[1]刘赟,王浩,陶如意,等.某自旋微小空间飞行器运动过程研究[J].南京理工大学学报(自然科学版),2014,38(03):385.
 Liu Yun,Wang Hao,Tao Ruyi,et al.Movement process of spinning microspacecraft[J].Journal of Nanjing University of Science and Technology,2014,38(03):385.
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某自旋微小空间飞行器运动过程研究
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《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

卷:
38卷
期数:
2014年03期
页码:
385
栏目:
出版日期:
2014-06-30

文章信息/Info

Title:
Movement process of spinning microspacecraft
作者:
刘赟12王浩2陶如意2朱德龙3
1.中国电子科技集团第二十八研究所,江苏 南京 210007;2.南京理工大学 能源与动力工程学院, 江苏 南京 210094;3.南昌陆军学院,江西 南昌 330103
Author(s):
Liu Yun12Wang Hao2Tao Ruyi2Zhu Delong3
1.The 28th Research Institute of China Electronics Technology Group Corporation,Nanjing 210007,China; 2.School of Energy and Power Engineering,NUST,Nanjing 210094,China; 3.Nanchang Military Academy,Nanchang 330103,China
关键词:
空间飞行器环境因素轨道动力学模型欧拉方程姿态动力学模型双欧法轨道参数姿态参数空气密度地球引力
Keywords:
spacecraftsenvironmental factorsorbital dynamic modelsEuler equationattitude dynamic modelsdualEuler methodorbital parametersattitude parametersair densitygravitational force
分类号:
V412.4
摘要:
为研究某自旋微小空间飞行器入轨运行一周的运动情况,建立各主要坐标系描述飞行器的运动状态。考虑较高轨道的空间环境因素对飞行器运行过程的影响,建立了飞行器轨道动力学模型和基于欧拉方程的姿态动力学模型。采用双欧法进行仿真计算,得到了飞行器入轨运行一周的轨道和姿态参数情况。结果表明:高轨道空间空气密度极低,飞行器主要受地球引力、太阳辐射压力及大气阻力的影响,靠自身旋转稳定,运动轨迹近似圆形,运行一周后轨道增高4.66 km,滚转角和偏航角产生波动,变化小于±0.04°;俯仰角随时间逐渐增大,变化幅度近似360°。
Abstract:
To study the movement of a certain spinning microspacecraft running a circle in orbit,primary reference frames are set up to describe the motion states of the spinning microspacecraft.An orbital dynamic model and an attitude dynamic model based on Euler equation are established considering the influences of environmental factors on the flight process of the spinning microspacecraft.The orbital and attitude parameters of the spinning microspacecraft running a circle in orbit are simulated using the dualEuler method.The results indicate that the air density of high altitude orbit is extremely low,and the spinning microspacecraft stabilized by spinning is mainly affected by the gravitational force,solar radiation pressure and atmospheric drag.The motion trajectory of the spinning microspacecraft approximates to a ring;the orbit altitude heightens 4.66 km after the spinning microspacecraft runs a circle;the roll angle and yaw angle fluctuate,the variation is less than ±0.04°;the pitch angle increases gradually over time,the change ranges approximate to 360°.

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备注/Memo

备注/Memo:
收稿日期:2012-10-30修回日期:2013-03-03
基金项目:南京理工大学自主科研基金(2011YBXM110)
作者简介:刘赟(1984-),女,博士,主要研究方向:飞行动力学,攻防对抗;E-mail:liuyun801@aliyun.com;通讯作者:王浩(1961-),男,博士,研究员,主要研究方向:武器发射动力学、子母战斗部开舱抛撒技术及子弹药弹道理论,E-mail:wanghao@njust.edu.cn。
引文格式:刘赟,王浩,陶如意,等.某自旋微小空间飞行器运动过程研究[J].南京理工大学学报,2014,38(3):385-389.
投稿网址:http://zrxuebao.njust.edu.cn
更新日期/Last Update: 2014-06-30