A target drone device for unmanned aerial vehicle training

Abstract

The utility model relates to target machine technical field discloses a target machine device for unmanned plane training, include: fuselage, and detachable installation on the wing of fuselage, flat tail wing and vertical tail wing, install the mounting groove of fuselage on being used for the installation of wing, flat tail wing and vertical tail wing, be provided with the clamping structure in the mounting groove with wing, flat tail wing and vertical tail wing on, through the cooperation between fuselage, wing, flat tail wing, vertical tail wing, mounting groove, clamping structure, clamping mechanism and quick release mechanism, through clamping mechanism convenient to wing and install the quick alignment, and make clamping mechanism further lock position to wing after installing in place, avoid wing and fall off in the process of unmanned plane training from shaking, thereby improve the stability of wing installation, the wing damaged after training is locked through quick release mechanism contact simultaneously, so that the damaged wing is replaced fast, improve the maintenance convenience, reduce the use cost of unmanned plane target machine overall replacement.

Description

Technical Field

[0001] This utility model relates to the field of target drone technology, specifically a target drone device for unmanned aerial vehicle (UAV) training. Background Technology

[0002] Target drones are aircraft used as shooting training targets. They simulate enemy forces during military exercises or weapons tests, and provide hypothetical targets and shooting opportunities for various types of artillery or missile systems. In the prior art, Chinese utility model application number CN202122148754.X discloses a drone target drone, including: fuselage, wings, and tail fin. The tail fin includes a horizontal tail fin and a vertical tail fin. A rocket booster and a shock-absorbing recovery device are installed under the fuselage. The rocket booster is perpendicular to the fuselage. The shock-absorbing recovery device includes: a ground contact link and a shock-absorbing device. The first end of the ground contact link is hinged to the head of the fuselage, and the second end of the ground contact link is connected to the fuselage through the shock-absorbing device. There are two sets of ground contact links and shock-absorbing devices installed on both sides of the fuselage. This utility model uses the ground contact link and the shock-absorbing device to form a shock-absorbing recovery device. The ground contact link prevents the drone target drone from directly contacting the ground, and the shock-absorbing device reduces the impact. When the drone lands without being hit, it can keep the drone target drone intact as much as possible. In existing UAV training target drones, the wings are most likely to be hit during training. However, most existing UAV target drones have an integrated frame or welded wings, which means that the entire drone needs to be replaced after it is damaged, and the damaged parts cannot be removed individually. This increases the cost of UAV target drone training. Therefore, we need to propose a UAV training target drone device. Utility Model Content

[0003] The purpose of this utility model is to provide a target drone device for UAV training. By installing a quick-locking mechanism on the fuselage, the wing can be quickly positioned. At the same time, an anti-detachment structure is set between the wing and the fuselage to ensure the stability of the wing installation and improve the efficiency of wing installation. Furthermore, a quick-release mechanism is set to improve the efficiency of wing disassembly, facilitate the individual replacement of damaged wings, and reduce the operating cost of the UAV training target drone, thereby solving the problems mentioned in the background art.

[0004] To achieve the above objectives, this utility model provides the following technical solution: a target drone device for UAV training, comprising: The fuselage, and the wings, horizontal stabilizer and vertical stabilizer that can be detachably mounted on the fuselage. The fuselage has mounting slots for mounting the wings, horizontal stabilizer and vertical stabilizer. The mounting slots are equipped with snap-fit ​​structures on the wings, horizontal stabilizer and vertical stabilizer, and the snap-fit ​​structures enable the assembly of the wings, horizontal stabilizer and vertical stabilizer. The mounting slot is equipped with a clamping mechanism for securing the wing, horizontal stabilizer, and vertical stabilizer. The mounting slot is also equipped with a quick-release mechanism that abuts against the clamping mechanism. The clamping mechanism and the quick-release mechanism enable the positioning and disassembly of the wing, horizontal stabilizer, and vertical stabilizer.

[0005] Preferably, the snap-fit ​​structure includes multiple sets of right-angle locking blocks and multiple sets of right-angle locking slots. The multiple sets of right-angle locking blocks are respectively inserted into the multiple sets of right-angle locking slots. The multiple sets of right-angle locking slots are all opened at the ends of the wing, horizontal stabilizer and vertical stabilizer. The multiple sets of right-angle locking blocks are all fixedly connected to the bottom of the mounting slot.

[0006] Preferably, the mounting groove has an inner groove, and the inner groove has a storage groove and a quick-release groove on both sides for mounting the clamping mechanism and the quick-release mechanism. A groove for the clamping mechanism to be inserted is provided between the storage groove and the inner groove. The ends of the wing, horizontal tail fin and vertical tail fin are all fixedly connected with protrusions that are inserted into the inner groove.

