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3. Application
This section illustrates the application of the previous theoretical results. The first example concerns the optimization of a linear or two-stage thrust profile. The second example shows the solution for a problem with a fixed thrust level, using analytical initialization of the adjoint.
3.1 Optimized thrust profile
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),...
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