低成本高超声速试验火箭姿态控制方法  

Attitude Control of Low-Cost Rockets for Hypersonic Research Flight Tests

作　　者：吴东升[1] 郑忠培[2] 丁智坚[1] 

机构地区：[1]中国空气动力研究与发展中心吸气式高超声速技术研究中心,绵阳621000 [2]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《宇航学报》2017年第9期946-955,共10页Journal of Astronautics

摘　　要：针对我国低成本高超声速试验火箭的需求,提出一种基于简易反作用控制系统(RCS)的进动和章动同步控制方法,实现高空旋转火箭的大范围姿态调整和再入姿态控制。该方法采用单喷管且喷气冲量固定的RCS执行机构,通过对旋转火箭在RCS间歇作用下动力学演进过程分析,建立了体现进动、章动耦合效应的状态空间模型和系统稳定条件,设计了开关控制策略。利用姿态角和角速率构建反馈信号控制RCS喷管开启,使姿态角满足要求。理论仿真表明:在RCS喷气冲量矩相对误差为26.7%,自旋角速度变化范围为2.0~4.0 r/s的条件下,仍然可以实现大范围俯仰角调整(+10°^-60°)。该方法可以应用于我国低成本高超声速试验火箭,推动高超声速研究性飞行试验广泛开展。To meet the requirements of the low-cost rockets for hypersonic flight tests,a synchronized control scheme is proposed for controlling the procession and nutation of a rocket through a simple reaction control system（ RCS）,which can achieve the large-scale attitude adjustment and reentry control. The RCS consists of a single nozzle with nonadjustable duration of jet-flow. Firstly,the spinning rocket dynamic processes with the control of RCS are analyzed. Then the system models and the stability conditions,which show the coupled effects of precession and nutation,are established. Finally,the RCS control strategy is designed with the help of the attitudes and the angular rate information. Moreover,the control strategy can make the rocket attitudes meet the demands. The theoretical simulation results demonstrate that the large-scale adjustment of the pitch angle（ ＋ 10° ^-60°） can still be achieved under the condition that the relative error of RCS impulsive moment is 26. 7% and the variation range of spin angular rate is 2. 0 ~ 4. 0 r/s. This method is applicable to the low-cost rockets for hypersonic flight experiments,and promotes the development of the extensive flight experiments for hypersonic research.

关 键 词：高超声速 自旋火箭 姿态控制 反作用控制系统 进动 章动 

分 类 号：V448[航空宇航科学与技术—飞行器设计]