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Damping flexible connecting method for spacecraft

A flexible connection and spacecraft technology, applied in space navigation equipment, space navigation aircraft, aircraft, etc., can solve the problems of unable to meet the needs of technological development, high cost of control system, high quality cost, etc., to achieve easy design, Wide application range and high strength effect

Inactive Publication Date: 2008-12-24
郑钢铁 +4
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When the volume of the instrument and equipment is large, the mass cost of improving the structural rigidity will be very high, and sometimes it may be unbearable
For those instruments and equipment that are sensitive to high-frequency jitter, relying solely on improving the performance of the control system is not only costly, but also cannot meet the needs of technological development due to reaching the limit of capabilities

Method used

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  • Damping flexible connecting method for spacecraft
  • Damping flexible connecting method for spacecraft
  • Damping flexible connecting method for spacecraft

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specific Embodiment approach 1

[0008] Specific implementation mode one: combine image 3 Describe this embodiment, the damping flexible connection method for spacecraft described in this embodiment is between the instrument and equipment sensitive to structural deformation and / or high-frequency vibration (hereinafter referred to as sensitive instrument 2) and the main structure 3 of the spacecraft Or all use the damping flexible connection device 1 to connect. The damping flexible connection device 1 absorbs the thermal stress between the sensitive instrument 2 and the adjacent spacecraft main structure 3, thereby reducing the thermal deformation transmitted from the spacecraft main structure 3 to the sensitive instrument 2, and the damping flexible connection device 1 is equivalent to A damping shock absorber is added between the sensitive instrument 2 and the spacecraft main structure 3 to play the role of vibration reduction and vibration isolation.

specific Embodiment approach 2

[0009] Specific implementation mode two: combination Figure 4 This embodiment is described. The damping flexible connection method for spacecraft described in this embodiment is to use the damping flexible connection device 1 to connect part or all of the static dynamic disturbance source 4 and the spacecraft main structure 3 . The damping flexible connection device 1 cuts off the force transmission path between the static dynamic disturbance source 4 and the spacecraft main structure 3, plays the role of absorbing thermal deformation and vibration isolation, and reduces the transmission from the static dynamic disturbance source 4 to the spacecraft main structure 3 on the disturbance.

specific Embodiment approach 3

[0010] Specific implementation mode three: combination Figure 5 This embodiment will be described. The damping flexible connection method for a spacecraft described in this embodiment is to use the damping flexible connection device 1 to connect between various components on the main structure 3 of the spacecraft. This embodiment can improve the overall mechanical properties of the spacecraft. The damping flexible connection device 1 weakens the coupling effect between the parts of the main structure 3 of the spacecraft in a balanced state, and cuts off the transmission path of thermal stress caused by temperature differences. , thereby improving the overall thermal deformation of the spacecraft structure, and improving the overall damping level of the spacecraft, and playing a role in vibration suppression as a whole.

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Abstract

The invention relates to a damping flexible connection method for spacecrafts, which can improve the affect of the rail heat distortion and high-frequency vibration of spacecrafts on the working performance of sensitive instruments and the stability of spacecraft control systems. The damping flexible connection method for spacecrafts uses a damping flexible connection device (1) on a joint having high internal stress and / or high vibration transmissibility on a spacecraft. The method has the following advantages that: on the one hand, the flexibility of the damping flexible connection device (1) is utilized to absorb the load produced by structural heat distortion, so as to reduce the static distortion of a mounting structure of a sensitive instrument (2); on the other hand, the damping of the damping flexible connection device (1) is utilized to improve the overall damping level of a spacecraft structure or the local damping level of the sensitive instrument, so as to play a role in inhibiting high-frequency vibration.

Description

technical field [0001] The invention relates to a damping flexible connection method for spacecraft. Background technique [0002] Instruments that are sensitive to structural deformation and / or high-frequency vibrations (hereinafter referred to as sensitive instruments), such as space cameras, space telescopes, and SAR systems, are increasingly used on modern spacecraft. Therefore, an important task in the design is to avoid Small deformation of the structure and suppression of high-frequency jitter. Through the dynamic and static analysis of the spacecraft’s in-orbit operation state, it is found that its disturbance mainly includes the following aspects: the temperature gradient between the various components due to the uneven solar radiation will cause the spacecraft structure to generate greater thermal stress, In particular, there will be very large thermal stress between the structural part directly exposed to solar radiation and the adjacent structure; the thermal sh...

Claims

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Application Information

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IPC IPC(8): B64G1/00
Inventor 郑钢铁张静刘明辉梁鲁白绍竣
Owner 郑钢铁
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