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Design method of complex spacecraft dynamics and loads based on large series structure

A series structure and design method technology, applied in space navigation equipment, space navigation equipment, computer-aided design, etc., to achieve the effect of reducing dynamic load and ensuring full effectiveness

Active Publication Date: 2019-07-12
SHANGHAI AEROSPACE SYST ENG INST
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Problems solved by technology

[0004] The object of the present invention is to provide a kind of complex spacecraft dynamics and load design method based on the large series structure form, can solve the load design prob

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  • Design method of complex spacecraft dynamics and loads based on large series structure
  • Design method of complex spacecraft dynamics and loads based on large series structure
  • Design method of complex spacecraft dynamics and loads based on large series structure

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Embodiment Construction

[0027] In order to make the above objects, features and advantages of the present invention more comprehensible, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0028] figure 1 It is a flowchart of a method for designing complex spacecraft dynamics and loads based on a large series structure in an embodiment of the present invention; figure 2 is a schematic diagram of a spacecraft finite element model according to an embodiment of the present invention; image 3 It is a schematic diagram of the distribution of a typical separation surface I point type separation nut according to an embodiment of the present invention; Figure 4 It is a schematic diagram of the response characteristics of the overload coefficient in the longitudinal direction of the center of mass of the entire spacecraft, the center of mass of the spacecraft assembly above the separation plane I, and the center of mass ...

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Abstract

The invention provides a complex spacecraft dynamics and load design method based on a large series structure, taking the spacecraft as a research object, and decomposing the spacecraft in a series form through dynamic modeling and simulation analysis. The dynamic performance parameters of each independent spacecraft can be used to realize the dynamic frequency stagger design and reduce the dynamic load; the quasi-static load at the center of mass of the spacecraft is used as the design input basis to decompose the components that form the spacecraft in series. The load on the separation interface of independent spacecraft; for the centroid overload above the separation interface of the spacecraft, realize the differential analysis and design, decompose the separation surface load at different heights of the centroid, and solve the problem of different boundary conditions in the spacecraft based on the large series structure. The problem of load design of independent spacecraft is to ensure that the load is not "under" the design, so as to ensure the full effectiveness of the overall design of the spacecraft.

Description

technical field [0001] The invention relates to a complex spacecraft dynamics and load design method based on a large series structure. Background technique [0002] The spacecraft mainly goes through three stages: the ground development and test stage, the launch stage, and the on-orbit operation stage. Among them, the simulated ground vibration test environment during the launch of the spacecraft and the mechanical environment during the launch stage are the most demanding on the main structure of the spacecraft. The dynamic analysis and load design of the above environment are the main basis for the spacecraft structure design. [0003] For a general traditional single-chamber spacecraft that does not involve multiple separation interfaces, it is sufficient to carry out the structural design of the spacecraft according to the quasi-static load and mechanical environment specified in the launch vehicle user manual. With the expansion of space missions and diversification ...

Claims

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Application Information

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IPC IPC(8): G06F30/00B64G1/00
Inventor 张华刘汉武胡震宇李东颖柳征勇肖余之
Owner SHANGHAI AEROSPACE SYST ENG INST
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