航天器刚性太阳翼在轨一维展开时间近似算法
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摘要
针对航天器总体方案设计阶段迭代数值仿真太阳翼在轨展开时间计算复杂问题,以航天器刚性基板一维展开太阳翼为研究对象,将太阳翼的在轨展开运动简化为单自由度的刚性运动。利用动-势能守恒原理,推导了太阳翼在轨展开时间的理论公式。根据实际工程参数对太阳翼展开时间的理论公式进行了简化、拟合,建立了太阳翼展开时间的近似算法。近似算法解析计算的太阳翼在轨展开时间与数值仿真计算结果比对表明:相对误差小于10%,可以满足工程要求。用该近似算法,可在航天器总体方案设计阶段较为简单地计算并合理提出太阳翼在轨展开时间指标。
Focusing on the complex computational process of the deployment time by numerical simulation in spacecraft conceptual design,usually being many times iterative computation,the engineering-approximate 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 engineering-approximate model is simplified according to the solar wings design.The error using engineering-approximate method is less than 10% by verifying with to numerical simulation.This solution provides an easy analytical tool for the spacecraft system engineers assessing solar wing deployment time in concept design phase.
Focusing on the complex computational process of the deployment time by numerical simulation in spacecraft conceptual design,usually being many times iterative computation,the engineering-approximate 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 engineering-approximate model is simplified according to the solar wings design.The error using engineering-approximate method is less than 10% by verifying with to numerical simulation.This solution provides an easy analytical tool for the spacecraft system engineers assessing solar wing deployment time in concept design phase.
引文
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[10]张永,彭向中.固定太阳翼展开后外弯基频的工程计算[J].宇航学报,2010,31(1):50-54Zhang Yong,Peng Xiangzhong.Spacecraft system design solar wings without yokes first mode frequency engineering-approximate method[J].Journal of Astronautics,2010,31(1):50-54(in Chinese)
[2]张和芬,袁智,柳翠翠.高分三号卫星飞行程序设计与在轨验证[J].航天器工程,2017,26(6):34-39Zhang Hefen,Yuan Zhi,Liu Cuicui.Design and onorbit verification of GF-3satellite flight program[J].Spacecraft Engineering,2017,26(6):34-39(in Chinese)
[3]王晛,陈天智,柴洪友.太阳翼地面展开锁定的动力学仿真分析[J].航天器工程,2011,20(3):86-92Wang Xian,Chen Tianzhi,Chai Hongyou.Dynamics simulation analysis of solar array ground deployment and locking[J].Spacecraft Engineering,2011,20(3):86-92(in Chinese)
[4]安源,谷松,金光.卫星太阳翼展开运动的分析及仿真[J].中国光学与应用光学文摘,2009,2(1):29-35An Yuan,Gu Song,Jin Guang.Analysis and simulation of deployment motion of satellite solar array[J].Chinese Journal of Optics and Applied Optics,2009,2(1):29-35(in Chinese)
[5]杨军.大型卫星太阳翼展开动力学研究[D].哈尔滨:哈尔滨工业大学,2006Yang Jun.Deployment dynamics of solar panels on large scale satellite[D].Harbin:Harbin Institute of Technology,2006(in Chinese)
[6]任守志,刘立平.零重力试验装置对太阳翼展开影响分析[J].航天器工程,2008,17(6):73-78Ren Shouzhi,Liu Liping.Influence of the zero-gravity test facility on the solar array's deployment test[J].Spacecraft Engineering,2008,17(6):73-78(in Chinese)
[7]马睿,姜东,吴邵庆,等.考虑重力影响的太阳翼模型修正方法研究[J].宇航学报,2014,35(12):1373-1378Ma Rui,Jiang Dong,Wu Shaoqing,et al.A model updating method for solar array considering the influence of gravity[J].Journal of Astronautics,2014,35(12):1373-1378(in Chinese)
[8]侯鹏,李志慧,宋涛,等.卫星太阳翼板面水平展开试验方法[J].哈尔滨工业大学学报,2016,48(10):176-182Hou Peng,Li Zhihui,Song Tao,et al.A novel method for horizontal deployable experiment of satellite solar array[J].Journal of Harbin Institute of Technology,2016,48(10):176-182(in Chinese)
[9]赵伟,雷军刚,程玉峰,等.太阳翼地面展开实验过程的振动监测[J].强度与环境,2007,34(1):49-54Zhao Wei,Lei Jungang,Cheng Yufeng,et al.Monitoring vibration of the solar wing spreading experiment[J].Structure&Environment Engineering,2007,34(1):49-54(in Chinese)
[10]张永,彭向中.固定太阳翼展开后外弯基频的工程计算[J].宇航学报,2010,31(1):50-54Zhang Yong,Peng Xiangzhong.Spacecraft system design solar wings without yokes first mode frequency engineering-approximate method[J].Journal of Astronautics,2010,31(1):50-54(in Chinese)