-
Notifications
You must be signed in to change notification settings - Fork 3.4k
/
Simon1994PlanetaryPositions.js
682 lines (609 loc) · 22.1 KB
/
Simon1994PlanetaryPositions.js
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
61
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
83
84
85
86
87
88
89
90
91
92
93
94
95
96
97
98
99
100
101
102
103
104
105
106
107
108
109
110
111
112
113
114
115
116
117
118
119
120
121
122
123
124
125
126
127
128
129
130
131
132
133
134
135
136
137
138
139
140
141
142
143
144
145
146
147
148
149
150
151
152
153
154
155
156
157
158
159
160
161
162
163
164
165
166
167
168
169
170
171
172
173
174
175
176
177
178
179
180
181
182
183
184
185
186
187
188
189
190
191
192
193
194
195
196
197
198
199
200
201
202
203
204
205
206
207
208
209
210
211
212
213
214
215
216
217
218
219
220
221
222
223
224
225
226
227
228
229
230
231
232
233
234
235
236
237
238
239
240
241
242
243
244
245
246
247
248
249
250
251
252
253
254
255
256
257
258
259
260
261
262
263
264
265
266
267
268
269
270
271
272
273
274
275
276
277
278
279
280
281
282
283
284
285
286
287
288
289
290
291
292
293
294
295
296
297
298
299
300
301
302
303
304
305
306
307
308
309
310
311
312
313
314
315
316
317
318
319
320
321
322
323
324
325
326
327
328
329
330
331
332
333
334
335
336
337
338
339
340
341
342
343
344
345
346
347
348
349
350
351
352
353
354
355
356
357
358
359
360
361
362
363
364
365
366
367
368
369
370
371
372
373
374
375
376
377
378
379
380
381
382
383
384
385
386
387
388
389
390
391
392
393
394
395
396
397
398
399
400
401
402
403
404
405
406
407
408
409
410
411
412
413
414
415
416
417
418
419
420
421
422
423
424
425
426
427
428
429
430
431
432
433
434
435
436
437
438
439
440
441
442
443
444
445
446
447
448
449
450
451
452
453
454
455
456
457
458
459
460
461
462
463
464
465
466
467
468
469
470
471
472
473
474
475
476
477
478
479
480
481
482
483
484
485
486
487
488
489
490
491
492
493
494
495
496
497
498
499
500
501
502
503
504
505
506
507
508
509
510
511
512
513
514
515
516
517
518
519
520
521
522
523
524
525
526
527
528
529
530
531
532
533
534
535
536
537
538
539
540
541
542
543
544
545
546
547
548
549
550
551
552
553
554
555
556
557
558
559
560
561
562
563
564
565
566
567
568
569
570
571
572
573
574
575
576
577
578
579
580
581
582
583
584
585
586
587
588
589
590
591
592
593
594
595
596
597
598
599
600
601
602
603
604
605
606
607
608
609
610
611
612
613
614
615
616
617
618
619
620
621
622
623
624
625
626
627
628
629
630
631
632
633
634
635
636
637
638
639
640
641
642
643
644
645
646
647
648
649
650
651
652
653
654
655
656
657
658
659
660
661
662
663
664
665
666
667
668
669
670
671
672
673
674
675
676
677
678
679
680
681
682
import Cartesian3 from "./Cartesian3.js";
import defined from "./defined.js";
import DeveloperError from "./DeveloperError.js";
import JulianDate from "./JulianDate.js";
import CesiumMath from "./Math.js";
import Matrix3 from "./Matrix3.js";
import TimeConstants from "./TimeConstants.js";
import TimeStandard from "./TimeStandard.js";
/**
* Contains functions for finding the Cartesian coordinates of the sun and the moon in the
* Earth-centered inertial frame.
*
* @namespace Simon1994PlanetaryPositions
*/
const Simon1994PlanetaryPositions = {};
function computeTdbMinusTtSpice(daysSinceJ2000InTerrestrialTime) {
/* STK Comments ------------------------------------------------------
* This function uses constants designed to be consistent with
* the SPICE Toolkit from JPL version N0051 (unitim.c)
* M0 = 6.239996
* M0Dot = 1.99096871e-7 rad/s = 0.01720197 rad/d
* EARTH_ECC = 1.671e-2
* TDB_AMPL = 1.657e-3 secs
*--------------------------------------------------------------------*/
//* Values taken as specified in STK Comments except: 0.01720197 rad/day = 1.99096871e-7 rad/sec
//* Here we use the more precise value taken from the SPICE value 1.99096871e-7 rad/sec converted to rad/day
//* All other constants are consistent with the SPICE implementation of the TDB conversion
//* except where we treat the independent time parameter to be in TT instead of TDB.
