| GEO星载激光通信终端二维转台伺服机构热设计 |
| |
| 引用本文： | 刘百麟,刘绍然,周佐新,于思源.GEO星载激光通信终端二维转台伺服机构热设计[J].红外与激光工程,2016,45(9):922003-0922003(6). |
| |
| 作者姓名： | 刘百麟 刘绍然 周佐新 于思源 |
| |
| 作者单位： | 1.中国空间技术研究院 通信卫星事业部,北京 100094; |
| |
| 基金项目： | 国家自然科学基金重点科学基金（11404082） |
| |
| 摘 要： | 星载激光通信终端二维转台伺服机构是一种高精度指向调节机构，工作时对温度场稳定性及均匀性有较高要求，空间热环境剧烈变化是诱导其温度波动的外因。为达到在轨温度场精稳控制，提出了一种GEO星载经纬仪式激光通信终端二维转台伺服机构温控方案，通过机电热一体化结构设计选材、主动跟踪控温、散热及隔热设计等技术途径，实现了空间大尺寸的高精密二维转台伺服机构温度场稳定性与均匀性的精稳控制，并经过热试验与热分析综合验证，结果表明:工作轨道全寿命期间，伺服机构核心部件温度稳定控制在22.3～34.6℃范围内，温度场均匀性可控制在4℃以内。
|
| 关 键 词： | 激光通信终端 经纬仪式 二维转台伺服机构 热设计 |
| 收稿时间： | 2016-01-10 |
Thermal control study of the 2D gimbal servo mechanism of GEO satellite-borne laser communication terminal |
| |
| Affiliation: | 1.Institute of Telecommunication Satellite,China Academy of Space Technology,Beijing 100094,China;2.National Key Laboratory of Tunable Laser Technology,Harbin Institute of Technology,Harbin 150001,China |
| |
| Abstract: | The 2D gimbal servo mechanism of the satellite-borne laser communication terminal, which is a pointing-regulating mechanism with high precision, has a strict requirement of temperature level and uniformity at the working time. The acute change of the orbital heat flux is the external factor that induces the temperature volatility. The thermal control scheme of the 2D gimbal servo mechanism of the GEO satellite-borne gimbal-type laser communication terminal was proposed. In the scheme, the structure design and material selection based on the structural/electrical/thermal concurrent design, active tracking temperature control, thermal dissipation and insulation design were all used to realize the precise control of the stability and uniformity of the temperature field of the space 2D gimbal servo mechanism with large scale and high precision. Meanwhile, the scheme was verified by both the thermal simulation and experiment test. The results show that the temperature range of the servo mechanism's core component is from 22.3℃ to 34.6℃ and its temperature difference is less than 4℃ in the whole lifetime on the working orbit. |
| |
| Keywords: | |
|
| 点击此处可从《红外与激光工程》浏览原始摘要信息 |
|
点击此处可从《红外与激光工程》下载全文 |
|
