摘要
针对大气制动轨道转移过程中出现的近心点下降问题,给出了一种利用气动力实现近心点高度控制的方法.设计了以倾侧角为控制变量的大气内飞行控制律,并参考相关星际探测任务进行了仿真验证.通过改变倾侧角调整气动力在高度方向上的分量来实现对制动轨道近心点高度的控制,并根据当前近心点高度与预定近心点高度自动调整反馈增益.在整个大气制动过程中本方法无需燃料消耗即可有效地限制近心点下降并最终减少下降量,同时使飞行过程中的最大动压和最大热流密度逐渐降低,保证了航天器的安全.
An approach of perigee altitude control using aerodynamic force was provided to deal with the decline of perigee during the orbital transfer process of aerobraking. The atmospheric flight control law consid- ering the bank angle as control variable was investigated, and the computer simulation which referred to the relevant interplanetary exploration mission was performed for demonstration. The perigee altitude was con- trolled by changing the bank angle to adjust the aerodynamic force component along altitude direction. And the feedback gains were automatically adjusted according to the currently actual altitude and the desired altitude of perigee. The present control law effectively limited the decline of perigee altitude and reduced the quantity of decline finally during whole aerobraking without fuel consumption. Meanwhile, the max dynamic pressure and the max heat flux were decreased gradually, which ensure the security of spacecraft.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2015年第3期517-522,共6页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家自然科学基金资助项目(11272028)
