CN209176908U - A compound-driven rotary-wing fixed-wing unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses a compound-driven rotary-wing fixed-wing unmanned aerial vehicle, which adopts all-electric drive vertical take-off and landing and forward-flying cruise, uses a compound inverted V-shaped tail and equichord-long rectangular four-straight wing surfaces with axisymmetric fuselage Layout: The rotor assembly is used to achieve vertical take-off and landing, and the vertical take-off and landing of the UAV is not restricted by the site. The transition mode of vertical take-off to level flight has small loss of height and high stability. The propeller and drive motor are used to realize the forward flight cruise, and the forward flight cruise speed of the UAV is fast and the continuation time is long. The composite inverted V-shaped tail conforms to the aerodynamic principle of the UAV, which can ensure the aerodynamic efficiency of the UAV's tail during flight; the UAV adopts a rectangular straight wing surface and a rotor arm structure to provide a large lift. When the UAV is flying forward and cruising, it can greatly improve the cruising efficiency and forward flight speed of the UAV, ensure the overall structural rigidity of the UAV, ensure the structural stability of the UAV during flight and the flight safety of the UAV.

Description

A compound-driven rotary-wing fixed-wing unmanned aerial vehicle

technical field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a compound-driven rotor fixed-wing unmanned aerial vehicle.

Background technique

Aircraft design experts and researchers have been trying to design an aircraft capable of short distances or with vertical takeoff and landing and forward cruise performance. At present, in practical applications, the aircraft that uses rotor combination to achieve vertical take-off and landing is relatively mature. In many fields, unmanned aerial vehicles have shown extraordinary performance and gradually entered the stage of people's life. Multi-rotor UAV has the performance of vertical take-off and landing. Therefore, it plays an important role in the field of aerial photography and aerial survey technology. It has simple structure, light weight, strong maneuverability and high reliability, but the body of multi-rotor UAV is small. And there is no fixed lifting surface, its cruising efficiency is not high, the flight speed is not fast, and the flight distance and application range are limited. Fixed-wing UAVs have forward-flight cruising performance and play an important role in many fields such as forest fire prevention and power pipe network inspection. They have high cruising efficiency, fast flight speed, and high flexibility, but fixed-wing UAVs do not have vertical take-off and landing performance. , the requirements for runways and run distances limit the scope of use of fixed-wing aircraft.

Chinese patent CN205770149 discloses "a multi-configuration fixed-wing rotor hybrid UAV", which includes a rotor assembly, a fixed-wing system and an equipment cabin. Flight controllers, sensors and power supplies are placed in the cabin of the equipment cabin. The UAV is composed of a fixed-wing body and a quadrotor, and has the performance of vertical take-off and landing and forward flight cruise. The UAV is characterized by being able to switch among the three modes of rotor UAV, fixed-wing UAV and hybrid UAV according to requirements. It has a wide range of uses and uses, but its structure is that the rotor assembly is directly fixed through the Connected to the body, the structural strength is relatively weak, only the lift is provided by the double wings, and the cruising efficiency is not high.

Patent CN206141829 discloses a "fixed-wing multi-rotor compound aircraft", which includes a main body frame, a tilting engine, a flying-wing fuselage, a rectangular wing and a sweep angle of the flying-wing fuselage. The aircraft has the performance of vertical take-off and landing and forward flight cruise. It adopts the tilting method of the rotor engine to realize the conversion between the UAV's vertical take-off and landing and forward flight cruise. Flying cruise efficiency, the disadvantage is that the method of tilting the engine to perform the transition between vertical take-off and landing and forward flying cruise is too complicated and the cost is relatively high.

Utility model content

In order to avoid the deficiencies of the existing technology, the utility model proposes a compound-driven rotor fixed-wing unmanned aerial vehicle, which adopts all-electric vertical take-off and landing, and the vertical take-off and landing is not restricted by the place of use; the compound inverted V The font-shaped tail layout ensures the efficiency of the rudder surface and the overall stability of the drone in the transition mode of the UAV from vertical to horizontal flight; the use of four straight wing layouts reduces the risk of the UAV in the transition mode from vertical to horizontal flight. The drop in flight height makes the UAV safe and reliable. The four-straight wing layout provides greater lift when the UAV is cruising forward, thereby improving the efficiency and flight speed of the UAV in forward cruising.

