CN212605809U

CN212605809U - Environmental monitoring unmanned aerial vehicle stabilized wing

Info

Publication number: CN212605809U
Application number: CN202020640186.8U
Authority: CN
Inventors: 吕久俊; 时宏
Original assignee: Liaoning Ecological Environment Protection Science And Technology Center
Current assignee: Liaoning Ecological Environment Protection Science And Technology Center
Priority date: 2020-04-24
Filing date: 2020-04-24
Publication date: 2021-02-26
Anticipated expiration: 2030-04-24

Abstract

The utility model relates to an unmanned aerial vehicle, a stable wing of environmental monitoring unmanned aerial vehicle in the technical field, which comprises a body, a plurality of fixed blocks are evenly arranged on the side surface of the body, two rotary rods are movably sleeved between the fixed blocks, both ends of the rotary rods penetrate through the fixed blocks and extend to the outside of the side surface of the fixed blocks, nuts are sleeved at both ends of the rotary rods, one end of the rotary rods, which is far away from the body, is fixedly connected with a connecting plate, the other end of the connecting plate is provided with a wing, one end of the top end of the wing, which is far away from the body, is fixedly connected with a vertical lifting device, the rotary rods can rotate by screwing the nuts, then the wing can rotate to be parallel to the body, the folding of the wing is completed, the carrying of the wing is prevented from being damaged by accidental injury, the screws are, influence unmanned aerial vehicle's flight, improved unmanned aerial vehicle's stability, this stable form wing life is longer, facilitate promotion.

Description

Environmental monitoring unmanned aerial vehicle stabilized wing

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is an environmental monitoring unmanned aerial vehicle stabilized wing.

Background

Unmanned aerial vehicle is called unmanned aerial vehicle for short, utilize radio remote control equipment and the unmanned aerial vehicle that the program control device of self-contained was controlled, current unmanned aerial vehicle wing is mostly fixed, can not fold the operation, lead to unmanned aerial vehicle when the transport, it is not very convenient, fragile, the windward resistance of wing is very big when the transition flies, can't transition smoothly to the level flight state, it is stable inadequately, can't satisfy people's user demand, therefore we propose an environmental monitoring unmanned aerial vehicle stable formula wing and solve above-mentioned problem.

SUMMERY OF THE UTILITY MODEL

The utility model provides an environmental monitoring unmanned aerial vehicle stabilized wing, with solving current crops cultivation device overall structure insecure, can appear becoming flexible or the phenomenon of collapsing often using, cause to grow seedlings and drop from growing seedlings the dish, break and grow seedlings, thereby cause the loss, insect damage can appear at the in-process of growing seedlings and grow seedlings, thereby cause the survival rate of growing seedlings to reduce, when cultivateing the seedling watering, kettle or atomizer usually, the judgement of watering degree is carried out according to operating personnel self experience, this kind of watering mode causes the waste of water resource easily, most crops cultivation device can't deal with the problem of cold and hot weather.

Realize above-mentioned purpose, the utility model provides a following technical scheme: the utility model provides an environmental monitoring unmanned aerial vehicle stabilized wing includes the organism, evenly be provided with a plurality of fixed blocks, two on the side of organism the rotary rod has been cup jointed in the activity between the fixed block, the rotary rod both ends all run through the fixed block and extend to the outside of fixed block side, the nut has been cup jointed at the both ends of rotary rod, the one end fixedly connected with connecting plate of organism is kept away from on the rotary rod, the other end of connecting plate is provided with the wing, the one end fixedly connected with VTOL device of organism is kept away from on the wing top.

Preferably, the number of the fixed blocks is four, and two fixed blocks are symmetrically distributed on two sides of the machine body in a group.

Preferably, the wing includes the wing main part, the one end of keeping away from the organism in the wing main part is equipped with outer wing, install the trailing edge flap on the top of wing main part, install the flaperon on the top of outer wing, the fracture space has been seted up in the wing main part, install the compound covering of venetian blind formula fracture in the fracture space, the both ends and the wing main part swivelling joint of the compound covering of venetian blind formula fracture, be equipped with the pole that inclines in the fracture space, the cover is equipped with the power device that inclines on the pole, be equipped with the space that link up in the wing main part, the both ends swivelling joint of pole that inclines is in lining up the space, the pole that inclines is equipped with the sealing washer with the space junction that link up, the sealing washer is equipped with the bearing with.

Preferably, a plurality of wing assistants are uniformly arranged in the cracking space, penetrate through the shutter type cracking composite skin and are fixedly connected to the wing main body.

