| 引用本文: | 孔宪仁,武晨,李海勤,等.反电动势对无扰载荷航天器精确定向的影响.[J].国防科技大学学报,2019,41(2):75-81.[点击复制] |
| KONG Xianren,WU Chen,LI Haiqin,et al.Effect of back electromotive force on accurate pointing of disturbance-free-payload spacecraft[J].Journal of National University of Defense Technology,2019,41(2):75-81[点击复制] |
|
| |
|
|
| 本文已被：浏览 6611次 下载 5197次 |
| 反电动势对无扰载荷航天器精确定向的影响 |
| 孔宪仁, 武晨, 李海勤, 杨震国 |
|
(哈尔滨工业大学 卫星技术研究所， 黑龙江 哈尔滨 150080)
|
| 摘要: |
| 无扰载荷航天器中非接触式作动器反电动势会引起有效载荷模块与支持模块之间的耦合，影响有效载荷模块的精确定向性能。通过建立无扰载荷航天器的耦合动力学模型，分析非接触式作动器反电动势对有效载荷模块精确定向性能的影响。考虑六支杆立方构型无扰载荷接口，结合拉格朗日方程和牛顿欧拉方法建立有效载荷模块平台动力学模型。推导非接触式作动器的输出力模型，并引入有效载荷模块平台动力学模型，给出考虑非接触式作动器反电动势的耦合动力学模型。将支持模块上飞轮动静不平衡引起的谐振作为干扰力矩，建立了无扰载荷航天器在轨定向状态的Simulink仿真模型。仿真结果表明，反电动势系数越大，干扰力矩对有效载荷模块的影响越大，有效载荷模块精确定向精度越低。 |
| 关键词: 无扰载荷航天器 反电动势 有效载荷精确定向 耦合动力学模型 |
| DOI：10.11887/j.cn.201902012 |
| 投稿日期：2017-12-26 |
| 基金项目: |
|
| Effect of back electromotive force on accurate pointing of disturbance-free-payload spacecraft |
| KONG Xianren, WU Chen, LI Haiqin, YANG Zhenguo |
|
(Research Center of Satellite Technology, Harbin Institute of Technology, Harbin 150080, China)
|
| Abstract: |
| The back electromotive force of the non-contact actuator in a disturbance-free-payload spacecraft can cause the coupling between payload module and support module, hence can be detrimental to the precise pointing of payload module. To analyze its effect, a coupling dynamics model was established for the disturbance free payload spacecraft. In consideration of the cubic architecture disturbance-free-payload-interface, this dynamics model was developed by a combination of the Newton-Euler method with the Lagrange formulation. The output force of the non-contact actuator was derived, which was introduced into the dynamics model of the payload module platform, then the coupling dynamics model with the back electromotive force was obtained. Considering the harmonic vibration caused by the static and dynamic unbalance of the flywheels as the disturbance torque, an on-orbit pointing model for the disturbance-free-payload spacecraft was established in Simulink. The simulation results illustrate that the larger value of the back electromotive force coefficient will cause larger effect on payload module. |
| Keywords: disturbance-free-payload spacecraft back electromotive force accurate pointing of payload module coupling dynamics model |
|
|
|
|
|
