Micro-miniature child-mother unmanned aerial vehicle cooperative attack training mounting and releasing device

Abstract

The utility model provides a micro-miniature child-mother unmanned aerial vehicle cooperative attack training mounting and releasing device, which belongs to the technical field of unmanned aerial vehicles and comprises a fixed-wing mother vehicle, a plurality of unmanned aerial vehicles and a plurality of unmanned aerial vehicles, the fixing frames are detachably fixed to the bottoms of the wings, and each fixing frame comprises a clamping mechanism; the multi-rotor sub-machine is fixed by the clamping mechanism, and when the clamping mechanism cancels the fixation of the sub-machine, the sub-machine can fall off from the mother machine and operate; according to the multi-rotor unmanned aerial vehicle disclosed by the utility model, the sub-aircraft can be carried near a preset position through the master aircraft, and then the sub-aircraft is put, so that the sub-aircraft can fly towards a specified position, and therefore, the flight range of the multi-rotor unmanned aerial vehicle can be effectively expanded, and the flexibility and the operation diversity of the multi-rotor unmanned aerial vehicle are further enhanced.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) equipment technology, specifically to a micro-miniature mother-daughter UAV collaborative attack training and deployment device. Background Technology

[0002] In recent years, with the rapid development of drone technology, micro-drones have been increasingly widely used in the military field. However, although multi-rotor drones / racing drones have advantages such as simple take-off and landing sites, small target signature, and high maneuverability, their flight principle determines that they have the following specific defects:

[0003] Short flight time: Multi-rotor drones are usually powered by batteries, and their flight time is generally less than 20-30 minutes, which is difficult to meet the needs of long-term missions.

[0004] Small flight radius: Limited by battery capacity and communication distance, the control radius of multi-rotor drones is usually no more than 5 kilometers, which limits their application in long-distance missions.

[0005] Short loiter time in mission area: Due to limited endurance, multi-rotor UAVs have a short loiter time in the mission area, making it difficult to achieve continuous reconnaissance or strike.

[0006] Low flight altitude: Multi-rotor drones typically fly at low altitudes, making them susceptible to terrain and obstacles, and also easier for air defense systems to detect and intercept.

[0007] Short control distance: The communication range of multi-rotor UAVs is limited, especially in complex electromagnetic environments where signals are easily interfered with, which further shortens the control distance.

[0008] These shortcomings severely limit the effectiveness of multi-rotor UAVs in practical missions. For example, during the launch phase, multi-rotor UAVs consume a significant amount of time and energy to reach the mission area, resulting in a substantial reduction in their loiter time and hindering efficient mission completion. Furthermore, due to their limited control range, multi-rotor UAVs require reliance on relay communication or multiple takeoffs and landings for long-distance missions, further reducing mission efficiency. Utility Model Content

[0009] In view of this, the present invention provides a micro-sized mother-daughter UAV collaborative attack training mounting and deployment device. The present invention can carry the daughter UAV to the vicinity of a predetermined location through the mother UAV, and then deploy the daughter UAV so that it can fly toward the designated location. This can effectively increase the flight range of multi-rotor UAVs, thereby enhancing the flexibility and operational versatility of multi-rotor UAVs.

[0010] To solve the above-mentioned technical problems, this utility model provides a micro-miniature mother-daughter UAV collaborative attack training mounting and deployment device, including:

[0011] A fixed-wing aircraft carrier, which includes multiple wings;

[0012] Several mounting brackets, which are detachably fixed to the bottom of the wing, and include clamping mechanisms;

[0013] The multi-rotor sub-engine is fixed by a clamping mechanism. The sub-engine can be fixed to the bottom of the mother aircraft by a fixing frame. When the clamping mechanism releases the sub-engine, the sub-engine can detach from the mother aircraft and run. The mother aircraft can carry the sub-engine to a preset location.

[0014] The mounting bracket has a cylindrical hollow structure, and the perimeter of the mounting bracket is hollow, which reduces the weight of the mounting bracket to a certain extent.

