Abstract
CubeSats are revolutionary to the space industry and are transforming space exploration which enables the next generation of scientists and engineers to complete all phases of space missions. Deployable solar panels have been widely used for the generation of enough power in CubeSats due to their limited volume area for solar cell integration. In general, the cable cutting release mechanism have been used in 1U-3U small satellites because of its simplicity and low cost. However, this mechanism has a low constraint force and is unable to apply constraints along the in-plane and out-of-plane directions. In this study, for the improvement of the conventional cable cutting mechanism, a spring-loaded pogo pin-based nichrome burn wire holding and release mechanism (HRM) was proposed and fabricated. The pogo pin constitutes an immensely attractive function for the holding and release mechanism of solar panels because it works as an electrical interface to provide power, a separation spring to initiate the reaction force to deploy the panels, and a status switch to determine deployments. In addition, the proposed mechanism guarantees the loading capability along the in-plane and out-of-plane directions of solar panels, the synchronous release of multiple panels, and a handling simplicity that differentiates it from the conventional mechanism. The design feasibility, structural safety, and reliability of the mechanism were verified through functionality tests and launch and on-orbit environmental tests. The proposed pogo pin-based holding and release mechanism would be equally applicable for other CubeSat deployable appendages.
Highlights
In 1957, the Soviet Union officially initiated the modern space age by launching the Sputnik satellite into low Earth orbit
The basic functional test results confirm that the spring-loaded pogo pin constitutes an attractive function for a holding and release mechanism because it works as an electrical interface to provide power to the burn resistor, which is mounted on the burn resistor printed circuit board (PCB) of the solar panels
By the microcontroller unit (MCU) indicated that all the solar panels were released within 2.5 s from the initiation of burn wire triggering, and the time gap between the released panels was at the maximum of 0.43 s
Summary
In 1957, the Soviet Union officially initiated the modern space age by launching the Sputnik satellite into low Earth orbit. The basic functional test results confirm that the spring-loaded pogo pin constitutes an attractive function for a holding and release mechanism because it works as an electrical interface to provide power to the burn resistor, which is mounted on the burn resistor PCB of the solar panels. It can establish a temporal electrical connection and it acts as a status switch to confirm the solar panel deployment status. The simple, reliable, and inexpensive HRM often contributes to significant cost reductions to a CubeSat program and aids in the success of space missions
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
