Vertical take-off and landing composite wing unmanned aerial vehicle adopting linked wing layout

Abstract

The vertical take-off and landing composite wing unmanned aerial vehicle comprises a vehicle body, front wings are installed on the two sides of the front portion of the vehicle body respectively, the front wings are sweepback wings, a vertical tail wing is installed on the rear top of the vehicle body, and rear wings are installed on the top of the vertical tail wing. Wingtips at two ends of the rear wing are respectively connected with wingtips of the two front wings through two end plates, vertical take-off and landing propellers are mounted at the bottoms of the front wings and the rear wings, and a level flight propeller is mounted at the tail of the fuselage. According to the technical scheme, resistance can be reduced, stability is improved, and then the loading capacity and cruising ability of the unmanned aerial vehicle are improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, concretely relates to a vertical take-off and landing compound wing unmanned plane with wing layout. BACKGROUND

[0002] Current small and medium-sized vertical take-off and landing compound wing unmanned plane mostly adopts conventional aerodynamic layout, and the load capacity and endurance time are short boards, and even if a few unmanned planes with slightly longer endurance time, the load capacity is also small.

[0003] The existing wing layout vertical take-off and landing unmanned plane has the problems of low efficiency and large flow field interference to the main wing in the arrangement form of vertical take-off and landing power propeller. SUMMARY

[0004] In view of the defects in the prior art, the utility model provides a vertical take-off and landing compound wing unmanned plane with wing layout, which can reduce resistance, improve stability, and further improve the load capacity and endurance of the unmanned plane.

[0005] A vertical take-off and landing compound wing unmanned plane with wing layout, comprising a fuselage, front wings are installed on both sides of the front part of the fuselage, the front wings are backward swept wings, a vertical tail is installed on the top of the rear part of the fuselage, a rear wing is installed on the top of the vertical tail, the wing tips of the rear wing are connected to the wing tips of the two front wings through two end plates respectively, vertical take-off and landing propellers are installed at the bottom of the front wings and the rear wing, and a cruising propeller is installed at the tail of the fuselage.

[0006] Preferably, the rear wing comprises a middle section and two outer sections, the middle section is connected to the vertical tail, the two outer sections are connected to the two ends of the middle section respectively, the middle section is a straight wing, and the outer sections are forward swept wings.

[0007] Preferably, the front edge sweep angle of the outer section is 13°.

[0008] Preferably, the front edge sweep angle of the front wing is 23.5°.

[0009] Preferably, the bottom of the front wing and the rear wing is detachably installed with a hanger, and the vertical take-off and landing propeller is installed at the bottom of the hanger.

[0010] Preferably, a landing gear is installed at the front bottom of the fuselage.

[0011] Preferably, the end plate is detachably connected with the front wing and the rear wing.

[0012] Preferably, a tail fin is mounted on the rear bottom of the fuselage.

[0013] The beneficial effects of the utility model are shown in the following: in the technical scheme, the end plate is connected with the front wing and the rear wing, which reduces the induced drag and strengthens the front and rear wing structure and improves the stability. In the technical scheme, the rear wing is affected by the downwash flow field of the front wing is reduced by the different sweep angles, shapes and installation angles of the front wing and the rear wing, so that the lift-drag ratio of the rear wing can reach 65%-70% of the front wing, and the lift-drag ratio of the unmanned aerial vehicle is improved. In the technical scheme, the efficiency of the underhung vertical take-off and landing propeller is improved, and the influence on the main wing flow field is small. In summary, the technical scheme can reduce the drag, improve the stability, and further improve the load capacity and endurance. BRIEF DESCRIPTION OF DRAWINGS

[0014] In order to more clearly illustrate the specific embodiments of the utility model or the technical scheme in the prior art, the drawings needed 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.

[0015] Figure 1 It is a whole structure schematic view of the utility model.

[0016] In the drawings, 1 is a fuselage, 2 is a front wing, 3 is a rear wing, 4 is a vertical tail, 5 is an end plate, 6 is a vertical take-off and landing propeller, 7 is a horizontal flight propeller, 8 is a landing gear, 9 is a tail fin, and 10 is a hanging rack. DETAILED DESCRIPTION

[0017] The embodiments of the technical scheme of the utility model will be described in detail below with reference to the drawings. The following embodiments are only used to more clearly illustrate the technical scheme of the utility model, so only as an example, and cannot limit the protection scope of the utility model.

[0018] It should be noted that, unless otherwise specified, the technical terms or scientific terms used in the present application should be the usual meaning understood by the technical personnel in the field of the utility model.

[0019] EMBODIMENT

[0020] As Figure 1As shown, the embodiment provides a vertical take-off and landing compound wing unmanned aerial vehicle with a tandem wing layout, comprising a fuselage 1, front wings 2 mounted on both sides of the front part of the fuselage 1, the front wings 2 being backward swept wings, a vertical tail 4 mounted on the top rear part of the fuselage 1, a rear wing 3 mounted on the top of the vertical tail 4, both ends of the rear wing 3 connected to the wing tips of the two front wings 2 through two end plates 5, vertical take-off and landing propellers 6 mounted on the bottom of the front wings 2 and the rear wing 3, and a cruising propeller 7 mounted on the tail of the fuselage 1.

[0021] The rear wing 3 in the embodiment comprises a middle section and two outer sections, the middle section being connected to the vertical tail 4, and the two outer sections being connected to both ends of the middle section, the middle section being a straight wing, and the outer sections being forward swept wings.

[0022] The front edge sweep angle of the outer section in the embodiment is 13°. The front edge backward sweep angle of the front wing 2 in the embodiment is 23.5°. The front wing 2 in the embodiment is provided with a slightly larger installation angle than the rear wing 3.

