| 引用本文: | 冯佳佳,王佐伟.基于综合评价指标的航天器反作用轮执行机构配置[J].控制理论与应用,2018,35(2):162~168.[点击复制] |
| FENG Jia-jia,WANG Zuo-wei.Spacecraft reaction wheel actuator configuration based on comprehensive evaluation index[J].Control Theory and Technology,2018,35(2):162~168.[点击复制] |
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| 基于综合评价指标的航天器反作用轮执行机构配置 |
| Spacecraft reaction wheel actuator configuration based on comprehensive evaluation index |
| 摘要点击 1928 全文点击 1586 投稿时间：2017-04-05 修订日期：2017-08-13 |
| 查看全文 查看/发表评论 下载PDF阅读器 |
| DOI编号 10.7641/CTA.2017.70226 |
| 2018,35(2):162-168 |
| 中文关键词 航天器 反作用轮 执行机构配置 评价方法 |
| 英文关键词 spacecraft reaction wheel actuator configuration evaluation method |
| 基金项目 国家自然科学基金项目(61333008)资助. |
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| 中文摘要 |
| 本文针对航天器控制系统设计中如何进行执行机构配置这一问题, 提出一种基于综合评价指标的航天器
反作用轮执行机构配置方法. 首先, 根据控制系统中执行机构配置的功能需求和硬件需求, 确定出满足需求的可行
配置方案集. 该方案集内的执行机构选择为反作用轮, 其安装结构选择为斜装式, 安装角是根据控制系统的实际需
求并以能耗最小为目标进行确定的. 然后, 针对确定出的可行配置方案集, 以执行机构配置的考量特性为评价指标
进行综合评价, 确定出可行配置方案集内的最优配置方案. 在评价方法中, 以最小二乘为工具对主观评价方法和客
观评价方法进行优化, 以各方案对正负理想方案的贴近度为依据确定出方案的优劣. 文章最后, 以航天器控制系统
设计中的实际执行机构配置需求为例, 应用该方法进行配置, 结果表明该方法可行和有效, 具有工程应用价值. |
| 英文摘要 |
| This paper presents a method of spacecraft reaction wheel actuator configuration based on comprehensive
evaluation index, which can be useful in the design of spacecraft control systems. Firstly, based on the functional and
hardware requirements of the actuator configuration in the control system, a set of feasible configuration schemes that
satisfies the requirements is determined. Reaction wheel is selected as the actuator in this set. In addition, its mounting
structure is skewed, with the mounting angle of the structure determined by the actual requirements of the control system
and the minimum energy consumption. Secondly, the optimal configuration scheme of the feasible configuration scheme
set is determined by the comprehensive evaluation of the characteristics of the actuator configuration. The least squares
method is used to optimize the subjective and objective evaluation methods, with the merits of the scheme determined by its
proximity to the positive and negative ideal schemes. Finally, the proposed method is applied to the actuator configuration
requirements of a spacecraft control system design, with the results showing that the method is feasible and effective and,
consequently, has value for engineering applications. |
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