CN209833994U

CN209833994U - Novel VTOL unmanned aerial vehicle of hookup wing configuration

Info

Publication number: CN209833994U
Application number: CN201920443194.0U
Authority: CN
Inventors: 夏季风
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-04-02
Filing date: 2019-04-02
Publication date: 2019-12-24
Anticipated expiration: 2029-04-02

Abstract

The utility model provides a novel vertical take-off and landing unmanned aerial vehicle with a connecting wing structure, which comprises a machine head, a machine body, a front wing, a rear wing and a propeller power mechanism; the machine head is connected to the front end of the machine body; the two front wings are horizontally and symmetrically connected to the front end of the fuselage; the rear wings are connected to the rear end of the machine body in a horizontally symmetrical mode, the wing tip portions of the rear wings located on the same side of the machine body are connected with the wing tip portions of the front wings, the two rear wings and the two front wings are combined to form a diamond shape, and the lower ends of the single rear wing and the single front wing are vertically provided with the propeller power mechanism. The utility model discloses can not compromise the problem of rigidity demand such as easily take off and land, the loading capacity is big, control is simple, the reliability height simultaneously with unmanned aerial vehicles such as solution fixed wing, many rotors, helicopter, overcome the current conventional overall arrangement VTOL unmanned aerial vehicle loading capacity in market not high, the not long inherent defect of time of endurance, reach the application purpose that satisfies different environment, accord with different conditions, adapt to different tasks with a platform.

Description

Novel VTOL unmanned aerial vehicle of hookup wing configuration

Technical Field

The utility model relates to an unmanned air vehicle technique field, concretely relates to novel VTOL unmanned aerial vehicle of hookup wing configuration.

Background

Unmanned aerial vehicle is called "aerial robot", from 1917 first unmanned aerial vehicle born to present nearly 100 years time, unmanned aerial vehicle technology continues to advance, and techniques such as microelectronics, navigation, control, communication have especially promoted unmanned aerial vehicle system's development, have promoted unmanned aerial vehicle system in military and civilian application. In recent years, the supervision of civil unmanned aerial vehicles is gradually relaxed, and the national policy specifications of the civil unmanned aerial vehicles and the deep transformation of low-altitude airspace regions promote the explosive growth of the industry of the civil unmanned aerial vehicles in China.

As a first country in the world of civil unmanned aerial vehicles, the civil unmanned aerial vehicles have extremely wide application, and the market mainly focuses on the fields of agriculture and forestry plant protection, film and television aerial photography, aviation surveying and mapping, electric power oil and gas pipeline inspection, emergency disaster prevention and control and the like at present.

At present, the mainstream unmanned aerial vehicle in the civil market of China mainly comprises fixed wings, multiple rotors, helicopters, vertical take-off and landing fixed wings and the like, wherein the fixed wings have obvious load endurance advantages, but have high requirements on take-off and landing sites and environments; the multi-rotor wing has a simple structure and is easy to control, but the disadvantages of load endurance and dependence on meteorological environment are obvious; the helicopter takes the take-off and landing requirements and certain load-carrying endurance capacity into consideration, but has a complex structure, difficult operation and poor reliability and maintainability; the existing vertical take-off and landing fixed wing only combines a fixed wing and a multi-rotor two-set system together simply, so that the take-off and landing performance is improved, but the rotor wing which sacrifices the structural weight and has more load carrying capacity and endurance time is not obviously enhanced.

SUMMERY OF THE UTILITY MODEL

The utility model provides a not enough to prior art, the utility model provides a novel VTOL unmanned aerial vehicle of hookup wing configuration to solve unmanned aerial vehicles such as stationary vane, many rotors, helicopter and can not compromise simultaneously easily take off and land, the loading capacity is big, control is simple, the problem of the high rigidity demand of reliability, overcome the current conventional overall arrangement VTOL unmanned aerial vehicle loading capacity in market not high, the not long inherent defect of time of endurance, reach and satisfy different environment, accord with different conditions, adapt to the application purpose of different tasks with a platform.

