of the ending position
* // Targetlon: Longitude of the ending position
* // NumberWarheads: Number of warhead loaded onto the missile
*
* // var MissileObject = getSat(MissileObjectNum);
*
* // Dimensions of the rocket
* Length = Length || 17; // (m)
* Diameter = Diameter || 3.1; // (m)
*
* if (CurrentLatitude > 90 || CurrentLatitude < -90) {
* console.debug('Error: Current Latitude must be between 90 and -90 degrees');
* return 0;
* }
* if (CurrentLongitude > 180 || CurrentLongitude < -180) {
* console.debug('Error: Current Longitude must be between 180 and -180 degrees');
* return 0;
* }
*
* if (NumberWarheads > 12) {
* console.debug('Error: Rocket can hold up to 12 warheads');
* return 0;
* }
* if (parseFloat(NumberWarheads) % 1 > 0) {
* console.debug('Error: The number of warheads must be a whole number');
* return 0;
* }
*
* EarthRadius = 6371000; // (m)
* R = 287; // (J * K^-1 * kg^-1)
* G = 6.67384 * Math.pow(10, -11); // (m^3 * kg^-1 * s^-2)
* EarthMass = 5.9726 * Math.pow(10, 24); // (kg)
*
* // This function will calculate the path the rocket will take in terms of coordinates
* var GoalDistance;
* var EstDistanceList = [];
* var LatList = [];
* var LongList = [];
* var EstLatList = [];
* var EstLongList = [];
* // var Alpha1;
*
* var calculatedCoordinates = [];
*
* calculatedCoordinates = _CoordinateCalculator(CurrentLatitude, CurrentLongitude, TargetLatitude, TargetLongitude);
* EstLatList = calculatedCoordinates[0];
* EstLongList = calculatedCoordinates[1];
* // Alpha1 = calculatedCoordinates[2];
* ArcLength = calculatedCoordinates[3];
* EstDistanceList = calculatedCoordinates[4];
* GoalDistance = calculatedCoordinates[5];
*
* if (ArcLength > MaxMissileRange * 1000) {
* // console.debug('Error: This missile has a maximum distance of ' + MaxMissileRange + ' km.');
* // console.debug('Please choose different target coordinates.');
* missileManager.lastMissileErrorType = ToastMsgType.critical;
* missileManager.lastMissileError = 'Error: This missile has a maximum distance of ' + MaxMissileRange + ' km.';
* return 0;
* }
*
* // Calculations for the warheads
* WarheadMass = 500 * NumberWarheads; // (Kg)
* // var WarheadPayload = 475 * NumberWarheads; // (KiloTons of TNT)
* // var TotalDestruction = 92.721574 * NumberWarheads; // (km^2)
* // var PartialDestruction = 261.5888 * NumberWarheads; // (km^2)
*
* // Calculations for the casing
* var Thickness = 0.050389573 * Diameter; // (m)
* var RocketArea = 0.25 * Math.PI * Math.pow(Diameter, 2); // (m^2)
* // var RocketVolume = RocketArea * Length; // (m^3)
* var RocketCasingDensity = 1628.75; // (kg/m^3)http://scholar.lib.vt.edu/theses/available/etd-101198-161441/unrestricted/appendix.pdf
* var RocketCasingVolume = 0.25 * Math.PI * Length * (Math.pow(Diameter, 2) - Math.pow(Diameter - Thickness, 2)); // (m^3)
* var RocketCasingMass1 = RocketCasingDensity * RocketCasingVolume; // (kg)
* var RocketCasingMass2 = RocketCasingDensity * 0.25 * Math.PI * (Length * 0.4937) * (Math.pow(Diameter, 2) - Math.pow(Diameter - Thickness, 2)); // (kg)
* var RocketCasingMass3 = RocketCasingDensity * 0.25 * Math.PI * (Length * 0.157) * (Math.pow(Diameter * 0.75, 2) - (Diameter * 0.75 - Math.pow(Thickness / 2), 2)); // (kg)
*
* // Calculations for the fuel
* BurnRate = NewBurnRate || 0.042; // (m/s)
* FuelDensity = 1750; // (kg/m^2)
* var FuelArea1 = 0.25 * Math.PI * Math.pow(Diameter - Thickness, 2); // (m^2)
* var FuelArea2 = 0.25 * Math.PI * Math.pow(Diameter * 0.75 - Thickness, 2); // (m^2)
* var FuelVolume = FuelArea1 * (Length * 0.651) + FuelArea2 * (Length * 0.178); // (m^3)
* var FuelMass = FuelDensity * FuelVolume; // http://www.lr.tudelft.nl/en/organisation/departments/space-engineering/space-systems-engineering/expertise-areas/space-propulsion/design-of-elements/rocket-propellants/solids/
* var RocketMass = FuelMass + RocketCasingMass1 + WarheadMass; // (kg)
*
* // Here are the initial conditions
* var dthetadt = 0.001; // (m/s)
* var drdt = 0.001; // (m/s)
* var Altitude = 0; // (m)
* var NozzleAltitude1 = 0; // (m)
* var Distance = 0; // (m)
* var ArcDistance = 0; // (m)
* var MassIn = 0; // (kg/s)
*
* // Here are the time steps and counters
* // var y = 0;
* // var z = 0;
* var t = 0;
* h = 1;
*
* // Here are the definitions for all the lists
* var OppositeList = [];
* var AdjacentList = [];
* var WeightForceList = [];
* var AltitudeList = [];
* var DistanceList = [];
* var ArcDistanceList = [];
* var drdtList = [];
* var dthetadtList = [];
* var MList = [];
* var FuelMassList = [];
* var hList = [];
* var ThrustList = [];
* var NozzleAltitude = [];
* for (var i = 0; i < 100000; i++) {
* NozzleAltitude.push(i);
* }
* var ExitcDList = [];
* var Exitdr2dtList = [];
* var Exitdtheta2dtList = [];
* var ExitDragForceList = [];
* var ExitcList = [];
* var ExitAirDensityList = [];
* var ExitPatmList = [];
* var ExitTatmList = [];
* var EntercDList = [];
* var Enterdr2dtList = [];
* var Enterdtheta2dtList = [];
* var EnterDragForceList = [];
* var EnterAirDensityList = [];
* var EnterPatmList = [];
* var EnterTatmList = [];
* var EntercList = [];
* // var TotalDistanceList = [];
* var TimeList = [];
* var dtheta2dt, ArcLength, dr2dt, WeightForce, DragForce, Thrust, cD, M, c, AirDensity, Patm, Tatm;
*
* var AngleCoefficient = _Bisection(FuelArea1, FuelArea2, FuelMass, FuelVolume, RocketArea, Altitude, RocketCasingMass1, RocketCasingMass2, RocketCasingMass3, NozzleAltitude1, drdt, dthetadt, Distance, ArcDistance, MassIn, ArcLength, GoalDistance);
*
* while (FuelMass / FuelDensity / FuelVolume > 0.4 && Altitude >= 0) {
* var iterationFunOutput = _IterationFun(FuelArea1, FuelMass, RocketArea, Altitude, RocketCasingMass1, NozzleAltitude1, drdt, dthetadt, Distance, ArcDistance, MassIn, AngleCoefficient);
* FuelMass = iterationFunOutput[0];
* RocketMass = iterationFunOutput[1];
* Tatm = iterationFunOutput[2];
* Patm = iterationFunOutput[3];
* AirDensity = iterationFunOutput[4];
* c = iterationFunOutput[5];
* M = iterationFunOutput[6];
* cD = iterationFunOutput[7];
* Thrust = iterationFunOutput[8];
* DragForce = iterationFunOutput[9];
* WeightForce = iterationFunOutput[10];
* dr2dt = iterationFunOutput[11];
* drdt = iterationFunOutput[12];
* Altitude = iterationFunOutput[13];
* Distance = iterationFunOutput[14];
* // ArcVelocity = iterationFunOutput[15];
* ArcDistance = iterationFunOutput[16];
* dtheta2dt = iterationFunOutput[17];
* dthetadt = iterationFunOutput[18];
* var NozzleAltitude2 = Altitude;
*
* AdjacentList.push(Math.cos(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* OppositeList.push(Math.sin(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* WeightForceList.push(WeightForce / RocketMass);
* ThrustList.push(Thrust / 1000);
* MList.push(M);
* AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
* DistanceList.push(Distance / 1000);
* ArcDistanceList.push(ArcDistance / 1000);
* for (i = 0; i < EstDistanceList.length; i++) {
* if (EstDistanceList[i] <= Distance / 1000 && !(EstDistanceList[i + 1] <= Distance / 1000)) {
* LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
* LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
* // if (!CurrentTime) console.log(t + 's - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Dist: ' + EstDistanceList[i].toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* // if (CurrentTime) console.log(new Date(t) + ' - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* break;
* }
* }
* drdtList.push(drdt);
* dthetadtList.push(dthetadt);
* var hListSum;
* for (i = 0; i < hList.length; i++) {
* hListSum += hList[i];
* }
* hList.push(h + hListSum);
* Exitdr2dtList.push(dr2dt);
* Exitdtheta2dtList.push(dtheta2dt);
* if (Altitude < 120000) ExitDragForceList.push(DragForce / 1000);
* if (Altitude < 100000) ExitcList.push(c);
* if (Altitude < 120000) ExitAirDensityList.push(AirDensity);
* if (Altitude < 120000) ExitPatmList.push(Patm / 101325);
* if (Altitude < 100000) ExitTatmList.push(Tatm);
* if (Altitude < 100000) ExitcDList.push(cD);
* if (FuelMass > 0) FuelMassList.push(FuelMass);
* TimeList.push(t);
* t += 1;
* }
* // var FirstStageTime = t;
*
* while (FuelMass / FuelDensity / FuelVolume > 0.19 && Altitude >= 0) {
* iterationFunOutput = _IterationFun(FuelArea1, FuelMass, RocketArea, Altitude, RocketCasingMass2, NozzleAltitude2, drdt, dthetadt, Distance, ArcDistance, MassIn, AngleCoefficient);
* FuelMass = iterationFunOutput[0];
* RocketMass = iterationFunOutput[1];
* Tatm = iterationFunOutput[2];
* Patm = iterationFunOutput[3];
* AirDensity = iterationFunOutput[4];
* c = iterationFunOutput[5];
* M = iterationFunOutput[6];
* cD = iterationFunOutput[7];
* Thrust = iterationFunOutput[8];
* DragForce = iterationFunOutput[9];
* WeightForce = iterationFunOutput[10];
* dr2dt = iterationFunOutput[11];
* drdt = iterationFunOutput[12];
* Altitude = iterationFunOutput[13];
* Distance = iterationFunOutput[14];
* // ArcVelocity = iterationFunOutput[15];
* ArcDistance = iterationFunOutput[16];
* dtheta2dt = iterationFunOutput[17];
* dthetadt = iterationFunOutput[18];
* var NozzleAltitude3 = Altitude;
*
* AdjacentList.push(Math.cos(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* OppositeList.push(Math.sin(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* WeightForceList.push(WeightForce / RocketMass);
* ThrustList.push(Thrust / 1000);
