Abstract
In this study, we present the Diverse Holding and Release Mechanism Can Satellite (DHRM CanSat) platform developed by the Space Technology Synthesis Laboratory (STSL) at Chosun University, South Korea. This platform focuses on several types of holding and release mechanisms (HRMs) for application in deployable appendages of nanosatellites. The objectives of the DHRM CanSat mission are to demonstrate the design effectiveness and functionality of the three newly proposed HRMs based on the burn wire triggering method, i.e., the pogo pin-type HRM, separation nut-type HRM, and Velcro tape-type HRM, which were implemented on deployable dummy solar panels of the CanSat. The proposed mechanisms have many advantages, including a high holding capability, simultaneous constraints in multi-plane directions, and simplicity of handling. Additionally, each mechanism has distinctive features, such as spring-loaded pins to initiate deployment, a plate with a thread as a nut for a high holding capability, and a hook and loop fastener for easy access to subsystems of the satellite without releasing the holding constraint. The design effectiveness and functional performance of the proposed mechanisms were demonstrated through an actual flight test of the DHRM CanSat launched by a model rocket.
Highlights
A can satellite (CanSat) is a pico-class miniaturized satellite with a mass of less than 1 kg that is integrated into a can-shaped structure, with approximately the radius and height being less than 10 cm and 20 cm, respectively [1]
A passive rotating actuator mechanism made of aluminum drives the panel from its stored to the deployed state and latches the panels in place with the end stopper
The 0.2 mm diameter Dyneema wire manufactured by Berkley company has a maximum allowable tension of 53.37 N, making it strong enough to stow the solar panel in the launch vibration environment [26]
Summary
A can satellite (CanSat) is a pico-class miniaturized satellite with a mass of less than 1 kg that is integrated into a can-shaped structure, with approximately the radius and height being less than 10 cm and 20 cm, respectively [1]. The DHRM CanSat has four deployable dummy solar panels for the functional validation of the proposed optimized versions of the burn wire triggering-based HRMs, i.e., the pogo pin-type HRM, the separation nut-type HRM, and the Velcro tape-type HRM. The separation nut-type HRM provides increased holding constraints in the multiple axes of the solar panel with a combination of a Dyneema wire and locking bolt; its working principle is based on a burn wire triggering release method. Three newly proposed optimized versions of burn wire triggering-based HRMs were fabricated, and their design effectiveness and functional performance were evaluated experimentally by implementing the DHRM CanSat deployable dummy solar panels. The HRMs proposed and tested in the DHRM CanSat could overcome the limitations of conventional burn wire triggering release mechanisms in terms of the structural safety of the tightened wire, reliability in release functionality, and simplicity of handling. These test results validate the design feasibility and functional performance of the proposed mechanisms
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