中国空间科学技术2013，Vol.33Issue(2)：1-6,6.DOI:10.3780/j.issn.1000-758X.2013.02.001
精确动力学模型中的行星引力辅助轨道设计
Trajectory Design of Gravity Assist in the High-fidelity Dynamic Model
摘要
Abstract
The precision orbit design using planet gravity assist in the high-fidelity model was studied.Orbit design was divided into two steps,preliminary design and iteration in the high-fidelity model.Preliminary design was based on the simplified model.Conic patched method was used to determine the launch window and the impulse induced by gravity assist.Taking the gravity assist as a continuous process in the high-fidelity model,the swing-by hyperbola was transformed into B-plane parameters.The earth-centered departure impulse was taken as design variable and the problem was solved by differential correction.Orbit design for Flora rendezvous in main asteroid belt after Mars gravity assist was presented and the relation of the results between the two models above was compared and analyzed in the illustrative example analysis.The result indicates that the orbit in the high-fidelity model which is based on the simplified model can be reached after few iterations.关键词
轨道设计/精确动力学模型/引力辅助/微分修正/深空探测Key words
Orbit design/High-fidelity model/Gravity assist/Differential correction/Deep space exploration引用本文复制引用
杨洪伟,陈杨,宝音贺西,李俊峰..精确动力学模型中的行星引力辅助轨道设计[J].中国空间科学技术,2013,33(2):1-6,6.基金项目
国家重点基础研究发展计划(973计划)(2012CB720000),航天飞行动力学技术重点实验室开放基金(2012ADFL006)资助项目 （973计划）
