An integrated drone

Abstract

The present invention provides an integrated unmanned aerial vehicle, comprising: n basic configuration unmanned aerial vehicles (1) and n-1 integrated payload compartments (2); n is a positive integer greater than 1; the basic configuration unmanned aerial vehicle (1) is a flying wing unmanned aerial vehicle, two basic configuration unmanned aerial vehicles (1) are arranged side by side, and the adjacent winglets of the two basic configuration unmanned aerial vehicles (1) are fixedly connected; the front end face of the integrated payload compartment (2) has the same shape as the front end face of the basic configuration unmanned aerial vehicle (1), and the rear end face of the integrated payload compartment (2) covers the adjacent wings (12) of the two basic configuration unmanned aerial vehicles (1); the cross section of the integrated payload compartment (2) is airfoil-shaped. By connecting two basic configuration unmanned aerial vehicles through the integrated payload compartment, a larger integrated unmanned aerial vehicle is formed, so that the wing loading of the unmanned aerial vehicle remains unchanged, and there is no need to additionally increase the strength and weight.

Description

Technical Field

[0001] The present invention belongs to the field of aviation technology, and particularly relates to an integrated unmanned aerial vehicle (UAV). Background Art

[0002] In the fields of UAVs, aircrafts, and vertical takeoff and landing aircrafts, the payload refers to fuel or batteries, lubricating oil, ammunition, goods, and other fuels and mission equipment carried during mission execution. Since the capacity of the payload is determined, in order to meet the requirements of different mission equipment or different flight ranges, the aircraft mainly adjusts the weight ratio of fuel or batteries to mission payloads to perform different missions.

[0003] At present, the method of adjusting the weight ratio of fuel or batteries to mission payloads can meet the requirements of different mission payload weights and different flight ranges. However, the designs of the fuel (battery) compartment and the mission payload compartment both adopt a relatively large space design, making it impossible to customize and optimize the aircraft in terms of volume and weight according to the payload and fuel requirements of different missions. That is, in the reconnaissance mission with a small payload and a long flight range, it is impossible to reduce the size of the mission payload compartment to reduce drag and improve flight efficiency, and at the same time, it is also impossible to reduce the weight of the redundant mission payload compartment structure. Similarly, in the mission with a large payload, there is also a certain waste of fuel tank space.

[0004] In addition, there are external-mounted payload compartments or auxiliary fuel tanks, etc. These mainly increase the payload or fuel by adding external-mounted mission payloads or fuels to improve the payload-carrying capacity or flight time and range. However, this external-mounted payload compartment only undergoes drag reduction treatment and cannot provide lift for the increased external weight. As a result, the wing loading of the aircraft increases, requiring the wings of the aircraft to be strengthened additionally. This causes the aircraft body to be too heavy during ordinary missions (i.e., when no external payload is required), resulting in reduced efficiency. Summary of the Invention

[0005] The present invention provides an integrated UAV to solve the problem that the existing payload compartment cannot be adjusted.

[0006] The present invention provides an integrated UAV, including: n basic configuration UAVs 1 and n - 1 integrated payload compartments 2; n is a positive integer greater than 1;

[0007] The basic configuration UAV 1 is a flying wing UAV. Two basic configuration UAVs 1 are arranged side by side, and the adjacent winglets at the wing tips of the two basic configuration UAVs 1 are fixedly connected;

[0008] The front end face of the integrated payload compartment 2 has the same shape as the front end face of the basic configuration UAV 1, and the rear end face of the integrated payload compartment 2 covers the adjacent wings 12 of the two basic configuration UAVs 1;

[0009] The cross-section of the integrated payload compartment 2 is in an airfoil shape.

[0010] Optionally, a plurality of combined access covers 17 are provided on the skins of the upper and lower surfaces of the wing 12 of the basic configuration UAV 1;

[0011] Each of the combined access covers 17 is located behind the connecting wing beam 18 of the wing 12, and the connecting wing beam 18 is a wing beam located at the middle position of the chord length of the wing 12;

[0012] A locking head 19 is provided inside the combined access cover 17;

[0013] A plurality of connectors 25 are provided on the rear end face of the integrated payload compartment 2. When the integrated payload compartment 2 covers the wing 12, the connectors 25 pass through the combined access covers 17 and are locked with the locking heads 19.

