Modularized reconfigurable flying wing unmanned aerial vehicle based on coaxial double rotors and tilting power

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and provides a modular reconfigurable flying wing unmanned aerial vehicle based on coaxial double rotors and tilting power, the design adopts a flying wing layout in which a high aspect ratio wing of a glider and a wing body are fused, and the flying efficiency is effectively improved; the pod is modularized, so that airborne equipment can be conveniently replaced; the wings are detachable, so that the repair cost of the damaged wings of the aircraft can be effectively reduced, and meanwhile, vehicle-mounted transportation of individual users is facilitated; compared with a fully-fixed combined type aircraft, the power arrangement of the coaxial double rotors with the fixed front propellers and the tilting of the rear propellers reduces the redundant dead weight, is simpler in structure compared with a fully-tilting aircraft, and is better in drag reduction effect compared with the power arrangement of the coaxial double rotors with the fixed rear propellers and the tilting of the propellers on the two sides of the front propellers.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a modular reconfigurable flying wing UAV based on coaxial dual rotors and tilting rotational force. Background Technology

[0002] Conventional aerodynamic aircraft can be broadly classified into two categories: fixed-wing aircraft and rotary-wing aircraft. Fixed-wing aircraft offer advantages such as high speed, long range, low noise, and high payload capacity, but also suffer from high takeoff and landing costs and limited application areas. Rotary-wing aircraft are characterized by vertical takeoff and landing (VTOL) and hovering capabilities, but also have disadvantages such as short range and low payload. VTOL fixed-wing aircraft can take off and land vertically like helicopters, and can also maintain forward flight by relying on lift generated by their wings. The VTOL section allows the aircraft to hover without a runway, while the fixed-wing section ensures high aerodynamic efficiency, high speed, and long flight time during forward flight. VTOL fixed-wing aircraft thus avoid the disadvantages of both rotary-wing and fixed-wing aircraft while possessing the advantages of both.

[0003] A search revealed that CN110844062A discloses a modular multi-purpose compound-wing UAV, comprising a frame platform, a fuselage mounted on top of the frame platform, wings mounted on both sides of the frame platform, a flying-wing servo mounted on each wing, a landing gear and an arm mounted on each side of the bottom of the frame platform, and a tail arm mounted in the middle. The two landing gears and two arms are symmetrical about the center of the tail arm. One end of the tail arm is connected to a vector power unit, and the other end is connected to the frame platform via a folding component. Each vector power unit includes a tilting mechanism and a motor. This modular multi-purpose compound-wing UAV can perform special missions using its rotor unit alone, or it can connect the rotor unit and the flying-wing unit in parallel to form a bimodal compound-wing UAV, carrying different equipment to perform diverse missions according to mission requirements.

[0004] The content of the existing technical solution 1: Patent publication number CN110844062A A modular multi-purpose compound wing layout UAV

[0005] The features of Option 1 are: the power layout uses two tilting motors at the front and one tilting motor at the rear; the rotor section can be used independently.

[0006] Disadvantages of Option 1: The wings and fuselage are completely fixed, resulting in low modularity; all power is tilted, leading to a complex and heavy mechanism; the cabin has no openings, requiring complete disassembly for battery replacement / maintenance; and the flight range is fixed.

[0007] In summary, existing drone technology has the following pain points:

[0008] 1. Traditional multi-rotor drones have short flight times, while fixed-wing drones require runways for takeoff and landing.

[0009] 2. All power tilting mechanisms are complex and have high maintenance costs.

[0010] 3. Conventional drones have poor functional expandability and are difficult to adapt to different mission requirements.

[0011] 4. Existing modular designs are mostly concentrated on payload equipment, with low modularity of the flight platform itself. Utility Model Content

[0012] This invention proposes a modular reconfigurable flying wing UAV based on coaxial dual rotors and tilting rotational force, which is a modular UAV that combines vertical take-off and landing capability with efficient cruise performance and rapid reconfiguration capability.

