CN209870731U

CN209870731U - Unmanned plane

Info

Publication number: CN209870731U
Application number: CN201920212496.7U
Authority: CN
Inventors: 陈健平
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-02-19
Filing date: 2019-02-19
Publication date: 2019-12-31
Anticipated expiration: 2029-02-19

Abstract

The utility model relates to an unmanned aerial vehicle, including the housing, the center of housing is equipped with the thrust duct, is the circumference along the housing center and distributes all to be equipped with at its front side, rear side, left side and right side and turn to the duct, is equipped with thrust rotor device, thrust wind-guiding subassembly in the thrust duct, turns to and is equipped with the horizontal rotor device in the duct, and is located turning to and is equipped with in the duct of both sides around and turns to the wind-guiding subassembly. The utility model discloses fast, the navigation is stable, can realize various flight status.

Description

Unmanned plane

Technical Field

The utility model relates to a flight technical field especially relates to an unmanned aerial vehicle.

Background

In the existing unmanned aerial vehicle field, the unmanned aerial vehicle is divided into a fixed wing unmanned aerial vehicle and a rotor unmanned aerial vehicle. The fixed wing unmanned aerial vehicle has long endurance, relatively large load capacity and high speed, but cannot take off vertically; rotor unmanned aerial vehicle continuation of the journey mileage is shorter, and the loading capacity is less relatively, but speed is slow, can't sail for a long time. Moreover, the wind resistance of the fixed-wing unmanned aerial vehicle and the rotor unmanned aerial vehicle is weak, so that the normal navigation of the unmanned aerial vehicle is influenced, wherein the fixed-wing unmanned aerial vehicle obtains lift force by means of two wings, and meanwhile, the up-and-down flow of air can also generate disturbance to the two wings of the unmanned aerial vehicle; when rotor unmanned aerial vehicle relies on rotor wind to blow from the side, can exert an influence to the rotor.

SUMMERY OF THE UTILITY MODEL

The to-be-solved technical problem of the utility model is to provide an unmanned aerial vehicle that is fast, navigation is stable, can realize various flight status.

The utility model relates to an unmanned aerial vehicle, including the housing, the center of housing is equipped with the thrust duct, all is equipped with the steering duct along the front side, rear side, left side and right side that the housing center is the circumference and distributes at it, be equipped with thrust rotor device, thrust wind-guiding subassembly in the thrust duct, be equipped with horizontal rotor device in the steering duct, and wherein be equipped with steering wind-guiding subassembly in two of them steering ducts with the housing centrosymmetry;

the thrust rotor wing device comprises a first rotor wing component and a second rotor wing component, the first rotor wing component and the second rotor wing component are oppositely arranged up and down and have opposite rotating directions, the first rotor wing component and the second rotor wing component are fixed on the connecting component, the connecting component is fixed with the housing, the thrust air guide component is arranged below the second rotor wing component and comprises a first positive and negative motor, a thrust air guide plate, a first rotating shaft and a pull rod, the thrust air deflector is distributed in a plurality along the radial direction of the encloser at equal intervals, the first rotating shaft is arranged in the middle of the thrust air deflector, two ends of the first rotating shaft are rotatably connected with the housing, an output shaft of the first positive and negative motor is arranged in parallel with the first rotating shaft, an output shaft of the first positive and negative motor is connected with a first rotating shaft on one of the thrust air deflectors, and adjacent thrust air deflectors are connected through a pull rod;

the horizontal rotor device comprises a third rotor component, the third rotor component is fixed on the upper portion of the connecting component, the steering air guide component is arranged below the third rotor component and comprises a second positive and negative motor, a steering air guide plate and a second rotating shaft, the thrust air guide plate is radially arranged along the housing, the second rotating shaft is arranged in the middle of the thrust air guide plate, two ends of the second rotating shaft are rotatably connected with the housing, an output shaft of the second positive and negative motor is connected with one end of the second rotating shaft, and an output shaft of the second positive and negative motor drives the second rotating shaft to rotate positively and negatively so as to drive the steering air guide plate.

Preferably, the horizontal rotor device further comprises a fourth rotor assembly, the fourth rotor assembly is arranged between the third rotor assembly and the steering wind guide assembly, the fourth rotor assembly is fixed at the lower part of the connecting assembly, and the third rotor assembly and the fourth rotor assembly are oppositely arranged up and down and have opposite rotating directions.

In any of the above-mentioned schemes preferred, first rotor subassembly, second rotor subassembly, third rotor subassembly, fourth rotor subassembly all include motor, paddle, the motor is fixed on coupling assembling, the output and the paddle of motor are connected.

