Design,fabrication and test of qualification model of wire thermal cutting based non-explosive separation device for a small satellite

Abstract

In this paper, we address the design, fabrication and test of a qualification model of a wire thermal cutting based non-explosive actuation (NEA) device for a small satellite. The important design parameters such as maximum allowable preload and release time are investigated through theoretical analysis. After it is fabricated based on theoretical results, we implemented the mechanical performance tests to assure operability and reliability for the compact size NEA device. From the result of the mechanical performance tests such as maximum preload, shock level and release time tests, we found that the proposed NEA device can be operated under a preload of 1000 kg_f within 550 ms stably and it generates a low shock of 58.57 G. The margin calculation shows that the proposed NEA device can hold a solar panel of 20 kg with a margin of safety (MS) of +0.32. In addition, we carried out the environment tests such as the vibration test and thermal vacuum test to qualify the proposed NEA device. From the vibration test, we found the resonant shapes after sine and random vibration were the same which means the proposed NEA device was successfully designed to have a stable structure. From the result of the thermal vacuum test, in addition, the proposed NEA device was well operated in a space environment condition.

Keywords

Non-explosive actuator (NEA)separation device Ni-Cr wire solar array panel high-preload

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