CN215707128U - Annular structure composite wing VTOL unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses an annular structure composite wing vertical take-off and landing unmanned aerial vehicle, which comprises an annular structure composite wing, a power propulsion structure and a flight control surface structure part, wherein the annular structure composite wing is used for generating flight lift force, providing structural strength, loading effective load and the like, the power propulsion structure realizes the vertical take-off and landing lift force and the flight thrust of the unmanned aerial vehicle, and the flight control surface structure part consists of a plurality of control surfaces and is used for controlling and adjusting horizontal flight and vertical attitude. Compared with the similar unmanned aerial vehicle, the unmanned aerial vehicle disclosed by the utility model has the advantages that the lift performance can be improved by more than 25% when flying flatly, the resistance is reduced by about 20%, the range is long, the load is large, and the unmanned aerial vehicle can be used for logistics transportation, post-disaster search and rescue and the like.

Description

Annular structure composite wing VTOL unmanned aerial vehicle

Technical Field

The utility model relates to a vertical take-off and landing unmanned aerial vehicle, in particular to an annular-structure composite-wing vertical take-off and landing unmanned aerial vehicle.

Background

The unmanned aerial vehicle has great application prospect in the aspects of logistics transportation, military reconnaissance, disaster early warning, geological survey, flood and flood rescue and the like, currently, the multi-rotor unmanned aerial vehicle and the fixed-wing unmanned aerial vehicle are available in the market, the two have advantages, the multi-rotor unmanned aerial vehicle can realize vertical take-off and landing, the fixed-wing unmanned aerial vehicle has the advantages of heavy load, long-range application potential, and the prior technical proposal combines the rotor and the fixed wing, in order to meet the functional requirements, but in the conventional scheme, a set of multi-rotor scheme is specially designed for realizing vertical take-off and landing, while in level flight, the weight of the multi-rotor-wing vertical system becomes important redundancy of flight, is not beneficial to flight, the payload has been reduced promptly, and simultaneously, unnecessary rotor system has caused unnecessary resistance to the level flies, forms useless and hinders, simultaneously, also has great influence to the unmanned aerial vehicle structure. For solving above problem, need design a section can realize VTOL, the unmanned aerial vehicle of the function that flies flatly, and do not cause phenomenons such as unnecessary load, the useless resistance that flies flatly, possesses the novel unmanned aerial vehicle who rises resistance ratio, high range, high-strength structure, but wide application in commodity circulation transportation, reconnaissance early warning etc..

The technical problem of the utility model is to realize the following key problems: (1) how to take the vertical take-off and landing functions of the unmanned aerial vehicle into consideration and improve the structural strength of the unmanned aerial vehicle; (2) how to effectively utilize a propulsion system and realize the multi-functional application of a set of propulsion system; (3) how to realize the effective improvement of the horizontal flying force-lifting performance and the lift-drag ratio characteristic. Effective solution of three key problem more than will solve the comprehensive problem of voyage, load, the mode of taking off and land to a great extent to make but this utility model unmanned aerial vehicle wide application in the high unmanned logistics transportation of economic nature, the trades such as emergency rescue, the military reconnaissance of adaptation take off and land condition.

Disclosure of Invention

The utility model aims to solve the problem that an improvement scheme or an alternative scheme is provided aiming at the defects in the prior art, and particularly provides a composite wing unmanned aerial vehicle with vertical take-off and landing functions, heavy load and excellent lift-drag ratio performance.

In order to solve the problems, the utility model adopts the following scheme: the unmanned aerial vehicle is characterized in that the unmanned aerial vehicle comprises an annular structure composite wing, a power propulsion structure and a flight control surface structure part; the annular structure composite wing consists of an annular structure wing, a straight wing and an effective load cabin; the straight wing penetrates through the annular structural wing; the payload bay is located at the center of the straight wing; the power propulsion structure comprises propulsion propellers and an unmanned aerial vehicle support, the propulsion propellers are symmetrically arranged on the annular structure wing through the unmanned aerial vehicle support, and the bottoms of the unmanned aerial vehicle supports are positioned on the same horizontal line; the flight control surface structure part consists of a plurality of control surfaces which are respectively arranged on the annular structure wing and the straight wing.

