A multi-degree-of-freedom momentum exchange actuator for attitude adjustment of spacecraft

A technology for aerospace vehicles and momentum exchange, which is applied in the direction of aerospace vehicles, aerospace vehicle guidance devices, aircraft, etc., can solve the problems of increased power loss, difficulty in multi-motor coordinated control, and large overall size, and achieve small error accumulation , compact structure and high motion precision

Active Publication Date: 2018-05-25
BEIHANG UNIV
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

However, this design scheme has some inherent defects that are difficult to overcome, such as the large overall size, the difficulty of multi-motor coordinated control, and the structural self-weight of multi-motor and multi-flywheel brings additional burden to the aircraft and greatly increases power loss.

Method used

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  • A multi-degree-of-freedom momentum exchange actuator for attitude adjustment of spacecraft
  • A multi-degree-of-freedom momentum exchange actuator for attitude adjustment of spacecraft
  • A multi-degree-of-freedom momentum exchange actuator for attitude adjustment of spacecraft

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Embodiment Construction

[0027] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0028] The multi-degree-of-freedom momentum exchange type spacecraft attitude adjustment actuator of the present invention includes a rotor part 1 and a stator part 2, such as figure 1 , figure 2 shown.

[0029] Such as image 3 As shown, the rotor part 1 is a solid spherical structure, and the rotor part 1 is provided with 6 rotor pole mounting slots 101; the layout of the 6 rotor pole mounting slots 101 is: one for each north and south pole, and 90° distribution on the equatorial plane 4. The magnetic pole casings 102 are embedded in each of the above-mentioned rotor magnetic pole installation slots 101 , and the magnetic pole casings 102 can be fixed on the rotor part 1 by threading or glueing. Each magnetic pole casing 102 is fixedly installed with a magnetically conductive magnetic pole 103 , and the magnetically conductive magnetic pole 103 is inst...

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Abstract

The invention discloses a multi-degree-of-freedom momentum exchange type aerospace vehicle attitude adjustment actuator, which is used to solve the disadvantages of redundant structure and large power loss of the existing aerospace vehicle momentum exchange type attitude adjustment actuator; it includes a rotor part and a stator part. The rotor part has a spherical structure and is embedded with a plurality of magnetically conductive poles. The magnetically conductive magnetic poles can be permanent magnets or soft magnetic. The stator part is a spherical structure assembled from upper and lower hemispheres and is embedded with multiple winding magnetic poles. The winding pole can be an air-core winding coil or a winding coil containing a soft magnetic core. The stator magnetic poles are arranged concentrically with the inside of the stator magnetic poles, and the two are connected by ball bearings. Furthermore, different winding energization strategies can be used to drive the rotor part to spin along different axes, and the attitude of the spacecraft can be adjusted by a single device based on the principle of momentum conservation.

Description

technical field [0001] The invention relates to the fields of multi-degree-of-freedom electromagnetic drive and aerospace, and relates to an electromagnetic space vehicle attitude adjustment device, specifically, a multi-freedom momentum exchange type space vehicle attitude adjustment actuator. Background technique [0002] In the field of aerospace and aerospace, the attitude adjustment actuators of aircraft are divided into three types: mass displacement type, momentum exchange type and environment field type according to the principle of torque generation. Among them, the traditional momentum exchange actuator needs to rely on multiple motors to drive multiple flywheels in different positions to adjust the attitude of the aircraft. However, this design scheme has some inherent defects that are difficult to overcome, such as the large overall size, the difficulty of multi-motor coordinated control, and the structural self-weight of multi-motor and multi-flywheel brings add...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/245
Inventor 严亮张璐朱波吴泽武刘德龙
Owner BEIHANG UNIV
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