摘要
针对小型运载火箭大气层飞行段飞行程序设计原则,提出并比较分析了指数斜率型、三角函数型、两段直线型和抛物线型等4种大气层飞行段飞行程序设计方案,研究了多次有迎角转弯技术在大推重比运载火箭大气层飞行段飞行程序设计中的应用。仿真结果表明,对于大推重比小型运载火箭,大气层飞行段采用多次有迎角转弯技术,可在一定程度上克服传统飞行程序设计方案带来的大迎角转弯问题。研究结果为小型运载火箭总体方案设计和弹道优化设计研究提供了理论基础。
The design constraint of flight program for small launch vehicles in atmosphere flight stage was summarized,four design schemes for flight program were proposed,including the exponential form,trigonometric function form,two-stage linear form and parabolic form,and some comparison was made by simulation and calculation.Meanwhile,the technology of making the multiple turn with attack angle was discussed,and simulation results show that,for small launch vehicle with large thrust-weight ratio,the problem of producing the large attack angle when making a turn using the traditional design method for flight program can be overcome in a certain extent by adopting the technology of multiple turn with attack angle.The research production provides theoretical basis for the study of overall design and trajectory optimization of a small launch vehicle.
出处
《飞行力学》
CSCD
北大核心
2010年第4期68-72,共5页
Flight Dynamics
基金
国家863计划基金资助(2007AAX02503)
中国博士后科学基金资助(200801491)
关键词
小型运载火箭
大气层飞行段
飞行程序
多次有迎角转弯
small launch vehicle
atmosphere flight stage
flight program
multiple turn with attack angle
