CN214566145U

CN214566145U - Fixed wing unmanned aerial vehicle with VTOL and hover function

Info

Publication number: CN214566145U
Application number: CN202120792421.8U
Authority: CN
Inventors: 周朱晶; 陆霄; 史文俊; 王首文; 郭广明
Original assignee: Yangzhou University
Current assignee: Yangzhou University
Priority date: 2021-04-19
Filing date: 2021-04-19
Publication date: 2021-11-02
Anticipated expiration: 2031-04-19

Abstract

The utility model discloses a fixed wing unmanned aerial vehicle with VTOL and function of hovering, compare in current fixed wing unmanned aerial vehicle, the tail screw mechanism of verting screw mechanism and fuselage afterbody of wing has been increased, realize through verting screw mechanism that the screw does to rotate around the horizontal axis and switch around the gesture of vertical rotation of axle, thereby make this fixed wing unmanned aerial vehicle can not only slide the take-off and land in long runway, can also realize the VTOL function, thereby it requires high to have solved fixed wing unmanned aerial vehicle take-off environment, the slow problem of many rotor unmanned aerial vehicle flight speed.

Description

Fixed wing unmanned aerial vehicle with VTOL and hover function

Technical Field

The utility model belongs to the technical field of small aircraft equipment, in particular to wing VTOL device verts.

Background

The existing unmanned aerial vehicle products mainly use fixed wings and multiple rotors, and the fixed wing unmanned aerial vehicle cannot realize vertical take-off and landing although the speed is high, and needs a longer take-off and landing runway; the multi-rotor unmanned aerial vehicle can vertically take off and land but has a slow flying speed.

Disclosure of Invention

The purpose of the invention is as follows: to above-mentioned prior art, provide a fixed wing unmanned aerial vehicle with VTOL and hover function, solve fixed wing unmanned aerial vehicle and take off the problem that the environment requires height, many rotor unmanned aerial vehicle flight speed is slow.

The technical scheme is as follows: a fixed wing unmanned aerial vehicle with vertical take-off, landing and hovering functions comprises a body, wings, an empennage, an undercarriage, and also comprises tilting propeller mechanisms and tail propeller mechanisms, wherein the tilting propeller mechanisms and the tail propeller mechanisms are respectively connected to the wings on two sides of the body;

the tilting propeller mechanism comprises a first propeller, a first motor, a first support, a tilting steering engine and a second support; the first propeller is connected with a first motor and driven by the first motor to rotate; the first motor is fixed on a first support, the first support is connected with an output shaft of a tilting steering engine, the tilting steering engine is fixedly connected with a second support, and the second support is fixedly connected with the wings; the tilting steering engine can drive the first support to rotate around a horizontal shaft, and drive the first propeller to switch from rotating around the horizontal shaft to rotating around a vertical shaft;

the tail propeller mechanism comprises a second propeller, a second motor and a third support, the third support is vertically fixed above the tail portion of the airplane body, the second motor is fixed to the top of the third support, the second propeller is connected with the second motor, and the second propeller can rotate around a vertical shaft.

Furthermore, in the tilting propeller mechanism, the tilting steering engine is a double-output-shaft motor horizontally arranged, the first support is bridged on the tilting steering engine, and two sides of the first support are respectively connected with one output end of the double-output-shaft motor.

Further, among the screw mechanism verts, the second support includes fixed connection the connecting portion of the steering wheel that verts, and with the long stalk portion that connecting portion link to each other, long stalk portion is fixed the wing below.

Further, among the screw mechanism verts, still include motor cap and gasket, first screw passes through the motor cap fastening with first motor, and the gasket setting is in between first motor and the first support.

Furthermore, a battery, a positioning module, a receiver module, a data transmission module and a flight controller module are arranged in the airplane body, the receiver module is connected with the data transmission module, the positioning module and the data transmission module are connected with the flight controller module, and the battery is used for supplying power.

Furthermore, the wings are provided with ailerons and steering engines for driving the ailerons, and the empennage is provided with a rudder.

