We suggest the approach to optimization of motion of spacecrafts with nuclear engines of high limited thrust on planet centric sections of interplanetary trajectories. The problem of optimization of interplanetary transfer is considered within the framework of the modified method of sphere of influence. The problem of optimization of motion on active section is stated as a problem of transfer from circular orbit to hyperbolic one, which is characterized by setting hyperbolic excess of velocity. The optimal control is investigated by means of the maximum principle of Pontryagin.
Computation of interplanetary trajectories of spacecrafts with nuclear rocket engines of high-limited thrust
Journal of Automation and Information Sciences ; 41 , 6 ; 58-69
2009
12 Seiten, 15 Quellen
Article (Journal)
English
Optimization of Interplanetary Trajectories for a Limited-Thrust Spacecraft
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