CN113452230B - High-thrust-density electromagnetic actuator for nano-satellite deployer - Google Patents

High-thrust-density electromagnetic actuator for nano-satellite deployer Download PDF

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Publication number
CN113452230B
CN113452230B CN202110752428.1A CN202110752428A CN113452230B CN 113452230 B CN113452230 B CN 113452230B CN 202110752428 A CN202110752428 A CN 202110752428A CN 113452230 B CN113452230 B CN 113452230B
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magnetic ring
yoke
magnetic
ring
magnet
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CN113452230A (en
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岳洪浩
赵勇
杨飞
陆一凡
吴君
余运锋
阮琪
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Harbin Institute of Technology
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Harbin Institute of Technology
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    • HELECTRICITY
    • H02GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02KDYNAMO-ELECTRIC MACHINES
    • H02K33/00Motors with reciprocating, oscillating or vibrating magnet, armature or coil system
    • H02K33/18Motors with reciprocating, oscillating or vibrating magnet, armature or coil system with coil systems moving upon intermittent or reversed energisation thereof by interaction with a fixed field system, e.g. permanent magnets

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Abstract

The invention provides a high thrust density electromagnetic actuator for a nano-satellite deployer, which mainly comprises a stator and a rotor, wherein the stator mainly comprises: the stator comprises a stator frame, a magnet yoke, a magnet ring and a lock nut; the active cell mainly includes: coil skeleton and coil. According to the invention, the upper and lower double-permanent-magnet branch magnetic fluxes are formed on the single-layer magnetic pole, so that the magnetic saturation of the magnetic yoke is effectively relieved by shunting the permanent-magnet magnetic fluxes, the thickness of the magnetic yoke is reduced, and the axial size and the volume quality of the actuator are reduced due to the single-layer coil configuration of the single-layer magnetic pole; the double permanent magnet branch loop improves the distribution of an air gap magnetic field, reduces thrust fluctuation and increases thrust density. The invention has the characteristics of small volume, light weight, high thrust density and stable thrust, and is very suitable for the deployer to carry out on-orbit speed regulation and release on the nano-satellite.

Description

High-thrust-density electromagnetic actuator for nano-satellite deployer
Technical Field
The invention relates to a high-thrust-density electromagnetic actuator for a nano-satellite deployer, and belongs to the technical field of aerospace.
Background
The cooperative work of a plurality of satellites to complete complex space exploration tasks becomes a research hotspot in the international aerospace field, such as formation, clustering and the like. Particularly, the advantages of short development period, low cost and the like of the nano-satellite are achieved, the formed cluster is high in flexibility and robustness, and tasks which cannot be completed independently by a large satellite or which are high in required cost can be completed. For the task of deploying the nano-satellites in the orbit, in order to save cost, a large amount of nano-satellites are stored and released in the orbit by using a deployer in one launching task. Because of the weak orbital control capability and limited fuel of the nano-satellites, it is desirable to be able to naturally form stable relative motion with each other by adjusting the speed, timing and angle of ejecting the nano-satellites when ejecting and separating the nano-satellites. This requires the on-track deployer to implement the pacing release for different quality satellites at a particular time. And the traditional deployer adopts compression springs more, so that the repeatable and accurate release of the nano-satellite is difficult to realize.
The electromagnetic actuator utilizes the electrified coil to generate electromagnetic force in a magnetic field, has high response speed and is very suitable for the deployer to repeatedly regulate the speed and release the nano-satellite. In industrial application, in order to improve the thrust density of an electromagnetic actuator, a halbach permanent magnet array and a topological structure thereof are often adopted, or the shape of magnetic steel and the magnetizing direction of the magnetic steel are changed. For aerospace applications, it is often desirable for electromagnetic actuators to be small and lightweight for ease of installation and to reduce launch costs.
Disclosure of Invention
In order to solve the technical problems of small size, light weight and the like of the expected electromagnetic actuator in the background art, the invention provides the high thrust density electromagnetic actuator for the nano-satellite deployer.
