boinor.twobody.thrust.change_argp

Argument of perigee change, with formulas developed by Pollard.

References

  • Pollard, J. E. “Simplified Approach for Assessment of Low-Thrust Elliptical Orbit Transfers”, 1997.

  • Pollard, J. E. “Evaluation of Low-Thrust Orbital Maneuvers”, 1998.

Functions

change_argp(k, a, ecc, argp_0, argp_f, f)

Change argument of perigee, with formulas developed by Pollard.

Module Contents

boinor.twobody.thrust.change_argp.change_argp(k, a, ecc, argp_0, argp_f, f)

Change argument of perigee, with formulas developed by Pollard. Guidance law from the model. Thrust is aligned with an inertially fixed direction perpendicular to the semimajor axis of the orbit.

Parameters:

  • k (Quantity) – Gravitational parameter (km**3 / s**2)

  • a (Quantity) – Semi-major axis (km)

  • ecc (float) – Eccentricity

  • argp_0 (Quantity) – Initial argument of periapsis (rad)

  • argp_f (Quantity) – Final argument of periapsis (rad)

  • f (Quantity) – Magnitude of constant acceleration (km / s**2)

Returns:

a_d, delta_V, t_f

Return type:

tuple (function, Quantity, Time)