The Decision of the Maximum Synchronous Torque During the Solar Array Deployment Using the Closed Cable Loop

Year : 2025 | Volume : 15 | Issue : 03 | Page : 37 49
    By

    Hyon-Mu Jo,

  • Song-Hyok Kim,

  • Ji-Hyon Kim,

  • Ju-Song Thak,

  • Yong-Gil Han,

  1. Assistant Professor, Department of Mechanical Science and Technology, Kim Chaek University of Technology, Pyongyang, North Korea
  2. Assistant Professor, Department of Mechanical Science and Technology, Kim Chaek University of Technology, Pyongyang, North Korea
  3. Assistant Professor, Department of Mechanical Science and Technology, Kim Chaek University of Technology, Pyongyang, North Korea
  4. Assistant Professor, Department of Mechanical Science and Technology, Kim Chaek University of Technology, Pyongyang, North Korea
  5. Assistant Professor, Department of Mechanical Science and Technology, Kim Chaek University of Technology, Pyongyang, North Korea

Abstract

It was a long time since mankind explored and studied the universe, but the early-age power sources have not changed a lot over that period. Solar panels have been used long ago and are still in use today. However, their efficiency has improved considerably. Large and complicated solar arrays are now used instead of simply attaching the panels directly on the face of the satellite. A solar array is essential for a spacecraft to carry out its mission successfully and the first task for the spacecraft in space is the deployment of the solar array. Since there is not much space in the nose cone of the launch vehicle, a stowed position of the solar panels is required. Also, during launch and ascent, the launch loads can be transmitted to the satellite structure in a better way, because of the stiffness of the solar array in the stowed configuration and its ability to take up high natural frequencies. A solar array is attached to the satellite by means of a yoke. The purpose of the yoke is to keep the array out of the satellite’s own shadow, and several solar panels are connected by a rotating hinge here. In general, these solar arrays are deployed synchronously by a synchronous mechanism. The synchronization system controls the relative movement of the yoke and the panels with respect to the sidewall of the satellite. Hereby interference of the solar array with the satellite is prevented. The closed cable loop (CCL) is a typical synchronous mechanism for the solar array deployment. The closed cable loop device is known as a suitable instrument for deploying solar array configurations and arrays. This study provides a multi- DOF dynamic model of a solar array with n panels using the CCL. A formula to calculate the synchronous torque for the ideal synchronization is derived from the dynamic model, and its characteristics are analyzed. And then, the decision method of the maximum synchronous torque is provided. The calculation results indicate that the method is accurate enough and can be used to determine the CCL design parameters.

Keywords: Solar array, deployment, multi-DOF dynamic model, synchronous torque, linkage

[This article belongs to Journal of Aerospace Engineering & Technology ]

How to cite this article:
Hyon-Mu Jo, Song-Hyok Kim, Ji-Hyon Kim, Ju-Song Thak, Yong-Gil Han. The Decision of the Maximum Synchronous Torque During the Solar Array Deployment Using the Closed Cable Loop. Journal of Aerospace Engineering & Technology. 2025; 15(03):37-49.
How to cite this URL:
Hyon-Mu Jo, Song-Hyok Kim, Ji-Hyon Kim, Ju-Song Thak, Yong-Gil Han. The Decision of the Maximum Synchronous Torque During the Solar Array Deployment Using the Closed Cable Loop. Journal of Aerospace Engineering & Technology. 2025; 15(03):37-49. Available from: https://journals.stmjournals.com/joaet/article=2025/view=228122


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Regular Issue Subscription Original Research
Volume 15
Issue 03
Received 30/06/2025
Accepted 16/09/2025
Published 25/09/2025
Publication Time 87 Days
138

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