CN206125423U - VTOL fixed wing uavs with power device verts - Google Patents

Abstract

The utility model relates to a vertical take-off and landing fixed-wing unmanned aerial vehicle with a tilting power device, which relates to the field of fixed-wing unmanned aerial vehicles. The vertical take-off and landing unmanned aerial vehicle with a tilting structure power unit includes a fuselage, wings, support arms, a rotor power unit system and an empennage. In vertical take-off and landing mode, four sets of rotor power devices installed symmetrically on the support arm provide power in the vertical direction for the UAV. The rotation speed of the two propellers on the rear side of the wing keeps its lift balanced with the vertical lift component of the two propellers on the front side, so that the UAV switches to the fixed-wing flight mode. The utility model simultaneously satisfies the requirements of UAVs for vertical take-off and landing and large load and long flight time, solves the limitations of the existing vertical take-off and landing aircraft in the vertical take-off and landing structure layout, increases the effective wing area, and greatly improves the flight efficiency .

Description

A vertical take-off and landing fixed-wing unmanned aerial vehicle with a tilting power device

technical field

The utility model relates to the field of fixed-wing unmanned aerial vehicles, in particular to a vertical take-off and landing fixed-wing unmanned aerial vehicle with a tilting power device.

Background technique

The precise definition of a vertical take-off and landing vehicle (VTOL) is: the ability to take off/land at zero speed, have the ability to hover, and can fly horizontally in the manner of a fixed-wing aircraft. Compared with traditional aircraft, vertical take-off and landing vehicles are independent of runways and have the advantage of being able to hover; compared with traditional helicopters, vertical take-off and landing vehicles have much higher forward flight speeds and have greater range. Because of these advantages, vertical take-off and landing aircraft is especially suitable for occasions that need to hover or have special requirements for take-off and landing sites.

UAVs are usually divided into fixed-wing UAVs and rotary-wing UAVs. Among them, fixed-wing UAVs generate lift through the relative motion between the fixed wings and the air, and have long endurance, fast speed, and high flight efficiency. It can realize long-duration and heavy-load flight. But at the same time, in the prior art, the disadvantages of fixed-wing UAVs are: they need a special open field for take-off and landing, and they cannot hover. Rotary-wing UAVs generate lift through the rotation of the rotary wing relative to the air. It has the characteristics of precise control and small requirements for take-off and landing sites. It can achieve vertical take-off and landing, but its flight efficiency is low and its battery life is short, so it cannot achieve large loads. Long flight time.

Most of the existing vertical take-off and landing aircraft adopt single-axis, double-axis or three-axis vertical take-off and landing structural layout forms with high difficulty in control, not only the stability and reliability of the vertical take-off and landing mode are difficult to guarantee, but also The method will cause the structure of the aircraft to be different from ordinary fixed-wing aircraft, which is too complicated, which will seriously affect the aerodynamic layout in the fixed-wing mode, thereby seriously affecting the flight quality in level flight. On the other hand, most of the existing vertical take-off and landing aircraft are limited by their structural design, and there is no way to use a large wingspan, so that the effective wing area cannot be increased, so that its flight efficiency cannot be improved. Airplanes are very different. Therefore, only by adopting the mature rotorcraft model layout form as much as possible without affecting the conventional fixed-wing aircraft layout structure, and achieving the vertical take-off and landing function, can the performance of all aspects of the vertical take-off and landing aircraft be improved to the greatest extent.

Utility model content

In order to solve the contradiction between the inability to simultaneously meet the requirements of vertical take-off and landing and large load and long endurance in the prior art, the utility model provides a vertical take-off and landing unmanned aerial vehicle with a tilting structure power device, which specifically includes: fuselage, wings, support arms, rotor power units and empennage.

Described fuselage and wing are fixed-wing aircraft layout;

The fuselage is a hollow shell structure, and the cargo compartment, airborne electronic equipment, batteries, beams and reinforcement frames are arranged inside the fuselage; the airborne electronic equipment includes flight control boards, electronic governors and sensor data terminal; the side of the fuselage is the installation interface of the wing; the battery is a polymer lithium ion battery; a pitot tube is installed on the front of the fuselage; a group of rotor power devices is installed on the tail of the fuselage.