[0014] Optionally, a positioning magnet 191 is further provided inside the combined access cover 17, and an electromagnetic positioning block 26 is provided at the tail of the connector 25.

[0015] Optionally, the integrated payload compartment 2 includes: a payload compartment 21, a wing-body fusion 22, and an integrated installation groove 23;

[0016] The interior of the wing-body fusion 22 is the payload compartment 21, or the payload compartment 21 is provided,

[0017] An integrated installation groove 23 is provided on the rear end face, and the concave surface of the integrated installation groove 23 matches the leading edge profile of the wing of the basic configuration UAV 1.

[0018] Optionally, a vertical tail cover 24 is provided at the tail of the integrated payload compartment 2;

[0019] The vertical tail cover 24 is used to integrally cover the adjacent winglet tips of two basic configuration UAVs 1 to form an integral vertical tail.

[0020] Optionally, the locking head 19 and the connector 25 are in a hook shape. The locking head 19 is rotatably connected to the connecting wing beam 18, and the connector 25 is rotatably connected to the rear end face of the integrated payload compartment 2.

[0021] Optionally, the cross-section of the integrated payload compartment 2 when covering the wing 12 of the basic configuration UAV 1 is in an airfoil shape.

[0022] Optionally, the basic configuration UAV 1 includes: a fuselage 11, a wing 12, winglets 13, a propulsion propeller 14, a reconnaissance device 15, and control surfaces 16;

[0023] Fuel or a battery and system equipment are provided inside the fuselage 11. The wings 12 are installed on both sides of the fuselage 11. Control surfaces 16 are installed on the wings 12. Winglets 13 are installed at the tips of the wings 12. The propulsion propeller 14 is installed at the rear of the fuselage, and the reconnaissance device 15 is installed below the front of the fuselage 11.

[0024] The present invention provides an integrated unmanned aerial vehicle, comprising: n basic configuration unmanned aerial vehicles 1 and n - 1 integrated payload compartments 2; n is a positive integer greater than 1; the basic configuration unmanned aerial vehicle 1 is a flying wing unmanned aerial vehicle, two basic configuration unmanned aerial vehicles 1 are arranged side by side, and the winglets at the adjacent wingtips of the two basic configuration unmanned aerial vehicles 1 are fixedly connected; the front end face of the integrated payload compartment 2 has the same shape as the front end face of the basic configuration unmanned aerial vehicle 1, and the rear end face of the integrated payload compartment 2 covers the adjacent wings 12 of the two basic configuration unmanned aerial vehicles 1; the cross section of the integrated payload compartment 2 is airfoil-shaped. By means of the cooperative operation of unmanned aerial vehicles, when performing a reconnaissance mission, smaller basic configuration unmanned aerial vehicles are adopted, and a customized large fuel tank and small reconnaissance equipment are used to perform the mission, optimizing the mission efficiency. When performing a large payload mission, two basic configuration unmanned aerial vehicles are connected by the integrated payload compartment to form a larger integrated unmanned aerial vehicle to perform a customized mission of carrying an integrated mission payload; and the payload compartment adopts an integrated design and is integrated with the basic unmanned aerial vehicle to become an integrated unmanned aerial vehicle with a larger wing area, so that the wing loading of the unmanned aerial vehicle remains unchanged, and there is no need to additionally increase the strength and weight, and high mission efficiency is maintained both in individual use and combined use, achieving that a single unmanned aerial vehicle can achieve multiple heavyweight unmanned aerial vehicle missions through combination and comprehensively optimizing the mission efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 is a schematic structural diagram of the basic configuration unmanned aerial vehicle provided by the present invention Figure 1 ;

[0026] Figure 2 is a schematic structural diagram of the basic configuration unmanned aerial vehicle provided by the present invention Figure 2 ;

[0027] Figure 3 is a schematic structural diagram of the basic configuration unmanned aerial vehicle provided by the present invention Figure 3 ;

[0028] Figure 4 is a schematic structural diagram of the integrated payload compartment provided by the present invention;

[0029] Figure 5 is a schematic structural diagram of the integrated unmanned aerial vehicle provided by the present invention Figure 1 ;

[0030] Figure 6 is Figure 5 an enlarged schematic diagram of part A in

[0031] Figure 7 is Figure 5 a sectional view taken along plane BB in

[0032] Figure 8 is a schematic structural diagram of the locking head;

