fix: 🐛 fix Satellite class

.prettierrc

@@ -10,7 +10,7 @@
   "arrowParens": "always",
   "requirePragma": false,
   "insertPragma": false,
-  "proseWrap": "never",
+  "proseWrap": "always",
   "htmlWhitespaceSensitivity": "ignore",
   "endOfLine": "lf",
   "embeddedLanguageFormatting": "off"

examples/sensor.ts

@@ -0,0 +1,30 @@
+/* eslint-disable no-console */
+import { Satellite } from '@src/objects/Satellite';
+import { Sensor } from '../src/objects';
+import { Degrees, Kilometers, SpaceObjectType, TleLine1, TleLine2 } from '../src/ootk';
+
+const capeCodRadar = new Sensor({
+  lat: <Degrees>41.754785,
+  lon: <Degrees>-70.539151,
+  alt: <Kilometers>0.060966,
+  minAz: 347 as Degrees,
+  maxAz: 227 as Degrees,
+  minEl: 3 as Degrees,
+  maxEl: 85 as Degrees,
+  minRng: 0 as Kilometers,
+  maxRng: 5556 as Kilometers,
+  name: 'Cape Cod',
+  type: SpaceObjectType.PHASED_ARRAY_RADAR,
+});
+
+const sat = new Satellite({
+  tle1: '1 00005U 58002B   23361.70345217  .00000401  00000-0  53694-3 0 99999' as TleLine1,
+  tle2: '2 00005  34.2395 218.8683 1841681  30.7692 338.8934 10.85144797345180' as TleLine2,
+});
+
+const date = new Date('2023-12-31T20:51:19.934Z');
+
+sat.propagateTo(date);
+
+// console.log(sat.raeOpt(capeCodRadar, date));
+console.log(sat.getJ2000().inertial);

examples/tsconfig.json

@@ -1,4 +1,7 @@
 {
+  "ts-node": {
+    "require": ["tsconfig-paths/register"]
+  },
   "compilerOptions": {
     "module": "commonjs",
     "target": "ES2015",

package.json

@@ -54,6 +54,7 @@
     "prettier": "^2.8.8",
     "prettier-plugin-organize-imports": "^3.2.3",
     "ts-node": "^10.9.2",
+    "tsconfig-paths": "^4.2.0",
     "typescript": "^4.9.5",
     "webpack": "^5.11.1",
     "webpack-cli": "^4.10.0"

src/body/Celestial.ts

@@ -1,12 +1,14 @@
-import { AzEl, Degrees, RaDec, Radians } from '@src/ootk';
+import { AzEl, RaDec, Radians } from '@src/ootk';
+import { RAD2DEG } from '@src/utils/constants';
+import { Degrees } from './../../lib/types/types.d';
 import { Sun } from './Sun';
 
 export class Celestial {
   private constructor() {
     // disable constructor
   }
 
-  static getStarAzEl(date: Date, lat: Degrees, lon: Degrees, ra: Radians, dec: Radians): AzEl<Radians> {
+  static getStarAzEl(date: Date, lat: Degrees, lon: Degrees, ra: Radians, dec: Radians): AzEl<Degrees> {
     const c: RaDec = {
       ra,
       dec,
@@ -16,8 +18,8 @@ export class Celestial {
     const el = <Radians>(azEl.el + Celestial.astroRefraction(azEl.el)); // elevation correction for refraction
 
     return {
-      az: azEl.az,
-      el,
+      az: (azEl.az * RAD2DEG) as Degrees,
+      el: (el * RAD2DEG) as Degrees,
     };
   }
 

