CN218229414U - Multi-rotor-wing inspection aircraft - Google Patents

Abstract

The utility model discloses an aircraft is patrolled and examined to many rotors, including aircraft body, first camera device, rotor device, second camera device and strutting arrangement, aircraft body side equidistant is equipped with the rotor device, aircraft body top electric connection second camera device, the first camera device of carousel swing joint is passed through to aircraft body bottom, body bottom sliding connection strutting arrangement, the utility model discloses when descending, impulsive force when descending of accessible strutting arrangement buffering aircraft, the arc makes the aircraft can slide subaerial, and the impulsive force of side when descending of buffer block can be cushioned to the swash plate of buffer block can increase the shooting range, and the air pressure that can produce transversely through the air in the square groove in the buffer block to make the aircraft more stable descending, can patrol through first camera device, first camera device adjustable height and angle increase the shooting scope, second camera device can avoid aircraft body striking flying bird in the top of aircraft body.

Description

Multi-rotor-wing inspection aircraft

Technical Field

The utility model relates to an aircraft technical field specifically is a many rotors patrol and examine aircraft.

Background

Through the retrieval, chinese patent No. CN 206921309U's patent discloses a many rotors traffic inspection aircraft, including the aircraft body, the side-mounting of aircraft body has a plurality of horn interface, just the horn interface with aircraft body seamless welding, the side of horn interface is equipped with linking arm and fixed screw, just the linking arm with the horn interface passes through fixed screw fixed connection, the top of linking arm is equipped with six rotors, ultrasonic transducer is installed to one side of horn interface, just ultrasonic transducer with the aircraft body passes through the powerful glue bonding, through installing supersonic generator and ultrasonic transducer, has improved camera treater and has patrolled and examined the image processing ability to the traffic through adopting the information collection appearance to can in time feed back real-time traffic situation, be favorable to the safe of traffic and pass, and according to the design of six rotors, realized the nimble use of aircraft body.

The above patents have the following disadvantages:

1. when the inspection aircraft lands, the foot rest at the bottom has poor anti-skid effect on the ground, so that the rotor wing of the inspection aircraft is easily damaged;

2. above-mentioned patent is patrolled and examined the aircraft and is patrolled and examined the time, the rigidity of camera, the angle that can not adjust the camera alone has certain use limitation.

SUMMERY OF THE UTILITY MODEL

Technical problem to be solved

Not enough to prior art, the utility model provides a many rotors patrol and examine aircraft has solved the problem that the background art provided.

(II) technical scheme

In order to achieve the above purpose, the utility model discloses a following technical scheme realizes: a multi-rotor patrol inspection aircraft comprises an aircraft body, a first camera device, rotor devices, a second camera device and a supporting device, wherein the rotor devices are arranged at the side end of the aircraft body at equal intervals;

the rotor wing device comprises a rotor wing, a rotor wing head, a supporting arm and a sealing ring, wherein the side end of the supporting arm is movably connected with the rotor wing through the rotor wing head, the rotor wings are distributed at equal intervals, and the sealing ring is arranged at the other side end of the supporting arm;

the first camera device comprises a high-definition camera, a night vision camera, a driving box, a signal receiver and a first electric push rod, the driving box is arranged in the first camera device, the surface of the driving box is electrically connected with the high-definition camera, the night vision camera and the signal receiver, a sliding rail is arranged at the side end of the driving box, the side end of the driving box is slidably connected with a first sliding block and the first electric push rod, and the side end of the first electric push rod is movably connected with a rotating shaft through a coupler.

Preferably, the supporting device comprises a first connecting block and a second connecting block, the first connecting block is symmetrically arranged at the side end of the supporting device, the second connecting block is arranged at the other side end of the supporting device, a sliding rail is arranged in the first connecting block, a second sliding block is slidably connected in the first connecting block, a second electric push rod is slidably connected at the side end of the first connecting block, the second sliding block and the second electric push rod are slidably connected with the arc-shaped plate, and an arc-shaped groove is formed in the arc-shaped plate.

Preferably, a slide rail is arranged in the second connecting block, a third slide block is connected in the second connecting block in a sliding manner, a third electric push rod is connected at the side end of the second connecting block in a sliding manner, the third electric push rod and the side end of the third slide block are connected with a buffer block in a sliding manner, an inclined plate is fixedly connected at the side end of the buffer block, and a square groove is formed in the buffer block.

Preferably, the second camera device comprises a distance measuring sensor and an intelligent camera, and the side end of the distance measuring sensor is electrically connected with the intelligent camera.

Preferably, a power supply and a data processor are arranged in the driving box, and a motor is arranged at the side end of the rotating shaft.

