A kinematic mount based on the statically determinate principle is designed using a single-axis right circular flexure hinge. The main role of this support structure is to reduce the influence the satellite platform on the space camera, thereby ensuring the thermal stability of the space camera in orbit. The mathematical model of the compliance of the single-axis right circular flexure hinge is derived based on the Castigliano’s second theorem. According to the index requirements and the compliance equations, the initial structure of kinematic mount is obtained. The optimization design is conducted with the initial structure as the optimization object and the natural frequency as the optimization objective to obtain the optimal structure. The finite element analysis shows that the optimal structure meets the index requirements. Compared with the initial structure, the natural frequency of the optimal structure is increased by 4.2%, the optimal structure in Rx, Ty, and Tz are better than the initial structure 13.3%, 21%, and 12.8%. Experiment verifications of compliance equation C33 of single-axis right circular flexure hinge and the compliance of the bipod are carried out. The experiment results indicate that the compliance equation C33 is correct, and the compliance of the bipod meets the design value. Therefore, it is concluded that all the compliance equations are correct, and the kinematic mount can meet the requirements of the thermal stability of the space camera in orbit.
A new method for the determination of the degree of freedom of the hexapod mount based on screw theory has been
proposed. The method is applied to the mobility analysis of the four configurations of the hexapod mount, say the 3-3
configuration, 3-6 configuration, 6-3 configuration and 6-6 configuration. The conclusion which the DOF of the four
structures of the hexapod mount is zero and over-constraint does not exist has been derived by the analysis of the motion
screw systems of the four structures, and it also presents that the four structures are equivalent in DOFs and the DOF of
variation configuration of the hexapod mount is also zero and over-constraint does not exist, which provides a strong
theoretical support for the feasibility of the kinematic supporting of the optical module. The method also provides a reference
for the mobility analysis of other parallel manipulators.
KEYWORDS: Space telescopes, Telescopes, Space sensors, Remote sensing, Sensors, Optimization (mathematics), Mirrors, Cameras, Computer aided design, James Webb Space Telescope
The truss structure had the merits of simple configuration, reliable, flexible assembly, specific stiffness and strong design ability. It was widely used in the support structure of Space camera and large telescope at home and abroad. The article described and analyzed truss structures of ground-based telescopes, space-based telescopes and Space camera. Conclusions that some reference should be followed in the truss design process were given. Simultaneously it also introduced the basic knowledge of truss design optimization, including the optimization ideas of truss structure and optimization algorithm of truss structure, which laid a good foundation for optimal design of truss in future.
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