水平空中发射固体有翼运载火箭总体/动力/气动/轨道一体化设计与优化  

Integration design and optimization of system/solid rocket motor/aerodynamics/trajectory for horizontally air-launched vehicle with wings

作　　者：孙丕忠[1] 朱伯鹏[1] 夏智勋[1] 黄琳[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2005年第3期157-160,168,共5页Journal of Solid Rocket Technology

基　　金：国家863高新技术项目(2003AA765030)

摘　　要：综合考虑固体火箭发动机设计、带翼火箭气动外形设计、轨道设计和总体特性相互作用相互影响的情况下,建立了水平空中发射固体有翼运载火箭总体/动力/气动/轨道一体化设计优化模型和系统分析模型。测试了系统分析软件,应用基于方向的遗传算法优选了某水平空中发射固体有翼运载火箭28个设计参数。结果表明,计算结果与工程实际结果吻合较好,优化设计效果明显,优化所得火箭起飞质量是原方案的84.32%。In comprehensive consideration of mutual confinement of solid rocket motor design, aerodynamic contour design of rocket with wings, trajectory design and system characteristics, a series of system/solid rocket motor/aerodynamics/trajectory integration design and analysis models for an horizontally air-launched vehicle with wings were derived. The system analysis software was tested and 28 design parameters for an horizontally air-launched vehicle were optimized by means of an improved genetic algorithm. The resuits show that calculation results of system analysis software agree well with actual engineering results, and the effect of optimum design is obvious, the take-off mass of optimum design scheme is 84.32 percentage of the take-off mass of primary design scheme.

关 键 词：空中发射 固体推进剂火箭 一体化设计 优化设计 

分 类 号：V421.1[航空宇航科学与技术—飞行器设计]