抄録
The utilization of the micro/nano satellites with 50kg or less weight has been rapidly growing and lots of micro satellites are going to be launched within several years. The micro/nano satellite has been expected to realize the various space missions with low cost and short development period. For example, large apparatus antenna with sufficient shape accuracy is required for future earth observation mission. Other than these requirements, the micro/nano satellites generally have deployable solar array panels to provide sufficient electric power. Thus low-cost deployable panel structure is getting important for micro/nano satellites. The key technology to reduce the production cost of the deployable panel structure is the simple and reliable deployment device, for example the hinge with sufficient deployment torque, the joint or latch mechanism with appropriate accuracy of relative position and angle, the hold release mechanism with enough holding force. Based on the above, we are advanced the development of the hinge with latch mechanism and the hold release mechanism as a simple and low-cost panel deployment device. In this paper, we will report on the status of development of the hold release mechanism and the hinge with latch mechanism which is the deployment mechanism of panel structure for micro/nano satellite.