The invention provides a high-thrust-density electromagnetic actuator for a nano-satellite deployer, which comprises a stator and a rotor, wherein the stator comprises a stator frame, an outer magnet yoke, an outer magnet ring, an outer upper magnet ring, an outer lower magnet ring, an outer upper magnet yoke, an outer locking nut, an inner magnet yoke, an inner magnet ring, an inner upper magnet ring, an inner lower magnet ring, an inner upper magnet yoke, an inner locking nut and an end magnet yoke; the rotor comprises a coil framework and an annular coil;
the outer magnet yoke is positioned on the radial inner side of the outer wall of the stator frame groove, the outer magnet ring is positioned at the radial inner center position of the outer magnet yoke, the outer upper magnet ring is positioned at the upper ends of the outer magnet yoke and the outer magnet ring, the outer lower magnet ring is positioned at the lower ends of the outer magnet yoke and the outer magnet ring, the outer locking nut is positioned at the upper end of the outer upper magnet yoke, the inner magnet yoke is positioned on the radial outer side of the inner wall of the stator frame groove, the inner magnet ring is positioned on the radial outer side of the inner magnet yoke, the inner upper magnet ring is positioned at the upper ends of the inner magnet yoke and the inner magnet ring, the inner lower magnet ring is positioned at the lower ends of the inner magnet yoke and the inner upper magnet ring, the inner upper magnet yoke is positioned at the upper end of the inner upper magnet yoke, the end magnet yoke is positioned at the lower ends of the outer lower magnet ring and the inner lower magnet ring, and the outer upper magnet yoke are fixedly installed on the stator frame through threads between the outer locking nut and the stator frame, the inner yoke, the inner magnetic ring, the inner upper magnetic ring, the inner lower magnetic ring, the inner upper magnetic yoke and the end magnetic yoke are fixedly installed in an annular groove of the stator frame through threads between the inner locking nut and the stator frame, air gaps are formed among the radial inner walls of the outer yoke, the outer magnetic ring, the outer upper magnetic ring, the outer lower magnetic ring, the outer upper magnetic yoke and the outer locking nut, the radial outer walls of the inner yoke, the inner magnetic ring, the inner upper magnetic ring, the inner lower magnetic ring, the inner upper magnetic yoke and the inner locking nut, the coil framework is located on the radial inner sides of the outer yoke, the outer magnetic ring, the outer upper magnetic ring, the outer lower magnetic ring, the outer upper magnetic yoke and the outer locking nut, and the annular coil is wound and fixed in the groove of the coil framework.
Preferably, the outer magnetic ring, the outer upper magnetic ring, the outer lower magnetic ring, the inner upper magnetic ring and the inner lower magnetic ring are made of cobalt alloy hard magnetic materials, wherein the outer magnetic ring and the inner magnetic ring are magnetized in the radial direction, the outer upper magnetic ring, the outer lower magnetic ring, the inner upper magnetic ring and the inner lower magnetic ring are magnetized in the axial direction, and the magnetizing directions are inner N in the outer S of the outer magnetic ring, upper N and lower N of the outer upper magnetic ring, upper N and lower S of the outer lower magnetic ring, inner N in the outer S of the inner magnetic ring, upper N and lower S of the inner upper magnetic ring and upper S and lower N of the inner lower magnetic ring; or the magnetizing directions are N inner S outside the outer magnetic ring, N upper S lower S outside the outer upper magnetic ring, S lower N outside the outer lower magnetic ring, N inner S outside the inner magnetic ring, S lower N inside the inner upper magnetic ring and N lower S above the inner lower magnetic ring.
Preferably, the outer yoke, the outer upper yoke, the inner upper yoke and the end yoke are made of soft magnetic alloy 1J50 material.
Preferably, the widths of the outer upper magnetic ring, the outer lower magnetic ring and the outer upper magnetic yoke are the sum of the thicknesses of the outer yoke and the outer magnetic ring, and the widths of the inner upper magnetic ring, the inner lower magnetic ring and the inner upper magnetic yoke are the sum of the thicknesses of the inner yoke and the inner magnetic ring.
The high-thrust-density electromagnetic actuator for the nano-satellite deployer has the beneficial effects that:
1. the invention forms an upper and a lower double permanent magnetic branch magnetic circuits on the single-layer magnetic pole structure, realizes the shunting of the permanent magnetic flux, thereby effectively relieving the magnetic saturation of the magnetic yoke, and reducing the thickness of the magnetic yoke and the volume quality of the electromagnetic actuator.