src/body/Earth.ts

@@ -1,4 +1,5 @@
 import { Radians } from '@src/ootk';
+import { EpochUTC } from '@src/time/EpochUTC';
 import { DataHandler } from '../data/DataHandler';
 import {
   asec2rad,
@@ -11,7 +12,6 @@ import {
 } from '../operations/constants';
 import { angularDiameter, AngularDiameterMethod, evalPoly } from '../operations/functions';
 import { Vector3D } from '../operations/Vector3D';
-import { EpochUTC } from '../time/EpochUTC';
 import { NutationAngles } from './NutationAngles';
 import { PrecessionAngles } from './PrecessionAngles';
 

src/body/Moon.ts

@@ -1,7 +1,7 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { deg2rad } from '../operations/constants';
 import { angularDiameter, AngularDiameterMethod } from '../operations/functions';
 import { Vector3D } from '../operations/Vector3D';
-import { EpochUTC } from '../time/EpochUTC';
 import { Earth } from './Earth';
 import { Sun } from './Sun';
 

src/body/Sun.ts

@@ -1,9 +1,9 @@
 import { AzEl, Degrees, Kilometers, Meters, Radians, SunTime } from '@src/ootk';
+import { EpochUTC } from '@src/time/EpochUTC';
 import { RaDec } from '@src/types/types';
 import { astronomicalUnit, deg2rad, speedOfLight, tau } from '../operations/constants';
 import { angularDiameter, AngularDiameterMethod } from '../operations/functions';
 import { Vector3D } from '../operations/Vector3D';
-import { EpochUTC } from '../time/EpochUTC';
 import { DEG2RAD, MS_PER_DAY } from '../utils/constants';
 import { Celestial } from './Celestial';
 import { Earth } from './Earth';

src/coordinate/ClassicalElements.ts

@@ -1,8 +1,8 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { Earth } from '../body/Earth';
 import { sec2min, secondsPerDay } from '../operations/constants';
 import { clamp, matchHalfPlane, newtonNu } from '../operations/functions';
 import { Vector3D } from '../operations/Vector3D';
-import { EpochUTC } from '../time/EpochUTC';
 import { rad2deg, tau } from './../operations/constants';
 import { EquinoctialElements } from './EquinoctialElements';
 import { OrbitRegime } from './OrbitRegime';

src/coordinate/EquinoctialElements.ts

@@ -1,6 +1,6 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { Earth } from '../body/Earth';
 import { newtonM } from '../operations/functions';
-import { EpochUTC } from '../time/EpochUTC';
 import { secondsPerDay, tau } from './../operations/constants';
 import { ClassicalElements } from './ClassicalElements';
 import { PositionVelocity } from './StateVector';

src/coordinate/Geodetic.ts

@@ -1,8 +1,8 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { Earth } from '../body/Earth';
 import { deg2rad, rad2deg } from '../operations/constants';
 import { angularDistance, AngularDistanceMethod } from '../operations/functions';
 import { Vector3D } from '../operations/Vector3D';
-import { EpochUTC } from '../time/EpochUTC';
 import { ITRF } from './ITRF';
 
 // / Geodetic coordinates.

src/coordinate/Hill.ts

@@ -1,9 +1,9 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { Earth } from '../body/Earth';
 import { Thrust } from './../force/Thrust';
 import { Waypoint } from './../maneuver/Waypoint';
 import { Matrix } from './../operations/Matrix';
 import { Vector3D } from './../operations/Vector3D';
-import { EpochUTC } from './../time/EpochUTC';
 import { J2000 } from './J2000';
 import { RelativeState } from './RelativeState';
 // / Hill Modified Equidistant Cyllindrical _(EQCM)_ coordinates.

src/coordinate/J2000.ts

@@ -6,20 +6,34 @@ import { StateVector } from './StateVector';
 import { TEME } from './TEME';
 
 export class J2000 extends StateVector {
+  /**
+   * Creates a J2000 instance from classical elements.
+   */
   static fromClassicalElements(elements: ClassicalElements): J2000 {
     const rv = elements.toPositionVelocity();
 
     return new J2000(elements.epoch, rv.position, rv.velocity);
   }
 
+  /**
+   * Gets the name of the coordinate system.
+   */
   get name(): string {
     return 'J2000';
   }
 
