poliastro2.math.thrust.change_ecc_inc

Simultaneous eccentricity and inclination changes.

References

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

Functions

beta(ecc_0, ecc_f, inc_0, inc_f, argp)
change_ecc_inc(k, a, ecc_0, ecc_f, inc_0, ...)
delta_V(V_0, ecc_0, ecc_f, beta_)	Compute required increment of velocity.
delta_t(delta_v, f)	Compute required increment of velocity.

poliastro2.math.thrust.change_ecc_inc.beta(ecc_0, ecc_f, inc_0, inc_f, argp)

poliastro2.math.thrust.change_ecc_inc.change_ecc_inc(k, a, ecc_0, ecc_f, inc_0, inc_f, argp, r, v, f)

poliastro2.math.thrust.change_ecc_inc.delta_V(V_0, ecc_0, ecc_f, beta_)

Compute required increment of velocity.

poliastro2.math.thrust.change_ecc_inc.delta_t(delta_v, f)

Compute required increment of velocity.