主动补偿式超低干扰力矩气浮转台的设计

刘延芳; 刘兴富; 齐乃明; 张刘

doi:10.3788/OPE.20162410.2432

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主动补偿式超低干扰力矩气浮转台的设计

微纳技术与精密机械 | 更新时间：2020-07-07

- 主动补偿式超低干扰力矩气浮转台的设计
- Design of supper low disturbance torque air bearing table with active compensation
- 光学精密工程 2016年24卷第10期页码：2432-2441
- 作者机构：
  
  1.哈尔滨工业大学航天学院, 黑龙江哈尔滨 150001
  2.上海微小卫星工程中心, 上海 201210
  3.吉林大学仪器科学与电器工程学院, 吉林长春 130061
- 作者简介：
  
  刘延芳(1986-),男,河南叶县人,博士后,讲师,硕士生导师,2014年于哈尔滨工业大学获得博士学位,主要从事航天器机电一体化及其地面试验技术、航天器及其结构动力学与控制、智能材料及智能结构动力学建模及控制。E-mail:lyf04025121@126.com
  [ "刘兴富(1990-),男,山东潍坊人,硕士,研究实习员,2013年于哈尔滨工业大学(威海)取得学士学位,2015年于哈尔滨工业大学取得硕士学位。主要从事空间机构设计,空间飞行器地面物理仿真试验" ]
- 基金信息：
  
  微小型航天器技术国防重点学科实验室开放基金资助项目(No.HIT.KLOF.MST.201507);中央高校基本科研业务费专项基金资助项目(No.HIT.NSRIF.201622)
- DOI：10.3788/OPE.20162410.2432
  中图分类号： V448.22;V474
- 收稿日期：2016-03-25，
  
  录用日期：2016-5-7，
  
  纸质出版日期：2016-10
- 稿件说明：
移动端阅览
刘延芳, 刘兴富, 齐乃明, 等. 主动补偿式超低干扰力矩气浮转台的设计[J]. 光学精密工程, 2016,24(10):2432-2441.

Yan-fang LIU, Xing-fu LIU, Nai-ming QI, et al. Design of supper low disturbance torque air bearing table with active compensation[J]. Optics and precision engineering, 2016, 24(10): 2432-2441.
刘延芳, 刘兴富, 齐乃明, 等. 主动补偿式超低干扰力矩气浮转台的设计[J]. 光学精密工程, 2016,24(10):2432-2441. DOI： 10.3788/OPE.20162410.2432.

Yan-fang LIU, Xing-fu LIU, Nai-ming QI, et al. Design of supper low disturbance torque air bearing table with active compensation[J]. Optics and precision engineering, 2016, 24(10): 2432-2441. DOI： 10.3788/OPE.20162410.2432.

摘要

由于微纳卫星反作用飞轮的输出力矩与气浮转台的干扰力矩属于同一量级，故无法直接采用气浮转台实现微纳卫星姿态动力学仿真及姿控系统的地面试验验证。为了解决这一问题，设计并研制了主动补偿式超低干扰力矩气浮转台。对气浮转台的干扰力矩进行分析，提出了3种减小干扰力矩的方法：通过优化设计，降低了黏滞阻尼力矩；通过配置斜向节流孔，并单独供气，产生大小可调的主动涡流以抵消气浮轴承的固有涡流，从而降低涡流力矩；利用气浮轴承的摆动特性实现高精度平衡调节，减弱了重力诱导力矩。最后，设计了微小力矩测量装置，测量了剩余干扰力矩并基于测试结果来指导涡流力矩和重力诱导力矩补偿过程。测试结果显示：气浮转台实现的干扰力矩小于5×10

-5

Nm，小于反作用飞轮的最小输出1×10

-4

Nm，满足微纳卫星姿态动力学及控制的地面验证需求。

Abstract

As the output moments of reaction wheels for micro-satellites and nano-satellites are the same as the disturbance moment of an Air Bearing Table (ABT)

the attitude dynamic simulation and ground test of the micro-satellites and nano-satellites can not be implemented directly by the ABT. To solve the problems

an active compensation ABT with a supper low disturbance moment was designed and developed. The disturbance moment of the ABT was analyzed and three kinds of methods to reduce the disturbance moment were proposed. Firstly

the viscous damping moment was reduced by optimizing design; Then

the vertex moment was reduced by setting sloping slant orifices to generate an active vertex to balance the inherent vertex of the air bearing

and to reduce the inherent vertex moment. Finally

the swing characteristics of air bearing was used to implement high precise balance adjustment and to reduce the gravity induced moment. A measuring device of micro-moment was designed and the remaining vertex moment was measured and the measuring results were used to direct the compensation of the vertex moment and gravity induced moment. Experimental results indicate that the disturbance moment of the ABT is smaller than 5×10

-5

which is less than the minimum output moment(1×10

-4

Nm) of the reaction wheel. Obtained results satisfy the requirements of the ground simulation of attitude dynamics and the control of micro-satellites and nano-satellites.

关键词

Keywords

references

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