助推器分离飞行姿态地面模拟控制与仿真分析  

Ground Flight Control and Simulation Analysis of Rocket Booster Separation Flight Attitude

作　　者：王求生[1] 王喆[1] 王竞男[1] 

机构地区：[1]北京强度环境研究所,北京100076

出　　处：《导弹与航天运载技术》2015年第4期62-65,共4页Missiles and Space Vehicles

摘　　要：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。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.

关 键 词：助推器分离 飞行姿态 地面模拟控制 仿真分析 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程]