[0033] Figure 9 It is a schematic structural diagram of the connection head;

[0034] Figure 10 It is a schematic structure of the integrated unmanned aerial vehicle provided by the present invention Figure 2 ;

[0035] Explanation of reference numerals:

[0036] 1 - Basic configuration unmanned aerial vehicle; 2 - Integrated payload compartment;

[0037] 11 - Fuselage; 12 - Wing;

[0038] 13 - Winglet; 14 - Propulsion propeller;

[0039] 15 - Reconnaissance equipment; 16 - Control surface;

[0040] 17 - Composite hatch; 18 - Connecting wing beam;

[0041] 19 - Locking head; 191 - Positioning magnet;

[0042] 21 - Payload compartment; 22 - Wing - body fusion;

[0043] 23 - Integrated installation groove; 24 - Vertical tail cover;

[0044] 25 - Connection head; 26 - Electromagnetic positioning block. Specific implementation manners

[0045] The integrated unmanned aerial vehicle provided by the present invention will be explained below with reference to the accompanying drawings.

[0046] The present invention optimizes the mission efficiency by means of unmanned aerial vehicle cooperative operation. When performing reconnaissance missions, a smaller basic configuration unmanned aerial vehicle is used, and a customized large fuel tank and small reconnaissance equipment are used to perform the mission. When performing large - payload missions, two basic configuration unmanned aerial vehicles are connected by an integrated payload compartment to form a larger integrated unmanned aerial vehicle to perform customized missions carrying integrated mission payloads; and the payload compartment adopts an integrated design and is integrated with the basic unmanned aerial vehicle to form an integrated unmanned aerial vehicle with a larger wing area, so that the wing loading of the unmanned aerial vehicle remains unchanged, without the need to additionally increase strength and weight, and high mission efficiency is maintained both in individual use and combined use, achieving that an unmanned aerial vehicle can achieve multiple - weight - class unmanned aerial vehicle missions through combination and comprehensively optimizing the mission efficiency.

[0047] As Figure 5 shown, the present invention provides an integrated unmanned aerial vehicle, including: a basic configuration unmanned aerial vehicle 1 and an integrated payload compartment 2.

[0048] Specifically, two basic configuration unmanned aerial vehicles 1 can be integrated into a larger unmanned aerial vehicle through the integrated payload compartment 2, realizing flexible configuration of small payload and large payload tasks, and can be customized and optimized according to different payloads and fuel weights. When the payload is small, lightweight basic configuration unmanned aerial vehicles are used to improve economy. When the payload is large, the integrated payload compartment is used for customization and optimization, and it can be extended to multi-aircraft joint operations to realize flexible matching and use of various weight payloads.

[0049] As Figures 1 - 3 and Figure 8 shown, the basic configuration unmanned aerial vehicle 1 includes: fuselage 11, wings 12, winglets 13, propulsion propellers 14, reconnaissance equipment 15, control surfaces 16, combined covers 17, as well as connecting wing beams 18, locking heads 19, and positioning magnets 191.

[0050] Fuel or batteries and system equipment are installed inside the fuselage 11. The wings 12 are installed on both sides of the fuselage 11. Control surfaces 16 are installed on the wings 12 to provide attitude control functions for the aircraft. Winglets 13 are installed at the tips of the wings 12 to improve course stability. Propulsion propellers 14 are installed at the rear of the fuselage to provide propulsion force. Reconnaissance equipment 15 is installed below the front of the fuselage 11 for reconnaissance.

[0051] The connecting wing beam 18 is arranged along the position with a larger thickness of the wing 12 in the wingspan direction to transmit the main wing aerodynamic force;

[0052] There are more than 2 combined covers 17, which are opened on the skin of the wing 12, arranged in the wingspan direction behind the connecting wing beam 18, and are opened when the unmanned aerial vehicle and the payload compartment are combined, and are usually closed and conformal with the wing skin.

[0053] The locking heads 19 are arranged at the upper and lower ends of the connecting wing beam 18 and are used to lock the connection joints of the integrated payload compartment, and can be rotated to open or lock; the positioning magnets 191 are arranged behind the combined covers 17 and are used to attract the electromagnets on the connection joints of the integrated payload compartment to assist in the relative positioning of the unmanned aerial vehicle and the payload compartment, speed up the combination process, and improve efficiency.

