Vibration isolation device suitable for satellite control moment gyroscope

A technology for controlling moment gyroscopes and moment gyroscopes, which is applied in the direction of aerospace vehicle guidance devices, transportation and packaging, and non-rotational vibration suppression. Problems such as the coincidence of gyroscope centroids, to achieve good anisotropic decoupling characteristics, light weight, and the effect of ensuring satellite performance

Active Publication Date: 2021-05-25
SHANGHAI SATELLITE ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In summary, the deficiencies of the existing technology are summarized as follows: the stiffness of longitudinal translation and lateral torsion cannot be independently designed, and the height of the design stiffness center and the control moment are not considered The center of mass of the gyroscope coincides

Method used

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  • Vibration isolation device suitable for satellite control moment gyroscope
  • Vibration isolation device suitable for satellite control moment gyroscope
  • Vibration isolation device suitable for satellite control moment gyroscope

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0036] The present invention provides a vibration isolation device suitable for satellite control moment gyroscopes, comprising a lower mounting plate 1, an upper mounting plate 2 and a vibration isolation assembly, the lower mounting plate 1 is used to fix the vibration isolation device of the present invention on the satellite On the star body, the upper mounting plate 2 is provided with a gyro mounting position 5 and is provided with a threaded hole. The gyro mounting position 5 is used to install the control moment gyro 4 and is preferably fixed by a threaded hole or a screw. The vibration isolation assembly It includes a first vibration isolator array and a second vibration isolator array, the first vibration isolator array is installed between the lower mounting plate 1 and the upper mounting plate 2, and the second vibration isolator array is installed on the upper mounting plate On the plate 2, the lower mounting plate 1 and the upper mounting plate are preferably coaxi...

Embodiment 2

[0046] This embodiment is a preferred example of Embodiment 1.

[0047] In this embodiment, a satellite control moment gyro vibration isolation device is provided, such as figure 1 As shown, it includes a lower mounting plate 1, an upper mounting plate 2 and a vibration isolation assembly, and the mounting base plate 1 is connected to the satellite body through 8 M8 screws;

[0048] The upper mounting plate 2 is connected to the control torque gyroscope 4 through 8 M8 screws, and the vibration isolation assembly includes 8 sets of vibration isolators 3;

[0049] Further, the vibration isolators 3 are installed parallel to each other, and are respectively connected to the lower mounting plate 1 and the upper mounting plate 2 through four M8 screws;

[0050] Further, the vibration isolator 3 adopts a slotted hollow cylinder, and the cross section is bidirectionally inwardly slotted, and 8 slots are cut along the direction of the generatrix, and adjacent slots are staggered at 9...

Embodiment 3

[0055] This embodiment is a modification example of Embodiment 1.

[0056] In this embodiment, the vibration isolator 3 is a slotted hollow cylinder, wherein the slots are arranged along the direction of the busbar of the vibration isolator 3, and the number of the slots is a positive integer multiple of 3 slots, For example, 3 slots, or 6 slots, every two adjacent slots are staggered at 120° or 60°. When the vibration isolator 3 is manufactured, each parameter is controlled according to the actual situation to adjust the stiffness.

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Abstract

The invention provides a vibration isolation device suitable for a satellite control moment gyro, the vibration isolation device comprises a lower mounting plate, an upper mounting plate and a vibration isolation assembly, the vibration isolation assembly comprises a first vibration isolator array and a second vibration isolator array, and the first vibration isolator array is mounted between the lower mounting plate and the upper mounting plate. The second vibration isolator array is mounted on the upper mounting plate, each of the first vibration isolator array and the second vibration isolator array comprises four vibration isolators, and the four vibration isolators are arranged in parallel. According to the invention, the coupling characteristic is designed by considering the mounting requirement of the control moment gyroscope from the actual vibration reduction requirement; The installed vibration isolation assembly is symmetrically and coplanarly arranged, so that the planeness requirement of the control moment gyroscope during installation is ensured, the rigidity center passes through the mass center of the control moment gyroscope, good decoupling characteristics in all directions are achieved, the multi-direction vibration isolation effect is achieved, and more stable and more excellent performance is obtained.

Description

technical field [0001] The invention relates to the technical field of satellite vibration isolation, in particular to a vibration isolation device suitable for satellite control moment gyroscopes. Background technique [0002] The service time, fast maneuverability, imaging performance and other indicators of modern satellites have all increased significantly. As the key actuator of the satellite attitude and orbit control system, the control moment gyroscope has the characteristics of large moment of inertia and fast adjustment speed, and is widely used in high-resolution and large-observation-angle satellites. However, due to a series of factors such as processing technology and assembly, the high-speed rotation of the inner rotor of the control torque gyroscope in the working state will bring high-level micro-vibrations. The high-frequency vibration of the control moment gyro seriously affects the work of the sensitive payload of the optical satellite, affecting its per...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/28F16F15/02
CPCB64G1/286F16F15/02
Inventor 刘兴天池忠明周伟敏赵发刚许银生聂斌斌应敏晓
Owner SHANGHAI SATELLITE ENG INST
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