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Inertial actuator rigid-flexible coupling micro-vibration isolation device

An actuator, rigid-flexible coupling technology, applied in aerospace vehicle guides, motor vehicles, non-rotational vibration suppression, etc., can solve the problems of large volume, low reliability, complex structure, etc., and achieve small volume and high reliability , design reasonable effect

Active Publication Date: 2017-07-14
SHANGHAI JIAO TONG 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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  • Inertial actuator rigid-flexible coupling micro-vibration isolation device
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  • Inertial actuator rigid-flexible coupling micro-vibration isolation device

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Embodiment 1

[0031] Such as figure 1 and 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 and 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.

[0033...

Embodiment 2

[0040] Such as Figure 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

The invention relates to an inertial actuator rigid-flexible coupling micro-vibration isolation device, which comprises a connecting rigid body with an annular structure, and two flexible varied rigidity beams arranged in the connecting rigid body, wherein two ends of the two flexible varied rigidity beams are connected with the connecting rigid body; and the two flexible varied rigidity beams are perpendicularly connected in the middle. The inertial actuator rigid-flexible coupling micro-vibration isolation device provided by the invention solves the problems that an existing active vibration isolation device is complex in structure, large in size, and low in reliability, has a better vibration isolation performance, and cannot affect a driving torque output by an 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 Applications(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 JIAO TONG UNIV