[0015] The clamping mechanism includes multiple hinge seats set on the outer side wall of the bottom of the fixed frame. The hinge seats are hinged with pawls, which can rotate on the hinge seats. The middle part of the pawl is connected to the hinge seats. The end of the pawl away from the mother machine has a slot. Multiple slots are used to clamp the frame of the daughter machine. The rotation of the pawl can clamp the daughter machine or cause the daughter machine to fall off.

[0016] The clamping mechanism also includes a drive assembly mounted on a fixed frame. The drive assembly is used to drive the ends of multiple jaws that are away from the slots to move relative to or away from each other. In other words, the drive assembly can indirectly drive the two slots to move closer together or open to the sides.

[0017] The drive assembly includes a motor installed in the hollow structure of the fixed frame. The output shaft of the motor is equipped with a movable disc, which can drive the movable disc to rotate. The movable disc is equipped with a connecting rod, which can pull the connecting rod to move. The other end of the connecting rod is connected to the end of the claw. The connecting rod is made of a deformable material and can deform during the displacement process.

[0018] The movable plate has multiple first through holes, which are set through the movable plate. Corresponding to the first through holes, several second through holes are set at the end of the claw, which are set through the claw at the end away from the slot. Both ends of the connecting rod have corner parts, which are fixed in the first and second through holes respectively. When the movable plate rotates, it can drive the claw to rotate through the connecting rod.

[0019] The claw end has multiple second through holes, which allows the position of the connecting rod end on the claw end to be changed.

[0020] The catch is detachably fixed to the hinge, making it easy to replace the catch.

[0021] The subframe frame is also provided with multiple limiting holes, and corresponding to the limiting holes, multiple limiting rods are provided on the outer surface of the bottom of the fixed frame. The limiting rods can further stabilize the position of the subframe.

[0022] The limit rod is detachably fixed to the mounting bracket, allowing for its removal.

[0023] The wing bottom is equipped with a pylon, which is used to fix multiple fixed frames and reduce wind resistance. The pylon can also be detached and installed on the wing bottom, and the fixed frame is also equipped with a wind-breaking structure.

[0024] The end of the bracket is provided with a T-shaped slide groove, in which the fixing bracket can slide without falling off. The bottom of the slide groove is connected to the bottom of the bracket. Multiple positioning grooves are provided on both sides of the bracket. The positioning grooves are cross-shaped and connected to the slide groove. The hinge seat is located in the positioning groove to prevent the fixing bracket from falling off the slide groove.

[0025] In summary, compared with the prior art, this application includes at least one of the following beneficial technical effects:

[0026] 1. Expanding the mission range of multi-rotor aircraft: This invention uses a fixed-wing mother aircraft to carry multi-rotor aircraft to the vicinity of a preset mission area, significantly expanding the flight radius and mission range of the aircraft. Fixed-wing mother aircraft have the advantages of long endurance and high flight altitude, effectively compensating for the shortcomings of multi-rotor aircraft in terms of endurance and flight radius, enabling them to perform missions at greater distances and in more complex environments.

[0027] 2. Improved mission execution efficiency: By mounting a delivery device, multi-rotor aircraft do not need to consume their own energy to fly to the mission area. Instead, they are carried to the vicinity of the target area by a fixed-wing mother aircraft and then released. This design significantly reduces the energy consumption of the aircraft during the takeoff phase and extends their loiter time in the mission area, thereby improving mission execution efficiency.

[0028] 3. Reliable mounting and release mechanism design: The clamping mechanism reliably secures the sub-aircraft using claws and slots. The drive assembly controls the opening and closing of the claws via a motor and movable disc, ensuring stable mounting of the sub-aircraft during flight and rapid and reliable separation during release. This design avoids the problem of the sub-aircraft shifting or detaching during high-speed flight or high-G maneuvers of the mother aircraft.

[0029] 4. Lightweight and Modular Design: The mounting frame adopts a cylindrical hollow structure and a perforated design, effectively reducing the overall weight of the device and minimizing its impact on the mother aircraft's flight performance. Simultaneously, the clamping mechanism and limit rods are detachable, facilitating maintenance and replacement, further enhancing the device's practicality and flexibility.