Preferably, the VTOL device includes the loop bar, the bottom fixed connection of loop bar is in the top of outer wing, the top activity of loop bar has cup jointed the rotating vane, the fixed stopper that is located the rotating vane top that has cup jointed on the loop bar.

Preferably, the power device that verts includes the propeller hub radome fairing, evenly be equipped with a plurality of screw on the propeller hub radome fairing, the bottom of propeller hub radome fairing is equipped with the mounting bracket.

Compared with the prior art, the beneficial effects of the utility model are that:

the stable wing of the environment monitoring unmanned aerial vehicle can rotate by screwing the nut, then the wing can rotate to be parallel to the body, the folding of the wing is completed, the space is greatly saved, the wing is prevented from being damaged due to accidental injury during carrying, the safety of the unmanned aerial vehicle is improved, the screw is fixed by screwing the nut, the wing is prevented from shaking during the flying process of the unmanned aerial vehicle, the flying of the unmanned aerial vehicle is prevented from being influenced, the stability of the unmanned aerial vehicle is improved, the integral strength and rigidity of the wing can be improved by arranging the wing aid, the rotating blade is limited by the limiting block, the rotating blade is prevented from being separated from the sleeve rod due to the action of centrifugal force in the rotating process, the flying accident is caused, the safety of the unmanned aerial vehicle is improved, the area of the wing is greatly increased by arranging the outer wing, more lifting force is provided for high-speed flat flying, and the wing, the wing area can be increased by installing the trailing edge flap and the flaperon, the lift coefficient of the wing is improved, and the stability of the body is improved.

Drawings

Fig. 1 is the utility model discloses environmental monitoring unmanned aerial vehicle stabilized wing major structure sketch map:

FIG. 2 is a schematic view of the wing main body structure of the present invention;

fig. 3 is the structure diagram of the tilting device of the present invention.

In the figure: the airplane comprises an airplane body 1, 11 fixing blocks, 12 rotating rods, 13 screw caps, 14 connecting plates, 2 wings, 21 wing main bodies, 22 outer wings, 23 trailing edge flaps, 24 flaperon ailerons, 25 cracking spaces, 26 louver type cracking composite skins, 27 through spaces, 28 sealing rings, 29 tilting rods, 3 vertical take-off and landing devices, 31 loop rods, 32 rotating blades, 33 limiting blocks, 4 tilting power devices, 41 propeller hub fairings, 42 propellers, 43 mounting racks and 5 wing assistants.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Please refer to fig. 1-3, the utility model provides an environmental monitoring unmanned aerial vehicle stabilized wing: comprises a machine body 1, a plurality of fixed blocks 11 are uniformly arranged on the side surface of the machine body 1, a rotary rod 12 is movably sleeved between the two fixed blocks 11, two ends of the rotary rod 12 penetrate through the fixed blocks 11 and extend to the outside of the side surface of the fixed blocks 11, two ends of the rotary rod 12 are sleeved with nuts 13, one end of the rotary rod 12 far away from the machine body 1 is fixedly connected with a connecting plate 14, the other end of the connecting plate 14 is provided with a wing 2, one end of the top end of the wing 2 far away from the machine body 1 is fixedly connected with a vertical lifting device 3, the rotary rod 12 can rotate by screwing the nuts 13, then the wing 2 can rotate to be parallel to the machine body 1, the folding of the wing 2 is completed, the space is greatly saved, the wing 2 is prevented from being accidentally injured and damaged during carrying, the safety of the unmanned aerial vehicle is improved, the screw rod, influence unmanned aerial vehicle's flight, improved unmanned aerial vehicle's stability, through starting VTOL device 3, can accelerate unmanned aerial vehicle rising and descend speed and stationarity.

It refers to figure 1, and fixed block 11 is equipped with four, and every two a set of symmetric distribution of fixed block 11 drive connecting plate 14 when screwing nut 13 and making rotary rod 12 rotatory in the both sides of organism 1 to transmission wing 2, through the distribution of fixed block 11, can not receive when making wing 2 rotatory and block, has both increased unmanned aerial vehicle's function, has reduced unmanned aerial vehicle self weight again.