The technical solution adopted by the utility model to solve the technical problems is: comprising the first rotor assembly, the second rotor assembly, the third rotor assembly, the fourth rotor assembly, the first propeller, the second propeller, the fuselage, the flight control system, battery, first wing, second wing, third wing, fourth wing, front landing gear, rear landing gear, first rotor arm, second rotor arm, aileron, drive motor, first tail, The second empennage is characterized in that the fuselage is formed of glass fiber reinforced plastics, the cross section of the fuselage head and the fuselage tail is elliptical, and the two sides of the fuselage are respectively the first wing, the third wing and the second wing , the fourth wing, the first wing and the third wing, the second wing and the fourth wing are installed symmetrically with the fuselage axis respectively; the first wing, the second wing, the third wing and the The fourth wing is of equichord long rectangular straight airfoil structure, the aspect ratio is 6-8, and the dihedral angle of the wing is 0-10 degrees; one end of the first rotor arm is fixedly connected with the tip of the first wing, The other end of the first rotor arm is fixedly connected to the tip of the second wing, one end of the second rotor arm is fixed to the tip of the third wing, and the other end of the second rotor arm is fixed to the tip of the fourth wing; the drive motor is fixed In the middle of the leading edge of the first wing and the third wing, ailerons are respectively installed at the 2/3 position of the trailing edge of the second wing and the fourth wing, and the two ailerons are connected with the second wing and the second wing respectively. The four wings are hinged; the first propeller and the second propeller are respectively fixedly connected to the front end of the drive motor, the first propeller and the second propeller have the same structure, and the first propeller and the second propeller turn in opposite directions during operation;

The first rotor assembly, the second rotor assembly, the third rotor assembly and the fourth rotor assembly are parts with the same structure, wherein the rotor is located on the upper part of the motor, and a plurality of rotors are installed in cooperation with the same number of motors, and are symmetrically fixed respectively On the first rotor arm and the second rotor arm, the rotors and motors of the first rotor assembly, the second rotor assembly, the third rotor assembly, and the fourth rotor assembly are all located on the same plane, and the first rotor assembly and the fourth rotor assembly are on the same plane during work. The rotors of the assembly rotate clockwise, and the rotors of the second rotor assembly and the third rotor assembly rotate counterclockwise;

The first tail and the second tail form a composite inverted V-shaped tail, and the anhedral angle between the first tail and the second tail is 30 to 60 degrees;

The front landing gear is located at the bottom 1/4 of the fuselage, and the rear landing gear is located at the bottom 2/3 of the fuselage. The height of the front landing gear and the rear landing gear is greater than the height of the V-shaped tail. When the drone is placed on the ground Or when taking off and landing vertically, the V-tail will not touch the ground.

The battery and the flight control system are respectively located in the middle of the fuselage. The battery is 1 to 2 pieces of 6s batteries. The installation position of the battery can be adjusted. The battery is used to provide power for the rotor motor and the propeller drive motor; Maneuvering and stability during flight.

beneficial effect

The utility model proposes a compound-driven rotor fixed-wing unmanned aerial vehicle, which adopts all-electric vertical take-off and landing and forward-flying cruise, and uses a compound inverted V-shaped tail and straight wing surface structure, and its vertical take-off and landing is not limited by the location. The vertical-to-level flight transition mode has less altitude loss and high stability. The UAV has high efficiency, fast speed and long flight time. When the UAV is flying forward and cruising, it can greatly improve the cruising efficiency and forward flight speed of the UAV; in the transition mode of the UAV from vertical to level flight, the layout of four straight wings can ensure that the flying height of the UAV is not high. It will be reduced, thereby ensuring the flight safety of drones.

The composite drive rotor fixed-wing unmanned aerial vehicle of the utility model adopts the first rotor arm and the second rotor arm to symmetrically fix the rotor assembly respectively, and the two rotor arms are fixedly connected with the four wings respectively, which improves the overall performance of the unmanned aerial vehicle. The structural rigidity can ensure the safety of the UAV during flight. The composite inverted V-shaped tail makes the aerodynamic efficiency of the UAV tail high during flight. Since the upper surface of the UAV has a large resistance component during flight, it will disturb the airflow flowing to the UAV tail. This further reduces the aerodynamic efficiency of the tail during the flight of the UAV, resulting in the problem of low maneuverability of the tail. The composite inverted V-shaped tail can ensure the maneuverability of the UAV tail and conform to the aerodynamic principle of the rotor fixed-wing UAV.

