CN109911254B - Contact type locker applied to magnetic attraction principle of space equipment - Google Patents
Contact type locker applied to magnetic attraction principle of space equipment Download PDFInfo
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- CN109911254B CN109911254B CN201910233908.XA CN201910233908A CN109911254B CN 109911254 B CN109911254 B CN 109911254B CN 201910233908 A CN201910233908 A CN 201910233908A CN 109911254 B CN109911254 B CN 109911254B
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Abstract
A contact type locker applied to a magnetic attraction principle of space equipment belongs to the technical field of space equipment. The invention relates to a contact type locker which can realize reliable locking and quick unlocking and is applied to the magnetic attraction principle of space equipment. The inner side of a magnetism isolating ring is tightly sleeved with annular magnetic steel and an annular magnetic conduction base from top to bottom, the inner side of the annular magnetic steel is tightly sleeved with an annular concave aluminum groove, the annular concave aluminum groove is arranged on the annular magnetic conduction base, the middle part of the annular concave aluminum groove is arranged in a suspended mode, the inner ring surface of the annular concave aluminum groove is formed by an inverted circular truncated cone-shaped inner ring surface and a cylindrical inner ring surface from top to bottom, a positioning rod is made of a magnetic conduction material and is formed by a cylinder and an inverted circular truncated cone body from top to bottom; when the locking device is locked, the circular truncated cone body of the positioning rod is matched with the inner annular surface of the circular truncated cone of the annular concave aluminum groove. The invention is suitable for the contact type position locking of space equipment adopting a magnetic attraction structure.
Description
Technical Field
The invention relates to a locker for space equipment, and belongs to the technical field of space equipment.
Background
Due to the limitation of installation space, a spacecraft has a plurality of devices, and the service life and the working cycle of each device are different. The non-operating mode devices need to be maintained in a dormant, folded state, and the moving parts of the devices need to be locked to avoid interference with other normally operating devices due to their free movement. In the working mode, the unlocking operation is required. As a result, locks of some specific function are often required on aircraft. The operating environment of the spacecraft determines that such locks must meet several special requirements:
(1) small volume and light weight. Due to space constraints, the lock should be as simple as possible and its locking and unlocking process should not cause large attitude changes of the device.
(2) The work is power-saving. Because the power supply battery of the aerospace equipment has limited electric quantity and needs to be preferentially supplied to the operation control equipment and the life support equipment, the lockers in the common modes of electrified coils or electromagnets and the like on the ground equipment are not suitable for the aerospace working condition.
(3) The operation is simple and the work is reliable. The safety requirement of the aerospace device is high, the locking device is required to have the characteristic of reliable work, and the locking performance cannot be lost due to environmental interference and long-time work.
(4) The locking force is not great. Because the space device works in the space weightless environment and does not have particularly large posture change generally, the locking force does not need to be large and is generally not more than a few newtons.
None of the prior art and existing products meets the above requirements.
Disclosure of Invention
The invention aims to design a contact type locker based on a magnetic attraction principle, capable of realizing reliable locking and quick unlocking and applied to a magnetic attraction principle of space equipment by adopting a special structure and magnetic circuit design, and meeting special equipment locking requirements of a space environment in structure and performance.
1. The invention is suitable for the contact type position locker for space equipment adopting a magnetic attraction structure.
2. One of the key technologies of the invention is the design of a positioning rod connected with aerospace equipment. The positioning rod is made of a magnetic conductive material, and the position of the equipment is locked through the magnetic attraction effect of the locking device on the positioning rod.
3. The second key technology of the invention is that the lock adopts the design scheme of annular magnetic steel, the positioning rod is attracted by magnetic force when sliding in the annular concave aluminum groove, and enough locking force is ensured in the locking process.
4. The key technology of the invention is that the annular magnetic steel of the locking device is arranged on the annular magnetic conduction base, the core function of the locking device is to limit the direction of a magnetic circuit, and an axial magnetic field which interacts with the positioning rod is formed in the annular magnetic steel.