In any of the above embodiments, preferably, the blade lengths of the first and second rotor assemblies are greater than the blade lengths of the third and fourth rotor assemblies.

In any of the above schemes, preferably, the connecting assembly includes a first connecting rod and a second connecting rod which are arranged in a crisscross manner, and both ends of the first connecting rod and the second connecting rod respectively penetrate through the thrust duct, extend into the steering duct corresponding to the positions of the thrust duct and are connected with the housing.

In any of the above schemes, preferably, the housing includes an upper housing and a bottom plate that are detachably connected, the center of the upper housing is a plane, the periphery of the upper housing is a slope surface connected with the plane, the periphery of the slope surface is connected with the bottom plate, and the thrust duct and the steering duct are arranged on the upper housing.

In any of the above schemes, preferably, the bottom of the casing is provided with a chassis support.

In any of the above schemes, preferably, a control box is arranged inside the housing or in the center of the top of the housing, and a storage battery, a flight control system and a controller are arranged in the control box.

Compared with the prior art, the utility model has the advantages and beneficial effects do:

(1) thrust rotor device all adopts double-deck rotor structure with horizontal rotor device, the rotor area increases, the area of contact of increase and air, first rotor subassembly and second rotor subassembly and third rotor subassembly and fourth rotor subassembly produced lift and power can offset unmanned aerial vehicle self when high-speed rotatory gravity, with the navigation inertia that improves unmanned aerial vehicle, and then improve unmanned aerial vehicle's anti-wind ability, guarantee that unmanned aerial vehicle takes off perpendicularly fast and normally navigates by water, and unmanned aerial vehicle's loading capacity.

(2) Thrust duct and the setting that turns to the duct, make unmanned aerial vehicle when rising or navigation, the air is from last to providing lift down, the air is respectively through the thrust duct, turn to in the duct gets into each rotor device place region, the thrust duct, turn to the duct and can separate the air resistance in peripheral air of unmanned aerial vehicle and the housing, reduce the influence of housing periphery crosswind to each rotor device, make the wind-force of each rotor device each side even, improve unmanned aerial vehicle's anti-wind ability and promote unmanned aerial vehicle's promotion power.

(3) The whole upper portion of housing is domatic, and the lower part is the horizontal plane, and the air flows to all around along the arc surface, reduces the air to unmanned aerial vehicle's rising resistance, improves unmanned aerial vehicle's rising speed and lift. The encloser seals each rotor wing device inside, has the guard action to each rotor wing device.

(4) The unmanned aerial vehicle body can realize the flight in various states, wherein the hovering control body is realized by the same rotating speed of each rotor wing assembly, the steering air deflector is in a vertical state when the unmanned aerial vehicle body is controlled to vertically ascend or horizontally fly, and for the horizontal flight, the vertical state of the steering air deflector can ensure that the unmanned aerial vehicle body does not deviate left and right, and the stable flight is ensured; by controlling the steering and the angle of the steering air deflectors on the front side and the rear side and combining with the state of the thrust air deflector, various states such as hovering rotation, rotation vertical rising, horizontal inclined flying and the like can be realized, and the device is suitable for various fields, particularly the logistics field, the military field, flight performance and the like.

The utility model discloses an unmanned aerial vehicle does further explanation below with the accompanying drawing.

Drawings

Fig. 1 is a perspective view of the unmanned aerial vehicle of the present invention;

fig. 2 is a structural diagram of a housing in the unmanned aerial vehicle of the present invention;

fig. 3 is a structural diagram of a thrust air guide assembly and a steering air guide assembly in the unmanned aerial vehicle of the present invention;

fig. 4 is an installation structure diagram of the thrust air guide assembly in the unmanned aerial vehicle of the present invention;

fig. 5 is a view of the installation structure of the first, second, third and fourth rotor assemblies of the unmanned aerial vehicle of the present invention;

fig. 6 is a structural diagram of a chassis support in the unmanned aerial vehicle of the present invention;

wherein: 1. a housing; 2. a thrust duct; 3. turning to a duct; 4. a first rotor assembly; 5. a second rotor assembly; 6. a thrust air guide component; 61. a first positive and negative motor; 62. a thrust air deflector; 63. a first rotating shaft; 64. a pull rod; 7. a third rotor assembly; 8. a fourth rotor assembly; 9. a steering wind guide component; 91. a second positive and negative motor; 92. a steering air deflector; 93. a second rotating shaft; 10. a first connecting rod; 11. a second connecting rod; 12. a motor; 13. a paddle; 14. a chassis support.

