Application
Space Trajectories. Orbit Injection at Optimum Thrust Level

This first example deals with a thrust profile optimization transfer, either linear or two-stage. The initial mass is 10,000 kg and the specific impulse of the engine is 300 s, corresponding to an ejection speed of 2,942 m/s. Initial conditions are an altitude of 150 km, a velocity of 5,000 m/s and a local slope of 30°, corresponding to an apogee at 661.7 km and a perigee at -5,209.4 km. The target orbit is a geostationary transfer orbit (GTO),...