Session
Weekend Session 6: Advanced Concepts - Research & Academia III
Location
Utah State University, Logan, UT
Abstract
Large empty volumes in optical payloads like telescopes and baffles take up significant, potentially useful space to package within a launcher volume, and can limit the minimum size of a spacecraft, having major implications on launch options and costs. Volume can be saved by using telescopic structures which can be deployed in-orbit. In previous work a light-weight wire-driven telescope was developed, which employed a constant torque spring motor with a damper to achieve a controlled deployment. This work focusses on the application of a similar deployment scheme to an optical baffle and the further development of the driving, tension-balancing and hold-down and release mechanisms required to achieve a usable sub-system package. In order to compensate for in orbit deformations, a tension balancing mechanism is proposed. A hold down release mechanism is also proposed for the launch. Preliminary FE analysis confirms the modal shapes of the deployed baffle are well beyond 100 Hz and validates the design concept. Initial functional and environmental testing has revealed minor issues, and redesign of the baffle structure will be done to conduct further tests. Future work will involve exploring other methods of manufacturing, using light absorbing materials/coatings and another round of design iteration and testing.
Wire Driven Mechanisms for Deployable Components for Optical Payloads
Utah State University, Logan, UT
Large empty volumes in optical payloads like telescopes and baffles take up significant, potentially useful space to package within a launcher volume, and can limit the minimum size of a spacecraft, having major implications on launch options and costs. Volume can be saved by using telescopic structures which can be deployed in-orbit. In previous work a light-weight wire-driven telescope was developed, which employed a constant torque spring motor with a damper to achieve a controlled deployment. This work focusses on the application of a similar deployment scheme to an optical baffle and the further development of the driving, tension-balancing and hold-down and release mechanisms required to achieve a usable sub-system package. In order to compensate for in orbit deformations, a tension balancing mechanism is proposed. A hold down release mechanism is also proposed for the launch. Preliminary FE analysis confirms the modal shapes of the deployed baffle are well beyond 100 Hz and validates the design concept. Initial functional and environmental testing has revealed minor issues, and redesign of the baffle structure will be done to conduct further tests. Future work will involve exploring other methods of manufacturing, using light absorbing materials/coatings and another round of design iteration and testing.