* MList.push(M);
* AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
* DistanceList.push(Distance / 1000);
* ArcDistanceList.push(ArcDistance / 1000);
* for (i = 0; i < EstDistanceList.length; i++) {
* if (EstDistanceList[i] <= Distance / 1000 && !(EstDistanceList[i + 1] <= Distance / 1000)) {
* LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
* LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
* // if (!CurrentTime) console.log(t + 's - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Dist: ' + EstDistanceList[i].toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* // if (CurrentTime) console.log(new Date(t) + ' - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* break;
* }
* }
* drdtList.push(drdt);
* dthetadtList.push(dthetadt);
* hListSum;
* for (i = 0; i < hList.length; i++) {
* hListSum += hList[i];
* }
* hList.push(h + hListSum);
* Exitdr2dtList.push(dr2dt);
* Exitdtheta2dtList.push(dtheta2dt);
* if (Altitude < 120000) ExitDragForceList.push(DragForce / 1000);
* if (Altitude < 100000) ExitcList.push(c);
* if (Altitude < 120000) ExitAirDensityList.push(AirDensity);
* if (Altitude < 120000) ExitPatmList.push(Patm / 101325);
* if (Altitude < 100000) ExitTatmList.push(Tatm);
* if (Altitude < 100000) ExitcDList.push(cD);
* if (FuelMass > 0) FuelMassList.push(FuelMass);
* TimeList.push(t);
* t += 1;
* }
* // var SecondStageTime = t;
*
* while (FuelMass / FuelDensity / FuelVolume > 0 && Altitude >= 0) {
* iterationFunOutput = _IterationFun(FuelArea2, FuelMass, RocketArea, Altitude, RocketCasingMass3, NozzleAltitude3, drdt, dthetadt, Distance, ArcDistance, MassIn, AngleCoefficient);
* FuelMass = iterationFunOutput[0];
* RocketMass = iterationFunOutput[1];
* Tatm = iterationFunOutput[2];
* Patm = iterationFunOutput[3];
* AirDensity = iterationFunOutput[4];
* c = iterationFunOutput[5];
* M = iterationFunOutput[6];
* cD = iterationFunOutput[7];
* Thrust = iterationFunOutput[8];
* DragForce = iterationFunOutput[9];
* WeightForce = iterationFunOutput[10];
* dr2dt = iterationFunOutput[11];
* drdt = iterationFunOutput[12];
* Altitude = iterationFunOutput[13];
* Distance = iterationFunOutput[14];
* // ArcVelocity = iterationFunOutput[15];
* ArcDistance = iterationFunOutput[16];
* dtheta2dt = iterationFunOutput[17];
* dthetadt = iterationFunOutput[18];
*
* AdjacentList.push(Math.cos(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* OppositeList.push(Math.sin(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* WeightForceList.push(WeightForce / RocketMass);
* ThrustList.push(Thrust / 1000);
* MList.push(M);
* AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
* DistanceList.push(Distance / 1000);
* ArcDistanceList.push(ArcDistance / 1000);
* for (i = 0; i < EstDistanceList.length; i++) {
* if (EstDistanceList[i] <= Distance / 1000 && !(EstDistanceList[i + 1] <= Distance / 1000)) {
* LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
* LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
* // if (!CurrentTime) console.log(t + 's - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Dist: ' + EstDistanceList[i].toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* // if (CurrentTime) console.log(new Date(t) + ' - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* break;
* }
* }
* drdtList.push(drdt);
* dthetadtList.push(dthetadt);
* hListSum;
* for (i = 0; i < hList.length; i++) {
* hListSum += hList[i];
* }
* hList.push(h + hListSum);
* Exitdr2dtList.push(dr2dt);
* Exitdtheta2dtList.push(dtheta2dt);
* if (Altitude < 120000) ExitDragForceList.push(DragForce / 1000);
* if (Altitude < 100000) ExitcList.push(c);
* if (Altitude < 120000) ExitAirDensityList.push(AirDensity);
* if (Altitude < 120000) ExitPatmList.push(Patm / 101325);
* if (Altitude < 100000) ExitTatmList.push(Tatm);
* if (Altitude < 100000) ExitcDList.push(cD);
* if (FuelMass > 0) FuelMassList.push(FuelMass);
* TimeList.push(t);
* t += 1;
* }
* // var ThirdStageTime = t;
*
* while (Altitude > 0) {
* FuelMass = 0;
* iterationFunOutput = _IterationFun(FuelArea2, FuelMass, RocketArea, Altitude, RocketCasingMass3, NozzleAltitude3, drdt, dthetadt, Distance, ArcDistance, MassIn, AngleCoefficient);
* FuelMass = iterationFunOutput[0];
* RocketMass = iterationFunOutput[1];
* Tatm = iterationFunOutput[2];
* Patm = iterationFunOutput[3];
* AirDensity = iterationFunOutput[4];
* c = iterationFunOutput[5];
* M = iterationFunOutput[6];
* cD = iterationFunOutput[7];
* Thrust = iterationFunOutput[8];
* DragForce = iterationFunOutput[9];
* WeightForce = iterationFunOutput[10];
* dr2dt = iterationFunOutput[11];
* drdt = iterationFunOutput[12];
* Altitude = iterationFunOutput[13];
* Distance = iterationFunOutput[14];
* // ArcVelocity = iterationFunOutput[15];
* ArcDistance = iterationFunOutput[16];
* dtheta2dt = iterationFunOutput[17];
* dthetadt = iterationFunOutput[18];
* AdjacentList.push(Math.cos(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* OppositeList.push(Math.sin(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* WeightForceList.push(WeightForce / RocketMass);
* MList.push(M);
* AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
* DistanceList.push(Distance / 1000);
* ArcDistanceList.push(ArcDistance / 1000);
* for (i = 0; i < EstDistanceList.length; i++) {
* if (EstDistanceList[i] <= Distance / 1000 && !(EstDistanceList[i + 1] <= Distance / 1000)) {
* LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
* LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
* // if (!CurrentTime) console.log(t + 's - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Dist: ' + EstDistanceList[i].toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* // if (CurrentTime) console.log(new Date(t) + ' - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* break;
* }
* }
* drdtList.push(drdt);
* dthetadtList.push(dthetadt);
* if (Altitude < 120000) EnterDragForceList.push(DragForce / 1000);
* if (Altitude < 120000) EntercList.push(c);
* if (Altitude < 120000) EnterAirDensityList.push(AirDensity);
* if (Altitude < 120000) EnterPatmList.push(Patm / 101325);
* if (Altitude < 120000) EnterTatmList.push(Tatm);
* if (Altitude < 120000) Enterdr2dtList.push(dr2dt);
* if (Altitude < 120000) Enterdtheta2dtList.push(dtheta2dt);
* if (Altitude < 120000) EntercDList.push(cD);
* TimeList.push(t);
* t += 1;
* }
* // var impactTime = t;
*
* // This will find the max acceleration, max velocity, and max height out of their lists
* // var MaxVerticalAcceleration = Exitdr2dtList.reduce(function (a, b) {
* // return Math.max(a, b);
* // });
* // var MaxAngularAcceleration = Exitdtheta2dtList.reduce(function (a, b) {
* // return Math.max(a, b);
* // });
* // var MaxVerticalVelocity = drdtList.reduce(function (a, b) {
* // return Math.max(a, b);
* // });
* // var MaxAngularVelocity = dthetadtList.reduce(function (a, b) {
* // return Math.max(a, b);
* // });
* var MaxAltitude = AltitudeList.reduce(function (a, b) {
* return Math.max(a, b);
* });
*
* console.log(`Max Altitude ${MaxAltitude}`);
* console.log(AltitudeList);
* console.log(`Required Altitude ${minAltitude}`);
* if (MaxAltitude < minAltitude) {
* missileManager.lastMissileErrorType = ToastMsgType.critical;
* missileManager.lastMissileError = `Failed Min Altitude Check! Max Altitude ${MaxAltitude} km.`;
* return -1;
* }
*
* console.log(CurrentTime);
*
* for (i = 0; i < AltitudeList.length; i++) {
* if (AltitudeList[i] === MaxAltitude) var MaxAltitudePossition = i;
* }
* console.log(`Time Until Max Altitude: ${MaxAltitudePossition}`);
* return MaxAltitudePossition; // Time Until Max Altitude
*
* // for (i = 0; i < drdtList.length; i++) {
* // if (drdtList[i] === MaxVerticalVelocity) var MaxVerticalVelocityPossition = i;
* // }
* // var AverageAngularVelocity = 0;
* // for (i = 0; i < dthetadtList.length; i++) {
* // if (dthetadtList[i] === MaxAngularVelocity) var MaxAngularVelocityPossition = i;
* // AverageAngularVelocity += dthetadtList[i];
* // }
* // for (i = 0; i < Exitdr2dtList.length; i++) {
* // if (Exitdr2dtList[i] === MaxVerticalAcceleration) var MaxVerticalAccelerationPossition = i;
* // }
* // for (i = 0; i < Exitdtheta2dtList.length; i++) {
* // if (Exitdtheta2dtList[i] === MaxAngularAcceleration) var MaxAngularAccelerationPossition = i;
* // }
*
* // if (MissileObject) {
* // MissileObject.static = false;
* // MissileObject.altList = AltitudeList;
* // MissileObject.latList = LatList;
* // MissileObject.lonList = LongList;
* // // MissileObject.timeList = TimeList;
* // MissileObject.active = true;
* // MissileObject.missile = true;
* // MissileObject.type = '';
* // MissileObject.id = MissileObjectNum;
* // MissileObject.ON = 'RV_' + MissileObject.id;
* // MissileObject.satId = MissileObjectNum;
* // MissileObject.maxAlt = MaxAltitude;
* // MissileObject.startTime = CurrentTime;
* // if (country) MissileObject.C = country;
*
* // if (MissileObject.apogee) delete MissileObject.apogee;
* // if (MissileObject.argOfPerigee) delete MissileObject.argOfPerigee;
* // if (MissileObject.eccentricity) delete MissileObject.eccentricity;
* // if (MissileObject.inclination) delete MissileObject.inclination;
* // // maxAlt is used for zoom controls
* // // if (MissileObject.maxAlt) delete MissileObject.maxAlt;
* // if (MissileObject.meanMotion) delete MissileObject.meanMotion;