Further, according to the design scheme, the unmanned aerial vehicle with the annular structure and the composite wing for vertical take-off and landing is characterized in that the annular structure wing is circular or elliptical in a forward flying view, in a lateral view, an upper wing and a lower wing of the annular structure wing are close to the rear and the front respectively, a sweepback angle is 0-30 degrees, and the wing type is one of a low-speed wing type, a laminar flow wing type or a supercritical wing type.

Further, according to above-mentioned design scheme unmanned aerial vehicle is taken off and land perpendicularly to loop configuration composite wing, its characterized in that, unmanned aerial vehicle support length is 2~4 times of the biggest chord length of loop configuration wing, adopts the high combined material of structural strength, and its bottom is located same water flat line to sufficient stability when taking off and land perpendicularly.

Further, according to the design scheme, the annular structure composite wing vertical take-off and landing unmanned aerial vehicle is characterized in that the flight control surface structure part consists of an elevator, a rudder, an auxiliary elevator and an aileron; the elevator is positioned at the inner side rear edge of the center of the lower wing of the annular structure wing; the rudder is positioned on the lower wing of the annular structure wing and close to the trailing edge of the straight wing; the elevator and the rudder are separated by an unmanned aerial vehicle bracket; the auxiliary elevator is positioned at the inner side rear edge of the center of the upper wing of the annular structure wing; the chord lengths of the elevator, the rudder and the auxiliary elevator are 10-40% of the chord length of the airfoil at the corresponding position; the ailerons are positioned at the trailing edge of the outer wing of the straight wing, the length of the ailerons is about 0.1-0.25 of the wingtip of the straight wing, and the length of the ailerons is 15-35% of the chord length of the wing profile at the corresponding position.

Furthermore, according to the design scheme, the annular structure composite wing vertical take-off and landing unmanned aerial vehicle is characterized in that the power propulsion structure consists of 4 propulsion propellers and 4 unmanned aerial vehicle supports; the propulsion propeller is arranged at the front end of the unmanned aerial vehicle bracket and is connected with the annular structure wing through the unmanned aerial vehicle bracket; the unmanned aerial vehicle supports are symmetrically distributed above and below the straight wing, and the propulsion propellers on the upper side and the lower side of the straight wing are located on different horizontal planes.

Further, according to above-mentioned design scheme unmanned aerial vehicle is taken off and land perpendicularly to loop configuration composite wing, its characterized in that, the paddle of propelling the screw can select for use metal, combined material, wooden material etc. is 2, 3, 4 paddles.

Further, according to the design scheme, the annular structure composite wing vertical take-off and landing unmanned aerial vehicle is characterized in that the straight wings are positioned on the diameter or the long axis of the annular structure wings; the spread length of the straight wing is 1.8-4 times of the diameter or the long axis of the wing with the annular structure; the wing profile of the straight wing is one of a low-speed wing profile, a laminar flow wing profile or a supercritical wing profile, and the wing tip of the straight wing is in a round sweepback shape.

The utility model has the following technical effects: the composite wing with the annular structure is used for generating flight lift force, providing structural strength, loading effective load and the like, the power propulsion structure realizes the vertical take-off and landing lift force and the horizontal flight thrust of the unmanned aerial vehicle, and the flight control surface structural part consists of a plurality of control surfaces and is used for horizontal flight and vertical attitude control adjustment.

The payload cabin is positioned in the center of the annular structure wing, aerodynamic resistance is reduced by adopting a streamline design, and the aerodynamic resistance is used for loading a photoelectric detector, a small radar or other payloads.

The unmanned aerial vehicle support adopts the high combined material of structural strength, and its bottom is located same water flat line to sufficient stability when VTOL.

By adopting the annular structure wing, higher structural strength can be realized, partial lift force during flat flight can be provided, and the resistance is relatively reduced by about 20-30%.

By adopting the composite wing combining the annular structure wing and the straight wing, the lift force is improved by about 25-35% during flat flight, and the increase of the load of the unmanned aerial vehicle is facilitated.

The unmanned aerial vehicle support is combined with the wings of the annular structure and the straight wings, so that the requirements of vertical take-off and landing and flying of multiple rotors are effectively combined, the functions of vertical take-off and landing and flying are realized, and meanwhile, the unmanned aerial vehicle support has a longer range and is longer in voyage, and the range is improved by about 15%.

