Target drone electromagnetic ejection boosting device

Abstract

The invention provides a target aircraft electromagnetic catapulting boosting device, and relates to the field of electromagnetic catapulting, the target aircraft electromagnetic catapulting boosting device comprises a track platform, an electromagnetic catapulting track is embedded in the middle of the track platform, an acceleration block is arranged in the middle of the electromagnetic catapulting track, a connecting unit is arranged above the acceleration block, and the connecting unit is connected with a target aircraft. The connecting unit is provided with an active separating mechanism controlled by the speed of the target drone, the connecting unit comprises a clamping sleeve fixedly connected with the target drone, an inserting groove is formed in the side, away from a machine head of the target drone, of the clamping sleeve, an inserting block is inserted into the inserting groove, and the inserting block and the clamping sleeve are in threaded connection through a threaded shaft with the bottom end arranged upwards. According to the target aircraft electromagnetic ejection boosting device, through the arrangement of the active separation mechanism controlled by the speed of the target aircraft, compared with the arrangement of a blocking mechanism or a constant tension breaking mechanism at the tail end of the track, the launching opportunity of the target aircraft and the ejection track can be accurately controlled through the arrangement.

Description

Technical Field

[0001] The present invention relates to the field of electromagnetic catapults, and specifically to an electromagnetic catapult booster device for target drones. Background Art

[0002] When a drone takes off by catapult, it is necessary to connect the aircraft restraint rod and the catapult rod to the catapult restraint device and the catapult shuttle respectively. The restraint rod is hinged to the upper and lower torsion arm hinge points of the nose landing gear through a fixed-force break-off bolt. During the tensioning stage, the catapult starts to load, and the aircraft is tensioned. When the restraint rod reaches the release load, the fixed-force break-off bolt is broken, and the aircraft breaks away from the restraint of the restraint rod and starts to taxi on the deck.

[0003] CN108298105A, an electromagnetic catapult for drones, includes a landing gear assembly, a towing rod, a driving device and a backrest device. The driving device consists of a linear motor and a catapult shuttle. The catapult shuttle is hinged to the end of the towing rod. A magnetic device with strong suction is arranged inside the catapult shuttle, and a magnetic device is arranged at the position where the towing rod contacts the catapult shuttle. Suction is generated during the movement of the catapult shuttle to reduce vibration, which is beneficial to the catapult of the drone. The present invention can reduce the vibration amplitude of the catapult shuttle and the towing rod during the catapult process, mitigate the adverse effects brought by vibration, and is beneficial to the catapult of the drone. However, this technical solution lacks the determination of the separation timing between the drone and the electromagnetic catapult.

[0004] CN106428605B proposes a combined braking system for an electromagnetic catapult of a drone, including a catapult rack and a drone support catapult platform. A slide rail is arranged on the catapult rack, and the drone support catapult platform is supported on the slide rail of the catapult rack through its two sides. The drone support catapult platform can move along the slide rail under the drive of a catapult motor. An inverse connection braking unit is arranged on the catapult rack, and at least one braking unit of a hydraulic braking unit and a permanent magnet eddy current braking unit is also arranged on the catapult rack. Multiple braking methods cooperate for combined braking, which can consume the kinetic energy of the mover of the permanent magnet linear motor and the drone support catapult platform within a short time and a short distance. However, in this technical solution, a passive braking unit is set. Although it can separate the drone from the electromagnetic catapult unit, the separation timing cannot be controlled. Summary of the Invention

[0005] Aiming at the deficiencies of the prior art, the present invention provides an electromagnetic catapult booster device for target drones, which solves the problems raised in the above background art.

[0006] To achieve the above object, the present invention is realized by the following technical solutions: a target aircraft electromagnetic catapult boost device, including an orbital platform, in the middle of which an electromagnetic catapult track is inlaid. An acceleration block is arranged in the middle of the electromagnetic catapult track, and a connection unit is arranged above the acceleration block. The connection unit is connected to the target aircraft, and the connection unit is provided with an active separation mechanism controlled by the speed of the target aircraft.

