OrbitalTrajectories.jl and its documentation is currently in development and is provided as a pre-1.0 release.
The interfaces (exported types/functions) here may, and most likely will, change in future updates, possibly breaking any existing code using OrbitalTrajectories.jl.
While these interfaces are being developed, the documentation provided here is of very limited use. For now, please instead refer to the tutorials/examples which will be kept up-to-date as best as possible.
Core.Type — MethodGeneric constructor for a DynamicalModel's underlying ODEFunctions.
OrbitalTrajectories.Dynamics.Abstract_DynamicalModel — MethodGeneric model function.
OrbitalTrajectories.Dynamics.STM_ODEFunction — MethodFunction to generate an ODE Function that computes the State Transition
Matrix simultaneously with the given function f. This requires f to have
a computable Jacobian function.OrbitalTrajectories.Dynamics.centrifugal_potential — MethodCentrifugal potential [DeiTos2017, Eq.13; Ichinomiya 2018, Eq. 2.2]
OrbitalTrajectories.Dynamics.elliptical_potential — MethodElliptical potential in barycentric frame [DeiTos2017, Eq. 15]
OrbitalTrajectories.Dynamics.hill_sphere_radius — MethodCompute the Hill sphere radius for two bodies
OrbitalTrajectories.Dynamics.jacobi — MethodJacobi integral = 2U - V^2 = -2E [Oshima 2019, Eq. 3; Koon, Eq. 2.3.13; Wakker, Eq. 3.54]
OrbitalTrajectories.Dynamics.pos_to_inertial — MethodReturns the position rotation matrix from a rotating 3BP frame to an inertial frame.
OrbitalTrajectories.Dynamics.sensitivity — MethodSensitivity of the final state with respect to initial state.
OrbitalTrajectories.Dynamics.sensitivity — MethodSensitivity of the state at time t2 with respect to the state at time t1 <= t2.
OrbitalTrajectories.Dynamics.sensitivity — MethodSensitivity of the state at time t with respect to initial state.
OrbitalTrajectories.Dynamics.sensitivity_trace — MethodSensitivity of the full propagated trajectory with respect to initial state.
OrbitalTrajectories.Dynamics.state_to_inertial — MethodReturns the state rotation matrix from a rotating 3BP frame to an inertial frame.
OrbitalTrajectories.SpiceUtils.dynamic_synodic_frame — MethodAutomatically build and return a dynamic frame for a synodic reference (b1 is the observer, b2 is the target).
OrbitalTrajectories.SpiceUtils.get_GM — MethodGet body gravitational constant (GM) from SPICE kernels
OrbitalTrajectories.SpiceUtils.get_pos — MethodGet a target body position from SPICE kernels.
OrbitalTrajectories.SpiceUtils.get_state — MethodGet a target body state from SPICE kernels
OrbitalTrajectories.SpiceUtils.mass_fraction — MethodGet the mass fraction of two bodies (smaller mass divided by total mass)