[0023] In the embodiment, the front wings 2 are mounted on both sides of the front part of the fuselage 1, the vertical tail 4 is mounted on the top rear part of the fuselage 1, the rear wing 3 is mounted on the top of the vertical tail 4, both ends of the rear wing 3 are connected to the wing tips of the two front wings 2 through the end plates 5, the vertical take-off and landing propellers 6 are mounted on the bottom of the front wings 2 and the rear wing 3, and the cruising propeller 7 is mounted on the tail of the fuselage 1. The end plates 5 are connected to the front wings 2 and the rear wing 3, which not only reduces the induced drag, but also strengthens the structure of the front and rear wings. The vertical take-off and landing propellers 6 are used to blow air downward to provide upward thrust to meet the vertical take-off and landing of the unmanned aerial vehicle. The cruising propeller 7 provides thrust for the unmanned aerial vehicle to fly forward after the unmanned aerial vehicle is converted from vertical take-off and landing mode to cruising mode. Through the different sweep angles, shapes and installation angles of the front wings 2 and the rear wing 3, the influence of the downwash flow field of the front wings 2 on the rear wing 3 is reduced, and the lift-drag ratio of the rear wing 3 can reach 65%-70% of that of the front wings 2. The efficiency of the downward hanging vertical take-off and landing propeller 6 is improved, and the influence on the main wing flow field is small.

[0024] The bottom of the front wing 2 and the rear wing 3 in the embodiment is detachably mounted with a hanger 10, and the vertical take-off and landing propeller 6 is mounted at the bottom of the hanger 10.

[0025] The hanger 10 in the embodiment has a certain forward inclination angle, and the vertical take-off and landing propeller 6 is mounted at the bottom of the hanger 10, away from the lower surface of the wing, to prevent the turbulence caused by the propeller from interfering with the wing flow field during forward flight. The hanger 10 is designed as a plug-in type fast plug and uses a buckle to lock, which is convenient for transportation and carrying. At the same time, when the hanger 10 is removed, the unmanned aerial vehicle can be quickly converted from vertical take-off and landing mode to taxi take-off and landing mode, which can further improve the load capacity and endurance time.

[0026] The front bottom of the fuselage 1 in the embodiment is mounted with a landing gear 8.

[0027] The end plate 5 is detachably connected with the front wing 2 and the rear wing 3 in the embodiment.

[0028] The tail fin 9 is mounted at the rear bottom of the fuselage 1 in the embodiment.

[0029] The landing gear 8 and the tail fin 9 are arranged in the embodiment, the tail fin 9 can strengthen the heading stability of the unmanned aerial vehicle on one hand, and can support the unmanned aerial vehicle together with the landing gear 8 as a support point for ground parking on the other hand.

[0030] The vertical tail 4 and the tail fin 9 are arranged with a certain sweepback angle to reduce the resistance in the embodiment.

[0031] Compared with the conventional layout composite wing vertical take-off and landing unmanned aerial vehicle, the unmanned aerial vehicle of the technology has more 60-100% load, and more 30-50% endurance on the basis of 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 technology has more 30-60% load, and more 25-40% endurance; compared with the existing tandem wing layout vertical take-off and landing unmanned aerial vehicle technology, the unmanned aerial vehicle of the technology has more 30-40% load, and more 30% endurance. When the pylon 10 and the vertical take-off and landing propeller 6 are removed, the unmanned aerial vehicle of the technology can be converted into a tandem wing layout fixed wing unmanned aerial vehicle within 1-2 minutes, and can take off and land in the form of taxiing, and the load and endurance are further increased by about 50% compared with the vertical take-off mode.

[0032] Finally, it should be noted 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 vertical take-off and landing compound wing unmanned aerial vehicle (UAV) employing a tandem wing configuration, characterized in that, The application relates to a vertical take-off and landing aircraft, which comprises a fuselage (1), front wings (2) mounted on both sides of the front of the fuselage (1), the front wings (2) being backward-swept wings, a vertical tail (4) mounted on the top of the rear of the fuselage (1), a rear wing (3) mounted on the top of the vertical tail (4), the two wing tips of the rear wing (3) being connected with the wing tips of the two front wings (2) through two end plates (5), vertical take-off and landing propellers (6) mounted on the bottom of the front wings (2) and the rear wing (3), and a cruising propeller (7) mounted on the tail of the fuselage (1).

2. The VSTOL compound-wing UAV with a tandem wing configuration according to claim 1, characterized in that, The rear wing (3) comprises a middle section and two outer sections, the middle section being connected with the vertical tail (4), the two outer sections being connected with the two ends of the middle section, the middle section being a straight wing, and the outer sections being forward-swept wings.

3. The VSTOL compound-wing UAV with a tandem wing configuration according to claim 2, wherein, The front edge of the outer section has a sweep angle of 13 degrees.

4. The VSTOL compound-wing UAV with a tandem wing configuration according to claim 2, wherein, The front edge of the front wing (2) has a backward sweep angle of 23.5 degrees.

5. The VSTOL compound-wing UAV with a tandem wing configuration according to claim 1, wherein, The front wings (2) and the rear wing (3) are detachably provided with hangers (10) on the bottom, and the vertical take-off and landing propellers (6) are mounted on the bottom of the hangers (10).

6. The VSTOL compound-wing UAV with a tandem wing configuration according to claim 1, wherein, The fuselage (1) is provided with landing gears (8) on the bottom.

7. The VSTOL compound-wing UAV with a tandem wing configuration according to claim 1, wherein, The end plates (5) are detachably connected with the front wings (2) and the rear wing (3).

8. The VSTOL compound-wing UAV with a tandem wing configuration according to claim 1, wherein, The fuselage (1) is provided with a tail fin (9) on the bottom.

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