The wing is a fixed-wing airfoil, the wing is a hollow structure, and the ribs and beam structure are arranged inside; a support arm is respectively installed under the wings on both sides of the drone; the tails of the two support arms are fixedly connected to the empennage .

Four groups of rotor power devices are symmetrically installed on the support arm, wherein two groups of rotor power devices are located at the leading edge of the support arm, constituting the tilting power device described in the utility model; On the support arm between; the geometric center of the four sets of rotor power devices coincides with the center of gravity of the entire drone.

Described empennage is inverted V shape.

The five groups of rotor power devices provide lift for vertical take-off and landing and part of the power for cruising for the UAV. Each group of rotor power units includes a brushless motor and a carbon fiber propeller; the brushless motor is an outer rotor brushless DC motor, which is fixed on the support arm or fuselage under the wing with screws, and is controlled by the onboard electronics. The equipment is controlled, and the energy is provided by a battery; the carbon fiber propeller includes a hub, a blade and an engine.

The utility model provides a vertical take-off and landing fixed-wing unmanned aerial vehicle with a tilting power device, which includes five groups of rotor power devices, wherein the two groups of rotor power devices are arranged on the front edge of the support arm through a tilting structure, and can be Two sets of rotor power units are located on the support arm between the wing and the empennage to provide vertical lift; the last set of rotor power units are located at the tail of the fuselage to provide forward thrust. In vertical take-off and landing mode, the four sets of rotor power devices on the support arm provide power in the vertical direction. After reaching a certain height, the two propellers on both sides of the front of the fuselage are tilted, and the speed of the two propellers on the rear side of the wing is reduced to maintain Its lift is balanced with the vertical lift component of the two propellers on the front side, so that the UAV switches to fixed-wing flight mode.

The utility model has the advantages of: combining the characteristics of the existing fixed-wing unmanned aerial vehicle and rotary-wing unmanned aerial vehicle, a kind of vertical take-off and landing fixed-wing unmanned aerial vehicle with a tilting power device proposed by the utility model is realized, and at the same time, it satisfies the The requirements of UAVs for vertical take-off and landing and large load and long endurance, solve the limitations of the existing vertical take-off and landing aircraft in the vertical take-off and landing structure layout, increase the effective wing area, and greatly improve the flight efficiency. All aspects of performance have been greatly improved.

Description of drawings

Fig. 1 is a structural schematic diagram of a vertical take-off and landing fixed-wing unmanned aerial vehicle with a tilting power device of the present invention;

Fig. 2 is a structural schematic diagram of the carbon fiber propeller of the rotor power device of the present invention.

In the picture:

1-fuselage; 2-wing; 3-support arm; 4-rotor power unit; 5-tail; 6-aileron; 7-pitot tube;

401-propeller hub; 402-blade; 403-engine.

detailed description

A vertical take-off and landing fixed-wing unmanned aerial vehicle with a tilting power device described in the present utility model realizes take-off/landing at zero speed in conjunction with the accompanying drawings and embodiments, has the ability to hover, and is horizontal in the manner of a fixed-wing aircraft. Flight for further clarification.

As shown in FIG. 1 , the utility model provides a vertical take-off and landing fixed-wing UAV with a tilting power device, including a fuselage 1 , wings 2 , support arms 3 , a rotor power device 4 and an empennage 5 .

The fuselage 1 and the wing 2 are conventional fixed-wing aircraft layouts.

The fuselage 1 is a hollow shell structure, and the interior of the fuselage is arranged with cargo compartments, airborne electronic equipment, batteries, beams and reinforcement frames; the airborne electronic equipment includes flight control boards, electronic governors and sensors Data terminal, etc.; the battery is a polymer lithium-ion battery; the side of the fuselage is the installation interface of the wing, and there is a hatch with a hatch under the fuselage, which is used for disassembly and maintenance of airborne electronic equipment and cargo storage. Loading and unloading; pitot tube 7 is installed on the front of fuselage 1, to measure the speed of motion of unmanned aerial vehicle; A group of rotor power unit 4 is installed on the tail of fuselage 1, provides forward thrust for unmanned aerial vehicle flight.