5. The fourth key technology of the invention is that the inner side of the locking device adopts an annular concave aluminum groove with a special structure, and the inner side surface of the annular concave aluminum groove adopts an inclined plane design. The core effect of the device is to limit the magnetic circuit direction and the position of the positioning rod, so that the positioning rod can slide and unlock under the action of transverse force, and the device is suitable for various motion modes.
The technical scheme adopted by the invention is as follows:
a contact type locker applied to the magnetic attraction principle of space equipment comprises a positioning rod, an annular concave aluminum groove, annular magnetic steel, a magnetism isolating ring and an annular magnetic conduction base; the inner side of the magnetism isolating ring is tightly sleeved with annular magnetic steel and an annular magnetic conduction base from top to bottom, the inner side of the annular magnetic steel is tightly sleeved with an annular concave aluminum groove, the annular concave aluminum groove is arranged on the annular magnetic conduction base, the inner annular surface of the annular concave aluminum groove is formed by an inverted circular truncated cone-shaped inner annular surface and a cylindrical inner annular surface from top to bottom, the positioning rod is made of a magnetic conduction material, and the positioning rod is formed by a cylinder and an inverted circular truncated cone body from top to bottom; when the locking device is locked, the circular truncated cone body of the positioning rod is matched with the inner annular surface of the circular truncated cone of the annular concave aluminum groove.
The invention has the beneficial effects that: the invention provides a magnetic attraction principle-based contact type position locking device for space equipment, which does not need to be electrified and consume energy, realizes the locking and unlocking of a positioning rod connected with the equipment through the special design of annular magnetic steel, an annular magnetic conduction base and an annular concave aluminum groove, has the advantages of simple operation and reliable work, and can meet the locking requirement of the space equipment.
Drawings
FIG. 1 is a schematic diagram of a magnetic attraction type touch lock for a space apparatus according to the present invention;
FIG. 2 is a schematic structural diagram of a positioning rod of a magnetic attraction type locking device applied to a space equipment according to the present invention entering a locking area;
FIG. 3 is a schematic diagram of a magnetic attraction type touch lock applied to a space equipment according to the present invention, which applies an upward unlocking force to a positioning rod to overcome a locking force;
FIG. 4 is a schematic diagram of a magnetic attraction type locking mechanism for a space apparatus according to the present invention, which is used to apply a lateral unlocking force to a positioning rod to overcome the resistance of the positioning rod.
The names and the reference numbers of the parts related in the figure are as follows:
the device comprises a positioning rod 1, a cylinder 1-1, a truncated cone 1-2, an annular concave aluminum groove 2, a truncated cone annular inner ring surface 2-1, a cylindrical inner ring surface 2-2, annular magnetic steel 3, a magnetism isolating ring 4 and an annular magnetic conduction base 5.
Detailed Description
The first embodiment is as follows: as shown in fig. 1 and fig. 2, the present embodiment describes a contact type locking device applied to the magnetic attraction principle of space equipment, which includes a positioning rod 1, an annular concave aluminum groove 2, an annular magnetic steel 3, a magnetism isolating ring 4 (the magnetism isolating ring 4 is made of a non-magnetic material), and an annular magnetic base 5; the inner side of the magnetism isolating ring 4 is tightly sleeved with an annular magnetic steel 3 and an annular magnetic conduction base 5 from top to bottom, the inner side of the annular magnetic steel 3 is tightly sleeved with an annular concave aluminum groove 2, the annular concave aluminum groove 2 is arranged on the annular magnetic conduction base 5, the inner annular surface of the annular concave aluminum groove 2 is composed of an inverted circular truncated cone-shaped inner annular surface 2-1 and a cylindrical inner annular surface 2-2 from top to bottom, the positioning rod 1 is made of a magnetic conduction material, and the positioning rod 1 is composed of a cylinder 1-1 and an inverted circular truncated cone body 1-2 from top to bottom; when the locking device is locked, the round table body 1-1 of the positioning rod 1 is matched with the circular table inner annular surface 2-1 of the annular concave aluminum groove 2. The diameter of the cylindrical inner ring surface 2-2 of the annular concave aluminum groove 2 is equal to the diameter of the inner ring surface of the annular magnetic conduction base 5, or the diameter of the cylindrical inner ring surface 2-2 of the annular concave aluminum groove 2 is smaller than the diameter of the inner ring surface of the annular magnetic conduction base 5.
