Release system for deployable micro satellites

A novel method of releasing a deployable in the micro-satellite class is developed from concept to launch environment and separation testing. The release system is a linear Marman-style mechanism that is lightweight, has a low part count, and is relatively simple and inexpensive to fabricate and assemble. This release system was conceptualized and structurally analyzed for a deployable in the 50 to 100 kg class of satellites. An integral component of the system is the dispenser plate which is mounted to a launch vehicle and serves as a clamping interface for the deployable. The clamped, flyaway portion of the system is the base plate of the deployable. The first key feature of the release system is the pair of linear Marman-style clamps that lock the flyaway to the dispenser on two opposite edges of the mating interface. The second key feature is the bowed spring bar that is used to nearly equally distribute preload over the entire linear clamp bar. A variety of pyrotechnic or non-explosive separation nuts can be used to restrain the clamp bar and spring bar. The release system was tested prior to the end of FY16 in sine and random vibrations simulating launch environments and in pre- and post-vibration deployments. A space vehicle mass simulator was built for the test to provide realistic conditions for the release system. The objective of the test was to demonstrate the structural capability of the release system. The separation function was also tested pre- and post-vibration to validate that the system will release the deployable after launch. All development and testing of the release system were supported by APL internal R&D (IRAD) funding.