* // if (MissileObject.perigee) delete MissileObject.perigee;
* // if (MissileObject.period) delete MissileObject.period;
* // if (MissileObject.raan) delete MissileObject.raan;
* // if (MissileObject.semiMajorAxis) delete MissileObject.semiMajorAxis;
* // if (MissileObject.semiMinorAxis) delete MissileObject.semiMinorAxis;
*
* // if (MissileDesc) MissileObject.desc = MissileDesc;
* // // console.log(MissileObject);
* // missileArray.push(MissileObject);
* // catalogManagerInstance.satCruncher.postMessage({
* // id: MissileObject.id,
* // typ: CruncerMessageTypes.NEW_MISSILE,
* // ON: 'RV_' + MissileObject.id, // Don't think catalogManagerInstance.satCruncher needs this
* // satId: MissileObject.id,
* // static: MissileObject.static,
* // missile: MissileObject.missile,
* // active: MissileObject.active,
* // type: MissileObject.type,
* // name: MissileObject.id,
* // latList: MissileObject.latList,
* // lonList: MissileObject.lonList,
* // altList: MissileObject.altList,
* // startTime: MissileObject.startTime,
* // });
* // updateOrbitBuffer(MissileObjectNum, MissileObject.latList, MissileObject.lonList, MissileObject.altList, MissileObject.startTime);
*
* // missileManager.missileArray = missileArray;
*
* // // if (MissileObject.latList) delete MissileObject.latList;
* // // if (MissileObject.lonList) delete MissileObject.lonList;
* // // if (MissileObject.altList) delete MissileObject.altList;
* // // if (MissileObject.startTime) delete MissileObject.startTime;
* // }
* // missileManager.missilesInUse++;
* // missileManager.lastMissileErrorType = 'normal';
* // missileManager.lastMissileError = 'Missile Named RV_' + MissileObject.id + '<br>has been created.';
* // return 1; // Successful Launch
*};
*missileManager.asatFlight = function (
* CurrentLatitude,
* CurrentLongitude,
* TargetLatitude,
* TargetLongitude,
* targetAltitude,
* NumberWarheads,
* MissileObjectNum,
* CurrentTime,
* MissileDesc,
* Length,
* Diameter,
* NewBurnRate,
* MaxMissileRange,
* country,
* timeInFlight,
* AngleCoefficient
*) {
* // This is the main function for this program. It calculates and designs the flight path of an intercontinental
* // ballistic missile (ICBM). This function calls upon many sub-functions to help it iteratively calculate many of the
* // changing variables as the rocket makes its path around the world. Changing variables that had to be taken into
* // account include:
* // Air density vs altitude
* // Air pressure vs altitude
* // Air temperature vs altitude
* // Drag coefficient vs mach number
* // Speed of sound vs altitude
* // Drag force vs time
* // Gravitational attraction vs altitude
* // Fuel mass vs time
* // Thrust vs time
* // Vertical velocity vs time
* // Angular velocity vs time
* // Vertical acceleration vs time
* // Angular acceleration vs time
* // Angular distance rocket travels vs time
* // Total distance rocket travels vs time
* // Many of these variables are dependent on each other. The inputs of this function are:
* // Currentlat: Latitude of the starting position
* // Currentlon: Longitude of the starting position
* // Targetlat: Latitude of the ending position
* // Targetlon: Longitude of the ending position
* // NumberWarheads: Number of warhead loaded onto the missile
* // The coordinates are to be inputed as degrees and NumberWarheads must be an intagure. The first thing the
* // program does is calculate everything regarding the path the rocket will take to minimize
* // distance needed to travel. It uses the CoordinateCalculator function to accomplish this.
* // It then calculates everything regarding the casing and fuel of the rocket. After calculating all
* // the necessary constants it starts its iterative calculation of the rockets actual path and collects
* // information into lists as it moves through its times steps. It changes its iterative approach once
* // the rocket runs out of fuel by dropping out everything used to calculate the trust. Once the rocket
* // reaches an altitude of zero meters it ends the iterations. Using all the information gathers it
* // presents them in the form of print statements and also plots.
*
* var MissileObject = getSat(MissileObjectNum);
*
* // Dimensions of the rocket
* Length = Length || 17; // (m)
* Diameter = Diameter || 3.1; // (m)
*
* if (CurrentLatitude > 90 || CurrentLatitude < -90) {
* console.debug('Error: Current Latitude must be between 90 and -90 degrees');
* return 0;
* }
* if (CurrentLongitude > 180 || CurrentLongitude < -180) {
* console.debug('Error: Current Longitude must be between 180 and -180 degrees');
* return 0;
* }
* if (TargetLatitude > 90 || TargetLatitude < -90) {
* // console.debug('Error: Target Latitude must be between 90 and -90 degrees');
* missileManager.lastMissileErrorType = ToastMsgType.critical;
* missileManager.lastMissileError = 'Error: Target Latitude must be<br>between 90 and -90 degrees';
* return 0;
* }
* if (TargetLongitude > 180 || TargetLongitude < -180) {
* // console.debug('Error: Target Longitude must be between 180 and -180 degrees');
* console.log(TargetLongitude);
* missileManager.lastMissileErrorType = ToastMsgType.critical;
* missileManager.lastMissileError = 'Error: Target Longitude must be<br>between 180 and -180 degrees';
* return 0;
* }
* if (NumberWarheads > 12) {
* console.debug('Error: Rocket can hold up to 12 warheads');
* return 0;
* }
* if (parseFloat(NumberWarheads) % 1 > 0) {
* console.debug('Error: The number of warheads must be a whole number');
* return 0;
* }
*
* var minAltitude = 0;
*
* EarthRadius = 6371000; // (m)
* R = 287; // (J * K^-1 * kg^-1)
* G = 6.67384 * Math.pow(10, -11); // (m^3 * kg^-1 * s^-2)
* EarthMass = 5.9726 * Math.pow(10, 24); // (kg)
*
* // This function will calculate the path the rocket will take in terms of coordinates
* // var GoalDistance;
* var EstDistanceList = [];
* var LatList = [];
* var LongList = [];
* var EstLatList = [];
* var EstLongList = [];
* // var Alpha1;
*
* var calculatedCoordinates = [];
*
* calculatedCoordinates = _CoordinateCalculator(CurrentLatitude, CurrentLongitude, TargetLatitude, TargetLongitude);
* EstLatList = calculatedCoordinates[0];
* EstLongList = calculatedCoordinates[1];
* // Alpha1 = calculatedCoordinates[2];
* ArcLength = calculatedCoordinates[3];
* EstDistanceList = calculatedCoordinates[4];
* // GoalDistance = calculatedCoordinates[5];
*
* // if (ArcLength < 320000) {
* // // console.debug('Error: This missile has a minimum distance of 320 km.');
* // // console.debug('Please choose different target coordinates.');
* // missileManager.lastMissileError = 'Error: This missile has a minimum distance of 320 km.';
* // return 0;
* // }
*
* if (ArcLength > MaxMissileRange * 1000) {
* // console.debug('Error: This missile has a maximum distance of ' + MaxMissileRange + ' km.');
* // console.debug('Please choose different target coordinates.');
* missileManager.lastMissileErrorType = ToastMsgType.critical;
* missileManager.lastMissileError = 'Error: This missile has a maximum distance of ' + MaxMissileRange + ' km.';
* return 0;
* }
*
* // Calculations for the warheads
* WarheadMass = 500 * NumberWarheads; // (Kg)
* // var WarheadPayload = 475 * NumberWarheads; // (KiloTons of TNT)
* // var TotalDestruction = 92.721574 * NumberWarheads; // (km^2)
* // var PartialDestruction = 261.5888 * NumberWarheads; // (km^2)
*
* // Calculations for the casing
* var Thickness = 0.050389573 * Diameter; // (m)
* var RocketArea = 0.25 * Math.PI * Math.pow(Diameter, 2); // (m^2)
* // var RocketVolume = RocketArea * Length; // (m^3)
* var RocketCasingDensity = 1628.75; // (kg/m^3)http://scholar.lib.vt.edu/theses/available/etd-101198-161441/unrestricted/appendix.pdf
* var RocketCasingVolume = 0.25 * Math.PI * Length * (Math.pow(Diameter, 2) - Math.pow(Diameter - Thickness, 2)); // (m^3)
* var RocketCasingMass1 = RocketCasingDensity * RocketCasingVolume; // (kg)
* var RocketCasingMass2 = RocketCasingDensity * 0.25 * Math.PI * (Length * 0.4937) * (Math.pow(Diameter, 2) - Math.pow(Diameter - Thickness, 2)); // (kg)
* var RocketCasingMass3 = RocketCasingDensity * 0.25 * Math.PI * (Length * 0.157) * (Math.pow(Diameter * 0.75, 2) - (Diameter * 0.75 - Math.pow(Thickness / 2), 2)); // (kg)
*
* // Calculations for the fuel
* BurnRate = NewBurnRate || 0.042; // (m/s)
* FuelDensity = 1750; // (kg/m^2)
* var FuelArea1 = 0.25 * Math.PI * Math.pow(Diameter - Thickness, 2); // (m^2)
* var FuelArea2 = 0.25 * Math.PI * Math.pow(Diameter * 0.75 - Thickness, 2); // (m^2)
* var FuelVolume = FuelArea1 * (Length * 0.651) + FuelArea2 * (Length * 0.178); // (m^3)
* var FuelMass = FuelDensity * FuelVolume; // http://www.lr.tudelft.nl/en/organisation/departments/space-engineering/space-systems-engineering/expertise-areas/space-propulsion/design-of-elements/rocket-propellants/solids/
* var RocketMass = FuelMass + RocketCasingMass1 + WarheadMass; // (kg)
*
* // Here are the initial conditions
* var dthetadt = 0.001; // (m/s)
* var drdt = 0.001; // (m/s)
* var Altitude = 0; // (m)
* var NozzleAltitude1 = 0; // (m)
* var Distance = 0; // (m)
* var ArcDistance = 0; // (m)
* var MassIn = 0; // (kg/s)
*
* // Here are the time steps and counters
* // var y = 0;
* // var z = 0;
* var t = 0;
* h = 1;
*
* // Here are the definitions for all the lists
* var OppositeList = [];
