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@ -109,7 +109,7 @@ TEST_CASE("state vectors to orbital elements, example 3.1", "[orbits]") |
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REQUIRE_THAT(el.nu, WithinAbs(orbitClampAngle(DEG2RAD(280)), 1)); |
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REQUIRE_THAT(el.nu, WithinAbs(orbitClampAngle(DEG2RAD(280)), 1)); |
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} |
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} |
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TEST_CASE("elements to state vectors, edge case equatorial orbit", "[orbits]") |
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TEST_CASE("state vectors to elements, edge case equatorial orbit", "[orbits]") |
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{ |
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{ |
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double mu = EARTH_GRAVITATIONAL_PARAMETER; |
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double mu = EARTH_GRAVITATIONAL_PARAMETER; |
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dvec3 r = dvec3(0, -8000, 0); |
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dvec3 r = dvec3(0, -8000, 0); |
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