In this paper, we present a compact non-explosive actuator device (NEA) that is activated with a thermal cutting method using Ni- Cr wire. Practical applications include the deployment of satellite appendages such as solar array panels and antennae. The pyrotechnic based separation device generates high shock and chemical contaminants, which cause malfunctions of components such as optic cameras and other sensors. The proposed NEA device is designed to generate low shock using unspool mechanism characteristic, and to have compact dimensions and a light mass. In the design process, we formulated equations based on a static analysis to verify that it satisfied the basic requirements. Then we fabricated the device based on a theoretical analysis and carried out pre-tests such as maximum preload and response time tests to verify the results of the theoretical analysis. The pre-test results showed an average maximum preload of 1,000 kgf and a response time of 600 ms. Consequently, we verified the feasibility of an NEA that could be activated within 600 ms under high preload. In order to develop a qualification model for the NEA, various additional tests are planned, including launching and space environment tests based on the European Satellite Agency standard test manual.