Structure and Thermal Control of Panel Extension Satellite (PETSAT)

Paper number

IAC-06-B5.7.08

Author

Dr. Yoshiki Sugawara, University of Tokyo, Japan

Coauthor

Prof. Shinichi Nakasuka, University of Tokyo, Japan

Coauthor

Mr. Kenji Higashi, Japan

Coauthor

Ms. Chisato Kobayashi, Astro-Technology SOHLA, Japan

Coauthor

Mr. Kanichi Koyama, Astro-Technology SOHLA, Japan

Coauthor

Mr. Takanori Okada, Astro-Technology SOHLA, Japan

Year

2006

Abstract

1. CONCEPT OF PETSAT

PETSAT consists of several "Functional Panels" each of which has a special dedicated function. By connecting these panels by reliable connection mechanism in "plug-in" fashion, the integrated system has a satellite function. These panels are stowed during launch into a small volume, and are extended on orbit.

Various combinations of different kinds of functional panels provide flexibility to deal with various mission requirements, even though the basic panels are the same for various missions. Such flexibility causes a change in the satellite development cycle. And each functional panel can be produced in mass quantity, resulting in improvement of the reliability.

To realize PETSAT, requirements for mechanical, thermal, electric and information interface must be satisfied. In this paper, our approaches to the requirements on mechanical and thermal interface are introduced.

2. APPROACH TO MECHANICAL INTERFACE

2. 1. Requirements

Panel structure with light-weight and enough space for mounting of devices is required. Moreover, condition for natural frequency must be satisfied or a method for rising natural frequency must be prepared.

To extend panels on orbit, reliable deployment mechanism and methods for fixing deployment angles are required.

2. 2. Panel structure and deployment mechanism

Structure of panel which satisfies requirement is designed and some analyzes and tests are carried out. And well-placed stiffener can raise the rigidity of panels.

To realize reliable deployment mechanism, torsional spring is applied, which can reduce the risk of vacuum metalizing. Moreover, to keep high reliability, latch mechanism for fixing deployment angles is not implemented. Instead, the deployment angle is kept by force of torsional spring designed appropriately.

3. TERMAL CONTROL ON PETSAT

3.1. Requirements

Thermal coupling within and between panels should be made very strong so that the temperature difference between each part of satellite should be as small as possible. This is the best "general" strategy for thermal control because the thermal environment is different from missions to missions.

3.2. Approach to Strengthen Thermal Coupling within and between Panels

To strengthen thermal coupling within panel, Heatlane is applied to each panel which is a heat-transfer mechanism utilizing phase change of working fluid. On the other hand, to strengthen thermal coupling between panels, magnetic fluid loop with magnetic pump is being developed and applied to each panel. The magnetic pump is based on that magnetizing force of the magnetic fluid depends on their temperature. Fig.3 shows principle model for heat transportation between two panels.

Abstract document

IAC-06-B5.7.08.pdf

Manuscript document

IAC-06-B5.7.08.pdf (🔒 authorized access only).

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