+  /**
+   * Gets a value indicating whether the coordinate system is inertial.
+   */
   get inertial(): boolean {
     return true;
   }
 
+  /**
+   * Converts the coordinates from J2000 to the International Terrestrial Reference Frame (ITRF).
+   *
+   * This is an ECI to ECF transformation.
+   */
   toITRF(): ITRF {
     const p = Earth.precession(this.epoch);
     const n = Earth.nutation(this.epoch);

src/coordinate/StateVector.ts

@@ -1,6 +1,6 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { Earth } from '../body/Earth';
 import { Vector3D } from '../operations/Vector3D';
-import { EpochUTC } from '../time/EpochUTC';
 import { tau } from './../operations/constants';
 import { ClassicalElements } from './ClassicalElements';
 

src/coordinate/TEME.ts

@@ -4,7 +4,15 @@ import { ClassicalElements } from './ClassicalElements';
 import { J2000 } from './J2000';
 import { StateVector } from './StateVector';
 
-// / True Equator Mean Equinox _(TEME)_ state vector
+/**
+ * True Equator Mean Equinox (TEME) is a coordinate system commonly used in satellite tracking and orbit prediction.
+ * It is a reference frame that defines the position and orientation of an object relative to the Earth's equator
+ * and equinox.
+ *
+ * By using the True Equator Mean Equinox (TEME) coordinate system, we can accurately describe the position and motion
+ * of satellites relative to the Earth's equator and equinox. This is particularly useful for tracking and predicting
+ * satellite orbits in various applications, such as satellite communication, navigation, and remote sensing.
+ */
 export class TEME extends StateVector {
   // / Create a new [TEME] object from a [ClassicalElements] object.
   static fromClassicalElements(elements: ClassicalElements): TEME {

src/coordinate/TLE.ts

@@ -1,9 +1,9 @@
 import { EciVec3, SatelliteRecord, StateVectorSgp4 } from '@src/ootk';
 import { Sgp4, Sgp4GravConstants } from '@src/sgp4/sgp4';
+import { EpochUTC } from '@src/time/EpochUTC';
 import { Earth } from '../body/Earth';
 import { deg2rad, rad2deg, secondsPerDay, tau } from '../operations/constants';
 import { Vector3D } from '../operations/Vector3D';
-import { EpochUTC } from '../time/EpochUTC';
 import { TEME } from './TEME';
 
 export enum Sgp4OpsMode {

src/covariance/CovarianceSample.ts

@@ -1,4 +1,5 @@
 /* eslint-disable class-methods-use-this */
+import { EpochUTC } from '@src/time/EpochUTC';
 import { J2000 } from '../coordinate/J2000';
 import { RelativeState } from '../coordinate/RelativeState';
 import { RIC } from '../coordinate/RIC';
@@ -9,7 +10,6 @@ import { Vector } from '../operations/Vector';
 import { Vector3D } from '../operations/Vector3D';
 import { RungeKutta89Propagator } from '../propagator/RungeKutta89Propagator';
 import { Epoch } from '../time/Epoch';
-import { EpochUTC } from '../time/EpochUTC';
 import { CovarianceFrame, StateCovariance } from './StateCovariance';
 
 // / Sigma point covariance sample.

src/force/Thrust.ts

@@ -1,5 +1,5 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { Vector3D } from '../operations/Vector3D';
-import { EpochUTC } from '../time/EpochUTC';
 import { J2000 } from './../coordinate/J2000';
 import { RIC } from './../coordinate/RIC';
 import { Force } from './Force';

src/interpolator/ChebyshevInterpolator.ts

@@ -1,6 +1,6 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { EpochWindow } from '@src/time/EpochWindow';
 import { J2000 } from './../coordinate/J2000';
-import { EpochUTC } from './../time/EpochUTC';
 import { ChebyshevCoefficients } from './ChebyshevCoefficients';
 import { StateInterpolator } from './StateInterpolator';
 

