载人飞船再入轨道和制导规律设计及六自由度弹道仿真  

Re-Entry Orbit Guidance Law Design and Six FreeDegree Ballistic Simulation for Manned Spaceboat

作　　者：赵汉元[1] 

机构地区：[1]国防科学技术大学,长沙410073

出　　处：《航天返回与遥感》2001年第1期38-42,共5页Spacecraft Recovery & Remote Sensing

摘　　要：载人飞船再入轨道和再入制导规律设计是载人飞船成功返回的关键技术。文章综合介绍再入轨道设计方法 ,用变ν(t)来满足轨道设计的要求 ;研究了再入纵向制导和侧向制导 ,用极大值原理确定纵向制导反馈增益系数 ,引入“漏斗式”的侧向制导 ,其制导效果良好 ;利用转移矩阵进行姿态控制可以解决欧拉角交连和奇异问题 ;Re_entry orbit guidance law design is one of key techniques for manned spaceboat. The paper introduces a re_entry orbit design method which take the variable ν(t) to meet the requirement of orbit design. In the field of longitudinal guidance, it applies the maximum principal to define the feedback gain factor. In the field of lateral guidance, it introduces “funnel_shaped” method. They are effective. It applies the transfer array to control attitude. The paper also brings out an iterative method for the GNC integration design of re_entry section of manned spaceboat.

关 键 词：返回轨道设计 再入制导 六自由度弹道仿真 载人飞船 再入轨道 制导规律设计 

分 类 号：V525[航空宇航科学与技术—人机与环境工程]