Dynamical modeling method for flexible spacecraft with friction boundary
A flexible spacecraft and dynamics modeling technology, applied in the direction of instrumentation, geometric CAD, electrical digital data processing, etc., can solve the problem of not considering the influence of the inherent characteristics of the boundary gap friction spacecraft
Active Publication Date: 2021-04-06
SHANGHAI AEROSPACE CONTROL TECH INST
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[0004] The object of the present invention is to provide a dynamic modeling method, electronic equipment and storage medium for a flexible spacecraft with frictional boundaries, so as to solve the problem that the traditional method does not consider the influence of boundary gap friction on the inherent characteristics of the spacecraft
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[0069] A method for modeling dynamics of a flexible spacecraft with frictional boundaries, electronic equipment and storage media proposed by the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. The advantages and features of the present invention will become clearer from the following description. It should be noted that the drawings are in a very simplified form and all use imprecise scales, which are only used to facilitate and clearly assist the purpose of illustrating the embodiments of the present invention. In order to make the objects, features and advantages of the present invention more comprehensible, please refer to the accompanying drawings. It should be noted that the structures, proportions, sizes, etc. shown in the drawings attached to this specification are only used to match the content disclosed in the specification, for those who are familiar with this technology to understan...
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The invention discloses a dynamical modeling method for a flexible spacecraft with a friction boundary. The method comprises the following steps: constructing an energy functional of the flexible spacecraft with the friction boundary; simulating general boundary conditions of a flexible structure in the flexible spacecraft, and constructing a displacement tolerance function of the flexible structure in the flexible spacecraft; solving a global analytic mode function of the flexible spacecraft according to the flexible spacecraft energy functional containing the friction boundary and the displacement tolerance function; and obtaining a low-dimensional analysis rigid-flexible coupling kinetic model of the flexible spacecraft according to the modal function of the flexible spacecraft, and carrying out kinetic characteristic analysis. The problem that the influence of boundary gap friction on the inherent characteristics of the spacecraft is not considered in a traditional method is solved; the method is high in applicability, can be applied to general boundary conditions, and can be used for conveniently processing spacecrafts with flexible bodies with complex shapes; and the low-dimensional analytical dynamic model is obtained, so that the design of a control law is facilitated.
Description
technical field [0001] The invention relates to the technical field of dynamic modeling of flexible spacecraft, in particular to a dynamic modeling method of flexible spacecraft with friction boundaries, electronic equipment and storage media. Background technique [0002] With the development of aerospace technology, spacecraft tend to be larger, more flexible and lighter. Restricted by the carrying envelope and deployment method, large flexible spacecraft need to adopt a deployable structural design method. On the one hand, due to factors such as processing, assembly, and wear of the structure, there will be unavoidable gaps between the hinges of the deployable structure after unfolding and locking; In order to release the thermal stress generated inside the structure, sufficient gaps will be reserved at the joints of the structural hinges during the design of the spacecraft structure. Two factors make the gap between the hinges unavoidable after the spacecraft is unfold...
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Login to View More IPC IPC(8): G06F30/15G06F119/14
CPCG06F30/15G06F2119/14Y02T90/00
Inventor 孙杰刘付成朱东方孙俊黄庭轩
Owner SHANGHAI AEROSPACE CONTROL TECH INST