[0007] Preferably, the connection unit includes a clamping sleeve fixedly connected to the target aircraft. On one side of the clamping sleeve away from the nose of the target aircraft, there is a plugging slot, and a plugging block is plugged inside the plugging slot. The plugging block and the clamping sleeve are threadedly connected by a threaded shaft arranged upward from the bottom end. A fixed frame is fixedly installed at the bottom end of the plugging block, and rollers are fixedly installed on both sides of the fixed frame. The fixed frame and the acceleration block are connected by a connecting rod.

[0008] Preferably, the front end of the clamping sleeve is streamlined, and the plugging slots include a plurality of continuously distributed up and down, and the plurality of plugging blocks are connected as a whole.

[0009] Preferably, the active separation mechanism includes a telescopic sleeve fixedly installed on the inner top wall of the fixed frame, and a friction pad that rubs against the orbital platform is fixedly installed at the bottom end of the telescopic sleeve.

[0010] Preferably, the connection unit includes a connection hanging point fixedly installed under the fuselage of the target aircraft. A connection platform is fixedly installed above the acceleration block, and the connection platform and the connection platform are fixedly connected by a connection frame. The active separation mechanism includes a cutting unit that cuts to break the connection frame.

[0011] Preferably, the cross-sectional shape of the connection frame is "Y" - shaped. The middle of the connection frame is connected to the connection hanging point by a separately distributed fixing rod, and the bottom end of the connection frame is plugged forward above the connection platform.

[0012] Preferably, the cutting unit includes hydraulic cylinders arranged on the left and right sides of the connection platform. A cutting knife is fixedly installed at the free end of the hydraulic cylinder, and the two cutting knives are symmetrically arranged.

[0013] Preferably, the cutting unit includes a cutting disc. A swinging rod is fixedly installed perpendicular to the flight direction of the target aircraft above the connection platform, and the cutting disc is fixedly installed at the free end of the swinging rod. The swinging rod swings from one side of the connection frame to the other side.

[0014] Preferably, a telescopic rod is fixedly installed at the rear end above the connection platform, and the free end of the telescopic rod moves forward to squeeze the connection frame to separate from the connection platform.

[0015] Preferably, an electromagnet is inlaid at the rear end of the connection platform, and a magnetic plate is fixedly installed at one end of the connection frame plugged inside the connection platform.

[0016] Compared with the prior art, the present invention has the following beneficial effects: 1. For the electromagnetic catapult booster device of the target aircraft, by setting an active separation mechanism controlled by the speed of the target aircraft, compared with setting a blocking mechanism at the end of the track or setting a constant-tensile force breaking mechanism, such a setting can accurately control the launching timing of the target aircraft and the catapult track.

[0017] 2. For the electromagnetic catapult booster device of the target aircraft, the connecting unit includes a clamping sleeve fixedly connected to the target aircraft. On one side of the clamping sleeve away from the nose of the target aircraft, there is a plugging slot. Inside the plugging slot, there is a plugging block. The plugging block and the clamping sleeve are threadedly connected by a threaded shaft arranged upward from the bottom end. At the bottom end of the plugging block, a fixed frame is fixedly installed. On both sides of the fixed frame, rollers are fixedly installed. The fixed frame and the acceleration block are connected by a connecting rod. Through such a setting, the rollers originally arranged at the target aircraft can be moved to the fixed frame. During the movement of the target aircraft, the fixed frame and the target aircraft are connected together by the threaded shaft. The rollers can support the target aircraft and, when moving to the launching position, the threaded shaft is removed, and the separation of the target aircraft catapult device is achieved through inertia. Such a setting can simplify the target aircraft and can reuse the rollers, thereby reducing the cost of the device.

[0018] 3. For the electromagnetic catapult booster device of the target aircraft, the cross-sectional shape of the connecting frame is "Y". The middle part of the connecting frame is connected to the connecting hanging point by a separately distributed fixed rod. The fixed rod can be connected to the connecting hanging point and the connecting frame by plugging. Through such a setting, it is convenient to replace the fixed rod. The bottom end of the connecting frame is inserted forward above the connecting platform. Through such a setting, the use cost of the device can be reduced.