2. Compared with the traditional double-sided double-magnetic-pole configuration, the double-sided single-layer magnetic-pole configuration effectively reduces the axial and radial dimensions of the electromagnetic actuator.
3. The magnetic fluxes of the upper permanent magnet branch loop and the lower permanent magnet branch loop respectively act on the upper area and the lower area of the air gap, the magnetic field is uniformly distributed, and compared with the traditional electromagnetic actuator, the electromagnetic actuator has the advantages that the output is more stable, and the thrust fluctuation is effectively inhibited.
4. In summary, the present invention has the advantage of reducing the volumetric mass of the electromagnetic actuator as well as increasing the thrust density.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention.
In the drawings:
FIG. 1 is a radial cross-sectional view of an electromagnetic actuator of a high thrust density electromagnetic actuator for a nanostar deployer of the present invention;
FIG. 2 is a cross-sectional view of a stator of an electromagnetic actuator of a high thrust density electromagnetic actuator for a nanostar deployer of the present invention;
FIG. 3 is a three-dimensional schematic diagram of a mover of an electromagnetic actuator of the high thrust density electromagnetic actuator for a nanostar deployer of the invention
FIG. 4 is a schematic diagram of a dual permanent magnet branch loop of an electromagnetic actuator of a high thrust density electromagnetic actuator for a nanosatellite deployer in accordance with the present invention;
FIG. 5 is a magnetic line simulation diagram of the left side portion of the electromagnetic actuator of the high thrust density electromagnetic actuator for the nanosatellite deployer of the invention;
the magnetic field generator comprises a stator frame 1, an outer yoke 2, an outer magnet ring 3, an outer upper magnetic ring 4A, an outer lower magnetic ring 4B, an outer upper magnetic yoke 5, an outer locking nut 6, an inner yoke 7, an inner magnetic ring 8, an inner upper magnetic ring 9A, an inner lower magnetic ring 9B, an inner upper magnetic yoke 10, an inner locking nut 11, an end magnetic yoke 12, a coil skeleton 13 and an annular coil 14.
Detailed Description
The following detailed description of embodiments of the invention is provided in conjunction with the appended drawings:
the first embodiment is as follows: the present embodiment is explained with reference to fig. 1 to 5.
Fig. 1 is a radial cross-sectional view of an electromagnetic actuator according to a technical solution of the present invention, which mainly includes a stator and a mover, and is characterized in that the stator mainly includes: the magnetic field generator comprises a stator frame 1, an outer yoke 2, an outer magnetic ring 3, an outer upper magnetic ring 4A, an outer lower magnetic ring 4B, an outer upper magnetic yoke 5, an outer locknut 6, an inner magnetic yoke 7, an inner magnetic ring 8, an inner upper magnetic ring 9A, an inner lower magnetic ring 9B, an inner upper magnetic yoke 10, an inner locknut 11 and an end magnetic yoke 12; the active cell mainly includes: a bobbin 13 and a loop coil 14; the outer magnet yoke 2 is located on the radial inner side of the outer wall of the groove of the stator frame 1, the outer magnet ring 3 is located at the radial inner center position of the outer magnet yoke 2, the outer upper magnet ring 4A is located at the axial upper end of the outer magnet yoke 2 and the outer magnet ring 3, the outer lower magnet ring 4B is located at the axial lower end of the outer magnet yoke 2 and the outer magnet ring 3, the outer upper magnet yoke 5 is located at the axial upper end of the outer upper magnet ring 4A, the outer locking nut 6 is located at the axial upper end of the outer upper magnet yoke 5, the inner magnet yoke 7 is located on the radial outer side of the inner wall of the groove of the stator frame 1, the inner magnet ring 8 is located on the radial outer side of the inner magnet yoke 7, the inner upper magnet ring 9A is located at the axial upper end of the inner magnet yoke 7 and the inner magnet ring 8, the inner lower magnet ring 9B is located at the axial lower end of the inner magnet yoke 7 and the inner magnet ring 8, the inner upper magnet yoke 10 is located at the axial upper end of the inner locking nut 11 is located at the axial upper magnet yoke 10, the end magnetic