CN111268120A

CN111268120A - Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power

Info

Publication number: CN111268120A
Application number: CN202010167541.9A
Authority: CN
Inventors: 张炜; 郭占鹏; 马一元
Original assignee: Northwestern Polytechnical University
Current assignee: Northwestern Polytechnical University
Priority date: 2020-03-11
Filing date: 2020-03-11
Publication date: 2020-06-12
Anticipated expiration: 2040-03-11
Also published as: CN111268120B

Abstract

The invention relates to a vertical take-off and landing unmanned aerial vehicle adopting distributed duct power, belonging to the technical field of unmanned aerial vehicles; the aircraft comprises an aircraft body, wings, ailerons, vertical empennages, a rudder, canard wings and a duct power unit, wherein the wings are symmetrically arranged on two sides of the rear part of the aircraft body, and the two ailerons are respectively hinged to the outer side positions of the trailing edges of the wings on the two sides; the two trailing edge flaps are respectively hinged to the inner measuring positions of the trailing edges of the wings at two sides and can rotate for 0-90 degrees relative to the wing surfaces of the wings; the duck wings are symmetrically arranged on two sides of the front part of the machine body, and the roots of the duck wings are connected with the machine body through a rotating shaft perpendicular to the axial direction of the machine body, so that the duck wings can rotate around the rotating shaft; the four groups of ducted power components are respectively arranged on the upper wing surfaces of the two trailing edge flaps and the two side canards and all provide electric energy by a turbine generator arranged in the fuselage; through canard wing vert and trailing edge flap deflection drive duct power pack and deflect and then change thrust direction and then realized unmanned aerial vehicle's VTOL.

Description

Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power

Technical Field

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a vertical take-off and landing unmanned aerial vehicle adopting distributed duct power.

Background

At present, unmanned aerial vehicles are mainly divided into fixed-wing unmanned aerial vehicles and rotor unmanned aerial vehicles. The fixed wing unmanned aerial vehicle has long endurance time and high flying speed, but has high requirements on the field for taking off and landing, and cannot hover to perform tasks such as detection, monitoring and the like. The rotor unmanned aerial vehicle has low requirements on take-off and landing sites, can hover to perform tasks such as detection and monitoring, but has low flying speed and poor maneuverability.

In order to solve the above problems, a chinese patent of the prior art, such as application No. 201810315808.7, discloses a "short take-off and landing unmanned aerial vehicle using distributed duct power", in which a distributed power system is coupled with aerodynamic components such as wings of the unmanned aerial vehicle to improve aerodynamic efficiency and propulsion efficiency of the unmanned aerial vehicle, and short take-off and landing can be already achieved. But in this patent, receive unmanned aerial vehicle driving system overall arrangement restriction, this unmanned aerial vehicle can't realize VTOL and then have fixed wing unmanned aerial vehicle and rotor unmanned aerial vehicle's advantage concurrently.

Disclosure of Invention

The technical problem to be solved is as follows:

in order to avoid the defects of the prior art, the invention provides a vertical take-off and landing unmanned aerial vehicle adopting distributed duct power, and the unmanned aerial vehicle adopts the distributed duct power to improve the pneumatic efficiency and the propulsion efficiency of the unmanned aerial vehicle. The unmanned aerial vehicle adopts a novel duck wing layout with power, the ducted power groups are evenly distributed on duck wing surfaces, and meanwhile, the ducted power groups are evenly distributed on upper wing surfaces of wing trailing edge flaps. Wherein the canard can realize that 0 to 90 degrees vert, and 90 degrees deflections can be realized to wing trailing edge flap to change the thrust direction of duct power unit. When the thrust directions of all the ducted power groups are downward, the resultant force directions of the ducted power groups can be ensured to be vertically upward and pass through the gravity center of the machine, and the vertical take-off and landing of the machine are realized.

The technical scheme of the invention is as follows: a vertical take-off and landing unmanned aerial vehicle adopting distributed duct power comprises a fuselage, wings, ailerons, vertical empennages and a rudder, wherein the wings are symmetrically arranged on two sides of the rear part of the fuselage, and the two ailerons are respectively hinged to the outer side positions of the trailing edges of the wings on the two sides; the two trailing edge flaps are respectively hinged to the inner measuring positions of the trailing edges of the wings at two sides and can rotate for 0-90 degrees relative to the wing surfaces of the wings; the vertical tail wing is arranged right above the tail part of the fuselage, and the rudder is arranged on the vertical tail wing; the method is characterized in that: the device also comprises duck wings and a duct power set;

