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Double-magnetic-circuit electromagnetic actuator with compensation magnetic steel

An electromagnetic actuator and dual magnetic circuit technology, applied in the field of aerospace, can solve the problems of large thrust fluctuation, large volume and mass, and low thrust density, etc., to reduce the thickness of the yoke, reduce the volume and mass, and increase the strength of the air gap magnetic field and the effect of thrust density

Active Publication Date: 2021-10-29
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the current traditional electromagnetic actuators have large volume and mass, low thrust density, and large thrust fluctuations, so it is difficult to be directly used to push nano-satellites to achieve on-orbit separation and release.

Method used

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  • Double-magnetic-circuit electromagnetic actuator with compensation magnetic steel
  • Double-magnetic-circuit electromagnetic actuator with compensation magnetic steel
  • Double-magnetic-circuit electromagnetic actuator with compensation magnetic steel

Examples

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Embodiment Construction

[0025] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention.

[0026] see Figure 1-4 Describe this embodiment, a double magnetic circuit electromagnetic actuator with compensation magnets, which includes a stator and a mover, the stator includes a stator frame 1, an outer magnetic structure and an inner magnetic structure, and the outer magnetic structure includes an outer yoke 2, The outer magnetic ring 3, the outer rear compensation magnetic ring 4A, the outer front compensation magnetic ring 4B and the outer paramagnetic yoke 5, the outer magnetic yoke 2 is located at the radial inner side of the outer wall of the annular groove of the stator frame 1, and the outer magnetic ring 3 is located at the outer magnetic yoke 2 The radial inner center position of the outer magnetic ring 4A is located at the axial rear end of the outer magnetic ...

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PUM

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Abstract

The invention provides a double-magnetic-circuit electromagnetic actuator with compensation magnetic steel, and belongs to the field of aerospace. The problems that an existing electromagnetic actuator is large in size and mass, small in thrust density and large in thrust fluctuation are solved. The actuator comprises a stator and a rotor; the stator comprises a stator frame, an outer magnetic structure and an inner magnetic structure; the outer magnetic structure comprises an outer magnetic yoke, an outer magnetic ring, an outer rear compensation magnetic ring, an outer front compensation magnetic ring and an outer paramagnetic yoke; the outer magnetic yoke is located on the radial inner side of the outer wall of an annular groove of the stator frame, and the outer magnetic ring is located in the center of the radial inner side of the outer magnetic yoke. The outer rear compensation magnetic ring is located at the axial rear end of the outer magnetic ring, the outer front compensation magnetic ring is located at the axial front end of the outer magnetic ring, the outer paramagnetic yoke is located on the radial inner side of the outer magnetic ring, and the outer magnetic structure is fixedly installed on the stator frame through the outer lock nut. The actuator is mainly used for electromagnetic actuators.

Description

technical field [0001] The invention belongs to the field of aerospace, in particular to a double magnetic circuit electromagnetic actuator with compensation magnets. Background technique [0002] It has become a research hotspot in today's international aerospace field that multiple satellites work together to complete complex space exploration tasks, such as formations and clusters. In particular, nano-satellites have the advantages of short development cycle and low cost. The clusters formed by them have high flexibility and good robustness, and can complete tasks that large satellites cannot independently complete or require high costs. [0003] In the on-orbit deployment of nano-satellites, in order to save costs, it is often necessary to use a deployer to store and release a large number of nano-satellites in orbit during a launch mission. Due to the weak orbit control capability of nano-satellites and the limited fuel they carry, facing more complex deployment tasks ...

Claims

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Application Information

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IPC IPC(8): H02K41/00H02K33/00
CPCH02K41/00H02K33/00
Inventor 岳洪浩赵勇杨飞陆一凡吴君余运锋阮琪
Owner HARBIN INST OF TECH
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