Journal of Astronautics ›› 2020, Vol. 41 ›› Issue (7): 868-879.doi: 10.3873/j.issn.1000-1328.2020.07.005

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Development of Flight Control Technology of Long March Launch Vehicles

SONG Zheng yu, PAN Hao, WANG Cong, GONG Qing hai   

  1. 1. China Academy of Launch Vehicle Technology, Beijing 100076, China; 2. Beijing Aerospace Automatic Control Institute, Beijing 100854, China
  • Received:2020-02-01 Revised:2020-03-30 Online:2020-07-15 Published:2020-07-25

Abstract: This paper firstly introduces the family of the new-generation Long March launch vehicles (LMLVs), and then reviews the evolution of their control systems from four aspects. The guidance method has developed from open-loop guidance, to iterative guidance, raising a variety of algorithms satisfying the large thrust direct injection and/or terminal attitude constraints, and greatly reducing the orbit injection errors. Based on the PID technology, the space modal and equivalent swing angle modeling are adopted in the attitude control method, to solve the problems of joint swing with side and core boosters’ engines; and an active load relief proposal is presented by combining with active-disturbance-rejection controller (ARDC). China’s Manned Space Program promotes the study on systematic reliability design, and a technical system has been formed gradually with the features of redundant devices, fault-tolerant algorithms, and onboard system reconfiguration, thus boosting the overall reliability improvement on the control system. The avionics system develops from the discrete, centralized architecture, to the integrated, distributed digital system. Finally, according to the current research focus in the aerospace control technologies, the latest practices and the prospects of LMLV’s flight control technology are summarized.

Key words: Launch vehicle, Guidance and control, Reliability design, Integrated modular avionics

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