Tailstock type vertical take-off and landing unmanned aerial vehicle based on cross wing configuration

Abstract

The invention discloses a tailstock type vertical take-off and landing unmanned aerial vehicle based on a cross-shaped wing structure. The tailstock type vertical take-off and landing unmanned aerial vehicle comprises a fuselage, cross-shaped wings, motor supports, a left wing supporting plate, a right wing supporting plate and unmanned aerial vehicle supporting legs. The vertical take-off and landing unmanned aerial vehicle adopts a cross wing pneumatic configuration, a motor bracket can be mounted at a wingtip of each wing according to the cross wing layout, a motor and a propeller are mounted on one side of each motor bracket, unmanned aerial vehicle supporting legs are mounted on the other side of each motor bracket, and when the unmanned aerial vehicle is placed on the ground, the propellers generate upward pulling force to realize vertical take-off and landing of the unmanned aerial vehicle. The switching between vertical take-off and landing and horizontal cruise is realized by controlling the rotating speed and the control surface of the motor; secondly, the upper and lower wings on the two sides adopt a wing connecting structure, so that the strength of the fuselage of the unmanned aerial vehicle is better, and the deformation amplitude of parts such as wingtips is smaller under the wing connecting structure; finally, the machine body is of a cylindrical structure, the structure is simple, and machining is convenient; the whole machine adopts a modular design, the wings can be quickly disassembled, and the transportation is convenient.

Description

Technical Field

[0001] The present invention relates to the field of aircraft technology, and in particular to a tail-seat vertical take-off and landing UAV based on a cross-wing configuration, which can realize switching between vertical take-off and landing and horizontal cruising, and has a very high energy consumption utilization rate. Background Art

[0002] Existing vertical take-off and landing fixed-wing drones have the following drawbacks: 1. Low structural strength. Conventional aerodynamic layouts use motors mounted below the wings, which results in significant deformation of the wingtips and other components, leading to significant damage to the wingtips during extended flight. 2. High manufacturing costs. Conventional aerodynamic layouts are complex, with numerous components and a high level of system complexity. 3. Large size. Conventional aerodynamic layouts often result in long wingspans, requiring larger space and transport containers. 4. High operating costs. Vertical and horizontal propulsion systems are typically separated.

[0003] Compared with existing vertical take-off and landing fixed-wing UAVs, the tail-seat vertical take-off and landing UAV based on the cross-wing configuration in the present invention adopts a connected wing layout on the upper and lower wings on both sides. The connected wing layout is a frame structure with better strength, and the deformation amplitude of parts such as the wing tips will also be smaller under the frame structure; the fuselage adopts a cylindrical structure design, which is simple in structure and easy to process; the fuselage is small in size and can fly and display in a narrow space, while reducing the transportation volume and facilitating transportation; the use cost is low, and a power system is used to realize the switching between vertical take-off and landing and horizontal cruising, and the energy efficiency utilization rate is very high. Summary of the Invention

[0004] In order to overcome the problems of low structural strength, high manufacturing and use costs, and large size of existing vertical take-off and landing fixed-wing UAVs, the purpose of the present invention is to propose a tail-seat vertical take-off and landing UAV based on a cross-wing configuration, aiming to improve the performance of vertical take-off and landing fixed-wing UAVs such as low structural strength, high manufacturing and use costs, and large size.

[0005] The present invention is achieved through the following technical solutions: A tail-seat vertical take-off and landing UAV based on a cross-wing configuration comprises a fuselage, wings, a motor bracket, a motor, a propeller, a support foot, and a support plate. The fuselage adopts a cylindrical structure and is embedded and fixed to four wings in a cross-wing configuration. The motor bracket is installed at the wing tip, the motor is installed at the front end of the motor bracket, the motor is installed with a propeller, the support foot is installed at the rear end of the motor bracket, and the upper and lower ends of the wing support plate are respectively installed with the upper and lower motor brackets.

[0006] The fuselage includes a cargo compartment, a battery compartment, and an equipment compartment from front to back.

[0007] The wings are installed at a position from the middle to the tail of the fuselage, and are fixed by means of buckles after the pins on the wings are inserted into slots on the fuselage.

[0008] The motor bracket is provided with latches on both sides of its exterior, which are respectively embedded in the wing and the wing support plate and fixed by snap fastenings.

[0009] The motor base is mounted on the motor bracket via screws, and the motor is a brushless motor.

[0010] The propeller is installed above the motor through a screw rod.

