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ReturnFromMoon updating tests
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Signed-off-by: Lamont Granquist <lamont@scriptkiddie.org>
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@lamont-granquist
lamont-granquist committed Nov 20, 2023
1 parent bf9e8dc commit 805aecd
Showing 1 changed file with 43 additions and 32 deletions.
75 changes: 43 additions & 32 deletions MechJebLibTest/ManeuversTests/ReturnFromMoonTests.cs
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Expand Up @@ -19,7 +19,7 @@ public ReturnFromMoonTests(ITestOutputHelper testOutputHelper)
}

[Fact]
private void NextManeuverToReturnFromMoonTest()
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);
Expand All @@ -30,10 +30,6 @@ private void NextManeuverToReturnFromMoonTest()
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(4198676.73768844, 5187520.71497923, -3.29371833446352);
var v0 = new V3(-666.230112925872, 539.234048888927, 0.000277598267012666);
*/
const double PER = 6.3781e6 + 60000; // 60km

// this test periodically just fails, although its about 1-in-150 right now
Expand All @@ -49,33 +45,6 @@ private void NextManeuverToReturnFromMoonTest()
Astro.ApoapsisFromStateVectors(MOON_MU, r0, v0) > MOON_SOI)
continue;

r0 = new V3(3033960.04435434, -538512.74449519, -1569171.01639252);
v0 = new V3(344.550626047212, -973.108221764261, 907.813925253141);

/*
r0 = new V3(-23744.6019871556, -935848.195057236, -2970820.75826717);
v0 = new V3(-511.683969531061, -141.692448007731, 975.982327934346);
r0 = new V3(-1358340.16497667, -2896749.43027493, -2706207.90479207);
v0 = new V3(774.176044284448, -468.922061598358, -642.571722922182);
r0 = new V3(-2370135.82005065, -78770.3300753334, 504857.052794559);
v0 = new V3(-735.735041897621, -590.266316007015, -137.364944041411);
r0 = new V3(1922287.76973033, 1688857.60199125, -1128186.04080648);
v0 = new V3(-644.272529354446, 90.1035308326145, -74.2516010414118);
r0 = new V3(1448096.6091073, 2242802.60448088, 593799.176165359);
v0 = new V3(316.818652356425, -684.168486708854, -453.106628476226);
r0 = new V3(72567.8252483425, -1202508.27881747, 995820.818247795);
v0 = new V3(733.61121478193, -501.358138165138, -26.4032981481417);
r0 = new V3(1105140.06213014, -8431008.05414815, -4729658.84487529);
v0 = new V3(-293.374690393787, -1173.3597686151, -411.755491683683);
*/
_testOutputHelper.WriteLine($"iteration: {i}");

(V3 dv, double dt, double newPeR) =
Expand Down Expand Up @@ -128,5 +97,47 @@ private void NextManeuverToReturnFromMoonOptguardTest()
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)]
[InlineData(-23744.6019871556, -935848.195057236, -2970820.75826717, -511.683969531061, -141.692448007731, 975.982327934346)]
[InlineData(-1358340.16497667, -2896749.43027493, -2706207.90479207, 774.176044284448, -468.922061598358, -642.571722922182)]
[InlineData(-2370135.82005065, -78770.3300753334, 504857.052794559, -735.735041897621, -590.266316007015, -137.364944041411)]
[InlineData(1922287.76973033, 1688857.60199125, -1128186.04080648, -644.272529354446, 90.1035308326145, -74.2516010414118)]
[InlineData(1448096.6091073, 2242802.60448088, 593799.176165359, 316.818652356425, -684.168486708854, -453.106628476226)]
[InlineData(72567.8252483425, -1202508.27881747, 995820.818247795, 733.61121478193, -501.358138165138, -26.4032981481417)]
[InlineData(1105140.06213014, -8431008.05414815, -4729658.84487529, -293.374690393787, -1173.3597686151, -411.755491683683)]
public void NextManeuverToReturnFromMoonHard(double rx, double ry, double rz, double vx, double vy, double vz)
{
// 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);

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) =
ReturnFromMoon.NextManeuver(398600435436096, 4902800066163.8, moonR0, moonV0, 66167158.6569544, r0, v0, PER, 0, 0, optguard: 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);
}
}
}

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