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Development of Optimal Guidance and Adaptive Algorithm for Vertical Landing Vehicle

垂直着陆飞行器最优制导与自适应算法开发

基本信息

批准号：
14550856
负责人：
SHIMADA Yuzo
金额：
$ 2.37万
依托单位：
Nihon University
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (C)
财政年份：
2002
资助国家：
日本
起止时间：
2002 至 2004
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-14550856/
关键词：
Minimum Jerk Optimal Guidance Reusable Launch Vehicle Exact Linearization DPS board Reentry Guidance Real Time Simulation Guidance and Control Time-to-go

项目摘要

1.Development of optimal guidance lawa)From 2002 to 2003, an optimal guidance law was investigated for the vertical and soft landing of a lunar lander, and obtained results were presented at the ICCAS conferences held in Korea in 2002 and 2003. b)A novel minimum jerk optimal guidance law was theoretically developed by assuming that the equation of motion of the Lunar lander was linear, and was submitted to the Transactions of the Japan Society for Aeronautical and Space Sciences with its simulation results in 2004. An article on this will appear in Vol.48,No.159 of this transaction in 2005. c)In 2004, by assuming that the motion of a reentry vehicle was nonlinear, a new guidance law was developed using an exact linearization method with the previously obtained minimum jerk optimal guidance law. The result was also submitted to the Journal of the Japan Society for Aeronautical and Space Sciences and will appear in this journal in the summer of 2004.2.Real time simulation using muti-DSP … More boardsa)A real time simulation was carried out using multi-DSP boards in order to confirm the validity of the above- mentioned optimal guidance law. In this simulation, the effects of finite-word length, a limiting-zero problem due to discretization, computational time delay, and measurement noise on the control system were examined, b)In particular, a theoretical analysis of the limiting-zero problem was carried and the relationship between the sampling time and the limiting-zero problem was clarified, c)Furthermore, a more precise simulation was carried out by reviewing the extraction process in which an optimal time-to-go solution was chosen from the real number solutions obtained from a six-degree algebraic equation with respect to time-to-go. d)Lastly, in the simulation in which actual sensor specifications were considered, the measurement noise was revealed to cause the downrange error to deviate at most 12 m at the terminal point (target point) ; however, its effect on fuel consumption was negligible. This result was presented at a domestic conference of the Japan Society for Aeronautical and Space Sciences in March, 2004. Less

1.最优制导的发展(LAWA)2002年至2003年，研究了月球着陆器垂直和软着陆的最优制导规律，并在2002年和2003年在韩国举行的ICCAS会议上介绍了所取得的结果。B)假设月球着陆器的运动方程是线性的，从理论上提出了一种新的最小抖动最优制导律，并于2004年提交给日本航空航天科学学会会刊及其仿真结果。关于这一点的一篇文章将出现在2005年这笔交易的第48卷第159期。C)2004年，通过假设再入飞行器的运动是非线性的，利用先前得到的最小急速最优导引律，采用精确线性化方法设计了一种新的导引律。研究结果还被提交给日本航空航天科学学会杂志，并将于2004年夏天发表在该杂志上。使用多数字信号处理器…进行实时仿真为了验证上述最优导引律的有效性，利用多块数字信号处理器板进行了实时仿真。在该仿真中，考察了有限字长、离散化引起的极限零问题、计算时延和测量噪声对控制系统的影响；b)对极限零问题进行了理论分析，阐明了采样时间与极限零问题之间的关系；c)通过回顾从关于剩余时间的六次代数方程得到的实数解中选择最优解的提取过程，进行了更精确的仿真。D)最后，在考虑实际传感器规格的仿真中，测量噪声导致在终点(目标点)处的量程误差最多偏离12m，但其对油耗的影响可以忽略不计。这一结果在2004年3月日本航空航天科学学会的一次国内会议上公布。较少

项目成果

期刊论文数量（28）

专著数量（0）

科研奖励数量（0）

会议论文数量（0）

专利数量（0）

垂直着陸機における誘導システムの構築

垂直起降飞机制导系统的构建

DOI：
发表时间：
2005
期刊：
日本航空宇宙学会北部支部2005年講演会
影响因子：
0
作者：
小川貴広;安部明雄;嶋田有三;内山賢治
通讯作者：
内山賢治

Minimum Jerk Guidance for Lunar Lander

月球着陆器的最小加加速度指南

DOI：
发表时间：
2005
期刊：
Transactions of the Japan Society for Aeronautical and Space Sciences 48・159
影响因子：
0
作者：
Kenji Uchiyama;Yuzo Shimada;Kazuhiro Ogawa
通讯作者：
Kazuhiro Ogawa

野村享右, 内山賢治, 嶋田有三: "月面着陸機の誘導制御アルゴリズムの検証"第47回宇宙科学技術連合講演会講演集. 631-636 (2003)

Kyosuke Nomura、Kenji Uchiyama、Yuzo Shimada：“月球着陆器制导和控制算法的验证”第 47 届空间科学技术联盟会议记录 631-636 (2003)。