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Superstructure with high resonant frequency and thermal mismatch zero warping and determination method thereof

A technology for resonant frequency and determination method, which is applied in special data processing applications, instruments, electrical digital data processing, etc., and can solve the problems of inability to meet the minimum natural frequency requirements of spacecraft structures, complex anisotropic manufacturing processes, and reduced system reliability, etc. problem, to achieve the effect of additive manufacturing integrated forming post-processing, good application prospects, and convenient post-processing

Active Publication Date: 2019-10-01
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

However, the existing material-scale technical solutions lead to shortcomings such as material brittleness, high density, anisotropy, or complex manufacturing processes, while the existing structural-scale technical solutions have structural natural frequencies that are too low to meet the needs of rocket launches. The minimum natural frequency requirement of the structure, especially for payloads of nearly 100 kilograms or heavier, requires the design of an additional pressing mechanism to increase the natural frequency during launch, but the pressing mechanism greatly increases the structural weight cost, The introduction of the hold-down mechanism also leads to a reduction in system reliability

Method used

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  • Superstructure with high resonant frequency and thermal mismatch zero warping and determination method thereof
  • Superstructure with high resonant frequency and thermal mismatch zero warping and determination method thereof
  • Superstructure with high resonant frequency and thermal mismatch zero warping and determination method thereof

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[0040] It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0041] Before discussing the example embodiments in greater detail, it should be mentioned that the specific structural and functional details of some example embodiments disclosed herein are merely representative and are for purposes of describing example embodiments of the invention. Purpose. This invention may, however, be embodied in many alternative forms and should not be construed as limited to only the embodiments set forth herein.

[0042] It will be understood that although the terms "first", "second", etc. may be used herein to describe various elements, these elements should not be limited by these terms. These terms are only used to distinguish one element from another. For example, a first element could be termed a second element, and, similarly, a second element could be termed a first element, withou...

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Abstract

The invention relates to a superstructure with high resonant frequency and thermal mismatch zero warping and a determination method thereof. The superstructure is used for connection of heterostructures and comprises a multistage microstructure, wherein each stage of microstructure comprises a plurality of microstructure units; the multi-stage microstructures are distributed from outside to inside, and an envelope line formed by each stage of microstructures with self-similar characteristics in the plane and an in-plane contour line of the heterostructure have a geometric similar relationship.Based on the super-structure provided by the invention, the buckling deformation during temperature change is close to zero, and the super-structure has the characteristic of high first-order resonant frequency and meets the use requirements of on-orbit dimensional stability and high emission rigidity of a spacecraft structure.

Description

technical field [0001] The invention relates to a connection structure between a spacecraft high-precision payload and a spacecraft structure, in particular to a superstructure with high resonance frequency and thermal mismatch zero warpage in a thermal mismatch deformation release structure of a heterogeneous structure and its Determine the method. Background technique [0002] Synthetic aperture radar, optical camera, star sensor and other payloads are the main means for spacecraft to realize functions such as space-based calibration and measurement, space science and detection. change within a certain range. In order to achieve high-resolution measurement, imaging, and surveillance, high-performance payloads place stringent requirements on the thermal deformation of spacecraft structures. The materials used for the payload and the spacecraft structure are often different, forming a heterogeneous structure. When the temperature changes, due to the thermal deformation of ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/17G06F30/23
Inventor 周浩张啸雨曾惠忠赵云鹏罗文波高峰王耀兵张龙雷红帅
Owner BEIJING INST OF SPACECRAFT SYST ENG
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