the duck wings are symmetrically arranged on two sides of the front part of the machine body, and the roots of the duck wings are connected with the machine body through a rotating shaft perpendicular to the axial direction of the machine body, so that the duck wings can rotate around the rotating shaft;

the four groups of ducted power components are respectively arranged on the upper wing surfaces of the two trailing edge flaps and the two side canards and all provide electric energy by a turbine generator arranged in the fuselage; the duct power set on the duck wing comprises 8 duct power units, and the thrust direction is changed along with the tilting of the duck wing; the ducted power set of the trailing edge flap comprises 10 ducted power units, and the thrust direction is changed by tilting of the trailing edge flap; the ducted power unit comprises a duct, a motor, an electronic speed regulator and a propeller.

The further technical scheme of the invention is as follows: the duck wing can wind the pivot is rotatory 0 ~ 90.

The further technical scheme of the invention is as follows: the duct power set penetrates through the upper wing surface and the lower wing surface of the duck wing.

Advantageous effects

The invention has the beneficial effects that: the hybrid power system adopts a gasoline-electric hybrid power scheme for improving the endurance time of the unmanned aerial vehicle, and can reduce oil consumption and emission. The pneumatic efficiency of the wing is improved by the boundary layer arranged on the upper surface of the ducted power group suction wing of the wing trailing edge flap upper wing surface; and the duck wings with power are adopted, so that the redundancy and the reliability of a power system are improved through the distribution of the power system of the whole unmanned aerial vehicle, and the phenomenon that the unmanned aerial vehicle is out of control due to single failure is avoided. Through canard wing vert and trailing edge flap deflection drive duct power pack and deflect and then change thrust direction and then realized unmanned aerial vehicle's VTOL.

Drawings

Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle in an efficient cruise state;

FIG. 2 is a structural bottom view of the unmanned aerial vehicle in the efficient cruise state;

FIG. 3 is a schematic structural diagram of the unmanned aerial vehicle in a vertical take-off and landing state;

fig. 4 is a structural bottom view of the unmanned aerial vehicle in a vertical take-off and landing state.

Description of reference numerals: 1-fuselage, 2-canard wing, 3-wing, 4-aileron, 5-vertical empennage, 6-rudder, and 7-ducted power unit.

Detailed Description

The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.

The invention relates to a vertical take-off and landing unmanned aerial vehicle adopting distributed duct power, which comprises a fuselage, duck wings, elevators, ailerons, vertical empennages, rudders and duct power sets, wherein the duct power sets are arranged on the upper wing surface and the lower wing surface of the duck wings, the duct power sets capable of deflecting are arranged on the wing trailing edge flaps, and vertical tails are arranged right above the tail of the fuselage.

This unmanned aerial vehicle's duck wing has played the effect of elevator for unmanned aerial vehicle takes off and land and flight in the manipulation of every single move direction. The ailerons are arranged at the positions of the rear edges of the left and right outer sides of the rear wing and are used for the rolling control of the unmanned aerial vehicle in taking off and landing and flying. The number of the trailing edge flaps is 2, the trailing edge flaps are respectively installed at the trailing edge positions of the left wing section and the right wing section of the wing in a hinged mode, and the trailing edge flaps rotate 0-90 degrees relative to the wing surfaces of the wing through a deflection mechanism in the wing.

The ducted power unit comprises 4 groups which are respectively arranged on the upper surfaces of the duck wings and the wings. Each group of ducted power sets comprises a ducted power unit, each ducted power unit comprises a duct, a motor, an electronic speed regulator and a propeller, and the ducted power sets deflect with trailing flaps to change the thrust direction. The ducted power components mounted on the duck wings are arranged in two rows, and each row is four; the ducted power components mounted on the upper surface of the wing are arranged in two rows, 10 in each row.

And a rudder is arranged on the rear side of the vertical tail wing and is used for controlling the taking-off and landing and the flying course of the unmanned aerial vehicle.

The power generation cabin is arranged on the lower cabin of the vertical empennage, the turbine generator is arranged in the power generation cabin, and fuel oil is combusted by the turbine generator to drive the power generation machine to provide electric energy as a ducted power set arranged on the wings.

The wing adopts a high aspect ratio straight wing form, the aspect ratio is 8-16, the sweepback angle is 5 degrees, and the dihedral angle is 0-10 degrees.