//* This is an approximation made to facilitate performance due to the higher prevalance of
//* the TT2TDB conversion over TDB2TT in order to avoid having to iterate when converting to TDB for the JPL ephemeris.
//* Days are used instead of seconds to provide a slight improvement in numerical precision.
//* For more information see:
//* http://www.cv.nrao.edu/~rfisher/Ephemerides/times.html#TDB
//* ftp://ssd.jpl.nasa.gov/pub/eph/planets/ioms/ExplSupplChap8.pdf
const g = 6.239996 + 0.0172019696544 * daysSinceJ2000InTerrestrialTime;
return 1.657e-3 * Math.sin(g + 1.671e-2 * Math.sin(g));
}
const TdtMinusTai = 32.184;
const J2000d = 2451545;
function taiToTdb(date, result) {
//Converts TAI to TT
result = JulianDate.addSeconds(date, TdtMinusTai, result);
//Converts TT to TDB
const days = JulianDate.totalDays(result) - J2000d;
result = JulianDate.addSeconds(result, computeTdbMinusTtSpice(days), result);
return result;
}
const epoch = new JulianDate(2451545, 0, TimeStandard.TAI); //Actually TDB (not TAI)
const MetersPerKilometer = 1000.0;
const RadiansPerDegree = CesiumMath.RADIANS_PER_DEGREE;
const RadiansPerArcSecond = CesiumMath.RADIANS_PER_ARCSECOND;
const MetersPerAstronomicalUnit = 1.4959787e11; // IAU 1976 value
const perifocalToEquatorial = new Matrix3();
function elementsToCartesian(
semimajorAxis,
eccentricity,
inclination,
longitudeOfPerigee,
longitudeOfNode,
meanLongitude,
result
) {
if (inclination < 0.0) {
inclination = -inclination;
longitudeOfNode += CesiumMath.PI;
}
//>>includeStart('debug', pragmas.debug);
if (inclination < 0 || inclination > CesiumMath.PI) {
throw new DeveloperError(
"The inclination is out of range. Inclination must be greater than or equal to zero and less than or equal to Pi radians."
);
}
//>>includeEnd('debug')
const radiusOfPeriapsis = semimajorAxis * (1.0 - eccentricity);
const argumentOfPeriapsis = longitudeOfPerigee - longitudeOfNode;
const rightAscensionOfAscendingNode = longitudeOfNode;
const trueAnomaly = meanAnomalyToTrueAnomaly(
meanLongitude - longitudeOfPerigee,
eccentricity
);
const type = chooseOrbit(eccentricity, 0.0);
//>>includeStart('debug', pragmas.debug);
if (
type === "Hyperbolic" &&
Math.abs(CesiumMath.negativePiToPi(trueAnomaly)) >=
Math.acos(-1.0 / eccentricity)
) {
throw new DeveloperError(
"The true anomaly of the hyperbolic orbit lies outside of the bounds of the hyperbola."
);
}
//>>includeEnd('debug')
perifocalToCartesianMatrix(
argumentOfPeriapsis,
inclination,
rightAscensionOfAscendingNode,
perifocalToEquatorial
);
const semilatus = radiusOfPeriapsis * (1.0 + eccentricity);
const costheta = Math.cos(trueAnomaly);
const sintheta = Math.sin(trueAnomaly);
const denom = 1.0 + eccentricity * costheta;
//>>includeStart('debug', pragmas.debug);
if (denom <= CesiumMath.Epsilon10) {
throw new DeveloperError("elements cannot be converted to cartesian");
}
//>>includeEnd('debug')
const radius = semilatus / denom;
if (!defined(result)) {
result = new Cartesian3(radius * costheta, radius * sintheta, 0.0);
} else {
result.x = radius * costheta;
result.y = radius * sintheta;
result.z = 0.0;
}
return Matrix3.multiplyByVector(perifocalToEquatorial, result, result);
}
function chooseOrbit(eccentricity, tolerance) {
//>>includeStart('debug', pragmas.debug);
if (eccentricity < 0) {
throw new DeveloperError("eccentricity cannot be negative.");
}
//>>includeEnd('debug')
if (eccentricity <= tolerance) {
return "Circular";
} else if (eccentricity < 1.0 - tolerance) {
return "Elliptical";
} else if (eccentricity <= 1.0 + tolerance) {
return "Parabolic";
}
return "Hyperbolic";
}
// Calculates the true anomaly given the mean anomaly and the eccentricity.