[0054] As Figure 4 and Figure 9As shown in the figure, the integrated payload bay 2 includes a payload bay 21, a wing-body fusion 22, an integrated installation groove 23, a vertical tail cover 24, a connector 25, and an electromagnetic positioning block 26. The payload bay 21 can be customized for various tasks according to different missions. The wing-body fusion 22 is on both sides of the payload bay 21, providing mechanical connection functions and can be integrated with the basic configuration UAV to form a new and larger wing-body fusion, providing additional lift to support the weight of the payload bay. The integrated installation groove 23 is used to relatively position and lock the basic configuration UAV 1 and the integrated payload bay 2 to form a whole. The mechanism and one side wing of the basic configuration UAV 1 are inserted into the integrated installation groove 23. The connector 25 is arranged at the rear of the integrated installation groove 23, and it abuts against the connecting wing beam 18 of the basic configuration UAV 1 by rotation and is locked by the locking head 19. The vertical tail cover 24 is used to integrally cover and wrap the adjacent winglet tips 13 of two basic configuration UAVs 1 to form an integral vertical tail. The electromagnetic positioning block 26 is arranged at the tail of the connector 25 and corresponds to the positioning magnet 191. It can form a corresponding magnetic field through energization and attract each other with the positioning magnet 191 to achieve the positioning effect. While positioning, the rotation of the connector 25 and the action of abutting against the connecting wing beam 18 are completed.

[0055] As Figures 5 - 7 shown, when realizing the combination of the basic configuration UAV 1 and the integrated payload bay 2, the basic connection is to form a UAV with a larger integrated wing-body fusion by combining two basic configuration UAVs 1 and one integrated payload bay 2. By assembling the basic configuration UAV 1 into the integrated installation groove 23 of the integrated payload bay 2, through the mutual positioning and attraction of the electromagnetic positioning block 25 and the positioning magnet 191, the connector 25 abuts against the connecting wing beam 18 of the basic configuration UAV 1 by rotation, and the locking head 19 rotates and locks, so that the UAV and the payload bay form a whole. At the same time, the aerodynamic shape of the payload bay is integrated with the aerodynamic shape of the wing to form a new airfoil. The vertical tail cover 24 of the integrated payload bay 2 abuts backward, and the two adjacent winglet tips 13 are integrally abutted and positioned and locked by magnetic attraction or mechanical devices, and are wrapped outside them, so that the two winglet tips form an integral vertical tail, and the basic configuration UAV 1 and the integrated payload bay 2 form an integrated UAV for a larger wing area.

[0056] During the integration process, the connector 25 first rotates and flips up so that the fuselage and the front part of the wing of the basic configuration UAV 1 can enter the integrated installation groove 23. Then, the position is determined by the attraction between the electromagnetic positioning block 26 and the positioning magnet 191, and the connector 25 is attracted and flipped downward. At the same time, the combined hatch 17 is opened. The connector rotates and drops with the magnetic attraction and abuts against the connecting wing beam 18. At this time, the locking head 19 flips upward to lock the connector 25, so that the basic configuration UAV 1 and the integrated payload bay 2 are physically connected and locked, and the locking position is at the advantageous position of the load transfer of the wing, which is beneficial to improving the load transfer efficiency of the aircraft.

[0057] Multiple positioning magnets are required during positioning, and their magnetic poles are staggered with each other, which is conducive to error-proof processing during docking and improves the docking efficiency.

[0058] As Figure 10 shown, this combination method can be widely used to support multiple drones to be combined into a larger-sized drone for use.

[0059] When the basic configuration drone 1 is used alone, the flight attitude adjustment method is as follows: the pitch attitude adjustment is achieved by the simultaneous upward or downward deflection of the control surfaces; the roll attitude adjustment is achieved by the reverse deflection adjustment of the control surfaces; the yaw attitude is achieved by the method of deflecting a single-side control surface, that is, the control surface on the target turning side deflects upward to obtain a downward and backward force, so that the drone deflects the heading with a bank angle to complete the yaw maneuver. When the drones are used in combination, the control surfaces are divided into left and right groups along the aircraft symmetry plane, and the flight attitude adjustment can be achieved by using a similar maneuver to that of the drone flying alone.