[0013] The aircraft employs a high-aspect-ratio glider wing combined with a blended wing-body configuration, effectively improving flight efficiency. Modular pods allow for easy replacement of onboard equipment. Detachable wings reduce repair costs for damaged wings and facilitate vehicle transport for individual users. The coaxial twin-rotor configuration with a fixed front propeller and a tilting rear propeller reduces unnecessary "dead weight" compared to fully fixed compound aircraft, is structurally simpler than fully tilting aircraft, and offers better drag reduction compared to a coaxial twin-rotor configuration with a fixed rear propeller and tilting front propellers.

[0014] The technical solution of this utility model is as follows: a modular reconfigurable flying wing UAV based on coaxial dual rotor and tilting propulsion, including a wing-body blended flying wing body, the fuselage and wing being detachably connected; a modular pod, which is detachably installed on the bottom of the fuselage via a sliding rail mechanism and used as landing gear; a front fixed coaxial dual rotor system, including a motor power strut, a motor and a propeller; and a rear tilting propeller system, including a tilting servo, a motor and a propeller;

[0015] Preferably, the connection structure between the modular pod and the fuselage includes: a longitudinal slide rail at the bottom of the fuselage that cooperates with a slide groove at the top of the pod; a cable docking port at the front of the pod and a limiting positioning pin hole at the rear.

[0016] Preferably, the connection structure between the wing and the fuselage includes: two round beams extending from the fuselage and inserted into corresponding holes on the wing;

[0017] The inner side of the wing is equipped with a pin hook that locks with the fuselage clip, and the clip has a built-in spring limit button.

[0018] Preferably, two counter-rotating motor shafts drive a pair of mirror-symmetrical propellers; the motors are fixed to the head of the machine via motor power struts, which are integrally formed with the machine body.

[0019] Preferably, the rear tilt propeller system includes: a motor support base, which is hinged to the fuselage via a tilt servo; the motor is fixed on the support base, and the propeller thrust direction is adjustable.

[0020] Preferably, the wing has an internal beam-rib truss structure covered with a lightweight skin, and a segmented control surface at the trailing edge: the inner side is an elevator connected to the wing via a hinge; the outer side is an aileron connected to the wing via a hinge; and the wingtip tail is fixed to the wingtip.

[0021] Preferably, the connecting structure of the hatch includes: a hook-shaped structure at the rear that engages with a slot at the rear of the fuselage; and a spring buckle at the front that can be opened by pressing to unlock.

[0022] Preferably, the pod is a modular design and can be replaced with: a battery expansion pod, a cargo transport pod, or a mission equipment pod.

[0023] Preferably, the wing is a modular design and can be replaced with a high aspect ratio lift wing or a low drag high speed wing.

[0024] Preferably, the connection interfaces of the fuselage, wings and pods all adopt standardized mechanical and electrical interfaces to support quick assembly and disassembly;

[0025] Preferably, the aircraft's flight controller has two operating modes: vertical flight and fixed-wing flight. In vertical flight, the motor drives the propeller to generate upward thrust, enabling the aircraft to overcome gravity and climb or descend vertically. The two rear tilt servos deflect equally, and the motor speed increases, generating forward thrust while balancing gravity and pitch moment, which propels the aircraft forward. When the two rear tilt servos deflect unequally, the previously balanced anti-torque torque becomes unbalanced, and the difference is the control torque required for turning, thus turning the aircraft. When the servo motors are not deflecting, the front motor speed decreases while the rear motor speed increases, generating forward thrust that causes the aircraft to pitch down and move forward; conversely, it moves backward. When the speed of the two clockwise rotating motors decreases and the speed of the two counterclockwise rotating motors increases, a clockwise steering torque is generated, causing the aircraft to turn clockwise; conversely, it turns counterclockwise. When the speed of the front motor remains constant, and the speed of the rear left motor increases while the speed of the right motor decreases, a rightward roll torque is generated, causing the aircraft to roll to the right; conversely, it rolls to the left. Therefore, the aircraft has redundant control capabilities, making it more maneuverable than aircraft with single-control mechanisms.

