A conical rod and sleeve type airborne assembly and disassembly device

Abstract

The utility model belongs to the technical field of aircraft structure design, provide a kind of conical rod conical sleeve type air combination separation device, including conical rod device (2) and conical sleeve device (4), respectively install in unmanned aerial vehicle 1 (1) one side wing tip end rib or unmanned aerial vehicle 3 (3) other side wing tip end rib, the conical rod device (2) is conical structure, and conical rod device (2) is provided with lock catch groove;The conical sleeve device (4) is conical sleeve structure, and conical sleeve device (4) is provided with lock catch in corresponding position, and it is locked or separated with conical rod device (2) and is engaged, realizes the air combination and separation of two or more unmanned aerial vehicles.This utility model can be used for the docking combination and separation of two or more unmanned aerial vehicles in the air, solves the technical problems, such as big space error range, big position fluctuation, difficult docking and easy collision between unmanned aerial vehicles.

Description

Technical Field

[0001] This utility model relates to the field of aircraft structural design technology, specifically to a conical rod-conical sleeve type aerial combination and separation device. Background Technology

[0002] In recent years, unmanned aerial vehicles (UAVs) have been developing towards intelligence, swarming, and human-machine collaboration. However, payload and endurance issues have limited the flight distance, deployment range, and combat capabilities of UAVs. Aerial autonomous docking technology enables two or more UAVs to dock, combine, and separate in mid-air, connecting multiple UAVs to form a cluster of aircraft with a larger aspect ratio and scale, endowing them with new capabilities or enhancing mission effectiveness. This effectively improves UAV endurance, expands combat radius, increases payload capacity, and enhances deployment efficiency, making it a crucial technology for the future development of UAVs.

[0003] Among these, the assembly and separation mechanism is one of the core components of aerial assembly and separation. Spacecraft aerial assembly and separation technology is relatively mature, with various assembly and separation mechanism schemes developed, including robotic arm type, novel electromagnetic type, three-pronged type, and flexible type. However, UAVs fly under atmospheric disturbances, and the turbulence at the aircraft's tail is both steady-state and unsteady, placing higher demands on assembly and separation. Aerospace-grade assembly and separation mechanisms cannot meet the aerial docking requirements of UAVs. For example, robotic arm-type docking mechanisms are complex and require excessively high attitude control; electromagnetic docking mechanisms lack long-distance docking capabilities and require excessively high mechanism control precision; three-pronged docking mechanisms have excessively high control requirements, demanding very low relative speed and angular velocity of the aircraft. Compared to spacecraft, UAVs experience greater airflow disturbances and a wider range of spatial position fluctuations, making aerial docking and separation relatively difficult. Currently, due to the large range of spatial errors and position fluctuations between UAVs, technical problems such as difficulty in alignment and easy collisions arise during docking, and no better technical means suitable for the dynamic aerial assembly and separation of UAVs have emerged. Summary of the Invention

[0004] This utility model discloses a cone-shaped aerial combination and separation device, which can be used for docking and separation of two or more UAVs in the air. It solves the technical problems of difficult docking and easy collision between UAVs due to large spatial error range, large position fluctuation.

[0005] This invention proposes a cone-shaped aerial combination and separation device, comprising a cone-shaped device 2 and a cone-shaped device 4, which are respectively installed on the wingtip rib of one side of the unmanned aerial vehicle 1 and the wingtip rib of the other side of the unmanned aerial vehicle 3. The cone-shaped device 2 has a cone-shaped structure and is provided with a locking groove; the cone-shaped device 4 has a cone-shaped sleeve structure and is provided with a locking buckle at a corresponding position, which can be fitted and locked with the cone-shaped device 2 or separated to realize the aerial combination and separation of two or more unmanned aerial vehicles.

[0006] Furthermore, the tapered rod device 2 includes a tapered rod mounting plate 21, a tapered rod 22, a locking groove 23, and a tapered shaft 24; the tapered rod mounting plate 21 is fixedly connected to the wingtip of the aircraft 1, the tapered rod 22 is tapered and is installed on the outer end face of the tapered rod mounting plate 21, the locking groove 23 is symmetrically distributed on the upper and lower conical surfaces of the tapered rod 22, and the tapered shaft 24 is a tapered positioning shaft, fixed to the rear end of the tapered rod mounting plate 21.

[0007] Furthermore, there are two tapered shafts 24, which are symmetrically arranged on the upper and lower ends of the tapered rod mounting plate 21.

[0008] Furthermore, the cone rod 22 and the cone rod mounting plate 21 form an integral whole and are connected to the wingtip on one side of the unmanned aerial vehicle 11 by a constant force screw connection. The cone head of the cone rod 22 is equipped with a contact switch 25.

[0009] Furthermore, the conical shaft 24 is a conical structure fixed on the conical rod mounting plate 21, used to cooperate with the conical hole 46 on the conical sleeve mesh 42 to achieve positioning and locking.

