spaceteams.SC_Compute_Server.orbit
¶
CartesianState
¶
CartesianState(R_km: Annotated[ArrayLike, float64, '[3, 1]'], V_km_s: Annotated[ArrayLike, float64, '[3, 1]'], mu_km3_s2: SupportsFloat)
KeplerianState
¶
KeplerianState(a_km: SupportsFloat, e: SupportsFloat, raan_rad: SupportsFloat, i_rad: SupportsFloat, omega_rad: SupportsFloat, ta_rad: SupportsFloat, mu_km3_s2: SupportsFloat)
LambertBattinResults
¶
LambertBattinResults(v0_km_s: Annotated[ArrayLike, float64, '[3, 1]'], v_km_s: Annotated[ArrayLike, float64, '[3, 1]'])
State
¶
fromCartesian
staticmethod
¶
fromCartesian(R_km: Annotated[ArrayLike, float64, '[3, 1]'], V_km_s: Annotated[ArrayLike, float64, '[3, 1]'], mu_km3_s2: SupportsFloat) -> State
fromKeplerian
staticmethod
¶
fromKeplerian(a_km: SupportsFloat, e: SupportsFloat, raan_rad: SupportsFloat, i_rad: SupportsFloat, omega_rad: SupportsFloat, ta_rad: SupportsFloat, mu_km3_s2: SupportsFloat) -> State
LagrangePropagation
¶
LagrangePropagation(state: State, delta_t: SupportsFloat, tolerance: SupportsFloat, max_iterations: SupportsInt) -> State
LambertBattin
¶
LambertBattin(r0: Annotated[ArrayLike, float64, '[3, 1]'], r: Annotated[ArrayLike, float64, '[3, 1]'], deltaTime: SupportsFloat, tm: SupportsFloat, mu: SupportsFloat, n: SupportsInt, tol: SupportsFloat, max_iter: SupportsInt) -> LambertBattinResults
calcTime
¶
calcTime(ta: SupportsFloat, e: SupportsFloat, a: SupportsFloat, mu: SupportsFloat, h: Annotated[ArrayLike, float64, '[3, 1]']) -> float