Function lupnt::AccelerationSolarRadiation

Function Documentation

Vec3 lupnt::AccelerationSolarRadiation(const Vec3 &r, const Vec3 &r_sun, Real bcoeff_srp, Real P0, Real AU)

Compute the cannonball solar radiation pressure (SRP) acceleration on a spacecraft.

Called by NumericalOrbitDynamics::CalcContrib once per step (when SRP is enabled), scaled by the eclipse Illumination factor for the relevant occulting body, to add the SRP contribution to the total acceleration.

Parameters:

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

  • r_sun – Sun position relative to the same central body [m]

  • bcoeff_srp – Spacecraft SRP ballistic coefficient, CR * area / mass [m^2/kg]

  • P0 – Solar radiation pressure at 1 AU [N/m^2]

  • AU – Length of one Astronomical Unit [m]

Returns:

SRP acceleration on the spacecraft [m/s^2]