CN110683030A - A vertical take-off and landing unmanned aerial vehicle - Google Patents

Abstract

The invention belongs to the aircraft design technology, and particularly relates to an unmanned aircraft that can take off and land vertically. In order to get rid of the constraints of the rotary-wing aircraft mode, the present invention integrates various flight characteristics of rotary-wing and fixed-wing aircraft. an engine, wherein the fuselage includes a left fuselage and a right fuselage, both connected by a canard at the front end, connected by an inner wing at the rear end, having a wing at the outer end, and a fuel including a rotor mounted at the rear end The engine has a vertical tail on the upper and lower sides of the rear end, and an electric motor 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. It greatly reduces the cost, provides a larger load space, and can meet the mission requirements of such aircraft for large-load transportation. The fuel consumption is lower, and the wind resistance is effectively improved when vertical.

Description

A vertical take-off and landing unmanned aerial vehicle

technical field

The invention belongs to the aircraft design technology, and particularly relates to an unmanned aircraft that can take off and land vertically.

Background technique

Conventional rotorcraft has low flight speed, short range, and limited carrying capacity. Increasing the flight speed, increasing the flight range, and increasing the load and transportation capacity have always been a hot field of rotorcraft research. The tailstock 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, and is more suitable for take-off and landing site restrictions. Larger occasions with strong requirements for hover performance and maneuverability. It has a large application space and good application prospects. It can play a significant role in a variety of military tasks such as reconnaissance, early warning, attack and unconventional combat conditions. Participants can also play a unique role in related important civil fields such as power line inspection, dam inspection, traffic accident investigation and other tasks.

SUMMARY OF THE INVENTION

The technical problem to be solved by the present invention is: to provide a tailstock type high-efficiency aircraft that can take off and land vertically, get rid of the constraints of the rotorcraft mode, integrate the various flight characteristics of the rotor and fixed-wing aircraft, and have a variety of flight control commands and A variety of key flight mission modes can realize vertical take-off and landing UAVs to complete heavy-load tasks.

The technical scheme of the present invention is: an unmanned aerial vehicle capable of taking off and landing vertically, the aerial vehicle includes a fuselage, a wing, a canard, a vertical tail, an electric engine and a fuel engine, wherein the fuselage includes a left fuselage and a right fuselage The two are connected by canards at the front end, connected by the inner wing at the rear end, have wings at the outer end, a fuel engine including a rotor is installed at the rear end, and there are vertical tails on the upper and lower sides of the rear end, An electric motor including a rotor is installed on 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.

Further, the fuselage and the wing adopt a wing-body fusion design, and are symmetrical with the longitudinal symmetry plane of the aircraft.

Further, the heads of the left fuselage and the right fuselage both adopt a translucent design, and are respectively an infrared photoelectric camera cabin and a visible light photoelectric camera cabin.

Further, the wing is a single trapezoidal wing, the wing tip is designed with a winglet, and there is a support rod for assisting vertical take-off and landing under the winglet, which is smooth and smooth with the airfoil, and the bottom end of the electric engine is Has struts for vertical take-off and landing.

Further, the canard is a straight wing with smooth transition design on both sides and the fuselage, and an elevator is arranged on the trailing edge.

Further, the vertical tail is swept back by 40 degrees at the 1/4 chord line.

Further, the interior of the fuselage also includes a flight control system, a power supply system and an emergency recovery device.

Further, during the vertical take-off and landing stage, the electric engine and the fuel engine provide the lift of the aircraft, the horizontal attitude is controlled by the asymmetric thrust provided by the engine, and the lateral attitude of the aircraft is controlled by the rudder and asymmetric thrust on the trailing edge of the vertical tail. .

Further, in the transition stage, the asymmetric thrust provided by the electric engine and the rudder on the trailing edge of the vertical tail are used to adjust the attitude of the aircraft. When the body reaches a certain speed to generate effective aerodynamic force, the rudder surfaces and the six rotors are jointly maintained. System stability.

Further, in 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 motion is controlled by the elevator, and the electric engine stops working.

