摘要
液体运载火箭飞行过程中面临推进剂晃动问题,满足姿控稳定条件下对防晃板进行减配,将有效地提升总体方案的可靠性与经济性。阐述了长征五号系列运载火箭贮箱防晃板优化过程,重点针对试样阶段一级氢箱防晃板减配问题开展了姿控设计。首先给出了刚晃弹动力学模型,开展了火箭晃动极-零问题分析,从频域分析与时域仿真的角度给出了姿控稳定结论,最后开展了飞行结果评估。研究结果表明,对晃动质量较小的贮箱防晃板可进行减配优化,姿控稳定设计允许部分秒点频域不稳定,时域仿真不发散是晃动稳定重要的设计依据。
Liquid launch vehicle is faced with the problem of propellant sloshing during flight.Reducing the slosh baffles under the stability condition of attitude control will effectively improve the reliability and economy of the overall scheme for launch vehicle.The slosh baffles reduction history of LM-5 Series launch vehicle is expound,and the attitude control design is presented toward the reduction of the first stage hydrogen liquid fuel tank for Shiyang.A rigid-slosh-flexible dynamic model for control is carried out.Then the pole-zero problem as to LM-5 rocket is discussed.The frequency domain analysis and time domain simulation is studied for attitude stability.Finally,the flight result is evaluated for the reduction of H-tank slosh baffles.Results show that the slosh baffles could be reduced with small sloshing mass,and the non-divergence of simulation in time domain is an important design basis for sloshing stability allowing partial time points to be unstable in frequency domain.
作者
余光学
邓舞燕
李东
Yu Guang-xue;Deng Wu-yan;Li Dong(Beijing Institute of Astronautical Systems Engineering,Beijing,100076;China Academy of Launch Vehicle Technology,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2021年第5期15-19,38,共6页
Missiles and Space Vehicles
关键词
长征五号运载火箭
姿控
氢箱
防晃板
稳定
LM-5 launch vehicle
attitude control
hydrogen liquid fuel tank
slosh baffle
stability
作者简介
余光学(1986-),男,博士,高级工程师,主要研究方向运载器姿态动力学与控制;邓舞燕(1976-),女,研究员,主要研究方向运载器姿态动力学与控制;李东(1967-),男,博士,研究员,主要研究方向运载火箭总体技术。
