CN212637899U - Fixed wing VTOL unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses a fixed wing VTOL unmanned aerial vehicle, including fuselage main part, outer wing, fin, drive division, the outer wing is provided with two, and the symmetry sets up in fuselage main part both sides, and the fin is V type symmetric connection in the afterbody of fuselage main part, and the drive division is used for providing flight power, is connected with fuselage main part and/or outer wing. The utility model discloses in, unmanned aerial vehicle can take off and land, hover, fly under the drive of drive division, through setting up V type fin at fuselage main part tail end, reduce unmanned aerial vehicle flight control's the degree of difficulty and increase the every single move balancing ability to improve unmanned aerial vehicle's every single move yaw stability and the nature controlled, and through the weathercock effect of fin, reduced unmanned aerial vehicle's windward area, improved unmanned aerial vehicle's wind resistance.

Description

Fixed wing VTOL unmanned aerial vehicle

Technical Field

The utility model belongs to the technical field of the flight equipment technique and specifically relates to a fixed wing VTOL unmanned aerial vehicle is related to.

Background

The body of the traditional fixed-wing unmanned aerial vehicle hovers in a vertical state, the wind resistance of the body is poor, the length of the body of the unmanned aerial vehicle is limited to avoid side turning, and the aerodynamic layout of the unmanned aerial vehicle is limited; or although vertical take-off and landing are adopted, the flying wing layout of the airframe, wings and other pneumatic components of the fixed-wing unmanned aerial vehicle is unreasonable, so that the unmanned aerial vehicle has low pneumatic efficiency and poor stability and operability during flying.

SUMMERY OF THE UTILITY MODEL

The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides a fixed wing VTOL unmanned aerial vehicle can improve unmanned aerial vehicle's flight stability.

An embodiment of the utility model provides a fixed wing VTOL unmanned aerial vehicle, include:

a main body of the body;

two outer wings are arranged and symmetrically arranged on two sides of the fuselage main body;

two empennages are arranged and symmetrically connected to the tail part of the machine body main body in a V shape;

and the driving part is used for providing flight power and is connected with the fuselage main body and/or the outer wing.

The embodiment of the utility model provides an in stationary vane VTOL unmanned aerial vehicle have following beneficial effect at least:

the utility model discloses in, unmanned aerial vehicle can take off and land, hover, fly under the drive of drive division, through setting up V type fin at fuselage main part tail end, reduce unmanned aerial vehicle flight control's the degree of difficulty and increase the every single move balancing ability to improve unmanned aerial vehicle's every single move yaw stability and the nature controlled, and through the weathercock effect of fin, reduced unmanned aerial vehicle's windward area, improved unmanned aerial vehicle's wind resistance.

According to the utility model discloses a fixed wing VTOL unmanned aerial vehicle of other embodiments, the outer wing with the fuselage main part fuses.

According to the utility model discloses a fixed wing VTOL unmanned aerial vehicle of other embodiments, the outer wing reaches the upside contour line of fuselage main part is the S type.

According to the utility model discloses a fixed wing VTOL unmanned aerial vehicle of other embodiments, the drive division includes a plurality of rotors, the rotor can rotate.

According to the utility model discloses a fixed wing VTOL unmanned aerial vehicle of other embodiments, the rotor install in the outer wing leading edge reaches the tail end of fuselage main part.

According to the utility model discloses a fixed wing VTOL unmanned aerial vehicle of other embodiments, each the outer wing all is connected with the rotor, the rotor for fuselage main part symmetry.

According to the utility model discloses a fixed wing VTOL unmanned aerial vehicle of other embodiments, the rotor can be relative the fuselage main part and/or the outer wing verts, in order to change the rotation plane of rotor.

According to the utility model discloses a fixed wing VTOL unmanned aerial vehicle of other embodiments, the rotor can be folded.

According to the utility model discloses a fixed wing VTOL unmanned aerial vehicle of other embodiments, the afterbody of fuselage main part stretches out the tail section, the fin with the rotor install in the tail section.

According to the utility model discloses a fixed wing VTOL unmanned aerial vehicle of other embodiments still includes energy system, energy system holding in the outer wing and/or in the fuselage main part.

Drawings

Fig. 1 is a schematic structural view of a flight state of the fixed-wing vertical take-off and landing unmanned aerial vehicle of the present invention;

fig. 2 is a schematic structural view of the fixed-wing vertical take-off and landing unmanned aerial vehicle in another flight state;

fig. 3 is a schematic structural view of the fixed-wing vertical take-off and landing unmanned aerial vehicle in other flight states;

fig. 4 is a schematic structural view of the fixed-wing vertical take-off and landing unmanned aerial vehicle in other flight states;

fig. 5 is the structure schematic diagram of the utility model discloses other flight status of fixed wing VTOL unmanned aerial vehicle.

