航空学报 > 2010, Vol. 31 Issue (1): 41-47

流体力学、飞行力学与发动机

小型固体运载火箭六自由度弹道仿真

杨希祥, 张为华   

  1. 国防科学技术大学 航天与材料工程学院
  • 收稿日期:2008-11-19 修回日期:2009-07-07 出版日期:2010-01-25 发布日期:2010-01-25
  • 通讯作者: 杨希祥

Six-Degree-of-Freedom Trajectory Simulation of Small Solid Launch Vehicles

Yang Xixiang, Zhang Weihua   

  1. College of Aerospace and Materials Engineering, National University of Defense Technology
  • Received:2008-11-19 Revised:2009-07-07 Online:2010-01-25 Published:2010-01-25
  • Contact: Yang Xixiang

摘要: 针对控制系统采用侧喷流发动机和栅格舵的新型小型多级固体运载火箭开展六自由度弹道仿真研究。给出侧喷流发动机安装模型和推力模型以及开关机控制规律,阐明气动力和气动力矩计算方法;并建立了固体发动机推力模型,以及完整的六自由度弹道动力学和运动学模型。仿真结果表明:建立的六自由度弹道仿真模型能正确反映运载火箭飞行特性;研究的固体运载火箭满足将300 kg有效载荷送入200 km太阳同步轨道的运载能力要求;姿态控制系统满足运载火箭姿态控制精度要求;侧喷流推进剂质量分配合理,为总体方案论证和初步设计提供了理论依据。

关键词: 小型固体运载火箭, 弹道, 喷流, 栅格舵, 运载能力

Abstract: This article studies the six-degree-of-freedom trajectory simulation of small multiple stage solid launch vehicles with control systems using lateral jet thrusters and grid fins. It provides the installation model, thrust model and the control law for the starting-up and cutoff operations of the lateral jet thrusters, and deals with the calculation method of aerodynamics and aerodynamic moment. Furthermore, it builds a thrust model of the solid rocket motor, and presents the whole six-degree-of-freedom kinetic equations and motion equations. Simulation results show that the six-degree-of-freedom trajectory simulation model thus established can express the flight performance of the launch vehicle with accuracy. The solid launch vehicle researched can meet the launching capability requirements for launching a payload of 300 kg to 200 km Sun-synchronous orbit, and the attitude control system can ensure the attitude control precision of the launch vehicle. All this can help provide a theoretic basis for the scheme demonstration and preliminary design of the solid launch vehicle.

Key words: small solid launch vehicle, trajectories, jet, grid fin, launching capability

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