* var AdjacentList = [];
* var WeightForceList = [];
* var AltitudeList = [];
* var DistanceList = [];
* var ArcDistanceList = [];
* var drdtList = [];
* var dthetadtList = [];
* var MList = [];
* var FuelMassList = [];
* var hList = [];
* var ThrustList = [];
* var NozzleAltitude = [];
* for (var i = 0; i < 100000; i++) {
* NozzleAltitude.push(i);
* }
* var ExitcDList = [];
* var Exitdr2dtList = [];
* var Exitdtheta2dtList = [];
* var ExitDragForceList = [];
* var ExitcList = [];
* var ExitAirDensityList = [];
* var ExitPatmList = [];
* var ExitTatmList = [];
* var EntercDList = [];
* var Enterdr2dtList = [];
* var Enterdtheta2dtList = [];
* var EnterDragForceList = [];
* var EnterAirDensityList = [];
* var EnterPatmList = [];
* var EnterTatmList = [];
* var EntercList = [];
* // var TotalDistanceList = [];
* var TimeList = [];
* var dtheta2dt, ArcLength, dr2dt, WeightForce, DragForce, Thrust, cD, M, c, AirDensity, Patm, Tatm;
*
* // var AngleCoefficient = _Bisection(FuelArea1, FuelArea2, FuelMass, FuelVolume, RocketArea, Altitude, RocketCasingMass1, RocketCasingMass2, RocketCasingMass3, NozzleAltitude1, drdt, dthetadt, Distance, ArcDistance, MassIn, ArcLength, GoalDistance);
* // console.log(AngleCoefficient);
*
* while (FuelMass / FuelDensity / FuelVolume > 0.4 && Altitude >= 0) {
* var iterationFunOutput = _IterationFun(FuelArea1, FuelMass, RocketArea, Altitude, RocketCasingMass1, NozzleAltitude1, drdt, dthetadt, Distance, ArcDistance, MassIn, AngleCoefficient);
* FuelMass = iterationFunOutput[0];
* RocketMass = iterationFunOutput[1];
* Tatm = iterationFunOutput[2];
* Patm = iterationFunOutput[3];
* AirDensity = iterationFunOutput[4];
* c = iterationFunOutput[5];
* M = iterationFunOutput[6];
* cD = iterationFunOutput[7];
* Thrust = iterationFunOutput[8];
* DragForce = iterationFunOutput[9];
* WeightForce = iterationFunOutput[10];
* dr2dt = iterationFunOutput[11];
* drdt = iterationFunOutput[12];
* Altitude = iterationFunOutput[13];
* Distance = iterationFunOutput[14];
* // ArcVelocity = iterationFunOutput[15];
* ArcDistance = iterationFunOutput[16];
* dtheta2dt = iterationFunOutput[17];
* dthetadt = iterationFunOutput[18];
* var NozzleAltitude2 = Altitude;
*
* AdjacentList.push(Math.cos(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* OppositeList.push(Math.sin(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* WeightForceList.push(WeightForce / RocketMass);
* ThrustList.push(Thrust / 1000);
* MList.push(M);
* AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
* DistanceList.push(Distance / 1000);
* ArcDistanceList.push(ArcDistance / 1000);
* for (i = 0; i < EstDistanceList.length; i++) {
* if (EstDistanceList[i] <= Distance / 1000 && !(EstDistanceList[i + 1] <= Distance / 1000)) {
* LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
* LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
* // if (!CurrentTime) console.log(t + 's - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Dist: ' + EstDistanceList[i].toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* // if (CurrentTime) console.log(new Date(t) + ' - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* break;
* }
* }
* drdtList.push(drdt);
* dthetadtList.push(dthetadt);
* var hListSum;
* for (i = 0; i < hList.length; i++) {
* hListSum += hList[i];
* }
* hList.push(h + hListSum);
* Exitdr2dtList.push(dr2dt);
* Exitdtheta2dtList.push(dtheta2dt);
* if (Altitude < 120000) ExitDragForceList.push(DragForce / 1000);
* if (Altitude < 100000) ExitcList.push(c);
* if (Altitude < 120000) ExitAirDensityList.push(AirDensity);
* if (Altitude < 120000) ExitPatmList.push(Patm / 101325);
* if (Altitude < 100000) ExitTatmList.push(Tatm);
* if (Altitude < 100000) ExitcDList.push(cD);
* if (FuelMass > 0) FuelMassList.push(FuelMass);
* TimeList.push(t);
* t += 1;
* }
* // var FirstStageTime = t;
*
* while (FuelMass / FuelDensity / FuelVolume > 0.19 && Altitude >= 0) {
* iterationFunOutput = _IterationFun(FuelArea1, FuelMass, RocketArea, Altitude, RocketCasingMass2, NozzleAltitude2, drdt, dthetadt, Distance, ArcDistance, MassIn, AngleCoefficient);
* FuelMass = iterationFunOutput[0];
* RocketMass = iterationFunOutput[1];
* Tatm = iterationFunOutput[2];
* Patm = iterationFunOutput[3];
* AirDensity = iterationFunOutput[4];
* c = iterationFunOutput[5];
* M = iterationFunOutput[6];
* cD = iterationFunOutput[7];
* Thrust = iterationFunOutput[8];
* DragForce = iterationFunOutput[9];
* WeightForce = iterationFunOutput[10];
* dr2dt = iterationFunOutput[11];
* drdt = iterationFunOutput[12];
* Altitude = iterationFunOutput[13];
* Distance = iterationFunOutput[14];
* // ArcVelocity = iterationFunOutput[15];
* ArcDistance = iterationFunOutput[16];
* dtheta2dt = iterationFunOutput[17];
* dthetadt = iterationFunOutput[18];
* var NozzleAltitude3 = Altitude;
*
* AdjacentList.push(Math.cos(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* OppositeList.push(Math.sin(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* WeightForceList.push(WeightForce / RocketMass);
* ThrustList.push(Thrust / 1000);
* MList.push(M);
* AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
* DistanceList.push(Distance / 1000);
* ArcDistanceList.push(ArcDistance / 1000);
* for (i = 0; i < EstDistanceList.length; i++) {
* if (EstDistanceList[i] <= Distance / 1000 && !(EstDistanceList[i + 1] <= Distance / 1000)) {
* LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
* LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
* // if (!CurrentTime) console.log(t + 's - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Dist: ' + EstDistanceList[i].toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* // if (CurrentTime) console.log(new Date(t) + ' - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* break;
* }
* }
* drdtList.push(drdt);
* dthetadtList.push(dthetadt);
* hListSum;
* for (i = 0; i < hList.length; i++) {
* hListSum += hList[i];
* }
* hList.push(h + hListSum);
* Exitdr2dtList.push(dr2dt);
* Exitdtheta2dtList.push(dtheta2dt);
* if (Altitude < 120000) ExitDragForceList.push(DragForce / 1000);
* if (Altitude < 100000) ExitcList.push(c);
* if (Altitude < 120000) ExitAirDensityList.push(AirDensity);
* if (Altitude < 120000) ExitPatmList.push(Patm / 101325);
* if (Altitude < 100000) ExitTatmList.push(Tatm);
* if (Altitude < 100000) ExitcDList.push(cD);
* if (FuelMass > 0) FuelMassList.push(FuelMass);
* TimeList.push(t);
* t += 1;
* }
* // var SecondStageTime = t;
*
* while (FuelMass / FuelDensity / FuelVolume > 0 && Altitude >= 0) {
* iterationFunOutput = _IterationFun(FuelArea2, FuelMass, RocketArea, Altitude, RocketCasingMass3, NozzleAltitude3, drdt, dthetadt, Distance, ArcDistance, MassIn, AngleCoefficient);
* FuelMass = iterationFunOutput[0];
* RocketMass = iterationFunOutput[1];
* Tatm = iterationFunOutput[2];
* Patm = iterationFunOutput[3];
* AirDensity = iterationFunOutput[4];
* c = iterationFunOutput[5];
* M = iterationFunOutput[6];
* cD = iterationFunOutput[7];
* Thrust = iterationFunOutput[8];
* DragForce = iterationFunOutput[9];
* WeightForce = iterationFunOutput[10];
* dr2dt = iterationFunOutput[11];
* drdt = iterationFunOutput[12];
* Altitude = iterationFunOutput[13];
* Distance = iterationFunOutput[14];
* // ArcVelocity = iterationFunOutput[15];
* ArcDistance = iterationFunOutput[16];
* dtheta2dt = iterationFunOutput[17];
* dthetadt = iterationFunOutput[18];
*
* AdjacentList.push(Math.cos(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* OppositeList.push(Math.sin(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* WeightForceList.push(WeightForce / RocketMass);
* ThrustList.push(Thrust / 1000);
* MList.push(M);
* AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
* DistanceList.push(Distance / 1000);
* ArcDistanceList.push(ArcDistance / 1000);
* for (i = 0; i < EstDistanceList.length; i++) {
* if (EstDistanceList[i] <= Distance / 1000 && !(EstDistanceList[i + 1] <= Distance / 1000)) {
* LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
* LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
* // if (!CurrentTime) console.log(t + 's - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Dist: ' + EstDistanceList[i].toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* // if (CurrentTime) console.log(new Date(t) + ' - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* break;
* }
* }
* drdtList.push(drdt);
* dthetadtList.push(dthetadt);
* hListSum;
* for (i = 0; i < hList.length; i++) {
* hListSum += hList[i];
* }
* hList.push(h + hListSum);
* Exitdr2dtList.push(dr2dt);
* Exitdtheta2dtList.push(dtheta2dt);
* if (Altitude < 120000) ExitDragForceList.push(DragForce / 1000);
* if (Altitude < 100000) ExitcList.push(c);
* if (Altitude < 120000) ExitAirDensityList.push(AirDensity);
* if (Altitude < 120000) ExitPatmList.push(Patm / 101325);
* if (Altitude < 100000) ExitTatmList.push(Tatm);
* if (Altitude < 100000) ExitcDList.push(cD);
* if (FuelMass > 0) FuelMassList.push(FuelMass);
* TimeList.push(t);
* t += 1;
* }
* // var ThirdStageTime = t;
*
* while (Altitude / 1000 <= targetAltitude) {
* // while (Altitude > 0) {
* FuelMass = 0;
* iterationFunOutput = _IterationFun(FuelArea2, FuelMass, RocketArea, Altitude, RocketCasingMass3, NozzleAltitude3, drdt, dthetadt, Distance, ArcDistance, MassIn, AngleCoefficient);