The utility model provides a novel vertical take-off and landing unmanned aerial vehicle with a connecting wing structure, which comprises a machine head, a machine body, a front wing, a rear wing and a propeller power mechanism;

the machine head is connected to the front end of the machine body;

the two front wings are arranged, and the root parts of the two front wings are horizontally and symmetrically connected to the front end of the fuselage;

the rear wings are two, the root parts of the two rear wings are horizontally and symmetrically connected to the rear end of the machine body, the wing tip parts of the rear wings positioned on the same side of the machine body are connected with the wing tip parts of the front wings, the two rear wings and the two front wings are combined to form a diamond shape, and the lower ends of the single rear wing and the single front wing are respectively and vertically provided with the propeller power mechanism.

In the above technical solution, the utility model discloses can also do following improvement.

The preferable technical scheme is characterized in that: the propeller power mechanism comprises a mounting seat, a shell, a brushless motor and a propeller; the one end and the back wing of mount pad or front wing fixed connection, the other end of mount pad are the open end, and the open end department of mount pad is equipped with the installation face, be equipped with the wire contact on the installation face, the casing lock joint is in the open end, brushless motor is fixed to be set up in the casing, and brushless motor is towards the one end and the wire contact of open end, and the one end that brushless motor kept away from the open end is the output and stretches out from the casing, the screw with output fixed connection.

The preferable technical scheme is characterized in that: the mounting surface is equidistantly provided with a plurality of clamping grooves in a knife shape, a plurality of buckles are annularly arranged in the casing at equal intervals, and a single buckle can be inserted into the corresponding clamping groove and locked in the clamping groove.

The preferable technical scheme is characterized in that: every the inboard of draw-in groove all is equipped with the bar reed of arranging along the length direction of draw-in groove, the bar reed arrives distance between the installation face is for gradually becoming big along its one end to its other end, the one end and the mount pad fixed connection of bar reed, and the installation face is kept away from to the one end of bar reed.

The preferable technical scheme is characterized in that: the opening end is provided with a circle of annular groove, and the casing is provided with a circle of thin wall matched with the annular groove.

The preferable technical scheme is characterized in that: the rear upper end of the machine body is vertically provided with a machine tail, and the rear end of the machine body is horizontally provided with the propeller power mechanism.

The preferable technical scheme is characterized in that: the lower front end of the machine body is connected with a front wheel through a front wheel carrier, the lower rear end of the machine body is connected with a rear wheel through a rear wheel carrier, and the two rear wheels are arranged on the rear wheel carrier in a bilateral symmetry mode.

The preferable technical scheme is characterized in that: the aircraft nose is triangle-shaped, and the left and right ends symmetry of aircraft nose is equipped with the duck wing.

The preferable technical scheme is characterized in that: the wing tips of the two front wings are symmetrically connected with a straight wing or a sweepback wing.

The preferable technical scheme is characterized in that: an umbrella cabin is arranged at the upper end of the machine body, an opening is formed in the upper end of the umbrella cabin, a cabin door is hinged to the opening of the umbrella cabin, an opening is formed in the upper end of the umbrella cabin and is hinged to one end of the cabin door, a first pin hole is formed in the other end of the cabin door, a second pin hole corresponding to the first pin hole is formed in the machine body, a steering engine is arranged in the machine body, the output end of the steering engine is fixedly connected with a rocker arm, and a bolt on the rocker arm can be inserted into the second pin hole and the first pin hole or withdrawn from the first pin hole and the second pin hole under the driving of the steering engine, so that the cabin door is locked or;

a supporting plate is horizontally arranged in the umbrella cabin, the supporting plate is connected with the inner bottom surface of the umbrella cabin through a plurality of springs, the springs are dispersedly arranged between the supporting plate and the umbrella cabin according to the requirement of uniform stress, and a parachute in a folded state is placed at the upper end of the supporting plate;

still include the umbrella rope, the umbrella rope is many and sets up for the parachute equipartition, the one end of single umbrella rope and the lower extreme fixed connection of parachute, and its other end stretches out and fixed connection on the hanging point of fuselage in the gap of parachute bay and hatch door.