Description of reference numerals:

a fuselage body 100, a tail section 110;

outer wing 200, mount 210;

a tail 300;

drive portion 400, rotor 410.

Detailed Description

The conception and the resulting technical effects of the present invention will be described clearly and completely with reference to the following embodiments, so that the objects, features and effects of the present invention can be fully understood. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and other embodiments obtained by those skilled in the art without inventive labor based on the embodiments of the present invention all belong to the protection scope of the present invention.

In the description of the embodiments of the present invention, if an orientation description is referred to, for example, the directions or positional relationships indicated by "upper", "lower", "front", "rear", "left", "right", etc. are based on the directions or positional relationships shown in the drawings, only for convenience of description and simplification of description, but not for indicating or implying that the indicated device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.

In the description of the embodiments of the present invention, if a feature is referred to as being "disposed", "fixed", "connected", or "mounted" on another feature, it can be directly disposed, fixed, or connected to the other feature or indirectly disposed, fixed, connected, or mounted on the other feature. In the description of the embodiments of the present invention, if "a plurality" is referred to, it means one or more, if "a plurality" is referred to, it means two or more, if "greater than", "less than" or "more than" is referred to, it is understood that the number is not included, and if "more than", "less than" or "within" is referred to, it is understood that the number is included. If reference is made to "first" or "second", this should be understood to distinguish between features and not to indicate or imply relative importance or to implicitly indicate the number of indicated features or to implicitly indicate the precedence of the indicated features.

Fig. 1 shows a schematic structural diagram of a flight state of a fixed-wing vertical take-off and landing drone of the present invention, referring to fig. 1, the fixed-wing vertical take-off and landing drone of the present invention includes a main body 100, an outer wing 200, an empennage 300 and a driving portion, the outer wing 200 is fixedly connected with the main body 100 as a fixed wing, the outer wing 200 is provided with two and symmetrical to the main body 100, the driving portion 400 is used for providing flight power for the drone, so as to ensure that the drone can take off, land, hover and fly, and the driving portion 400 can be installed on the main body 100 and/or the outer wing 200; in this embodiment, two empennages 300 are arranged at the tail end of the main body 100, and the two empennages 300 are symmetrically connected to the tail end of the main body 100 in a V shape, so that the V-shaped empennages 300 can reduce the difficulty of flight control of the unmanned aerial vehicle and increase the capability of pitching balancing, the defect of insufficient pitching/transverse stability of the unmanned aerial vehicle flying wing layout is overcome, the influence of the tail end of the main body 100 and the empennages 300 on the cruise resistance is small, and the stability and the controllability of pitching and yawing of the unmanned aerial vehicle in the flat flight process can be effectively ensured; in addition, V type fin 300 in this embodiment has the weather vane characteristic, is the state of hovering at unmanned aerial vehicle, when being in the gust environment, fin 300 receives behind the crosswind moment of a compliance wind direction of natural production with the directional windward direction of aircraft nose, reduces the windward area to reduce unmanned aerial vehicle's energy consumption, improve unmanned aerial vehicle's wind-resistance.

In this embodiment, unmanned aerial vehicle can take off and land, hover, fly under the drive of drive division 400, through setting up V type fin 300 at fuselage main part 100 tail ends, reduces unmanned aerial vehicle flight control's the degree of difficulty and increases the pitching balancing ability to improve unmanned aerial vehicle's every single move yaw stability and nature controlled, and through the weathercock effect of fin 300, reduced unmanned aerial vehicle's windward area, improved unmanned aerial vehicle's wind resistance.

In addition, in this embodiment, outer wing 200 fuses with fuselage main part 100 and forms central lift body to fuselage main part 100 and outer wing 200 all can provide lift for unmanned aerial vehicle, the internal loading space increase of central lift body that the wing body fuses simultaneously, unmanned aerial vehicle's energy system load space has been increased, the battery capacity increase in the energy system, can improve unmanned aerial vehicle's cruise time, the energy system can hold in outer wing 200 and/or fuselage main part 100, the energy system includes loading device, the battery, fuel, payload etc. After the central lifting body that the wing body fuses is made up with outer wing 200, can show the exhibition that increases unmanned aerial vehicle long, and then promote unmanned aerial vehicle's infiltration area aspect ratio and aerodynamic efficiency, reduced unmanned aerial vehicle's induced resistance to through the reduction of resistance and the stack combination of the improvement of lift, improve unmanned aerial vehicle's the efficiency of cruising.