The annular structure wing is the slash when unmanned aerial vehicle level flies and arranges, can effectual reduction resistance and impel the interference between the screw to promote flight power, make it possess farther journey and longer duration of a voyage, bigger at the load.

During the use, with the vertical placing on the plane of unmanned aerial vehicle, keep the gesture of standing through four unmanned aerial vehicle supports. The four propulsion propellers are started to maintain stable upward lift, after the unmanned aerial vehicle is lifted off, the flight control surface structure part is adjusted, the upper propulsion propeller group and the lower propulsion propeller group of the straight wing are adjusted in a matched mode to generate power difference until the unmanned aerial vehicle is adjusted to be in a flat flight state, then the power of the upper propulsion propeller group and the lower propulsion propeller group of the straight wing are continuously adjusted to maintain balance, flat flight is achieved, the annular structure wing and the straight wing provide most of lift during flat flight, and adjustment of flight postures is achieved through the matching of the flight control surface structure part and the propulsion propellers. The same is true when landing, and the unmanned aerial vehicle is adjusted to be in a vertical state and then slowly landed.

Drawings

Fig. 1 is an oblique view of the drone of the present invention.

Fig. 2 is a top view of the drone of the present invention.

Fig. 3 is a side view of the drone of the present invention (level flight).

Fig. 4 is a side view (in a suspended state) of the drone of the present invention.

Fig. 5 is a front view (level flight state) of the drone of the present invention.

In the figure, 11 ring structure wings, 12 straight wings, 13 payload pods, 21 propeller, 22 drone support, 31 elevators, 32 rudders, 33 elevator auxiliary rudders, 34 ailerons.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The meaning of the above terms in the present invention can be understood in a specific case by those skilled in the art.

Example 1:

the utility model provides an annular structure composite wing vertical take-off and landing unmanned aerial vehicle, which comprises an annular structure composite wing, a power propulsion structure and a flight control surface structure part, wherein the annular structure composite wing is used for generating flight lift force, providing structural strength, loading effective load and the like, the power propulsion structure realizes the vertical take-off and landing lift force and the plane thrust of the unmanned aerial vehicle, and the flight control surface structure part consists of a plurality of control surfaces and is used for controlling and adjusting plane flight and vertical attitude.

The annular structure composite wing is composed of an annular structure wing 11, a straight wing 12 and a payload cabin 13, the annular structure wing 11 is circular or elliptical in a flight forward view angle, in a lateral view angle, an upper wing of the annular structure wing 11 is close to the rear, a lower wing of the annular structure wing 11 is close to the front, a sweepback angle is 0-30 degrees, the wing type adopts a low-speed wing type, a laminar flow wing type, a supercritical wing type and the like, and when the wing type is elliptical, two focuses are positioned on the straight wing 12; the straight wing 12 is positioned on the diameter or the long axis of the annular structure wing 11, the span length of the straight wing 12 is 1.8-4 times of the diameter or the long axis of the annular structure wing 11, the wing profile of the straight wing 12 is a low-speed wing profile, a laminar flow wing profile, a supercritical wing profile and the like, and the wing tip is round and swept backward; the payload compartment 13 is located at the center of the ring structure wing 11, adopts a streamline design to reduce aerodynamic drag, and is used for loading a photoelectric detector, a small radar or other payloads.

The power propulsion structure consists of 4 propulsion propellers 21 and 4 unmanned aerial vehicle supports 22, the propulsion propellers 21 are respectively positioned on the annular structure wing 11 and symmetrically distributed above and below the straight wing, and the blades can be made of 2, 3 or 4 blades and can be made of metal, composite materials, wood materials and the like; unmanned aerial vehicle support 22 links to each other with propulsion screw 21, and unmanned aerial vehicle support 22 length adopts the high carbon fiber of structural strength or combined material for 2~4 times of the biggest chord length of loop configuration wing 11, and its bottom is located same water flat line to sufficient stability when VTOL.

