某自旋微小空间飞行器运动过程研究  

Movement process of spinning micro-spacecraft

作　　者：刘赟[1,2] 王浩[2] 陶如意[2] 朱德龙 

机构地区：[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

出　　处：《南京理工大学学报》2014年第3期385-389,共5页Journal of Nanjing University of Science and Technology

基　　金：南京理工大学自主科研基金(2011YBXM110)

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°。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＆nbsp;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°.

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 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]