Compared with the prior art, the beneficial effects of the utility model are that: the utility model discloses a set up aircraft nose, fuselage, front wing, back wing and screw power unit, the utility model discloses a rhombus wing itself just can become the organism configuration of many rotors, only need with screw power unit arrange on the wing of four hookups of each other can, need not to increase extra structure weight. Moreover, because only one propeller power mechanism is arranged on the front wing or the rear wing, when the aircraft flies in a rotor wing mode, only a single rotor wing is arranged on the front wing or the rear wing to provide bending moment generated by lift force, alternating torque existing on the existing composite wing can not occur, and elastic deformation of the front wing or the rear wing is reduced to the minimum due to higher strength and rigidity of the configuration.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.

Fig. 1 is a schematic structural diagram of a novel vertical take-off and landing unmanned aerial vehicle with a configuration of a coupling wing according to embodiment 1 of the present invention.

Fig. 2 is another schematic structural diagram of the novel VTOL UAV of the embodiment 1 of the present invention.

Fig. 3 is a schematic structural view of a propeller power mechanism according to embodiment 1 of the present invention.

Fig. 4 is a partially enlarged schematic view of a propeller power mechanism according to embodiment 1 of the present invention.

Fig. 5 is a schematic view of the installation of the housing, the brushless motor and the propeller according to embodiment 1 of the present invention.

Fig. 6 is a schematic structural diagram of a novel VTOL UAV with a configuration of coupling wings according to embodiment 2 of the present invention.

Fig. 7 is a schematic view of a part of a novel VTOL UAV of embodiment 2 of the present invention.

Fig. 8 is a schematic structural diagram of a novel VTOL UAV with a configuration of coupling wings according to embodiment 3 of the present invention.

Fig. 9 is a partially enlarged schematic view of a novel VTOL UAV of embodiment 3 of the present invention.

Fig. 10 is a schematic structural diagram of a novel vertical take-off and landing unmanned aerial vehicle with a configuration of coupling wings according to embodiment 4 of the present invention.

Detailed Description

To further understand the contents, features and functions of the present invention, the following embodiments are illustrated and described in detail as follows:

In the figure, the respective symbols have the following meanings:

1. a machine head; 11. duck wings; 2. a body; 21. a front wheel carrier; 22. a front wheel; 23. a rear wheel carrier; 24. a rear wheel; 3. a front wing; 4. a rear wing; 5. a propeller power mechanism; 51. a mounting seat; 511. an open end; 512. a mounting surface; 513. a wire contact; 514. a card slot; 515. a reed; 516. a ring groove; 52. a housing; 521. buckling; 522. thin wall; 53. a brushless motor; 54. a propeller; 6. and (4) a tail.

Referring to fig. 1 to 5, the present embodiment provides a novel vertical take-off and landing drone with a coupled wing configuration, including a nose 1, a fuselage 2, a front wing 3, a rear wing 4, and a propeller power mechanism 5;

the machine head 1 is connected to the front end of the machine body 2;

the number of the front wings 3 is two, and the root parts of the two front wings 3 are horizontally and symmetrically fixedly connected to the front end of the fuselage 2;

the rear wings 4 are two, the root parts of the two rear wings 4 are horizontally and symmetrically fixedly connected to the rear end of the machine body 2, the wing tip parts of the rear wings 4 positioned on the same side of the machine body 2 are connected with the wing tip parts of the front wings 3, the two rear wings 4 and the two front wings 3 are combined to form a diamond shape, and the lower ends of the single rear wing 4 and the single front wing 3 are vertically provided with one propeller power mechanism 5.