In this embodiment, the outer wing 200 and the fuselage main body 100 are fused, and the shapes of the upper side contour lines of the outer wing 200 and the fuselage main body 100 are the same, so that the outer wing 200 and the fuselage main body 100 are fused to form a flying wing. Compared with the existing vertical take-off and landing unmanned aerial vehicle, the hybrid wing body and the S-shaped central lifting body are arranged, so that the endurance time is improved by 1-2 times. Outer wing 200 can set up to the recurve wing section with the upside contour line of fuselage main part 100, and the wing of recurve wing section can reduce unmanned aerial vehicle's pneumatic low head moment to adjust unmanned aerial vehicle's focus, make unmanned aerial vehicle's full aircraft focus and wing focus coincidence, unmanned aerial vehicle's lift force action point and focus coincidence guarantee the stability of unmanned aerial vehicle flight.

In addition, it should be noted that, unmanned aerial vehicle in this embodiment adopts and fuses wing body and the 300 compound mode of V type fin, the unmanned aerial vehicle that mixes wing body and fuses outer wing overall arrangement can improve more than 50% than conventional VTOL unmanned aerial vehicle lift-drag ratio under the same speed, when unmanned aerial vehicle meets the crosswind, because the extra aerodynamic force that fin 300 weathercock effect produced changes flight resistance into, because the pneumatic overall arrangement lift-drag ratio of unmanned aerial vehicle in this embodiment is great, unmanned aerial vehicle's resistance is compared in other aerodynamic force a lot less, thereby unmanned aerial vehicle's wind-resistance has been improved.

The driving part 400 can select the engine to combine with the propeller to form a power device to generate forward thrust, and the central lifting body generates lift force to realize the flight of the unmanned aerial vehicle. In this embodiment, drive portion 400 includes a plurality of rotors 410, and rotor 410 can rotate, and rotor 410 rotates and can produce lift and thrust, realizes unmanned aerial vehicle's take off and land and flight.

All be connected with rotor 410 on each outer wing 200 in this embodiment, and rotor 410 is symmetrical for fuselage main part 100 to guarantee unmanned aerial vehicle flight's balance and stability. Rotor 410 installs in the leading edge of outer wing 200 and the tail end of fuselage main part 100, makes rotor 410 be triangular distribution, and stability when can guarantee unmanned aerial vehicle flight state through the lift that the rotational speed of adjusting each rotor 410 changes triangular distribution.

In addition, in this embodiment, the rear portion of the main body 100 extends out of the tail section 110 to install the aerodynamic layout of the V-shaped empennage 300, the small tail section 110 and the V-shaped empennage 300 have less influence on the cruise resistance, and the V-shaped empennage 300 is combined with the flying layout of the hybrid wing body to improve the aerodynamic efficiency and flight stability of the unmanned aerial vehicle. Rotor 410 and the tail section 110 of V type fin 300 sharing fuselage main part 100 of fuselage main part 100 tail end make unmanned aerial vehicle's mixed wing body and rotor 410 VTOL combine, satisfy unmanned aerial vehicle's lift and flight stability demand simultaneously.

In fig. 1, a state diagram of the vertical take-off and landing and hovering phases of the drone is shown, the rotation plane of the rotor 410 is horizontal, downward thrust is provided, the stability of the left-right and front-back postures of the drone in the hovering state can be ensured by changing the rotation speed of different rotors 410, and yaw control of the drone is realized by vector differential of two rotors 410 connected to the front edge of the outer wing 200.

In addition, rotor 410 in this embodiment can incline relatively fuselage main part 100 and/or outer wing 200 to change rotor 410's rotation plane, make rotor 410 produce the thrust of different directions, satisfy unmanned aerial vehicle at the flight demand of different stages.

Fig. 2 shows unmanned aerial vehicle is at VTOL or hover state to the structural sketch of the state transition state that flies of level, and this in-process, front and back rotor 410 verts certain angle simultaneously, and the rotation plane of rotor 410 is the slope form, can provide vertical lift and front and back thrust simultaneously, makes unmanned aerial vehicle accelerate forward when keeping sufficient lift. Rotor 410's inclination can be selected according to unmanned aerial vehicle's actual flight demand, and in this embodiment, rotor 410 verts 45.

Fig. 3 shows unmanned aerial vehicle at the structural schematic diagram of the flat state of flying, after unmanned aerial vehicle accelerates to predetermineeing speed, rotor 410's inclination converts the zero degree, and rotor 410's rotation plane is perpendicular, and unmanned aerial vehicle is flat to fly, and rotor 410 only provides thrust and does not provide lift.

Because rotor 410 in this embodiment can infinitely vert, therefore unmanned aerial vehicle can share one set of driving system at the required lift of VTOL, hover stage and the required thrust of cruise stage, adopts two kinds of independent actuating systems in the unmanned aerial vehicle of combined type VTOL overall arrangement to compare, has reduced driving system's weight and unmanned aerial vehicle's load, and rotor 410 verts does not receive the restriction of wing span, combines with the outer wing 200 of hybrid wing body more easily.