Description of drawings

A compound-driven rotor fixed-wing unmanned aerial vehicle of the present invention will be further described in detail in conjunction with the accompanying drawings and embodiments below.

Fig. 1 is the axonometric view of the utility model composite drive rotor fixed-wing unmanned aerial vehicle.

Fig. 2 is the front view of the utility model composite drive rotor fixed-wing unmanned aerial vehicle.

Fig. 3 is a top view of the composite-driven rotor fixed-wing unmanned aerial vehicle of the present invention.

Fig. 4 is a side view of the composite-driven rotor fixed-wing unmanned aerial vehicle of the present invention.

In the picture:

1. First rotor assembly 2. Second rotor assembly 3. Third rotor assembly 4. Fourth rotor assembly 5. First propeller 6. Second propeller 7. Fuselage 8. Flight control system 9. Battery 10. First Wing 11. Second wing 12. Third wing 13. Fourth wing 14. Front landing gear 15. Rear landing gear 16. First rotor arm 17. Second rotor arm 18. Aileron 19. Drive motor 20. First fin 21. Second fin

Detailed ways

This embodiment is a compound-driven rotor fixed-wing unmanned aerial vehicle.

Referring to Figures 1 to 4, the compound-driven rotor fixed-wing unmanned aerial vehicle of this embodiment adopts electric vertical take-off and landing and forward flight cruise, and utilizes four-wing surface layout and composite inverted V-shaped tail structure to ensure that the unmanned aerial vehicle has a vertical The performance of take-off and landing and forward flight cruise ensures the safety and stability of the UAV's transition mode from vertical to horizontal flight, and improves the efficiency and flight speed of the UAV's forward flight cruise.

In this embodiment, the first rotor assembly 1, the second rotor assembly 2, the third rotor assembly 3 and the fourth rotor assembly 4 all include the same rotor and motor, and the rotor is used for the vertical take-off and landing process of the drone. The UAV does not rotate when flying forward and cruising. The first rotor assembly 1 and the second rotor assembly 2 are fixedly connected to the first rotor arm 16 respectively, the third rotor assembly 3 and the fourth rotor assembly 4 are respectively fixed to the second rotor arm 17, and the distance between the two rotor assemblies It can ensure that the rotors will not touch each other when they rotate. The two ends of the first rotor arm 16 are fixedly connected with the tip of the first wing 10 and the tip of the second wing 11 respectively, and the two ends of the second rotor arm 17 are respectively connected with the tip of the third wing 12 and the tip of the fourth wing 13. The wingtips are fixed to ensure that the pulling force generated by the rotor can be transmitted to the fuselage 7 . The rotors of the first rotor assembly 1 and the fourth rotor assembly 4 rotate clockwise, and the rotors of the second rotor assembly 2 and the third rotor assembly 3 rotate counterclockwise to ensure that the torque generated during the rotation of the rotors can be self-balanced. The wing roots of the first wing 10, the second wing 11, the third wing 12 and the fourth wing 13 are all fixedly connected with the UAV fuselage 7 to ensure that the lift produced by the wing surface is passed to the aircraft. 7 on the body. The first wing 10, the second wing 11, the third wing 12, the fourth wing 13 and the fuselage 7 adopt the better balsa wood or fiberglass material of strength and rigidity; in this example, the first wing 10, The second wing 11, the third wing 12, the fourth wing 13 and the fuselage 7 are made of fiberglass. The first wing 10, the second wing 11, the third wing 12 and the fourth wing 13 are all rectangular straight airfoil structures with equal chord length, the aspect ratio is 7, and the dihedral angle is 5 degrees. The cross section of the fuselage head of the UAV is elliptical, and the cross-sectional area is relatively large. The cross-section of the fuselage 7 tail is oval, and the cross-sectional area is small. Large and then reduced; the middle part of the fuselage 7 is used to install the battery 9 and the flight control system 8, and the tail of the fuselage 7 is upturned and fixedly connected with the first empennage 20 and the second empennage 21. The first propeller 5 and the second propeller 6 are positioned at the front end of the driving motor 19, and the driving motor 19 drives the propellers to rotate, and the first propeller 5 and the second propeller 6 rotate in the opposite direction during work; the first propeller 5 rotates clockwise in this example , The second propeller 6 rotates counterclockwise. The first propeller 5 and the second propeller 6 are installed on the leading edge of the first wing 10 and the third wing 12 respectively, at the wing 1/2 position; at the rear of the second wing 11 and the fourth wing 13 Part 2/3 positions are equipped with ailerons 18 respectively, and the two ailerons are respectively hinged with the second wing and the fourth wing to manipulate the unmanned aerial vehicle. The part with the largest cross-sectional area in the middle of the fuselage 7 is provided with a large opening, and the battery 9 and the flight control system 8 are installed inside the fuselage 7 to ensure the supply of the drone's power system and to assist the manipulation of the drone during flight; In the example, the large opening of the UAV fuselage is located at 1/2 of the fuselage. The battery 9 is 1-2 pieces of 6s battery; this example adopts 1 piece of 6s battery, and the wire passes through the relief holes of the first wing 10, the second wing 11, the third wing 12 and the fourth wing 13 to connect the battery 9 and The rotor motor and the driving motor 19 are connected together to complete the matching of the unmanned aerial vehicle power system. The flight control system 8 includes a flight control board for assisting the control of the drone and recording the flight data of the drone. The front landing gear 14 is affixed to the 1/4 place of the fuselage, and the rear landing gear 15 is affixed to the 2/3 place of the fuselage, which is used when the UAV is placed on the ground or takes off and lands vertically; the front landing gear 14 and the The height of the rear landing gear 15 is consistent and greater than the height of the composite inverted V-shaped tail formed by the first empennage 20 and the second empennage 21, so that when the UAV is placed or taken off on the ground, the composite inverted V-shaped tail will not contact the ground. Touch occurs; ensure the lateral heading stability and maneuverability of the drone; the anhedral angle of the first empennage 20 and the second empennage is 30-60 degrees; the anhedral angle of the first empennage 20 and the second empennage 21 in this example is 45 degrees.

