ssapy.propagator

Classes for propagating orbits.

Functions

abstractmethod(funcobj)	A decorator indicating abstract methods.
default_numerical(*args[, cls, accel, ...])	Construct a numerical propagator with sensible default acceleration.
norm(arr)	Compute the Euclidean norm of an array over the last axis while preserving leading axes.
teme_to_gcrf(t)	Return the rotation matrix that converts TEME cartesian coordinates to GCRS cartesian coordinates.

Classes

ABC()	Helper class that provides a standard way to create an ABC using inheritance.
KeplerianPropagator()	A basic Keplerian propagator for finding the position and velocity of an orbiting object at some future or past time.
LRU_Cache(user_function[, maxsize])	Simplified Least Recently Used Cache.
Propagator()	Abstract base class for orbit propagators.
RK4Propagator(accel, h)	Runge-Kutta 4th order numerical integrator.
RK78Propagator(accel, h[, tol])	Runge-Kutta 8th order numerical integrator with adaptive step size computed from embedded 7th order integrator error estimate.
RK8Propagator(accel, h)	Runge-Kutta 8th order numerical integrator.
RKPropagator()	Abstract base class for Runge-Kutta-based orbit propagators.
SGP4Propagator([t, truncate])	Propagate using simplified perturbation model SGP4.
SciPyPropagator(accel[, ode_kwargs])	Propagate using the scipy.integrate.solve_ivp ODE solver.
SeriesPropagator([order])	Propagate using Taylor series expansion of Keplerian motion.
Time(val[, val2, format, scale, precision, ...])	Represent and manipulate times and dates for astronomy.

Class Inheritance Diagram