test: ✅ add tests for Tle

src/coordinate/ClassicalElements.ts

@@ -1,12 +1,11 @@
-import { Degrees, Kilometers, Radians, Seconds } from '../main';
+import { Minutes, PositionVelocity, Degrees, Kilometers, Radians, Seconds } from '../main';
 import { Vector3D } from '../operations/Vector3D';
 import { EpochUTC } from '../time/EpochUTC';
-import { earthGravityParam, RAD2DEG, sec2min, secondsPerDay, TAU } from '../utils/constants';
+import { earthGravityParam, MINUTES_PER_DAY, RAD2DEG, sec2min, TAU } from '../utils/constants';
 import { clamp, matchHalfPlane, newtonNu } from '../utils/functions';
 import { EquinoctialElements } from './EquinoctialElements';
 import { OrbitRegime } from '../enums/OrbitRegime';
 import { StateVector } from './StateVector';
-import { PositionVelocity } from 'src/types/types';
 import { ClassicalElementsParams } from '../interfaces/ClassicalElementsParams';
 
 /**
@@ -97,7 +96,7 @@ export class ClassicalElements {
 
     return new ClassicalElements({
       epoch: state.epoch,
-      semimajorAxis: a as Kilometers,
+      semimajorAxis: a,
       eccentricity: e,
       inclination: i as Radians,
       rightAscension: o as Radians,
@@ -181,16 +180,18 @@ export class ClassicalElements {
    * Calculates the period of the orbit.
    * @returns The period in seconds.
    */
-  get period(): Seconds {
-    return (TAU * Math.sqrt(this.semimajorAxis ** 3 / this.mu)) as Seconds;
+  get period(): Minutes {
+    const periodSec = (TAU * Math.sqrt(this.semimajorAxis ** 3 / this.mu)) as Seconds;
+
+    return (periodSec / 60) as Minutes;
   }
 
   /**
    * Compute the number of revolutions completed per day for this orbit.
    * @returns The number of revolutions per day.
    */
   get revsPerDay(): number {
-    return secondsPerDay / this.period;
+    return MINUTES_PER_DAY / this.period;
   }
 
   /**

src/coordinate/EquinoctialElements.ts

@@ -1,9 +1,9 @@
 import { Kilometers, Radians, Seconds } from '../main';
 import { EpochUTC } from '../time/EpochUTC';
-import { earthGravityParam, secondsPerDay, TAU } from '../utils/constants';
+import { earthGravityParam, MINUTES_PER_DAY, TAU } from '../utils/constants';
 import { newtonM } from '../utils/functions';
 import { ClassicalElements } from './ClassicalElements';
-import { PositionVelocity } from 'src/types/types';
+import { Minutes, PositionVelocity } from 'src/types/types';
 import { EquinoctialElementsParams } from '../interfaces/EquinoctialElementsParams';
 
 /**
@@ -135,10 +135,12 @@ export class EquinoctialElements {
 
   /**
    * Gets the period of the orbit.
-   * @returns The period in seconds.
+   * @returns The period in minutes.
    */
-  get period(): Seconds {
-    return (TAU * Math.sqrt(this.semimajorAxis ** 3 / this.mu)) as Seconds;
+  get period(): Minutes {
+    const periodSec = (TAU * Math.sqrt(this.semimajorAxis ** 3 / this.mu)) as Seconds;
+
+    return (periodSec / 60) as Minutes;
   }
 
   /**
@@ -147,7 +149,7 @@ export class EquinoctialElements {
    * @returns The number of revolutions per day.
    */
   get revsPerDay(): number {
-    return secondsPerDay / this.period;
+    return MINUTES_PER_DAY / this.period;
   }
 
   /**

src/coordinate/TEME.ts

@@ -18,22 +18,40 @@ import { StateVector } from './StateVector';
  * communication, navigation, and remote sensing.
  */
 export class TEME extends StateVector {
-  // / Create a new [TEME] object from a [ClassicalElements] object.
-  static fromClassicalElements(elements: ClassicalElements): TEME {
-    const rv = elements.toPositionVelocity();
-
-    return new TEME(elements.epoch, rv.position, rv.velocity);
-  }
-
+  /**
+   * Gets the name of the coordinate system.
+   * @returns The name of the coordinate system.
+   */
   get name(): string {
     return 'TEME';
   }
 
+  /**
+   * Gets a value indicating whether the coordinate is inertial.
+   * @returns A boolean value indicating whether the coordinate is inertial.
+   */
   get inertial(): boolean {
     return true;
   }
 