[0030] 5. Reduced wind resistance and improved flight stability: The pylons feature a T-shaped sliding groove and a cross-shaped positioning groove design, which not only secures multiple mounting points but also effectively reduces wind resistance and improves the aircraft's flight stability. Furthermore, the pylons' aerodynamic structure further optimizes aerodynamic performance, ensuring the aircraft's stability during high-speed flight.

[0031] 6. Flexible Adaptability to Diverse Task Requirements: The mounting and deployment device of this utility model can flexibly adjust the number and position of sub-units according to task requirements, realizing the "one-mount-multiple" function. By adjusting the position of the fixing frame on the mounting bracket, it can accommodate sub-units of different sizes and weights, further enhancing the applicability and task versatility of the device.

[0032] 7. Simplified Operation and Maintenance: The gripper and limit lever of the clamping mechanism are designed to be detachable, facilitating quick replacement and maintenance. Meanwhile, the connecting rod of the drive assembly is made of a deformable material, allowing it to deform as the movable disc rotates, ensuring smooth opening and closing of the gripper and further simplifying the operation process. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of the structure of the micro-miniature mother-daughter UAV collaborative attack training and deployment device of this utility model;

[0034] Figure 2 This is a schematic diagram of the structure of the motor of this utility model;

[0035] Figure 3 This is a schematic diagram of the structure of the hanging bracket of this utility model.

[0036] Explanation of reference numerals in the attached figures:

[0037] 300. Fixed frame; 310. Clamping mechanism; 311. Hinge seat; 312. Grappling claw; 313. Slot; 314. Motor; 315. Movable plate; 316. Connecting rod; 317. First through hole; 318. Second through hole; 320. Limiting rod; 400. Hanger; 401. Slide groove; 402. Positioning groove. Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the following will be described in conjunction with the accompanying drawings of the embodiments of this utility model. Figure 1-3 The technical solutions of the embodiments of this utility model are clearly and completely described herein. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. All other embodiments obtained by those skilled in the art based on the described embodiments of this utility model are within the protection scope of this utility model.

[0039] Example 1;

[0040] Miniature mother-daughter UAV collaborative attack training payload and deployment device, such as Figure 1 As shown, it consists of three parts: a fixed-wing mother aircraft, a fixed frame 300, and a multi-rotor aircraft. The fixed frame 300 is bonded to the bottom of the wing of the fixed-wing mother aircraft. Each fixed frame 300 is equipped with a clamping mechanism 310, which can be used to clamp the multi-rotor aircraft. When the clamping mechanism 310 no longer clamps the aircraft, the aircraft can detach from the fixed frame 300. In this way, the fixed-wing mother aircraft can carry several multi-rotor aircraft to a designated location and then release the clamping mechanism 310 from the aircraft, allowing the aircraft to fly precisely toward the designated location to perform its mission.

[0041] Specifically, the fixing frame 300 is composed of a cylindrical hollow structure, such as... Figure 1 As shown: The outer wall around the mounting frame 300 is designed with a hollow structure, which enables the lightweight design of the mounting frame 300, reduces the load of the mother aircraft during flight, and thus indirectly increases the flight distance of the mother aircraft. In addition, the mounting frame 300 can be made of plastic material, which can further reduce the weight of the mounting frame 300 and reduce the production cost of the mounting frame 300.

[0042] The effect of designing the mounting frame with a hollow structure is that, since the top of the sub-unit is a protruding structure, after the sub-unit is fixed on the mounting frame, the protrusion on the top of the sub-unit is located at the bottom of the mounting frame. This reduces the overall volume of the mounting frame and the sub-frame, reduces wind resistance, and makes the whole structure more compact.

[0043] Furthermore, the clamping mechanism 310 includes two hinge seats 311 disposed on the fixed frame 300, such as... Figure 1 As shown: The hinge base 311 is located on the outer side wall of the bottom of the fixed frame 300 and on both sides of the fixed frame 300. Each hinge base 311 is equipped with a pawl 312 by hinge. The middle part of the pawl 312 is connected to the hinge base 311, so the pawl 312 can rotate on the hinge base 311. The end of the pawl 312 away from the mother machine is provided with a slot 313. The slots 313 on the two pawls 312 are arranged opposite each other. The clamping mechanism 310 also includes a drive assembly. This is used to drive the ends of multiple jaws 312 away from the slots 313 to move relative to or away from each other, thereby indirectly driving the jaws 312 to rotate, causing the two slots 313 to rotate relative to or away from each other. After the two slots 313 rotate relative to each other, they can be used to clamp the sub-machine frame, thus fixing the sub-machine. When the two slots 313 rotate away from each other, they can remove the limiting effect of the two slots 313 on the sub-machine frame, so that the sub-machine can fall off the fixing frame 300.

