An unmanned aerial vehicle capable of vertical take-off and landing

Abstract

The present invention belongs to aircraft design technology, and specifically relates to an unmanned aerial vehicle capable of vertical take-off and landing. In order to get rid of the constraints of the rotorcraft mode, the present invention integrates multiple flight characteristics of rotorcraft and fixed-wing aircraft. The proposed unmanned aerial vehicle capable of vertical take-off and landing includes a fuselage, wings, canards, vertical tails, electric engines and fuel engines, wherein the fuselage includes a left fuselage and a right fuselage, the two are connected by canards at the front end, connected by inner wings at the rear end, have wings at the outer end, a fuel engine including a rotor is installed at the rear end, vertical tails are provided on the upper and lower sides of the rear end, and an electric engine including a rotor is installed at the tip of the vertical tail; the trailing edge of the wing has flaps and ailerons, and the trailing edge of the vertical tail has a rudder. Greatly reduce costs, provide a larger load space, and can meet the mission requirements of large-load transportation of such aircraft. Lower fuel consumption, effectively improve wind resistance when vertical.

Description

Technical Field

[0001] The invention belongs to aircraft design technology, and in particular relates to an unmanned aircraft capable of vertical take-off and landing. Background Art

[0002] Conventional rotorcraft have low flight speed, short range, and limited carrying capacity. Improving flight speed, increasing flight range, and increasing load-carrying capacity have always been a hot area of ​​rotorcraft research. Tail-seat vertical take-off and landing aircraft is an effective solution. Compared with other configurations of rotorcraft, it has the characteristics of symmetrical aerodynamic characteristics, good maneuverability, compact structure, and high hovering performance. It is more suitable for occasions with large take-off and landing site restrictions and strong requirements for hovering performance and maneuverability. It has a large application space and good application prospects. It can play a significant role in various military tasks such as reconnaissance, early warning, attack, and unconventional combat conditions. It plays an irreplaceable and important role in the future military field and will be a major participant in future wars. It can also play a unique role in related important civilian fields such as power line inspection, dam detection, and traffic accident investigation. Summary of the invention

[0003] The technical problem to be solved by the present invention is to provide a tail-seat efficient aircraft that can take off and land vertically, break away from the constraints of the rotorcraft mode, integrate multiple flight characteristics of rotorcraft and fixed-wing aircraft, have multiple flight control instructions and multiple key flight mission modes, and enable vertical take-off and landing UAVs to complete large-load tasks.

[0004] The technical solution of the present invention is: an unmanned aerial vehicle capable of vertical take-off and landing, the aircraft comprising a fuselage, wings, canards, a vertical tail, an electric engine and a fuel engine, wherein the fuselage comprises a left fuselage and a right fuselage, the two are connected at the front end by a canard, and at the rear end by an inner wing, and have wings at the outer end, a fuel engine including a rotor is installed at the rear end, vertical tails are provided on the upper and lower sides of the rear end, and an electric engine including a rotor is installed at the tip of the vertical tail; the trailing edge of the wing has flaps and ailerons, and the trailing edge of the vertical tail has a rudder.

[0005] Furthermore, the fuselage and the wing adopt a wing-body fusion design and are symmetrical about the longitudinal symmetry plane of the aircraft.

[0006] Furthermore, the heads of the left fuselage and the right fuselage are both translucent in design, which are respectively an infrared photoelectric camera cabin and a visible light photoelectric camera cabin.

[0007] Furthermore, the wing is a mid-single trapezoidal wing, the wingtip is designed with a wingtip winglet, and a support rod for assisting vertical take-off and landing is provided below the wingtip winglet, which has a smooth transition with the wing surface, and the bottom end of the electric engine has a support rod for vertical take-off and landing.

[0008] Furthermore, the canard is a straight wing, with smooth transition design between the two sides and the fuselage, and an elevator is arranged on the trailing edge.

[0009] Furthermore, the vertical tail has a sweep angle of 40 degrees on the 1 / 4 chord line.

[0010] Furthermore, the interior of the fuselage also includes a flight control system, a power supply system and an emergency recovery device.

[0011] Furthermore, during the vertical take-off and landing phase, the electric engine and the fuel engine provide lift for the aircraft, the horizontal attitude is controlled by the asymmetric thrust provided by the engine, and the lateral heading attitude control of the aircraft is controlled by the rudder and asymmetric thrust at the trailing edge of the vertical tail.

[0012] Furthermore, during the transition phase, the attitude of the aircraft is adjusted through the asymmetric thrust provided by the electric engine and the rudder at the trailing edge of the vertical tail. When the fuselage reaches a certain speed to generate effective aerodynamic force, the control surfaces and six rotors are combined to maintain system stability.