[0010] Furthermore, the conical sleeve device 4 includes a mounting plate 41, a conical sleeve mesh 42, a conical sleeve head 43, a latch 44, a latch support 45, and a conical hole 46; wherein the mounting plate 41 is connected to the wingtip rib of the unmanned aerial vehicle 33 by a fixed-force screw connection, and a conical sleeve head 43 is provided at the outer end; the end of the conical sleeve head 43 that connects to the conical sleeve mesh 42 has four mounting bosses 1 47 evenly distributed around it, which are fixedly connected to the conical sleeve mesh 42; the latch 44 is a flat plate structure with a hook, which is hinged to the latch support 45; the conical hole 46 is a conical inner hole structure fixed on the conical sleeve head 43, which is used to cooperate with the conical shaft 24 on the conical rod 22.

[0011] Furthermore, the mounting plate 41, the conical sleeve head 43, and the conical hole 46 form the front section of the conical sleeve, which is used to fit and transmit force with the conical rod and to accurately position it; the conical sleeve mesh 42 and the mounting boss 2 48 form the rear section of the conical sleeve, which is used to guide the conical rod device 2.

[0012] Furthermore, the conical sleeve 43 is a conical sleeve with grooves on the top, bottom, and outer sides to facilitate the insertion of the locking buckle 44 and the conical rod 22. The outer rear end of the conical sleeve 43 is provided with two conical holes 46 for cooperating with the conical shaft 24 on the conical rod mechanism.

[0013] Furthermore, the conical sleeve 42 is a mesh conical sleeve structure, which reduces air resistance through the mesh holes and allows the guide cone rod 22 to fit with the conical sleeve 42 in a large space. The conical sleeve 42 has four mounting bosses 2 48 evenly distributed around its end, which are connected to the conical sleeve head 43 by bolts.

[0014] Beneficial effects of the invention This invention provides a small-sized structure for aerial docking of two or more unmanned aerial vehicles (UAVs). It solves the technical problem of large spatial error ranges and significant positional fluctuations between UAVs, which lead to difficult docking and a high risk of collisions. Specific benefits are as follows: 1. The aerial combination and separation mechanism of this utility model includes a cone rod and a cone sleeve, which can accurately realize the combination and separation of two or more UAVs in the air.

[0015] 2. In the aerial assembly and separation mechanism of this utility model, the cone rod has grooves at the top and bottom, into which a locking buckle can be inserted to fix the mechanism. The conical mandrel is installed on the wingtip plate frame, which can lock the device after the aircraft is assembled.

[0016] 3. In the aerial combination and separation mechanism of this utility model, the cone rod and cone sleeve are installed with the wings of the lead and wingmen through the constant force bolts on the mounting plate, so as to automatically disconnect and detach when the load exceeds the bearing capacity, thereby avoiding damage to the wings during the combination and separation process and causing flight accidents. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the docking and separation process of this utility model; Figure 2 This is a detailed structural diagram of the tapered rod device of this utility model; Figure 3 This is a detailed structural diagram of the conical sleeve device of this utility model; Figure 4 This is a schematic diagram of the combined state of the cone rod and cone sleeve of this utility model; Figure 5 This is a schematic diagram of the separation process of the cone rod and cone sleeve of this utility model; Among them, 1—unmanned aerial vehicle 1, 3—unmanned aerial vehicle 3; 2—Cone rod mechanism, 21—Mounting plate, 22—Cone rod, 23—Locking groove, 24—Cone shaft, 25—Contact switch; 4—tapered sleeve mechanism; 41—mounting plate; 42—tapered sleeve mesh; 43—tapered sleeve head; 44—lock; 45—lock support; 46—tapered hole; 47—mounting boss 1; 48—mounting boss 2. Detailed Implementation

[0018] To enhance understanding of this utility model, it will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0019] like Figures 1-5As shown, a cone-shaped aerial combination and separation device includes a cone-shaped device 2 and a cone-shaped device 4, which are respectively installed on the wingtip rib of one side of the unmanned aerial vehicle 11 and the wingtip rib of the other side of the unmanned aerial vehicle 33. The cone-shaped device 2 has a cone-shaped structure and is provided with a locking groove. The cone-shaped device 4 has a cone-shaped sleeve structure and is provided with a locking buckle at a corresponding position. It can be fitted and locked with the cone-shaped device 2 or separated to realize the aerial combination and separation of two or more unmanned aerial vehicles.

[0020] like Figure 2 As shown, the tapered rod device 2 includes a tapered rod mounting plate 21, a tapered rod 22, a locking groove 23, and a tapered shaft 24; the tapered rod mounting plate 21 is fixedly connected to the wingtip of the aircraft 1, the tapered rod 22 is tapered and is installed on the outer end face of the tapered rod mounting plate 21, the locking groove 23 is symmetrically distributed on the upper and lower conical surfaces of the tapered rod 22, and the tapered shaft 24 is a tapered positioning shaft, fixed to the rear end of the tapered rod mounting plate 21.

