Locking device of aircraft

Abstract

The utility model discloses a locking device of an aircraft. The locking device comprises a mounting frame, a first mounting seat and a second mounting seat, the utility model has the beneficial effects that the magnetic block and the electromagnet are adopted, when unlocking is needed, the electromagnet is electrified to generate a magnetic pole opposite to the magnetic block, under the action of attraction of the opposite poles, the magnetic force overcomes the elastic force of the spring, the spring is compressed, the magnetic block gets close to the mounting box by virtue of the magnetic force and is adsorbed and fixed with the mounting box, and the locking pin is pulled to retract for unlocking, so that quick unlocking is completed; the problem that a traditional device is low in fusing speed is solved, the unlocking speed and the working efficiency are improved, when the locking state needs to be restored, the electromagnet can generate a magnetic pole with the same polarity as the magnetic block only by changing the direction of current input into the electromagnet, the magnetic block is spread out to exceed the magnetic force range of the magnetic force and the iron plate under the effect of like-pole repulsion, and meanwhile the magnetic block is not prone to being broken. And when the spring is reset, the locking pin can be quickly reset, so that the trouble of replacing parts is avoided, the repeated use is convenient and simple, and the use convenience is remarkably improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft equipment, and more specifically, to a locking device for an aircraft. Background Technique

[0002] Locking and unlocking devices are required for equipment such as aircraft, missiles, and underwater equipment. For example, for drone express delivery, parachute cutting protection, deep-sea test equipment delivery, and unlocking of mechanisms for deep-sea cableless samplers.

[0003] After retrieval, it is found that the application number is CN202023059779.4, and the name is a locking and unlocking device for an aircraft. This application points out that currently, most locking and unlocking devices are pyrotechnic devices, such as pyrotechnic pin pullers. Although they can meet the basic requirements of separation and unlocking, they have disadvantages such as being flammable, explosive, and having a large impact, and can only be used once, so their application is greatly limited. By using a non-pyrotechnic pin puller without impact, through the design of the structure and drive circuit, the fusible tension rope can be electrically melted, the unlocking time can be precisely controlled, and there is no impact during the unlocking process. The pin puller can be recycled and reused, with a wide application range and strong practicability. However, when this application is used, the tension rope needs to be frequently replaced, which is rather troublesome. At the same time, the melting time of the tension rope is long, the reaction is not fast and sensitive enough, affecting the work efficiency, and further improvements can be made.

[0004] Regarding the problems in the related technology, no effective solution has been proposed yet. Content of the Utility Model

[0005] (I) Technical Problems to be Solved

[0006] In view of the deficiencies of the prior art, the utility model provides a locking device for an aircraft, which has the advantages of high work efficiency and more convenient use, thereby solving the problems in the above background technique.

[0007] (II) Technical Solutions

[0008] To achieve the above advantages of high work efficiency and more convenient use, the specific technical solutions adopted by the utility model are as follows:

[0009] A locking device for an aircraft, comprising a mounting frame, a first mounting seat, and a second mounting seat. The top surface of the mounting frame is fixedly provided with the first mounting seat and the second mounting seat. A locking pin penetrates through the surfaces of the first mounting seat and the second mounting seat. One end of the locking pin is connected to a magnetic block through an end plate. On the other side of the magnetic block, a mounting box is fixedly installed on the top surface of the mounting frame. An electromagnet is fixedly installed inside the mounting box. A collar is fixedly sleeved on the outer surface of the locking pin between the first mounting seat and the second mounting seat. A spring is sleeved on the outer side of the locking pin between the collar and the second mounting seat.

[0010] Further, the input end of the electromagnet is electrically connected to the output end of the control switch through a current commutator, and the output end of the electromagnet faces the magnetic block.

[0011] Further, one side surface of the installation box is fixedly embedded with an iron plate, and the iron plate is attached to the surface of the output end of the electromagnet.

[0012] Further, a connecting plate is fixedly installed on the other side surface of the installation box, and the connecting plate is fixedly connected to the installation frame through a fixing screw.

[0013] Further, mounting holes are penetrated through the corners of the surface of the installation frame, and multiple groups of mounting holes are arranged.

[0014] Further, both ends of the spring are fixedly connected to the surface of the collar and one side of the second mounting seat respectively.

[0015] Further, the maximum elastic force of the spring is less than the magnetic force when the magnetic block is attached to the iron plate.

[0016] Further, the magnetic force of the electromagnet after being energized is greater than the elastic force of the spring.