function meanAnomalyToTrueAnomaly(meanAnomaly, eccentricity) {
//>>includeStart('debug', pragmas.debug);
if (eccentricity < 0.0 || eccentricity >= 1.0) {
throw new DeveloperError("eccentricity out of range.");
}
//>>includeEnd('debug')
const eccentricAnomaly = meanAnomalyToEccentricAnomaly(
meanAnomaly,
eccentricity
);
return eccentricAnomalyToTrueAnomaly(eccentricAnomaly, eccentricity);
}
const maxIterationCount = 50;
const keplerEqConvergence = CesiumMath.EPSILON8;
// Calculates the eccentric anomaly given the mean anomaly and the eccentricity.
function meanAnomalyToEccentricAnomaly(meanAnomaly, eccentricity) {
//>>includeStart('debug', pragmas.debug);
if (eccentricity < 0.0 || eccentricity >= 1.0) {
throw new DeveloperError("eccentricity out of range.");
}
//>>includeEnd('debug')
const revs = Math.floor(meanAnomaly / CesiumMath.TWO_PI);
// Find angle in current revolution
meanAnomaly -= revs * CesiumMath.TWO_PI;
// calculate starting value for iteration sequence
let iterationValue =
meanAnomaly +
(eccentricity * Math.sin(meanAnomaly)) /
(1.0 - Math.sin(meanAnomaly + eccentricity) + Math.sin(meanAnomaly));
// Perform Newton-Raphson iteration on Kepler's equation
let eccentricAnomaly = Number.MAX_VALUE;
let count;
for (
count = 0;
count < maxIterationCount &&
Math.abs(eccentricAnomaly - iterationValue) > keplerEqConvergence;
++count
) {
eccentricAnomaly = iterationValue;
const NRfunction =
eccentricAnomaly -
eccentricity * Math.sin(eccentricAnomaly) -
meanAnomaly;
const dNRfunction = 1 - eccentricity * Math.cos(eccentricAnomaly);
iterationValue = eccentricAnomaly - NRfunction / dNRfunction;
}
//>>includeStart('debug', pragmas.debug);
if (count >= maxIterationCount) {
throw new DeveloperError("Kepler equation did not converge");
// STK Components uses a numerical method to find the eccentric anomaly in the case that Kepler's
// equation does not converge. We don't expect that to ever be necessary for the reasonable orbits used here.
}
//>>includeEnd('debug')
eccentricAnomaly = iterationValue + revs * CesiumMath.TWO_PI;
return eccentricAnomaly;
}
// Calculates the true anomaly given the eccentric anomaly and the eccentricity.
function eccentricAnomalyToTrueAnomaly(eccentricAnomaly, eccentricity) {
//>>includeStart('debug', pragmas.debug);
if (eccentricity < 0.0 || eccentricity >= 1.0) {
throw new DeveloperError("eccentricity out of range.");
}
//>>includeEnd('debug')
// Calculate the number of previous revolutions
const revs = Math.floor(eccentricAnomaly / CesiumMath.TWO_PI);
// Find angle in current revolution
eccentricAnomaly -= revs * CesiumMath.TWO_PI;
// Calculate true anomaly from eccentric anomaly
const trueAnomalyX = Math.cos(eccentricAnomaly) - eccentricity;
const trueAnomalyY =
Math.sin(eccentricAnomaly) * Math.sqrt(1 - eccentricity * eccentricity);
let trueAnomaly = Math.atan2(trueAnomalyY, trueAnomalyX);
// Ensure the correct quadrant
trueAnomaly = CesiumMath.zeroToTwoPi(trueAnomaly);
if (eccentricAnomaly < 0) {
trueAnomaly -= CesiumMath.TWO_PI;
}
// Add on previous revolutions
trueAnomaly += revs * CesiumMath.TWO_PI;
return trueAnomaly;
}
// Calculates the transformation matrix to convert from the perifocal (PQW) coordinate
// system to inertial cartesian coordinates.
