运载火箭末级自适应控制方案研究  

Research on Adaptive Control Scheme of Launch Vehicle Final Stage

作　　者：张丹 朱蕾蕾 张晓东[2] 王威 陈祺 林洁 ZHANG Dan;ZHU Leilei;ZHANG Xiaodong;WANG Wei;CHEN Qi;LIN Jie(Shanghai Aerospace Control Technology Institute,Shanghai 201109,China;Shanghai Academy of Spaceflight Technology,Shanghai 201109,China)

机构地区：[1]上海航天控制技术研究所,上海201109 [2]上海航天技术研究院,上海201109

出　　处：《上海航天（中英文）》2020年第S02期126-130,135,共6页Aerospace Shanghai（Chinese&English）

基　　金：海军装备预先研究项目(995-02030401-0139)

摘　　要：在现役型号火箭密集发射的任务形势下,为进一步提高姿态控制系统的稳定性能和控制效率,研究了现役某型号三级段无速率陀螺控制方案,相比目前普遍采用的三级姿控方案具有明显的裕度和稳定性优势;提出根据箭体模型采用自适应参数设计方案,可以提高设计效率,为现役型号火箭发射保成功提供支持。通过箭体模型的频域和时域的仿真分析,验证了该控制方案的优越性能,对控制网络微分强超调大的问题解决具有一定的参考价值。The three-stage rate-free gyro control scheme for a certain active rocket is studied in order to further improve the stability of the attitude control system performance and control efficiency under the mission situation of intensive launch of active model rockets. It is shown that the scheme has obvious advantages of margin and stability compared with the triple attitude control scheme widely used at present,and the design efficiency can be improved if the adaptive parameter design scheme is adopted according to the rocket model,which provides support for the successful launch of active rockets. The superior performance of the control scheme is verified by the simulation analysis of the arrow model in the frequency domain and time domain,which has a certain reference value for solving the problem of strong overshoot in the control network differential.

关 键 词：现役型号 控制系统 三级主动段 自适应 网络微分 

分 类 号：U666.12[交通运输工程—船舶及航道工程]