Power Analysis of Optimal Earth Observation Micro-Satellite Design Under Different Control Parameter

2018 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES) Pub Date : 2018-09-01 DOI:10.1109/ICARES.2018.8547065

M. S. N. Ubay, A. Halim

{"title":"Power Analysis of Optimal Earth Observation Micro-Satellite Design Under Different Control Parameter","authors":"M. S. N. Ubay, A. Halim","doi":"10.1109/ICARES.2018.8547065","DOIUrl":null,"url":null,"abstract":"The main task of an earth observation satellite is to deliver accurate and valid earth surface information to the ground station. In order to perform this task, the satellite is equipped with an attitude control system. The control system establishes closed-loop with attitude sensors, especially in the imaging operation. However, the limitation of satellite power supply capacity causes the restriction of attitude control operation, which in turn, limits the satellite imaging capacity. The aim of this paper is to analyze the power performance of optimal satellite design by observing the effects of a Proportional Integral Differential (PID) parameter changes to satellite power consumption. In this paper, firstly optimal satellite parameters are chosen. The parameter choice is based on a quadratic objective function that representing power consumption. In the sequence, the PID attitude control system is designed for the satellite. Through simulation, the effects of various PID parameters have been studied.","PeriodicalId":113518,"journal":{"name":"2018 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","volume":"4 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2018-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"2018 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1109/ICARES.2018.8547065","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}

引用次数: 0

Abstract

The main task of an earth observation satellite is to deliver accurate and valid earth surface information to the ground station. In order to perform this task, the satellite is equipped with an attitude control system. The control system establishes closed-loop with attitude sensors, especially in the imaging operation. However, the limitation of satellite power supply capacity causes the restriction of attitude control operation, which in turn, limits the satellite imaging capacity. The aim of this paper is to analyze the power performance of optimal satellite design by observing the effects of a Proportional Integral Differential (PID) parameter changes to satellite power consumption. In this paper, firstly optimal satellite parameters are chosen. The parameter choice is based on a quadratic objective function that representing power consumption. In the sequence, the PID attitude control system is designed for the satellite. Through simulation, the effects of various PID parameters have been studied.

查看原文本刊更多论文

不同控制参数下对地观测微卫星优化设计功率分析

对地观测卫星的主要任务是向地面站提供准确有效的地表信息。为了完成这项任务，卫星配备了姿态控制系统。控制系统与姿态传感器建立了闭环，特别是在成像操作中。然而，卫星供电能力的限制导致姿态控制操作的限制，进而限制了卫星的成像能力。本文的目的是通过观察比例积分微分(PID)参数变化对卫星功耗的影响来分析卫星优化设计的功率性能。本文首先选取最优卫星参数;参数选择是基于一个表示功耗的二次目标函数。在此基础上，设计了卫星的PID姿态控制系统。通过仿真，研究了不同PID参数对系统的影响。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

求助全文

约1分钟内获得全文求助全文

来源期刊

2018 IEEE International Conference on Aerospace Electronics and Remote Sensing Technology (ICARES)

自引率

0.00%

发文量