[0019] 4. For the electromagnetic catapult booster device of the target aircraft, a telescopic rod is fixedly installed at the upper end of the tail of the connecting platform. The free end of the telescopic rod moves forward to squeeze the connecting frame to separate from the connecting platform. After launching one target aircraft, the connecting frame is pushed out by the telescopic rod, so that the connecting rod and the connecting platform can be separated, and then it is convenient to install the next target aircraft at the electromagnetic catapult track. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 is a schematic structural diagram of the present invention; Figure 2 is a schematic connection diagram of the clamping sleeve of the present invention; Figure 3 is a schematic connection diagram of the connecting rod of the present invention; Figure 4 is a schematic connection diagram of the fixed frame of the present invention; Figure 5 is a schematic structural diagram of Embodiment 2 of the present invention; Figure 6 is a schematic connection diagram of the fixed rod of the present invention; Figure 7 Schematic connection diagram of the connection platform of the present invention Figure 8 Schematic connection diagram of the cutting disc of the present invention

[0021] In the figure: 1. Rail platform; 2. Electromagnetic ejection track; 3. Acceleration block; 4. Connection unit; 5. Active separation mechanism; 401. Clamping sleeve; 402. Insertion slot; 403. Insertion block; 404. Threaded shaft; 405. Fixed frame; 406. Roller; 407. Connecting rod; 408. Connection hanging point; 409. Connection platform; 410. Connection frame; 411. Fixed rod; 501. Telescopic sleeve; 502. Friction pad; 54. Cutting unit; 541. Hydraulic cylinder; 542. Cutting knife; 543. Cutting disc; 544. Swing rod; 545. Telescopic rod; 546. Electromagnet; 547. Magnetic plate Specific embodiments

[0022] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application

[0023] It should be noted that all directional indications in the embodiments of the present application are only used to explain the relative position relationship, movement conditions, etc. between components in a specific posture. If this specific posture changes, the directional indication will also change accordingly

[0024] In the present application, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. shall be understood in a broad sense. For example, "fixation" 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 communication inside two components or the interaction relationship between two components, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific situations

[0025] In addition, in this application, descriptions such as "first" and "second" are for descriptive purposes only, and should not be construed as indicating or implying their relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions between various embodiments may be combined with each other, but it must be based on the ability of those of ordinary skill in the art to implement. When the combination of technical solutions results in contradictions or is impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0026] As Figures 1 - 8 shown, in Embodiment 1, the electromagnetic catapult booster device for the target aircraft includes a track platform 1, in the middle of which an electromagnetic catapult track 2 is inlaid. An acceleration block 3 is arranged in the middle of the electromagnetic catapult track 2. A connecting unit 4 is arranged above the acceleration block 3. The connecting unit 4 is connected to the target aircraft. The connecting unit 4 is provided with an active separation mechanism 5 controlled by the speed of the target aircraft. By setting the active separation mechanism 5 controlled by the speed of the target aircraft, compared with setting a blocking mechanism at the end of the track or setting a constant-tension fracture mechanism, such a setting can accurately control the launching timing of the target aircraft and the catapult track.

[0027] Specifically, the connecting unit 4 includes a clamping sleeve 401 fixedly connected to the target aircraft. On one side of the clamping sleeve 401 away from the nose of the target aircraft, a plugging slot 402 is arranged. A plugging block 403 is plugged inside the plugging slot 402. The plugging block 403 and the clamping sleeve 401 are threadedly connected by a threaded shaft 404 arranged upward from the bottom end. A fixing frame 405 is fixedly installed at the bottom end of the plugging block 403. Roller wheels 406 are fixedly installed on both sides of the fixing frame 405. The fixing frame 405 is connected to the acceleration block 3 through a connecting rod 407. Through such a setting, the original roller wheels 406 arranged at the target aircraft can be moved to the fixing frame 405. During the movement of the target aircraft, the fixing frame 405 and the target aircraft are connected together by the threaded shaft 404. The roller wheels 406 can play a supporting role for the target aircraft, and when moving to the launching position, the threaded shaft 404 is removed, and the separation of the catapult device of the target aircraft is achieved through inertia. Such a setting can simplify the target aircraft and can reuse the roller wheels 406, thereby reducing the cost of the device.