[0011] The supporting feet are mounted on the motor bracket via screw rods.

[0012] Both ends of the wing support plate are provided with slots which are respectively connected to the upper and lower motor brackets, so that the upper and lower wings on both sides become a frame structure.

[0013] The length of the fuselage is 1000 mm; the wingspan is 910 mm; and the length of the motor bracket is 280 mm.

[0014] The beneficial effects of the present invention are as follows: First, in terms of the power system, a single power system is used to achieve switching between vertical take-off and landing and horizontal cruising, with a very high energy efficiency. Secondly, in terms of the wing structure, the wings on both sides adopt a wing-linked layout, which is a frame structure with better strength, and the deformation amplitude of parts such as the wingtip is also smaller under the frame structure; thirdly, the fuselage structure adopts a cylindrical structure design, which is simple and easy to process; finally, in terms of the fuselage volume, the fuselage of the invention is small, and can be flown and displayed in narrow spaces, while reducing the transportation volume and facilitating transportation; compared with conventional layouts, the vertical take-off and landing UAV has high energy efficiency, small size, and is easy to process.

[0015] The tail-seat vertical take-off and landing UAV with a cross-wing configuration provides new ideas for vertical take-off and landing fixed-wing UAVs. It is believed that its future application prospects will be very broad. Whether it is electricity, oil and gas pipelines, forestry, or emergency rescue, surveying and mapping and other fields, it will play a huge role. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural diagram of a tail-seat vertical take-off and landing UAV based on a cross-wing configuration.

[0017] Figure 2 This is a schematic diagram of the internal structure of a tail-seat vertical take-off and landing UAV based on a cross-wing configuration.

[0018] Figure 3 It is a front view of a tail-seat vertical take-off and landing UAV based on a cross-wing configuration.

[0019] Figure 4 It is a side view of a tail-seat vertical take-off and landing UAV based on a cross-wing configuration.

[0020] Figure 5 It is a rear view of a tail-seat vertical take-off and landing UAV based on a cross-wing configuration.

[0021] Among them: fuselage 1, wing 2, motor bracket 3, motor 4, propeller 5, support foot 6, wing support plate 7, cargo compartment 8, battery compartment 9, equipment compartment 10. DETAILED DESCRIPTION

[0022] The specific embodiments of the present invention will be further described below with reference to the accompanying drawings.

[0023] like Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 As shown, a tail-seat vertical take-off and landing UAV based on a cross-wing configuration includes a fuselage 1, wings 2, a motor bracket 3, a motor 4, a propeller 5, a support leg 6, a support plate 7, a cargo compartment 8, a battery compartment 9, and an equipment compartment 10; the internal structure of the fuselage 1 is divided into a cargo compartment 8, a battery compartment 9, and an equipment compartment 10 from front to back, the fuselage 1 and the four wings 2 are embedded and fixed to each other, the motor bracket 3 is installed at the tip of the wing 2, the motor 4 is installed at the front end of the motor bracket 3, the propeller 5 is installed on the motor 4, the support leg 6 is installed at the rear end of the motor bracket 3, and the upper and lower ends of the wing support plate 7 are respectively installed with the upper and lower motor brackets 3.

[0024] The internal structure of the fuselage 1 is divided into a cargo compartment, a battery compartment, and an equipment compartment. The length of the fuselage 1 is 1000 mm.

[0025] The fuselage adopts a cylindrical structure design, which is simple in structure and easy to process; the fuselage is made of composite materials.

[0026] Wing 2 is installed between the middle and tail of fuselage 1, 470 mm away from the head. The pin on wing 2 is inserted into the slot on fuselage 1 and fixed with a buckle. The wingspan of wing 2 is 910 mm. The power cables and signal cables of the battery compartment and equipment compartment can be transitioned to the motor bracket through the carbon rod of the wing.

[0027] Motor bracket 3 has latches on both sides, which are embedded in the wing and support plate, respectively, and then secured with clips. The motor bracket is cylindrical and made of composite material. The motor bracket provides internal wiring to power the motor. The length of the motor bracket is 280 mm.

[0028] The base of motor 4 is installed on the motor bracket through 4 screws. The motor adopts a brushless motor with an outer diameter of 35 mm and a stator thickness of 20 mm. The motor KV value is 560, the maximum continuous power is 2000 W, the motor weight is 219 g, the maximum number of battery cells supported is 6 s, and the maximum pulling force is 5012 g.

