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首页> 美国政府科技报告 >Optimal Low-Thrust Interplanetary Orbit Transfer Including Earth Escape Spiral Trajectory
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Optimal Low-Thrust Interplanetary Orbit Transfer Including Earth Escape Spiral Trajectory

机译：包含地球逃逸螺旋轨迹的最优低推力行星际轨道转移

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A numerical analysis was carried out on minimum-time low-thrust Earth-Mars transfer including Earth escape spiral trajectory. This is a three-point boundary-value problem with a constraint at the interior point t=t(1) when the hyperbolic velocity is attained in the geocentric force field, and the terminal constraints at the final time t=t(f) (=t(1) +t(2)). Minimal time t(1) asterisk for the Earth escape problem is obtained here by the authors in a manner similar to that in Ref. 3, and t(1) astrisk for the Earth-Mars heliocentric transfer problem is well-known. A three-dimensional search procedure using delta t(1), delta t(f), and the control correction length alpha as three parameters is developed to solve the present complicated problem numerically. The obtained total mission time t(f) is slightly shorter than the sum of t(1) asterisk and t(2) asterisk. The control history in the escape portion is quite different from that in an optimal escape problem, but in the interplanetary portion it is similar to that in an optimal interplanetary transfer problem.

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