[0026] Preferably, in fixed-wing flight, the motors drive the propellers to generate forward thrust, propelling the aircraft forward. Airflow over the wing surface generates lift, helping the aircraft overcome gravity and maintain flight. At this time, the aircraft's aerodynamic control efficiency is improved, and the aircraft controls its attitude via elevators, ailerons, and propulsion motors. Simultaneous upward deflection of both elevators causes the aircraft to pitch up, and vice versa. Deflection of the left aileron downward and the right aileron upward causes the aircraft to roll to the right, and vice versa. Increased speed of the left propulsion motor and decreased speed of the right propulsion motor cause the aircraft to yaw to the left, and vice versa.

[0027] The beneficial effects of this utility model are as follows:

[0028] The aircraft's pods feature a modular design, allowing it to quickly adapt to different mission requirements. For example, a high-resolution camera module can be carried for reconnaissance missions; additional batteries can be added to extend the flight range for logistics missions; and an emergency supplies release module can be carried for search and rescue missions.

[0029] The aircraft's wings are also modularly designed, allowing the aircraft's aerodynamic characteristics to be adjusted according to mission requirements. For example, when mission payload is emphasized, a larger wing area can be used, while when mission speed is emphasized, a wing with less drag can be used. It is even possible to replace the wings with solar-coated ones to greatly increase the flight time.

[0030] Features:

[0031] Each functional module uses standardized mechanical interfaces with mortise and tenon joints and snap-locking mechanisms.

[0032] The unified electrical interface protocol includes power, signal, and data buses;

[0033] Installation, disassembly, and replacement can be completed in minutes.

[0034] Advantages:

[0035] Scalability: The modular design allows the drone's functionality to be expanded by adding different modules. Users can purchase different modules as needed without replacing the entire drone.

[0036] Easy maintenance: The modular design makes drone maintenance and repair easier. Damaged modules can be quickly replaced, reducing maintenance time and costs.

[0037] Convenient transportation: The modular design of the wings makes the transportation of drones more convenient.

[0038] Cost-effectiveness: Modular design reduces production and maintenance costs. Different modules can be manufactured separately, lowering overall production costs. Furthermore, modular design extends the drone's lifespan, reducing the total cost of ownership.

[0039] In the military field: Modular flying-wing UAVs can be used for reconnaissance, surveillance, and communications relay missions. Their high flexibility and scalability give them a significant advantage in complex battlefield environments.

[0040] In the civilian sector: Modular flying-wing drones can be used in logistics delivery, agricultural plant protection, disaster monitoring, environmental monitoring, and emergency rescue. For example, in logistics delivery, delivery efficiency and range can be improved by adding extra batteries and cargo compartments.

[0041] In the field of scientific research: Modular flying-wing UAVs can be used for scientific research tasks such as meteorological research, geological exploration, and ecological monitoring. Their scalability allows scientists to quickly equip them with different sensors and equipment according to their research needs. Attached Figure Description

[0042] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0043] Figure 1 This is a schematic diagram of the entire machine of this utility model;

[0044] Figure 2 This is a top view of the entire machine of this utility model;

[0045] Figure 3 This is a full front view of the present invention.

[0046] Figure 4 This is a left-side view of the entire machine of this utility model;

[0047] Figure 5 This is a schematic diagram of the detachable modular wing of this utility model;

[0048] Figure 6 This is a schematic diagram of the internal structure of the wing of this utility model.

[0049] Figure 7 This is a schematic diagram of the detachable modular design of the pod and hatch of this utility model (the rear power system and support rods are omitted).