[0007] Preferably, the clamping mechanism in both sets of storage slots includes two sets of springs and a base plate. Both sets of springs are fixedly connected to one side of the base plate, and a locking block located in the groove is fixedly connected to the other end of the base plate, with one side of the locking block abutting against one side of the protrusion.

[0008] Preferably, the quick-release mechanism includes a directional rod and an internal hexagonal bidirectional bolt installed in the quick-release groove. Two sets of abutments are slidably disposed on the directional rod, and the two sets of abutments are respectively disposed at both ends of the internal hexagonal bidirectional bolt.

[0009] Preferably, the outer side of the fuselage has multiple sets of hidden slots for mounting with hexagonal bidirectional bolts, and the wings and the horizontal stabilizer are arranged in equal proportions.

[0010] Preferably, the front of the fuselage is provided with a head cover, and an airspeed meter is installed on the head cover, and the rear of the fuselage is provided with a tail section.

[0011] Preferably, the horizontal stabilizer has a rectangular planar shape, the horizontal stabilizer has a 2-degree installation angle with the horizontal plane, the trailing edge of the horizontal stabilizer has an elevator, and the vertical stabilizer adopts a symmetrical airfoil and a trapezoidal planar shape.

[0012] Compared with the prior art, the beneficial effects of this utility model are: This utility model mainly utilizes the cooperation between the fuselage, wings, horizontal stabilizer, vertical stabilizer, mounting groove, snap-fit ​​structure, clamping mechanism, and quick-release mechanism. The snap-fit ​​mechanism facilitates quick and easy alignment and installation of the wings, and after installation, the clamping mechanism further locks the wings in place, preventing them from shaking and falling off during UAV training, thereby improving the stability of the wing installation. At the same time, damaged wings after training are locked in place by the quick-release mechanism, allowing for quick replacement of damaged wings, improving maintenance convenience, and reducing the overall replacement cost of the UAV target drone. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overall structure of the UAV of this utility model; Figure 2 This is a schematic diagram of the exploded structure of this utility model; Figure 3 This is a schematic diagram of the mounting groove structure of this utility model; Figure 4 This is a schematic diagram of the clamping mechanism and quick-release mechanism of this utility model.

[0014] In the diagram: 1. Fuselage; 2. Wing; 3. Horizontal stabilizer; 4. Vertical stabilizer; 5. Helmet; 6. Airspeed indicator; 7. Tail; 8. Mounting slot; 81. Inner slot; 82. Quick-release slot; 83. Groove; 84. Storage slot; 9. Protrusion; 10. Right-angle locking slot; 11. Right-angle locking block; 12. Clamping mechanism; 121. Base plate; 122. Locking block; 123. Spring component; 13. Quick-release mechanism; 131. Hex socket head cap screw; 132. Abutment block; 133. Directional rod. Detailed Implementation

[0015] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0016] Please see Figure 1-4 This utility model provides a technical solution: a target drone device for UAV training, comprising: The fuselage 1, and the wings 2, horizontal stabilizer 3 and vertical stabilizer 4 that can be detachably installed on the fuselage 1. The fuselage 1 has a mounting slot 8 for installing the wings 2, horizontal stabilizer 3 and vertical stabilizer 4. The mounting slot 8 has a snap-fit ​​structure with the wings 2, horizontal stabilizer 3 and vertical stabilizer 4. The snap-fit ​​structure enables the assembly of the wings 2, horizontal stabilizer 3 and vertical stabilizer 4. The mounting slot 8 is equipped with a clamping mechanism 12 for fastening the wing 2, horizontal stabilizer 3, and vertical stabilizer 4. The mounting slot 8 is also equipped with a quick-release mechanism 13 that abuts against the clamping mechanism 12. The clamping mechanism 12 and the quick-release mechanism 13 enable the positioning and disassembly of the wing 2, horizontal stabilizer 3, and vertical stabilizer 4. The wing 2, horizontal stabilizer 3, and vertical stabilizer 4 are all clipped delta wings. Through the action of the clipped delta wings, the occurrence of local supersonic speeds can be delayed.

[0017] The snap-fit ​​structure includes multiple sets of right-angle locking blocks 11 and multiple sets of right-angle locking grooves 10. The multiple sets of right-angle locking blocks 11 are respectively inserted into the multiple sets of right-angle locking grooves 10. The multiple sets of right-angle locking grooves 10 are all opened at the ends of the wing 2, horizontal tail 3 and vertical tail 4. The multiple sets of right-angle locking blocks 11 are all fixedly connected to the bottom of the mounting groove 8. In this embodiment, the insertion and engagement of the right-angle locking block 11 and the right-angle locking groove 10 can quickly achieve the initial positioning of the wing 2, horizontal tail 3 and vertical tail 4 with the fuselage 1, ensuring the accurate installation position of each component, laying the foundation for subsequent fastening and disassembly. At the same time, the structure is simple and reliable and easy to operate.