Detailed Description

As shown in fig. 1-6, the utility model relates to an unmanned aerial vehicle, including housing 1, the center of housing 1 is equipped with thrust duct 2, is the circumference along housing 1 center and distributes all to be equipped with on its front side, rear side, left side and right side and turn to duct 3, is equipped with thrust rotor device, thrust wind-guiding subassembly 6 in the thrust duct 2, turns to and is equipped with horizontal rotor device in the duct 3, and is located turning to and is equipped with in the duct 3 of both sides around and turns to wind-guiding subassembly 9.

The thrust rotor wing device comprises a first rotor wing component 4 and a second rotor wing component 5, wherein the first rotor wing component 4 and the second rotor wing component 5 are arranged up and down oppositely and have opposite rotating directions, the first rotor wing component 4 and the second rotor wing component 5 are fixed on a connecting component, and the connecting component is fixed with the housing 1; the horizontal rotor assembly comprises a third rotor assembly 7, the third rotor assembly 7 being secured to an upper portion of the attachment assembly.

The horizontal rotor device further comprises a fourth rotor assembly 8, the fourth rotor assembly 8 is arranged between the third rotor assembly 7 and the steering air guide assembly 9, the fourth rotor assembly 8 is fixed at the lower part of the connecting assembly, and the third rotor assembly 7 and the fourth rotor assembly 8 are arranged up and down oppositely and rotate in opposite directions.

The arrangement of the third rotor assembly 7 or the combination of the third rotor assembly 7 and the fourth rotor assembly 8 in the horizontal rotor apparatus depends on the actual load capacity of the airframe, and the preferred configuration in the horizontal rotor apparatus is the arrangement of the combination of the third rotor assembly 7 and the fourth rotor assembly 8.

The thrust rotor wing device is positioned in the center of the housing 1 and is mainly used for controlling the vertical takeoff and horizontal flight of the aircraft body; the horizontal rotor wing devices positioned at the front side and the rear side generate speed difference by changing the rotating speed of the rotor wings at the front side and the rear side, so that the aircraft body is controlled to fly in a pitching manner; the horizontal rotor wing devices positioned at the left side and the right side generate speed difference by changing the rotating speed of the rotor wings at the left side and the right side, so that the aircraft body is controlled to transversely roll and fly.

In addition, first rotor subassembly 4 is the same with second rotor subassembly 5, the third rotor subassembly 7 of each direction and the speed of fourth rotor subassembly 8, and unmanned aerial vehicle is hover state.

Thrust rotor device all adopts double-deck rotor structure with horizontal rotor device, the rotor area increases, the area of contact of increase and air, unmanned aerial vehicle self's gravity can be offset to first rotor subassembly 4 and second rotor subassembly 5 and third rotor subassembly 7 and fourth rotor subassembly 8 produced lift and power when high-speed rotatory, with the navigation inertia that improves unmanned aerial vehicle, and then improve unmanned aerial vehicle's anti-wind ability, guarantee that unmanned aerial vehicle takes off perpendicularly fast and normally navigates by water, and unmanned aerial vehicle's loading capacity.

Thrust duct 2 with turn to duct 3's setting, make unmanned aerial vehicle when ascending or navigation, the air is from last to providing lift down, the air is respectively through thrust duct 2, turn to duct 3 and get into each rotor device in the region, thrust duct 2, turn to duct 3 and can separate the air resistance in peripheral air of unmanned aerial vehicle and the housing 1, reduce the influence of 1 periphery crosswind of housing to each rotor device, make the wind-force of each rotor device each side even, improve unmanned aerial vehicle's anti-wind ability and promote unmanned aerial vehicle's promotion power.

Further, first rotor subassembly 4, second rotor subassembly 5, third rotor subassembly 7, fourth rotor subassembly 8 all include motor 12, paddle 13, and motor 12 fixes on coupling assembling, and the output and the paddle 13 of motor 12 are connected. The blades 13 are rotated at high speed by the motor 12.

Further, the length of blades 13 of first rotor assembly 4 and second rotor assembly 5 is greater than the length of blades 13 of third rotor assembly 7 and fourth rotor assembly 8.

Furthermore, the connecting assembly comprises a first connecting rod 10 and a second connecting rod 11 which are arranged in a cross manner, and two ends of the first connecting rod 10 and the second connecting rod 11 respectively penetrate through the thrust duct 2 and extend into the steering duct 3 corresponding to the positions of the thrust duct and the second connecting rod, and are connected with the housing 1.