* FuelMass = iterationFunOutput[0];
* RocketMass = iterationFunOutput[1];
* Tatm = iterationFunOutput[2];
* Patm = iterationFunOutput[3];
* AirDensity = iterationFunOutput[4];
* c = iterationFunOutput[5];
* M = iterationFunOutput[6];
* cD = iterationFunOutput[7];
* Thrust = iterationFunOutput[8];
* DragForce = iterationFunOutput[9];
* WeightForce = iterationFunOutput[10];
* dr2dt = iterationFunOutput[11];
* drdt = iterationFunOutput[12];
* Altitude = iterationFunOutput[13];
* Distance = iterationFunOutput[14];
* // ArcVelocity = iterationFunOutput[15];
* ArcDistance = iterationFunOutput[16];
* dtheta2dt = iterationFunOutput[17];
* dthetadt = iterationFunOutput[18];
* AdjacentList.push(Math.cos(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* OppositeList.push(Math.sin(ArcDistance / EarthRadius) * (Altitude + EarthRadius));
* WeightForceList.push(WeightForce / RocketMass);
* MList.push(M);
* AltitudeList.push(Math.round((Altitude / 1000) * 1e2) / 1e2);
* DistanceList.push(Distance / 1000);
* ArcDistanceList.push(ArcDistance / 1000);
* for (i = 0; i < EstDistanceList.length; i++) {
* if (EstDistanceList[i] <= Distance / 1000 && !(EstDistanceList[i + 1] <= Distance / 1000)) {
* LatList.push(Math.round(EstLatList[i] * 1e2) / 1e2);
* LongList.push(Math.round(EstLongList[i] * 1e2) / 1e2);
* // if (!CurrentTime) console.log(t + 's - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Dist: ' + EstDistanceList[i].toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* // if (CurrentTime) console.log(new Date(t) + ' - Altitude: ' + (Altitude/1000).toFixed(1) + ' - Lat: ' + EstLatList[i].toFixed(1) + ' - Lon: ' + EstLongList[i].toFixed(1));
* break;
* }
* }
* drdtList.push(drdt);
* dthetadtList.push(dthetadt);
* if (Altitude < 120000) EnterDragForceList.push(DragForce / 1000);
* if (Altitude < 120000) EntercList.push(c);
* if (Altitude < 120000) EnterAirDensityList.push(AirDensity);
* if (Altitude < 120000) EnterPatmList.push(Patm / 101325);
* if (Altitude < 120000) EnterTatmList.push(Tatm);
* if (Altitude < 120000) Enterdr2dtList.push(dr2dt);
* if (Altitude < 120000) Enterdtheta2dtList.push(dtheta2dt);
* if (Altitude < 120000) EntercDList.push(cD);
* TimeList.push(t);
* t += 1;
* }
* // var timeInFlight = t;
*
* // This will find the max acceleration, max velocity, and max height out of their lists
* // var MaxVerticalAcceleration = Exitdr2dtList.reduce(function (a, b) {
* // return Math.max(a, b);
* // });
* // var MaxAngularAcceleration = Exitdtheta2dtList.reduce(function (a, b) {
* // return Math.max(a, b);
* // });
* // var MaxVerticalVelocity = drdtList.reduce(function (a, b) {
* // return Math.max(a, b);
* // });
* // var MaxAngularVelocity = dthetadtList.reduce(function (a, b) {
* // return Math.max(a, b);
* // });
* var MaxAltitude = AltitudeList.reduce(function (a, b) {
* return Math.max(a, b);
* });
*
* // console.log(MaxAltitude);
* console.log(CurrentTime);
*
* if (MaxAltitude < minAltitude) {
* // Try again with 25% increase to burn rate
* // let burnMultiplier = Math.min(3, minAltitude / MaxAltitude);
* // setTimeout(function () {
* missileManager.asatFlight(CurrentLatitude, CurrentLongitude, TargetLatitude, TargetLongitude, targetAltitude, NumberWarheads, MissileObjectNum, CurrentTime, MissileDesc, Length, Diameter, NewBurnRate, MaxMissileRange, country);
* // }, 10);
* return 0;
* }
*
* // for (i = 0; i < AltitudeList.length; i++) {
* // if (AltitudeList[i] === MaxAltitude) var MaxAltitudePossition = i;
* // }
* // for (i = 0; i < drdtList.length; i++) {
* // if (drdtList[i] === MaxVerticalVelocity) var MaxVerticalVelocityPossition = i;
* // }
* // var AverageAngularVelocity = 0;
* // for (i = 0; i < dthetadtList.length; i++) {
* // if (dthetadtList[i] === MaxAngularVelocity) var MaxAngularVelocityPossition = i;
* // AverageAngularVelocity += dthetadtList[i];
* // }
* // for (i = 0; i < Exitdr2dtList.length; i++) {
* // if (Exitdr2dtList[i] === MaxVerticalAcceleration) var MaxVerticalAccelerationPossition = i;
* // }
* // for (i = 0; i < Exitdtheta2dtList.length; i++) {
* // if (Exitdtheta2dtList[i] === MaxAngularAcceleration) var MaxAngularAccelerationPossition = i;
* // }
*
* // console.log('Max Angular Velocity: ' + MaxAngularVelocity / 1000);
* // console.log('Average Angular Velocity: ' + AverageAngularVelocity / dthetadtList.length / 1000);
*
* // This will print the variables at their max value with its respective time in minutes
* // It takes into acount the difference in the singular and plural form of the words 'minutes' and 'seconds'
*
* // if (CurrentTime) {
* // console.info('First Stage = ' + new Date(FirstStageTime));
* // console.info('Second Stage = ' + new Date(SecondStageTime));
* // console.info('Third Stage = ' + new Date(ThirdStageTime));
* // console.info('Impact Time = ' + new Date(impactTime));
* // } else {
* // console.info('First Stage = ' + FirstStageTime + ' sec (' + FirstStageTime / 60 + ' min)');
* // console.info('Second Stage = ' + SecondStageTime + ' sec (' + SecondStageTime / 60 + ' min)');
* // console.info('Third Stage = ' + ThirdStageTime + ' sec (' + ThirdStageTime / 60 + ' min)');
* // console.info('Impact Time = ' + impactTime + ' sec (' + impactTime / 60 + ' min)');
* // }
* // console.info('ArcDistance = ' + Math.round(ArcDistance / 1000, 2) + 'Km');
* // console.info('Distance to target is' + Math.round(ArcLength / 1000, 2) + 'km');
* // console.info('Direction to target is' + Math.round(Alpha1, 2) + ' degrees from north');
* // console.info('Warhead payload delivered:' + WarheadPayload + 'Kilotons of TNT');
* // console.info('Total Blast area for complete structural destruction:' + Math.round(TotalDestruction, 2) + 'Square Kilometers');
* // console.info('Total Blast area for partial structural destruction:' + Math.round(PartialDestruction, 2) + 'Square Kilometers');
*
* if (MissileObject) {
* MissileObject.static = false;
* MissileObject.altList = AltitudeList;
* MissileObject.latList = LatList;
* MissileObject.lonList = LongList;
* // MissileObject.timeList = TimeList;
* MissileObject.active = true;
* MissileObject.missile = true;
* MissileObject.type = '';
* MissileObject.id = MissileObjectNum;
* MissileObject.ON = 'RV_' + MissileObject.id;
* MissileObject.satId = MissileObjectNum;
* MissileObject.maxAlt = MaxAltitude;
* MissileObject.startTime = CurrentTime;
* if (country) MissileObject.C = country;
*
* if (MissileObject.apogee) delete MissileObject.apogee;
* if (MissileObject.argOfPerigee) delete MissileObject.argOfPerigee;
* if (MissileObject.eccentricity) delete MissileObject.eccentricity;
* if (MissileObject.inclination) delete MissileObject.inclination;
* // maxAlt is used for zoom controls
* // if (MissileObject.maxAlt) delete MissileObject.maxAlt;
* if (MissileObject.meanMotion) delete MissileObject.meanMotion;
* if (MissileObject.perigee) delete MissileObject.perigee;
* if (MissileObject.period) delete MissileObject.period;
* if (MissileObject.raan) delete MissileObject.raan;
* if (MissileObject.semiMajorAxis) delete MissileObject.semiMajorAxis;
* if (MissileObject.semiMinorAxis) delete MissileObject.semiMinorAxis;
*
* if (MissileDesc) MissileObject.desc = MissileDesc;
* // console.log(MissileObject);
* missileArray.push(MissileObject);
* catalogManagerInstance.satCruncher.postMessage({
* id: MissileObject.id,
* typ: CruncerMessageTypes.NEW_MISSILE,
* ON: 'RV_' + MissileObject.id, // Don't think catalogManagerInstance.satCruncher needs this
* satId: MissileObject.id,
* static: MissileObject.static,
* missile: MissileObject.missile,
* active: MissileObject.active,
* type: MissileObject.type,
* name: MissileObject.id,
* latList: MissileObject.latList,
* lonList: MissileObject.lonList,
* altList: MissileObject.altList,
* startTime: MissileObject.startTime,
* });
* updateOrbitBuffer(MissileObjectNum, MissileObject.latList, MissileObject.lonList, MissileObject.altList, MissileObject.startTime);
*
* missileManager.missileArray = missileArray;
*
* // if (MissileObject.latList) delete MissileObject.latList;
* // if (MissileObject.lonList) delete MissileObject.lonList;
* // if (MissileObject.altList) delete MissileObject.altList;
* // if (MissileObject.startTime) delete MissileObject.startTime;
* }
* missileManager.missilesInUse++;
* missileManager.lastMissileErrorType = 'normal';
* missileManager.lastMissileError = 'Missile Named RV_' + MissileObject.id + '<br>has been created.';
* return [timeInFlight, LatList[timeInFlight - 1], LongList[timeInFlight - 1]]; // Successful Launch
*};
*/
// Internal Functions
export const calculatePressure = (Altitude: number) => {
/*
* This function calculates the atmospheric pressure. The only iMathut is the
* Altitude. The constiables in the function are:
*/
/*
* Po: Atmospheric pressure at sea level
* mol: Amount of air in one gram
* Tsea: Temperature at sea level
* r: Gas constant for air
* g: Gravitational constant
*/
// The function will return the calculated atmospheric pressure
const Po = 101325; // (Pa)
const mol = 0.02897; // (mol)
const Tsea = 288; // (K)
const _R = 8.31451; // (J / K mol)
const g = 9.81; // (m/s^2)
return Po * Math.exp((-mol * g * Altitude) / (_R * Tsea)); // (Pa)
};
export const calculateTemperature = (Altitude: number) => {
/*
* This function calculates the atmospheric temperature at any given altitude.
