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Rigid-flexible coupling micro-vibration isolation device for inertial actuator

An actuating mechanism, rigid-flexible coupling technology, applied in the directions of aerospace vehicle guidance devices, motor vehicles, non-rotational vibration suppression, etc., can solve the problems of low reliability, complex structure, large size, etc., and achieve high reliability and small size. , The effect of good vibration isolation performance

Active Publication Date: 2018-08-17
SHANGHAI JIAOTONG UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Aiming at the above-mentioned deficiencies in the prior art, the present invention proposes a rigid-flexible coupling micro-vibration vibration isolation device of an inertial actuator, which overcomes the problems of complex structure, large volume and low reliability of the existing active vibration isolation device, and has better Vibration isolation performance without affecting the rotational torque output by the inertial actuator

Method used

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  • Rigid-flexible coupling micro-vibration isolation device for inertial actuator
  • Rigid-flexible coupling micro-vibration isolation device for inertial actuator
  • Rigid-flexible coupling micro-vibration isolation device for inertial actuator

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Embodiment 1

[0031] Such as figure 1 with Figure 4 As shown, this embodiment includes: the XZ flexible variable stiffness beam 1 fixedly arranged on the connecting rigid body 3, the YZ flexible variable stiffness beam 2 fixedly arranged on the connecting rigid body 3, the YZ flexible variable stiffness beam 2 and the XZ flexible variable stiffness beam 1 perpendicular to each other.

[0032] Such as figure 2 with image 3 As shown, the XZ flexible variable stiffness beam 1 and the YZ flexible variable stiffness beam 2 include: an elastic substrate 6, an electroactive polymer layer 7 disposed on the elastic substrate 6, and a first insulating mounting plate 4 (or a second insulating mounting plate 5 ), the elastic matrix 6 selects 65Mn spring steel rectangular beams for bending, the shape of the elastic matrix 6 includes a plurality of oblique waves, and the ratio of the width of the elastic matrix 6 to the thickness and the stiffness in the length direction is greater than 500.

[00...

Embodiment 2

[0040] Such as Image 6 As shown, the difference between this embodiment and Embodiment 1 is that the XZ flexible variable stiffness beam 1 and the YZ flexible variable stiffness beam 2 are realized by using a flexible node distributed matrix 9 with a cylindrical electroactive polymer 10 .

[0041] Compared with Embodiment 1, the further technical effects of this embodiment are: the overall structure can be designed smaller, the flexible variable stiffness beam needs less intelligent materials, the overall stiffness and damping control is easier, the reliability is higher, and the flexibility The node distributed matrix 9 can be made of non-metallic elastic material, and the cylindrical electroactive polymer 10 is also easier to design and manufacture.

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Abstract

A rigid-flexible coupling micro-vibration isolation device for an inertial actuator, comprising: a ring-shaped connecting rigid body and two flexible variable stiffness beams arranged inside the connecting rigid body, wherein: the two ends of the two flexible variable stiffness beams are respectively connected to the connecting rigid body Connected and connected vertically in the middle. The invention overcomes the problems of complex structure, large volume and low reliability of the existing active vibration isolation device, has better vibration isolation performance, and does not affect the rotational moment output by the inertial actuator.

Description

technical field [0001] The invention relates to a technology in the field of satellite equipment, in particular to a rigid-flexible coupling micro-vibration isolation device for an inertial actuator. Background technique [0002] The construction of high-quality new satellite platforms is a major national strategic demand. In order to ensure the stability of the satellite’s in-orbit operation and the ideal working environment for the equipped equipment, a high-precision attitude control system is required. The inertial actuator is an important part of the attitude control system, mainly including the gyro torquer and the momentum wheel. Sensitive loads carried by new satellite platforms, such as parabolic antennas on communication satellites and high-precision cameras on observation satellites, have high requirements on the stability of satellites during normal operation, and generally require vibrations less than 1×10 -4 g level. The momentum wheel is an important micro-v...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F16F15/02B64G1/22B64G1/24
CPCF16F15/02B64G1/22B64G1/24B64G1/228B64G1/245
Inventor 张文明邹鸿翔魏新生王森赵林川颜格
Owner SHANGHAI JIAOTONG UNIV