In the embodiment, the nose 1, the fuselage 2, the front wing 3, the rear wing 4 and the propeller power mechanisms 5 are arranged, in the embodiment, because the wing tip part of the rear wing 4 positioned on the same side of the fuselage 2 is connected with the wing tip part of the front wing 3, and the two rear wings 4 and the two front wings 3 are combined to form a rhombus shape, the rhombus wing can be in a multi-rotor body structure, and meanwhile, the four propeller power mechanisms 5 are respectively arranged on the two front wings 3 and the two rear wings 4, when the aircraft flies in a rotor mode, only a single rotor wing is arranged on the front wings 3 or the rear wings 4 to provide bending moment generated by lift force, alternating torque existing on the existing composite wing can not occur, and the elastic deformation of the front wings 3 or the rear wings 4 is reduced to the minimum due to the higher strength and rigidity of the structure.

Referring to fig. 1 to 5, the propeller power mechanism 5 includes a mounting base 51, a housing 52, a brushless motor 53 and a propeller 54; one end of the mounting base 51 is fixedly connected with the rear wing 4 or the front wing 3, the other end of the mounting base 51 is an open end 511, a mounting surface 512 is arranged at the open end 511 of the mounting base 51, a wire contact 513 is arranged on the mounting surface 512, the housing 52 is buckled at the open end 511, the brushless motor 53 is fixedly arranged in the housing 52, one end of the brushless motor 53 facing the open end 511 is in contact with the wire contact 513, one end of the brushless motor 53 far away from the open end 511 is an output end and extends out of the housing 52, and the propeller 54 is fixedly connected with the output end.

By arranging the mounting seat 51, the machine shell 52, the brushless motor 53 and the propeller 54, the fast-assembly interface is adopted in the embodiment, the machine shell 52 is mounted at the opening end 511 of the mounting seat 51, at the moment, the opening end 511 of the mounting seat 51 is sealed, the brushless motor 53 is in contact with the wire contact 513 to electrify the brushless motor 53, and the propeller 54 is driven to rotate by the brushless motor 53 in the rotating process, so that the vertical lifting of the machine body 2 is realized, in the embodiment, the four brushless motors 53 ensure the stability of the machine body 2 in the lifting process; in addition, it should be noted that, for a better takeoff place, when the takeoff and landing environment is better, the housing 52, the brushless motor 53 and the propeller 54 can be detached, and only the mounting base 51 is kept on the airframe 2, so that the weight of the unmanned aerial vehicle can be reduced, the unmanned aerial vehicle can fly more stably, and the carrying capacity and the range of the unmanned aerial vehicle are improved; when there is not better place of taking off, when the environment of taking off and land is relatively poor promptly, need to dismantle casing 52, brushless motor 53 and screw 54 and install on mount pad 51, though unmanned aerial vehicle's weight becomes heavy, it obtains the function of taking off and land perpendicularly, can take off smoothly, has got rid of the reliance to better environment of taking off and land, and the unmanned aerial vehicle of this embodiment can adapt to the occasion of taking off and land of multiple different grade type.

Referring to fig. 3 to 5, three slots 514 are annularly arranged on the mounting surface 512 at equal intervals, the slots 514 are knife-shaped, three fasteners 521 are annularly arranged in the housing 52 at equal intervals, and a single fastener 521 can be inserted into the corresponding slot 514 and locked in the slot 514.

Through setting up draw-in groove 514 and buckle 521, the orientation of arranging of three draw-in groove 514 here is the same, and the user is through inserting buckle 521 into draw-in groove 514, and is rotating 20 left and right sides towards the less one end of draw-in groove 514 area, can lock buckle 521 in draw-in groove 514 to avoided casing 52 and 51 separation, leaded to the unable normal flight of unmanned aerial vehicle, perhaps damaged because of casing 52 drops at the flight in-process.

In addition, in the embodiment, the brushless motor 53 is turned on, the direction of rotation of the propeller 54 is controlled by the brushless motor 53, the direction of rotation of the propeller 54 is opposite to the screwing direction of the buckle 521, and the reverse torque generated in the rotation process of the propeller 54 enables the buckle 521 to be screwed in the locking direction, so that the buckle 521 is prevented from being separated from the clamping groove 514 due to vibration.

