航天器工程2019，Vol.28Issue(2)：51-55,5.DOI:10.3969/j.issn.1673G8748.2019.02.008
航天器刚性太阳翼在轨一维展开时间近似算法
EngineeringGapproximate Method of the Spacecraft Solar Wing Deployment Time with Rigid Substrate in Orbit
苟仲秋 1张永 1王杰1
作者信息
- 1. 中国空间技术研究院载人航天总体部,北京 100094
- 折叠
摘要
Abstract
Focusing on the complex computational process of the deployment time by numerical simulation in spacecraft conceptual design,usually being many times iterative computation,the engineeringGapproximate method is proposed for calculating the orbital deployment time of solar wings with rigid substrate and yokes.The deployment process is assumed to be equivalently single freedom rigid kinematics model,and based on conservation of energy,a deployment time theory formula is proposed,then engineeringGapproximate model is simplified according to the soG lar wings design.The error using engineeringGapproximate method is less than 10% by verifying with to numerical simulation.This solution provides an easy analytical tool for the spacecraft sysG tem engineers assessing solar wing deployment time in concept design phase.关键词
航天器/刚性太阳翼/展开时间Key words
spacecraft/rigid substrate solar wing/deployment time分类
航空航天引用本文复制引用
苟仲秋,张永,王杰..航天器刚性太阳翼在轨一维展开时间近似算法[J].航天器工程,2019,28(2):51-55,5.