-  // / Convert this to a [J2000] state vector object.
+  /**
+   * Creates a TEME (True Equator Mean Equinox) object from classical orbital
+   * elements.
+   *
+   * @param elements - The classical orbital elements.
+   * @returns A new TEME object.
+   */
+  static fromClassicalElements(elements: ClassicalElements): TEME {
+    const rv = elements.toPositionVelocity();
+
+    return new TEME(elements.epoch, rv.position, rv.velocity);
+  }
+
+  /**
+   * Converts the TEME (True Equator Mean Equinox) coordinates to J2000
+   * coordinates.
+   * @returns The J2000 coordinates.
+   */
   toJ2000(): J2000 {
     const p = Earth.precession(this.epoch);
     const n = Earth.nutation(this.epoch);

src/coordinate/Tle.ts

@@ -41,6 +41,7 @@ import {
   Line2Data,
   Minutes,
   SatelliteRecord,
+  Seconds,
   StateVectorSgp4,
   TleData,
   TleDataFull,
@@ -175,8 +176,10 @@ export class Tle {
     return this.semimajorAxis * (1 - this.eccentricity);
   }
 
-  get period(): number {
-    return TAU * Math.sqrt(this.semimajorAxis ** 3 / earthGravityParam);
+  get period(): Minutes {
+    const periodSec = (TAU * Math.sqrt(this.semimajorAxis ** 3 / earthGravityParam)) as Seconds;
+
+    return (periodSec / 60) as Minutes;
   }
 
   private static parseEpoch_(epochStr: string): EpochUTC {

test/coordinate/TEME.test.ts

@@ -0,0 +1,48 @@
+import { exampleDate } from '../lib/mockData';
+import { ClassicalElements, EpochUTC, J2000, Kilometers, Radians, TEME, Vector3D } from './../../src/main';
+describe('TEME', () => {
+  let stateVector: TEME;
+
+  beforeEach(() => {
+    stateVector = new J2000(
+      EpochUTC.fromDateTime(new Date(1705109326817)),
+      new Vector3D(1538.223335842895 as Kilometers, 5102.261204021967 as Kilometers, 4432.634965003577 as Kilometers),
+      new Vector3D(
+        -7.341518909379302 as Kilometers,
+        0.6516718453998644 as Kilometers,
+        1.7933882499861993 as Kilometers,
+      ),
+    ).toTEME();
+  });
+
+  // name
+  it('should return the name of the coordinate system', () => {
+    expect(stateVector.name).toMatchSnapshot();
+  });
+
+  // inertial
+  it('should return whether the coordinate system is inertial', () => {
+    expect(stateVector.inertial).toMatchSnapshot();
+  });
+
+  // fromClassicalElements
+  it('should create a TEME coordinate from classical orbital elements', () => {
+    const epoch = EpochUTC.fromDateTime(exampleDate);
+    const elements = new ClassicalElements({
+      epoch,
+      semimajorAxis: 6943.547853722985 as Kilometers,
+      eccentricity: 0.0011235968124658146,
+      inclination: 0.7509087232045765 as Radians,
+      rightAscension: 0.028239555738616327 as Radians,
+      argPerigee: 2.5386411901807353 as Radians,
+      trueAnomaly: 0.5931399364974058 as Radians,
+    });
+
+    expect(TEME.fromClassicalElements(elements)).toMatchSnapshot();
+  });
+
+  // toJ2000
+  it('should convert the TEME coordinates to J2000 coordinates', () => {
+    expect(stateVector.toJ2000()).toMatchSnapshot();
+  });
+});