function perifocalToCartesianMatrix(
argumentOfPeriapsis,
inclination,
rightAscension,
result
) {
//>>includeStart('debug', pragmas.debug);
if (inclination < 0 || inclination > CesiumMath.PI) {
throw new DeveloperError("inclination out of range");
}
//>>includeEnd('debug')
const cosap = Math.cos(argumentOfPeriapsis);
const sinap = Math.sin(argumentOfPeriapsis);
const cosi = Math.cos(inclination);
const sini = Math.sin(inclination);
const cosraan = Math.cos(rightAscension);
const sinraan = Math.sin(rightAscension);
if (!defined(result)) {
result = new Matrix3(
cosraan * cosap - sinraan * sinap * cosi,
-cosraan * sinap - sinraan * cosap * cosi,
sinraan * sini,
sinraan * cosap + cosraan * sinap * cosi,
-sinraan * sinap + cosraan * cosap * cosi,
-cosraan * sini,
sinap * sini,
cosap * sini,
cosi
);
} else {
result[0] = cosraan * cosap - sinraan * sinap * cosi;
result[1] = sinraan * cosap + cosraan * sinap * cosi;
result[2] = sinap * sini;
result[3] = -cosraan * sinap - sinraan * cosap * cosi;
result[4] = -sinraan * sinap + cosraan * cosap * cosi;
result[5] = cosap * sini;
result[6] = sinraan * sini;
result[7] = -cosraan * sini;
result[8] = cosi;
}
return result;
}
// From section 5.8
const semiMajorAxis0 = 1.0000010178 * MetersPerAstronomicalUnit;
const meanLongitude0 = 100.46645683 * RadiansPerDegree;
const meanLongitude1 = 1295977422.83429 * RadiansPerArcSecond;
// From table 6
const p1u = 16002;
const p2u = 21863;
const p3u = 32004;
const p4u = 10931;
const p5u = 14529;
const p6u = 16368;
const p7u = 15318;
const p8u = 32794;
const Ca1 = 64 * 1e-7 * MetersPerAstronomicalUnit;
const Ca2 = -152 * 1e-7 * MetersPerAstronomicalUnit;
const Ca3 = 62 * 1e-7 * MetersPerAstronomicalUnit;
const Ca4 = -8 * 1e-7 * MetersPerAstronomicalUnit;
const Ca5 = 32 * 1e-7 * MetersPerAstronomicalUnit;
const Ca6 = -41 * 1e-7 * MetersPerAstronomicalUnit;
const Ca7 = 19 * 1e-7 * MetersPerAstronomicalUnit;
const Ca8 = -11 * 1e-7 * MetersPerAstronomicalUnit;
const Sa1 = -150 * 1e-7 * MetersPerAstronomicalUnit;
const Sa2 = -46 * 1e-7 * MetersPerAstronomicalUnit;
const Sa3 = 68 * 1e-7 * MetersPerAstronomicalUnit;
const Sa4 = 54 * 1e-7 * MetersPerAstronomicalUnit;
const Sa5 = 14 * 1e-7 * MetersPerAstronomicalUnit;
const Sa6 = 24 * 1e-7 * MetersPerAstronomicalUnit;
const Sa7 = -28 * 1e-7 * MetersPerAstronomicalUnit;
const Sa8 = 22 * 1e-7 * MetersPerAstronomicalUnit;
const q1u = 10;
const q2u = 16002;
const q3u = 21863;
const q4u = 10931;
const q5u = 1473;
const q6u = 32004;
const q7u = 4387;
const q8u = 73;
const Cl1 = -325 * 1e-7;
const Cl2 = -322 * 1e-7;
const Cl3 = -79 * 1e-7;
const Cl4 = 232 * 1e-7;
const Cl5 = -52 * 1e-7;
const Cl6 = 97 * 1e-7;
const Cl7 = 55 * 1e-7;
const Cl8 = -41 * 1e-7;
const Sl1 = -105 * 1e-7;
const Sl2 = -137 * 1e-7;
const Sl3 = 258 * 1e-7;
const Sl4 = 35 * 1e-7;
const Sl5 = -116 * 1e-7;
const Sl6 = -88 * 1e-7;
const Sl7 = -112 * 1e-7;
const Sl8 = -80 * 1e-7;
const scratchDate = new JulianDate(0, 0.0, TimeStandard.TAI);
// Gets a point describing the motion of the Earth-Moon barycenter according to the equations described in section 6.
