Tilting power vertical take-off and landing unmanned aerial vehicle adopting linked wing layout

Abstract

The utility model discloses a tiltable power vertical take-off and landing unmanned aerial vehicle adopting a linked wing layout. The tiltable power vertical take-off and landing unmanned aerial vehicle comprises a fuselage, a pair of front wings, a pair of rear wings, a tail connecting wing and a side end connecting wing, the pair of front wings are respectively connected to two sides of the head of the fuselage; the pair of rear wings are respectively arranged on two sides above the rear part of the fuselage; the tail connecting wing is arranged on the upper side of the rear part of the fuselage and is respectively connected with the rear wings on the two sides; wingtips of the rear wings are connected with the front wings through the side end connecting wings. A front propeller is mounted on the lower side of each front wing, a lower hanging type mounting arm capable of tilting and adjusting in the front-back direction is arranged on the lower side of each rear wing, and a rear propeller is mounted at the tail end of the lower hanging type mounting arm. According to the utility model, the influence of the downward washing flow field of the front wing on the rear wing can be reduced, the lift-drag ratio of the rear wing is improved, the dead weight is reduced, and the cruising ability is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to aerospace and low-altitude equipment technical field, concretely relates to a kind of tiltable power vertical take-off unmanned aerial vehicle using wing layout. BACKGROUND

[0002] Current small and medium-sized vertical take-off compound wing unmanned aerial vehicle is mostly using conventional aerodynamic layout, and payload and endurance time are short board, even if there are a few unmanned aerial vehicles with slightly longer endurance time, the payload is also relatively small.

[0003] There are some new layouts on the market to solve the above problems, such as tandem wing layout of front and rear wings (for reference to Chinese utility model patent CN218112983U discloses a tandem wing unmanned aerial vehicle), or wing layout (for reference to Chinese utility model patent CN207860452U discloses a vertical take-off wing unmanned aerial vehicle), the induced drag of tandem wing layout is greater than that of wing layout, and the structural strength is also not as good as wing layout.

[0004] The existing wing layout vertical take-off unmanned aerial vehicle has the problems of low efficiency and large interference to the main wing flow field in the arrangement form of vertical take-off power propeller.

[0005] In addition, whether it is the current tandem wing layout or wing layout vertical take-off unmanned aerial vehicle technology, the rear wing is affected by the downwash airflow of the front wing, resulting in low lift-drag ratio, which affects the overall lift-drag ratio.

[0006] In addition, the rotor power and the tail thrust are independently arranged, and in different flight modes, another set of power system will bring a large dead weight, reducing the endurance time of the whole machine. UTILITY MODEL CONTENTS

[0007] In view of the defects in the prior art, the utility model provides a tiltable power vertical take-off unmanned aerial vehicle using wing layout to reduce the influence of the rear wing by the downwash flow field of the front wing, improve the lift-drag ratio of the rear wing, and reduce the dead weight and improve the endurance.

[0008] The utility model provides a tiltable power vertical take-off unmanned aerial vehicle using wing layout, comprising:

[0009] A fuselage;

[0010] A pair of front wings, the pair of front wings are respectively connected to the two sides of the head of the fuselage;

[0011] A pair of rear wings, the pair of rear wings are respectively arranged on the two sides above the rear of the fuselage;

[0012] Tail connecting wing, the tail connecting wing is arranged on the upper side of the rear of the fuselage and connected with the rear wings on both sides respectively;

[0013] side end connecting wings, the wing tips of each of the rear wings are connected with the front wing through the side end connecting wings;

[0014] Wherein, the lower side of each of the front wings is installed with a front propeller, the lower side of each of the rear wings is provided with a downward hanging type mounting arm capable of being adjusted in the forward and backward directions, and the tail end of the downward hanging type mounting arm is installed with a rear propeller.

[0015] Further, the front wing is a backward swept wing, and the rear wing is a straight wing near the tail end connecting wing and a forward swept wing near the side end connecting wing.

[0016] Further, the sweep angle of the front edge of the backward swept wing is 23.5°±2°, and the sweep angle of the front edge of the forward swept wing is 13°±2°.

[0017] Further, the installation angle of the front wing is greater than that of the rear wing.

[0018] Further, the tail end connecting wing comprises two V-shaped connecting wing plates, one end of each of the two connecting wing plates is fixed on the fuselage, and the other end of each of the two connecting wing plates is connected with the rear wing on the side.

[0019] Further, the rear side of each of the two connecting wing plates is provided with a rudder surface.

[0020] Further, the front side of the front wing is provided with a front hanging type mounting arm, and the front propeller is installed on the lower side of the front hanging type mounting arm.

[0021] Further, the maximum angle of forward inclination of the downward hanging type mounting arm is α, and the included angle β between the axis of the downward hanging type mounting arm and the rear propeller is 180°-α.