Has the advantages that: the utility model discloses a fixed wing unmanned aerial vehicle with VTOL and function of hovering, compare in current fixed wing unmanned aerial vehicle, the tail screw mechanism of verting screw mechanism and fuselage afterbody of wing has been increased, realize through verting screw mechanism that the screw does to rotate around the horizontal axis and switch around the gesture of vertical rotation of axle, thereby make this fixed wing unmanned aerial vehicle can not only slide the take-off and land in long runway, can also realize the VTOL function, thereby it requires high to have solved fixed wing unmanned aerial vehicle take-off environment, the slow problem of many rotor unmanned aerial vehicle flight speed.

Drawings

Fig. 1 is a schematic view of the whole structure of the fixed-wing unmanned aerial vehicle of the present invention;

fig. 2 is a schematic structural view of a tilt propeller mechanism;

fig. 3 is a schematic structural diagram of a tail rotor mechanism at the tail part of a fuselage.

Detailed Description

The present invention will be further explained with reference to the accompanying drawings.

As shown in figure 1, the fixed wing unmanned aerial vehicle with the functions of vertical take-off, landing and hovering comprises a body 1, wings 2, an empennage 3 and an undercarriage 4, wherein the wings 2 on two sides of the body 1 are respectively connected with a tilting propeller mechanism, and a tail propeller mechanism is arranged at the tail of the body.

As shown in fig. 2, the tilt propeller mechanism includes a first propeller 5, a first motor 6, a first bracket 7, a tilt steering engine 8, and a second bracket 9. The first propeller 5 is connected with the first motor 6, and the first propeller 5 and the first motor 6 are fastened through a motor cap 13 and driven to rotate by the first motor 6. The first motor 6 is fixed on the first bracket 7, and a gasket 14 is arranged between the first motor 6 and the first bracket 7. The first support 7 is connected with an output shaft of the tilting steering engine 8, the tilting steering engine 8 is fixedly connected with the second support 9, and the second support 9 is fixedly connected with the wing 2. Specifically, the tilting steering engine 8 is a horizontally arranged double-output-shaft motor, the first support 7 is bridged on the tilting steering engine 8, and two sides of the first support are respectively connected with one output end of the double-output-shaft motor. The second support 9 comprises a connecting part fixedly connected with the tilting steering engine 8 and a long handle part connected with the connecting part, and the long handle part is fixed below the wing 2, so that the tilting propeller mechanism is located on the front side below the wing 2. The tilting steering engine 8 can drive the first support 7 to rotate around the horizontal shaft, and drives the first propeller 5 to rotate around the horizontal shaft to switch around the rotating posture of the vertical shaft. The wings 2 are provided with ailerons 15 and steering gears for driving the ailerons 15.

As shown in fig. 3, the tail rotor mechanism includes a second rotor 10, a second motor 11, and a third bracket 12, the third bracket 12 is vertically fixed above the tail of the fuselage 1, the second motor 11 is fixed on the top of the third bracket 12, the second rotor 10 is connected to the second motor 11, and the second rotor 10 can rotate around a vertical shaft. The tail 3 is provided with a rudder 16.

The aircraft is characterized in that a battery, a positioning module, a receiver module, a data transmission module and an aircraft controller module are arranged in the aircraft body 1, the receiver module is connected with the data transmission module, the positioning module and the data transmission module are connected with the aircraft controller module, and the battery is used for supplying power.

The utility model discloses a fixed wing unmanned aerial vehicle, when taking off, receive the signal that the module comes from the ground station through the receiver, through data transmission module and flight controller module processing analysis, with the leading-in steering wheel 8 that verts of signal, drive first screw 5 through the steering wheel 8 that verts and adjust to around the rotatory gesture of vertical axle, then control first motor 6 and begin the operation with higher speed, drive first screw 5 fast revolution, provide ascending lift for the aircraft. In the take-off process, the flight controller module simultaneously controls the second motor 11 to start to operate in an accelerating mode, drives the second propeller 10 to rotate rapidly, provides upward lift force for the airplane, balances the lift force generated by the tilting propeller mechanism, and achieves balance of the flight attitude of the airplane. Because the tail part of the airplane body is wider, the airflow circulation of the propellers on the airplane motor is influenced, and the third support 12 is additionally arranged below the motor, so that the smooth circulation of the airflow passing through the second propeller 10 is ensured.