[0028] Specifically, the front end of the clamping sleeve 401 is streamlined. Through such a setting, the wind resistance of the clamping sleeve 401 can be reduced. The plugging slot 402 includes a plurality of continuously distributed upper and lower ones. The plurality of plugging blocks 403 are connected as a whole. Through such a setting, the connection stability between the plugging block 403 and the clamping sleeve 401 can be ensured.

[0029] Specifically, the active separation mechanism 5 includes a telescopic sleeve 501 fixedly installed on the inner top wall of the fixed frame 405. A friction pad 502 that rubs against the track platform 1 is fixedly installed at the bottom end of the telescopic sleeve 501. The telescopic sleeve 501 is extended and retracted by controlling the speed of the target drone. When the telescopic sleeve 501 extends until the friction pad 502 contacts the track platform 1, the connection unit 4 is quickly paused, so that the connection unit 4 can be separated from the target drone.

[0030] As Figures 5 - 8 shown, in Embodiment 2, the connection unit 4 includes a connection hanging point 408 fixedly installed under the fuselage of the target drone. A connection platform 409 is fixedly installed above the acceleration block 3. The connection platforms 409 are fixedly connected by a connection frame 410. The active separation mechanism 5 includes a cutting unit 54 that cuts the connection frame 410 to break it. In this embodiment, the target drone itself has a roller mechanism and is fixedly connected to the target drone through the connection hanging point 408. The cutting timing of the cutting unit 54 is controlled by the speed of the target drone to separate the target drone from the track.

[0031] Specifically, the cross-sectional shape of the connection frame 410 is "Y". The middle of the connection frame 410 is connected to the connection hanging point 408 through a separately distributed fixing rod 411. The fixing rod 411 can be connected to the connection hanging point 408 and the connection frame 410 by plugging. Through such a setting, it is convenient to replace the fixing rod 411. The bottom end of the connection frame 410 is plugged into the front above the connection platform 409.

[0032] Specifically, the cutting unit 54 includes hydraulic cylinders 541 arranged on the left and right sides of the connection platform 409. A cutting knife 542 is fixedly installed at the free end of the hydraulic cylinder 541. The two cutting knives 542 are symmetrically arranged. In the solution, the fixing rod 411 can be composed of multiple individual rods with smaller diameters. During the movement of the cutting knife 542, the fixing rod 411 is cut off at the same time.

[0033] The cutting unit 54 includes a cutting disc 543. A swing rod 544 is fixedly installed above the connection platform 409 perpendicular to the flight direction of the target drone. The cutting disc 543 is fixedly installed at the free end of the swing rod 544. The swing rod 544 swings from one side of the connection frame 410 to the other side. In this solution, the fixing rod 411 can be a sleeve. The swing of the swing rod 544 drives the rotating cutting disc 543 to rotate, and then the fixing rod 411 can be cut by friction. The swing timing and swing speed of the swing rod 544 are both controlled by the speed of the target drone. It starts and swings before the takeoff speed of the target drone. When the takeoff speed of the target drone is reached, the fixing rod 411 breaks, and the target drone is separated from the connection unit 4. By separating actively in this way, the jitter of the target drone when the connection unit 4 suddenly reduces speed and separates from the target drone can be reduced.

[0034] Specifically, a telescopic rod 545 is fixedly installed at the upper end of the connection platform 409. The free end of the telescopic rod 545 moves forward to squeeze the connection frame 410 to separate from the connection platform 409. After launching one target drone, the connection frame 410 is pushed out by the telescopic rod 545, so that the connection rod 407 and the connection platform 409 can be separated, and then it is convenient to install the next target drone at the electromagnetic catapult track 2.

[0035] Such as Figure 8 Shown in Embodiment 3, an electromagnet 546 is embedded at the rear end of the connection platform 409. A magnetic plate 547 is fixedly installed at one end of the connection frame 410 inserted into the connection platform 409. By setting the electromagnet 546, the connection frame 410 after cutting can be separated from the connection platform 409 through the mutual repulsion between the electromagnet 546 and the magnetic plate 547.