[0018] The mounting slot 8 has an inner slot 81, and the inner slot 81 has a storage slot 84 and a quick release slot 82 on both sides for mounting the clamping mechanism 12 and the quick release mechanism 13. The storage slot 84 and the inner slot 81 have a groove 83 for the clamping mechanism 12 to be inserted. The ends of the wing 2, the horizontal tail 3 and the vertical tail 4 are all fixedly connected to the protrusions 9 that are inserted into the inner slot 81. Specifically, the inner groove 81 provides installation space for the protrusion 9. Inserting the protrusion 9 into the inner groove 81 can further enhance the stability of the connection between the wing 2, horizontal stabilizer 3, and vertical stabilizer 4 and the fuselage 1. The storage groove 84 and quick-release groove 82 provide installation positions for the clamping mechanism 12 and quick-release mechanism 13, respectively, improving the rationality of the layout and not occupying extra space. The groove 83 provides an active path for the clamping block 122 of the clamping mechanism 12, ensuring that the clamping mechanism 12 can smoothly engage and fasten the protrusion 9.

[0019] The clamping mechanism 12 in both sets of storage slots 84 includes two sets of springs 123 and a base plate 121. The two sets of springs 123 are fixedly connected to one side of the base plate 121. The other end of the base plate 121 is fixedly connected to a locking block 122 located in the groove 83, and one side of the locking block 122 abuts against one side of the protrusion 9. Furthermore, the elastic force of the spring component 123 (mainly composed of a telescopic sleeve and an external return spring) can push the base plate 121 to move the locking block 122 within the groove 83, so that the right-angled edge of the locking block 122 tightly abuts against the protrusion 9, thereby firmly fixing the wing 2, horizontal tail 3 and vertical tail 4 to the fuselage 1, preventing the components from loosening due to vibration during flight, ensuring the stability of the target drone flight, and the symmetrical arrangement of the locking mechanism 12 makes the wing 2 more stable after installation.

[0020] The quick-release mechanism 13 includes a guide rod 133 and an internal hexagonal double-ended bolt 131 installed in the quick-release groove 82. Two sets of abutments 132 are slidably arranged on the guide rod 133, and the two sets of abutments 132 are respectively arranged at both ends of the internal hexagonal double-ended bolt 131.

[0021] In a further preferred embodiment, when the internal hexagonal bidirectional bolt 131 rotates, it can drive the two sets of abutments 132 to slide relative to each other along the directional rod 133, so that the abutments 132 can abut against the locking block 122 of the locking mechanism 12, thereby disengaging the locking block 122 from the protrusion 9 and achieving quick disassembly.

[0022] The outer side of the fuselage 1 has multiple hidden slots for installing hexagonal double-head bolts 131. The wings 2 and the horizontal stabilizer 3 are set in proportion. The hidden slots (not shown in the figure) can hide the hexagonal double-head bolts 131, so as to avoid the bolts protruding from the outer side of the fuselage 1 and affecting the aerodynamic performance of the target drone. At the same time, the bolts are protected from external collision damage. The equal setting of the wings 2 and the horizontal stabilizer 3 is conducive to ensuring the balance performance of the target drone and improving the flight stability.

[0023] The nose of the fuselage 1 is provided with a head cover 5, and an airspeed meter 6 is installed on the head cover 5. The tail of the fuselage 1 is provided with a tail section 7. It is worth noting that the helmet hood 5 protects the head of the fuselage 1, the airspeed indicator 6 can monitor the airspeed of the target drone in real time, providing accurate flight data for training, and the tail 7 is equipped with a turbojet engine (existing technology, which will not be described in detail), which facilitates the high-speed flight of the unmanned target drone, improves flight performance, and ensures that the target drone can fly stably during training.

[0024] The horizontal stabilizer 3 has a rectangular planar shape and a 2-degree installation angle with the horizontal plane. An elevator is located on the trailing edge of the horizontal stabilizer 3. The vertical stabilizer 4 adopts a symmetrical airfoil and a trapezoidal planar shape. During assembly and use, align the end of the wing 2 with the mounting slot 8 on the fuselage 1, insert the right-angle locking block 11 into the right-angle locking slot 10 and push it to move one end a distance to complete the initial positioning. At the same time, the protrusions 9 of each component are inserted into the inner groove 81. During the movement, the protrusions 9 will abut against the locking block 122 of the locking mechanism 12 and drive the base plate 121 to compress the spring 123. When the wing 2 is installed in place, under the action of the spring 123, the locking block 122 moves in the groove 83 and abuts against the protrusion 9, firmly fastening the wing 2 to the fuselage 1. The horizontal tail 3 and vertical tail 4 are installed in the same way as the wing 2.