Referring to fig. 4, a strip-shaped reed 515 disposed along a longitudinal direction of each slot 514 is disposed inside each slot 514, a distance between each strip-shaped reed 515 and the mounting surface 512 gradually increases from one end to the other end thereof, one end of each strip-shaped reed 515 is fixedly connected to the mounting seat 51, and one end of each strip-shaped reed 515 is far away from the mounting surface 512.

By arranging strip-shaped reed 515, when casing 52 is clamped on mounting seat 51, casing 52 can extrude strip-shaped reed 515, and strip-shaped reed 515 is used for providing pretightening force for casing 52.

Referring to fig. 1, the open end 511 is provided with a ring groove 516, and the housing 52 is provided with a thin wall 522 matching with the ring groove 516.

By inserting the thin wall 522 into the ring groove 516, water and dust are prevented from entering the housing 52, and short-circuiting or poor contact of the wire contact 513 is prevented.

Referring to fig. 1 to 2, a tail 6 is vertically disposed at the rear upper end of the body 2, and a propeller power mechanism 5 is horizontally disposed at the rear end of the body 2.

The propeller power mechanism 5 provided at the rear end of the body 2 has the same structure as the propeller power mechanism 54 provided at the lower end of the front wing 3 or the rear wing 4, and is used to drive the body 2 to move forward while assisting the body 2 to ascend.

Referring to fig. 1 to 2, the lower front end of the body 2 is connected to a front wheel 22 through a front wheel frame 21, the lower rear end of the body 2 is connected to a rear wheel 24 through a rear wheel frame 23, and the two rear wheels 24 are symmetrically arranged on the rear wheel frame 23.

Front wheels 22 and rear wheels 24 are provided to support the body 2 while assisting forward movement and ascent of the body 2.

Referring to fig. 1 and 2, the handpiece 1 is triangular, and the left and right ends of the handpiece 1 are symmetrically provided with the duck wings 11.

The duck wings 11 on the two sides of the nose 1 are important structures for improving the aerodynamic characteristics of the front wing 3 and the rear wing 4, and the favorable vortex generated by the duck wings 11 can reduce the mutual interference between the front wing 3 and the rear wing 4 and the propeller power mechanism 5.

Example 2

In the figures, the same reference numerals are used as in the previous embodiments, and the definitions of the reference numerals in the previous embodiments are still used.

The newly appearing reference numerals are defined as follows: 25. an umbrella cabin; 251. a second pin hole; 252. a support plate; 253. a spring; 26. a cabin door; 261. a first pin hole; 27. a steering engine; 271. a rocker arm; 272. a bolt; 28. a parachute; 281. an umbrella rope; 29. and (5) hanging points.

Referring to fig. 6 to 7, the present embodiment is different from embodiment 1 in that: an umbrella cabin 25 is arranged at the upper end of the machine body 2, an opening is formed in the upper end of the umbrella cabin 25, an opening 511 of the umbrella cabin 25 is hinged to one end of a cabin door 26, a first pin hole 261 is formed in the other end of the cabin door 26, a second pin hole 251 corresponding to the first pin hole 261 is formed in the machine body 2, a steering engine 27 is arranged in the machine body 2, an output end of the steering engine 27 is fixedly connected with a rocker arm 271, and a bolt 272 on the rocker arm 271 can be driven by the steering engine 27 to be inserted into the second pin hole 251 and the first pin hole 261 or be withdrawn from the first pin hole 261 and the second pin hole 251, so that the cabin door 26 is locked or unlocked;

a supporting plate 252 is horizontally arranged in the umbrella cabin 25, the supporting plate 252 is connected with the inner bottom surface of the umbrella cabin 25 through four springs 253, the four springs 253 are dispersedly arranged between the supporting plate 252 and the umbrella cabin 25 according to the requirement of uniform stress, and a parachute 28 in a folded state is placed at the upper end of the supporting plate 252;

the parachute line 281 is four and evenly distributed relative to the parachute 28, one end of the single parachute line 281 is fixedly connected with the lower end of the parachute 28, and the other end of the single parachute line 281 extends out of a gap between the parachute bay 25 and the bay door 26 and is fixedly connected to the hanging point 29 of the fuselage 2.