yoke 12 is positioned at the axial lower end of the outer lower magnetic ring 4B and the inner lower magnetic ring 9B, the outer yoke 2, the outer magnetic ring 3, the outer upper magnetic ring 4A, the outer lower magnetic ring 4B and the outer upper magnetic yoke 5 are fixedly arranged on the stator frame 1 through threads between the outer locking nut 6 and the stator frame 1, the inner yoke 7, the inner magnetic ring 8, the inner upper magnetic ring 9A, the inner lower magnetic ring 9B, the inner upper magnetic yoke 10 and the end magnetic yoke 12 are fixedly arranged in an annular groove of the stator frame 1 through threads between the inner locking nut 11 and the stator frame 1, an air gap is formed between the outer yoke 2, the outer magnetic ring 3, the outer upper magnetic ring 4A, the outer lower magnetic ring 4B, the outer upper magnetic yoke 5, the radial inner wall of the outer locking nut 6, the inner yoke 7, the inner magnetic ring 8, the inner upper magnetic ring 9A, the inner lower magnetic ring 9B, the inner upper magnetic yoke 10 and the radial outer wall of the inner locking nut 11, the coil skeleton 13 is positioned between the outer yoke 2, the outer magnetic ring 3, the inner upper magnetic ring 4B and the radial inner locking nut 6, The radial inner sides of the outer magnetic ring 3, the outer upper magnetic ring 4A, the outer lower magnetic ring 4B, the outer upper magnetic yoke 5 and the outer lock nut 6 are provided, and the annular coil 14 is surrounded and fixed in a groove of the coil framework 13.
Fig. 2 is a sectional view of a stator of an electromagnetic actuator according to a technical solution of the present invention, the stator mainly including: the magnetic field generator comprises a stator frame 1, an outer yoke 2, an outer magnetic ring 3, an outer upper magnetic ring 4A, an outer lower magnetic ring 4B, an outer upper magnetic yoke 5, an outer locknut 6, an inner magnetic yoke 7, an inner magnetic ring 8, an inner upper magnetic ring 9A, an inner lower magnetic ring 9B, an inner upper magnetic yoke 10, an inner locknut 11 and an end magnetic yoke 12; the outer magnet yoke 2 is located on the radial inner side of the outer wall of the groove of the stator frame 1, the outer magnet ring 3 is located at the radial inner center position of the outer magnet yoke 2, the outer upper magnet ring 4A is located at the axial upper end of the outer magnet yoke 2 and the outer magnet ring 3, the outer lower magnet ring 4B is located at the axial lower end of the outer magnet yoke 2 and the outer magnet ring 3, the outer upper magnet yoke 5 is located at the axial upper end of the outer upper magnet ring 4A, the outer locking nut 6 is located at the axial upper end of the outer upper magnet yoke 5, the inner magnet yoke 7 is located on the radial outer side of the inner wall of the groove of the stator frame 1, the inner magnet ring 8 is located on the radial outer side of the inner magnet yoke 7, the inner upper magnet ring 9A is located at the axial upper end of the inner magnet yoke 7 and the inner magnet ring 8, the inner lower magnet ring 9B is located at the axial lower end of the inner magnet yoke 7 and the inner magnet ring 8, the inner upper magnet yoke 10 is located at the axial upper end of the inner locking nut 11 is located at the axial upper magnet yoke 10, the end magnetic yoke 12 is located at the axial lower end of the outer lower magnetic ring 4B and the inner lower magnetic ring 9B, the outer yoke 2, the outer magnetic ring 3, the outer upper magnetic ring 4A, the outer lower magnetic ring 4B and the outer upper magnetic yoke 5 are fixedly arranged on the stator frame 1 through threads between the outer lock nut 6 and the stator frame 1, the inner yoke 7, the inner magnetic ring 8, the inner upper magnetic ring 9A, the inner lower magnetic ring 9B, the inner upper magnetic yoke 10 and the end magnetic yoke 12 are fixedly arranged in an annular groove of the stator frame 1 through threads between the inner lock nut 11 and the stator frame 1, and air gaps are formed among the radial inner walls of the outer yoke 2, the outer magnetic ring 3, the outer upper magnetic ring 4A, the outer lower magnetic ring 4B, the outer upper magnetic yoke 5 and the outer lock nut 6, the radial outer walls of the inner yoke 7, the inner magnetic ring 8, the inner upper magnetic ring 9A, the inner lower magnetic ring 9B, the inner upper magnetic yoke 10 and the inner lock nut 11.
