poliastro.core.thrust.change_ecc_inc

Simultaneous eccentricity and inclination changes.

References

  • Pollard, J. E. “Simplified Analysis of Low-Thrust Orbital Maneuvers”, 2000.

Summary

Functions

beta(ecc_0, ecc_f, inc_0, inc_f, argp)

delta_V(V_0, ecc_0, ecc_f, beta_)

Compute required increment of velocity.

delta_t(delta_v, f)

Compute required increment of velocity.

change_ecc_inc(k, a, ecc_0, ecc_f, inc_0, inc_f, argp, r, v, f)

Contents

poliastro.core.thrust.change_ecc_inc.beta(ecc_0, ecc_f, inc_0, inc_f, argp)
poliastro.core.thrust.change_ecc_inc.delta_V(V_0, ecc_0, ecc_f, beta_)

Compute required increment of velocity.

poliastro.core.thrust.change_ecc_inc.delta_t(delta_v, f)

Compute required increment of velocity.

poliastro.core.thrust.change_ecc_inc.change_ecc_inc(k, a, ecc_0, ecc_f, inc_0, inc_f, argp, r, v, f)