function computeSimonEarthMoonBarycenter(date, result) {
// t is thousands of years from J2000 TDB
taiToTdb(date, scratchDate);
const x =
scratchDate.dayNumber -
epoch.dayNumber +
(scratchDate.secondsOfDay - epoch.secondsOfDay) /
TimeConstants.SECONDS_PER_DAY;
const t = x / (TimeConstants.DAYS_PER_JULIAN_CENTURY * 10.0);
const u = 0.3595362 * t;
const semimajorAxis =
semiMajorAxis0 +
Ca1 * Math.cos(p1u * u) +
Sa1 * Math.sin(p1u * u) +
Ca2 * Math.cos(p2u * u) +
Sa2 * Math.sin(p2u * u) +
Ca3 * Math.cos(p3u * u) +
Sa3 * Math.sin(p3u * u) +
Ca4 * Math.cos(p4u * u) +
Sa4 * Math.sin(p4u * u) +
Ca5 * Math.cos(p5u * u) +
Sa5 * Math.sin(p5u * u) +
Ca6 * Math.cos(p6u * u) +
Sa6 * Math.sin(p6u * u) +
Ca7 * Math.cos(p7u * u) +
Sa7 * Math.sin(p7u * u) +
Ca8 * Math.cos(p8u * u) +
Sa8 * Math.sin(p8u * u);
const meanLongitude =
meanLongitude0 +
meanLongitude1 * t +
Cl1 * Math.cos(q1u * u) +
Sl1 * Math.sin(q1u * u) +
Cl2 * Math.cos(q2u * u) +
Sl2 * Math.sin(q2u * u) +
Cl3 * Math.cos(q3u * u) +
Sl3 * Math.sin(q3u * u) +
Cl4 * Math.cos(q4u * u) +
Sl4 * Math.sin(q4u * u) +
Cl5 * Math.cos(q5u * u) +
Sl5 * Math.sin(q5u * u) +
Cl6 * Math.cos(q6u * u) +
Sl6 * Math.sin(q6u * u) +
Cl7 * Math.cos(q7u * u) +
Sl7 * Math.sin(q7u * u) +
Cl8 * Math.cos(q8u * u) +
Sl8 * Math.sin(q8u * u);
// All constants in this part are from section 5.8
const eccentricity = 0.0167086342 - 0.0004203654 * t;
const longitudeOfPerigee =
102.93734808 * RadiansPerDegree + 11612.3529 * RadiansPerArcSecond * t;
const inclination = 469.97289 * RadiansPerArcSecond * t;
const longitudeOfNode =
174.87317577 * RadiansPerDegree - 8679.27034 * RadiansPerArcSecond * t;
return elementsToCartesian(
semimajorAxis,
eccentricity,
inclination,
longitudeOfPerigee,
longitudeOfNode,
meanLongitude,
result
);
}
// Gets a point describing the position of the moon according to the equations described in section 4.
function computeSimonMoon(date, result) {
taiToTdb(date, scratchDate);
const x =
scratchDate.dayNumber -
epoch.dayNumber +
(scratchDate.secondsOfDay - epoch.secondsOfDay) /
TimeConstants.SECONDS_PER_DAY;
const t = x / TimeConstants.DAYS_PER_JULIAN_CENTURY;
const t2 = t * t;
const t3 = t2 * t;
const t4 = t3 * t;
// Terms from section 3.4 (b.1)
let semimajorAxis = 383397.7725 + 0.004 * t;
let eccentricity = 0.055545526 - 0.000000016 * t;
const inclinationConstant = 5.15668983 * RadiansPerDegree;
let inclinationSecPart =
-0.00008 * t + 0.02966 * t2 - 0.000042 * t3 - 0.00000013 * t4;
const longitudeOfPerigeeConstant = 83.35324312 * RadiansPerDegree;
let longitudeOfPerigeeSecPart =
14643420.2669 * t - 38.2702 * t2 - 0.045047 * t3 + 0.00021301 * t4;
const longitudeOfNodeConstant = 125.04455501 * RadiansPerDegree;
let longitudeOfNodeSecPart =
-6967919.3631 * t + 6.3602 * t2 + 0.007625 * t3 - 0.00003586 * t4;
const meanLongitudeConstant = 218.31664563 * RadiansPerDegree;
let meanLongitudeSecPart =
1732559343.4847 * t - 6.391 * t2 + 0.006588 * t3 - 0.00003169 * t4;
// Delaunay arguments from section 3.5 b
const D =
297.85019547 * RadiansPerDegree +
RadiansPerArcSecond *
(1602961601.209 * t - 6.3706 * t2 + 0.006593 * t3 - 0.00003169 * t4);
const F =
93.27209062 * RadiansPerDegree +
RadiansPerArcSecond *
(1739527262.8478 * t - 12.7512 * t2 - 0.001037 * t3 + 0.00000417 * t4);