[0021] Two conical shafts 24 are provided, which are symmetrically arranged on the upper and lower rear ends of the conical rod mounting plate 21.

[0022] The cone rod 22 and the cone rod mounting plate 21 form an integral whole and are connected to the wingtip on one side of the unmanned aerial vehicle 11 by a constant force screw connection. The cone head of the cone rod 22 is equipped with a contact switch 25.

[0023] The conical shaft 24 is a conical structure fixed on the conical rod mounting plate 21, used to cooperate with the conical hole 46 on the conical sleeve mesh 42 to achieve positioning and locking.

[0024] like Figure 3 As shown, the conical sleeve device 4 includes a mounting plate 41, a conical sleeve mesh 42, a conical sleeve head 43, a locking buckle 44, a locking buckle support 45, and a conical hole 46. The mounting plate 41 is connected to the wingtip rib of the unmanned aerial vehicle 33 by a fixed-force screw connection, and a conical sleeve head 43 is provided at its outer end. The end of the conical sleeve head 43 that connects to the conical sleeve mesh 42 has four mounting bosses 1 47 evenly distributed around its circumference, which are fixedly connected to the conical sleeve mesh 42. The locking buckle 44 is a flat plate structure with a hook, which is hinged to the locking buckle support 45. The conical hole 46 is a conical inner hole structure fixed on the conical sleeve head 43, which is used to cooperate with the conical shaft 24 on the conical rod 22.

[0025] The mounting plate 41, the tapered sleeve head 43, and the tapered hole 46 form the front section of the tapered sleeve, which is used to fit and transmit force with the tapered rod and to accurately position it; the tapered sleeve mesh 42 and the mounting boss 2 48 form the rear section of the tapered sleeve, which is used to guide the tapered rod device 2.

[0026] The conical sleeve 43 is a conical sleeve with grooves on the top, bottom and outer sides to facilitate the insertion of the locking buckle 44 and the conical rod 22. The outer rear end of the conical sleeve 43 is provided with two conical holes 46 for cooperating with the conical shaft 24 on the conical rod mechanism.

[0027] The conical sleeve 42 is a mesh conical sleeve structure. The mesh reduces air resistance and allows the guide cone rod 22 to fit against the conical sleeve 42 in a large space. The conical sleeve 42 has four mounting bosses 2 48 evenly distributed around its end, which are connected to the conical sleeve head 43 by bolts.

[0028] like Figure 1 , Figures 4-5 As shown, the main functional performance of the cone-shaped aerial combination and separation mechanism of this utility model includes: (1) It can provide a certain guiding capability during docking to reduce the accuracy requirements of position adjustment between the two aircraft, and reduce the measurement accuracy requirements of the position measurement system and the control accuracy requirements of the dual-aircraft control system; (2) It has sufficient reliability, is easy to lock, and has excellent locking capability in all three axes after locking, and is not easy to loosen; when multiple aircraft are combined, it is necessary to consider using the connection mechanism to transmit force, so it is required to be interconnected with the internal structure of the wing to achieve reliable force transmission; (3) It can quickly detach when it needs to detach, without causing secondary damage; (4) In case of emergency, exceeding the design torque, or under stress, it can self-damage without damaging the structure of the wing and affecting the safety of the entire aircraft; (5) The locking time of the docking mechanism is 0.2s; (6) The detachment time is 0.2s; (7) The bending moment resistance of the docking mechanism is 2Nm; (8) The torque resistance is 3Nm; (9) The weight is 0.8kg.

[0029] This utility model discloses a cone-rod cone-sleeve type aerial assembly and separation device, which is used in the aircraft assembly and separation process as follows: When combining, such as Figure 4 As shown, an aircraft equipped with a cone-rod mechanism accelerates forward to approach an aircraft equipped with a cone sleeve while maintaining a flight path in which the cone rod and cone sleeve are basically coaxial. During the approach and combination process, the cone rod is guided forward to engage by the cone net at the tail of the cone sleeve. After the cone rod contacts the latch, it squeezes the locking hook to deflect until the latch and locking groove are fully engaged and pressed into the locking groove, thus locking the two aircraft. At the same time, the contact switch at the head of the cone rod is squeezed, sending a combination completion signal to the flight control computer, and the aircraft enters the combination state flight control.

