CN111998028A

CN111998028A - Damper for vibration suppression of spacecraft structure

Info

Publication number: CN111998028A
Application number: CN202010798433.1A
Authority: CN
Inventors: 肖登红; 高勇; 周小红; 仝宗凯
Original assignee: Beijing Research Institute of Mechanical and Electrical Technology
Current assignee: Beijing Research Institute of Mechanical and Electrical Technology
Priority date: 2020-08-11
Filing date: 2020-08-11
Publication date: 2020-11-27
Anticipated expiration: 2040-08-11
Also published as: CN111998028B

Abstract

The invention discloses a damper for inhibiting structural vibration of a spacecraft, which comprises a damper outer ring (1), a damper inner ring (2) and a plurality of damping unit cells (3), wherein the damping unit cells (3) are uniformly distributed between the damper outer ring (1) and the damper inner ring (2) along the annular direction, and each damping unit cell (3) is stressed along the radial direction. The invention adopts a unit cell structure to be integrally arranged along a ring, overcomes the dead zone effect of the head and the tail boundary, and realizes the effect of circumferential energy absorption of 360 degrees.

Description

Damper for vibration suppression of spacecraft structure

Technical Field

The invention belongs to the technical field of vibration impact mitigation, and particularly relates to a damper for suppressing structural vibration of a spacecraft.

Background

The vibration isolation and suppression technology research has very important practical significance. The passive vibration control technology is also called damping control technology, and is a technology which adopts a damper or a damping material, increases the self damping of a spacecraft structure and consumes the structural vibration energy by utilizing the damping energy consumption principle. The method has the advantages of high reliability, easy realization, long service life and relatively mature development. At present, passive damping suppression technology is applied in orbit on various spacecrafts launched abroad. The damper for the spacecraft is the foundation of the passive vibration technology of the spacecraft. Due to the non-maintainability of the spacecraft, the spacecraft damper has extremely high reliability, can adapt to complex environments such as space high vacuum, heat exchange change and the like, and can meet the service life requirement of 5-15 years in orbit. Meanwhile, in order to meet the vibration suppression requirements of different frequency bands and different load environments, various types of damper products need to be developed. The existing damper design and research about the vibration suppression of the aerospace structure concentrates on the aspect of online displacement load, but the research about the suppression of the rotation load is less, and a proper and effective damper design scheme is lacked.

In view of the above, the invention provides a design scheme of a negative-stiffness honeycomb structure of an annular damper, which has the advantages of good structural damping characteristic, high reliability and high robustness, and can be applied to the vibration reduction requirements of relevant mechanical structures of spacecrafts.

Disclosure of Invention

The invention aims to provide a 360-degree circumferential energy absorption damper for suppressing the structural vibration of a spacecraft.

The invention relates to a damper for suppressing structural vibration of a spacecraft, which comprises a damper outer ring 1, a damper inner ring 2 and a plurality of damping unit cells 3; the damping unit cells 3 are uniformly distributed between the outer ring 1 of the damper and the inner ring 2 of the damper along the annular direction; each damping unit cell 3 is stressed in the radial direction.

Further, the damping unit cell 3 is a thin laminated structure and comprises an upper laminated sheet 4, a middle laminated sheet 5 and a lower laminated sheet 6, and the damping unit cell 3 achieves energy dissipation through friction among the upper laminated sheet 4, the middle laminated sheet 5 and the lower laminated sheet 6.

Further, the damping unit cell 3 is formed into a honeycomb shape by coaxially arranging two groups of thin sheet laminated structures.

The invention has the following beneficial effects:

1) according to the annular damping structure, the energy consumption effect is realized by using the damping unit cell, the damping unit cell is of a sheet laminated structure, and the damping effect is realized by using friction energy absorption among the laminated sheets;

2) the annular damping structure provided by the invention adopts a single cell structure to be integrally arranged along an annular shape, so that the blind area effect of the head and the tail boundaries is overcome, and the effect of 360-degree circumferential energy absorption is realized.

Drawings

FIG. 1 is a schematic view of an annular damping structure according to the present invention;

FIG. 2 is a schematic diagram of a damping unit cell structure.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings.

The basic idea of the invention is: the linear damper can only bear plane load in one direction (axial direction) due to the limitation of the structure. For axial surface loads, no force is available. In addition, the linear damper has an end effect at two ends (boundaries), that is, a large stress is generated on a free boundary, which affects the overall energy absorption effect of the structure.

On the basis, the invention provides an annular damper, which comprises a damper outer ring 1, a damper inner ring 2 and a plurality of damping unit cells 3 as shown in figure 1. The damping unit cells 3 are connected end to end and uniformly distributed in the cavities between the outer ring 1 of the damper and the inner ring 2 of the damper along the circumferential direction to form a ring array structure. Each damping unit cell 3 is stressed along the radial direction; radial energy transfer is realized; the number of unit cells and the diameter of the ring can be adjusted according to different application objects.

The damping unit cell 3 is a thin laminated structure and comprises an upper laminated sheet 4, a middle laminated sheet 5 and a lower laminated sheet 6, and the damping unit cell 3 achieves energy dissipation through friction among the upper laminated sheet 4, the middle laminated sheet 5 and the lower laminated sheet 6.

As shown in fig. 2, the damping unit cell 3 is formed in a honeycomb shape by two sets of laminated sheet structures arranged coaxially.

The above embodiments are only for explaining and explaining the technical solution of the present invention, but should not be construed as limiting the scope of the claims. It should be clear to those skilled in the art that any simple modification or replacement based on the technical solution of the present invention may be adopted to obtain a new technical solution, which falls within the scope of the present invention.

Claims

1. The damper for suppressing the structural vibration of the spacecraft is characterized by comprising a damper outer ring (1), a damper inner ring (2) and a plurality of damping unit cells (3); the damping unit cells (3) are uniformly distributed between the outer ring (1) and the inner ring (2) of the damper along the annular direction; each damping unit cell (3) is stressed along the radial direction.

2. Damper for vibration suppression of spacecraft structures according to claim 1, characterized in that the damping unit cell (3) is a thin sheet laminate structure comprising an upper laminate (4), an intermediate laminate (5) and a lower laminate (6), the damping unit cell (3) dissipating energy through friction between the upper laminate (4), the intermediate laminate (5) and the lower laminate (6).

3. A damper for vibration suppression of spacecraft structures according to claim 2, wherein the damping unit cell (3) is formed as a honeycomb from two sets of sheet laminations arranged coaxially.