The outer yoke 2, the outer upper yoke 5, the inner yoke 7, the inner upper yoke 10 and the end part yoke 12 are made of soft magnetic alloy 1J50, and the stator frame 1, the outer lock nut 6 and the inner lock nut 11 are made of super hard aluminum alloy 7A 09. The outer magnetic ring 3, the outer upper magnetic ring 4A, the outer lower magnetic ring 4B, the inner magnetic ring 8, the inner upper magnetic ring 9A and the inner lower magnetic ring 9B are made of cobalt alloy hard magnetic materials, wherein the outer magnetic ring 3 and the inner magnetic ring 8 are magnetized in the radial direction, the outer upper magnetic ring 4A, the outer lower magnetic ring 4B, the inner upper magnetic ring 9A and the inner lower magnetic ring 9B are magnetized in the axial direction, and the magnetizing directions are as follows: the magnetic flux sensor comprises an outer magnetic ring 3, an outer S inner N, an outer upper magnetic ring 4A, an outer S upper N lower N, an outer lower magnetic ring 4B, an inner magnetic ring 8, an inner S outer N, an inner upper magnetic ring 9A, an inner N lower S and an inner lower magnetic ring 9B, an inner S upper N lower N and an inner lower N; the magnetizing direction can also be: the magnetic ring comprises an outer magnetic ring 3, an outer upper magnetic ring 4A, an outer lower magnetic ring 4B, an outer inner magnetic ring 8, an inner upper magnetic ring 9A, an inner lower magnetic ring 9B, an inner magnetic ring, a magnetic. The widths of the outer upper magnetic ring 4A, the outer lower magnetic ring 4B and the outer upper magnetic yoke 5 are the sum of the thicknesses of the outer magnetic yoke 2 and the outer magnetic ring 3, and the widths of the inner upper magnetic ring 9A, the inner lower magnetic ring 9B and the inner upper magnetic yoke 10 are the sum of the thicknesses of the inner magnetic yoke 7 and the inner magnetic ring 8.
Fig. 3 is a three-dimensional schematic diagram of a mover of an electromagnetic actuator according to a technical solution of the present invention, where the mover mainly includes: the coil framework 13 is positioned at the radial inner side of the outer yoke 2, the outer magnetic ring 3, the outer upper magnetic ring 4A, the outer lower magnetic ring 4B, the outer upper magnetic yoke 5 and the outer lock nut 6, and the annular coil 14 surrounds and is fixed in a groove of the coil framework 13.
Fig. 4 is a schematic diagram of a dual permanent magnet branch loop of an electromagnetic actuator according to the technical solution of the present invention, wherein the upper permanent magnet branch loop generated by the present invention is: the upper magnetic flux starts from the N pole of the outer upper magnetic ring 4A, sequentially passes through the upper half part of the outer yoke 2 to reach the S pole of the outer magnetic ring 3, flows out of the N pole of the outer magnetic ring 3, reaches the S pole of the inner magnetic ring 8 through an air gap, flows out of the N pole of the inner magnetic ring 8, reaches the S pole of the inner upper magnetic ring 9A through the inner yoke 7, flows out of the N pole of the inner upper magnetic ring 9A, sequentially passes through the inner upper magnetic yoke 10, the air gap and the outer upper magnetic yoke 5 and returns to the S pole of the outer upper magnetic ring 4A; the lower permanent magnet branch loop generated by the invention is as follows: the lower magnetic flux emanates from the N pole of the outer lower magnetic ring 4B, passes through the lower half of the outer yoke 2 to reach the S pole of the outer magnetic ring 3, flows out of the N pole of the outer magnetic ring 3, passes through the air gap to reach the S pole of the inner magnetic ring 8, flows out of the N pole of the inner magnetic ring 8, passes through the lower half of the inner yoke 7 to reach the S pole of the inner lower magnetic ring 9B, flows out of the N pole of the inner lower magnetic ring 9B, passes through the end yoke 12, and returns to the S pole of the outer lower magnetic ring 4B.
