JPL is developing deployable radio frequency (RF) reflector booms for spaceflight usage on two differentEarth orbiter projects scheduled to launch in the early 2020’s. The static alignment and thermal stabilityrequirements for these RF reflector booms are challenging. A common mechanism design has beendeveloped for the deployment and latching of boom hinges that avoids significant parasitic loads on thealignment critical structures after completion of mechanism function. The mechanism design includes ahigh-aspect-ratio torsion spring with viscous damper for hinge closure as well as an actuator-driven flexuredhook and roller latch for joint preloading. This paper describes noteworthy mechanism design details, testresults, challenges, and lessons learned during the development effort.
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