Abstract
The hinge, a key component of deployable space mechanism, has a significant influence on the precision of the whole mechanism. Hysteresis is one of the uncontrollable factors affecting the precision of the hinge. However, much work so far has focused on the equivalent model of hysteresis, which is far from the actual situation. In this paper, the hysteresis model of the general rotary hinge was established via the finite element method (ABAQUS/Standard 6.14-4). The correctness of the model was verified by experiments, and the loss factor was defined to measure the size of hysteresis. The response surface method was then used to establish the response surface of the hysteresis loss factor of the general rotary hinge. Results show that the hinge was optimised. By comparing the response surfaces of the two types of hinges, the modified hinge can effectively reduce hysteresis loss factor. Importantly, the repeatability of the hinge can be effectively improved by reducing hysteresis loss factor through repeatability experiments. Using this method, the response surface of the hinge's hysteresis loss factor can be established accurately, and the hysteresis loss factor can be reduced through optimal design to improve the precision of the hinge. This method can provide reference and guidance for the hinge design of the high-precision deployable mechanism.
Highlights
With the rapid development of space science and technology, increasingly large in-orbit platforms are applied, and space deployable mechanisms are developed and applied rapidly
The majority of studies are based on the equivalent model, lacking experimental verification and far from the actual situation
The response surface of the hysteresis loss factor was established by the response surface method (RSM)
Summary
With the rapid development of space science and technology, increasingly large in-orbit platforms are applied, and space deployable mechanisms are developed and applied rapidly. Heald [13] studied the deployment repeatability of jointed precision structures through examining the sensitivity of the mechanical uncertainty and found that bounding the displacement was possible by using the width of the hysteresis. Mann [16] established the equivalent model of precision joint and analysed quasi-static and dynamic responses. HYSTERESIS MODEL OF GENERAL ROTARY HINGE A. FINITE ELEMENT MODEL OF HYSTERESIS Fig. 1 shows that the finite element model of the general rotary hinge was established in finite element software ABAQUS. The hysteresis curve of the general rotary hinge can be obtained by the contact force and displacement curves of the three stages. Overlap but form an annular force-displacement curve when reciprocating tension and compression are applied to the hinge, that is, the hysteresis loop.
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