Referring to fig. 2, the wing 2 includes a wing main body 21, an outer wing 22 is disposed at one end of the wing main body 21 far away from the body 1, a trailing edge flap 23 is mounted at the top end of the wing main body 21, a flaperon 24 is mounted at the top end of the outer wing 22, a cracking space 25 is formed in the wing main body 21, a louver type cracking composite skin 26 is mounted in the cracking space 25, two ends of the louver type cracking composite skin 26 are rotatably connected with the wing main body 21, an inclined rod 29 is disposed in the cracking space 25, an inclined power device 4 is sleeved on the inclined rod 29, a through space 27 is disposed in the wing main body 21, two ends of the inclined rod 29 are rotatably connected in the through space 27, a sealing ring 28 is disposed at a connection position between the inclined rod 29 and the through space 27, a bearing is disposed at a connection position between the sealing ring 28 and the inclined rod 26, the area of the wing 2 is greatly increased by the arrangement of the, the wing load is greatly reduced, the area of the wing 2 can be increased by installing the trailing edge flap 23 and the flaperon 24, the lift coefficient of the wing 2 is improved, the stability of the body 1 is improved, the shutter type cracking composite skin 26 can crack or compound along with the tilting of the tilting power device 4, when the aircraft vertically takes off and lands, the axis direction of the tilting power device 4 is vertical relative to the ground, the shutter type cracking composite skin 26 cracks, a large part of washing power jet flow penetrates through a through space in the wing to blow downwards, the lift efficiency can be greatly improved, so that the aircraft is provided with the dynamic lift as large as possible, and meanwhile, the aircraft can realize vertical taking off and landing, hovering steering or left-right translation, and maneuvering flight such as forward flight, backward flight and the like by controlling the deflection direction of the plurality of shutter type cracking composite skins 26, and the whole wing 2, especially, the outer wing 22 of the wing main body 21 is still kept horizontally fixed, when the aircraft is transited to horizontal flight, the louver type cracking composite skin 26 is closed along with the tilting of the tilting power device 4 and is recombined into a complete wing, so that the aerodynamic lift force is provided for the aircraft, the aerodynamic efficiency can be greatly improved, at the moment, the power jet flow of the tilting power device 4 is blown backwards, the propeller is completely changed into a thruster, the aircraft is pushed to horizontally fly at high speed, the tilting power device 4 is provided with an engine, the tilting power device 4 is ensured to stably tilt through the matching of the tilting rod 29 and the sealing ring 28, and the weight of the wing 2 is reduced through the arrangement of the cracking space 25 and the through space 27, so that the bearing capacity of the aircraft body 1 is increased.

Referring to fig. 2, a plurality of wing assistants 5 are uniformly arranged in the cracking space 25, the wing assistants 5 penetrate through the louver type cracking composite skin 26 and are fixedly connected to the wing main body 21, the overall strength and rigidity of the wing 2 can be improved by arranging the wing assistants 5, and the tilting power device 4 cannot generate friction with the louver type cracking composite skin 26 when tilting.

Referring to fig. 1, VTOL device 3 includes loop bar 31, the bottom fixed connection of loop bar 31 is in the top of outer wing 22, the rotating vane 32 has been cup jointed in the top activity of loop bar 31, the fixed stopper 33 that is located the rotating vane 32 top that has cup jointed on the loop bar 31, restrict rotating vane 32 through stopper 33, prevent rotating vane 32 at the pivoted in-process, break away from loop bar 31 because of the effect of centrifugal force, cause the flight accident, unmanned aerial vehicle's security has been improved.

Referring to fig. 3, the tilting power device 4 includes a hub fairing 41, a plurality of propellers 42 are uniformly arranged on the hub fairing 41, a mounting rack 43 is arranged at the bottom end of the hub fairing 41, the tilting power device 4 can be protected through the arrangement of the hub fairing 41, the propellers 42 rotate at high speed to drive the airframe 1 to fly, the tilting power device 4 is a tilting rotor aircraft, the tilting rotor aircraft is a rotor propulsion device which can change direction respectively arranged at two ends of the wing 2, the whole propulsion device can rotate around the wing shaft from up to forward and can be fixed in a required direction, so that an upward lift force or forward thrust can be generated, the tilting rotor aircraft takes advantages of a fixed-wing aircraft and a helicopter, can vertically take off and land as an ordinary helicopter and hover in the air, and can cruise at a higher speed as a fixed-wing aircraft, when the propulsion device of the rotor craft is vertically upward, the rotor shaft is vertical to the ground, is in a flight state of a cross helicopter and can hover, fly forwards and backwards and fly sideways in the air, and when the aircraft needs to fly horizontally, the operating system can change the magnitude of the lift force on the rotor and the tilting direction of the lift force of the rotor, so that the aircraft can keep or change the flight state.