In this embodiment, by arranging the umbrella cabin 25, the cabin door 26, the steering engine 27, the parachute 28 and the umbrella rope 281, in the normal flight process of the unmanned aerial vehicle, the parachute 28 is stored in the umbrella cabin 25 in a folded state, the umbrella rope 281 extends out from a gap between the umbrella cabin 25 and the cabin door 26 and is fixedly connected to the hanging point 29 of the fuselage 2, at this time, the other end of the rocker 271 is inserted into the second pin hole 251 and the first pin hole 261 to lock the cabin door 26, and at this time, the four springs 253 are in a compressed state.

When unmanned aerial vehicle meets with extreme weather, when meeting the barrier in the air or unmanned aerial vehicle self breaks down, in order to avoid the direct crash of unmanned aerial vehicle, reduce the descending loss of unmanned aerial vehicle, steering wheel 27 rotates through control signal control, the bolt 272 that steering wheel 27's output drove rocking arm 271 withdraws from in first pinhole 261 and the second pinhole 251 in proper order, hatch door 26 is in the unblock state this moment, and four springs 253 are by compression state recovery deformation, it rises to promote layer board 252, layer board 252 further drives parachute 28 again and rises and make parachute 28 release from the umbrella cabin 25, parachute 28 is after breaking away from umbrella cabin 25, become the form of relaxing by the rugosity, and make parachute 28 open completely by the air that makes progress, parachute 281 is in the state of tightening this moment, realize unmanned aerial vehicle's urgent landing.

In addition, because the other end of the parachute line 281 extends out from the gap between the parachute bay 25 and the bay door 26 and is fixedly connected to the hanging points 29 of the fuselage 2, the four hanging points 29 are uniformly distributed on the fuselage 2 and use the gravity center of the fuselage 2 as round points, so that the stress of the whole fuselage 2 is more balanced, and the unmanned aerial vehicle can land stably.

In addition, when front wing 3 and rear wing 4 in this application no longer set up screw power unit 5, the utility model discloses only when the rear end of fuselage sets up a screw power unit 5, unmanned aerial vehicle takes off through the screw power unit 5 or the ejection mechanism of rear end, simultaneously because the weight of fuselage 2 becomes light, makes unmanned aerial vehicle can load more goods, through parachute 28, still can realize unmanned aerial vehicle's steady landing, makes unmanned aerial vehicle safe landing.

Control signal control steering wheel 27 in this embodiment is conventional technical means, is not the protection of the utility model is important, does not do here and does not describe any more.

Example 3

The newly appearing reference numerals are defined as follows: 7. and (4) sweeping the wing backwards.

Referring to fig. 8 and 9, the present embodiment is different from embodiment 2 in that: the wing tips of the two front wings 3 are symmetrically connected with sweepback wings 7.

The sweepback wing 7 that sets up can increase 2 partial lift of fuselage, stability, can also improve the loading capacity in addition, simultaneously can also improve flying speed, make the application scene of sweepback wing 7 abundanter, here, can set up corresponding bolt and pinhole at the wing point portion of preceding wing 3 and the wing root of sweepback wing 7, through inserting the bolt pinhole hole, then insert the pinhole in the rethread jackscrew, and the tight bolt in top, thereby make preceding wing 3 and the sweepback wing 7 fastening concatenation, this embodiment is through this kind of mode to sweepback wing 7 fast loading and unloading, effectively promote unmanned aerial vehicle's loading capacity, stability etc., unmanned aerial vehicle's application occasion and scope have still been extended simultaneously.

Example 4

The newly appearing reference numerals are defined as follows: 8. straight wing.

Referring to fig. 10, the difference between the present embodiment and fig. 3 is that the swept-back wing 7 is replaced by a straight wing 8.