const l =
134.96340251 * RadiansPerDegree +
RadiansPerArcSecond *
(1717915923.2178 * t + 31.8792 * t2 + 0.051635 * t3 - 0.0002447 * t4);
const lprime =
357.52910918 * RadiansPerDegree +
RadiansPerArcSecond *
(129596581.0481 * t - 0.5532 * t2 + 0.000136 * t3 - 0.00001149 * t4);
const psi =
310.17137918 * RadiansPerDegree -
RadiansPerArcSecond *
(6967051.436 * t + 6.2068 * t2 + 0.007618 * t3 - 0.00003219 * t4);
// Add terms from Table 4
const twoD = 2.0 * D;
const fourD = 4.0 * D;
const sixD = 6.0 * D;
const twol = 2.0 * l;
const threel = 3.0 * l;
const fourl = 4.0 * l;
const twoF = 2.0 * F;
semimajorAxis +=
3400.4 * Math.cos(twoD) -
635.6 * Math.cos(twoD - l) -
235.6 * Math.cos(l) +
218.1 * Math.cos(twoD - lprime) +
181.0 * Math.cos(twoD + l);
eccentricity +=
0.014216 * Math.cos(twoD - l) +
0.008551 * Math.cos(twoD - twol) -
0.001383 * Math.cos(l) +
0.001356 * Math.cos(twoD + l) -
0.001147 * Math.cos(fourD - threel) -
0.000914 * Math.cos(fourD - twol) +
0.000869 * Math.cos(twoD - lprime - l) -
0.000627 * Math.cos(twoD) -
0.000394 * Math.cos(fourD - fourl) +
0.000282 * Math.cos(twoD - lprime - twol) -
0.000279 * Math.cos(D - l) -
0.000236 * Math.cos(twol) +
0.000231 * Math.cos(fourD) +
0.000229 * Math.cos(sixD - fourl) -
0.000201 * Math.cos(twol - twoF);
inclinationSecPart +=
486.26 * Math.cos(twoD - twoF) -
40.13 * Math.cos(twoD) +
37.51 * Math.cos(twoF) +
25.73 * Math.cos(twol - twoF) +
19.97 * Math.cos(twoD - lprime - twoF);
longitudeOfPerigeeSecPart +=
-55609 * Math.sin(twoD - l) -
34711 * Math.sin(twoD - twol) -
9792 * Math.sin(l) +
9385 * Math.sin(fourD - threel) +
7505 * Math.sin(fourD - twol) +
5318 * Math.sin(twoD + l) +
3484 * Math.sin(fourD - fourl) -
3417 * Math.sin(twoD - lprime - l) -
2530 * Math.sin(sixD - fourl) -
2376 * Math.sin(twoD) -
2075 * Math.sin(twoD - threel) -
1883 * Math.sin(twol) -
1736 * Math.sin(sixD - 5.0 * l) +
1626 * Math.sin(lprime) -
1370 * Math.sin(sixD - threel);
longitudeOfNodeSecPart +=
-5392 * Math.sin(twoD - twoF) -
540 * Math.sin(lprime) -
441 * Math.sin(twoD) +
423 * Math.sin(twoF) -
288 * Math.sin(twol - twoF);
meanLongitudeSecPart +=
-3332.9 * Math.sin(twoD) +
1197.4 * Math.sin(twoD - l) -
662.5 * Math.sin(lprime) +
396.3 * Math.sin(l) -
218.0 * Math.sin(twoD - lprime);
// Add terms from Table 5
const twoPsi = 2.0 * psi;
const threePsi = 3.0 * psi;
inclinationSecPart +=
46.997 * Math.cos(psi) * t -
0.614 * Math.cos(twoD - twoF + psi) * t +
0.614 * Math.cos(twoD - twoF - psi) * t -
0.0297 * Math.cos(twoPsi) * t2 -
0.0335 * Math.cos(psi) * t2 +
0.0012 * Math.cos(twoD - twoF + twoPsi) * t2 -
0.00016 * Math.cos(psi) * t3 +
0.00004 * Math.cos(threePsi) * t3 +
0.00004 * Math.cos(twoPsi) * t3;
const perigeeAndMean =
2.116 * Math.sin(psi) * t -
0.111 * Math.sin(twoD - twoF - psi) * t -
0.0015 * Math.sin(psi) * t2;
longitudeOfPerigeeSecPart += perigeeAndMean;
meanLongitudeSecPart += perigeeAndMean;
longitudeOfNodeSecPart +=
-520.77 * Math.sin(psi) * t +
13.66 * Math.sin(twoD - twoF + psi) * t +
1.12 * Math.sin(twoD - psi) * t -
1.06 * Math.sin(twoF - psi) * t +
0.66 * Math.sin(twoPsi) * t2 +
0.371 * Math.sin(psi) * t2 -
0.035 * Math.sin(twoD - twoF + twoPsi) * t2 -
0.015 * Math.sin(twoD - twoF + psi) * t2 +
0.0014 * Math.sin(psi) * t3 -