[0044] Furthermore, the drive assembly includes a motor 314 disposed within the hollow structure of the mounting bracket 300, such as... Figure 1 ,2 As shown: The output shaft of the motor 314 is provided with a movable disk 315. The movable disk 315 has a circular cross-section. The movable disk 315 and the fixed frame 300 are located on the same axis. When the motor 314 works, it can coaxially drive the movable disk 315 to rotate. During the process of the motor 314 driving the movable disk 315 to rotate, it can drive the second through hole 318 at the end of the pawl 312 to move, so that the pawl 312 can rotate on the hinge seat 311.

[0045] Specifically, the end of the claw 312 is provided with multiple second through holes 318, such as... Figure 1 As shown: multiple second perforations 318 are arranged in a linear array on the claw 312, and since the connecting rod 316 is made of aluminum, the connection position between the connecting rod 316 and the claw 312 can be changed.

[0046] It is worth mentioning that the connection between the catch 312 and the hinge seat 311 is detachable, such as... Figure 1 As shown: The hinge seat 311 has a concave structure. Two positioning blocks are symmetrically arranged on the hinge seat 311. Positioning grooves 402 are provided on the two side walls of the pallet 312 corresponding to the two positioning blocks. The positioning blocks can be inserted into the positioning grooves 402. The hinge seat 311 is made of deformable plastic material. Both the positioning blocks and the positioning grooves 402 are semi-circular structures. In this way, when the pallet 312 is disassembled or installed, the pallet 312 can be pulled out or pushed into the hinge seat 311 directly, which makes it easy to replace the pallet 312.

[0047] Furthermore, the submachine frame is also vertically equipped with two limiting holes, such as... Figure 1 As shown: corresponding to the two limiting holes, two limiting rods 320 are also provided at the bottom of the fixing frame 300. The two limiting rods 320 are located on both sides of the outer wall of the fixing frame 300. Both limiting rods 320 have an L-shaped structure, that is, when the sub-frame is clamped and fixed, the limiting rods 320 are located in the limiting holes, so as to maintain the stability of the sub-frame in the clamping mechanism 310.

[0048] Furthermore, the limiting rod 320 is detachably fixed to the fixing bracket 300, such as... Figure 1 As shown: Specifically, the end of the limiting rod 320 is also provided with multiple insert rods, and the corresponding insert rods are provided with multiple slots on the outer wall of the fixing frame 300. Inserting the insert rods into the slots can fix the limiting rod 320, and also facilitate the replacement of the limiting rod 320.

[0049] Example 2;

[0050] The difference from Embodiment 1 is that it also includes a mounting bracket 400, which has an overall locomotive-like structure, such as... Figure 3As shown: The pylon 400 is fixed to the bottom of the wing by adhesive bonding. The pylon 400 can be used to fix multiple fixed frames 300. The multiple fixed frames 300 are fixed to the pylon 400 in a linear manner, which can greatly reduce the wind resistance of the mother aircraft during flight. In addition, the end of the pylon 400 facing the nose of the mother aircraft is also equipped with a wind-breaking structure, which can further reduce wind resistance.

[0051] Specifically, a T-shaped groove 401 is provided on the end of the bracket 400 away from the wind-breaking structure, such as... Figure 3 As shown: The bottom of the slide groove 401 is connected to the bottom of the hanger 400. The fixed frame 300 can slide within the slide groove 401. The hanger 400 also has multiple sets of positioning grooves 402 on both sides. The positioning grooves 402 are cross-shaped and communicate with the slide groove 401. Each set of positioning grooves 402 is used to limit the fixed frame 300. That is, before the fixed frame 300 is installed into the hanger 400, the claw 312 and the limiting rod 320 need to be removed, and then the hinge seat 311 is slid into the slide groove 401 along its length. Inside 401, when the fixed frame 300 slides between the two positioning slots 402, the fixed frame 300 is rotated 90 degrees, and the hinge seat 311 can be screwed into the positioning slot 402. Then, the force applied to the fixed frame 300 is released, and the fixed frame 300 is pressed downward. The hinge seat 311 on the fixed frame 300 moves to the bottom position between the two positioning slots 402 (the hinge seat and the positioning slot are interlocked). Then, the claw 312 and the limit rod 320 are installed to clamp the submachine normally.