test/coordinate/Tle.test.ts

@@ -0,0 +1,84 @@
+import { exampleDate } from '../lib/mockData';
+import { ClassicalElements, EpochUTC, Kilometers, Radians, Tle, TleLine1, TleLine2 } from '../../src/main';
+
+describe('Tle', () => {
+  let tle: Tle;
+
+  beforeEach(() => {
+    // Sample TLE
+    const tle1 = '1 56006U 23042W   24012.45049317  .00000296  00000-0  36967-4 0  9992' as TleLine1;
+    const tle2 = '2 56006 143.0043  13.3620 0001137 267.5965  92.4747 15.02542972 44491' as TleLine2;
+
+    tle = new Tle(tle1, tle2);
+  });
+
+  // toString
+  it('should return the TLE as a string', () => {
+    expect(tle.toString()).toMatchSnapshot();
+  });
+
+  // semiMajorAxis
+  it('should return the semi-major axis', () => {
+    expect(tle.semimajorAxis).toMatchSnapshot();
+  });
+
+  // eccentricity
+  it('should return the eccentricity', () => {
+    expect(tle.eccentricity).toMatchSnapshot();
+  });
+
+  // inclination
+  it('should return the inclination', () => {
+    expect(tle.inclination).toMatchSnapshot();
+  });
+
+  // inclinationDeg
+  it('should return the inclination in degrees', () => {
+    expect(tle.inclinationDegrees).toMatchSnapshot();
+  });
+
+  // apogee
+  it('should return the apogee', () => {
+    expect(tle.apogee).toMatchSnapshot();
+  });
+
+  // perigee
+  it('should return the perigee', () => {
+    expect(tle.perigee).toMatchSnapshot();
+  });
+
+  // period
+  it('should return the period', () => {
+    expect(tle.period).toMatchSnapshot();
+  });
+
+  // propagate
+  it('should propagate the TLE', () => {
+    const epoch = EpochUTC.fromDateTime(exampleDate);
+    const propagated = tle.propagate(epoch);
+
+    expect(propagated).toMatchSnapshot();
+  });
+
+  // state
+  it('should return the state vector', () => {
+    expect(tle.state).toMatchSnapshot();
+  });
+
+  // fromClassicalElements
+  it('should create a TLE from classical orbital elements', () => {
+    const epoch = EpochUTC.fromDateTime(exampleDate);
+    const elements = new ClassicalElements({
+      epoch,
+      semimajorAxis: 6943.547853722985 as Kilometers,
+      eccentricity: 0.0011235968124658146,
+      inclination: 0.7509087232045765 as Radians,
+      rightAscension: 0.028239555738616327 as Radians,
+      argPerigee: 2.5386411901807353 as Radians,
+      trueAnomaly: 0.5931399364974058 as Radians,
+    });
+    const tle = Tle.fromClassicalElements(elements);
+
+    expect(tle).toMatchSnapshot();
+  });
+});

test/coordinate/__snapshots__/ClassicalElements.test.ts.snap

@@ -14,7 +14,7 @@ exports[`ClassicalElements should calculate the orbit regime of ClassicalElement
 
 exports[`ClassicalElements should calculate the perigee of ClassicalElements 1`] = `6935.746105487338`;
 
-exports[`ClassicalElements should calculate the period of ClassicalElements 1`] = `5758.152068066809`;
+exports[`ClassicalElements should calculate the period of ClassicalElements 1`] = `95.96920113444682`;
 
 exports[`ClassicalElements should calculate true anomaly in degrees 1`] = `33.984415021959016`;
 

test/coordinate/__snapshots__/EquinoctialElements.test.ts.snap

@@ -68,9 +68,9 @@ exports[`ClassicalElements should return the mean motion 1`] = `0.00109302064133
 
 exports[`ClassicalElements should return the mean motion 2`] = `0.0010926340790517568`;
 
-exports[`ClassicalElements should return the period 1`] = `5748.459882237341`;
+exports[`ClassicalElements should return the period 1`] = `95.80766470395568`;
 
-exports[`ClassicalElements should return the period 2`] = `5750.493626038512`;
+exports[`ClassicalElements should return the period 2`] = `95.8415604339752`;
 
 exports[`ClassicalElements should return the retrograde factor 1`] = `1`;
 

test/coordinate/__snapshots__/TEME.test.ts.snap

@@ -0,0 +1,41 @@
+// Jest Snapshot v1, https://goo.gl/fbAQLP
+
+exports[`TEME should convert the TEME coordinates to J2000 coordinates 1`] = `
+J2000 {
+  "epoch": EpochUTC {
+    "posix": 1705109326.817,
+  },
+  "position": Vector3D {
+    "x": 1538.2233358428946,
+    "y": 5102.2612040219665,
+    "z": 4432.634965003576,
+  },
+  "velocity": Vector3D {
+    "x": -7.341518909379303,
+    "y": 0.6516718453998649,
+    "z": 1.793388249986199,
+  },
+}
+`;
+
+exports[`TEME should create a TEME coordinate from classical orbital elements 1`] = `
+TEME {
+  "epoch": EpochUTC {
+    "posix": 1705109326.817,
+  },
+  "position": Vector3D {
+    "x": -6935.3813042612455,
+    "y": -146.1261328371035,
+    "z": 46.43907991639276,
+  },
+  "velocity": Vector3D {
+    "x": 0.07740377357485445,
+    "y": -5.543955093986134,
+    "z": -5.174123893746047,
+  },
+}
+`;
+
+exports[`TEME should return the name of the coordinate system 1`] = `"TEME"`;
+
+exports[`TEME should return whether the coordinate system is inertial 1`] = `true`;