In addition, in this embodiment, the rotor 410 may be folded to allow the rotor 410 to be close to the tail end of the outer wing 200 or the fuselage body 100, thereby achieving the effect of accommodating the rotor 410. Because unmanned aerial vehicle adopts the wing body to fuse the overall arrangement, its lift-drag ratio of itself is higher, fly to the speed of cruising at unmanned aerial vehicle tie, the demand to thrust reduces by a wide margin, the power of unmanned aerial vehicle tail section 110 or outer wing 200 leading edge can be selected to be removed this moment, the rotor 410 at corresponding position is folding, thereby reduce rotor 410 and fuselage main part 100 by a wide margin, the aerodynamic interference between outer wing 200, flight resistance and driving system's consumption, improve unmanned aerial vehicle's the efficiency of cruising. Fig. 4 is a flight state diagram for removing the power of the rotor 410 at the tail end of the fuselage body 100, and fig. 5 is a flight state diagram for removing the power of the rotor 410 at the leading edge of the outer wing 200.

It should be noted that the tilting and folding of rotor 410 can be performed by a conventional rotating member. Taking the rotor 410 on the outer wing 200 as an example, the front edge of the outer wing 200 extends out of the mounting rack 210, the rotor 410 is rotatably mounted on the mounting rack 210, and the rotor 410 can generate lift force or thrust when rotating; a rotating shaft (not shown) is further arranged between the rotor 410 and the mounting frame 210, the rotating shaft is rotatably connected with the mounting frame 210, the rotor 410 is rotatably connected with the rotating shaft, a rotating plane of the rotating shaft relative to the mounting frame 210 is not parallel to a rotating plane of the rotor 410 relative to the rotating shaft, and the rotating shaft is driven by a motor to rotate, so that when the rotating shaft rotates relative to the mounting frame 210, the rotating plane of the rotor 410 changes; the installation rack 210 can be hinged to the outer wing 200, the installation rack 210 can rotate relative to the outer wing 200, the rotor 410 and the rotating shaft are close to the outer wing 200 after the installation rack 210 rotates, the rotor 410 is folded, or the installation rack 210 is of a connecting rod structure, the connecting rod is hinged to the outer wing 200, the rotor 410 and the rotating shaft can be close to the outer wing 200 through the rotation of the connecting rod, and the rotor 410 is folded. While the above provides the case that the rotor 410 is folded at the bottom of the outer wing 200 by the rotation of the mounting bracket 210, it is of course possible to mount a driving part on the mounting bracket 210 so that the rotor 410 is folded at the side of the mounting bracket 210, and the driving folding manner is not listed here.

In addition, still can install the cloud platform on the unmanned aerial vehicle, carry on the camera element on the cloud platform, the record can be shot to unmanned aerial vehicle's the condition of cruising to the camera element, still can set up control element, GPS inductive element etc. on the unmanned aerial vehicle, is convenient for acquire unmanned aerial vehicle's flight information and positional information.

The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art. Furthermore, the embodiments of the present invention and features of the embodiments may be combined with each other without conflict.

Claims (10)

1. Fixed wing VTOL unmanned aerial vehicle, its characterized in that includes:

a main body of the body;

two outer wings are arranged and symmetrically arranged on two sides of the fuselage main body;

two empennages are arranged and symmetrically connected to the tail part of the machine body main body in a V shape;

and the driving part is used for providing flight power and is connected with the fuselage main body and/or the outer wing.

2. The fixed-wing VTOL unmanned aerial vehicle of claim 1, wherein the outer wing is fused with the fuselage body.

3. The fixed-wing VTOL UAV of claim 2, wherein the upper contour lines of the outer wing and the fuselage body are S-shaped.

4. The fixed-wing VTOL unmanned aerial vehicle of claim 1, wherein the drive section comprises a plurality of rotors, the rotors being rotatable.

5. The fixed-wing VTOL UAV of claim 4, wherein the rotor is mounted at the outer wing leading edge and the aft end of the fuselage body.

6. The fixed-wing VTOL UAV of claim 5, wherein each of the outer wings has the rotor connected thereto, the rotor being symmetric with respect to the fuselage body.

7. A fixed-wing VTOL UAV according to any of claims 4-6, wherein the rotor can tilt with respect to the fuselage body and/or the outer wing to change its plane of rotation.

8. The fixed-wing VTOL UAV of any of claims 4-6, wherein the rotor is foldable.

9. The fixed-wing VTOL UAV of any one of claims 5-6, wherein a tail section extends from the tail of the fuselage body, the tail wing and the rotor wing being mounted to the tail section.

10. The fixed-wing VTOL unmanned aerial vehicle of claim 1, further comprising an energy system housed within the outer wing and/or the fuselage body.

Images