[0013] Furthermore, during the forward flight phase, the heading is controlled by the rudder, the rolling attitude is controlled by the ailerons, the body attitude is adjusted by the self-balancing system, the lifting movement is controlled by the elevator, and the electric engine stops working.

[0014] The beneficial effects of the present invention are as follows: the thrust direction of the vertical take-off and landing aircraft of the present invention is always consistent with the movement direction of the fuselage, so that the engine thrust is in the vertical direction during the take-off and landing phases, and the engine thrust is in the forward flight direction during the cruising phase. There is no thrust conversion structure, and the flight attitude is changed only by relying on the flight control system to achieve the transition from the vertical take-off and landing mode to the level flight cruising mode. The structure is simpler than that of a vertical take-off and landing UAV with tilt-rotation power, and the safety and reliability are higher.

[0015] The twin-fuselage design allows the use of two different light-transmitting materials, visible light and infrared, to design the pod's conformal cover. This greatly reduces costs compared to the conformal materials used in independent pod designs with the same performance requirements. At the same time, the twin-fuselage design provides the aircraft with a larger load space, which can meet the mission requirements of large-load transportation for this type of aircraft.

[0016] The dual oil-powered engines increase the lateral control margin of this type of vertical take-off and landing UAV during takeoff, improve wind resistance, and compared with a single-engine design that provides the same thrust, it has lower fuel consumption, a smaller engine size, and a relatively smaller fuselage design resistance; the canard design effectively improves wind resistance when vertical. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural schematic diagram of the unmanned aerial vehicle capable of vertical take-off and landing of the present invention;

[0018] Figure 2 Schematic diagram of the vertical take-off and landing phase of the vertical take-off and landing unmanned aerial vehicle of the present invention;

[0019] Figure 3 It is a top view schematic diagram of the forward flight stage of the vertical take-off and landing unmanned aerial vehicle of the present invention.

[0020] Among them, 1-fuselage, 2-wing, 3-canard, 4-vertical tail, 5-electric engine, 6-fuel engine DETAILED DESCRIPTION

[0021] See also Figure 1 , a schematic structural diagram of a vertical take-off and landing unmanned aerial vehicle of the present invention comprises a fuselage 1, wings 2, canards 3, a vertical tail 4, an electric engine 5 and a fuel engine 6. The vertical take-off and landing unmanned aerial vehicle adopts a canard layout, an aerodynamic layout of a single wing in a double fuselage, and the fuselage and the wing 2, the fuselage and the canard 3 all adopt a wing-body fusion design.

[0022] The fuselage 1 is a double-fuselage design, including a left fuselage and a right fuselage, which are symmetrical about the longitudinal symmetry plane of the aircraft; vertical tails 4 are respectively provided on the upper and lower sides of the tail of the left fuselage and the right fuselage, and the joint part adopts a wing-body fusion design; the two heads of the left fuselage and the right fuselage are optoelectronic camera cabins, which adopt a translucent design and use two different light-transmitting materials, infrared and visible light, for aiming, launching or reconnaissance; the tail ends of the left fuselage and the right fuselage are provided with fuel engines 6, which have rotors; the middle parts of the left fuselage and the right fuselage are used to accommodate batteries, fuel tanks, flight control systems, power supplies and electrical systems, etc.

[0023] The wing 2 is a mid-single trapezoidal wing, using the low-speed high-lift airfoil Naca Ls-0417mod as the wing root, benedek 8405A as the wing tip airfoil, with an installation angle of 3 degrees, an angle of 0 degrees, a twist angle of 3 degrees, a tip-root ratio of 0.32, and an elevator aileron arranged at the trailing edge; the design support rod at the wing tip is smoothly transitioned with the wing surface. The benedek10355B airfoil is used between the left and right fuselages. The wing part structure adopts a double-beam design, with strengthening ribs designed at the wing root and wing tip, and ribs are evenly distributed on the rest of the parts. The skin is made of carbon fiber fiberglass and is integrally formed.

[0024] The canard 3 is installed at the front end of the middle part of the left and right fuselages, adopts a straight wing, a mid-wing, an installation angle of 2°, a tip-to-root ratio of 1, a span of 850 cm, and an elevator is arranged at the trailing edge.

[0025] The vertical tail 4 is symmetrically installed on the upper and lower sides of the left and right fuselages, with a 1 / 4 chord sweep angle of 40 degrees, an aspect ratio of 11, and a tip-to-root ratio of 0.55; electric engines 5 with rotors are installed at the wingtips of the vertical tail fins on the upper and lower sides; and rudders are provided at the trailing edges of the vertical tail fins on both sides.

