There are 2 coplanar orbits (same $i$,$\Omega$,$\omega$):
- Apogee and perigee on 200km
- Perigee on 700km, apogee on 8000 km
I used the
izzo.lambert function from the
poliastro (python) package to solve the problem.
I used the transfer time in the interval [30, 60*24*10] minutes and the true anomaly of the first maneuver in the interval [0,360]. The spacecraft mass is approximately 8 tons, İSP is about 330 s. The optimal transfer became:
- 0.14 km/s impulse on 168 deg true anomaly of initial orbit
- 1.32 km/s impulse on the perigee of destination orbit
Due to the last impulse, I spend almost 3 tons of fuel! Is this fine? Is it practically feasible to spend 3 tons in 1 impulse?
Is there a better way?