The wing 2 is a fixed-wing airfoil with a hollow structure, internally arranged with ribs and beam structures, and there is an opening below the middle part of the wing 2, which is used to install the digital steering gear used by the control aileron 6; under the wings on both sides Each support arm 3 is installed, and the tails of the two support arms 3 are fixedly connected to the empennage 5, and the fuselage 1 is connected to the empennage 5 through the support arms 3.

Described support arm 3 is fuselage connection device, connects fuselage 1 and empennage 5; Four groups of rotor power units 4 are symmetrically installed on support arm 3, and wherein two groups of rotor power units 4 are positioned at the leading edge of support arm 3, constitute this The tilting power device system described in the utility model can be tilted by 90 degrees through the tilting structure, that is, it can be tilted from a position horizontal to the wing 2 to a position perpendicular to the wing 2; the other two sets of rotor power devices 4 are located on the wing 2 On the supporting arm between the empennage 5; the geometric centers of the four groups of rotor power units 4 coincide with the center of gravity of the entire UAV, providing the UAV with lift for vertical take-off and landing and horizontal thrust after tilting.

The five groups of rotor power units 4 provide lift and part of the power when cruising for the unmanned aerial vehicle; each group of rotor power units 4 includes a brushless motor and a carbon fiber propeller. The brush motor is an external rotor brushless DC motor, which is fixed on the support arm 3 or the fuselage 1 under the wing 2 with screws, controlled by the onboard electronic equipment, and powered by a battery; the carbon fiber propeller includes a hub 401 , blade 402 and engine 403, as shown in FIG. 2 .

The empennage 5 is an inverted V shape as shown in FIG. 1 .

A kind of vertical take-off and landing fixed-wing unmanned aerial vehicle described in the utility model with tilting power device realizes the specific process of flying mission as follows:

(1) A take-off command is given, and lift is provided by four rotor power units 4 on the support arm 3 to realize vertical take-off;

(2) After reaching a certain altitude, under the instruction of the flight control board, control the deflection angle of the two rotors on the front side of wing 2, adjust the speed of the two rotors on the rear side to balance the vertical lift provided by the front and rear rotors, and turn on The rotor power unit 4 at the tail of the fuselage 1 increases the horizontal thrust, and controls the deflection angle of the empennage 5 at the same time, so that the UAV is transferred from the hovering state to the cruising flight state, and the wings 2 provide more lift to improve the cruising flight Efficiency, into route flight.

Claims (2)

1. a kind of VTOL fixed-wing unmanned plane with the power set that vert, it is characterised in that：Including fuselage, wing, prop up Brace, rotor power device and empennage；

Described fuselage is fixed wing aircraft layout with wing；

Described fuselage is hollow housing structure, and fuselage interior arranges cargo compartment, air environment, battery and beam and reinforcement Frame；Described air environment includes flight control panel, electron speed regulator and sensing data terminal；Described battery is poly- Compound lithium ion battery；Fuselage side is the mounting interface of wing, has the hatch with hatchcover below fuselage；The anterior installation of fuselage There is pitot；One group of rotor power device is installed on afterbody；

Described wing is fixed-wing aerofoil profile, and wing is hollow type structure, inside arrangement rib and girder construction；In unmanned plane both sides Wing lower section is respectively installed by a piece support arm；The afterbody of two support arms is fixedly connected empennage；

Four groups of rotor power devices are symmetrically installed on described support arm, wherein two groups of rotor power devices are located at before support arm Edge, constitutes the power set that vert described in the utility model, and in addition two groups of rotor power devices are located between wing and empennage On support arm；The geometric center of four groups of rotor power devices overlaps with the position of centre of gravity of whole unmanned plane；

Described empennage is reverse V-shaped.

2. a kind of VTOL fixed-wing unmanned plane with the power set that vert according to claim 1, its feature exists In：Described rotor power device includes a brushless electric machine and a carbon fiber spiral oar；Described brushless electric machine turns for outer Sub- brshless DC motor, on the support arm being fixed on below wing using screw or fuselage, is controlled by air environment, The energy is provided by battery；Described carbon fiber spiral oar includes propeller hub, blade and engine.