Fig. 5 is a magnetic line simulation diagram of the left part of the electromagnetic actuator according to the technical solution of the present invention, and it is obvious that magnetic fluxes form an upper closed permanent magnetic branch loop and a lower closed permanent magnetic branch loop, so that magnetic flux density saturation of a magnetic yoke is effectively alleviated, the air gap magnetic field strength is increased, the thrust fluctuation can be effectively reduced due to smooth magnetic lines in an air gap region, and the innovation and feasibility of the present invention are verified.
The working principle of the high-thrust-density electromagnetic actuator for the nano-satellite deployer is as follows:
according to the invention, an upper permanent magnet branch circuit and a lower permanent magnet branch circuit are formed in a single-layer magnetic pole structure, so that the shunting of permanent magnet magnetic flux is realized, the magnetic saturation in a magnetic yoke is effectively relieved, the air gap magnetic field intensity is increased, and an electrified coil placed in an air gap generates ampere force so as to push a nano satellite to release.
The generation principle of the upper permanent magnet branch loop is as follows: the upper magnetic flux flows from the N pole of the outer upper magnetic ring 4A, sequentially through the upper half of the outer yoke 2 to the S pole of the outer magnetic ring 3, flows out of the N pole of the outer magnetic ring 3, through the air gap to the S pole of the inner magnetic ring 8, flows out of the N pole of the inner magnetic ring 8, through the inner yoke 7 to the S pole of the inner upper magnetic ring 9A, flows out of the N pole of the inner upper magnetic ring 9A, sequentially through the inner upper magnetic yoke 10, the air gap and the outer upper magnetic yoke 5 to return to the S pole of the outer upper magnetic ring 4A.
The generation principle of the lower permanent magnet branch loop is as follows: the lower magnetic flux emanates from the N pole of the outer lower magnetic ring 4B, passes through the lower half of the outer yoke 2 to reach the S pole of the outer magnetic ring 3, flows out of the N pole of the outer magnetic ring 3, passes through the air gap to reach the S pole of the inner magnetic ring 8, flows out of the N pole of the inner magnetic ring 8, passes through the lower half of the inner yoke 7 to reach the S pole of the inner lower magnetic ring 9B, flows out of the N pole of the inner lower magnetic ring 9B, passes through the end yoke 12, and returns to the S pole of the outer lower magnetic ring 4B.
The above-mentioned embodiments further explain the objects, technical solutions and advantages of the present invention in detail. It should be understood that the above-mentioned embodiments are only examples of the present invention, and are not intended to limit the present invention, and that the reasonable combination of the features described in the above-mentioned embodiments can be made, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (4)

1. A high-thrust-density electromagnetic actuator for a nano-satellite deployer is characterized by comprising a stator and a rotor, wherein the stator comprises a stator frame (1), an outer yoke (2), an outer magnetic ring (3), an outer upper magnetic ring (4A), an outer lower magnetic ring (4B), an outer upper magnetic yoke (5), an outer lock nut (6), an inner yoke (7), an inner magnetic ring (8), an inner upper magnetic ring (9A), an inner lower magnetic ring (9B), an inner upper magnetic yoke (10), an inner lock nut (11) and an end magnetic yoke (12); the rotor comprises a coil framework (13) and an annular coil (14);
the outer magnet yoke (2) is located on the radial inner side of the outer wall of the groove of the stator frame (1), the outer magnet ring (3) is located on the radial inner center position of the outer magnet yoke (2), the outer upper magnet ring (4A) is located at the upper ends of the outer magnet yoke (2) and the outer magnet ring (3), the outer lower magnet ring (4B) is located at the lower ends of the outer magnet yoke (2) and the outer magnet ring (3), the outer upper magnet yoke (5) is located at the upper end of the outer upper magnet ring (4A), the outer lock nut (6) is located at the upper end of the outer upper magnet yoke (5), the inner magnet yoke (7) is located on the radial outer side of the inner wall of the groove of the stator frame (1), the inner magnet ring (8) is located on the radial outer side of the inner magnet yoke (7), the inner upper magnet ring (9A) is located at the upper ends of the inner magnet