[0022] Further, the maximum angle α of forward inclination of the downward hanging type mounting arm is 20°+5°, and the maximum angle γ of backward inclination of the downward hanging type mounting arm is 130°±5°.

[0023] Further, the lower side of the front part of the fuselage is provided with a main landing gear, and the lower side of the tail part of the fuselage is provided with a tail fin.

[0024] The beneficial effects of the utility model lie in:

[0025] When the unmanned aerial vehicle vertically takes off and lands, the downward hanging type mounting arm is driven to incline forward, so that the rear propeller at the tail end of the downward hanging type mounting arm faces downward, and the two front propellers and the rear propeller can provide stable vertical lift for the unmanned aerial vehicle; when the unmanned aerial vehicle turns to the flat flight state, the downward hanging type mounting arm is gradually turned to face backward under the control of the flight control system, so as to provide the tail thrust for the horizontal flight of the unmanned aerial vehicle; in this way, the tail thrust does not need to be separately arranged, the dead weight of the whole machine can be reduced, and the endurance capability can be improved.

[0026] More importantly, in the level flight state, the rear propeller rotates to the rear side of the rear wing, which can actively control the flow field while providing the tail thrust, on the one hand, the airflow of the rear wing is straightened, the influence of the rear wing by the flow field of the front wing is minimized, the lift-drag ratio of the rear wing is greatly improved, on the other hand, the rotating direction of the airflow flowing through the rear propeller is opposite to the direction of the wing tip vortex, which further offsets the downwash caused by the wing tip vortex, further improves the lift-drag ratio of the rear wing. BRIEF DESCRIPTION OF DRAWINGS

[0027] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the specific embodiments or the prior art description will be briefly introduced below. In all the drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, each element or part is not necessarily drawn according to the actual proportion.

[0028] Figure 1 is a perspective view of the embodiment of the present application;

[0029] Figure 2 is a top view of the embodiment of the present application;

[0030] Figure 3 is a schematic view of the embodiment of the present application in vertical take-off and landing;

[0031] Figure 4 is a schematic view of the embodiment of the present application in level flight state;

[0032] Figure 5 is a schematic view of the embodiment of the present application in which the rotating direction of the airflow flowing through the rear propeller is opposite to the direction of the wing tip vortex;

[0033] Figure 6 is a schematic view of the embodiment of the present application in which the rudder surface on the two connected wing plates plays the effect of elevator;

[0034] Figure 7 is a schematic view of the embodiment of the present application in which the rudder surface on the two connected wing plates plays the effect of rudder.

[0035] In the drawings, 100 is a fuselage; 200 is a front wing; 300 is a rear wing; 310 is a flat wing; 320 is a forward-swept wing; 400 is a tail connecting wing; 410 is a connecting wing plate; 420 is a rudder surface; 500 is a side end connecting wing; 610 is a front propeller; 620 is a front hanging type mounting arm; 710 is a lower hanging type mounting arm; 720 is a rear propeller; 800 is a main landing gear; and 900 is a tail fin. DETAILED DESCRIPTION

[0036] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings. These embodiments are merely illustrative of the present invention and should not be construed as limiting the scope of protection of the present invention.

[0037] It should be noted that, unless otherwise stated, the technical or scientific terms used in this application shall have the ordinary meaning as understood by one of ordinary skill in the art to which this utility model pertains.

[0038] like Figures 1-7 As shown, this utility model embodiment provides a tiltable powered vertical take-off and landing unmanned aerial vehicle with a connected wing layout, including a fuselage 100, a pair of front wings 200, a pair of rear wings 300, a tail connecting wing 400 and a side connecting wing 500.

[0039] The two forewings 200 are respectively connected to the two sides of the nose of the fuselage 100.

[0040] In this embodiment, the front wing 200 is a swept wing, and the sweep angle of the leading edge of the swept wing is 23.5°±2°, preferably 23.5°.

[0041] The pair of rear wings 300 are located on both sides above the rear of the fuselage 100.

[0042] In this embodiment, the section of the rear wing 300 connected to the tail wing 400 is a straight wing 310, and the section connected to the side end wing 500 is a forward-swept wing 320. The sweep angle of the leading edge of the forward-swept wing 320 is 13°±2°, preferably 13°.

[0043] In this embodiment, the mounting angle of the front wing 200 is greater than that of the rear wing 300. Here, the mounting angle refers to the angle between the width direction of the wing and the horizontal.

[0044] The tail connecting wing 400 is located on the upper rear of the fuselage 100 and is connected to the rear wings 300 on both sides.

[0045] Preferably, the tail connecting wing 400 includes two V-shaped connecting wing plates 410, one end of each connecting wing plate 410 is fixed to the fuselage 100, and the other end of each connecting wing plate 410 is connected to the rear wings 300 on both sides.