The flight control surface structure part comprises an elevator 31, a rudder 32, an auxiliary elevator 33 and an aileron 34, wherein the elevator 31 is positioned at the inner rear edge of the lower wing of the annular structure wing 11, the rudder 32 is positioned at the lower wing and is close to the rear edge of the straight wing 12, the elevator 31 and the rudder 32 are separated by an unmanned aerial vehicle bracket 22, the auxiliary elevator 33 is positioned at the inner rear edge of the upper wing of the annular structure wing 11, and the chord lengths of the elevator 31, the rudder 32 and the auxiliary elevator 33 are 10-40% of the chord length of the wing at the corresponding position; the ailerons 34 are positioned at the trailing edge of the outer wing of the straight wing 12, the wing tip of the straight wing 12 is about 0.1-0.25 of the span length, and the chord length of the ailerons 34 is 15-35% of the chord length of the wing at the corresponding position.

When the unmanned aerial vehicle vertically takes off and lands, the 4 propelling propellers 21 face upwards to generate pulling force, and after the unmanned aerial vehicle reaches the level flying height, the unmanned aerial vehicle changes to a level flying state, the 4 propelling propellers 21 generate pushing force forwards, and the annular structure wing 11 and the straight wing 12 jointly generate lifting force.

Example 2:

example 2 differs from example 1 in that: the annular structure wing 11 is circular in a forward flying view angle, in a lateral view angle, an upper wing and a lower wing of the annular structure wing 11 are close to the back and the front respectively, a sweep angle is 5 degrees, and the wing is a low-speed wing; the span length of the straight wing 12 is 2.5 times of the diameter or long axis of the annular structure wing 11, and the wing profile of the straight wing 12 is a low-speed wing profile;

the propeller 21 blade is made of metal material and 2 blades; the length of the unmanned aerial vehicle bracket 22 connected with the lower wing propulsion propeller 21 is 2 times of the maximum chord length of the annular structure wing 11, and the unmanned aerial vehicle bracket is made of carbon fiber;

the chord lengths of the elevator 31, the rudder 32 and the auxiliary elevator 33 are 10 percent of the chord length of the airfoil at the corresponding position; the chord length of the aileron 34 is about 0.1 percent of the chord length of the straight wing 12 and the chord length of the aileron 34 is 15 percent of the chord length of the wing at the corresponding position.

Example 3:

example 3 differs from example 1 in that: the annular structure wing 11 is elliptical in a forward flight view, in a lateral view, an upper wing and a lower wing of the annular structure wing 11 are close to the back and the front respectively, a sweep angle is 15 degrees, and the wing section is a laminar flow wing section; the span length of the straight wing 12 is 3 times of the diameter or long axis of the annular structure wing 11, and the wing profile of the straight wing 12 is a laminar flow wing profile;

the propeller 21 is made of carbon fiber composite material and 3 blades; the length of the unmanned aerial vehicle bracket 22 connected with the lower wing propulsion propeller 21 is 2.5 times of the maximum chord length of the annular structure wing 11, and the unmanned aerial vehicle bracket is made of composite materials;

the chord lengths of the elevator 31, the rudder 32 and the auxiliary elevator 33 are 20 percent of the chord length of the airfoil at the corresponding position; the chord length of the aileron 34 is about 0.15 percent of the chord length of the straight wing 12 and the chord length of the aileron 34 is 25 percent of the chord length of the wing at the corresponding position.

Example 4:

example 4 differs from example 1 in that: the annular structure wing 11 is elliptical in the forward visual angle of flight, the upper wing and the lower wing of the annular structure wing 11 are close to the back and the sweep angle is 25 degrees in the lateral visual angle, and the wing profile adopts a supercritical wing profile; the span length of the straight wing 12 is 3.5 times of the diameter or long axis of the annular structure wing 11, and the wing profile of the straight wing 12 is a supercritical wing profile;

the propeller 21 blade is made of carbon fiber composite material and 4 blades; the length of the unmanned aerial vehicle bracket 22 connected with the lower wing propulsion propeller 21 is 3.5 times of the maximum chord length of the annular structure wing 11, and the unmanned aerial vehicle bracket is made of carbon fiber;

the chord lengths of the elevator 31, the rudder 32 and the auxiliary elevator 33 are 35 percent of the chord length of the airfoil at the corresponding position; the chord length of the aileron 34 is about 0.20 percent of the chord length of the straight wing 12 and the chord length of the aileron 34 is 35 percent of the chord length of the wing at the corresponding position.