The flight modes of the UAV in this embodiment are vertical take-off and landing mode, transition mode from vertical take-off to level flight, and forward flight cruise mode.

Vertical take-off and landing mode: during the vertical take-off of the UAV in this embodiment, the rotors of the first rotor assembly 1, the second rotor assembly 2, the third rotor assembly 3 and the fourth rotor assembly 4 rotate under the drive of the motor, providing upward The lifting force is used for the vertical lift of the UAV; the first propeller 5, the second propeller 6 and the drive motor 19 do not rotate during the vertical take-off of the UAV; the first empennage 20, the second empennage 21 and the aileron 18 Ensure the lateral and longitudinal stability of the UAV during the vertical take-off of the UAV. During the vertical take-off process, the UAV is controlled by the flight control system 8 to control the rotor speeds of the first rotor assembly 1, the second rotor assembly 2, the third rotor assembly 3 and the fourth rotor assembly 4, so as to ensure that the UAV can operate normally. Take off vertically. During the vertical take-off process of the UAV, the rotor speeds of the first rotor assembly 1, the second rotor assembly 2, the third rotor assembly 3 and the fourth rotor assembly 4 gradually increase until they are stable, and the flying height of the UAV gradually increases. When the flying height of the UAV reaches above 100m, the UAV completes the vertical take-off process. The vertical landing of the UAV is opposite to the vertical take-off process of the UAV. The rotor speeds of the first rotor assembly 1, the second rotor assembly 2, the third rotor assembly 3 and the fourth rotor assembly 4 gradually decrease from the stability. When the man-machine landed on the ground through the front landing gear 14 and the rear landing gear 15, the rotor speeds of the first rotor assembly 1, the second rotor assembly 2, the third rotor assembly 3 and the fourth rotor assembly 4 were reduced to zero, and no one was there. The aircraft successfully landed on the ground, and its vertical landing process ended.