[0030] When separated, such as Figure 5 As shown, an aircraft equipped with a cone sleeve mechanism accelerates forward and detaches from the aircraft equipped with the cone sleeve while maintaining a flight path in which the cone rod and the cone sleeve are basically coaxial. During the detachment process, the cone rod is guided to detach backward by the cone net at the tail of the cone sleeve. After the cone rod contacts the latch, it squeezes the latch to deflect and disengage from the locking groove, thereby unlocking the two aircraft. At the same time, the contact switch at the head of the cone rod is released from pressure, the flight control computer loses the positioning signal, and the aircraft switches to single-aircraft separation flight control.

[0031] Although preferred embodiments of this application have been described, those skilled in the art will recognize them upon observation. Having grasped the basic inventive concept, further changes and modifications can be made to these embodiments. Therefore, the scope of protection of this application is intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application. Obviously, those skilled in the art can make various alterations and variations to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of protection of this application and the like, this application also intends to include these modifications and variations.

Claims

1. A cone-rod cone-sleeve type aerial combined separation device, characterized in that, The device includes a cone rod device (2) and a cone sleeve device (4), which are respectively installed on the wingtip rib of one side of the unmanned aerial vehicle 1 (1) or the wingtip rib of the other side of the unmanned aerial vehicle 3 (3). The cone rod device (2) is a cone-shaped structure and is provided with a locking groove. The cone sleeve device (4) is a cone-shaped sleeve structure and is provided with a locking buckle at the corresponding position. It is engaged and locked or separated from the cone rod device (2) to realize the aerial combination and separation of two or more unmanned aerial vehicles.

2. The cone-rod cone-sleeve type aerial combined separation device according to claim 1, characterized in that... The cone rod device (2) includes a cone rod mounting plate (21), a cone rod (22), a locking groove (23), and a cone shaft (24); the cone rod mounting plate (21) is fixedly connected to the wingtip of the unmanned aerial vehicle 1 (1), the cone rod (22) is conical and is installed on the outer end face of the cone rod mounting plate (21), the locking groove (23) is symmetrically distributed on the upper and lower conical surfaces of the cone rod (22), and the cone shaft (24) is a conical positioning shaft, fixed at the rear end of the cone rod mounting plate (21).

3. The cone-rod cone-sleeve type aerial combined separation device according to claim 2, characterized in that... Two conical shafts (24) are provided, which are symmetrically arranged on the upper and lower ends of the conical rod mounting plate (21).

4. The cone-rod cone-sleeve type aerial combined separation device according to claim 2, characterized in that... The cone rod (22) and the cone rod mounting plate (21) form a whole and are connected to the wingtip on one side of the unmanned aerial vehicle 1 (1) by a constant force screw connection. The cone head of the cone rod (22) is equipped with a contact switch (25).

5. A cone-rod cone-sleeve type aerial combined separation device according to claim 2, characterized in that... The conical shaft (24) is a conical structure fixed on the conical rod mounting plate (21) and is used to cooperate with the conical hole (46) on the conical sleeve mesh (42) to achieve positioning and locking.

6. The cone-shaped aerial combined separation device according to claim 1, characterized in that... The cone sleeve device (4) includes a mounting plate (41), a cone sleeve net (42), a cone sleeve head (43), a latch (44), a latch support (45), and a cone hole (46); wherein the mounting plate (41) is connected to the wingtip rib of the unmanned aerial vehicle 3 (3) by a constant force screw connection, and a cone sleeve head (43) is provided at the outer end; the end of the cone sleeve head (43) connected to the cone sleeve net (42) has four mounting bosses 1 (47) evenly distributed around it, which are fixedly connected to the cone sleeve net (42); the latch (44) is a flat plate structure with a hook, which is hinged to the latch support (45); the cone hole (46) is a cone-shaped inner hole structure fixed on the cone sleeve head (43), which is used to cooperate with the cone shaft (24) on the cone rod (22).

7. A cone-rod cone-sleeve type aerial combined separation device according to claim 6, characterized in that... The mounting plate (41), the cone sleeve head (43), and the cone hole (46) form the front section of the cone sleeve, which is used to fit with the cone rod to transmit force and for precise positioning; the cone sleeve mesh (42) and the mounting boss 2 (48) form the rear section of the cone sleeve, which is used to guide the cone rod device (2).

8. A cone-rod cone-sleeve type aerial combined separation device according to claim 6, characterized in that... The conical sleeve (43) is a conical sleeve with grooves on the top, bottom and outer sides to facilitate the insertion of the buckle (44) and the conical rod (22). The outer side of the conical sleeve (43) has two conical holes (46) at the rear end for cooperating with the conical shaft (24) on the conical rod mechanism.

9. A cone-shaped aerial combined separation device according to claim 6, characterized in that... The cone sleeve mesh (42) is a mesh cone sleeve structure. The mesh holes reduce air resistance and allow the guide cone rod (22) to fit with the cone sleeve mesh (42) in a large space. The cone sleeve mesh (42) has four mounting bosses 2 (48) evenly distributed around the end, which are connected to the cone sleeve head (43) by bolts.

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