Function lupnt::AccelerationRelativisticCorrection

Function Documentation

Vec3 lupnt::AccelerationRelativisticCorrection(const Vec3 &r, const Vec3 &v, Real GM, Real c_light)

Computes the first-order relativistic correction due to a central body.

Compute the first-order post-Newtonian (Schwarzschild) relativistic acceleration correction relative to a central body.

Called by NumericalOrbitDynamics::CalcContrib (when relativistic corrections are enabled) once for the Sun-relative term and again for an optional “relativity center” body (e.g. Earth or Moon), summing both into the total acceleration. Implements Montenbruck & Gill Sec. 3.7.3 Eq. 3.146.

Parameters:

  • r – Spacecraft position relative to central body [m]

  • v – Spacecraft velocity relative to central body [m/s]

  • GM – Gravitational coefficient of central body [m^3/s^2]

  • c_light – Speed of light [m/s]

  • r – Spacecraft position relative to the central body [m]

  • v – Spacecraft velocity relative to the central body [m/s]

  • GM – Gravitational parameter of the central body [m^3/s^2]

  • c_light – Speed of light [m/s]

Returns:

Relativistic acceleration correction [m/s^2] O. Montenbruck and G. Eberhard, Satellite orbits: models, methods, and applications, Sec. 3.7.3 Eq. 3.146. Berlin: New York: Springer, 2000. doi: 10.1007/978-3-642-58351-3.

Returns:

Post-Newtonian acceleration correction [m/s^2]