The flat straight wing 8 that sets up can increase 2 lift of fuselage in order to improve the load, make the application scene of flat straight wing 8 abundanter, here, can set up corresponding bolt and pinhole at the wingtip of front wing 3 and the root of the flat wing 8, through inserting the bolt pinhole, then insert in the pinhole through the jackscrew, and the tight bolt in top, thereby make front wing 3 and the fastening concatenation of flat straight wing 8, this kind of mode of this embodiment through to the 8 fast loading and unloading of flat straight wing, effectively promote unmanned aerial vehicle's dead weight, stability etc., unmanned aerial vehicle's application and scope have still been extended to the while.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", and the like, indicate the orientation or positional relationship indicated based on the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

In the present application, unless expressly stated or limited otherwise, the first feature may be directly on or directly under the second feature or indirectly via intermediate members. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction. Although embodiments of the present invention have been shown and described, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art without departing from the scope of the present invention.

Claims

1. The utility model provides a novel VTOL unmanned aerial vehicle of hookup wing configuration which characterized in that: comprises a machine head, a machine body, a front wing, a rear wing and a propeller power mechanism;

the machine head is connected to the front end of the machine body;

2. The novel VTOL UAV of claim 1, wherein: the propeller power mechanism comprises a mounting seat, a shell, a brushless motor and a propeller; the one end and the back wing of mount pad or front wing fixed connection, the other end of mount pad are the open end, and the open end department of mount pad is equipped with the installation face, be equipped with the wire contact on the installation face, the casing lock joint is in the open end, brushless motor is fixed to be set up in the casing, and brushless motor is towards the one end and the wire contact of open end, and the one end that brushless motor kept away from the open end is the output and stretches out from the casing, the screw with output fixed connection.

3. The novel VTOL UAV of claim 2, wherein: the mounting surface is equidistantly provided with a plurality of clamping grooves in a knife shape, a plurality of buckles are annularly arranged in the casing at equal intervals, and a single buckle can be inserted into the corresponding clamping groove and locked in the clamping groove.

4. The novel VTOL UAV of claim 3, wherein: every the inboard of draw-in groove all is equipped with the bar reed of arranging along the length direction of draw-in groove, the bar reed arrives distance between the installation face is for gradually becoming big along its one end to its other end, the one end and the mount pad fixed connection of bar reed, and the installation face is kept away from to the one end of bar reed.

5. The novel VTOL UAV of claim 4, wherein: the opening end is provided with a circle of annular groove, and the casing is provided with a circle of thin wall matched with the annular groove.

6. The novel VTOL UAV of claim 1, wherein: the lower front end of the machine body is connected with a front wheel through a front wheel carrier, the lower rear end of the machine body is connected with a rear wheel through a rear wheel carrier, and the two rear wheels are arranged on the rear wheel carrier in a bilateral symmetry mode.

7. The novel VTOL UAV of claim 1, wherein: the rear upper end of the machine body is vertically provided with a machine tail, and the rear end of the machine body is horizontally provided with the propeller power mechanism.

8. The novel VTOL UAV of claim 1, wherein: the aircraft nose is triangle-shaped, and the left and right ends symmetry of aircraft nose is equipped with the duck wing.

9. The novel VTOL UAV of claim 1, wherein: the wing tips of the two front wings are symmetrically connected with a straight wing or a sweepback wing.

10. The novel VTOL UAV of claim 1, wherein: an umbrella cabin is arranged at the upper end of the machine body, an opening is formed in the upper end of the umbrella cabin, the opening of the umbrella cabin is hinged with one end of a cabin door, a first pin hole is formed in the other end of the cabin door, a second pin hole corresponding to the first pin hole is formed in the machine body, a steering engine is arranged in the machine body, the output end of the steering engine is fixedly connected with a rocker arm, and a bolt on the rocker arm can be inserted into the second pin hole and the first pin hole or withdrawn from the first pin hole and the second pin hole under the driving of the steering engine, so that the cabin door is locked or unlocked;