The thrust air guide assembly 6 is arranged below the second rotor assembly 5, the thrust air guide assembly 6 comprises a first positive and negative electricity 61, thrust air guide plates 62, a first rotating shaft 63 and pull rods 64, the thrust air guide plates 62 are distributed in a plurality of radial equal intervals along the housing 1, the first rotating shaft 63 is arranged in the middle of the thrust air guide plates 62, two ends of the first rotating shaft 63 are rotatably connected with the housing 1, an output shaft of the first positive and negative electricity 61 is arranged in parallel with the first rotating shaft 63, an output shaft of the first positive and negative electricity 61 is connected with the first rotating shaft 63 on one thrust air guide plate 62, adjacent thrust air guide plates 62 are connected through the pull rods 64, and the thrust air guide plates 62 are driven to rotate positively and negatively through the first positive and negative motors 61 and the pull rods 64; turn to air guide assembly 9 and set up the below at fourth rotor subassembly 8, turn to air guide assembly 9 and include positive and negative motor 91 of second, turn to aviation baffle 92, second pivot 93, thrust aviation baffle 62 radially sets up along housing 1, second pivot 93 sets up the middle part at thrust aviation baffle 62, the both ends of second pivot 93 rotate with housing 1 and are connected, the output shaft and the one end of second pivot 93 of positive and negative motor 91 of second are connected, the output shaft of positive and negative motor 91 of second is through driving second pivot 93 in order to drive turn to aviation baffle 92 forward and backward rotation.

Through setting up thrust wind guide assembly 6 and turning to wind guide assembly 9 in order to realize unmanned aerial vehicle's navigation thrust or resistance and the change of unmanned aerial vehicle navigation direction. Specifically, the thrust rotor wing device controls the machine body to take off vertically and fly horizontally by changing the rotation angle of the thrust air guide assembly 6; thrust air guide assembly 6 is through utilizing thrust aviation baffle 62 forward and reverse rotation, increases horizontal thrust to and make unmanned aerial vehicle can realize the VTOL, compare with conventional rotor unmanned aerial vehicle, speed obviously promotes. Thrust aviation baffle 62's rotation angle is less than 90 degrees, thrust aviation baffle 62's turned angle is decided according to unmanned aerial vehicle's navigation state, wherein, when unmanned aerial vehicle rose, thrust aviation baffle 62 is 0 degree with the contained angle of vertical face, this moment, thrust aviation baffle 62 is vertical state, the vertical rise of unmanned aerial vehicle, guarantee that unmanned aerial vehicle's rising power and rising speed unmanned aerial vehicle when going on horizontal navigation after rising to the take the altitude, the angle between thrust aviation baffle 62 and the vertical face is big more, the air is big more to unmanned aerial vehicle's horizontal driving force, at this moment, drive thrust aviation baffle 62 through first positive electricity 61 and counter electricity and rotate, preferably, when horizontal navigation, thrust aviation baffle 62's rotation angle scope is 0 ~ 45 degrees.

The aircraft body is controlled by the steering air guide assemblies 9 in the steering ducts 3 at the front side and the rear side to realize the flying states of steering, rotating, turning and oblique flying, wherein when the aircraft body is in a suspension flying state or horizontal flying state, the steering air guide plates 92 are vertical, when the steering air guide plates 92 at the front side and the rear side rotate in different directions, the aircraft body realizes the flying states of steering, turning and rotating, and when the steering air guide plates 92 at the front side and the rear side rotate in the same direction, the aircraft body realizes the oblique flying state.

It should be noted that the unmanned aerial vehicle body in this embodiment can realize flying in various states, wherein hovering is controlled by the same rotating speed of each rotor assembly, and when the unmanned aerial vehicle body is controlled to vertically ascend or horizontally fly, the steering air deflector 92 is in a vertical state, and for horizontal flying, the vertical state of the steering air deflector 92 can ensure that the unmanned aerial vehicle body does not deviate left and right, and stable flying is ensured; by controlling the steering and the angle of the steering air deflectors 92 at the front side and the rear side and combining with the state of the thrust air deflector 62, various states such as hovering rotation, rotating vertical rising, horizontal inclined flying and the like can be realized, and the device is suitable for various fields, in particular to the logistics field, the military field, flight performance, the fire fighting field, the earthquake relief field and the like.

