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Normal acceleration reduce guidanceand control for sub-orbit vehicle re-entry
Li WH(李文皓); Xiao XX(肖歆昕); Zhang H(张珩); Xiao XX(肖歆昕)
2017
会议名称21st AIAA International Space Planes and Hypersonics Technologies Conference
会议日期6-9 March 2017
会议地点Xiamen, China
会议录名称21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
摘要

In this paper, a new angle-of-attack(AOA) guidance law and controller with multi-control surface and reaction control system (RCS) are designed to reduce normal acceleration in sub-orbit re-entry phase. First, the six-degree-of-freedom (6-DOF) nonlinear dynamic model of sub-orbit vehicles established, and the overload characteristics is analyzed under traditional AOA guidance law. Second, an AOA guidance law added height element is proposed to reduce the Normal accelerate peak value during re-entry. Furthermore, an Inverse-PIDA control law and composite control strategy are designed to control multi-aerodynamic surface and RCS. Finally the proposed approach is applied in a sub-orbit vehicle re-entry flight, validation simulation are conducted by using the proposed guidance law and controller with the 6-DOF nonlinear dynamic model , Monte-Carlo statistical analysis shows it can get well control performance with 卤20% aerodynamic elements uncertainty and random wind. 漏 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词Aerodynamics Air Navigation Angle Of Attack Control Surfaces Control Theory Degrees Of Freedom (Mechanics) Dynamic Models Flight Control Systems Flight Simulators Monte Carlo Methods Reentry Spacecraft Surface Reactions Uncertainty Analysis Vehicles
ISBN号978-1-62410-463-3
URL查看原文
收录类别EI
语种英语
文献类型会议论文
条目标识符http://dspace.imech.ac.cn/handle/311007/72198
专题先进制造工艺力学重点实验室
通讯作者Xiao XX(肖歆昕)
推荐引用方式
GB/T 7714
Li WH,Xiao XX,Zhang H,et al. Normal acceleration reduce guidanceand control for sub-orbit vehicle re-entry[C]. USA:American Institute of Aeronautics and Astronautics Inc, AIAA,2017.
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