Preferably, an aircraft driving disc is arranged in the aircraft body, and a power supply and a data processor are arranged in the aircraft driving disc.

(III) advantageous effects

The utility model provides a many rotors patrol and examine aircraft. The method has the following beneficial effects:

(1) The utility model discloses when descending, accessible strutting arrangement's arc makes the aircraft can slide at the low latitude and subaerial, and the impulsive force of side when the swash plate buffering aircraft of through the buffer block side descends, wherein be equipped with square groove in the buffer block, square groove in the buffer block can transversely pass through the air at the in-process of aircraft whereabouts, the air pressure that produces like this can make the landing of the better auxiliary aircraft of strutting arrangement ability, make the descending of aircraft more steady, the aforesaid also can solve simultaneously and patrol and examine the problem that the aircraft landing effect is not good.

(2) The utility model discloses, the scenery of aircraft body below is tourd through first camera device during use, first camera device accessible carousel and pivot are rotated, can use the height of first electric putter slip adjustment drive case simultaneously, the high definition camera that sets up like this in the adjustable drive incasement, night vision camera and signal receiver's height and angle, it is more to make high definition camera and night vision camera shoot the scope, but also make signal receiver multi-angle received signal, make signal receiver can better received signal, simultaneously the aforesaid can solve and patrol and examine the aircraft when patrolling and examining, the rigidity of camera, there is the problem of certain use limitation, the utility model discloses still be equipped with second camera device, second camera device is on the top of aircraft body, mainly shoots sky direction, can shoot and respond to flying bird etc. through range finding sensor and intelligent camera, when can avoiding the flight of aircraft body like this way, because of flying bird striking or mistake bump the aircraft, lead to the problem that the aircraft damaged.

Drawings

FIG. 1 is a schematic view of the whole of the present invention;

FIG. 2 is a side perspective view of the present invention;

FIG. 3 is a schematic view of the overall flying state of the present invention;

FIG. 4 is a top perspective view of the whole body of the present invention;

fig. 5 is a schematic structural diagram of the first camera device of the present invention.

Fig. 6 is a schematic side view of the supporting device of the present invention.

In the figure, 1, an aircraft body; 11. an aircraft drive disk; 2. a first image pickup device; 21. a high definition camera; 22. a night vision camera; 23. a drive box; 24. a signal receiver; 25. a rotating shaft; 26. a first electric push rod; 27. a first slider; 3. a rotor device; 31. a rotor; 32. a rotor head; 33. a support arm; 34. a seal ring; 4. a second image pickup device; 41. a ranging sensor; 42. an intelligent camera; 5. a support device; 51. a first connection block; 511. a second slider; 512. a second electric push rod; 513. an arc-shaped plate; 514. an arc-shaped groove; 52. a second connecting block; 521. a third electric push rod; 522. a third slider; 523. a buffer block; 524. a sloping plate; 525. a square groove.

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.

Referring to fig. 1-6, an embodiment of the present invention provides a technical solution: a multi-rotor patrol inspection aircraft comprises an aircraft body 1, a first camera device 2, a rotor device 3, a second camera device 4 and a supporting device 5, wherein the rotor devices 3 are arranged at the side end of the aircraft body 1 at equal intervals, the top end of the aircraft body 1 is electrically connected with the second camera device 4, the bottom end of the aircraft body 1 is movably connected with the first camera device 2 through a turntable, the bottom end of the aircraft body 1 is slidably connected with the supporting device 5, the aircraft body 1 can shoot and patrol a scenery below the aircraft body 1 through the first camera device 2, the rotor device 3 enables the aircraft body 1 to fly, the second camera device 4 mainly shoots the sky direction, the problem that the aircraft is damaged due to collision or mistaken collision of flying birds with the aircraft during flying of the aircraft body is avoided, and the supporting device 5 plays a role in auxiliary supporting in the descending process of the aircraft body 1;

the rotor wing device 3 comprises a rotor wing 31, a rotor wing head 32, a supporting arm 33 and a sealing ring 34, the side end of the supporting arm 33 is movably connected with the rotor wing 31 through the rotor wing head 32, the rotor wing 31 is distributed at equal intervals, the sealing ring 34 is arranged at the other side end of the supporting arm 33, the rotor wing device 3 supports the rotor wing 31 and the rotor wing head 32 through the supporting arm 33, the rotor wing head 32 can drive the rotor wing 31 to rotate, the electric drive of the rotor wing head 32 comes from a power supply and a data processor which are arranged in the driving disc 11, and the sealing ring 34 plays a role in protecting the joint of the supporting arm 33;