[0046] In this embodiment, the tail connecting wing 400 is designed in a V-shape, which can reduce interference drag. At the same time, the area between the two rear wings 300 avoids the central region where the downwash field of the forewing is strongest, which greatly improves the flow field of the rear wing affected by the downwash field of the forewing. Furthermore, the tail connecting wing 400 between the two rear wings 300 is designed in a V-shape, which provides better stress conditions than the existing T-shaped structure.

[0047] More preferably, the rear side of the two connecting wings 410 is provided with a rudder 420. Referring to Figure 6 When the rudders 420 on the two connecting wings 410 are both deflected inward, the function of an elevator is achieved, referring to Figure 7 When the rudders 420 on the two connecting wings 410 are deflected to the same side, the function of a rudder is achieved, therefore, the embodiment provides the rudders 420 on the rear side of the two connecting wings 410, which can simultaneously achieve the functions of an elevator and a rudder.

[0048] Optionally, the two connecting wings 410 of the tail connecting wing 400 have a certain sweep angle to reduce the resistance in the level flight state.

[0049] The wing tips of each rear wing 300 are connected to the side end connecting wing 500 between the front wing 200 and the side end connecting wing 500, which not only reduces the induced drag, but also strengthens the structure of the front and rear wings.

[0050] Optionally, the side end connecting wing 500 is designed in a quick-release manner between the front wing 200 and the rear wing 300, which is convenient for transportation and installation.

[0051] The underside of each front wing 200 is provided with a front propeller 610, and the underside of each rear wing 300 is provided with a downward hanging mounting arm 710 that can be adjusted in the front and rear directions, and the end of the downward hanging mounting arm 710 is provided with a rear propeller 720.

[0052] It can be understood that the adjustment of the inclination of the downward hanging mounting arm 710 can be driven by an electric motor, a hydraulic motor, etc., and the embodiment does not make specific limitations thereon, and preferably an electric motor is used.

[0053] Optionally, the front side of the front wing 200 is provided with a front hanging mounting arm 620, and the front propeller 610 is installed on the underside of the front hanging mounting arm 620. The front hanging mounting arm 620 has a streamlined shape, which can reduce the resistance and at the same time ensure the aerodynamic efficiency of the front propeller 610 in vertical take-off and landing.

[0054] In the embodiment, referring to Figure 3 , the maximum angle of the forward inclination of the downward hanging mounting arm 710 is α, and the included angle β between the downward hanging mounting arm 710 and the rear propeller 720 is 180°-α. When the downward hanging mounting arm 710 is inclined forward to the maximum angle, the rear propeller 720 is just vertically downward, which can reduce the influence of the rear wing 300 on the aerodynamic efficiency of the rear propeller 720.

[0055] Specifically, referring to Figure 3 and Figure 4 , the maximum angle of the forward inclination of the downward hanging mounting arm 710 is 20°+5°, and preferably 20°, and the maximum angle of the rear inclination of the downward hanging mounting arm 710 is γ, which is 130°±5°, and preferably 130°.

[0056] In this embodiment, the lower side of the front part of the fuselage 100 is provided with the main landing gear 800, and the lower side of the tail part of the fuselage 100 is provided with the tail fin 900, which can strengthen the heading stability of the unmanned aerial vehicle and also serve as a support point together with the two-point main landing gear 800 of the front part of the fuselage 100 when the unmanned aerial vehicle is parked on the ground.

[0057] Optionally, the tail fin 900 has a certain sweepback angle to reduce the drag in the flat flying state.

[0058] Referring to Figure 3 When the unmanned aerial vehicle takes off vertically, the downwardly hanging mounting arm 710 is tilted forward, so that the rear propeller 720 at the end of the downwardly hanging mounting arm 710 faces downward, and the two front propellers 610 and the rear propeller 720 can provide stable vertical lift for the unmanned aerial vehicle, referring to Figure 4 When the unmanned aerial vehicle turns to the flat flying state, the downwardly hanging mounting arm 710 is gradually turned backward under the control of the flight control system to provide a tail thrust for the horizontal flight of the unmanned aerial vehicle, so that a separate tail thrust does not need to be arranged, the dead weight of the whole machine can be reduced, and the endurance can be improved.

[0059] More importantly, in the flat flying state, the rear propeller 720 is turned to the rear side of the rear wing 300, which can actively control the flow field while providing the tail thrust, on the one hand, the airflow of the rear wing 300 is straightened, which maximally reduces the influence of the downwash flow field of the front wing 200 on the rear wing 300, greatly improves the lift-drag ratio of the rear wing 300, and on the other hand, the rotation direction of the airflow flowing through the rear propeller 720 (see the arrow direction around the rear propeller 720 in Figure 5 is opposite to the direction of the tip vortex (see the arrow direction around the wing tip of the rear wing 300 in Figure 5 ), so as to offset the downwash caused by the tip vortex and further improve the lift-drag ratio of the rear wing 300.

