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Device and method for satellite vibration isolation

A technology of vibration isolation and driving device, which is applied in the field of satellites to achieve the effect of simple structure and meeting the requirements of stability

Inactive Publication Date: 2016-12-14
CHINA ACADEMY OF SPACE TECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The larger the payload of the satellite, the higher the requirement for stability. However, there are unavoidable disturbance factors in the satellite that affect the stability of the satellite payload, such as the momentum wheel in the satellite, the driving mechanism of the solar panel, the control moment gyro and The periodic movement of the vibration source such as the antenna pointing mechanism will produce disturbance, and the work of ion propulsion, cryogenic refrigerator and environmental disturbance will also produce vibration

Method used

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  • Device and method for satellite vibration isolation
  • Device and method for satellite vibration isolation
  • Device and method for satellite vibration isolation

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0021] Embodiment 1. Satellite vibration isolation device. The structure of the satellite vibration isolation device is as follows: figure 1 with figure 2 shown.

[0022] exist figure 1 with figure 2 Among them, the satellite vibration isolation device 1 of the present embodiment includes: an upper flange 5, a lower flange 6, and a flexible hinge 4 (the side view of which is as shown in figure 2 shown) and at least two drives 2 ( figure 1 Four driving devices 2 are shown in the figure); preferably, the satellite vibration isolation device 1 of the present embodiment may also include: at least two position sensors (Fig. not shown).

[0023] The upper flange 5 is mainly used to securely connect the satellite vibration isolation device 1 to the satellite load 10. For example, the upper flange 5 is provided with a plurality of upper flange mounting holes 7, and the upper flange 5 passes through the upper flange mounting holes 7 and corresponding Fasteners are fixedly con...

Embodiment 2

[0034] Embodiment 2, a specific application of the satellite vibration isolation device 1 .

[0035] A specific example in which the satellite vibration isolation device 1 of the present embodiment is applied to an optical satellite is as follows: image 3 as shown, image 3 The satellite vibration isolation device 1 is fixedly connected with the satellite load 10 on the one hand, and fixedly connected with the satellite platform 11 on the one hand, and the satellite platform 11 is provided with two solar cell wings 12; the Z axis is the direction of the satellite load 10, and the X axis The Y axis and Y axis may be two radial directions perpendicular to each other in the radial direction of the satellite payload 10 .

[0036] The satellite load in the optical satellite is usually a space optical camera, and the satellite vibration isolation device 1 of this embodiment can make the space optical camera work in a stable environment, that is, this embodiment can make the optica...

Embodiment 3

[0038] Embodiment 3, satellite vibration isolation method. The procedure of this method is as follows Figure 4 shown.

[0039] Figure 4 Among them, the satellite vibration isolation method of this embodiment includes: S400, S410 and S420. next to Figure 4 Each step contained in is described separately.

[0040] S400. Receive attitude change information of the satellite payload 10 in inertial space transmitted from the inertial measurement unit rigidly connected to the satellite payload 10 .

[0041] Specifically, the inertial measurement unit is rigidly connected to the satellite payload 10, and the inertial measurement unit may be a star sensor or a high-precision gyroscope or other components. The inertial measurement unit can measure the attitude change information of the satellite payload 10 in the inertial space in real time, and the inertial measurement unit can upload the measured attitude change information of the satellite payload 10 in the inertial space to t...

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Abstract

The invention discloses a device and method for satellite vibration isolation. The device for the satellite vibration isolation comprises an upper flange, a lower flange, a flexible hinge and at least two drive devices, wherein the upper flange is firmly connected to a satellite load; the lower flange is firmly connected to a satellite platform; the flexible hinge is disposed between the upper flange and the lower flange, and the flexible hinge is firmly connected to both the upper flange and the lower flange; and the drive devices are disposed between the upper flange and the lower flange, the drive devices are firmly connected to the upper flange and the lower flange, and the drive devices conduct radial rotation around the satellite load along with the lower flange according to drive control signals transmitted by a controller. The technical scheme provided by the invention has the advantages that a quiet and steady working environment can be provided for the satellite load; and a requirement of the satellite load for stability can be satisfied. In addition, the device for the satellite vibration isolation disclosed by the embodiment is characterized by a simple structure, high control accuracy, and low rigidness coupling, etc.

Description

technical field [0001] The invention relates to satellite technology, in particular to a satellite vibration isolation device and a satellite vibration isolation method. Background technique [0002] For satellites such as optical remote sensing satellites, astronomical observation satellites, and laser communication satellites, in order to improve the imaging or communication performance of the satellites, the satellite payloads are often larger in size, such as larger apertures or longer focal lengths. The larger the satellite payload, the higher the stability requirements. However, there are inevitably disturbance factors in the satellite that affect the stability of the satellite payload, such as the momentum wheel in the satellite, the solar panel drive mechanism, the control moment gyro and Periodic movement of vibration sources such as antenna pointing mechanisms will produce disturbances, and the work of ion thrusters, cryogenic refrigerators, and environmental distu...

Claims

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Application Information

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IPC IPC(8): B64G1/22
CPCB64G1/22B64G1/228
Inventor 岳荣刚王虎妹宋鹏飞王世涛孙晓峰刘晓磊
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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