[0025] When disassembly is required, the internal hexagonal double-headed bolt 131 of the quick-release mechanism 13 is rotated with a tool, which drives the two sets of abutments 132 to slide relative to each other along the guide rod 133, so that the abutments 132 abut against the locking block 122 of the locking mechanism 12, thereby compressing the spring 123, releasing the locking block 122 from abutting the protrusion 9, and then the wing 2 can be pushed to disengage the right-angle locking block 11 from the right-angle locking groove 10, so that the wing 2 can be removed from the mounting groove 8. The disassembly method of the horizontal stabilizer 3 and the vertical stabilizer 4 is the same. During flight training, the nose of the fuselage 1 is protected by the helmet hood 5, the airspeed indicator 6 monitors the airspeed, the tail 7 optimizes the aerodynamic layout, and the proportional setting of the wings 2 and the horizontal stabilizer 3 ensures flight balance and achieves stable operation of the target drone.

[0026] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A target drone device for unmanned aerial vehicle (UAV) training, characterized in that, include: The fuselage (1) and the wings (2), horizontal tail (3) and vertical tail (4) detachably mounted on the fuselage (1). The fuselage (1) is provided with mounting slots (8) for mounting the wings (2), horizontal tail (3) and vertical tail (4). The mounting slots (8) are provided with snap-fit ​​structures on the wings (2), horizontal tail (3) and vertical tail (4) to achieve the assembly of the wings (2), horizontal tail (3) and vertical tail (4). The mounting slot (8) is equipped with a clamping mechanism (12) for fastening the wing (2), horizontal stabilizer (3) and vertical stabilizer (4). The mounting slot (8) is also equipped with a quick-release mechanism (13) that abuts against the clamping mechanism (12). The clamping mechanism (12) and the quick-release mechanism (13) are used to position and remove the wing (2), horizontal stabilizer (3) and vertical stabilizer (4).

2. The target drone device for UAV training according to claim 1, characterized in that: The snap-fit ​​structure includes multiple sets of right-angle locking blocks (11) and multiple sets of right-angle locking slots (10). The multiple sets of right-angle locking blocks (11) are respectively inserted into the multiple sets of right-angle locking slots (10). The multiple sets of right-angle locking slots (10) are all opened at the ends of the wings (2), horizontal stabilizer (3) and vertical stabilizer (4). The multiple sets of right-angle locking blocks (11) are all fixedly connected to the bottom of the mounting slot (8).

3. The target drone device for UAV training according to claim 2, characterized in that: The mounting groove (8) has an inner groove (81) and storage grooves (84) and quick-release grooves (82) for mounting the clamping mechanism (12) and quick-release mechanism (13) are provided on both sides of the inner groove (81). A groove (83) for the clamping mechanism (12) to be inserted is provided between the storage groove (84) and the inner groove (81). The ends of the wing (2), horizontal tail (3) and vertical tail (4) are all fixedly connected with protrusions (9) that are inserted into the inner groove (81).

4. The target drone device for UAV training according to claim 3, characterized in that: The clamping mechanism (12) in both sets of storage slots (84) includes two sets of springs (123) and a base plate (121). Both sets of springs (123) are fixedly connected to one side of the base plate (121). The other end of the base plate (121) is fixedly connected to a locking block (122) located in the groove (83), and one side of the locking block (122) abuts against one side of the protrusion (9).

5. The target drone device for UAV training according to claim 4, characterized in that: The quick-release mechanism (13) includes a guide rod (133) and an internal hexagonal double-ended bolt (131) installed in the quick-release groove (82). Two sets of abutments (132) are slidably arranged on the guide rod (133), and the two sets of abutments (132) are respectively arranged at both ends of the internal hexagonal double-ended bolt (131).

6. The target drone device for UAV training according to claim 5, characterized in that: The fuselage (1) has multiple sets of hidden slots for mounting hexagonal double-sided bolts (131) on its outer side, and the wings (2) and the horizontal stabilizer (3) are set in equal proportion.

7. The target drone device for UAV training according to claim 1, characterized in that: The fuselage (1) has a head cover (5) at the head and an airspeed meter (6) installed on the head cover (5), and the fuselage (1) has a tail (7) at the tail.

8. The target drone device for UAV training according to claim 1, characterized in that: The horizontal stabilizer (3) is a rectangular planar structure. The horizontal stabilizer (3) has a 2-degree installation angle with the horizontal plane. The trailing edge of the horizontal stabilizer (3) is equipped with an elevator. The vertical stabilizer (4) adopts a symmetrical airfoil and a trapezoidal planar shape.

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