[0017] (III) Beneficial effects

[0018] Compared with the prior art, the present utility model provides a locking device for an aircraft, which has the following beneficial effects:

[0019] (1) The present utility model adopts a magnetic block and an electromagnet. In the daily locking situation, the locking pin is in the extended and locked state. When unlocking is required, the electromagnet is energized to generate a magnetic pole opposite to that of the magnetic block. Under the action of opposite-sex attraction, the magnetic force overcomes the elastic force of the spring, the spring is compressed, the magnetic block approaches and adsorbs and fixes to the installation box by the magnetic force, and the locking pin is pulled back to unlock, completing rapid unlocking, solving the problem of slow fusing speed of traditional equipment, and improving the unlocking speed and working efficiency.

[0020] (2) The present utility model adopts an electromagnet. When the locked state needs to be restored, only the direction of the current input to the electromagnet needs to be changed, and the electromagnet can generate a magnetic pole same as that of the magnetic block. Under the action of same-sex repulsion, the magnetic block is spread out beyond the magnetic force range between the magnetic force and the iron plate. At the same time, the spring resets, and the locking pin can be quickly reset, avoiding the trouble of replacing parts, being convenient and simple for repeated use, and significantly improving the convenience of use. Brief description of the drawings

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0022] Figure 1 is a schematic external structure diagram of a locking device for an aircraft proposed by the present invention;

[0023] Figure 2 is a schematic internal structure diagram of a locking device for an aircraft proposed by the present invention;

[0024] Figure 3 is a schematic structure diagram of an installation box proposed by the present invention;

[0025] Figure 4 is a schematic structure diagram of a locking pin proposed by the present invention.

[0026] In the figure:

[0027] 1, mounting bracket; 2, first mounting seat; 3, second mounting seat; 4, end plate; 5, magnetic block; 6, installation box; 7, electromagnet; 8, iron plate; 9, connecting plate; 10, fixing screw; 11, collar; 12, spring; 13, locking pin; 14, mounting hole. Detailed implementation manners

[0028] To further illustrate the embodiments, the present invention provides drawings. These drawings are part of the disclosure of the present invention. They are mainly used to illustrate the embodiments and can be used in conjunction with the relevant descriptions in the specification to explain the operating principles of the embodiments. With reference to these contents, those of ordinary skill in the art should be able to understand other possible implementation manners and the advantages of the present invention. The components in the figures are not drawn to scale, and similar component symbols are usually used to represent similar components.

[0029] According to an embodiment of the present invention, a locking device for an aircraft is provided.

[0030] Now, the present invention will be further described in conjunction with the drawings and specific implementation manners. As Figures 1-4As shown in the figure, a locking device for an aircraft according to an embodiment of the present invention includes a mounting frame 1, a first mounting seat 2, and a second mounting seat 3. The top surface of the mounting frame 1 is fixedly provided with the first mounting seat 2 and the second mounting seat 3. A locking pin 13 penetrates through the surfaces of the first mounting seat 2 and the second mounting seat 3. The locking pin 13 is slidably connected to the first mounting seat 2 and the second mounting seat 3. One end of the locking pin 13 is connected to a magnetic block 5 through an end plate 4. On the other side of the magnetic block 5, a mounting box 6 is fixedly installed on the top surface of the mounting frame 1. An electromagnet 7 is fixedly installed inside the mounting box 6. A collar 11 is fixedly sleeved on the outer surface of the locking pin 13 between the first mounting seat 2 and the second mounting seat 3. A spring 12 is sleeved outside the locking pin 13 between the collar 11 and the second mounting seat 3. The two ends of the spring 12 are respectively fixedly connected to the collar 11 and one side surface of the second mounting seat 3. In the daily locking situation, the locking pin 13 is in an extended and locked state. When unlocking is required, an electric current is passed through the electromagnet 7 to generate a magnetic pole opposite to that of the magnetic block 5. Under the action of opposite-sex attraction, the magnetic force overcomes the elastic force of the spring 12, the spring 12 compresses, and the magnetic block 5 approaches and is adsorbed and fixed to the mounting box 6 by the magnetic force. The locking pin 13 is pulled back to unlock, completing rapid unlocking, solving the problem of slow fusing speed of traditional equipment, and improving the unlocking speed and work efficiency.

[0031] In one embodiment, the input end of the electromagnet 7 is electrically connected to the output end of the control switch through a current commutator, which is convenient for the staff to switch the direction of the current input to the electromagnet 7. The output end of the electromagnet 7 faces the magnetic block 5. When the locking state needs to be restored, only by changing the direction of the current input to the electromagnet 7, the electromagnet 7 can generate a magnetic pole of the same sex as the magnetic block 5. Under the action of same-sex repulsion, the magnetic block 5 is spread out beyond the magnetic force range of the magnetic force and the iron plate 8. At the same time, the spring 12 resets, and the locking pin 13 can be quickly reset, avoiding the trouble of replacing parts, being convenient and simple to reuse, and significantly improving the convenience of use.

