Function lupnt::AccelerationSolarRadiation

Function Documentation

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

Computes the acceleration due to solar radiation pressure.

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.

Note

O. Montenbruck and G. Eberhard, Satellite orbits: models, methods, and applications. Berlin : New York: Springer, 2000. doi: 10.1007/978-3-642-58351-3.

Parameters:

  • r – Spacecraft position [m]

  • r_sun – Sun position [m]

  • area – Cross-section [m^2]

  • mass – Spacecraft mass [kg]

  • CR – Solar radiation pressure coefficient (0: translucent, 1: black body 2: perfect mirror)

  • P0 – Solar radiation pressure at 1 AUa

  • AU – Length of one Astronomical Unit

  • 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:

Acceleration [m/s^2]

Returns:

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