src/interpolator/CubicSplineInterpolator.ts

@@ -1,6 +1,6 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { EpochWindow } from '@src/time/EpochWindow';
 import { J2000 } from '../coordinate/J2000';
-import { EpochUTC } from '../time/EpochUTC';
 import { CubicSpline } from './CubicSpline';
 import { StateInterpolator } from './StateInterpolator';
 

src/interpolator/Interpolator.ts

@@ -1,5 +1,5 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { EpochWindow } from '@src/time/EpochWindow';
-import { EpochUTC } from '../time/EpochUTC';
 
 // / Interpolator base class.
 export abstract class Interpolator {

src/interpolator/LagrangeInterpolator.ts

@@ -1,7 +1,7 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { EpochWindow } from '@src/time/EpochWindow';
 import { J2000 } from '../coordinate/J2000';
 import { Vector3D } from '../operations/Vector3D';
-import { EpochUTC } from '../time/EpochUTC';
 import { StateInterpolator } from './StateInterpolator';
 
 export class LagrangeInterpolator extends StateInterpolator {

src/interpolator/StateInterpolator.ts

@@ -1,8 +1,8 @@
 /* eslint-disable @typescript-eslint/no-unused-vars */
 /* eslint-disable class-methods-use-this */
 
+import { EpochUTC } from '@src/time/EpochUTC';
 import { J2000 } from '../coordinate/J2000';
-import { EpochUTC } from '../time/EpochUTC';
 import { Interpolator } from './Interpolator';
 
 // / Base class for state vector interpolators.

src/interpolator/VerletBlendInterpolator.ts

@@ -1,9 +1,9 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { EpochWindow } from '@src/time/EpochWindow';
 import { Earth } from '../body/Earth';
 import { J2000 } from '../coordinate/J2000';
 import { copySign } from '../operations/functions';
 import { Vector3D } from '../operations/Vector3D';
-import { EpochUTC } from '../time/EpochUTC';
 import { CubicSplineInterpolator } from './CubicSplineInterpolator';
 import { LagrangeInterpolator } from './LagrangeInterpolator';
 import { StateInterpolator } from './StateInterpolator';

src/maneuver/TwoBurnOrbitTransfer.ts

@@ -1,6 +1,6 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { Earth } from '../body/Earth';
 import { Thrust } from '../force/Thrust';
-import { EpochUTC } from '../time/EpochUTC';
 
 // / Container for a two-burn orbit transfer.
 export class TwoBurnOrbitTransfer {

src/maneuver/Waypoint.ts

@@ -1,9 +1,9 @@
+import { EpochUTC } from '@src/time/EpochUTC';
 import { J2000 } from '../coordinate/J2000';
 import { RIC } from '../coordinate/RIC';
 import { Thrust } from '../force/Thrust';
 import { StateInterpolator } from '../interpolator/StateInterpolator';
 import { Vector3D } from '../operations/Vector3D';
-import { EpochUTC } from '../time/EpochUTC';
 import { ForceModel } from './../force/ForceModel';
 import { DownhillSimplex } from './../optimize/DownhillSimplex';
 import { LambertIOD } from './../orbit_determination/LambertIOD';

src/objects/detailed-sat.ts → src/objects/.detailed-sat.ts

@@ -30,7 +30,7 @@ import {
   TleLine2,
 } from '../types/types';
 
-import { OptionsParams, Sat } from './sat';
+import { OptionsParams, Satellite } from './Satellite';
 
 /**
  * Information about a space object.
@@ -47,7 +47,7 @@ interface ObjectInfo {
 /**
  * Represents a detailed satellite object with launch, spacecraft, and operations details.
  */
-export class DetailedSat extends Sat {
+export class DetailedSat extends Satellite {
   configuration: string;
   country: string;
   dryMass: string;