[0032] In one embodiment, an iron plate 8 is fixedly embedded in one side surface of the mounting box 6, and the iron plate 8 is attached to the surface of the output end of the electromagnet 7. The iron plate 8 is convenient for conducting magnetic force. At the same time, after the magnetic block 5 is attached to the iron plate 8, the generated magnetic force overcomes the elastic force of the spring 12, and the electromagnet 7 can be powered off to avoid power consumption.

[0033] In one embodiment, a connecting plate 9 is fixedly installed on the other side surface of the mounting box 6, and the connecting plate 9 is fixedly connected to the mounting frame 1 through a fixing screw 10, which is a common installation and fixing structure and will not be elaborated here.

[0034] In one embodiment, mounting holes 14 are penetrated through the corners of the surface of the mounting frame 1, and multiple groups of mounting holes 14 are arranged, which is convenient for the fixed installation of the mounting frame 1.

[0035] In one embodiment, the maximum elastic force of the spring 12 is less than the magnetic force when the magnetic block 5 is in contact with the iron plate 8. Among them, after the electromagnet 7 is energized, the magnetic force is greater than the elastic force of the spring 12, which facilitates the electromagnet 7 to overcome the elastic force and attract the magnetic block 5.

[0036] Working principle:

[0037] In the daily locked state, the locking pin 13 is in the extended and locked state. When unlocking is required, an electric current is passed through the electromagnet 7 to generate a magnetic pole opposite to that of the magnetic block 5. Under the action of opposite-sex attraction, the magnetic force overcomes the elastic force of the spring 12, the spring 12 is compressed, and the magnetic block 5 approaches and is adsorbed and fixed to the installation box 6 by the magnetic force, pulling the locking pin 13 to retract and unlock, completing rapid unlocking, solving the problem of slow fusing speed of traditional equipment, improving the unlocking speed and working efficiency. At the same time, when the locked state needs to be restored, only the direction of the current input to the electromagnet 7 needs to be changed, and the electromagnet 7 can generate a magnetic pole the same as that of the magnetic block 5. Under the action of same-sex repulsion, the magnetic block 5 is spread out beyond the magnetic force range between the magnetic force and the iron plate 8. At the same time, the spring 12 is reset, and the locking pin 13 can be quickly reset, avoiding the trouble of replacing parts, being convenient and simple to reuse, and significantly improving the convenience of use.

[0038] In the present utility model, unless otherwise clearly specified and defined, terms such as "installation", "setting", "connection", "fixation", "swivel connection", etc. shall be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two components or the interaction relationship between two components. Unless otherwise clearly defined, for those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0039] The above are only the preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A locking device for an aircraft, characterized in that: The invention comprises a mounting frame (1), a first mounting seat (2) and a second mounting seat (3); the first mounting seat (2) and the second mounting seat (3) are fixedly mounted on the top surface of the mounting frame (1); a locking pin (13) is connected through the surfaces of the first mounting seat (2) and the second mounting seat (3); one end of the locking pin (13) is connected to a magnetic block (5) through an end plate (4); a mounting box (6) is fixedly mounted on the other side of the magnetic block (5) on the top surface of the mounting frame (1); an electromagnet (7) is fixedly mounted inside the mounting box (6); a collar (11) is fixedly sleeved on the outer surface of the locking pin (13) between the first mounting seat (2) and the second mounting seat (3); and a spring (12) is sleeved on the outer side of the locking pin (13) between the collar (11) and the second mounting seat (3).

2. The locking device of an aircraft according to claim 1, characterized in that: The input end of the electromagnet (7) is electrically connected to the output end of the control switch via a current commutator, and the output end of the electromagnet (7) faces the magnetic block (5).

3. The locking device of an aircraft according to claim 1, characterized in that: An iron plate (8) is fixedly embedded in a surface of one side of the installation box (6), and the iron plate (8) is in contact with the surface of the output end of the electromagnet (7).

4. The locking device of an aircraft according to claim 1, characterized in that: A connecting plate (9) is fixedly mounted on the other side surface of the installation box (6), and the connecting plate (9) is fixedly connected to the installation frame (1) via fixing screws (10).

5. The locking device of an aircraft according to claim 1, characterized in that: The mounting frame (1) has mounting holes (14) extending through the corners of the surface thereof, and the mounting holes (14) are arranged in a plurality of groups.

6. The locking device of an aircraft according to claim 1, characterized in that: The two ends of the spring (12) are respectively fixedly connected to the collar (11) and a surface of one side of the second mounting seat (3).

7. The locking device of an aircraft according to claim 1, characterized in that: The maximum elastic force of the spring (12) is smaller than the magnetic force when the magnetic block (5) and the iron plate (8) are in contact with each other.

8. The locking device of an aircraft according to claim 1, characterized in that: When the electromagnet (7) is energized, the magnetic force is greater than the elastic force of the spring (12).

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