[0029] The propeller 5 is installed above the brushless motor through a screw. The propeller 5 uses a 12*6.5 carbon fiber propeller.

[0030] The support foot 6 is installed on the motor bracket through a screw. The support foot adopts a semicircular design and is made of rubber material to provide support for the drone to take off and land.

[0031] The wing support plates 7 have slots at both ends that connect to the upper and lower motor brackets 3, forming a single frame structure for enhanced strength. The wing support plates are 500 mm long. They are shaped like airfoils and made of composite materials. They are embedded within the upper and lower motor brackets and secured with clips. Their primary function is to secure the upper and lower wings together and enhance fuselage strength.

[0032] The cargo compartment 8 is located in the front cabin of the UAV. The cargo compartment can be used to install cargo or pods according to the mission scenario. The cargo compartment is 190 mm wide and 300 mm long.

[0033] The battery compartment 9 is located at the middle hatch of the drone. The power battery uses a 6S lithium battery and is fixed to the middle compartment of the fuselage 1 by Velcro. The battery compartment is 190 mm wide and 150 mm long.

[0034] The equipment compartment 10 is located in the tail compartment of the UAV, and includes electronic control, receiver, flight control, data link, etc.

[0035] The electronic speed controller (ESC) regulates the current for the drone's motors; the receiver communicates with the remote controller, enabling human-in-the-loop control within a range of 60 km; the data link enables real-time image transmission; and the equipment compartment is 190 mm wide and 100 mm long.

[0036] The flight controller is responsible for controlling the drone's flight status, ensuring stability and safety in the air. The entire drone has a modular design that allows for quick disassembly and easy transportation.

[0037] The above-described embodiments illustrate only several implementations of the present invention, using a fuselage length of 1000 mm as an example. While the description is relatively specific and detailed, it should not be construed as limiting the scope of the invention. It should be noted that those skilled in the art will be able to make various modifications and improvements without departing from the spirit of the present invention, all of which fall within the scope of protection of the present invention. The scope of protection of the present invention is defined by the appended claims and any equivalent technical solutions.

Claims

1. A tail-seat vertical take-off and landing UAV based on a cross-wing configuration, characterized in that: The invention comprises a fuselage (1), wings (2), a motor bracket (3), a motor (4), a propeller (5), a support leg (6), and a support plate (7); the fuselage (1) adopts a cylindrical structure, and is embedded and fixed with four wings (2) in a cross-wing configuration; the motor bracket (3) is installed at the tip of the wing (2); the motor (4) is installed at the front end of the motor bracket (3); the propeller (5) is installed on the motor (4); the support leg (6) is installed at the rear end of the motor bracket (3); and the upper and lower ends of the wing support plate (7) are respectively installed with the upper and lower motor brackets (3).

2. The cross-wing tail-seat vertical take-off and landing UAV according to claim 1, characterized in that: The fuselage (1) includes, from front to back, a cargo compartment (8), a battery compartment (9), and an equipment compartment (1) (0).

3. The cross-wing tail-seat vertical take-off and landing UAV according to claim 1, characterized in that: The wing (2) is installed at a position from the middle to the tail of the fuselage (1), and is fixed by a buckle after the pin on the wing (2) is inserted into the slot on the fuselage (1).

4. The cross-wing tail-seat vertical take-off and landing UAV according to claim 1, characterized in that: The motor bracket (3) is provided with latches on both sides of its exterior, which are respectively embedded in the wing (2) and the wing support plate (7) and fixed by snap fasteners.

5. The cross-wing tail-seat vertical take-off and landing UAV according to claim 1, characterized in that: The motor (4) base is mounted on the motor bracket (3) via four screws, and the motor (4) is a brushless motor.

6. The cross-wing tail-seat vertical take-off and landing UAV according to claim 1, characterized in that: The propeller (5) is installed above the motor (4) via a screw.

7. The cross-wing tail-seat vertical take-off and landing UAV according to claim 1, characterized in that: The support foot (6) is mounted on the motor bracket via a screw.

8. The cross-wing tail-seat vertical take-off and landing UAV according to claim 1, characterized in that: The wing support plate (7) is provided with slots at both ends thereof and is respectively connected to the upper and lower motor brackets (3), so that the upper and lower wings on both sides become a frame structure.

9. The cross-wing tail-seat vertical take-off and landing UAV according to claim 1, characterized in that: The length of the fuselage (1) is 1000 mm; the span of the wing (2) is 910 mm; and the length of the motor bracket is 280 mm.

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