yoke (7) and the inner magnet ring (8), and the inner lower magnet ring (9B) is located at the lower ends of the inner magnet yoke (7) and the inner magnet ring (8), the inner upper magnetic yoke (10) is positioned at the upper end of the inner upper magnetic ring (9A), the inner lock nut (11) is positioned at the upper end of the inner upper magnetic yoke (10), the end magnetic yoke (12) is positioned at the lower ends of the outer lower magnetic ring (4B) and the inner lower magnetic ring (9B), the outer magnetic yoke (2), the outer magnetic ring (3), the outer upper magnetic ring (4A), the outer lower magnetic ring (4B) and the outer upper magnetic yoke (5) are fixedly arranged on the stator frame (1) through threads between the outer lock nut (6) and the stator frame (1), the inner magnetic yoke (7), the inner magnetic ring (8), the inner upper magnetic ring (9A), the inner lower magnetic ring (9B), the inner upper magnetic yoke (10) and the end magnetic yoke (12) are fixedly arranged in an annular groove of the stator frame (1) through threads between the inner lock nut (11) and the stator frame (1), the outer magnetic yoke (2), the outer magnetic ring (3), the outer upper magnetic ring (4A) and the outer lower magnetic ring (9A), An air gap is formed between the radial inner wall of the outer lower magnetic ring (4B), the outer upper magnetic yoke (5), the outer lock nut (6) and the radial outer wall of the inner magnetic yoke (7), the inner magnetic ring (8), the inner upper magnetic ring (9A), the inner lower magnetic ring (9B), the inner upper magnetic yoke (10) and the inner lock nut (11), the coil framework (13) is positioned at the radial inner side of the outer magnetic yoke (2), the outer magnetic ring (3), the outer upper magnetic ring (4A), the outer lower magnetic ring (4B), the outer upper magnetic yoke (5) and the outer lock nut (6), and the annular coil (14) is surrounded and fixed in a groove of the coil framework (13);
the widths of the outer upper magnetic ring (4A), the outer lower magnetic ring (4B) and the outer upper magnetic yoke (5) are the sum of the thicknesses of the outer magnetic yoke (2) and the outer magnetic ring (3), and the widths of the inner upper magnetic ring (9A), the inner lower magnetic ring (9B) and the inner upper magnetic yoke (10) are the sum of the thicknesses of the inner magnetic yoke (7) and the inner magnetic ring (8).
2. The high thrust density electromagnetic actuator for a nanostar deployer of claim 1, wherein the outer magnetic ring (3), the outer upper magnetic ring (4A), the outer lower magnetic ring (4B), the inner magnetic ring (8), the inner upper magnetic ring (9A), and the inner lower magnetic ring (9B) are all cobalt alloy hard magnetic materials, wherein the outer magnetic ring (3) and the inner magnetic ring (8) are magnetized radially, the outer upper magnetic ring (4A), the outer lower magnetic ring (4B), the inner upper magnetic ring (9A), and the inner lower magnetic ring (9B) are magnetized axially, and the magnetization directions are S in the outer S inner N of the outer magnetic ring (3), the outer upper S lower N of the outer upper magnetic ring (4A), the outer N lower S of the outer lower magnetic ring (4B), the outer S inner N of the inner upper magnetic ring (8), the inner upper N lower S of the inner upper magnetic ring (9A), and the inner lower S of the inner lower magnetic ring (9B).
3. The high thrust density electromagnetic actuator for a nanostar deployer of claim 1, wherein the outer magnetic ring (3), the outer upper magnetic ring (4A), the outer lower magnetic ring (4B), the inner magnetic ring (8), the inner upper magnetic ring (9A) and the inner lower magnetic ring (9B) are all cobalt-coated hard magnetic material, wherein the outer magnetic ring (3) and the inner magnetic ring (8) are radially magnetized, the outer upper magnetic ring (4A), the outer lower magnetic ring (4B), the inner upper magnetic ring (9A) and the inner lower magnetic ring (9B) are axially magnetized, and the magnetization directions are N inner S outside the outer magnetic ring (3), N lower S above the outer upper magnetic ring (4A), S lower N above the outer lower magnetic ring (4B), N inner S outside the inner magnetic ring (8), S lower N above the inner upper magnetic ring (9A) and S above the inner lower magnetic ring (9B).
4. The high thrust density electromagnetic actuator for a nanostar deployer of claim 1, wherein the outer yoke (2), the outer upper yoke (5), the inner yoke (7), the inner upper yoke (10) and the end yoke (12) are soft magnetic alloy 1J50 material.
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