Design and verification of kinematic system in deploying mechanism for CubeSats

Jiao-long ZHANG; Jun ZHOU

doi:10.3788/OPE.20172504.0919

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Design and verification of kinematic system in deploying mechanism for CubeSats

Micro/Nano Technology and Fine Mechanics | 更新时间：2020-07-07

- Design and verification of kinematic system in deploying mechanism for CubeSats
- Optics and Precision Engineering Vol. 25, Issue 4, Pages: 919-927(2017)
- 作者机构：
  
  西北工业大学精确制导与控制研究所陕西省微小卫星工程实验室, 陕西西安 710072
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20172504.0919
  CLC： V421.7
- Received：07 September 2016，
  
  Accepted：07 December 2016，
  
  Published：25 April 2017
- 稿件说明：
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Jiao-long ZHANG, Jun ZHOU. Design and verification of kinematic system in deploying mechanism for CubeSats[J]. Optics and precision engineering, 2017, 25(4): 919-927.
DOI：

Jiao-long ZHANG, Jun ZHOU. Design and verification of kinematic system in deploying mechanism for CubeSats[J]. Optics and precision engineering, 2017, 25(4): 919-927. DOI： 10.3788/OPE.20172504.0919.

摘要

为实现“翱翔之星”立方星在轨可靠分离，达到初始分离速度和姿态的要求，设计了立方星星箭分离机构运动系统并进行了实验验证。提出了一种利用分离弹簧推动立方星打开舱门，并采用弹簧销轴完成舱门锁定的运动系统结构方案。首先，基于能量守恒定理确定了分离弹簧的结构参数；其次，建立了星箭分离过程中立方星与舱门的运动耦合系统动力学模型，并利用MATLAB软件进行了数值仿真；最后，对星箭分离机构样机进行了地面分离试验。实验结果显示，实际分离过程与数值仿真结果基本一致，实现了立方星无干涉分离及舱门的可靠锁定。该星箭分离机构成功实现了“翱翔之星”立方星的在轨分离，卫星下传数据表明其初始分离速度为1.08 m/s，三轴角速度均小于2°/s，完全满足立方星初始分离速度和姿态的要求，可为后续立方星星箭分离机构的标准化设计提供参考。

Abstract

To implement the reliable deployment for the CubeSat "star of Aoxiang" on-orbit and to meet the requirements of initial deploying velocity and deploying posture

a kinematic system in deploying mechanism for CubeSats was designed and corresponding experimental verification was performed. A structure scheme of the kinematics system was proposed. It uses a disengaging spring to impulse the CubeSat for opening cabin door and uses a spring pin to lock the door. Firstly

structure parameters of the disengaging spring were confirmed according to energy conservation principle. Then

a dynamic model for kinematic coupling system between CubeSat and cabin door in the process of deployment was established

and a numerical simulation was implemented by MATLAB software. Finally

ground deploying tests were carried out for a prototype of the deploying mechanism. The experimental results show that the actual deployment process is the same as numerical simulation result basically and it realizes the deployment of CubeSats without interference and the reliable lock of cabin door. The proposed deploying mechanism realizes on-orbit deployment of CubeSat "star of Aoxiang" successfully. The downlink data indicate that initial deploying velocity is 1.08 m/s and three-axis angular velocity is less than 2°/s

which meets the requirements of initial depoloying velocity and posture for CubeSat completely. It provides references for standardized design of deploying mechanisms for following CubeSats.

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Keywords

references

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