[0036] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, those skilled in the art can combine and combine the different embodiments or examples described in this specification.

[0037] In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on what can be achieved by those of ordinary skill in the art. When the combination of technical solutions results in contradictions or cannot be achieved, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0038] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. Target aircraft electromagnetic catapult boost device, including a track platform (1), characterized in that: In the middle of the track platform (1), an electromagnetic catapult track (2) is inlaid. An acceleration block (3) is arranged in the middle of the electromagnetic catapult track (2). Above the acceleration block (3), a connection unit (4) is arranged. The connection unit (4) is connected to the target drone, and the connection unit (4) is provided with an active separation mechanism (5) controlled by the speed of the target drone.

2. The electromagnetic catapult boost device for the target drone according to claim 1, characterized in that: The connection unit (4) includes a clamping sleeve (401) fixedly connected to the target drone. On the side of the clamping sleeve (401) away from the nose of the target drone, a plugging slot (402) is arranged. Inside the plugging slot (402), a plugging block (403) is plugged. The plugging block (403) and the clamping sleeve (401) are threadedly connected through a threaded shaft (404) arranged upward from the bottom end. At the bottom end of the plugging block (403), a fixed frame (405) is fixedly installed. On both sides of the fixed frame (405), rollers (406) are fixedly installed. The fixed frame (405) and the acceleration block (3) are connected through a connecting rod (407).

3. The electromagnetic catapult boosting device for the target aircraft according to claim 2, characterized in that: The front end of the clamping sleeve (401) is streamlined. The plugging slot (402) includes a plurality of continuously distributed ones up and down, and the plurality of plugging blocks (403) are connected as a whole.

4. The electromagnetic catapult boost device for target drones according to claim 2 or 3, characterized in that: The active separation mechanism (5) includes a telescopic sleeve (501) fixedly installed on the inner top wall of the fixed frame (405). At the bottom end of the telescopic sleeve (501), a friction pad (502) that frictions with the track platform (1) is fixedly installed.

5. The electromagnetic catapult boost device for the target aircraft according to claim 1, wherein: The connection unit (4) includes a connection hanging point (408) fixedly installed under the fuselage of the target drone. Above the acceleration block (3), a connection platform (409) is fixedly installed. The connection platform (409) and the connection platform (409) are fixedly connected through a connection frame (410).

6. The electromagnetic catapult boosting device for target aircraft according to claim 5, characterized in that: The cross-sectional shape of the connection frame (410) is "Y". The middle of the connection frame (410) is connected to the connection hanging point (408) through a separately distributed fixing rod (411). The bottom end of the connection frame (410) is inserted forward above the connection platform (409). The active separation mechanism (5) includes a cutting unit (54) that cuts to break the connection frame (410).

7. The electromagnetic catapult boost device for the target aircraft according to claim 6, wherein: The cutting unit (54) includes hydraulic cylinders (541) arranged on the left and right sides of the connection platform (409). At the free end of the hydraulic cylinders (541), a cutting knife (542) is fixedly installed. The two cutting knives (542) are symmetrically arranged.

8. The electromagnetic catapult boost device for the target aircraft according to claim 6, characterized in that: The cutting unit (54) includes a cutting disc (543). Above the connection platform (409), a swing rod (544) is fixedly installed perpendicular to the flight direction of the target drone. The cutting disc (543) is fixedly installed at the free end of the swing rod (544). The swing rod (544) swings from one side of the connection frame (410) to the other side.

9. The electromagnetic catapult boost device for target aircraft according to claim 7 or 8, characterized in that: At the upper tail end of the connection platform (409), a telescopic rod (545) is fixedly installed. The free end of the telescopic rod (545) moves forward to squeeze the connection frame (410) to separate from the connection platform (409).

10. The electromagnetic ejection boost device for target aircraft according to claim 5 or 7 or 8, characterized in that: An electromagnet (546) is inlaid at the rear end of the connection platform (409). At the end of the connection frame (410) inserted inside the connection platform (409), a magnetic plate (547) is fixedly installed.

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