When the aircraft arrives a take the altitude, the flight controller module firstly controls the first motor 6 to slow down gradually, and simultaneously drives the first propeller 5 to switch from rotating around the vertical axis to rotating around the horizontal axis under the action of the tilting steering engine 8, and controls the first motor 6 to accelerate gradually, so that the aircraft turns into the fixed wing flight attitude from the vertical attitude. In this process, the second propeller 10 is controlled to rotate rapidly to maintain sufficient lift to avoid stalling when the aircraft is changing flight attitude. And controlling the second motor 11 to stop rotating after the airplane is converted from the vertical state to the fixed-wing flying attitude.

During flight, the control of the ailerons 15 and the rudder 16 on the tail 3 is similar to that of a conventional fixed wing drone. The flight control is connected with a safety switch, the airplane can be unlocked only by closing the safety switch before the airplane flies, and safety accidents caused by the fact that an operator does not touch the airplane under the unintentional condition are prevented. And the data transmission module connected with the flight controller module can transmit various parameters of the airplane, such as the height, the motor rotating speed, the levelness and the like to the ground station in real time. Some parameters of the flight control may also be changed by the ground station. The front part of the airplane body is also provided with a positioning module and a compass, and the connecting flight controller module can transmit the flight position and direction to the ground station, so that an operator can obtain data conveniently, and the flight state of the airplane can be mastered. The landing gear of the airplane is arranged at the bottom of the airplane body, and the design of the landing gear can ensure that the airplane can take off and land vertically and can realize the sliding take-off and landing of the common fixed wing airplane under the condition of longer runway. The 4S lithium battery is arranged in the aircraft body, so that the stability of current in the flight process of the aircraft is guaranteed, and the flight quality of the aircraft is guaranteed.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.

Claims

1. A fixed wing unmanned aerial vehicle with vertical take-off, landing and hovering functions comprises a fuselage (1), wings (2), an empennage (3) and an undercarriage (4), and is characterized in that the wings (2) on two sides of the fuselage (1) are respectively connected with a tilting propeller mechanism and a tail propeller mechanism positioned at the tail of the fuselage;

the tilting propeller mechanism comprises a first propeller (5), a first motor (6), a first support (7), a tilting steering engine (8) and a second support (9); the first propeller (5) is connected with a first motor (6) and is driven by the first motor (6) to rotate; the first motor (6) is fixed on a first support (7), the first support (7) is connected with an output shaft of a tilting steering engine (8), the tilting steering engine (8) is fixedly connected with a second support (9), and the second support (9) is fixedly connected with the wing (2); the tilting steering engine (8) can drive the first support (7) to rotate around a horizontal shaft, and drives the first propeller (5) to switch from rotating around the horizontal shaft to rotating around a vertical shaft;

the tail propeller mechanism comprises a second propeller (10), a second motor (11) and a third support (12), the third support (12) is vertically fixed above the tail of the machine body (1), the second motor (11) is fixed at the top of the third support (12), the second propeller (10) is connected with the second motor (11), and the second propeller (10) can rotate around a vertical shaft.

2. The fixed-wing unmanned aerial vehicle with functions of vertical take-off, landing and hovering as claimed in claim 1, wherein in the tilting propeller mechanism, the tilting steering engine (8) is a horizontally arranged double-output-shaft motor, the first support (7) is bridged over the tilting steering engine (8), and two sides of the first support are respectively connected with an output end of the double-output-shaft motor.

3. The fixed-wing drone with VTOL and hover functions of claim 1, wherein in the tilt rotor mechanism, the second bracket (9) comprises a connection part fixedly connected to the tilt steering engine (8), and a long handle part connected to the connection part, the long handle part is fixed under the wing (2).

4. The fixed-wing drone with VTOL and hover functions of claim 2, characterized in that, in the tilt rotor mechanism, it further comprises a motor cap (13) and a gasket (14), the first rotor (5) and the first motor (6) are fastened by the motor cap (13), and the gasket (14) is disposed between the first motor (6) and the first bracket (7).

5. The fixed-wing UAV with VTOL and hover functions of any of claims 1-4, wherein the fuselage (1) has a battery, a positioning module, a receiver module, a data transmission module, and a flight controller module, the receiver module is connected to the data transmission module, the positioning module and the data transmission module are connected to the flight controller module, and the battery is used for supplying power.

6. The fixed-wing UAV with the functions of vertical take-off, landing and hovering according to any one of claims 1 to 4, wherein an aileron (15) and a steering engine for driving the aileron (15) are disposed on the wing (2), and a rudder (16) is disposed on the tail wing (3).