[0060] In summary, in this embodiment, by means of different sweep angles, aspect ratios, planar shapes, mounting angles of the front and rear wings 300 and V-shaped design of the middle section of the rear wing, combined with the active straightening of the airflow by the rear propeller 720 after tilting, the influence of the downwash flow field of the front wing 200 on the rear wing 300 is maximally reduced, the lift-drag ratio of the rear wing 300 is greatly improved, and the efficiency is improved from 50%-60% of the efficiency of the front wing 200 to 70%-75%. Combined with the reduced drag in the flat flying state by the optimized straightening type front hanging mounting arm 620, the lift-drag ratio of the whole machine can be improved by 35%-40%.

[0061] By means of the tiltable tail thrust system, the dead weight of the whole machine is reduced by 60%, and the endurance performance is greatly improved.

[0062] By adopting the above-mentioned tandem wing layout, the tilt-rotor unmanned aerial vehicle can carry more than 100-130% of the load and has more than 60-80% of the endurance compared with the conventional layout compound wing vertical take-off and landing unmanned aerial vehicle based on the same wing span size; compared with the tandem wing vertical take-off and landing unmanned aerial vehicle technology, the unmanned aerial vehicle of the embodiment can carry more than 50-80% of the load and has more than 50-65% of the endurance; compared with the existing tandem wing layout vertical take-off and landing unmanned aerial vehicle technology, the unmanned aerial vehicle of the embodiment can carry more than 50% of the load and has more than 30% of the endurance.

[0063] Finally, it should be pointed out that: the above embodiments are only used to illustrate the technical solutions of the utility model, and not to limit them; although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the utility model, and they should be covered in the scope of the claims and the specification of the utility model.

Claims

1. A tiltable powered vertical take-off and landing drone with a tandem wing configuration, characterized in that, The utility model relates to a kind of unmanned aerial vehicle of vertical take-off and landing of tilting power with wing layout, including: Fuselage; A pair of front wings, which are respectively connected to the two sides of the head of the fuselage; A pair of rear wings, which are respectively provided on the two sides above the rear of the fuselage; Tail connecting wing, which is provided on the upper side of the rear of the fuselage and connected to the rear wings on both sides respectively; Side end connecting wing, the wing tip of each rear wing is connected to the front wing through the side end connecting wing; Wherein, the lower side of each front wing is equipped with a front propeller, and the lower side of each rear wing is provided with a downward-hung mounting arm that can be adjusted in the forward and backward directions, and the end of the downward-hung mounting arm is equipped with a rear propeller.

2. The unmanned aerial vehicle of vertical take-off and landing of tilting power with wing layout according to claim 1, wherein: The front wing is a backward-swept wing, and the rear wing is a straight wing near the tail connecting wing and a forward-swept wing near the side end connecting wing.

3. The unmanned aerial vehicle of vertical take-off and landing of tilting power with wing layout according to claim 2, wherein: The sweep angle of the leading edge of the backward-swept wing is 23.5°±2°, and the sweep angle of the leading edge of the forward-swept wing is 13°±2°.

4. The unmanned aerial vehicle of vertical take-off and landing of tilting power with wing layout according to claim 1, wherein: The installation angle of the pair of front wings is greater than that of the rear wings.

5. The unmanned aerial vehicle of vertical take-off and landing of tilting power with wing layout according to claim 1, wherein: The tail connecting wing includes two V-shaped connecting wing plates, one end of each of the two connecting wing plates is fixed on the fuselage, and the other end of each of the two connecting wing plates is connected to the rear wing on the corresponding side.

6. The unmanned aerial vehicle of vertical take-off and landing of tilting power with wing layout according to claim 5, wherein: The rear side of each of the two connecting wing plates is provided with a rudder surface.

7. The unmanned aerial vehicle of vertical take-off and landing of tilting power with wing layout according to claim 1, wherein: The front side of each front wing is provided with a front-hung mounting arm, and the front propeller is installed on the lower side of the front-hung mounting arm.

8. The unmanned aerial vehicle of vertical take-off and landing of tilting power with wing layout according to claim 1, wherein: The maximum angle of forward tilting of each downward-hung mounting arm is α, and the included angle β between the downward-hung mounting arm and the axis of the rear propeller is 180°-α.

9. The unmanned aerial vehicle of vertical take-off and landing of tilting power with wing layout according to claim 7, wherein: The maximum angle of forward tilting of each downward-hung mounting arm is α, and the maximum angle of backward tilting of each downward-hung mounting arm is γ.

10. The unmanned aerial vehicle of vertical take-off and landing of tilting power with wing layout according to claim 1, wherein: The lower side of the front part of the fuselage is provided with a main landing gear, and the lower side of the tail part of the fuselage is provided with a tail fin.

Images