When the lock is in use, the securing lever 1 is connected to the device to be locked.
The second embodiment is as follows: as shown in fig. 1 to 4, in this embodiment, a first specific embodiment is further described, the annular magnetic steel 3 is axially magnetized, and the magnetizing direction is in an up-down direction (the upper end of the annular magnetic steel 3 is an N pole, and the lower end is an S pole).
The third concrete implementation mode: as shown in fig. 1 to 4, this embodiment is further described with respect to the first or second embodiment, a diameter of a cylinder 1-1 of the positioning rod 1 is 9mm, and a diameter of a lower end surface of the truncated cone 1-2 of the positioning rod 1 is 3 mm; the diameter of the outer ring surface of the magnetism isolating ring 4 is 28mm, the diameter of the inner ring surface of the magnetism isolating ring 4 is 18mm, and the height of the magnetism isolating ring 4 is 7 mm; the diameter of the inner ring surface of the annular magnetic steel 3 is 10mm, and the height of the annular magnetic steel 3 is 3 mm; the diameter of the inner ring surface of the annular magnetic conduction base 5 is 6mm, and the height of the annular magnetic conduction base 5 is 4 mm; the diameter of the bottom of the circular truncated cone-shaped inner annular surface 2-1 of the annular concave aluminum groove 2 is 3mm, and the oblique angle (namely the included angle between the circular truncated cone-shaped inner annular surface 2-1 and the axis of the annular concave aluminum groove 2) of the circular truncated cone-shaped inner annular surface 2-1 of the annular concave aluminum groove 2 is 45 degrees. And finally, the locking force of the locking position obtained by design is 3.2N, which is higher than 2N required by design, and the design requirement is met.
The working principle is as follows: as shown in figure 1, in the invention, a positioning rod 1 is made of a magnetic conductive material, a magnetism isolating ring 4 made of a non-magnetic conductive material is arranged outside an annular magnetic steel 3, and a magnetism isolating annular concave aluminum groove 2 is adopted inside the annular magnetic steel 3. One of the functions of the annular concave aluminum groove 2 is to limit the position of the positioning rod 1, and in the process that the positioning rod 1 moves downwards, the magnetic resistance is continuously reduced, and the locking force is gradually increased. The position now devised will ensure that the locking force is almost maximal at the locking position. The annular concave aluminum groove 2 has the second function of facilitating locking and unlocking operations. When locking is required, as shown in fig. 2, as long as the positioning rod 1 enters the corresponding locking area, the required locking position can be automatically reached under the action of the locking force. When unlocking is needed, as long as an upward unlocking force is applied to the positioning rod 1 to overcome the locking force, as shown in fig. 3, or a transverse unlocking force is applied to the positioning rod 1 to overcome the resistance force of the movement of the positioning rod 1, as shown in fig. 4, the positioning rod 1 can be separated from the locker, and position unlocking is achieved.
Claims (3)
1. The utility model provides a be applied to contact locker of principle is inhaled to magnetism of space equipment which characterized in that: comprises a positioning rod (1), an annular concave aluminum groove (2), annular magnetic steel (3), a magnetism isolating ring (4) and an annular magnetic conduction base (5); the inner side of the magnetism isolating ring (4) is tightly sleeved with an annular magnetic steel (3) and an annular magnetic conduction base (5) from top to bottom, the inner side of the annular magnetic steel (3) is tightly sleeved with an annular concave aluminum groove (2), the annular concave aluminum groove (2) is arranged on the annular magnetic conduction base (5), the inner ring surface of the annular concave aluminum groove (2) is formed by an inverted circular truncated cone-shaped inner ring surface (2-1) and a cylindrical inner ring surface (2-2) from top to bottom, the positioning rod (1) is made of a magnetic conduction material, and the positioning rod (1) is formed by a cylinder (1-1) and an inverted circular truncated cone body (1-2) from top to bottom; when the locking device is locked, the round table body (1-2) of the positioning rod (1) is matched with the circular inner annular surface (2-1) of the round table of the annular concave aluminum groove (2).