* The function has one iMathut for altitude. Because atmospheric temperature can not
* be represented as one equation, this function is made up of a series of curve fits
* which each make up a section of the atmosphere. After an elevation of 120 km
* the atmosphere becomes so sparse that it become negligible so the function keeps a
* constant temperature after that point.
*/
Altitude /= 1000; // (km)
if (Altitude < 12.5) {
return 276.642857143 - 5.02285714286 * Altitude;
} // (K)
if (Altitude < 20) {
return 213.0;
} // (K)
if (Altitude < 47.5) {
return 171.224358974 + 2.05384615385 * Altitude;
} // (K)
if (Altitude < 52.5) {
return 270.0;
} // (K)
if (Altitude < 80) {
return 435.344405594 - 3.13916083916 * Altitude;
} // (K)
if (Altitude < 90) {
return 183.0;
} // (K)
if (Altitude < 110) {
return -221.111111111 + 4.47 * Altitude;
} // (K)
if (Altitude < 120) {
return -894.0 + 10.6 * Altitude;
} // (K)
if (Altitude >= 120) {
return -894.0 + 10.6 * 120;
} // (K)
// Catch All
return -894.0 + 10.6 * 120; // (K)
};
export const calculateDrag = (M: number) => {
/*
* This function calculates the drag coefficient of the rocket. This function is based
* off of a plot that relates the drag coefficient with the mach number of the rocket.
* Because the plot can not be represented with one equation it is broken up into multiple
* curve fits. The only iMathut for the function is the mach number the rocket is traveling.
*/
if (M < 0.5) {
return 0.125;
}
if (M < 1.1875) {
return -0.329086061307 + 2.30117394072 * M + -4.06597222013 * M ** 2 + 3.01851851676 * M ** 3 + -0.666666666129 * M ** 4;
}
if (M < 1.625) {
return 0.10937644721 + -4.61979595244 * M + 9.72917139612 * M ** 2 + -6.33333563852 * M ** 3 + 1.33333375211 * M ** 4;
}
if (M < 3.625) {
return 0.97916002909 + -0.540978181863 * M + 0.125235817144 * M ** 2 + -0.00666103733277 * M ** 3 + -0.000558009790208 * M ** 4;
}
if (M > 3.625) {
return 0.25;
}
// Catch All
return 0.25;
};
export const calculateThrust = (MassOut: number, Altitude: any, FuelArea: number, NozzleAltitude: any) => {
/*
* This function calculates the thrust force of the rocket by maximizing the efficiency
* through designing the correct shaped nozzle for the given rocket scenario. For this
* function is gives the option for stages of the rocket to be introduced. Theoretically
* this function can have an unlimited amount of stages but for this particular use there
* will only be 3 stages. The iMathuts for the function are:
*/
/*
* MassOut: Mass leaving the nozzle
* Altitude: Rockets current elevation
* FuelArea: Burn area in the combustion chamber
* NozzleAltitude: Altitude immediately after a rocket stage detaches
*/
/*
* The constants for the function were based off of data found for the Trident II Intercontinental
* ballistic missile. These constants are:
* k: Specific heat ratio for the fuel
* Ru: Universal gas constant
* Tc: Chamber temperature
* Pc: Chamber pressure
* Mw: Molecular weight of the fuel
* q: Mass flow out through the nozzle
* Pa: Atmospheric pressure used for optimizing nozzle diameters
* The iteratively calculated variables for this function are:
* Pe: Current atmospheric pressure
* Pt: Throat pressure
* Tt: Throat temperature
* At: Throat area
* Nm: Mach number of the exiting gas
* Ae: Exit area of the nozzle
* Ve: Velocity of the fuel exiting the nozzle
* After making all of these calculations the function will return the force generated by the trust
* of the fuel in units of Newtons. This function will also make sure that the exit nozzle area will
* not exceed that of the cross sectional area for the inside of rocket casing.
*/
const k = 1.2; // Heat Ratio
const Ru = 8314.4621; // Universal Gas Constant (m^3 Pa / K mol)
const Tc = 3700; // (K)
const Pc = 25 * 10 ** 6; // Chamber Pressure (Pa)
const Mw = 22; // Molecular Weight
const q = MassOut; // Mass Flow Rate (kg/s)
const Pa = calculatePressure(NozzleAltitude); // Ambient pressure used to calculate nozzle (Pa)
const Pe = calculatePressure(Altitude); // Actual Atmospheric Pressure (Pa)
const Pt = (Pc * (1 + (k - 1) / 2)) ** (-k / (k - 1)); // Throat Pressure (Pa)
const Tt = Tc / (1 + (k - 1) / 2); // Throat Temperature (k)
const At = (q / Pt) * Math.sqrt((Ru * Tt) / (Mw * k)); // Throat Area (m^2)
const Nm = Math.sqrt((2 / (k - 1)) * (Pc / Pa) ** ((k - 1) / k - 1)); // Mach Number
let Ae = (At / Nm) * (1 + (((k - 1) / 2) * Nm ** 2) / ((k + 1) / 2)) ** ((k + 1) / (2 * (k - 1))); // Exit Nozzle Area (m^2)
if (Ae > FuelArea) {
Ae = FuelArea;
}
const VeSub = ((2 * k) / (k - 1)) * ((Ru * Tc) / Mw) * (1 - Pe / Pc) ** ((k - 1) / k);
const Ve = Math.sqrt(VeSub); // Partical Exit Velocity (m/s)
return q * Ve + (Pe - Pa) * Ae; // Thrust (N)
};
// prettier-ignore
export const calculateCoordinates = (
CurrentLatitude: number,
CurrentLongitude: number,
TargetLatitude: number,
TargetLongitude: number,
): [number[], number[], number, number, number[], number] => { // NOSONAR
/*
* This function calculates the path of the rocket across the earth in terms of coordinates by using
* great-circle equations. It will also calculate which direction will be the shortest distance to the
* target and then calculate the distance across the surface of the earth to the target. There is only
* one constant for this function and that is the radius of the earth. After finding all the variables
* for the final and initial points it will the calculate the coordinates along the path by first extending
* the line between the two points until it reaches the equator. To calculate coordinates along the path it
* needs the angle the line makes at the equator and also at what longitude the line intersects the equator.
* The iMathuts for this function are:
* Phi1: Latitude coordinate of the starting point
* Lambda1: Longitude coordinate of the starting point
* Phi2: Latitude coordinate of the ending point
* Lambda2: Longitude coordinate of the ending point
* The variables that are calculated are:
* Lambda12: Angle difference between the starting and ending longitude coordinates
* Alpha1: Angle from north the initial point will start its travel at
* Alpha2: Angle from north the final point will be traveling at
* DeltaTheta12: Angle between the two initial and final coordinates
* ArcLength: Distance along the earth between the two points
* Alphao: Angle off of the great circle line and north when extended back to the equator.
* DeltaSigma01: Angular distance between the point at the equator and the initial point.
* DeltaSigma02: Angular distance between the point at the equator and the final point
* Lambda01: Longitude difference between the initial point and the point at the equator
* Lambdao: Longitude at the point where the great circle intersects the equator
* Sigma: Arc distance between the first point and any point along the great circle.
* Phi: Latitude at the arbitrary point on the great circle
* Lambda: Longitude at the arbitrary point on the great circle
* This function generates 100 points along the great circle and calculates each longitude and latitude
* and then stores them in lists. Because these list will be used to plot the great circle path the
* coordinate will be broken up into multiple lists if the path passes over edge of the map. The last thing
* the function does before returning the outputs is plotting the great circle onto a map of the globe.
