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Aircraft thermally-induced vibration dynamics response evaluation method

A dynamic response, spacecraft technology, applied in the direction of instruments, special data processing applications, electrical digital data processing, etc.

Active Publication Date: 2016-06-01
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

For complex spacecraft, this type of method is difficult to meet the analysis requirements. It is necessary to carry out modeling and simulation analysis of spacecraft thermal-induced micro-vibration coupling dynamics from the system height, which is very important for analyzing the influence of flexible attachment thermal-induced micro-vibration dynamics environment on spacecraft attitude. , especially the imaging resolution of high-resolution remote sensing satellites, has important engineering application value

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  • Aircraft thermally-induced vibration dynamics response evaluation method
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  • Aircraft thermally-induced vibration dynamics response evaluation method

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Embodiment Construction

[0032] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0033] A schematic diagram of a flexible spacecraft considering space thermal loads is shown in figure 1 shown. B represents the rigid body at the center of the spacecraft, and A i denotes the i-th flexible attachment, o b is the center of mass of the spacecraft, o a for Annex A i Hinge with Astral. The modeling coordinate system adopts the orbital coordinate system {r}, the star coordinate system {b} and the attachment coordinate system {a}, all of which are three-dimensional Cartesian coordinate systems. The origin of the orbital coordinate system {r} is o r , and the three coordinate axes are x r 、y r and z r ;The origin of the star coordinate system {b} is o b , and the three coordinate axes are x b 、y b and z b ;The origin of the attachment coordinate system {a} is o a , and the three coordinate axes are x a 、y a and z a .

[0034] (...

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Abstract

The invention discloses an aircraft thermally-induced vibration dynamics response evaluation method. A flexible aircraft thermally-induced micro-vibration coupling dynamics analysis method is adopted, so that response higher in accuracy can be acquired when compared with a simplified aircraft thermally-induced micro-vibration non-coupling dynamics modeling method which is currently used and composed of a two-dimensional cantilever and a central rigid body, analysis of influence on aircraft posture, especially high-resolution remote sensing satellite imaging resolution, by flexible accessory thermally-induced micro-vibration dynamics environment is better facilitated.

Description

technical field [0001] The invention relates to the field of dynamic analysis of spacecraft structures, in particular to a dynamic response evaluation method for thermally induced vibration of a spacecraft. Background technique [0002] With the rapid development of high-precision spacecraft, micro-vibration has become an important factor affecting its high imaging resolution and high pointing accuracy for high-precision spacecraft. The thermally induced microvibration dynamic environment of flexible structures in spacecraft microvibration has become an important factor that must be considered in the performance indicators of high-precision spacecraft payloads such as high-pointing precision communication satellites and high-resolution remote sensing satellites. The reason is that this type of spacecraft has a large flexible appendage structure with light weight, low stiffness, and low natural frequency. During orbital operation, the micro-vibration response of the spacecraf...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/23
Inventor 刘绍奎邹元杰刘正山葛东明史纪鑫庞世伟
Owner BEIJING INST OF SPACECRAFT SYST ENG
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