CAJ | 학술논문

采用仿真分析与试验验证有机结合优化方法，提出一种助推器模拟件绕点圆周运动与转动飞行姿态控制技术，实现了助推器分离飞行姿态模拟控制，为大型助推器竖直分离回收系统性能考核提供方法。助推器分离飞行姿态地面模拟系统运动轨迹仿真结果与试验测量数据一致性较好，验证本飞行姿态模拟技术的可行性。该技术成功应用于新一代运载火箭助推器分离试验设计，可为未来重型运载火箭助推器分离回收技术研究提供指导。
채용방진분석여시험험증유궤결합우화방법，제출일충조추기모의건요점원주운동여전동비행자태공제기술，실현료조추기분리비행자태모의공제，위대형조추기수직분리회수계통성능고핵제공방법。조추기분리비행자태지면모의계통운동궤적방진결과여시험측량수거일치성교호，험증본비행자태모의기술적가행성。해기술성공응용우신일대운재화전조추기분리시험설계，가위미래중형운재화전조추기분리회수기술연구제공지도。
The flight attitude control technology on circular motion and rotation of rocket booster simulative component was introduced by using the numerical simulation analysis and experimental validation optimization methods. Rocket booster separation flight attitude simulation control was obtained to supply recovery system testing of large rocket booster vertical separation with power source. The simulation results were agree with the ground testing and measuring data of the trajectories of rocket booster separation flight attitude ground simulative system, and it validated the feasibility of the flight attitude control technology. This technology was applied to rocket booster separation experiment design of new generation launch vehicle, and provides direction on heavy launch vehicle booster separation and recovery technology development.