Earth-Mars transfers with ballistic escape and low-thrust capture

被引：41
|
作者：
Mingotti, G. [2 ]
Topputo, F. [1 ]
Bernelli-Zazzera, F. [1 ]
机构：
[1] Politecn Milan, Dipartimento Ingn Aerospaziale, I-20156 Milan, Italy
[2] Univ Paderborn, Inst Ind Math, D-33098 Paderborn, Germany
来源：
CELESTIAL MECHANICS & DYNAMICAL ASTRONOMY | 2011年 / 110卷 / 02期
关键词：
Restricted three-body problem; Invariant manifolds; Low-thrust transfer; n-body models; Ballistic capture; Lunar-gravity assist; RESTRICTED 3-BODY PROBLEM; INVARIANT-MANIFOLDS; TRAJECTORY OPTIMIZATION; PERIODIC-ORBITS; HALO ORBITS; INTERPLANETARY TRANSFERS; CELESTIAL MECHANICS; MISSION DESIGN; MOON; L2;
D O I：
10.1007/s10569-011-9343-5
中图分类号：
P1 [天文学];
学科分类号：
0704 ;
摘要：
In this paper novel Earth-Mars transfers are presented. These transfers exploit the natural dynamics of n-body models as well as the high specific impulse typical of low-thrust systems. The Moon-perturbed version of the Sun-Earth problem is introduced to design ballistic escape orbits performing lunar gravity assists. The ballistic capture is designed in the Sun-Mars system where special attainable sets are defined and used to handle the low-thrust control. The complete trajectory is optimized in the full n-body problem which takes into account planets' orbital inclinations and eccentricities. Accurate, efficient solutions with reasonable flight times are presented and compared with known results.
引用
收藏
页码：169 / 188
页数：20
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