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CN-117208232-B - Vibration isolation and buffer integrated support and mounting structure for satellite momentum wheel

CN117208232BCN 117208232 BCN117208232 BCN 117208232BCN-117208232-B

Abstract

The invention provides a vibration isolation and buffer integrated bracket and a mounting structure for a satellite momentum wheel, wherein the vibration isolation and buffer integrated bracket comprises a mounting platform, a vibration isolation assembly and a mounting bracket, one end of the vibration isolation assembly is connected with the mounting platform, and the other end of the vibration isolation assembly is connected with the mounting bracket; the vibration isolation assembly comprises two orthogonal pairs of elastic sheets which are axially arranged along the vibration isolation assembly, and damping energy dissipation materials are filled between any pair of elastic sheets. The device also comprises a momentum wheel and a satellite structure plate, wherein the mounting platform is fixedly connected with the momentum wheel, and the mounting bracket is fixedly connected with the satellite structure plate. When the vibration isolation assembly is subjected to transverse force in the bending direction of the elastic sheet, transverse displacement is easy to generate, the transverse linear rigidity of the vibration isolation assembly in two orthogonal directions is close to and far smaller than the axial linear rigidity, and when the vibration isolation assembly transversely vibrates, the elastic sheet in the corresponding direction can drive damping energy consumption materials to generate shearing deformation, so that vibration energy is greatly consumed, the amplitude of the momentum wheel is reduced, and the momentum wheel is ensured to safely pass through the transmitting section.

Inventors

  • Dong yaohai
  • LI HAO
  • DENG ZEHUA
  • Xiong Lianglei
  • ZHANG ZHENGYAO
  • WANG MENG

Assignees

  • 上海卫星工程研究所

Dates

Publication Date
20260508
Application Date
20230816

Claims (8)

  1. 1. The vibration isolation and buffering integrated support for the satellite momentum wheel is characterized by comprising a mounting platform (1), a vibration isolation assembly (2) and a mounting support (3), wherein one end of the vibration isolation assembly (2) is connected with the mounting platform (1), and the other end of the vibration isolation assembly (2) is connected with the mounting support (3); The vibration isolation assembly (2) comprises two orthogonal pairs of elastic thin sheets (201) which are axially arranged along the vibration isolation assembly (2), damping energy consumption materials (204) are filled between any pair of elastic thin sheets (201), and the transverse linear rigidity of the vibration isolation assembly in two orthogonal directions is far smaller than the axial linear rigidity; The vibration isolation assembly (2) further comprises two connecting blocks (202) and a holding block (203), and the two connecting blocks (202) are respectively arranged at two sides of the holding block (203) along the axial direction of the vibration isolation assembly (2); one pair of the elastic sheets (201) is connected with one connecting block (202) and the holding block (203), and the other pair of the elastic sheets (201) is connected with the other connecting block (202) and the holding block (203); Any one of the elastic sheets (201) is arc-shaped, and the arc-shaped middle part of any one of the elastic sheets (201) is concave towards the direction close to the central shaft of the vibration isolation assembly (2).
  2. 2. The integrated vibration isolation and damping mount for a satellite momentum wheel according to claim 1, wherein a joint (202 a) is provided on either side of the connection block (202) facing away from the retaining block (203).
  3. 3. The integrated vibration isolation and buffer support for the satellite momentum wheel according to claim 2, characterized in that a platform connection groove (101) is arranged on the mounting platform (1), a support connection groove (301) is arranged on the mounting support (3), a joint (202 a) on one connecting block (202) of the vibration isolation assembly (2) is tightly connected with the platform connection groove (101), and a joint (202 a) on the other connecting block (202) of the vibration isolation assembly (2) is tightly connected with the support connection groove (301).
  4. 4. A vibration isolation and buffering integrated bracket for a satellite momentum wheel according to claim 3, wherein a plurality of platform connecting grooves (101) are uniformly distributed on a mounting platform (1) along the circumferential direction of the mounting platform (1), a plurality of bracket connecting grooves (301) are uniformly distributed on a mounting bracket (3) along the circumferential direction of the mounting bracket (3), the array axes of the platform connecting grooves (101) and the array axes of the bracket connecting grooves (301) are collinear, the number of the platform connecting grooves (101) and the number of the bracket connecting grooves (301) are equal, and the distance between the center of any one of the platform connecting grooves (101) and the array axis and the distance between the center of any one of the bracket connecting grooves (301) and the array axis are the same.
  5. 5. The integrated vibration isolation and damping mount for a satellite momentum wheel according to claim 4, wherein the central axis of the vibration isolation assembly (2) is parallel or collinear with the array axis of platform attachment grooves (101).
  6. 6. The integrated vibration isolation and damping support for a satellite momentum wheel according to claim 1, wherein a damping system (4) is arranged between the mounting platform (1) and the mounting support (3), the damping system (4) comprises a damping sleeve (102) arranged on the mounting platform (1) and a damping shaft (302) arranged on the mounting support (3), and the damping shaft (302) and the damping sleeve (102) are coaxially nested and mounted.
  7. 7. The vibration isolation and buffering integrated support for the satellite momentum wheel according to claim 6, wherein a buffering washer (5) is sleeved on the buffering shaft (302), the buffering washer (5) is in contact with the inner wall of the buffering sleeve (102), and a radial buffering space is formed between the buffering shaft (302) and the inner wall of the buffering sleeve (102); the buffer shaft (302) is in clearance fit with the bottom of the exchange sleeve.
  8. 8. A mounting structure for a satellite momentum wheel, characterized in that a vibration isolation and buffering integrated bracket for a satellite momentum wheel according to any one of claims 1-7 is adopted, and the mounting structure further comprises a momentum wheel (6) and a satellite structural plate (7), wherein the mounting platform (1) is fixedly connected with the momentum wheel (6), and the mounting bracket (3) is fixedly connected with the satellite structural plate (7).