[0060] A combined drone proposed by the present invention integrates two basic configuration drones 1 into a larger drone through the integrated payload compartment 2, realizes the customized optimization transportation of the integrated payload task, and can use a single lightweight basic configuration drone to perform tasks when the payload is small to improve the economy.

[0061] The integrated payload compartment 2 of the present invention can be customized according to different tasks, provides the mechanism connection function through the wing-body fusion 22 and can be fused with the basic configuration drone to form a wing-body fusion, realizes the external shape fusion of the integrated drone while providing the connection and bearing function, improves the flight efficiency, and bears the wing surface load of the wing, so that the wing does not need to increase the wing area or wing strength like the traditional external hanging payload compartment, reducing the weight of the drone and improving the efficiency.

[0062] The payload compartment and the drone of the present invention form a larger wing-body fusion, reducing the drag of the payload compartment and improving the flight efficiency; at the same time, the vertical tail cover 24 integrates and abuts two adjacent winglet tips 13 and wraps them on the outside to form an integral vertical tail, reducing the flight drag and further improving the flight efficiency.

Claims

1. An integrated unmanned aerial vehicle, characterized in that, Including: n basic configuration unmanned aerial vehicles (1) and n - 1 integrated payload compartments (2); n is a positive integer greater than 1; The basic configuration unmanned aerial vehicle (1) is a flying wing unmanned aerial vehicle. Two basic configuration unmanned aerial vehicles (1) are arranged side by side, and the adjacent winglet tips of the two basic configuration unmanned aerial vehicles (1) are fixedly connected; The front end face shape of the integrated payload compartment (2) is consistent with the front end face of the basic configuration unmanned aerial vehicle (1). The rear end face of the integrated payload compartment (2) covers the adjacent wings (12) of the two basic configuration unmanned aerial vehicles (1); The cross section of the integrated payload compartment (2) is airfoil-shaped; On the skins of the upper and lower surfaces of the wing (12) of the basic configuration unmanned aerial vehicle (1), a plurality of combined access covers (17) are provided; Each of the combined access covers (17) is located behind the connecting wing beam (18) of the wing (12). The connecting wing beam (18) is a wing beam located at the middle position of the chord length of the wing (12); A locking head (19) is arranged inside the combined access cover (17); A plurality of connecting heads (25) are arranged on the rear end face of the integrated payload compartment (2). When the integrated payload compartment (2) covers the wing (12), the connecting heads (25) pass through the combined access covers (17) and lock with the locking heads (19); The locking head (19) and the connecting head (25) are hook-shaped. The locking head (19) is rotatably connected to the connecting wing beam (18), and the connecting head (25) is rotatably connected to the rear end face of the integrated payload compartment (2); The locking head (19) and the connecting head (25) adopt an up-and-down double-layer docking method; A vertical tail cover (24) is arranged at the tail of the integrated payload compartment (2); The vertical tail cover (24) is used to integrally cover the adjacent winglet tips of the two basic configuration unmanned aerial vehicles (1) to form an integral vertical tail.

2. The integrated drone according to claim 1, wherein A positioning magnet (191) is further arranged inside the combined access cover (17), and an electromagnetic positioning block (26) is arranged at the tail of the connecting head (25).

3. The integrated drone according to claim 1, wherein The integrated payload compartment (2) includes: a payload compartment (21), a wing-body fusion (22), and an integrated installation groove (23); Inside the wing-body fusion (22) is the payload compartment (21), or there is a payload compartment (21) arranged; An integrated installation groove (23) is arranged on the rear end face, and the concave surface of the integrated installation groove (23) matches the leading edge shape of the wing of the basic configuration unmanned aerial vehicle (1).

4. The integrated drone according to claim 1, characterized in that, When the integrated payload compartment (2) covers the wing (12) of the basic configuration unmanned aerial vehicle (1), the cross section is airfoil-shaped.

5. The integrated drone according to claim 1, wherein The basic configuration unmanned aerial vehicle (1) includes: a fuselage (11), a wing (12), winglet tips (13), a propulsion propeller (14), a reconnaissance device (15), and a control surface (16); Fuel or a battery and system equipment are arranged inside the fuselage (11). The wing (12) is installed on both sides of the fuselage (11). A control surface (16) is installed on the wing (12). The winglet tips (13) are installed at the tips of the wing (12). The propulsion propeller (14) is installed at the rear of the fuselage, and the reconnaissance device (15) is installed below the front of the fuselage (11).

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