Further, the thrust air deflector 62 is arranged in a central symmetry manner by the first rotating shaft 63, and the steering air deflector 92 is arranged in a central symmetry manner by the second rotating shaft 93, so that the positive and negative moments of the thrust air deflector 62 and the steering air deflector 92 are offset to zero when the two rotate, and the unmanned aerial vehicle is ensured to run stably.

Further, the pull rod assembly comprises a first pull rod 64 and a second pull rod 65, the middle of the first pull rod 64 is connected with the output shaft of the first positive and negative electricity 61, two ends of the first pull rod 64 are respectively connected with the end of the second pull rod 65 in a rotating manner, the inner side of the first pull rod 64 is fixedly connected with the first rotating shaft 63 on the thrust air deflector 62 positioned in the middle, and the second pull rod 65 is fixedly connected with the first rotating shaft 63 on the thrust air deflectors 62 positioned at two sides. The first forward and reverse rotation motor 12 drives the first pull rod 64 and the second pull rod 65 in sequence by power, and the second pull rod 65 drives the thrust air deflector 62 to realize forward and reverse rotation.

Further, the housing 1 comprises an upper housing body and a bottom plate which are detachably connected, the center of the upper housing body is a plane, the periphery of the upper housing body is a slope surface connected with the plane, the periphery of the slope surface is connected with the bottom plate, and the thrust duct and the steering duct are arranged on the upper housing body. Wherein, the thrust duct 2 is arranged at the central plane of the upper cover body, and the steering duct 3 is arranged on the slope. The whole upper portion of housing 1 is domatic, and the lower part is the horizontal plane, and the air flows to all around along the arc surface, reduces the air to unmanned aerial vehicle's rising resistance, improves unmanned aerial vehicle's rising speed and lift. The housing 1 encloses each rotor device inside, and has a protective effect on each rotor device.

Further, a chassis support 14 is provided at the bottom of the housing 1.

Furthermore, a control box is arranged inside the housing 1 or in the center of the top of the housing 1, and a storage battery, a flight control system and a controller are arranged in the control box.

When the unmanned aerial vehicle navigates, air firstly enters the area where each rotor wing device is located through the thrust duct 2 and each steering duct 3, and then is guided out through each air guide component.

The above-mentioned embodiments are only for describing the preferred embodiments of the present invention, and are not intended to limit the scope of the present invention, and various modifications and improvements made by those skilled in the art without departing from the design spirit of the present invention should fall into the protection scope defined by the claims of the present invention.

Claims

1. An unmanned aerial vehicle, its characterized in that: the wind power generation device comprises a housing, wherein a thrust duct is arranged at the center of the housing, steering ducts are arranged on the front side, the rear side, the left side and the right side of the housing along the center of the housing in a circumferential manner, a thrust rotor wing device and a thrust wind guide assembly are arranged in the thrust duct, a horizontal rotor wing device is arranged in the steering duct, and steering wind guide assemblies are arranged in the steering ducts on the front side and the rear side;

2. The drone of claim 1, wherein: the horizontal rotor device still includes the fourth rotor subassembly, the fourth rotor subassembly sets up the third rotor subassembly with turn to between the wind-guiding subassembly, the lower part at coupling assembling is fixed to the fourth rotor subassembly, third rotor subassembly and fourth rotor subassembly relative setting and rotation direction are opposite from top to bottom.

3. A drone according to claim 2, characterized in that: first rotor subassembly, second rotor subassembly, third rotor subassembly, fourth rotor subassembly all include motor, paddle, the motor is fixed on coupling assembling, the output and the paddle of motor are connected.

4. A drone according to claim 3, characterised in that: the blade lengths of the first rotor assembly and the second rotor assembly are greater than the blade lengths of the third rotor assembly and the fourth rotor assembly.

5. A drone according to claim 3, characterised in that: the connecting assembly comprises a first connecting rod and a second connecting rod which are arranged in a cross manner, and two ends of the first connecting rod and the second connecting rod respectively penetrate through the thrust duct, extend into the steering duct corresponding to the positions of the thrust duct and are connected with the housing.

6. The drone of claim 1, wherein: the housing comprises an upper cover body and a bottom plate which are detachably connected, the center of the upper cover body is a plane, the periphery of the upper cover body is a slope surface connected with the plane, the periphery of the slope surface is connected with the bottom plate, and the thrust duct and the steering duct are arranged on the upper cover body.

7. The drone of claim 1, wherein: and a chassis support is arranged at the bottom of the housing.

8. The drone of claim 1, wherein: the aircraft is characterized in that a control box is arranged inside the housing or in the center of the top of the housing, and a storage battery, a flight control system and a controller are arranged in the control box.