Single-layer magnetic pole electromagnetic actuator with double windings

An electromagnetic actuator and double-winding technology, which is applied in the aerospace field, can solve the problems of small thrust, obvious armature reaction, and low energy conversion rate of electromagnetic actuators, achieve high thrust density, increase air gap magnetic field strength, small size effect

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, in the current traditional electromagnetic actuator, the electromagnetic field generated by the coil weakens the original permanent magnetic field generated by the magnetic ring, and the armature reaction is obvious, resulting in low energy conversion rate and small thrust of the electromagnetic actuator.

Method used

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  • Single-layer magnetic pole electromagnetic actuator with double windings
  • Single-layer magnetic pole electromagnetic actuator with double windings
  • Single-layer magnetic pole electromagnetic actuator with double windings

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Embodiment Construction

[0028] 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.

[0029] see Figure 1-7 Describe this embodiment, a single-layer magnetic pole electromagnetic actuator with double windings, it includes a stator and a mover, the stator includes a stator frame 1, an outer magnetic structure and an inner magnetic structure, the outer magnetic structure includes an outer yoke 2, an outer Magnetic ring 3, outer rear magnetic ring 4A, outer front magnetic ring 4B, commutation magnetic guide ring 5, outer paramagnetic yoke 6 and outer front magnetic yoke 7, outer magnetic yoke 2 is located at the radial inner center of the outer wall of the groove of stator frame 1 position, the outer magnetic ring 3 is located at the radial inner center of the outer magnetic ring 2, the outer rear magnetic ring 4A is located at the axial rear end of the outer magne...

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Abstract

The invention provides a single-layer magnetic pole electromagnetic actuator with double windings, and belongs to the field of aerospace. The problem that an existing electromagnetic actuator is small in thrust is 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 magnetic ring, an outer front magnetic ring, a commutation magnetic conduction ring, an outer paramagnetic yoke and an outer front magnetic yoke, and the rotor is arranged in the stator. And low-cost and high-efficiency in-orbit release of the nano-satellite can be a double-air-gap double-winding structure is adopted, the current direction of the inner winding is opposite to the current direction of the outer winding, armature reaction is restrained, and the energy conversion rate is improved. The actuator is mainly used for electromagnetic actuators.

Description

technical field [0001] The invention belongs to the field of aerospace, in particular to a single-layer magnetic pole electromagnetic actuator with double windings. 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 order to save costs, a deployer is often used to store and release a large number of nano-satellites in a predetermined orbit during a rocket launch mission. Nano-satellites have weak orbit control capabilities and limited fuel. Therefore, it is expected that when these nano-satellites are ejected and separated, the separation ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02K41/00H02K33/00
CPCH02K41/00H02K33/00
Inventor 岳洪浩赵勇杨飞陆一凡吴君阮琪
Owner HARBIN INST OF TECH
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