The working principle is as follows: when the unmanned aerial vehicle is used, the nut 13 is screwed, the rotating rod 12 can rotate, then the wing 2 can rotate to be parallel to the machine body 1, the folding of the wing 2 is completed, the space is greatly saved, the damage of the wing 2 caused by accidental injury during carrying is prevented, the safety of the unmanned aerial vehicle is improved, the screw is fixed by screwing the nut 13, the wing 2 is prevented from shaking in the flight process of the unmanned aerial vehicle, the flight of the unmanned aerial vehicle is influenced, the stability of the unmanned aerial vehicle is improved, the ascending and descending speed and the descending stability of the unmanned aerial vehicle can be accelerated by starting the vertical lifting device 3, the tilting power device 4 is started to lead the louvered type cracking composite skin 26 to crack or be compounded along with tilting, when the vertical lifting device is vertically lifted, the axis direction of the tilting power device 4 is vertical to the ground, at the time, the louvered type cracking composite skin 26 cracks, a large part of downward washing power jet flow passes, the lift efficiency can be greatly improved, so that the aircraft can be provided with the dynamic lift as much as possible, meanwhile, the aircraft can realize the maneuvering flight such as vertical take-off and landing, hovering steering or horizontal translation, forward flight, backward flight and the like by controlling the deflection direction of the plurality of shutter type cracking composite skins 26, at the moment, the whole wing 2, especially the outer wing 22 of the wing main body 21 still keeps horizontal fixed, when the transition is carried out to the horizontal flight, the shutter type cracking composite skins 26 are closed along with the tilting of the tilting power device 4 and are recombined into a complete wing, the aerodynamic lift is provided for the aircraft, the aerodynamic efficiency can be greatly improved, at the moment, the power jet flow of the tilting power device 4 is blown backwards, and the propeller is completely changed into a thruster to push the aircraft to horizontally fly at high speed.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides an environmental monitoring unmanned aerial vehicle stabilized wing, includes organism (1), its characterized in that: evenly be provided with a plurality of fixed blocks (11), two on the side of organism (1) the activity has cup jointed rotary rod (12) between fixed block (11), fixed block (11) and the outside that extends to fixed block (11) side are all run through at rotary rod (12) both ends, nut (13) have been cup jointed at the both ends of rotary rod (12), keep away from one end fixedly connected with connecting plate (14) of organism (1) on rotary rod (12), the other end of connecting plate (14) is provided with wing (2), keep away from one end fixedly connected with VTOL device (3) of organism (1) on wing (2) top.

2. The environmental monitoring unmanned aerial vehicle stabilized wing of claim 1, wherein: the number of the fixed blocks (11) is four, and every two fixed blocks (11) are symmetrically distributed on two sides of the machine body (1) in a group.

3. The environmental monitoring unmanned aerial vehicle stabilized wing of claim 1, wherein: the aircraft wing (2) comprises a wing main body (21), one end, far away from the aircraft body (1), of the wing main body (21) is provided with an outer wing (22), the top end of the wing main body (21) is provided with a trailing edge flap (23), the top end of the outer wing (22) is provided with a flaperon (24), the wing main body (21) is provided with a cracking space (25), a louver type cracking composite skin (26) is arranged in the cracking space (25), two ends of the louver type cracking composite skin (26) are rotatably connected with the wing main body (21), an inclined rotating rod (29) is arranged in the cracking space (25), the inclined rotating rod (29) is sleeved with a tilting power device (4), a through space (27) is arranged in the wing main body (21), and two ends of the inclined rotating rod (29) are rotatably connected in the through space (27), the tilting rod (29) is provided with a sealing ring (28) at the joint of the through space (27), and the sealing ring (28) is provided with a bearing at the joint of the tilting rod (29).

4. The environmental monitoring unmanned aerial vehicle stabilized wing of claim 3, wherein: a plurality of wing assistants (5) are uniformly arranged in the cracking space (25), and the wing assistants (5) penetrate through the shutter type cracking composite skin (26) and are fixedly connected to the wing main body (21).

5. The environmental monitoring unmanned aerial vehicle stabilized wing of claim 1, wherein: vertical take-off and landing device (3) include loop bar (31), the bottom fixed connection of loop bar (31) is in the top of outer wing (22), rotatory leaf (32) have been cup jointed in the top activity of loop bar (31), fixed cover has been connect stopper (33) that are located rotatory leaf (32) top on loop bar (31).

6. The environmental monitoring unmanned aerial vehicle stabilized wing of claim 3, wherein: the tilting power device (4) comprises a propeller hub fairing (41), a plurality of propellers (42) are uniformly arranged on the propeller hub fairing (41), and a mounting frame (43) is arranged at the bottom end of the propeller hub fairing (41).