Nutation instability of spinning solid rocket motor spacecraft  

作　　者：Dan YANG Yongliang XIONG Qian REN Xianyong WANG 

机构地区：[1]School of Naval Architecture and Ocean Engineering, Huazhong University of Science and Technology, Wuhan 430074, China [2]Department of Mechanics, Huazhong University of Science and Technology, Wuhan 430074, China [3]Hubei Key Laboratory of Engineering Structural Analysis and Safety Assessment, Luoyu Road 1037, Wuhan 430074, China

出　　处：《Chinese Journal of Aeronautics》2017年第4期1363-1372,共10页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China (Nos. 11502086 and 11502087)

摘　　要：The variation of mass, and moment of inertia of a spin-stabilized spacecraft leads to concern about the nutation instability. Here a careful analysis on the nutation instability is performed on a spacecraft propelled by solid rocket booster（SRB）. The influences of specific solid propellant designs on transversal angular velocity are discussed. The results show that the typical SRB of End Burn suppresses the non-principal axial angular velocity. On the contrary, the frequently used SRB of Radial Burn could amplify the transversal angular velocity. The nutation instability caused by a design of Radial Burn could be remedied by the addition of End Burn at the same time based on the study of the combination design of both End Burn and Radial Burn.The analysis of the results proposes the design conception of how to control the nutation motion.The method is suitable to resolve the nutation instability of solid rocket motor with complex propellant patterns.The variation of mass, and moment of inertia of a spin-stabilized spacecraft leads to concern about the nutation instability. Here a careful analysis on the nutation instability is performed on a spacecraft propelled by solid rocket booster（SRB）. The influences of specific solid propellant designs on transversal angular velocity are discussed. The results show that the typical SRB of End Burn suppresses the non-principal axial angular velocity. On the contrary, the frequently used SRB of Radial Burn could amplify the transversal angular velocity. The nutation instability caused by a design of Radial Burn could be remedied by the addition of End Burn at the same time based on the study of the combination design of both End Burn and Radial Burn.The analysis of the results proposes the design conception of how to control the nutation motion.The method is suitable to resolve the nutation instability of solid rocket motor with complex propellant patterns.

关 键 词：Attitude control Nutation dampers Payloads Solid rocket booster Spin stabilization of spacecraft 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] V448.221