摘要
为克服飞行干扰,经典迭代制导方法根据目标入轨点参数,通过调整火箭飞行姿态达到精确入轨的目的,导致主动段终端姿态散布较大。对于没有配置姿控发动机的火箭,迭代制导带来的主动段终端姿态偏差将由有效载荷通过姿态调整来克服。有效载荷往往将姿态调整时间累积至星箭分离后有效载荷可用测控时间,反过来限制火箭运载能力优化。基于某型号二级液体火箭,本文提出一种在二级游机关机前,利用4台游动发动机进行主动姿态调整,以满足有效载荷入轨姿态要求的方法。目前,该方法已在某型号二级火箭上得到成功应用,取得良好效果。
In order to overcome flight interference,the classical iterative guidance method achieves injection accuracy by adjusting the launch vehicle flight attitude according to the target orbit point parameters,resulting in large attitude dispersion at the active terminal. For launch vehicle without attitude control engine,the attitude deviation of the active segment terminal caused by iterative guidance can be overcome by attitude adjustment of the payload. The payload often accumulates the attitude adjustment time to the available measurement and control time of the payload after the separation of the launch vehicle,which in turn limits the optimization of the launch vehicle carrying capacity.Based on a certain type of two-stage liquid launch vehicle,in this paper,a method of using four vernier engines for adjusting the active attitude before second vernier engine shutoff is proposed to meet the requirements of the payload.At present,this method has been successfully applied to a certain type of two-stage launch vehicle,and good results have been obtained.
作者
朱亮聪
杨勇
陈文达
秦川
王其晓
ZHU Liangcong;YANG Yong;CHEN Wenda;QIN Chuan;WANG Qixiao(Aerospace System Engineering Institute of Shanghai,Shanghai 201109,China;Shanghai Academy of Spaceflight Technology,Shanghai 201109,China)
出处
《上海航天（中英文）》
CSCD
2020年第S02期16-21,共6页
Aerospace Shanghai（Chinese&English）
关键词
运载火箭
终端姿态约束
迭代制导
游机调姿
主动调姿
launch vehicle
terminal attitude constraint
iterative guidance
vernier engine adjustment
active attitude adjustment
