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一种亚轨道飞行器再入飞行的攻角制导方法
张珩; 李文皓; 肖歆昕
2013-04-10
Rights Holder中国科学院力学研究所
Abstract本发明公开了一种亚轨道飞行器再入飞行的攻角制导方法,通过仿真模拟分时间段获取攻角设计的预测值,对于每一时间段,利用飞行器同态预测模型,找到使飞行器的法向过载值始终处于期望的法向过载动平衡的波动区域内的攻角设计预测值,实现该时间段内的法向过载动态平衡;利用拟合方法,由攻角设计预测值得到飞行器实际再入飞行的攻角设计参数,确定飞行器再入飞行攻角设计值;在各飞行时刻引入阻力加速度积分比修正,使得实际再入飞行的阻力加速度积分值与攻角设计值下的预测阻力加速度积分值趋同,进而使得亚轨道飞行器再入飞行的法向过载在由各时间段组成的动平衡段中维持于预定区间上下波动,达到降低亚轨道再入飞行的法向过载峰值的目的。
Application Date2010-10-28
Date Available2013-04-11
Patent NumberZL201010522829X
Language中文
Country中国
Document Type专利
Identifierhttp://dspace.imech.ac.cn/handle/311007/47147
Collection先进制造工艺力学实验室
Recommended Citation
GB/T 7714
张珩,李文皓,肖歆昕. 一种亚轨道飞行器再入飞行的攻角制导方法. ZL201010522829X[P]. 2013-04-10.
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