Description

Vibration isolation and buffer integrated support and mounting structure for satellite momentum wheel Technical Field The invention relates to the technical field of vibration isolation of satellite momentum wheels, in particular to a vibration isolation and buffer integrated bracket for a satellite momentum wheel and an installation structure. Background The momentum wheel is used as a rotating component with important functions of positioning, energy storage, control and the like of spacecrafts such as satellites, and the like, and can output broadband tiny excitation to the outside due to the characteristics of the structure of the momentum wheel when in-orbit operation, so that the satellite platform is induced to generate tiny vibration, the pointing precision and stability of sensitive loads on the satellites are seriously affected, and the resolution ratio of an ultra-high precision instrument is reduced. Therefore, research on the micro-vibration suppression technology aiming at the momentum wheel is particularly important to the development of high-resolution satellites in China. Aiming at the problem, the aim of vibration suppression is mainly achieved by installing a bracket with a passive vibration isolation function between the momentum wheel and the star. However, in order to obtain a wider vibration isolation frequency band in engineering and simultaneously ensure that the momentum wheel can safely pass through the vibration environment of the transmitting section, an unlocking mechanism is generally required to be added to the vibration isolation bracket, so that additional quality and resource consumption can be brought, and meanwhile, the reliability of the system can be reduced. The prior Chinese patent application document with the publication number of CN207374708U discloses a momentum wheel bracket for avoiding the influence of micro-vibration resonance, which comprises a top structural wall, a left structural wall, a right structural wall, a middle structural wall, a front outer structural wall, a mounting structural wall, a rear outer structural wall, an ear piece mounting plate, a momentum wheel bracket mounting hole and a momentum wheel mounting hole, and is used for mounting a momentum wheel executing mechanism of a spacecraft. The support in the prior art only depends on improving the natural frequency to avoid coupling with the momentum wheel interference, does not have an on-orbit vibration isolation function, provides a rigid support for the momentum wheel in the transmitting section, and cannot provide a buffering function. The prior Chinese patent application document with publication number of CN114060466B discloses a light vibration isolation metal composite flywheel bracket, a preparation method and application thereof, and belongs to the technical field of metal material structural design and processing. The metal composite flywheel bracket comprises a magnesium alloy bottom plate with light weight and high damping performance, a titanium alloy lattice sandwich flywheel mounting surface with a vibration buffering function, a titanium alloy supporting beam with high rigidity, and a light vibration isolation metal composite flywheel bracket prepared by a method combining metal block processing and metal 3D printing. The bracket in the prior art has high first-order frequency and narrow vibration isolation frequency band, and cannot be suitable for isolating low-frequency disturbance. At present, an on-orbit vibration isolation requirement caused by a momentum wheel is needed to be met, and the momentum wheel is ensured to safely pass through a vibration environment of a transmitting section. Disclosure of Invention Aiming at the defects in the prior art, the invention aims to provide a vibration isolation and buffering integrated bracket and a mounting structure for a satellite momentum wheel. The vibration isolation and buffering integrated support for the satellite momentum wheel comprises a mounting platform, a vibration isolation assembly and a mounting support, wherein one end of the vibration isolation assembly is connected with the mounting platform, the other end of the vibration isolation assembly is connected with the mounting support, the vibration isolation assembly comprises two orthogonal pairs of elastic thin sheets which are axially mounted along the vibration isolation assembly, and damping energy consumption materials are filled between any pair of elastic thin sheets. Preferably, the vibration isolation assembly further comprises two connecting blocks and a retaining block, wherein the two connecting blocks are respectively arranged on two sides of the retaining block along the axial direction of the vibration isolation assembly, one pair of elastic sheets is connected with one connecting block and the retaining block, and the other pair of elastic sheets is connected with the other connecting block and the retaining block. Preferably, a joint is arrange