the first camera device 2 comprises a high-definition camera 21, a night vision camera 22, a driving box 23, a signal receiver 24 and a first electric push rod 26, the driving box 23 is arranged in the first camera device 2, the driving box 23 is electrically connected with the high-definition camera 21, the night vision camera 22 and the signal receiver 24 on the surface, a slide rail is arranged at the side end of the driving box 23, the side end of the driving box 23 is slidably connected with a first slider 27 and the first electric push rod 26, the side end of the first electric push rod 26 is movably connected with a rotating shaft 25 through a coupler, the first camera device 2 can shoot and patrol the day and night respectively through the high-definition camera 21 and the night vision camera 22, the application range is wide, a power source and a data processor are arranged in the driving box 23 and can provide data control and electric support, the signal receiver 24 can receive signals and transmit the signals to the data processor for processing, the driving box 23 is pushed through the first electric push rod 26, so that the first camera device 2 can slide up and down to adjust the height, the first slider 27 slides while sliding, and the first slider 27 plays a role in assisting the sliding of the first electric push rod 26.

The supporting device 5 comprises a first connecting block 51 and a second connecting block 52, the first connecting block 51 is symmetrically arranged at the side end of the supporting device 5, the second connecting block 52 is arranged at the other side end of the supporting device 5, a sliding rail is arranged in the first connecting block 51, a second sliding block 511 is slidably connected in the first connecting block 51, the second electric push rod 512 is slidably connected at the side end of the first connecting block 51, the second sliding block 511 and the second electric push rod 512 are slidably connected with an arc-shaped plate 513, an arc-shaped groove 514 is arranged in the arc-shaped plate 513, the supporting device 5 assists the aircraft body 1 to land through the first connecting block 51 and the second connecting block 52, wherein the first connecting block 51 vertically slides through the second electric push rod 512 to adjust the height, the second electric push rod 512 slides while driving the second sliding block 511 to slide, the second sliding block 511 plays a role in assisting the second electric push rod 512, and when the first connecting block 51 slides to adjust the height, the aircraft body 1 to land through the arc-shaped plate, the aircraft body 1 can land through the arc-shaped plate 513, the aircraft body can slowly slide in the aircraft body, and the aircraft body can buffer the impact force more stably in the aircraft body 1.

The aircraft is characterized in that a sliding rail is arranged in the second connecting block 52, a third sliding block 522 is slidably connected in the second connecting block 52, the side end of the second connecting block 52 is slidably connected with a third electric push rod 521, the side ends of the third electric push rod 521 and the third sliding block 522 are slidably connected with a buffer block 523, the side end of the buffer block 523 is fixedly connected with an inclined plate 524, a square groove 525 is arranged in the buffer block 523, the second connecting block 52 can slide up and down through the third electric push rod 521 to adjust the height, the third electric push rod 52 slides while driving the third sliding block 522 to slide, the third sliding block 522 plays a role in assisting the sliding of the third electric push rod 521, when the aircraft body 1 descends, the supporting device 5 can simultaneously slide and shovel the ground through the inclined plate 524 of the buffer block 523 to buffer the speed of the aircraft body 1, air can transversely pass through the air in the square groove 525 in the buffer block 523, and the generated air pressure enables the supporting device to better assist the aircraft to descend, so that the aircraft descends more stably.

Second camera device 4 includes range sensor 41 and intelligent camera 42, range sensor 41 side electric connection intelligent camera 42, but second camera device 4 passes through range sensor 41 sensing aerial flightings or shelter from the thing to handle in transmitting data to the data processor in the aircraft driving-disc 11, then can send data to operator's operating equipment through signal receiver 24 in, but the flightings in intelligent detection sky in the intelligent camera 42 and shoot.

The driving box 23 is internally provided with a power supply and a data processor, the side end of the rotating shaft 25 is provided with a motor, the driving box 23 provides data control and processing through the data processor, the power supply provides electric power, and the motor can control the rotating shaft 25 to drive the rotating disc to rotate and enable the first camera device 2 to rotate.

The aircraft driving device is characterized in that an aircraft driving disc 11 is arranged in the aircraft body 1, a power supply and a data processor are arranged in the aircraft driving disc 11, and the aircraft body 1 provides overall power supply driving and data control through the power supply and the data processor of the driving disc 11.

