长征二号丙火箭分离体落区控制技术研究与实践  

Research and Practice of the Landing Area Control Technology of LM-2C Launch Vehicle Separate Bodies

作　　者：邢建伟 牟宇 崔照云 李君 滕海山[2] XING Jianwei;MOU Yu;CUI Zhaoyun;LI Jun;TENG Haishan(Beijing Institute of Aerospace Systems Engineering,Beijing,100076)

机构地区：[1]北京宇航系统工程研究所,北京100076 [2]北京空间机电研究所,北京100094

出　　处：《导弹与航天运载技术（中英文）》2023年第3期27-32,共6页Missiles and Space Vehicles

摘　　要：随着社会经济的快速发展,中国内陆火箭发射场高密度发射形势与火箭分离体落区生产生活之间的矛盾日益突出。长征二号丙火箭开展了基于栅格舵的一子级落区控制技术和基于降落伞的整流罩落区控制技术研究,通过搭载飞行试验改进设计方案,突破了宽马赫数复杂包线的气动设计与精确预示、高动态强气动耦合条件下的子级再入精确控制、面向结构高动态大变形的整流罩再入剖面设计等关键技术,实现了中国首次基于栅格舵的火箭一子级落区精确控制飞行验证和首次整流罩带伞平稳降落,为火箭分离体落区安全性问题提供了一套可行的解决方案。With the rapid development of China economy,the contradiction between the high-density launch of the inland launch site and the life of launch vehicle separate bodies landing area is intensifying.The landing area control technology based on grid fins and parachute has been studied for LM-2C first stage and fairing,the design proposal is improved by piggyback flight,and some key technology has been conquered,such as the aerodynamic characteristics predict accurately for wide Mach number and complex boundary,the re-enter GNC(Guidance,Navigation and Control)for high dynamic and strong coupling conditions,and the fairing reenter flight profile for structural high dynamic and large deformation.Both the first flight of launch vehicle first stage landing area control with grid fins in China,and first flight of launch vehicle fairing landing with parachute in China,are achieved by CZ-2C.A set of solutions is provided by LM 2C for launch vehicle separate bodies landing area control.

关 键 词：长征二号丙 分离体 落区控制 

分 类 号：V421.4[航空宇航科学与技术—飞行器设计]