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Vibration reduction restriction damping layer of spacecraft

A technology of restraint damping and spacecraft, which is applied in the direction of aerospace vehicles, aircraft, and aerospace equipment, etc., can solve the problems of increasing launch costs and increasing the quality of spacecraft, and achieve high reliability and safety, low quality cost, The effect of not reducing the bearing stiffness

Inactive Publication Date: 2005-09-07
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The cost of improving the structural strength of the spacecraft is to increase the mass of the spacecraft, thereby increasing the launch cost, and the increased mass is an invalid load during the normal operation of the spacecraft in orbit

Method used

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  • Vibration reduction restriction damping layer of spacecraft
  • Vibration reduction restriction damping layer of spacecraft
  • Vibration reduction restriction damping layer of spacecraft

Examples

Experimental program
Comparison scheme
Effect test

specific Embodiment approach 1

[0007] Specific embodiment 1: The spacecraft vibration reduction constrained damping layer of this embodiment is composed of a constrained layer 1 and a damping layer 2, and the prefabricated viscoelastic damping material 2 is bonded to the inner and outer layers 3 of the connector by using an adhesive. pressure treatment to make the bonding firm; after the adhesive is cured, stick the prefabricated constraining layer 1 on the upper surface of the damping layer 2, and make the bonding firm after pressure treatment. Adhere to any part of the outer layer 3 of the connector. If the edge of the constrained layer 1 is adhered to a certain part of the outer layer 3 of the connector, part of the vibration will be directly transmitted to the constrained layer 1 through the adhesive part, thereby weakening its restraining effect on the damping layer 2, and the vibration reduction effect cannot be maximized. good. Such as figure 1 As shown, the constrained damping structure is a stru...

specific Embodiment approach 2

[0010] Specific implementation mode two: In this implementation mode, the connecting part of the spacecraft is a conical shell structure as an example, such as figure 2 As shown, the spacecraft damping constrained damping layer is composed of a constrained layer 1 and a damping layer 2, and the damping layer 2 is bonded to the connecting piece between the spacecraft and the launch vehicle (such as the star-rocket adapter, the spacecraft adapter cone, the on-board Engine skin and other parts) on the outer layer 3, the constraining layer 1 is bonded on the surface of the damping layer 2. The additional damping layer 2 can be made of ZN-1 viscoelastic material with a thickness of 1 mm. The damping layer 2 is prefabricated into multiple pieces according to the outer surface size of the cone shell structure; the constrained layer 1 is made of C / E composite material T300 / AG80, The thickness is 1.2mm; each layer is bonded with J47D foam glue, J47C film or J133 glue.

specific Embodiment approach 3

[0011] Specific implementation mode three: In this implementation mode, the connecting part of the spacecraft has a beam structure as an example, such as image 3 with 4 As shown, the structure of the damping constrained damping layer of the spacecraft is the same as that of the specific embodiment 1. The additional damping layer 2 can be made of a viscoelastic material of ZN-1 with a thickness of 1 mm. The damping layer 2 is prefabricated according to the beam size; the constrained layer 1 Double-layer glass cloth (single-layer thickness 0.2mm) is used to wrap the outer surface of the damping layer 2, and glue is added to soak and drive away air bubbles to harden it, forming a composite material with glue as the body.

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Abstract

The invention is the spacecraft damping restraining layer, and relates to a damping structure. The invention comprises the restraining layer (1) and the damp layer (2), the damp layer is adhered on the inner and outer faces (3) of the connecting piece, the restraining layer (1) is adhered on the upper surface of the damp layer (2). The additive restraining damp layer of the invention does not change the present interfaces, not damage the original structure and not lower the bearing rigidity. The invention has apparent damping effect. The computer emulation shows that the twinkle acceleration response of binding surfaces falls about 70%, the biggest relative acceleration falls from 3.6g to 1g; the twinkle displacement of binding surfaces falls about 55% and the biggest relative displacement falls from 0.35mm to 0.15mm.

Description

Technical field: [0001] The invention relates to a vibration-damping structure, in particular to a vibration-damping constrained damping layer mainly used for spacecraft. Background technique: [0002] During the entire working life, the dynamic environment of the spacecraft during launch is the most severe. Compared with the in-orbit flight state, the mechanical environment of the spacecraft during the rocket launch process is even harsher. Therefore, ensuring that the spacecraft can survive in the mechanical environment of the launch process is the main effort in the current spacecraft structural strength design. The cost of improving the structural strength of the spacecraft is to increase the mass of the spacecraft, thereby increasing the launch cost, and the increased mass is an invalid load during the normal operation of the spacecraft in orbit. Invention content: [0003] The object of the present invention is to provide a kind of spacecraft vibration-reducing con...

Claims

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Application Information

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IPC IPC(8): B64G1/22
Inventor 郑钢铁梁鲁杜华军刘丽坤申智春张静黄文虎
Owner HARBIN INST OF TECH