Transition mode from vertical lift to level flight: In the process of converting the UAV from the vertical take-off and landing mode to the forward flight cruise mode, it needs to go through the dynamic transition stage from vertical lift to level flight. Man-machine vertical lift to level flight transition mode; in this mode, the flying height of the drone exceeds 100m, and the forward flight speed of the drone reaches more than 15m/s, and the mode ends; in this mode, the first rotor assembly 1, the second The rotor speeds of the rotor assembly 2 , the third rotor assembly 3 and the fourth rotor assembly 4 gradually decrease until they are zero. The rotational speeds of the first propeller 5, the second propeller 6 and the driving motor 19 gradually increase until they are stable. In the early stage of this flight mode, the flight control system is still used to control the rotor speeds of the first rotor assembly 1, the second rotor assembly 2, the third rotor assembly 3 and the fourth rotor assembly 4, and the first Empennage 20, second empennage 21, aileron 18 and flight control system 8 carry out the control of UAV; In this flight mode, a large lift force is generated, and the flying height of the UAV will not be greatly reduced in this flight mode.

Fly forward cruise mode: the first rotor assembly 1, the second rotor assembly 2 of the unmanned aerial vehicle, the rotor speed of the third rotor assembly 3 and the fourth rotor assembly 4 are zero; the first propeller 5, the second propeller 6 and the drive motor 19. The rotating speed is stable, which is used to provide the pulling force for the forward flight of the UAV; the UAV is controlled by using the first tail 20, the second tail 21, the aileron 18 and the flight control system 8; the first wing 10, the second The wing 11, the third wing 12 and the fourth wing 13 generate greater lift to overcome the gravity of the drone to ensure the stable cruise of the drone.

Claims (2)

1. A compound-driven rotor fixed-wing UAV, comprising a first rotor assembly, a second rotor assembly, a third rotor assembly, a fourth rotor assembly, a first propeller, a second propeller, a fuselage, a flight control system, battery, first wing, second wing, third wing, fourth wing, front landing gear, rear landing gear, first rotor arm, second rotor arm, aileron, drive motor, first tail, Second empennage, it is characterized in that: described fuselage adopts fiberglass molding, and the cross-section of fuselage head and fuselage afterbody is ellipse, and fuselage both sides are respectively first wing, the 3rd wing and the second wing wing, the fourth wing, the first wing and the third wing, the second wing and the fourth wing are installed symmetrically with the fuselage axis respectively; the first wing, the second wing, the third wing and the fourth wing are both equichord long rectangular straight airfoil structures, the aspect ratio is 6-8, and the dihedral angle of the wing is 0-10 degrees; one end of the first rotor arm is fixedly connected to the tip of the first wing , the other end of the first rotor arm is fixedly connected to the tip of the second wing, one end of the second rotor arm is fixed to the tip of the third wing, and the other end of the second rotor arm is fixed to the tip of the fourth wing; the drive motor It is fixed in the middle of the leading edge of the first wing and the third wing, and ailerons are respectively installed at the 2/3 position of the trailing edge of the second wing and the fourth wing, and the two ailerons are respectively connected with the second wing, the The fourth wing is hinged; the first propeller and the second propeller are respectively fixedly connected to the front end of the drive motor, the first propeller and the second propeller have the same structure, and the first propeller and the second propeller turn in opposite directions during operation; The first rotor assembly, the second rotor assembly, the third rotor assembly and the fourth rotor assembly are parts with the same structure, wherein the rotor is located on the upper part of the motor, and a plurality of rotors are installed in cooperation with the same number of motors, and are symmetrically fixed respectively On the first rotor arm and the second rotor arm, the rotors and motors of the first rotor assembly, the second rotor assembly, the third rotor assembly, and the fourth rotor assembly are all located on the same plane, and the first rotor assembly and the fourth rotor assembly are on the same plane during work. The rotors of the assembly rotate clockwise, and the rotors of the second rotor assembly and the third rotor assembly rotate counterclockwise; The first tail and the second tail form a composite inverted V-shaped tail, and the anhedral angle between the first tail and the second tail is 30 to 60 degrees; The front landing gear is located at the bottom 1/4 of the fuselage, and the rear landing gear is located at the bottom 2/3 of the fuselage. The height of the front landing gear and the rear landing gear is greater than the height of the V-shaped tail. When the drone is placed on the ground Or when taking off and landing vertically, the V-tail will not touch the ground. 2. The rotor fixed-wing unmanned aerial vehicle of compound drive according to claim 1, is characterized in that: described battery and flight control system are respectively positioned at middle position in fuselage, and battery is 1～2 6s batteries, and battery installation position Adjustable, the battery is used to power the rotor motor and the propeller drive motor; the flight control system is used to ensure the control and stability of the UAV during flight.