computeMeanOrbit(SpacecraftState, Collection) | | 94% | | 62% | 6 | 9 | 1 | 27 | 0 | 1 |
getSelectedCoefficients() | | 0% | | 0% | 2 | 2 | 2 | 2 | 1 | 1 |
setAttitudeProvider(AttitudeProvider) | | 58% | | 50% | 1 | 2 | 2 | 5 | 0 | 1 |
getInitialIntegrationState() | | 67% | | 100% | 0 | 2 | 2 | 5 | 0 | 1 |
setInitialState(SpacecraftState) | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
setSatelliteRevolution(int) | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
removeForceModels() | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
getSatelliteRevolution() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
initialIsOsculating() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
beforeIntegration(SpacecraftState, AbsoluteDate) | | 100% | | 100% | 0 | 4 | 0 | 19 | 0 | 1 |
computeOsculatingOrbit(SpacecraftState, List) | | 100% | | 100% | 0 | 3 | 0 | 9 | 0 | 1 |
computeOsculatingState(SpacecraftState, Collection) | | 100% | | 100% | 0 | 2 | 0 | 8 | 0 | 1 |
afterIntegration() | | 100% | | 100% | 0 | 5 | 0 | 12 | 0 | 1 |
createMapper(AbsoluteDate, double, OrbitType, PositionAngle, AttitudeProvider, Frame) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
DSSTPropagator(AbstractIntegrator, boolean) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
DSSTPropagator(AbstractIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
computeMeanState(SpacecraftState, Collection) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
setSelectedCoefficients(Set) | | 100% | | 100% | 0 | 2 | 0 | 2 | 0 | 1 |
addForceModel(DSSTForceModel) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
resetInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
setInitialState(SpacecraftState, boolean) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
setInterpolationGridToFixedNumberOfPoints(int) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
setInterpolationGridToMaxTimeGap(double) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getMainStateEquations(AbstractIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
tolerances(double, Orbit) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |