CN215851830U - Semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses a semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle which comprises a fused fuselage structure, a hybrid structure wing part, an empennage part and a flight control surface part, wherein the fused fuselage structure is used for mounting and running a payload, a wheel type undercarriage and the like, the hybrid structure wing part realizes high lift force, thrust increase and the like, and the flight control surface part realizes flight attitude adjustment control. The wing with the diamond structure provides reasonable loading space for designing and installing radars and antennas, has higher lift-drag ratio, lift characteristic, structural performance and flight stability, improves the cruising performance by adopting a large aspect ratio, can be widely used for military reconnaissance, information collection, battlefield command, battlefield information processing and the like, and has great application prospect in drainage environment protection, ecological data measurement, aviation mapping, emergency rescue and the like.

Description

Semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle

Technical Field

The utility model relates to a semi-annular lift-increasing wing unmanned aerial vehicle, in particular to a semi-annular lift-increasing folding type wing unmanned aerial vehicle with a mixed structure.

Background

Unmanned aerial vehicle is applied towards such as a plurality of directions development such as shooting, reconnaissance, monitoring, and in recent years, the development of trades such as net red tourism live broadcast, tourism follow and shoot has proposed more requirements to unmanned aerial vehicle's technical application. From technical scheme, current use unmanned aerial vehicle mostly be small-size many rotor unmanned aerial vehicle, many rotor unmanned aerial vehicle all have great weakness in using voyage, payload, application environment, use height, can't realize the demand that free tourism such as plateau, mountain region, desert, Gobi beach, grassland of large tracts of land was shot, was looked a view in the air. Aiming at the requirements, the small-sized fixed wing unmanned aerial vehicle has great advantages in the aspects of voyage, flying height, flying speed and the like, meanwhile, in order to improve the carrying convenience and application value of the small-sized fixed wing unmanned aerial vehicle, the design is improved from the aspects of the overall design requirement, lift-drag ratio, performance technology and the like of the unmanned aerial vehicle, and meanwhile, the lifting design is completed on the structural performance, the overall appearance, the layout of high-lift aerodynamic wings and the like of the unmanned aerial vehicle; due to the fact that in actual use, requirements on the diversity of effective loads such as an optical camera, an infrared camera, a battery endurance system and the like exist, or a low-resistance high-lift load loading space is designed as far as possible, so that the high-lift-force high-speed cruising performance is adapted. Therefore, the market urgently needs a fixed wing unmanned aerial vehicle which can be designed according to the requirements of customers, is convenient to carry and has various functions.

The utility model has the technical problems that the current small-sized follow-up fixed wing unmanned aerial vehicle has the following key problems: (1) the device can realize two functions of air cruise and land cruise shooting, has higher space loading characteristic and realizes diversified functions; (2) the overall appearance of the fixed wing unmanned aerial vehicle is high in range, high in lift force and small in occupied space; (3) the wing can be carried by a single person and a vehicle, and the wing can be folded and folded to form the body so as to save a large amount of space. The effective solution of three above key problems will promote small-size fixed wing unmanned aerial vehicle to a great extent with clapping the performance and realizing the technique, promote the technical innovation of unmanned aerial vehicle for aerial photography, free tourism, this kind of unmanned aerial vehicle also can be used to aviation rescue, reconnaissance etc..

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 small-sized fixed wing unmanned aerial vehicle which has low-altitude tracking shooting and is convenient to carry.

In order to solve the problems, the utility model adopts the following scheme: the semi-annular high-lift foldable hybrid wing unmanned aerial vehicle is characterized by comprising a fused fuselage structure, a hybrid structure wing part, an empennage part, a flight control surface part and a wing unfolding and folding mechanism.

The integrated fuselage structure is used for mounting and operating effective loads, wheel type undercarriage and the like, the wing part of the mixed structure realizes high lift force, thrust increase and the like, and the flight control surface part realizes flight attitude adjustment control.

The fusion type fuselage structure comprises a nose cabin, a fuselage framework, a four-wheel type undercarriage and an undercarriage supporting seat; the fuselage framework is connected with the nose cabin and extends to the tail wing part; the four-wheel type undercarriage is positioned on the belly of the machine body, the front two wheels are positioned on the cabin position of the machine head, and the rear two wheels are positioned below the rear part of the framework of the machine body and are respectively connected with the cabin position of the machine head and the lower part of the framework of the machine body through undercarriage supporting seats.

The wing unfolding and folding mechanism is connected with the fused fuselage structure and is positioned between the fuselage skeleton and the nose cabin.

The wing part of the mixed structure comprises a main wing, a semi-annular wing, an auxiliary wing and a propulsion propeller; the semi-annular wing is arranged in the middle of the main wing; the auxiliary wing is arranged below the main wing, one end of the auxiliary wing is connected with the semi-annular wing, and the other end of the auxiliary wing is connected with the main wing through a wing connecting panel; the propulsion propeller is arranged at the front edge of the main wing and is positioned at the center of the semi-annular wing; the main wing is connected with the wing unfolding and folding mechanism through the wing connecting panel to realize the unfolding or folding of the wing part of the mixed structure, and the wing part of the mixed structure is folded on two sides of the fused fuselage structure in the folding state.

The tail wing part comprises a supporting structure, a horizontal tail and double vertical tails; the supporting structure is arranged at the upper part of the rear end of the machine body framework; the horizontal tail is arranged at the upper part of the supporting structure; the double vertical tails are vertically arranged at two sides of the horizontal tail.

The flight control surface part comprises a flap, an aileron, an elevator and a rudder; the flap is arranged at the inner rear edge of the main wing; the ailerons are arranged on the outer rear edge of the main wing; the elevator is arranged at the rear edge of the horizontal tail; the rudder is arranged at the rear edge of the double vertical tails.

Further, according to the design scheme, the semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle is characterized in that the aircraft nose cabin adopts a low-resistance flat streamline appearance design, a loading space is arranged in the aircraft nose cabin, and a shell of the aircraft nose cabin is made of glass fiber or composite material; the frame of the machine body is made of reinforced aluminum alloy or light high-strength material; the side of fuselage skeleton is equipped with the space that is used for mixed structure wing part to place the wing when receiving.

Further, according to the design scheme, the semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle is characterized in that the front two wheels of the four-wheel undercarriage are positioned at a position, which is 5% -15% of the length of a fuselage, away from a nose cabin, and the rear two wheels are positioned at a position, which is 5% -15% of the length of the fuselage, away from a tail part, below the rear part of a fuselage framework; the landing gear supporting seat is made of reinforced aluminum alloy, stainless steel or light high-strength material.

Further, according to the design scheme, the semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle is characterized in that the wing profile of the main wing is a low-speed wing profile, a laminar flow wing profile or a supercritical wing profile, the main wing is made of glass fiber reinforced plastics or light high-strength materials, and the aspect ratio is 6-10; the wing profile of the semi-annular wing is a low-speed wing profile or a laminar flow wing profile; the auxiliary wing airfoil is a low-speed airfoil, a laminar flow airfoil or a supercritical airfoil, and is made of glass fiber reinforced plastics or light high-strength materials; the propulsion propeller adopts 2-blade propeller, 3-blade propeller or 4-blade propeller, and the propeller blades are made of wood, glass fiber or light materials.

Further, according to the design scheme, the semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle is characterized in that the wing profile of the horizontal tail is a symmetrical wing profile; the wing profile of the double vertical tails is a symmetrical wing profile.

Further, according to the design scheme, the semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle is characterized in that the span-wise length of the flap is about 50% -60% of the half span length, and the chord length direction is 5% -15% of the chord length of the main engine; the spanwise length of the auxiliary wing is about 40-50% of the half span length, and the length in the chord length direction is 5-15% of the chord length of the main engine; the length of the elevator in the chord length direction is 10-25% of the chord length of the horizontal tail; the length of the rudder in the chord length direction is 10-25% of the chord length of the double vertical tails.

Further, according to the design scheme, the semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle is characterized in that the wing unfolding and folding mechanism comprises a fuselage reinforcing frame, a wing unfolding end face, a wing unfolding clamping groove, a wing folding end face, a wing folding clamping groove, a wing fuselage connecting structure and a wing connecting panel; the fuselage reinforcing frame is arranged between the aircraft nose cabin and the fuselage framework and penetrates through the fuselage; the upper end and the lower end of the wing connecting panel are respectively fixedly connected with the main wing and the auxiliary wing; the wing and body connecting structure is fixedly connected with the wing connecting panel; the wing and fuselage connecting structure is movably connected with the outer side end of the fuselage reinforcing frame; the wing unfolding end face is arranged in front of the outer side of the fuselage reinforcing frame; the wing unfolding clamping groove is arranged on the wing connecting panel and positioned in the front part of the wing and body connecting structure, and is matched with the wing unfolding end face, and when the wing is unfolded, the wing unfolding end face can be clamped with the wing unfolding clamping groove; the wing retraction end surface is arranged at the rear of the outer side of the fuselage reinforcing frame; the wing retraction clamping groove is arranged at the rear part of the wing body connecting structure on the wing connecting panel and matched with the wing retraction end face, and when the wing is retracted, the wing retraction end face is clamped with the wing retraction clamping groove.

The utility model has the following technical effects: (1) the low-resistance flat streamline appearance design is adopted, the aerodynamic performance of the machine body is effectively improved, meanwhile, a large load loading space is provided, and technical support is provided for diversified application directions.

(2) By adopting the wing with the mixed structure, namely the effective combination of the main wing, the auxiliary wing and the semi-annular wing, the larger lift force is effectively improved, and meanwhile, the span-wise space is saved.

(3) Through fuselage, the wing integrated optimization design, realize the effective expansion of wing and pack up two kinds of states, when having improved the unmanned aerial vehicle convenience, realized the one-machine multi-purpose function of two kinds of operating condition of air cruise flight (wing expansion state), land navigation state (wing packing up state).

Drawings

Fig. 1 is a perspective view (wing-deployed state) of the drone of the present invention.

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

Fig. 3 is a top view of the drone of the present invention.

Fig. 4 is a perspective view of the drone of the present invention (wing stowed state).

Fig. 5 is a structural schematic diagram of a wing unfolding and folding mechanism.

In the figure, 11 nose cabins, 12 fuselage skeletons, 13 four-wheel type undercarriages, 14 undercarriages supporting seats, 21 main wings, 22 semicircular wings, 23 auxiliary wings, 24 propeller propellers, 31 supporting structures, 32 horizontal tails, 33 double vertical tails, 41 flaps, 42 ailerons, 43 elevators, 44 rudders, 51 fuselage reinforcing frames, 52 wing expanding end faces, 53 wing expanding clamping grooves, 54 wing retracting end faces, 55 wing retracting clamping grooves, 56 wing-fuselage connecting structures and 57 wing connecting panels.

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", etc., 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 particular orientation, be constructed and operated in a particular 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 specified 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 specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Example 1:

the utility model provides a semi-annular lift-increasing foldable hybrid structure wing unmanned aerial vehicle which comprises a fused fuselage structure, a hybrid structure wing part, an empennage part and a flight control plane part, wherein the fused fuselage structure is used for mounting and running a payload, a wheel type undercarriage and the like, the hybrid structure wing part realizes high lift force, thrust increase and the like, and the flight control plane part realizes flight attitude adjustment control.

The fused fuselage structure consists of a nose cabin 11, a fuselage framework 12, a four-wheel undercarriage 13 and an undercarriage supporting seat 14. The aircraft nose cabin 11 adopts a low-resistance flat streamline appearance design, is a main loading space of a payload, and a shell of the aircraft nose cabin is made of glass fiber; the fuselage framework 12 is connected with the nose cabin 11 and extends to the empennage structure, and a mixed structure wing part retraction state space is reserved for reinforcing aluminum alloy; the four-wheel undercarriage 13 is positioned at the belly of the fuselage, the front two wheels are positioned at the cabin 11 of the nose and are 5 percent of the length of the fuselage away from the nose, and the rear two wheels are positioned below the rear part of the framework 12 of the fuselage and are 10 percent of the length of the fuselage away from the tail; the undercarriage supporting seat 14 is used for connecting the four-wheel undercarriage 13 with the nose cabin 11 and the fuselage framework 12, plays a supporting role, and is made of reinforced aluminum alloy, stainless steel or other light high-strength materials.

The wing part of the mixed structure consists of a main wing 21, a semi-annular wing 22, an auxiliary wing 23 and a propulsion propeller 24. The main wing 21 is located on the upper part of the wing part of the mixed structure and is a main structure for generating lift force, the wing part adopts a low-speed wing shape, a laminar flow wing shape or a supercritical wing shape, the material is a light high-strength material such as glass fiber reinforced plastic, the aspect ratio is 6, the main wing 21 can be in an unfolding state and a folding state, the unfolding state is a flying state, and the folding state is a land navigation or non-working state; the semi-annular wing 22 is positioned in the middle of the main wing 21, the diameter of the semi-annular wing is about one third of the half span length of the main wing 21, and the wing is a low-speed wing; the auxiliary wing 23 is positioned below the main wing 21 and connected with the fuselage and the semi-annular wing 22, the wing is a low-speed wing, a laminar wing or a supercritical wing, and the material is light high-strength material such as glass fiber reinforced plastics; the propulsion propeller 24 is positioned at the front edge of the main wing 21 and the center of the semi-annular wing 22, and adopts 2-blade propeller which is made of wood.

The tail section consists of a support structure 31, a horizontal tail 32, and a double vertical tail 33. The supporting structure 31 is located at the upper part of the rear end of the fuselage skeleton 12, the horizontal tail 32 is located at the upper part of the supporting structure 31, the wing profiles are symmetrical wing profiles, the double vertical tails 33 are located on two sides of the horizontal tail 32, and the wing profiles are symmetrical wing profiles.

The flight control surface part consists of a flap 41, an aileron 42, an elevator 43 and a rudder 44. The flap 41 is positioned at the inner rear edge of the main wing 21, the spanwise length is about 50% of half spanwise length, and the chord length direction is 10% of the chord length of the main wing 21; the ailerons 42 are positioned at the rear edge of the outer side of the main wing 21, the spanwise length is about 40 percent of half spanwise length, and the length of the chord length direction is 5 percent of the chord length of the main wing 21; the elevator 43 is positioned at the rear edge of the horizontal tail 32, and the length of the elevator in the chord length direction is 10% of that of the horizontal tail 32; the rudder 44 is positioned at the rear edge of the double vertical tails 33, and the length of the chord length direction is 10 percent of the chord length of the double vertical tails 33.

Example 2:

the utility model provides a semi-annular lift-increasing foldable hybrid structure wing unmanned aerial vehicle which comprises a fused fuselage structure, a hybrid structure wing part, an empennage part and a flight control plane part, wherein the fused fuselage structure is used for mounting and running a payload, a wheel type undercarriage and the like, the hybrid structure wing part realizes high lift force, thrust increase and the like, and the flight control plane part realizes flight attitude adjustment control.

The fused fuselage structure consists of a nose cabin 11, a fuselage framework 12, a four-wheel undercarriage 13 and an undercarriage supporting seat 14. The aircraft nose cabin 11 adopts the low-resistance flat streamline appearance design, which is the main loading space of the effective load, and the shell of the aircraft nose cabin is made of composite material; the fuselage framework 12 is connected with the nose cabin 11 and extends to the empennage structure, and a mixed structure wing part retraction state space is reserved for reinforcing aluminum alloy; the four-wheel undercarriage 13 is positioned at the belly of the fuselage, the front two wheels are positioned at the cabin 11 of the nose and are 10 percent of the length of the fuselage from the nose, and the rear two wheels are positioned below the rear part of the framework 12 of the fuselage and are 5 percent of the length of the fuselage from the tail; the undercarriage supporting seat 14 is used for connecting the four-wheel undercarriage 13 with the nose cabin 11 and the fuselage framework 12, plays a supporting role, and is made of reinforced aluminum alloy, stainless steel or other light high-strength materials.

The wing part of the mixed structure consists of a main wing 21, a semi-annular wing 22, an auxiliary wing 23 and a propulsion propeller 24. The main wing 21 is positioned on the upper part of the wing part of the mixed structure and is a main structure for generating lift force, the wing part adopts a low-speed wing shape, the material is glass fiber reinforced plastic, the aspect ratio is 8, the main wing 21 can be in an unfolding state and a folding state, the unfolding state is a flying state, and the folding state is a land navigation or non-working state; the semi-annular wing 22 is positioned in the middle of the main wing 21, the diameter of the semi-annular wing is about one third of the half span length of the main wing 21, and the wing is a laminar wing; the auxiliary wing 23 is positioned below the main wing 21 and connected with the fuselage and the semi-annular wing 22, and the wing is a low-speed wing made of glass fiber reinforced plastic; the propulsion propeller 24 is positioned at the front edge of the main wing 21 and the center of the semi-annular wing 22, and adopts 3-blade propeller which is made of glass fiber.

The tail section consists of a support structure 31, a horizontal tail 32, and a double vertical tail 33. The supporting structure 31 is located at the upper part of the rear end of the fuselage skeleton 12, the horizontal tail 32 is located at the upper part of the supporting structure 31, the wing profiles are symmetrical wing profiles, the double vertical tails 33 are located on two sides of the horizontal tail 32, and the wing profiles are symmetrical wing profiles.

The flight control surface part consists of a flap 41, an aileron 42, an elevator 43 and a rudder 44. The flap 41 is positioned at the inner rear edge of the main wing 21, the spanwise length is about 55% of half spanwise length, and the chord length direction is 10% of the chord length of the main wing 21; the ailerons 42 are positioned at the rear edge of the outer side of the main wing 21, the spanwise length is about 45 percent of half spanwise length, and the length of the chord length direction is 15 percent of the chord length of the main wing 21; the elevator 43 is positioned at the rear edge of the horizontal tail 32, and the length of the elevator in the chord length direction is 15% of that of the horizontal tail 32; the rudder 44 is positioned at the rear edge of the double vertical tails 33, and the length of the chord length direction is 15 percent of the chord length of the double vertical tails 33.

Example 3:

the utility model provides a semi-annular lift-increasing foldable hybrid structure wing unmanned aerial vehicle which comprises a fused fuselage structure, a hybrid structure wing part, an empennage part and a flight control plane part, wherein the fused fuselage structure is used for mounting and running a payload, a wheel type undercarriage and the like, the hybrid structure wing part realizes high lift force, thrust increase and the like, and the flight control plane part realizes flight attitude adjustment control.

The fused fuselage structure consists of a nose cabin 11, a fuselage framework 12, a four-wheel undercarriage 13 and an undercarriage supporting seat 14. The aircraft nose cabin 11 adopts a low-resistance flat streamline appearance design, is a main loading space of a payload, and a shell of the aircraft nose cabin is made of glass fiber; the fuselage framework 12 is connected with the nose cabin 11, extends to the empennage structure, is made of light high-strength materials, and leaves a mixed structure wing part retraction state space; the four-wheel undercarriage 13 is positioned at the belly of the fuselage, the front two wheels are positioned at the nose cabin 11 and are 12 percent of the length of the fuselage away from the nose, and the rear two wheels are positioned below the rear part of the fuselage framework 12 and are 10 percent of the length of the fuselage away from the tail; the undercarriage supporting seat 14 is used for connecting the four-wheel undercarriage 13 with the nose cabin 11 and the fuselage framework 12, plays a supporting role, and is made of reinforced aluminum alloy, stainless steel or other light high-strength materials.

The wing part of the mixed structure consists of a main wing 21, a semi-annular wing 22, an auxiliary wing 23 and a propulsion propeller 24. The main wing 21 is located on the upper part of the wing part of the mixed structure and is a main structure for generating lift force, the wing part adopts a low-speed wing shape, the material is glass fiber reinforced plastic, the aspect ratio is 10, the main wing 21 can be in an unfolding state and a folding state, the unfolding state is a flying state, and the folding state is a land navigation or non-working state; the semi-annular wing 22 is positioned in the middle of the main wing 21, the diameter of the semi-annular wing 22 is about one third of the half span length of the main wing 21, and the wing profile of the semi-annular wing 22 is a supercritical wing profile; the auxiliary wing 23 is positioned below the main wing 21 and connected with the fuselage and the semi-annular wing 22, the wing is a low-speed wing, a laminar wing or a supercritical wing, and the material is glass fiber reinforced plastic; the propulsion propeller 24 is positioned at the front edge of the main wing 21 and the center of the semi-annular wing 22, and 4-blade propellers are adopted and made of glass fibers.

The tail section consists of a support structure 31, a horizontal tail 32, and a double vertical tail 33. The supporting structure 31 is located at the upper part of the rear end of the fuselage skeleton 12, the horizontal tail 32 is located at the upper part of the supporting structure 31, the wing profiles are symmetrical wing profiles, the double vertical tails 33 are located on two sides of the horizontal tail 32, and the wing profiles are symmetrical wing profiles.

The flight control surface part consists of a flap 41, an aileron 42, an elevator 43 and a rudder 44. The flap 41 is positioned at the inner rear edge of the main wing 21, the spanwise length is about 60 percent of half spanwise length, and the chord length direction is 15 percent of the chord length of the main wing 21; the ailerons 42 are positioned at the outer rear edge of the main wing 21, the spanwise length is about 40 percent of half spanwise length, and the length in the chord length direction is 15 percent of the chord length of the main wing 21; the elevator 43 is positioned at the rear edge of the horizontal tail 32, and the length of the elevator in the chord length direction is 20% of that of the horizontal tail 32; the rudder 44 is positioned at the rear edge of the double vertical tails 33, and the length of the chord length direction is 20 percent of the chord length of the double vertical tails 33.

The wing unfolding and folding mechanism comprises a fuselage reinforcing frame 51, a wing unfolding end surface 52, a wing unfolding clamping groove 53, a wing folding end surface 54, a wing folding clamping groove 55, a wing-fuselage connecting structure 56 and a wing connecting panel 57; the fuselage reinforcing frame 51 is arranged between the aircraft nose cabin 11 and the fuselage framework 12 and penetrates through the fuselage; the upper end and the lower end of the wing connecting panel 57 are respectively fixedly connected with the main wing 21 and the auxiliary wing 23; the wing-body connecting structure 56 is fixedly connected with a wing connecting panel 57; the wing-body connecting structure 56 is movably connected with the outer side end part of the body reinforcing frame 51; the wing unfolding end surface 52 is arranged in front of the outer side of the fuselage reinforcing frame 51; the wing unfolding clamping groove 53 is arranged on the wing connecting panel 57 and positioned in front of the wing and fuselage connecting structure 56, and is matched with the wing unfolding end surface 52, and when the wing is unfolded, the wing unfolding end surface 52 can be clamped with the wing unfolding clamping groove 53; the wing retraction end surface 54 is arranged at the rear of the outer side of the fuselage reinforcing frame 51; the wing retraction slot 55 is arranged at the rear part of the wing body connecting structure 56 on the wing connecting panel 57 and matched with the wing retraction end surface 54, and when the wing is retracted, the wing retraction end surface 54 is clamped with the wing retraction slot 55.

The specific embodiments described herein are merely illustrative of the spirit of the utility model. Various modifications or additions may be made to the described embodiments or alternatives may be employed by those skilled in the art without departing from the spirit or ambit of the utility model as defined in the appended claims.

Although the terms nose cabin 11, fuselage skeleton 12, four-wheel undercarriage 13, undercarriage supporting base 14, main wing 21, semi-annular wing 22, auxiliary wing 23, propeller 24, support structure 31, horizontal tail 32, double vertical tail 33, flap 41, aileron 42, elevator 43, rudder 44, 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 (8)

1. A semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle is characterized in that the semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle comprises a fused fuselage structure, a hybrid wing part, an empennage part, a flight control surface part and a wing unfolding and folding mechanism;

the fusion type fuselage structure comprises a nose cabin (11), a fuselage framework (12), a four-wheel type undercarriage (13) and an undercarriage supporting seat (14); the fuselage framework (12) is connected with the nose cabin (11) and extends to the tail wing part; the four-wheel type undercarriage (13) is positioned at the belly of the machine body, the front two wheels are positioned at the nose cabin (11), the rear two wheels are positioned below the rear part of the machine body framework (12), and are respectively connected with the nose cabin (11) and the lower part of the machine body framework (12) through an undercarriage supporting seat (14) and fixedly connected with each other;

the wing unfolding and folding mechanism is connected with the fused fuselage structure and is positioned between the fuselage skeleton (12) and the nose cabin (11);

the wing part of the hybrid structure comprises a main wing (21), a semi-annular wing (22), an auxiliary wing (23) and a propulsion propeller (24); the semi-annular wing (22) is arranged in the middle of the main wing (21); the auxiliary wing (23) is arranged below the main wing (21), one end of the auxiliary wing is connected with the semi-annular wing (22), and the other end of the auxiliary wing is connected with the main wing (21) through a wing connecting panel (57); the propulsion propeller (24) is arranged at the front edge of the main wing (21) and is positioned at the center of the semi-annular wing (22); the main wing (21) is connected with the wing unfolding and folding mechanism through a wing connecting panel (57) to realize the unfolding or folding of the wing part of the mixed structure, and the wing part of the mixed structure is folded at two sides of the fused fuselage structure in the folding state;

the tail wing part comprises a supporting structure (31), a horizontal tail (32) and a double vertical tail (33); the supporting structure (31) is arranged at the upper part of the rear end of the fuselage skeleton (12); the horizontal tail (32) is arranged at the upper part of the supporting structure (31); the double vertical tails (33) are vertically arranged at two sides of the horizontal tail (32);

the flight control surface part comprises a flap (41), an aileron (42), an elevator (43) and a rudder (44); the flap (41) is arranged at the inner rear edge of the main wing (21); the ailerons (42) are arranged on the outer rear edge of the main wing (21); the elevator (43) is arranged at the rear edge of the horizontal tail (32); the rudder (44) is arranged at the rear edge of the double vertical tails (33).

2. The semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle of claim 1, wherein the nose cabin (11) is designed in a low-resistance flat streamline shape, a loading space is arranged in the nose cabin, and a shell of the nose cabin is made of glass fiber or composite material; the frame (12) is made of reinforced aluminum alloy or light high-strength material; and a space for placing the wings when the wing parts of the mixed structure are received is arranged on the side edge of the fuselage skeleton (12).

3. The semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle according to claim 1, wherein the front two wheels of the four-wheel undercarriage (13) are located at a position 5% -15% of the length of a fuselage from a nose cabin (11), and the rear two wheels are located at a position 5% -15% of the length of the fuselage from a tail part below the rear part of a fuselage skeleton (12); the landing gear supporting seat (14) is made of reinforced aluminum alloy, stainless steel or light high-strength material.

4. The semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle according to claim 1, wherein the main wing (21) is a low-speed wing, a laminar flow wing or a supercritical wing, is made of glass fiber reinforced plastic or a light high-strength material, and has an aspect ratio of 6-10; the airfoil profile of the semi-annular airfoil (22) is a low-speed airfoil profile or a laminar airfoil profile or a supercritical airfoil profile; the auxiliary wing (23) is a low-speed wing, a laminar flow wing or a supercritical wing, and is made of glass fiber reinforced plastics or light high-strength materials; the propulsion propeller (24) adopts 2-blade propeller, 3-blade propeller or 4-blade propeller, and the propeller blades are made of wood, glass fiber or light materials.

5. The semi-annular high lift foldable hybrid wing drone according to claim 1, characterised in that the wing profile of the horizontal tail (32) is a symmetrical wing profile; the wing profile of the double vertical tails (33) is a symmetrical wing profile.

6. The semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle of claim 1, wherein the semi-annular wing (22) has a diameter of 25% -35% of the half span length of the main wing (21).

7. The semi-annular lift-enhancing foldable hybrid wing unmanned aerial vehicle of claim 1, wherein the span-wise length of the flap (41) is about 50% -60% of the half span-wise length, and the chord length direction is 5% -15% of the chord length of the main wing (21); the spanwise length of the ailerons (42) is about 40-50% of half spanwise length, and the length in the chord length direction is 5-15% of the chord length of the main wing (21); the length of the elevator (43) in the chord length direction is 10-25% of that of the horizontal tail (32); the length of the rudder (44) in the chord length direction is 10-25% of the chord length of the double vertical tails (33).

8. The semi-annular lift-increasing foldable hybrid wing unmanned aerial vehicle according to claim 1, wherein the wing unfolding and folding mechanism comprises a fuselage reinforcing frame (51), a wing unfolding end surface (52), a wing unfolding clamping groove (53), a wing folding end surface (54), a wing folding clamping groove (55), a wing-fuselage connecting structure (56) and a wing connecting panel (57); the fuselage reinforcing frame (51) is arranged between the aircraft nose cabin (11) and the fuselage framework (12) and penetrates through the fuselage; the upper end and the lower end of the wing connecting panel (57) are respectively fixedly connected with the main wing (21) and the auxiliary wing (23); the wing and fuselage connecting structure (56) is fixedly connected with the wing connecting panel (57); the wing and fuselage connecting structure (56) is movably connected with the outer side end part of the fuselage reinforcing frame (51); the wing unfolding end surface (52) is arranged in front of the outer side of the fuselage reinforcing frame (51); the wing unfolding clamping groove (53) is arranged on the wing connecting panel (57) and positioned in the front part of the wing and body connecting structure (56), and is matched with the wing unfolding end surface (52), and when the wing is unfolded, the wing unfolding end surface (52) can be clamped with the wing unfolding clamping groove (53); the wing retraction end surface (54) is arranged at the rear of the outer side of the fuselage reinforcing frame (51); the wing retraction clamping groove (55) is arranged at the rear part of the wing body connecting structure (56) on the wing connecting panel (57) and matched with the wing retraction end surface (54), and when the wing is retracted, the wing retraction end surface (54) is clamped with the wing retraction clamping groove (55).

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