[0026] The electric engine 5 is divided into two parts, the upper part has a parabolic cross section that wraps the blade insert, and the lower part has a parabolic cross section that wraps the internal motor to form an electric engine compartment; the tail section is designed with a support rod; the four sets of rotors are equidistant about the central axis of the unmanned aerial vehicle, and are symmetrical in pairs. The optimization solution is that the four sets of rotors are distributed in a square.

[0027] Table 1 shows the main performance indicators of the vertical take-off and landing unmanned aerial vehicle.

[0028] Table 1

[0029]

[0030]

[0031] Vertical take-off and landing phase: Figure 2 As shown, four electric engines 5 and a fuel engine 6 at the rear of the fuselage provide lift for the aircraft, the horizontal attitude is controlled by the asymmetric thrust of the engines, and the lateral heading attitude control of the aircraft is controlled by the rudder at the trailing edge of the vertical tail and the asymmetric power of the fuselage on both sides.

[0032] Transition stage: The asymmetric thrust provided by the electric engine 5 and the rotation of the rudder at the trailing edge of the vertical tail realize the movement in the horizontal and height directions. The posture of the fuselage is stabilized by the self-balancing system. When the fuselage reaches a certain speed and generates effective aerodynamic force, the rudder, elevator and aileron at the trailing edge of the outer wing are connected to maintain the stability of the system together with the four rotors.

[0033] Forward flight phase: heading is controlled by the rudder, roll attitude is controlled by the ailerons, body attitude is adjusted by the self-balancing system, and lifting movement is controlled by the elevator.

Claims

1. An unmanned aerial vehicle capable of vertical take-off and landing, characterized in that: The aircraft comprises a fuselage (1), wings (2), canards (3), a vertical tail (4), an electric engine (5) and a fuel engine (6), wherein the fuselage comprises a left fuselage and a right fuselage, the two being connected at the front end by the canards (3) and at the rear end by the inner wing, the outer end having a wing (2), the rear end having a fuel engine (6) including a rotor installed, the upper and lower sides of the rear end having a vertical tail (4), the tip of the vertical tail (4) having an electric engine (5) including a rotor installed, and the bottom end of the electric engine (5) having a support rod for vertical take-off and landing; the trailing edge of the wing (2) having a flap and an aileron, and the trailing edge of the vertical tail (4) having a rudder; During the vertical take-off and landing phase, the electric engine (5) and the fuel engine (6) provide lift for the aircraft, the horizontal attitude is controlled by the asymmetric thrust provided by the engines, and the lateral heading attitude control of the aircraft is controlled by the rudder and asymmetric thrust at the trailing edge of the vertical tail; During the transition phase, the attitude of the aircraft is adjusted by the asymmetric thrust provided by the electric engine (5) and the rudder at the trailing edge of the vertical tail. When the aircraft reaches a certain speed to generate effective aerodynamic force, the control surfaces and the six rotors are combined to maintain system stability. During the forward flight stage, the heading is controlled by the rudder, the rolling attitude is controlled by the ailerons, the body attitude is adjusted by the self-balancing system, the lifting movement is controlled by the elevator, and the electric engine (5) stops working.

2. The vertical take-off and landing unmanned aerial vehicle according to claim 1, characterized in that: The fuselage (1) and the wing adopt a wing-body fusion design and are symmetrical with respect to the longitudinal symmetry plane of the aircraft.

3. The unmanned aerial vehicle capable of vertical take-off and landing according to claim 1, characterized in that: The heads of the left and right fuselages are both translucent in design, and are respectively an infrared optoelectronic camera cabin and a visible light optoelectronic camera cabin.

4. The unmanned aerial vehicle capable of vertical take-off and landing according to claim 1, characterized in that: The wing (2) is a mid-single trapezoidal wing, the wing tip is designed with a wing tip winglet, and a support rod for assisting vertical take-off and landing is provided below the wing tip winglet, which smoothly transitions to the wing surface.

5. The unmanned aerial vehicle capable of vertical take-off and landing according to claim 1, characterized in that: The canard (3) is a straight wing, with both sides designed to smoothly transition with the fuselage, and an elevator arranged on the trailing edge.

6. The unmanned aerial vehicle capable of vertical take-off and landing according to claim 1, characterized in that: The vertical tail (4) has a sweep angle of 40 degrees at the 1 / 4 chord line.

7. The unmanned aerial vehicle capable of vertical take-off and landing according to claim 1, characterized in that: The interior of the fuselage (1) also includes a flight control system, a power supply system and an emergency recovery device.

Images