Although the terms ring structure wing 11, straight wing 12, payload bay 13, propeller 21, drone cradle 22, elevator 31, rudder 32, elevator auxiliary rudder 33, aileron 34, etc. are used more herein, the possibility of using other terms is not excluded. These terms are used merely to more conveniently describe and explain the nature of the present invention; they are to be construed as being without limitation to any additional limitations that may be imposed by the spirit of the present invention.

Claims (7)

1. The unmanned aerial vehicle is characterized in that the unmanned aerial vehicle comprises an annular structure composite wing, a power propulsion structure and a flight control surface structure part; the annular structure composite wing consists of an annular structure wing (11), a straight wing (12) and a payload cabin (13); the straight wing (12) penetrates through the annular structural wing (11); the payload bay (13) is located at the centre of a straight wing (12); the power propulsion structure comprises propulsion propellers and an unmanned aerial vehicle support, the propulsion propellers are symmetrically arranged on the annular structure wing (11) through the unmanned aerial vehicle support, and the bottoms of the unmanned aerial vehicle supports are positioned on the same horizontal line; the flight control surface structure part consists of a plurality of control surfaces which are respectively arranged on the annular structure wing (11) and the straight wing (12).

2. The ring-structured composite wing VTOL UAV according to claim 1, wherein the ring-structured wing (11) is circular or elliptical in the forward view, and the upper wing and the lower wing of the ring-structured wing (11) are backward and forward respectively in the lateral view, and the sweep angle is 0-30 degrees, and the wing profile is one of a low-speed wing profile, a laminar wing profile or a supercritical wing profile.

3. The ring-shaped structure composite wing VTOL UAV of claim 1, wherein, the length of the UAV bracket (22) is 2-4 times of the maximum chord length of the ring-shaped structure wing (11), and the UAV bracket is made of a composite material with high structural strength, and the bottom of the UAV bracket is positioned on the same horizontal line, so that the UAV bracket has enough stability during VTOL.

4. The ring structure composite wing VTOL UAV of claim 1, wherein the flight control surface structure is partially composed of elevators (31), rudders (32), lift-assisted rudders (33), ailerons (34); the elevator (31) is positioned at the central inner rear edge of the lower wing of the annular structure wing (11); the rudder (32) is positioned at the lower wing of the annular structure wing (11) and close to the rear edge of the straight wing (12); the elevator (31) and the rudder (32) are separated by an unmanned aerial vehicle bracket (22); the auxiliary elevator (33) is positioned at the inner side rear edge of the center of the upper wing of the annular structure wing (11); the chord lengths of the elevator (31), the rudder (32) and the auxiliary elevator (33) are 10-40% of the chord length of the airfoil at the corresponding position; the ailerons (34) are positioned at the trailing edge of the outer wing of the straight wing (12), the wing tip of the straight wing (12) is about 0.1-0.25 of the span length, and the chord length of the ailerons (34) is 15-35% of the chord length of the wing section at the corresponding position.

5. The ring structure composite wing VTOL UAV of claim 1, wherein the power propulsion structure is composed of 4 propulsion propellers (21) and 4 UAV supports (22); the propulsion propeller (21) is arranged at the front end of the unmanned aerial vehicle support (22) and is connected with the annular structure wing (11) through the unmanned aerial vehicle support (22); the unmanned aerial vehicle supports (22) are symmetrically distributed above and below the straight wing (12), and the propulsion propellers on the upper side and the lower side of the straight wing (12) are located on different horizontal planes.

6. The ring-structured composite wing VTOL UAV according to claim 1, wherein the blades of the propulsion propeller are 2, 3 or 4 blades made of metal, composite material or wood.

7. The ring structure composite wing VTOL UAV of claim 2, wherein the straight wing (12) is located on the diameter or long axis of the ring structure wing (11); the spreading length of the straight wing (12) is 1.8-4 times of the diameter or the long axis of the annular structure wing (11); the wing profile of the straight wing (12) is one of a low-speed wing profile, a laminar flow wing profile or a supercritical wing profile, and the wing tip of the straight wing is in round sweepback.

Images