摘要
针对控制系统,采用姿控发动机和格栅舵的小型多级固体运载火箭开展了运载能力分析研究。给出了运载火箭飞行方案,提出了一种飞行程序角的工程设计方法。给出了姿控发动机工作模型,建立了六自由度弹道计算和优化模型,采用混合进化算法进行弹道优化,并给出了仿真算例。仿真计算及分析表明,小型多级固体运载火箭满足发射小卫星的运载能力要求,姿控发动机推进剂分配方案合理,为总体方案论证和初步设计提供了理论依据。
The launching capability of small muhiple-stage solid launch vehicles was analyzed, which use attitude control motor and grid fins in the control system. The flight scheme of launch vehicle was given, and a design method of flight sequence angle was put forward. Also the work model of attitude control motor was given, and the model for six-degree-of-freedom trajectory calculation and optimization was established. Futhermore an optimization calculation case with hybrid evolutionary algorithm was given. Simulation and computational results show that the small multiple-stage solid launch vehicles can meet the requirements of launching capability for launching small satellites, and the scheme for propellant of attitude control motor is reasonable. All those can provide theoretic reference for feasibiligy study and preliminary design of solid launch vehicles.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2009年第4期355-359,共5页
Journal of Solid Rocket Technology
基金
国家高技术研究发展计划("863"计划)资助项目(2006AAXO2106)
关键词
小型固体运载火箭
飞行程序
混合进化算法
弹道优化
运载能力
small solid launch vehicle
flight program
hybrid evolutionary algorithm
trajectory optimization
launching capability
