removeForceModels() | | 0% | | 0% | 2 | 2 | 8 | 8 | 1 | 1 |
addForceModel(DSSTForceModel) | | 73% | | 83% | 1 | 4 | 3 | 13 | 0 | 1 |
computeMeanOrbit(FieldSpacecraftState, AttitudeProvider, Collection, double, int) | | 95% | | 72% | 5 | 10 | 1 | 44 | 0 | 1 |
getSelectedCoefficients() | | 0% | | 0% | 2 | 2 | 2 | 2 | 1 | 1 |
afterIntegration() | | 71% | | 75% | 1 | 3 | 2 | 8 | 0 | 1 |
setAttitudeProvider(AttitudeProvider) | | 57% | | 50% | 1 | 2 | 2 | 5 | 0 | 1 |
setInitialState(FieldSpacecraftState, PropagationType) | | 77% | | 66% | 1 | 3 | 1 | 8 | 0 | 1 |
setSatelliteRevolution(int) | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
getAllForceModels() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
getSatelliteRevolution() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
initialIsOsculating() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
getOrbitType() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
getPositionAngleType() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
beforeIntegration(FieldSpacecraftState, FieldAbsoluteDate) | | 100% | | 100% | 0 | 5 | 0 | 22 | 0 | 1 |
computeOsculatingOrbit(FieldSpacecraftState, List) | | 100% | | 100% | 0 | 3 | 0 | 12 | 0 | 1 |
computeOsculatingState(FieldSpacecraftState, AttitudeProvider, Collection) | | 100% | | 100% | 0 | 2 | 0 | 10 | 0 | 1 |
createMapper(FieldAbsoluteDate, CalculusFieldElement, OrbitType, PositionAngleType, AttitudeProvider, Frame) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
FieldDSSTPropagator(Field, FieldODEIntegrator, PropagationType, AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
FieldDSSTPropagator(Field, FieldODEIntegrator, AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
hasNewtonianAttraction() | | 100% | | 100% | 0 | 3 | 0 | 2 | 0 | 1 |
computeMeanState(FieldSpacecraftState, AttitudeProvider, Collection, double, int) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
resetInitialState(FieldSpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
getInitialIntegrationState() | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
setSelectedCoefficients(Set) | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
FieldDSSTPropagator(Field, FieldODEIntegrator, PropagationType) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
setInterpolationGridToFixedNumberOfPoints(int) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
setInterpolationGridToMaxTimeGap(CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
FieldDSSTPropagator(Field, FieldODEIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
setMu(CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
computeMeanState(FieldSpacecraftState, AttitudeProvider, Collection) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getMainStateEquations(FieldODEIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
tolerances(CalculusFieldElement, CalculusFieldElement, FieldOrbit) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
setInitialState(FieldSpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
tolerances(CalculusFieldElement, FieldOrbit) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
superSetMu(CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |