Design, analysis, and testing of kinematic mount for astronomical observation instrument used in space camera

Abstract

A statically determinate kinematic mount structure is designed for an astronomical observation instrument. The basic principle of the proposed kinematic mount is introduced in detail, including the design principle, its structure, and its degrees of freedom. The compliance equations for the single-axis right circle flexure hinge are deduced, and mathematical models of the compliances of the bipod in the X-axis and Z-axis directions are established. Based on the index requirements, the range of one design parameter (the hinge groove depth, R) for the kinematic mount is determined. Parametric design is performed, with the entire structure being the design object and the first three eigenfrequencies as the design objective; the final design parameter for the kinematic mount is 1.9 mm. The first three eigenfrequencies of the final structure are 36.49 Hz, 38.65 Hz, and 72.41 Hz, which meet the frequency requirements. The Z-direction deformation and the bipod compliances in the X-axis and Z-axis directions are analyzed through simulations and experiments. The results show that (1) the Z-direction deformation of the bipod meets the displacement requirement; (2) the deviations between the finite element results and the compliance equation C results, and between the finite element results and the compliance equation C results are 8.8% and 3.92%, respectively; (3) the deviation between the experimental results and the compliance equation C results is 10.3%. It is concluded that the bipod compliance equations in the X-axis and Z-axis directions are valid, and that the kinematic mount thus meets the design requirements.

Design and analysis of a triangular bi-axial flexure hinge

“…The triangular bi-axial flexure hinge consists of four triangular flexure hinges that is firstly connected in parallel and then in series. According to the spring series-parallel principle, 36 the model of equal effectiveness is shown in Figure 6, so its flexibility matrix C TBH is:…”

The performance characterization of carbon fiber–reinforced plastic for space applications

“…Therefore, it is absolutely necessary to ensure the dimensional stability of telescope truss structures. 7–10…”

“…Therefore, it is absolutely necessary to ensure the dimensional stability of telescope truss structures. [7][8][9][10] For a given design application, CFRP can be tailored for strength, stiffness, coefficient of thermal expansion, and high reliability. CFRP consists of carbon fiber and polymeric matrix resin.…”

Repeatability Analysis of Overconstrained Kinematic Coupling Using a Parallel-Mechanism-Equivalent Model

“…Both of the two couplings can achieve high repeatability [1], and therefore are widely used to clamp components of sensitive equipment, such as the optical telescope assembly [2,3], antenna panels [4] and high-precision microcontact printing device [5]. Apart from the traditional Kelvin-type and Maxwell-type couplings, the two components of which are restrained by 6 contact points, quasi-kinematic couplings [6,7] and compliant semi-kinematic couplings [8,9] with higher accuracy performance are designed and analyzed.…”