boinor.core.thrust.change_ecc_inc

Simultaneous eccentricity and inclination changes (in sub-package core).

References

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

Functions

beta(ecc_0, ecc_f, inc_0, inc_f, argp)	Note: "The argument of perigee will vary during the orbit transfer
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, ...)	core functions of simultaneous eccentricity and inclination changes towards a given final value

Module Contents

boinor.core.thrust.change_ecc_inc.beta(ecc_0, ecc_f, inc_0, inc_f, argp)

Note: “The argument of perigee will vary during the orbit transfer due to the natural drift and because e may approach zero. However, [the equation] still gives a good estimate of the desired thrust angle.”

boinor.core.thrust.change_ecc_inc.delta_V(V_0, ecc_0, ecc_f, beta_)

Compute required increment of velocity.

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

Compute required increment of velocity.

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

core functions of simultaneous eccentricity and inclination changes towards a given final value