重力空射稳定伞阻力特征自动化设计  

Automated Design of Stabilizing Parachute Drag Area for Gravity Air Launch

作　　者：尹凯[1] 张红英[1] 陈建平[1] 童明波[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《航天返回与遥感》2015年第1期9-15,共7页Spacecraft Recovery & Remote Sensing

基　　金：国家自然科学基金(11002070);江苏高校优势学科建设工程基金

摘　　要：为进行重力空射稳定伞的初步设计,文章以多体动力学软件(ADAMS)为二次开发平台,构建了重力空射箭-伞系统的动力学仿真模型;推导了火箭和稳定伞的气动模型,并利用动态链接子程序实现了气动力的加载;通过ADAMS命令语言建立了参数化模型和用户界面。在此基础上,自编可行方向优化算法实现了稳定伞阻力特征的自动化设计。最后,根据仿真计算结果对试验火箭出舱时间、安全通道、回收方式等问题进行了分析,为后续空射稳定伞的细节设计以及空射总体方案的确定提供了参考。In order to preliminarily design the stabilizing parachute for gravity air launch（GAL）, the rocket-parachute dynamic model is established based on multi-body dynamics software ADAMS. The aerodynamic models of rocket and parachute are derived, and the aerodynamic forces are applied with dll subroutines; the parametric model and user interface are built with ADAMS command language. In addition, the automated design of stabilizing parachute drag area is implemented with feasible direction method. Finally, the time test rocket stays in cabin, security channel and recovery method are analyzed. The results provide a reference for subsequent detail design of stabilizing parachute and verification of GAL overall design.

关 键 词：重力空射 稳定伞 火箭回收 多体动力学软件二次开发 可行方向法 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]