项目名称: 新型火星进入鲁棒自适应制导与容错控制方法研究
项目编号: No.61273051
项目类型: 面上项目
立项/批准年度: 2013
项目学科: 自动化技术、计算机技术
项目作者: 李爽
作者单位: 南京航空航天大学
项目金额: 80万元
中文摘要: 传统的火星进入制导控制采用纯弹道进入和开环控制方式,由于火星进入过程中状态和环境参数存在较大的不确定性,导致最终的着陆误差椭圆半径在数百公里的量级,无法满足下一代火星探测任务对制导精度和控制系统可靠性的要求。本项目拟从新型火星进入鲁棒自适应制导方法、火星进入轨迹优化与最优制导一体化设计方法和火星进入容错控制方法三个方面出发,对下一代火星进入制导与控制所涉及的关键技术进行深入系统地研究,为我国即将开展的火星探测任务提供必要的技术储备。通过本项目的研究,将完成基于直接自适应和非线性结构自适应模型逆的火星进入制导、基于神经网络滑模变结构的火星进入制导、考虑状态灵敏度的火星进入标称轨迹优化与最优制导一体化设计、基于改进神经网络算法的火星进入容错控制和基于直接模型参考自适应的火星进入控制重构等新型制导控制方法和关键技术的研究,并通过数学仿真和半实物仿真对所发展的制导与控制方法进行仿真验证。
中文关键词: 火星进入;鲁棒自适应制导;神经网络;容错控制;一体化设计
英文摘要: Traditional Mars entry adopts pure ballistic entry and open-loop control mode. The huge uncertainties in the entry state and environment parameters lead to the radius of the final landing error ellipse on the order of hundreds of kilometers, which cannot meet the requirements of next-generation Mars exploration missions on entry guidance precision and control system reliability. The project intends to systematically investigate the innovative methods and key technologies involved in the next-generation Mars enter guidance and control from the following three aspects, new robust and adaptive Mars entry guidance methods, integrated design method of Mars entry nominal trajectory optimization and optimal guidance and Mars entry fault-tolerant control methods, which will provide the necessary technical reserves for China's upcoming Mars exploration missions. The main contents of this project include: direct mode adaptive, nonlinear structure adaptive model inversion and neural network sliding mode variable structure based Mars entry guidance, integration design method of Mars entry reference trajectory optimization and the optimal guidance considering the state sensitivity, improved neural network algorithm and based on Mars entry fault-tolerant control, direct model reference adaptive based Mars entry reconstruction
英文关键词: Mars entry;robust adaptive guidance;neural network;fault-tolerant control;integrated design