面向控制的高超声速飞行器总体优化设计方法  

Analysis of the control-oriented conceptual design optimization methods for hypersonic aerospace vehicles

作　　者：苏二龙[1] 罗建军[1] 闫颖鑫[2] 方群[1] 黄兴李[2] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]北京临近空间飞行器系统工程研究所,北京100076

出　　处：《飞行力学》2012年第3期267-271,共5页Flight Dynamics

摘　　要：从前期高超声速飞行器基础理论以及关键技术的研究到现今的飞行试验可以看出,高超声速飞行器在总体设计阶段过晚考虑飞行器动力学特性和控制性能会给后期控制系统设计带来极大的困难。在对两类高超声速飞行器试飞与控制相关问题分析的基础上,提出了面向控制的高超声速飞行器总体优化设计方法,给出了面向控制的总体优化设计研究方法、思路和模块框架。From the early phase of the hypersonic aerospace vehicle basic theory and key technologies research to the current flight tests,it can be seen that delaying application of detailed dynamics analysis and controls design in the conceptual design of hypersonic aerospace vehicle phase would lead to great challenge to the control system design.In this paper,the control-oriented conceptual design optimization methods for a hypersonic aerospace vehicle were brought forward based on two types of flight test and the analysis of control-related problems of a hypersonic aerospace vehicle.And,the control-oriented conceptual design optimization research outlines and the module frame were given finally.

关 键 词：高超声速飞行器 面向控制 总体优化设计 动力学模型 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]