[0050] In the diagram: 1. Wingtip tail; 2. Aileron; 3. Elevator; 4. Motor strut; 5. Motor mount; 6. Tilting servo; 7. Propeller; 8. Motor; 9. Wing; 10. Canopy; 11. Pod; 12. Fuselage. Detailed Implementation

[0051] The technical solutions of this utility model will be clearly and completely described below with reference to the embodiments of this utility model. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this utility model.

[0052] Please see Figures 1-7 This utility model provides a technical solution: a modular reconfigurable flying wing UAV based on coaxial dual rotors and tilting propulsion, including a wing-body blended flying wing body, with its fuselage 12 and wing 9 detachably connected; a modular pod 11, which is detachably installed at the bottom of the fuselage 12 via a sliding rail mechanism and used as landing gear; a front fixed coaxial dual rotor system, including a motor power strut 4, a motor 8 and a propeller 7; and a rear tilting propeller system, including a tilting servo 6, a motor 8 and a propeller 7.

[0053] Please see Figures 1-7 The connection structure between the modular pod 11 and the fuselage 12 includes: a longitudinal slide rail at the bottom of the fuselage 12 that cooperates with a slide groove at the top of the pod 11; a cable docking port at the front of the pod 11 and a limit positioning pin hole at the rear.

[0054] Please see Figures 1-7 The connection structure between the wing 9 and the fuselage 12 includes: two round beams extending from the fuselage 12, which are inserted into the corresponding holes of the wing 9; a pin hook is provided on the inner side of the wing 9, which is locked to the fuselage 12, and the buckle has a built-in spring limit button.

[0055] Please see Figures 1-7 Two counter-rotating motor shafts drive a pair of mirror-symmetrical propellers 7 respectively; the motors are fixed to the head of the machine by motor power struts 4, and the motor power struts are integrally formed with the body 12.

[0056] Please see Figures 1-7 The rear tilt propeller system includes: a motor support 5, which is hinged to the fuselage 12 via a tilt servo 6; a motor 8 fixed on the support; and a propeller 7 whose thrust direction is adjustable.

[0057] Please see Figures 1-7 The wing 9 features an internal beam-rib truss structure covered by a lightweight skin, and segmented control surfaces on the trailing edge.

[0058] The inner side is the elevator 3, which is connected to the wing 9 via a hinge; the outer side is the aileron 2, which is connected to the wing 9 via a hinge; the wingtip tail 1 is fixed to the wingtip.

[0059] Please see Figures 1-7The connecting structure of the canopy 10 includes: a hook-shaped structure at the tail end that engages with a slot at the rear of the fuselage 12; and a spring-loaded buckle at the front end that can be opened by pressing to unlock.

[0060] Please see Figures 1-7 The pod 11 is a modular design and can be replaced with: a battery extension pod, a cargo transport pod, or a mission equipment pod.

[0061] Please see Figures 1-7 The wing 9 is a modular design and can be replaced with either a high aspect ratio lift wing or a low drag high speed wing.

[0062] Please see Figures 1-7 The connection interfaces of the fuselage 12, wings 9 and pods 11 all adopt standardized mechanical and electrical interfaces, which support quick assembly and disassembly.

[0063] Working principle:

[0064] The aircraft is positioned with its landing gear in contact with the ground and its nose pointing forward. The aircraft power is activated, and the flight controller is adjusted to vertical flight mode. The aircraft motors are started, and their speeds are adjusted until the aircraft is vertically lifted off the ground and accelerates upwards. The aircraft ascends vertically to the flight mode switching altitude and enters the flight mode switching phase. The tilt servo 6 is engaged to generate forward thrust, decreasing the aircraft's vertical speed and increasing its horizontal speed. Once the horizontal speed reaches a certain level, the flight controller switches to fixed-wing mode, and the aircraft enters the fixed-wing cruise phase. After completing the fixed-wing flight mission and reaching the vicinity of the landing surface, the tilt servo 6 is engaged to gradually reduce the aircraft's forward thrust, increasing its vertical speed and decreasing its horizontal speed. The aircraft's flight attitude is adjusted to vertical flight, and the flight controller switches to vertical takeoff and landing mode, entering the vertical takeoff and landing phase. The aircraft motors are adjusted to ensure a smooth vertical descent until the landing gear contacts the ground. The aircraft motors are then shut off, and the aircraft completes its landing.

