Abstract: An opto-mechanical deployable telescope includes a hub, at least one deployable multiple petal primary mirror mounted to the hub, a deployment assembly, a secondary optic assembly, and a deployment engine assembly. The deployment assembly is operable to move the at least one primary mirror between a stowed position and a deployed position. The deployment engine assembly is operable to power the deployment assembly using stored mechanical energy. The deployment assembly includes a kinematic or semi-kinematic interface between the hub and the at least one primary mirror to hold petals of the at least one primary mirror in alignment relative to each other in the deployed position. The secondary optic assembly comprising a secondary optical member and is operable to axially position the secondary optical member relative to the primary mirror.

Abstract: An opto-mechanical deployable telescope includes a hub, at least one deployable multiple petal primary mirror mounted to the hub, a deployment assembly, a secondary optic assembly, and a deployment engine assembly. The deployment assembly is operable to move the at least one primary mirror between a stowed position and a deployed position. The deployment engine assembly is operable to power the deployment assembly using stored mechanical energy. The deployment assembly includes a kinematic or semi-kinematic interface between the hub and the at least one primary mirror to hold petals of the at least one primary mirror in alignment relative to each other in the deployed position. The secondary optic assembly comprising a secondary optical member and is operable to axially position the secondary optical member relative to the primary mirror.

Abstract: An opto-mechanical deployable telescope includes a hub, at least one deployable multiple petal primary mirror mounted to the hub, a deployment assembly, and a deployment engine assembly. The deployment assembly is operable to move the at least one primary mirror between a stowed position and a deployed position. The deployment engine assembly is operable to power the deployment assembly using stored mechanical energy. The deployment assembly includes a kinematic or semi-kinematic interface between the hub and the at least one primary mirror to hold petals of the at least one primary mirror in alignment relative to each other in the deployed position.

Abstract: An opto-mechanical deployable telescope includes a hub, at least one deployable multiple petal primary mirror mounted to the hub, a deployment assembly, and a deployment engine assembly. The deployment assembly is operable to move the at least one primary mirror between a stowed position and a deployed position. The deployment engine assembly is operable to power the deployment assembly using stored mechanical energy. The deployment assembly includes a kinematic or semi-kinematic interface between the hub and the at least one primary mirror to hold petals of the at least one primary mirror in alignment relative to each other in the deployed position.

Abstract: A method and system that compensates for thermal induced stresses in structures composed of different materials fastened together. The system utilizes three compensation mounts made from a material with a coefficient of thermal expansion that is between that of the two materials being fastened together. These mounts can be linear or, for a thinner structure, the mounts are “C” shaped. The size of the “C” mounts and fastening locations are calculated based on the coefficient of thermal expansion for the two materials being fastened together and the “C” mount material. The geometry of the “C” mounts allows for fastening the two planar surfaces without introducing a large thickness increase to the structure. This system allows for materials to be fastened together, and when placed in an environment with temperature fluctuations, the system experiences zero, minimal or insignificant amounts of thermal induced stress.

Abstract: A method and system that compensates for thermal induced stresses in structures composed of different materials fastened together. The system utilizes three compensation mounts made from a material with a coefficient of thermal expansion that is between that of the two materials being fastened together. These mounts can be linear or, for a thinner structure, the mounts are “C” shaped. The size of the “C” mounts and fastening locations are calculated based on the coefficient of thermal expansion for the two materials being fastened together and the “C” mount material. The geometry of the “C” mounts allows for fastening the two planar surfaces without introducing a large thickness increase to the structure. This system allows for materials to be fastened together, and when placed in an environment with temperature fluctuations, the system experiences zero, minimal or insignificant amounts of thermal induced stress.