The distributed duct power vertical take-off and landing unmanned aerial vehicle is divided into a vertical take-off stage, a transitional flight stage, an efficient cruise stage and a vertical landing stage, and the flight process is as follows:

a. in the vertical takeoff stage, energy storage batteries in the aircraft body provide electric energy for four ducted power sets on the wings and the duck wings, and the four ducted power sets all work in the maximum power state. Four groups of duct power sets installed on the canard wing tilting and wing trailing edge deflection drive to deflect downwards to 90 degrees, thrust in a vertical downward direction is provided for the unmanned aerial vehicle, and vertical take-off is realized.

b. In the transitional flight stage, after the unmanned aerial vehicle climbs to a preset height, the four ducted power sets gradually turn to the horizontal state from the vertical state, so that the aircraft gradually accelerates until enough lift force is generated on the wings to enable the aircraft to fly horizontally, and at the moment, the four ducted power sets are converted to the horizontal state.

c. In the efficient cruising stage, a turbine engine in the airplane body drives a generator to work, one part of generated electric energy flows into an energy storage battery in the airplane body to be charged, the other part of the generated electric energy supplies energy to four groups of ducted power groups, and the ducted power groups positioned at the rear edge positions of the wings improve the pneumatic efficiency of the wings by sucking boundary layer airflow on the upper surfaces of the wings.

d. In the vertical landing stage, energy storage batteries in the aircraft body provide electric energy for four ducted power sets on the wings and the duck wings, and the four ducted power sets all work under the maximum power state. Four groups of duct power groups installed on the canard wing tilting and wing trailing edge deflection drive to deflect downwards to 90 degrees, and vertical downward thrust is provided for the unmanned aerial vehicle, so that vertical landing is realized.

As shown in fig. 1 to 4, the vertical take-off and landing unmanned aerial vehicle using distributed duct power in the embodiment includes a fuselage, wings, canard wings, elevators, ailerons, vertical tail wings, rudder, and duct power sets. The section of the middle part of the machine body is a rounded rectangle, and the machine head and the machine tail are respectively gradually contracted forwards and backwards. The wing adopts a high aspect ratio straight wing form, the aspect ratio is 11, the sweep angle is 5 degrees, and the dihedral angle is 0 degree. The ailerons are arranged at the positions of the trailing edges of the left and right outer sides of the wing. The 2 trailing edge flaps are respectively installed at the trailing edge positions of the wings in a hinged mode, and the trailing edge flaps rotate 0-90 degrees relative to the wing surfaces of the wings through a driving mechanism inside the wings. A group of ducted power groups are respectively arranged on the upper wing surface and the duck wing surface of each trailing edge flap, wherein the ducted power groups arranged on the duck wings are arranged in two rows, and each row is four; the ducted power components mounted on the upper surface of the wing are arranged in two rows, 10 in each row. Each ducted power unit comprises a duct, a motor, an electronic speed regulator and a propeller, and a ducted power set changes the thrust direction after the trailing edge flap deflects. The vertical tail wing is arranged above the tail part of the fuselage, and the rear part of the vertical tail wing is provided with a rudder. The generator cabin is positioned at the bottom of the vertical tail wing. The nose landing gear is installed under the front portion of the fuselage, and the main landing gear is respectively installed under the rear portion of the fuselage.

When a certain motor on the duct power pack breaks down in the flight process, the unmanned aerial vehicle can keep the thrust of the left side and the right side of the unmanned aerial vehicle balanced by adjusting the output power of the rest motors, and the flight safety of the unmanned aerial vehicle is guaranteed.

Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.

Claims

1. A vertical take-off and landing unmanned aerial vehicle adopting distributed duct power comprises a fuselage, wings, ailerons, vertical empennages and a rudder, wherein the wings are symmetrically arranged on two sides of the rear part of the fuselage, and the two ailerons are respectively hinged to the outer side positions of the trailing edges of the wings on the two sides; the two trailing edge flaps are respectively hinged to the inner measuring positions of the trailing edges of the wings at two sides and can rotate for 0-90 degrees relative to the wing surfaces of the wings; the vertical tail wing is arranged right above the tail part of the fuselage, and the rudder is arranged on the vertical tail wing; the method is characterized in that: the device also comprises duck wings and a duct power set;

2. The unmanned aerial vehicle that takes off and lands perpendicularly that adopts distributed duct power of claim 1 characterized in that: the duck wing can wind the pivot is rotatory 0 ~ 90.

3. The unmanned aerial vehicle that takes off and lands perpendicularly that adopts distributed duct power of claim 1 characterized in that: the duct power set penetrates through the upper wing surface and the lower wing surface of the duck wing.