* The outputs are:
* The list of latitudes
* The list of longitudes
* The angle from north to start the great circle
* The angular distance between the starting and ending point
*/
const r = EarthRadius; // (m)
const Phi1 = (CurrentLatitude * Math.PI) / 180; // (Rad)
const Lambda1 = (CurrentLongitude * Math.PI) / 180; // (Rad)
const Phi2 = (TargetLatitude * Math.PI) / 180; // (Rad)
const Lambda2 = (TargetLongitude * Math.PI) / 180; // (Rad)
let Lambda12;
if (Lambda2 - Lambda1 >= -180 && Lambda2 - Lambda1 <= 180) {
Lambda12 = Lambda2 - Lambda1;
} // (Rad)
if (Lambda2 - Lambda1 > 180) {
Lambda12 = Lambda2 - Lambda1 - 2 * Math.PI;
} // (Rad)
if (Lambda2 - Lambda1 < -180) {
Lambda12 = Lambda2 - Lambda1 + 2 * Math.PI;
} // (Rad)
const Alpha1 = Math.atan2(Math.sin(Lambda12), Math.cos(Phi1) * Math.tan(Phi2) - Math.sin(Phi1) * Math.cos(Lambda12)); // (Rad)
const DeltaTheta12 = Math.acos(Math.sin(Phi1) * Math.sin(Phi2) + Math.cos(Phi1) * Math.cos(Phi2) * Math.cos(Lambda12)); // (Rad)
const ArcLength = DeltaTheta12 * r; // (m)
const Alphao = Math.asin(Math.sin(Alpha1) * Math.cos(Phi1)); // (Rad)
const DeltaSigma01 = Math.atan2(Math.tan(Phi1), Math.cos(Alpha1)); // (Rad)
const DeltaSigma02 = DeltaSigma01 + DeltaTheta12; // (Rad)
const Lambda01 = Math.atan2(Math.sin(Alphao) * Math.sin(DeltaSigma01), Math.cos(DeltaSigma01)); // (Rad)
const Lambdao = Lambda1 - Lambda01; // (Rad)
const EstLatList = [];
const latList1 = [];
const latList2 = [];
const latList3 = [];
const EstLongList = [];
const lonList1 = [];
const lonList2 = [];
const lonList3 = [];
const EstDistanceList: number[] = [];
let GoalDistance;
for (let i = 0; i <= 2400; i++) {
const Sigma = DeltaSigma01 + (i * (DeltaSigma02 - DeltaSigma01)) / 2000; // (Rad)
const Phi = (Math.asin(Math.cos(Alphao) * Math.sin(Sigma)) * 180) / Math.PI; // (Degrees)
const Lambda = ((Lambdao + Math.atan2(Math.sin(Alphao) * Math.sin(Sigma), Math.cos(Sigma))) * 180) / Math.PI; // (Degrees)
if (i === 2000) {
GoalDistance = (Sigma - DeltaSigma01) * r;
}
EstDistanceList.push(((Sigma - DeltaSigma01) * r) / 1000);
if (Lambda >= -180 && Lambda <= 180) {
lonList1.push(Lambda); // (Degrees)
latList1.push(Phi); // (Degrees)
} else if (Lambda < -180) {
lonList3.push(Lambda + 360); // (Degrees)
latList3.push(Phi); // (Degrees)
} else if (Lambda > 180) {
lonList2.push(Lambda - 360); // (Degrees)
latList2.push(Phi); // (Degrees)
} else {
// Do nothing
}
}
for (const lat of latList1) {
EstLatList.push(lat);
}
for (const lat of latList2) {
EstLatList.push(lat);
}
for (const lat of latList3) {
EstLatList.push(lat);
}
for (const lon of lonList1) {
EstLongList.push(lon);
}
for (const lon of lonList2) {
EstLongList.push(lon);
}
for (const lon of lonList3) {
EstLongList.push(lon);
}
return [EstLatList, EstLongList, (Alpha1 * 180) / Math.PI, ArcLength, EstDistanceList, GoalDistance];
};
// prettier-ignore
export const launchDetailed = (
FuelArea: number,
FuelMass: number,
RocketArea: number,
Altitude: number,
RocketCasingMass: number,
NozzleAltitude: number,
drdt: number,
dthetadt: number,
Distance: number,
ArcDistance: number,
MassIn: number,
AngleCoefficient: number,
) => { // NOSONAR
/*
* This function is the heart of the program. It calculates the simulated flight
* of the missile. This is only one step of the flight, to get the whole flight
* simulated it must be iterated in a loop. The iMathuts for the function are:
* FuelArea: Area of the fuel surface being burned
* FuelMass: Current mass left in the rocket
* RocketArea: Cross sectional area of the missile
* Altitude: Current altitude of the missile
* RocketCasingMass: Mass of the casing for the missile
* NozzleAltitude: Altitude when the casing stage detaches
* drdt: Current velocity in the vertical direction
* dthetadt: Current angular velocity around the earth
* Distance: Current distance traveled by the missile
* ArcDistance: Current distance traveled along the earths surface
* MassIn: Current fuel mass entering the rocket (always 0)
* AngleCoefficient: The coefficient used to govern the missiles trajectory
* The outputs for this function are:
* FuelMass: Mass left in the missile
* RocketMass: Total Mass of the missile
* Tatm: Atmospheric temperature
* Patm: Atmospheric pressure
* AirDensity: Density of the atmosphere
* c: Current speed of sound of the atmosphere
* M: Missiles mach number
* cD: Missiles drag Coefficient
* Thrust: Thrust produced by the missile
* DragForce: Drag force acting upon the missile
* WeightForce: Gravitational attraction exerted by the earth
* dr2dt: Acceleration in the vertical direction
* drdt: New velocity in the vertical direction
* Altitude: New altitude of the missile
* Distance: New distance traveled by the missile
* ArcVelocity: Velocity of the missile across the surface of the earth
* ArcDistance: New distance traveled along the earths surface
* dtheta2dt: Angular acceleration around the earth
* dthetadt: New angular velocity around the earth
* Some of these values do not need to be returned for calculations in later
* iterations but are returned anyways to present the data later on in plots
* in order to understand the flight of the missile and its governing principles
*/
// This governs the thrust angle as a function of altitude
let ThrustAngle;
if (Altitude < 1200000) {
ThrustAngle =
(90 -
AngleCoefficient *
(1.5336118956 +
0.00443173537387 * Altitude -
9.30373890848 * 10 ** -8 * Altitude ** 2 +
8.37838197732 * 10 ** -13 * Altitude ** 3 -
2.71228576626 * 10 ** -18 * Altitude ** 4)) *
0.0174533;
// (Degrees)
} else {
ThrustAngle = 30;
}
// This calculates the angle the drag force acts upon the missile
const Radius = EarthRadius + Altitude; // (m)
const DragAngle = Math.atan2(drdt, dthetadt); // (Degrees)
let MassOut = 0; // (kg)
// This calculates fuel mass vs time
if (FuelMass > 0) {
MassOut = FuelDensity * FuelArea * BurnRate; // (kg)
const dmdt = MassIn - MassOut; // (kg/s)
FuelMass += dmdt * h; // (kg)
} else {
FuelMass = 0;
}
const RocketMass = FuelMass + RocketCasingMass + WarheadMass; // (Kg)
const Tatm = calculateTemperature(Altitude); // (K)
const Patm = calculatePressure(Altitude); // (pa)
const AirDensity = Patm / (R * Tatm); // (kg/m^3)
// This calculates the drag coeficiant
const c = (1.4 * R * Tatm) ** (1 / 2); // (m/s)
const M = Math.sqrt(drdt ** 2 + dthetadt ** 2) / c; // (Unitless)
const cD = calculateDrag(Math.abs(M)); // (Unitless)
// This calculates all the forces acting upon the missile
let Thrust = 0;
if (FuelMass > 0) {
Thrust = calculateThrust(MassOut, Altitude, FuelArea, NozzleAltitude);
} // (N)
const DragForce = (1 / 2) * AirDensity * (drdt ** 2 + dthetadt ** 2) * RocketArea * cD; // (N)
const WeightForce = (G * EarthMass * RocketMass) / Radius ** 2; // (N)
// Vertical Acceleration and velocity
const dr2dt = (Thrust * Math.sin(ThrustAngle) - DragForce * Math.sin(DragAngle) - WeightForce) / RocketMass + Radius * (dthetadt / Radius) ** 2; // (m/s^2)
drdt += dr2dt * h; // (m/s)
Altitude += drdt * h; // (m)
Distance += dthetadt * h; // (m)
// Angular distance the missile traveled vs time
const ArcVelocity = (dthetadt * EarthRadius) / Radius; // (m/s)
ArcDistance += ArcVelocity * h; // (m)
// Angular acceleration and velocity
const dtheta2dt = (Thrust * Math.cos(ThrustAngle) - DragForce * Math.cos(DragAngle)) / RocketMass - 2 * drdt * (dthetadt / Radius); // (m/s^2)
dthetadt += dtheta2dt * h; // (m/s)
return [FuelMass, RocketMass, Tatm, Patm, AirDensity, c, M, cD, Thrust, DragForce, WeightForce, dr2dt, drdt, Altitude, Distance, ArcVelocity, ArcDistance, dtheta2dt, dthetadt];
};
// prettier-ignore
export const calculateAngle = (
FuelArea1: number,
FuelArea2: number,
FuelMass: number,
FuelVolume: number,
RocketArea: number,
Altitude: number,
RocketCasingMass1: number,
RocketCasingMass2: number,
RocketCasingMass3: number,
NozzleAltitude1: number,
drdt: number,
dthetadt: number,
Distance: number,
ArcDistance: number,
MassIn: number,
_ArcLength: number,
GoalDistance: number,
) => { // NOSONAR
/*
* This function is designed to calculate the needed angle coefficient to for the trust
* to govern the missiles path into its designated target. Because this missile has the
* capability of entering into orbit, more complicated calculations needed to be used to
* ensure that the program would be successful in finding the correct drag coefficient
* in all instances. How the function works is by running the missile simulation multiple
* times with different angle coefficients to find with one lands the missile closest to
* its target. Once it has a ball park region for the angle coefficient it runs a modified
* bisection method to further bring the angle coefficient closer to the needed value to
* land the missile on the target. The inputs for the program are:
* FuelArea1: Area of the fuel surface being burned for the first and second stages of the missile
* FuelArea2: Area of the fuel surface being burned for the third stage of the missile
* FuelMass: Mass left in the missile
* FuelVolume: Initial value of the total volume of fuel stored in the missile
* RocketArea: Cross sectional area of the missile
* Altitude: Initial condition for the altitude (0 meters)
* RocketCasingMass1: Mass of the casing for the missiles during the first stage
* RocketCasingMass2: Mass of the casing for the missiles during the second stage
* RocketCasingMass3: Mass of the casing for the missiles during the third stage
* NozzleAltitude1: The altitude used to calculate the nozzle for the first stage (0 meters)
* drdt: Initial condition for the velocity in the vertical direction (0 m/s)
* dthetadt: Initial condition for the angular velocity around the earth (0 m/s)
* Distance: Initial condition for the distance traveled by the missile (0 meters)
* ArcDistance: Initial condition for the distance traveled along the earths surface (0 meters)
* MassIn: Initial condition for the mass entering the missile (always 0)
* ArcLength: Distance from the starting point to the target along the surface of the earth
* The functions output it:
* AngleCoefficient: The angle coefficient which directs the missile directly to it's target
*/
const DistanceSteps = [];
let AngleCoefficient = 0;
let DistanceClosePossition = 0;
let AC1 = 0;
let AC2 = 0;
const Steps = 500;
for (let i = 0; i < Steps; i++) {
AngleCoefficient = (i * 1) / Steps / 2 + 0.5;
DistanceSteps.push(
launchSimple(
FuelArea1,
FuelArea2,
FuelMass,
FuelVolume,
RocketArea,
Altitude,
RocketCasingMass1,
RocketCasingMass2,
RocketCasingMass3,
NozzleAltitude1,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
AngleCoefficient,
),
);
}
let DistanceClosest = DistanceSteps[0];
let oldDistanceClosest = Math.abs(DistanceSteps[0] - GoalDistance);
for (const distance_ of DistanceSteps) {
const newDistanceClosest = Math.abs(distance_ - GoalDistance);
if (newDistanceClosest < oldDistanceClosest) {
oldDistanceClosest = newDistanceClosest;
DistanceClosest = distance_;
}
}
for (let i = 0; i < Steps; i++) {
if (DistanceSteps[i] === DistanceClosest) {
DistanceClosePossition = i;
break;
}
}
AngleCoefficient = (DistanceClosePossition * 1) / Steps / 2 + 0.5;
// bisection method
AC1 = (DistanceClosePossition - 2) / Steps / 2 + 0.5;
AC2 = (DistanceClosePossition + 2) / Steps / 2 + 0.5;