It should be noted that: the utility model discloses the scenery that aircraft body 1 can shoot and patrol the aircraft body 1 below through first camera device 2, first camera device 2 can shoot and patrol daytime and night respectively through high definition camera 21 and night vision camera 22, signal receiver 24 can accept the signal, and with signal transmission to the data processor processing, promote drive box 23 through first electric putter 26, make first camera device 2 can slide adjustment height from top to bottom, drive the carousel rotation and make first camera device 2 rotatable through motor controllable pivot 25, rotor device 3 makes aircraft body 1 can fly, rotor device 3 supports rotor 31 and rotor head 32 through support arm 33, rotor head 32 can drive rotor 31 to rotate, second camera device 4 mainly shoots the direction, when avoiding aircraft body flight, because flying bird strikes or miss the aircraft, the problem that leads to aircraft damage, through range finding sensor 41 can sense aerial flier or shelter when second camera device 4 uses, the landing object that can the detection sky of intelligence in camera 42 and shoot, support device 5 plays the effect of aircraft body 1 in the sky, support device 5 can make the aircraft body support the effect of aircraft body 1 through the buffer arc block 52 that the first connection block 5 and the buffer arc block 52 that aircraft body 5 can make the aircraft body pass through the buffer arc block 52 that slides and the buffer block 52 that the aircraft body 52 that the arc block 5 can be connected when the aircraft body slides slowly, the aircraft body passes through the buffer arc block 52, make the aircraft body 5 and the buffer arc block that the aircraft body can be connected in the aircraft body 5 that the aircraft body can be connected with the aircraft body in the arc-sliding and the aircraft body can be more slowly through the arc-shaped slide more the arc-shaped sliding process of the aircraft body, the buffer arc-shaped sliding, the square groove 525 in the buffer block 523 can transversely pass through air, and the air pressure generated in the way enables the supporting device to better assist the landing of the aircraft, so that the landing of the aircraft is more stable.

The basic principles and the main features of the invention and the advantages of the invention have been shown and described above, it will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, but that the invention may be embodied in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.

Claims (6)

1. The utility model provides an aircraft is patrolled and examined to many rotors which characterized in that: the aircraft comprises an aircraft body (1), first camera devices (2), rotor wing devices (3), second camera devices (4) and a supporting device (5), wherein the rotor wing devices (3) are arranged at the side end of the aircraft body (1) at equal intervals, the top end of the aircraft body (1) is electrically connected with the second camera devices (4), the bottom end of the aircraft body (1) is movably connected with the first camera devices (2) through a turntable, and the bottom end of the aircraft body (1) is connected with the supporting device (5) in a sliding manner;

the rotor wing device (3) comprises a rotor wing (31), a rotor wing head (32), a supporting arm (33) and a sealing ring (34), wherein the side end of the supporting arm (33) is movably connected with the rotor wing (31) through the rotor wing head (32), the rotor wing (31) is distributed at equal intervals, and the sealing ring (34) is arranged at the other side end of the supporting arm (33);

the first camera device (2) comprises a high-definition camera (21), a night vision camera (22), a driving box (23), a signal receiver (24) and a first electric push rod (26), the driving box (23) is arranged in the first camera device (2), the driving box (23) is electrically connected with the high-definition camera (21), the night vision camera (22) and the signal receiver (24) on the surface, a sliding rail is arranged at the side end of the driving box (23), the side end of the driving box (23) is slidably connected with a first sliding block (27) and the first electric push rod (26), and the side end of the first electric push rod (26) is movably connected with a rotating shaft (25) through a shaft coupling.

2. The multi-rotor inspection vehicle according to claim 1, wherein: support arrangement (5) include first connecting block (51) and second connecting block (52), support arrangement (5) side symmetry is equipped with first connecting block (51), support arrangement (5) another side is equipped with second connecting block (52), be equipped with the slide rail in first connecting block (51), sliding connection second slider (511) in first connecting block (51), first connecting block (51) side sliding connection second electric putter (512), second slider (511) and second electric putter (512) side sliding connection arc (513), be equipped with arc recess (514) in arc (513).

3. The multi-rotor inspection vehicle according to claim 2, wherein: be equipped with the slide rail in the second connecting block (52), sliding connection third slider (522) in the second connecting block (52), second connecting block (52) side sliding connection third electric putter (521), third electric putter (521) and third slider (522) side sliding connection buffer block (523), buffer block (523) side fixed connection swash plate (524), be equipped with square groove (525) in buffer block (523).

4. The multi-rotor inspection vehicle according to claim 1, wherein: the second camera device (4) comprises a distance measuring sensor (41) and an intelligent camera (42), and the side end of the distance measuring sensor (41) is electrically connected with the intelligent camera (42).

5. The multi-rotor inspection vehicle according to claim 1, wherein: a power supply and a data processor are arranged in the driving box (23), and a motor is arranged at the side end of the rotating shaft (25).

6. The multi-rotor inspection vehicle according to claim 1, wherein: an aircraft driving disc (11) is arranged in the aircraft body (1), and a power supply and a data processor are arranged in the aircraft driving disc (11).

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