[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1; 2; 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 Yun1; 2; Wang Hao2; Tao Ruyi2; Zhu 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:
spacecrafts; environmental factors; orbital dynamic models; Euler equation; attitude dynamic models; dualEuler method; orbital parameters; attitude parameters; air density; gravitational 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°.

参考文献/References:

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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