let ACNew: number = (AC1 + AC2) / 2;
const qRunACNew = launchSimple(
FuelArea1,
FuelArea2,
FuelMass,
FuelVolume,
RocketArea,
Altitude,
RocketCasingMass1,
RocketCasingMass2,
RocketCasingMass3,
NozzleAltitude1,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
ACNew,
);
let error = Math.abs((GoalDistance - qRunACNew) / GoalDistance) * 100;
while (error > 0.01 && Math.abs(AC2 - AC1) >= 0.0001) {
ACNew = (AC1 + AC2) / 2;
error =
Math.abs(
(GoalDistance -
launchSimple(
FuelArea1,
FuelArea2,
FuelMass,
FuelVolume,
RocketArea,
Altitude,
RocketCasingMass1,
RocketCasingMass2,
RocketCasingMass3,
NozzleAltitude1,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
ACNew,
)) /
GoalDistance,
) * 100;
if (
launchSimple(
FuelArea1,
FuelArea2,
FuelMass,
FuelVolume,
RocketArea,
Altitude,
RocketCasingMass1,
RocketCasingMass2,
RocketCasingMass3,
NozzleAltitude1,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
ACNew,
) > GoalDistance
) {
AC2 = ACNew;
} else {
AC1 = ACNew;
}
}
AngleCoefficient = ACNew;
return AngleCoefficient;
};
// prettier-ignore
export const launchSimple = (
FuelArea1: any,
FuelArea2: any,
FuelMass: number,
FuelVolume: number,
RocketArea: any,
Altitude: number,
RocketCasingMass1: any,
RocketCasingMass2: any,
RocketCasingMass3: any,
NozzleAltitude1: any,
drdt: any,
dthetadt: any,
Distance: any,
ArcDistance: any,
MassIn: any,
AngleCoefficient: number,
) => { // NOSONAR
/*
* This function calculates the entire simulation of the missiles tragectory without
* collecting any information along the way. It's purpose is for the angle cooefficeint
* optimizer to have a quick way to run the simulation and retreive the final distance
* the missile traveled along the surface of the earth. The functions inputs are:
* FuelArea1: Area of the fuel surface being burned for the first and second stages of the missile
* FuelArea2: Area of the fuel surface being burned for the third stage of the missile
* FuelMass: Mass left in the missile
* FuelVolume: Initial value of the total volume of fuel stored in the missile
* RocketArea: Cross sectional area of the missile
* Altitude: Initial condition for the altitude (0 meters)
* RocketCasingMass1: Mass of the casing for the missiles during the first stage
* RocketCasingMass2: Mass of the casing for the missiles during the second stage
* RocketCasingMass3: Mass of the casing for the missiles during the third stage
* NozzleAltitude1: The altitude used to calculate the nozzle for the first stage (0 meters)
* drdt: Initial condition for the velocity in the vertical direction (0 m/s)
* dthetadt: Initial condition for the angular velocity around the earth (0 m/s)
* Distance: Initial condition for the distance traveled by the missile (0 meters)
* ArcDistance: Initial condition for the distance traveled along the earths surface (0 meters)
* MassIn: Initial condition for the mass entering the missile (always 0)
* AngleCoefficient: Coefficient used to govern the angle of the thrust to dirrect the missile towards its target
* The output for this function is:
* ArcDistance: The total distance traveled by the missile along the surface of the earth
* var RocketMass, Tatm, Patm, AirDensity, c, M, cD, Thrust, DragForce, WeightForce, dr2dt, ArcVelocity, theta2dt;
*/
let NozzleAltitude2, NozzleAltitude3;
let iterationFunOutput = [];
const MaxAltitude = [];
while (FuelMass / FuelDensity / FuelVolume > 0.4 && Altitude >= 0) {
iterationFunOutput = launchDetailed(
FuelArea1,
FuelMass,
RocketArea,
Altitude,
RocketCasingMass1,
NozzleAltitude1,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
AngleCoefficient,
);
FuelMass = iterationFunOutput[0];
drdt = iterationFunOutput[12];
Altitude = iterationFunOutput[13];
MaxAltitude.push(Altitude);
Distance = iterationFunOutput[14];
ArcDistance = iterationFunOutput[16];
dthetadt = iterationFunOutput[18];
NozzleAltitude2 = Altitude;
}
while (FuelMass / FuelDensity / FuelVolume > 0.19 && Altitude >= 0) {
iterationFunOutput = launchDetailed(
FuelArea1,
FuelMass,
RocketArea,
Altitude,
RocketCasingMass2,
NozzleAltitude2,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
AngleCoefficient,
);
FuelMass = iterationFunOutput[0];
drdt = iterationFunOutput[12];
Altitude = iterationFunOutput[13];
MaxAltitude.push(Altitude);
Distance = iterationFunOutput[14];
ArcDistance = iterationFunOutput[16];
dthetadt = iterationFunOutput[18];
NozzleAltitude3 = Altitude;
}
while (FuelMass / FuelDensity / FuelVolume > 0 && Altitude >= 0) {
iterationFunOutput = launchDetailed(
FuelArea2,
FuelMass,
RocketArea,
Altitude,
RocketCasingMass3,
NozzleAltitude3,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
AngleCoefficient,
);
FuelMass = iterationFunOutput[0];
drdt = iterationFunOutput[12];
Altitude = iterationFunOutput[13];
MaxAltitude.push(Altitude);
Distance = iterationFunOutput[14];
ArcDistance = iterationFunOutput[16];
dthetadt = iterationFunOutput[18];
}
while (Altitude > 0) {
FuelMass = 0;
iterationFunOutput = launchDetailed(
FuelArea2,
FuelMass,
RocketArea,
Altitude,
RocketCasingMass3,
NozzleAltitude3,
drdt,
dthetadt,
Distance,
ArcDistance,
MassIn,
AngleCoefficient,
);
FuelMass = iterationFunOutput[0];
drdt = iterationFunOutput[12];
Altitude = iterationFunOutput[13];
MaxAltitude.push(Altitude);
Distance = iterationFunOutput[14];
💡 Add Copilot custom instructions for smarter, more guided reviews. Learn how to get started.
| Altitude, | ||
| RocketCasingMass2, | ||
| NozzleAltitude2, | ||
| while (fuelMass / fuelDensity / fuelVolume > 0.4 && altitude >= 0) { |
There was a problem hiding this comment.
Incorrect loop condition. This should check fuelMass / fuelDensity / fuelVolume > 0.19 (not > 0.4). This appears to be a copy-paste error during refactoring - the original code at line 1093 in the old version had the condition > 0.19 for this second stage.
Suggested change
| while (fuelMass / fuelDensity / fuelVolume > 0.4 && altitude >= 0) { | |
| while (fuelMass / fuelDensity / fuelVolume > 0.19 && altitude >= 0) { |
| Altitude, | ||
| RocketCasingMass3, | ||
| NozzleAltitude3, | ||
| while (fuelMass / fuelDensity / fuelVolume > 0.4 && altitude >= 0) { |
There was a problem hiding this comment.
Incorrect loop condition. This should check fuelMass / fuelDensity / fuelVolume > 0 (not > 0.4). This appears to be a copy-paste error during refactoring - the original code at line 1139 in the old version had the condition > 0 for this third stage.
Suggested change
| while (fuelMass / fuelDensity / fuelVolume > 0.4 && altitude >= 0) { | |
| while (fuelMass / fuelDensity / fuelVolume > 0 && altitude >= 0) { |
| import { ServiceLocator } from '@app/engine/core/service-locator'; | ||
|
|
||
| let BurnRate: number, EarthMass: number, EarthRadius: number, FuelDensity: number, G: number, R: number, WarheadMass: number, h: number; | ||
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; |
There was a problem hiding this comment.
Unused variable burnRate.
Suggested change
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; | |
| let earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; |
| import { ServiceLocator } from '@app/engine/core/service-locator'; | ||
|
|
||
| let BurnRate: number, EarthMass: number, EarthRadius: number, FuelDensity: number, G: number, R: number, WarheadMass: number, h: number; | ||
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; |
There was a problem hiding this comment.
Unused variable earthMass.
Suggested change
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; | |
| let burnRate: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; |
| import { ServiceLocator } from '@app/engine/core/service-locator'; | ||
|
|
||
| let BurnRate: number, EarthMass: number, EarthRadius: number, FuelDensity: number, G: number, R: number, WarheadMass: number, h: number; | ||
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; |
There was a problem hiding this comment.
Unused variable earthRadius.
Suggested change
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; | |
| let burnRate: number, earthMass: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; |
| import { ServiceLocator } from '@app/engine/core/service-locator'; | ||
|
|
||
| let BurnRate: number, EarthMass: number, EarthRadius: number, FuelDensity: number, G: number, R: number, WarheadMass: number, h: number; | ||
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; |
There was a problem hiding this comment.
Unused variable g.
Suggested change
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; | |
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, r: number, warheadMass: number, h: number; |
| import { ServiceLocator } from '@app/engine/core/service-locator'; | ||
|
|
||
| let BurnRate: number, EarthMass: number, EarthRadius: number, FuelDensity: number, G: number, R: number, WarheadMass: number, h: number; | ||
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; |
There was a problem hiding this comment.
Unused variable r.
Suggested change
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; | |
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, warheadMass: number, h: number; |
| import { ServiceLocator } from '@app/engine/core/service-locator'; | ||
|
|
||
| let BurnRate: number, EarthMass: number, EarthRadius: number, FuelDensity: number, G: number, R: number, WarheadMass: number, h: number; | ||
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; |
There was a problem hiding this comment.
Unused variable warheadMass.
Suggested change
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, warheadMass: number, h: number; | |
| let burnRate: number, earthMass: number, earthRadius: number, fuelDensity: number, g: number, r: number, h: number; |
| warheadMass, | ||
| ); | ||
| FuelMass = iterationFunOutput[0]; | ||
| fuelMass = iterationFunOutput[0]; |
There was a problem hiding this comment.
The value assigned to fuelMass here is unused.
Suggested change
| fuelMass = iterationFunOutput[0]; |
| ); | ||
|
|
||
| FuelMass = iterationFunOutput[0]; | ||
| fuelMass = iterationFunOutput[0]; |
There was a problem hiding this comment.
The value assigned to fuelMass here is unused.
Suggested change
| fuelMass = iterationFunOutput[0]; |
|
Sign up for free
to join this conversation on GitHub.
Already have an account?
Sign in to comment
Add this suggestion to a batch that can be applied as a single commit.
This suggestion is invalid because no changes were made to the code.
Suggestions cannot be applied while the pull request is closed.
Suggestions cannot be applied while viewing a subset of changes.
Only one suggestion per line can be applied in a batch.
Add this suggestion to a batch that can be applied as a single commit.
Applying suggestions on deleted lines is not supported.
You must change the existing code in this line in order to create a valid suggestion.
Outdated suggestions cannot be applied.
This suggestion has been applied or marked resolved.
Suggestions cannot be applied from pending reviews.
Suggestions cannot be applied on multi-line comments.
Suggestions cannot be applied while the pull request is queued to merge.
Suggestion cannot be applied right now. Please check back later.
Files refactored: