/
ReturnFromMoonTests.cs
164 lines (134 loc) · 8.03 KB
/
ReturnFromMoonTests.cs
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
using System;
using MechJebLib.Functions;
using MechJebLib.Maneuvers;
using MechJebLib.Primitives;
using MechJebLib.TwoBody;
using MechJebLib.Utils;
using Xunit;
using Xunit.Abstractions;
using static System.Math;
using static MechJebLib.Utils.Statics;
namespace MechJebLibTest.ManeuversTests
{
public class ReturnFromMoonTests
{
private readonly ITestOutputHelper _testOutputHelper;
public ReturnFromMoonTests(ITestOutputHelper testOutputHelper)
{
_testOutputHelper = testOutputHelper;
}
[Fact]
private void NextManeuverToReturnFromMoonRandomTest()
{
// this forces JIT compilation(?) of the SQL solver which takes ~250ms
ChangeOrbitalElement.ChangePeriapsis(1.0, new V3(1, 0, 0), new V3(0, 1.0, 0), 1.0);
var solver = new ReturnFromMoon();
Logger.Register(o => _testOutputHelper.WriteLine((string)o));
const double CENTRAL_MU = 398600435436096;
const double MOON_MU = 4902800066163.8;
var moonR0 = new V3(325420116.073166, -166367503.579338, -138858150.96145);
var moonV0 = new V3(577.012296778094, 761.848508254181, 297.464594270612);
const double MOON_SOI = 66167158.6569544;
const double MOON_SURFACE = 3474 * 1000; // 3,474 km
const double PER = 6.3781e6 + 60000; // PeA = 60 km
var random = new Random();
// this test does randomly fail
for (int i = 0; i < 1; i++)
{
// FIXME: weakly bound orbits give the algorithm problems.
double per = (MOON_SOI * 0.6 - MOON_SURFACE) * random.NextDouble() + MOON_SURFACE;
double apr = (MOON_SOI * 0.6 - MOON_SURFACE) * random.NextDouble() + MOON_SURFACE;
if (per > apr)
(per, apr) = (apr, per);
double l = 1 / (0.5 * (1 / apr + 1 / per));
double ecc = (apr - per) / (apr + per);
double inc = PI * random.NextDouble();
double lan = TAU * random.NextDouble();
double argp = TAU * random.NextDouble();
double nu = TAU * random.NextDouble();
(V3 r0, V3 v0) = Astro.StateVectorsFromKeplerian(MOON_MU, l, ecc, inc, lan, argp, nu);
_testOutputHelper.WriteLine($"iteration: {i}");
(V3 dv, double dt, double newPeR) =
solver.NextManeuver(398600435436096, 4902800066163.8, moonR0, moonV0, 66167158.6569544, r0, v0, PER, 0);
(V3 r1, V3 v1) = Shepperd.Solve(MOON_MU, dt, r0, v0);
double tt1 = Astro.TimeToNextRadius(MOON_MU, r1, v1 + dv, MOON_SOI);
(V3 r2, V3 v2) = Shepperd.Solve(MOON_MU, tt1, r1, v1 + dv);
(V3 moonR2, V3 moonV2) = Shepperd.Solve(CENTRAL_MU, dt + tt1, moonR0, moonV0);
V3 r3 = moonR2 + r2;
V3 v3 = moonV2 + v2;
_testOutputHelper.WriteLine($"periapsis: {Astro.PeriapsisFromStateVectors(CENTRAL_MU, r3, v3)}");
Astro.PeriapsisFromStateVectors(CENTRAL_MU, r3, v3).ShouldEqual(PER, 1e-2);
newPeR.ShouldEqual(PER, 1e-2);
}
}
[Fact]
private void NextManeuverToReturnFromMoonOptguardTest()
{
// this forces JIT compilation(?) of the SQL solver which takes ~250ms
ChangeOrbitalElement.ChangePeriapsis(1.0, new V3(1, 0, 0), new V3(0, 1.0, 0), 1.0);
var solver = new ReturnFromMoon();
Logger.Register(o => _testOutputHelper.WriteLine((string)o));
const double CENTRAL_MU = 398600435436096;
const double MOON_MU = 4902800066163.8;
var moonR0 = new V3(325420116.073166, -166367503.579338, -138858150.96145);
var moonV0 = new V3(577.012296778094, 761.848508254181, 297.464594270612);
const double MOON_SOI = 66167158.6569544;
// this is a pretty reasonable circular equatorial lunar orbit
var r0 = new V3(4198676.73768844, 5187520.71497923, -3.29371833446352);
var v0 = new V3(-666.230112925872, 539.234048888927, 0.000277598267012666);
const double PER = 6.3781e6 + 60000; // 60km
(V3 dv, double dt, double newPeR) =
solver.NextManeuver(398600435436096, 4902800066163.8, moonR0, moonV0, 66167158.6569544, r0, v0, PER, 0, true);
(V3 r1, V3 v1) = Shepperd.Solve(MOON_MU, dt, r0, v0);
double tt1 = Astro.TimeToNextRadius(MOON_MU, r1, v1 + dv, MOON_SOI);
(V3 r2, V3 v2) = Shepperd.Solve(MOON_MU, tt1, r1, v1 + dv);
(V3 moonR2, V3 moonV2) = Shepperd.Solve(CENTRAL_MU, dt + tt1, moonR0, moonV0);
V3 r3 = moonR2 + r2;
V3 v3 = moonV2 + v2;
_testOutputHelper.WriteLine($"periapsis: {Astro.PeriapsisFromStateVectors(CENTRAL_MU, r3, v3)}");
Astro.PeriapsisFromStateVectors(CENTRAL_MU, r3, v3).ShouldEqual(PER, 1e-3);
newPeR.ShouldEqual(PER, 1e-3);
}
[Theory]
[InlineData(3033960.04435434, -538512.74449519, -1569171.01639252, 344.550626047212, -973.108221764261, 907.813925253141, 1062.48341419771)]
[InlineData(-23744.6019871556, -935848.195057236, -2970820.75826717, -511.683969531061, -141.692448007731, 975.982327934346,
1075.8211667678943)]
[InlineData(-1358340.16497667, -2896749.43027493, -2706207.90479207, 774.176044284448, -468.922061598358, -642.571722922182,
627.70157063181409)]
[InlineData(-2370135.82005065, -78770.3300753334, 504857.052794559, -735.735041897621, -590.266316007015, -137.364944041411,
563.130459005366)]
[InlineData(1922287.76973033, 1688857.60199125, -1128186.04080648, -644.272529354446, 90.1035308326145, -74.2516010414118, 1558.41290770448)]
[InlineData(1448096.6091073, 2242802.60448088, 593799.176165359, 316.818652356425, -684.168486708854, -453.106628476226, 1092.1980531031697)]
[InlineData(72567.8252483425, -1202508.27881747, 995820.818247795, 733.61121478193, -501.358138165138, -26.4032981481417, 1959.1953018440845)]
[InlineData(1105140.06213014, -8431008.05414815, -4729658.84487529, -293.374690393787, -1173.3597686151, -411.755491683683,
0)] // initial hyperbolic
public void NextManeuverToReturnFromMoonHard(double rx, double ry, double rz, double vx, double vy, double vz, double dvOpt)
{
// this forces JIT compilation(?) of the SQL solver which takes ~250ms
ChangeOrbitalElement.ChangePeriapsis(1.0, new V3(1, 0, 0), new V3(0, 1.0, 0), 1.0);
var solver = new ReturnFromMoon();
Logger.Register(o => _testOutputHelper.WriteLine((string)o));
const double CENTRAL_MU = 398600435436096;
const double MOON_MU = 4902800066163.8;
var moonR0 = new V3(325420116.073166, -166367503.579338, -138858150.96145);
var moonV0 = new V3(577.012296778094, 761.848508254181, 297.464594270612);
const double MOON_SOI = 66167158.6569544;
var r0 = new V3(rx, ry, rz);
var v0 = new V3(vx, vy, vz);
const double PER = 6.3781e6 + 60000; // 60km
(V3 dv, double dt, double newPeR) =
solver.NextManeuver(398600435436096, 4902800066163.8, moonR0, moonV0, 66167158.6569544, r0, v0, PER, 0);
(V3 r1, V3 v1) = Shepperd.Solve(MOON_MU, dt, r0, v0);
double tt1 = Astro.TimeToNextRadius(MOON_MU, r1, v1 + dv, MOON_SOI);
(V3 r2, V3 v2) = Shepperd.Solve(MOON_MU, tt1, r1, v1 + dv);
(V3 moonR2, V3 moonV2) = Shepperd.Solve(CENTRAL_MU, dt + tt1, moonR0, moonV0);
V3 r3 = moonR2 + r2;
V3 v3 = moonV2 + v2;
_testOutputHelper.WriteLine($"periapsis: {Astro.PeriapsisFromStateVectors(CENTRAL_MU, r3, v3)}");
Astro.PeriapsisFromStateVectors(CENTRAL_MU, r3, v3).ShouldEqual(PER, 1e-3);
newPeR.ShouldEqual(PER, 1e-3);
if (dvOpt > 0)
dv.magnitude.ShouldEqual(dvOpt, 1e-2);
}
}
}