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 |