The beneficial effects of the present invention are: the direction of the thrust of the aircraft capable of taking off and landing vertically is always consistent with the direction of movement of the body, so that the thrust of the engine is in the vertical direction during the take-off and landing phase, and the thrust of the engine is in the forward flight direction during the cruise phase, and there is no thrust. Converting the structure, only relying on the flight control system to change the flight attitude to achieve the cruise mode from the vertical take-off and landing mode to the level flight, and the structure is simpler, safer and more reliable than the vertical take-off and landing drone with tilting power. Sex is higher.

The dual fuselage allows the use of two different light-transmitting materials, visible light and infrared, to design the pod's conformal cover. Compared with the conformal material used in the design of independent pods that require the same performance, the cost is greatly reduced. The design provides a larger load space for this aircraft, which can meet the mission requirements for large-load transportation of such aircraft.

The dual-oil-powered engine increases the control margin of this type of vertical take-off and landing UAV in the lateral direction when it takes off, improves the wind resistance, and has lower fuel consumption, smaller engine size, and better wind resistance than the single-engine design that provides the same thrust. The resistance of the body design is relatively smaller; the design of the canard effectively improves the wind resistance when it is vertical.

Description of drawings

Fig. 1 is the structural representation of the unmanned aerial vehicle that can take off and land vertically according to the present invention;

2 is a schematic diagram of the vertical take-off and landing stage of the vertical take-off and landing unmanned aerial vehicle of the present invention;

3 is a schematic top view of the forward flight stage of the vertical take-off and landing unmanned aerial vehicle of the present invention.

Among them, 1-fuselage, 2-wing, 3-canard, 4-vertical tail, 5-electric engine, 6-fuel engine

Detailed ways

Please refer to FIG. 1 , which is a schematic structural diagram of the vertical take-off and landing unmanned aerial vehicle of the present invention, including a fuselage 1 , a wing 2 , a canard 3 , a vertical tail 4 , an electric engine 5 and a fuel engine 6 . The vertical take-off and landing unmanned aerial vehicle adopts the canard layout and the aerodynamic layout of the single wing in the double fuselage.

The fuselage 1 is a double fuselage design, including a left fuselage and a right fuselage, both of which are symmetrical about the longitudinal symmetry plane of the aircraft; Tail 4, the joint part adopts the wing-body fusion design; the two heads of the left fuselage and the right fuselage are photoelectric camera cabins, which adopt a translucent design, and use two different light-transmitting materials of infrared and visible light respectively for aiming. Launching or reconnaissance; the rear ends of the left and right fuselages have fuel engines 6 with rotors; the middle of the left and right fuselages are used to house batteries, fuel tanks, flight control systems, power supplies, and electrical systems.

The wing 2 is a single trapezoidal wing. The low-speed and high-lift airfoil Naca Ls-0417mod is used as the root of the wing, and the benedek 8405A is used as the wing tip. The installation angle is 3 degrees, the dihedral angle is 0 degrees, and the twist angle is 3 degrees. 3 degrees, the tip-to-root ratio is 0.32, and the elevons are arranged on the trailing edge; the design support rod at the wing tip and the airfoil surface are too smooth. The benedek 10355B airfoil is used between the left fuselage and the right fuselage. The structure of the wing part is designed with double spar type, and reinforcing ribs are designed at the wing root and wing tip, and the rest of the wing is evenly distributed with ribs. The skin is made of carbon fiber glass fiber reinforced plastic, which is integrally formed.

The canard 3 is installed at the front end of the middle of the left fuselage and the right fuselage. It adopts a straight wing, a middle single wing, an installation angle of 2°, a slight root ratio of 1, a length of 850cm, and an elevator arranged on the trailing edge.

The vertical tail 4 is installed symmetrically on the upper and lower sides of the left fuselage and the right fuselage, with a 1/4 chord line sweep angle of 40 degrees, an aspect ratio of 11, and a tip-to-root ratio of 0.55; vertical tail fins on the upper and lower sides At the tip, an electric motor 5 is installed, which has a rotor; the trailing edges of the vertical tails on both sides are provided with rudders.

The electric motor 5 is divided into two parts, the upper section is a parabolic wrapping blade insert, and the lower section is parabolic, wrapping the internal motor to form an electric engine compartment; the tail section is designed with a support rod; the four sets of rotors are about the center of the unmanned aerial vehicle. The axes are equidistant and symmetrical. The optimal solution is that the four sets of rotors are distributed in a square.

Table 1 is the main performance index of the VTOL UAV.

Table 1

Vertical take-off and landing stage: As shown in Figure 2, the four electric engines 5 and the fuel engine 6 at the tail of the fuselage provide aircraft lift, the horizontal attitude is controlled by the asymmetry of engine thrust, and the lateral heading attitude of the aircraft is controlled by the trailing edge of the vertical tail. The rudder and the power asymmetry of the fuselage on both sides are controlled.

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

Forward flight stage: the heading is controlled by the rudder, the roll attitude is controlled by the ailerons, the body attitude is adjusted by the self-balancing system, and the lift motion is controlled by the elevator.

Claims (10)

1. A vertical take-off and landing unmanned aerial vehicle is characterized in that: the aircraft comprises a fuselage (1), a wing (2), a canard (3), a vertical tail (4), an electric motor (5) and a fuel oil The engine (6), wherein the fuselage comprises a left fuselage and a right fuselage, which are connected at the front end by a canard (3), at the rear end by an inner wing, and have a wing (2) at the outer end, A fuel engine (6) including a rotor is installed at the rear end, a vertical tail (4) is arranged on the upper and lower sides of the rear end, and an electric motor (5) including a rotor is installed at the tip of the vertical tail (4); The trailing edge of the wing (2) has flaps and ailerons, and the trailing edge of the vertical tail (4) has a rudder. 2 . The unmanned aerial vehicle capable of taking off and landing vertically according to claim 1 , wherein the fuselage ( 1 ) and the wings adopt a wing-body fusion design, and are symmetrical with the longitudinal symmetry plane of the aircraft. 3 . 3. The unmanned aerial vehicle that can take off and land vertically according to claim 1 is characterized in that: the heads of the left fuselage and the right fuselage all adopt a translucent design, which are respectively an infrared photoelectric camera cabin and a visible light photoelectric camera cabin . 4. The unmanned aerial vehicle that can take off and land vertically according to claim 1, is characterized in that: the wing (2) is a single trapezoidal wing, and the wing tip is designed with a winglet, which has a winglet under the winglet. A support rod for assisting vertical take-off and landing, which is smooth over the airfoil, and the bottom end of the electric motor (5) has a support rod for vertical take-off and landing. 5. The unmanned aerial vehicle capable of taking off and landing vertically according to claim 1, wherein the canard (3) is a straight wing, with smooth transition design on both sides and the fuselage, and an elevator is arranged on the trailing edge. 6 . The unmanned aerial vehicle capable of taking off and landing vertically according to claim 1 , wherein the vertical tail ( 4 ) has a sweep angle of 40 degrees at the 1/4 chord line. 7 . 7. The vertical take-off and landing unmanned aerial vehicle according to claim 1, characterized in that: the interior of the fuselage (1) further comprises a flight control system, a power supply system and an emergency recovery device. 8. The unmanned aerial vehicle that can take off and land vertically according to claim 1, is characterized in that: during the vertical take-off and landing stage, the electric motor (5) and the fuel engine (6) provide the lift of the aircraft, and the horizontal attitude is provided by the different engine of the engine. Symmetrical thrust is used for control, and the aircraft's lateral heading attitude is controlled by the rudder on the trailing edge of the vertical tail and asymmetrical thrust. 9. The unmanned aerial vehicle that can take off and land vertically according to claim 1, is characterized in that: during the transition stage, the asymmetric thrust provided by the electric motor (5) and the rudder of the trailing edge of the vertical tail adjust the attitude of the aircraft, When the body reaches a certain speed to generate effective aerodynamic force, the rudder surfaces and six rotors are combined to maintain the stability of the system. 10. The vertical take-off and landing unmanned aerial vehicle according to claim 1 is characterized in that: during the forward flight stage, the heading is controlled by the rudder, the roll attitude is controlled by the ailerons, and the body attitude is adjusted by the self-balancing system, The lifting movement is controlled by the elevator, and the electric motor (5) stops working.

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