[0065] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A modular reconfigurable flying-wing UAV based on coaxial dual rotors and tilting rotational force, characterized in that, The main body of the wing-body blended flying wing is detachably connected to the fuselage (12) and the wing (9); the modular pod (11) is detachably installed at the bottom of the fuselage (12) via a sliding rail mechanism and is used as landing gear; the front fixed coaxial dual rotor system includes a motor power strut (4), a motor (8) and a propeller (7); the rear tilt propeller system includes a tilt servo (6), a motor (8) and a propeller (7); and a quick-opening canopy (10) is locked to the fuselage (12) via a tail hook and a front buckle.

2. The modular reconfigurable flying-wing UAV based on coaxial dual rotors and tilting rotational force according to claim 1, characterized in that, The connection structure between the modular pod (11) and the fuselage (12) includes: a longitudinal slide rail at the bottom of the fuselage (12) that cooperates with a slide groove at the top of the pod (11); a cable docking port at the front of the pod (11) and a limit positioning pin hole at the rear.

3. The modular reconfigurable flying-wing UAV based on coaxial dual rotors and tilting rotational force according to claim 1, characterized in that, The connection structure between the wing (9) and the fuselage (12) includes: two round beams extending from the fuselage (12) and inserted into the corresponding holes of the wing (9); a pin hook is provided on the inner side of the wing (9) and is locked to the fuselage (12) with a built-in spring limit button.

4. A modular reconfigurable flying-wing UAV based on coaxial dual rotors and tilting rotational force as described in claim 1, characterized in that, Two counter-rotating motor shafts drive a pair of mirror-symmetrical propellers (7); the motors are fixed to the head of the machine by motor power struts (4), and the motor power struts and the body (12) are integrally formed.

5. A modular reconfigurable flying-wing UAV based on coaxial dual rotors and tilting rotational force according to claim 1, characterized in that, The rear tilt propeller system includes: a motor support (5), which is hinged to the fuselage (12) via a tilt servo (6); a motor (8) fixed on the support; and a propeller (7) whose thrust direction is adjustable.

6. A modular reconfigurable flying-wing UAV based on coaxial dual rotors and tilting rotational force according to claim 1, characterized in that, The wing (9) has an internal beam-rib truss structure, is covered with a lightweight skin, and has segmented control surfaces on the trailing edge. The inner side is the elevator (3), which is connected to the wing (9) via a hinge; the outer side is the aileron (2), which is connected to the wing (9) via a hinge; the wingtip tail (1) is fixed to the end of the wing.

7. A modular reconfigurable flying-wing UAV based on coaxial dual rotors and tilting rotational force according to claim 1, characterized in that, The connecting structure of the hatch (10) includes: a hook-shaped structure at the tail end that engages with a slot at the rear of the fuselage (12); and a spring buckle at the front end that can be opened by pressing to unlock.

8. A modular reconfigurable flying-wing UAV based on coaxial dual rotors and tilting rotational force according to claim 1, characterized in that, The pod (11) is a modular design and can be replaced by: a battery extension pod, a cargo transport pod, or a mission equipment pod.

9. A modular reconfigurable flying-wing UAV based on coaxial dual rotors and tilting rotational force according to claim 1, characterized in that, The wing (9) is a modular design and can be replaced with a high aspect ratio lift wing or a low drag high speed wing.

10. A modular reconfigurable flying-wing UAV based on coaxial dual rotors and tilting rotational force according to claim 1, characterized in that, The connection interfaces of the fuselage (12), wings (9) and pods (11) all adopt standardized mechanical and electrical interfaces, which support quick assembly and disassembly.

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