0.0011 * Math.sin(threePsi) * t3 -
0.0009 * Math.sin(twoPsi) * t3;
// Add constants and convert units
semimajorAxis *= MetersPerKilometer;
const inclination =
inclinationConstant + inclinationSecPart * RadiansPerArcSecond;
const longitudeOfPerigee =
longitudeOfPerigeeConstant +
longitudeOfPerigeeSecPart * RadiansPerArcSecond;
const meanLongitude =
meanLongitudeConstant + meanLongitudeSecPart * RadiansPerArcSecond;
const longitudeOfNode =
longitudeOfNodeConstant + longitudeOfNodeSecPart * RadiansPerArcSecond;
return elementsToCartesian(
semimajorAxis,
eccentricity,
inclination,
longitudeOfPerigee,
longitudeOfNode,
meanLongitude,
result
);
}
// Gets a point describing the motion of the Earth. This point uses the Moon point and
// the 1992 mu value (ratio between Moon and Earth masses) in Table 2 of the paper in order
// to determine the position of the Earth relative to the Earth-Moon barycenter.
const moonEarthMassRatio = 0.012300034; // From 1992 mu value in Table 2
const factor = (moonEarthMassRatio / (moonEarthMassRatio + 1.0)) * -1;
function computeSimonEarth(date, result) {
result = computeSimonMoon(date, result);
return Cartesian3.multiplyByScalar(result, factor, result);
}
// Values for the <code>axesTransformation</code> needed for the rotation were found using the STK Components
// GreographicTransformer on the position of the sun center of mass point and the earth J2000 frame.
const axesTransformation = new Matrix3(
1.0000000000000002,
5.619723173785822e-16,
4.690511510146299e-19,
-5.154129427414611e-16,
0.9174820620691819,
-0.39777715593191376,
-2.23970096136568e-16,
0.39777715593191376,
0.9174820620691819
);
let translation = new Cartesian3();
/**
* Computes the position of the Sun in the Earth-centered inertial frame
*
* @param {JulianDate} [julianDate] The time at which to compute the Sun's position, if not provided the current system time is used.
* @param {Cartesian3} [result] The object onto which to store the result.
* @returns {Cartesian3} Calculated sun position
*/
Simon1994PlanetaryPositions.computeSunPositionInEarthInertialFrame = function (
julianDate,
result
) {
if (!defined(julianDate)) {
julianDate = JulianDate.now();
}
if (!defined(result)) {
result = new Cartesian3();
}
//first forward transformation
translation = computeSimonEarthMoonBarycenter(julianDate, translation);
result = Cartesian3.negate(translation, result);
//second forward transformation
computeSimonEarth(julianDate, translation);
Cartesian3.subtract(result, translation, result);
Matrix3.multiplyByVector(axesTransformation, result, result);
return result;
};
/**
* Computes the position of the Moon in the Earth-centered inertial frame
*
* @param {JulianDate} [julianDate] The time at which to compute the Sun's position, if not provided the current system time is used.
* @param {Cartesian3} [result] The object onto which to store the result.
* @returns {Cartesian3} Calculated moon position
*/
Simon1994PlanetaryPositions.computeMoonPositionInEarthInertialFrame = function (
julianDate,
result
) {
if (!defined(julianDate)) {
julianDate = JulianDate.now();
}
result = computeSimonMoon(julianDate, result);
Matrix3.multiplyByVector(axesTransformation, result, result);
return result;
};
export default Simon1994PlanetaryPositions;