Abstract
A spring-loaded pogo pin as a holding and release mechanism of solar panels for cube satellite applications is proposed which functions as an electrical interface, a separation spring, and a status switch. The proposed mechanism has many advantages, including an increased loading capability, negligible induced shock level, synchronous release of multiple panels, and handling simplicity during integration. A demonstration model of the mechanism was fabricated and functionally tested under various test conditions such as different input voltages, different numbers of tightened nylon wires, and different temperatures (ranging from −40°C to 70°C).
Highlights
A cube satellite (CubeSat) is a type of cube-shaped pico-class miniaturized satellite with a volume of 10 cm3 and a mass less than 1.33 kg with respect to a standard size of one unit (1 U) [1]
A pogo pin [20] is a device that is extensively used in electronics to establish a temporary connection between two printed circuit boards (PCBs). This constitutes an extremely attractive function for the application of separation devices because it functions as an electrical interface to provide power, a separation spring to initiate reaction force, and a status switch to determine a deployment status of the solar panel
In order to measure the dynamic response from the solar panel after synchronous burn wire triggering, accelerometers with a thickness of 1.5 mm were attached on each dummy PCB solar panel
Summary
A cube satellite (CubeSat) is a type of cube-shaped pico-class miniaturized satellite with a volume of 10 cm and a mass less than 1.33 kg with respect to a standard size of one unit (1 U) [1]. Various holding and release mechanisms (HRMs) were developed for the separation of the deployable structures for CubeSat applications. Pyrotechnic devices are extensively used in the aerospace engineering field and in commercial satellite separation. They typically induce increased levels of shock responses owing to the sudden transient release of strain energy.
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