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火星探测器进入段自适应滑模制导律设计

发表时间:2014-06-30  浏览量:46216  下载量:22843
全部作者: 许康,马广富,李晓宇,周远强
作者单位: 哈尔滨工业大学航天学院
摘 要: 针对火星探测器进入段制导问题,设计自适应滑模制导律。首先,建立火星探测器进入段运动学模型,并对侧向运动方程进行线性化。基于由开伞点高度和飞行路径角构建的性能指标,采用Legendre伪光谱法优化得到进入段的标称轨迹和相应的阻力加速度。然后,采用神经网络逼近进入段参数不确定性,并设计自适应滑模制导律。最后,数学仿真结果表明,此设计方法能有效逼近系统不确定性,制导律优于传统的比例微分制导律。
关 键 词: 飞行器控制、导航技术;火星探测器;进入段;伪光谱法;神经网络;自适应滑模制导
Title: Design of adaptive sliding mode entry guidance law for Mars probe
Author: XU Kang, MA Guangfu, LI Xiaoyu, ZHOU Yuanqiang
Organization: School of Astronautics, Harbin Institute of Technology
Abstract: Considering Mars probe entry guidance law design problem, an adaptive sliding mode guidance law is presented. Firstly, the entry motion model of Mars probe is established and lateral motion model is linearized. Based on existing performance index, a nominal trajectory is designed using Legendre pseudo spectral method and drag. Then, a neural network is introduced to approximate the uncertainty throughout whole entry phase and an adaptive sliding mode guidance law is designed based on it. At last, simulation results show a more effective performance of the guidance law presented in this paper compared with traditional proportion differential guidance law.
Key words: aerocraft control, navigation technology; Mars probe; entry phase; pseudo spectral method; neural network; adaptive sliding mode guidance
发表期数: 2014年6月第12期
引用格式: 许康,马广富,李晓宇,等. 火星探测器进入段自适应滑模制导律设计[J]. 中国科技论文在线精品论文,2014,7(12):1213-1218.
 
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