[0052] Furthermore, it should be noted that, in the description of this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0053] The above description is the preferred embodiment of this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this utility model, and these improvements and modifications should also be considered within the protection scope of this utility model.

Claims

1. A micro-sized mother-daughter UAV collaborative attack training and deployment device, characterized in that: include; A fixed-wing aircraft carrier, which includes multiple wings; Several mounting brackets (300) are detachably fixed to the bottom of the wing and include a clamping mechanism (310); The multi-rotor sub-engine is fixed by a clamping mechanism (310). When the clamping mechanism (310) releases the sub-engine, the sub-engine can detach from the mother engine and operate. The fixing frame (300) is a cylindrical hollow structure, and the periphery of the fixing frame (300) is a hollow structure; The clamping mechanism (310) includes a plurality of hinge seats (311) disposed on the outer side wall of the bottom of the fixed frame (300). A claw (312) is hinged on the hinge seat (311). The middle part of the claw (312) is connected to the hinge seat (311). The end of the claw (312) away from the mother machine has a slot (313). The plurality of slots (313) are used to clamp the frame of the daughter machine. The clamping mechanism (310) also includes a drive assembly disposed on the fixed frame (300), the drive assembly being used to drive the ends of the multiple claws (312) away from the slot (313) to move relative to or away from each other.

2. The micro-miniature mother-daughter UAV cooperative attack training mounting and deployment device as described in claim 1, characterized in that: The drive assembly includes a motor (314) disposed within the hollow structure of the fixed frame (300). The output shaft of the motor (314) is provided with a movable disc (315), and the movable disc (315) is provided with a connecting rod (316). The other end of the connecting rod (316) is connected to the end of the pawl (312). The connecting rod (316) is made of a deformable material.

3. The micro-miniature mother-daughter UAV cooperative attack training and deployment device as described in claim 2, characterized in that: The movable disc (315) is provided with a plurality of first through holes (317), and a plurality of second through holes (318) are provided at the end of the claw (312) corresponding to the first through holes (317). Both ends of the connecting rod (316) are provided with corner portions, and the corner portions at both ends of the connecting rod (316) are respectively fixed in the first through holes (317) and the second through holes (318).

4. The micro-miniature mother-daughter UAV cooperative attack training mounting and deployment device as described in claim 3, characterized in that: The end of the claw (312) is provided with a plurality of second through holes (318).

5. The micro-miniature mother-daughter UAV cooperative attack training mounting and deployment device as described in claim 3, characterized in that: The catcher (312) is detachably fixed to the hinge seat (311).

6. The micro-miniature mother-daughter UAV cooperative attack training mounting and deployment device as described in claim 1, characterized in that: The submachine frame is also provided with multiple limiting holes, and corresponding to the limiting holes, multiple limiting rods (320) are also provided on the bottom outer surface of the fixing frame (300).

7. The micro-miniature mother-daughter UAV cooperative attack training and deployment device as described in claim 6, characterized in that: The limiting rod (320) is detachably fixed to the fixing frame (300).

8. The micro-miniature mother-daughter UAV cooperative attack training and deployment device as described in any one of claims 1 to 7, characterized in that: The wing bottom is provided with a hanger (400) for fixing multiple mounting brackets (300).

9. The micro-miniature mother-daughter UAV cooperative attack training and deployment device as described in claim 8, characterized in that: The end of the bracket (400) is provided with a T-shaped groove (401), the bottom of the groove (401) is connected to the bottom of the bracket (400), and multiple positioning grooves (402) are provided on both sides of the bracket (400). The positioning grooves (402) are cross-shaped and are connected to the grooves (401).

Images