2. A magnetic attraction type touch lock device according to claim 1, wherein the magnetic attraction type touch lock device further comprises: the annular magnetic steel (3) is axially magnetized, and the magnetizing direction is in the up-and-down direction.
3. A touch-lock according to claim 1 or 2, applied to the magnetic attraction principle of space devices, characterized in that: the diameter of a cylinder (1-1) of the positioning rod (1) is 9mm, and the diameter of the lower end face of the round table body (1-2) of the positioning rod (1) is 3 mm; the diameter of the outer ring surface of the magnetism isolating ring (4) is 28mm, the diameter of the inner ring surface of the magnetism isolating ring (4) is 18mm, and the height of the magnetism isolating ring (4) is 7 mm; the diameter of the inner ring surface of the annular magnetic steel (3) is 10mm, and the height of the annular magnetic steel (3) is 3 mm; the diameter of the inner ring surface of the annular magnetic conduction base (5) is 6mm, and the height of the annular magnetic conduction base (5) is 4 mm; the diameter of the bottom of the circular truncated cone-shaped inner annular surface (2-1) of the annular concave aluminum groove (2) is 3mm, and the oblique angle of the circular truncated cone-shaped inner annular surface (2-1) of the annular concave aluminum groove (2) is 45 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910233908.XA CN109911254B (en) | 2019-03-26 | 2019-03-26 | Contact type locker applied to magnetic attraction principle of space equipment |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910233908.XA CN109911254B (en) | 2019-03-26 | 2019-03-26 | Contact type locker applied to magnetic attraction principle of space equipment |
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| CN109911254A CN109911254A (en) | 2019-06-21 |
| CN109911254B true CN109911254B (en) | 2021-07-13 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6047726B2 (en) * | 1983-06-06 | 1985-10-23 | 株式会社マグリ−ダ | Engagement tool |
| CN1063176A (en) * | 1990-12-28 | 1992-07-29 | 株式会社应用技术研究所 | Magnetic lock device |
| CN104097792A (en) * | 2014-07-29 | 2014-10-15 | 北京卫星环境工程研究所 | Electromagnetic unlocking structure for in-orbit unfolding operation of spacecraft detection device mechanism |
| CN105217057A (en) * | 2015-09-17 | 2016-01-06 | 中国空间技术研究院 | A kind of based on rope system docking star between energy transform device |
| CN109466808A (en) * | 2018-12-14 | 2019-03-15 | 哈尔滨工业大学 | A kind of electromagnetism docking facilities and method based on linear motor |
-
2019
- 2019-03-26 CN CN201910233908.XA patent/CN109911254B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6047726B2 (en) * | 1983-06-06 | 1985-10-23 | 株式会社マグリ−ダ | Engagement tool |
| CN1063176A (en) * | 1990-12-28 | 1992-07-29 | 株式会社应用技术研究所 | Magnetic lock device |
| CN104097792A (en) * | 2014-07-29 | 2014-10-15 | 北京卫星环境工程研究所 | Electromagnetic unlocking structure for in-orbit unfolding operation of spacecraft detection device mechanism |
| CN105217057A (en) * | 2015-09-17 | 2016-01-06 | 中国空间技术研究院 | A kind of based on rope system docking star between energy transform device |
| CN109466808A (en) * | 2018-12-14 | 2019-03-15 | 哈尔滨工业大学 | A kind of electromagnetism docking facilities and method based on linear motor |
Non-Patent Citations (1)
| Title |
|---|
| 一种小型锁销式锁制器的设计;廖庆文,殷唯凯,陈强;《电机控制与应用》;20180810;第45卷(第8期);全文 * |
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Inventor after: Li Yong Inventor after: Hu Jianhui Inventor after: Wang Jian Inventor after: Liu Chengjun Inventor after: Wang Baochao Inventor after: Sun Jianfei Inventor after: Zhao Meng Inventor after: Ma Jing Inventor after: Tan Liying Inventor before: Wang Baochao Inventor before: Li Yong Inventor before: Sun Jianfei Inventor before: Zhao Meng Inventor before: Wang Jian Inventor before: Hu Jianhui Inventor before: Ma Jing Inventor before: Tan Liying |
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