CN211642593U

CN211642593U - Novel aerial survey aircraft

Info

Publication number: CN211642593U
Application number: CN202020187893.6U
Authority: CN
Inventors: 郑耀辉
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-02-19
Filing date: 2020-02-19
Publication date: 2020-10-09
Anticipated expiration: 2030-02-19

Abstract

The utility model discloses a novel aerial survey uses aircraft, including landing leg, pillar, fixed block, slider, box, battery, controller and signal receiver, the top of landing leg is provided with the pillar, pillar bottom and landing leg top fixed connection, the bottom of fixed block and the top fixed connection of pillar, the left front side, left rear side, right front side and the right rear side of the bottom of box all are provided with the recess, and the inboard of the bottom of recess is provided with the baffle, and the inboard of recess is provided with the slider above the baffle, slider and recess sliding connection, the top of fixed block runs through the baffle and extends to in the recess and is connected with the bottom fixed connection of slider, the inboard of recess is provided with compression spring above the slider; the utility model discloses a when the aircraft falls to the ground, compression spring plays the effect of buffering to the landing leg, protects the landing leg, prolongs its life, through the environment around the inductor response, has improved the security of the flight of aircraft.

Description

Novel aerial survey aircraft

Technical Field

The utility model particularly relates to an aircraft technical field for aerial survey especially relates to a novel aircraft for aerial survey.

Background

The aerial survey aircraft is powerful supplement of the traditional aerial photogrammetry means, has the characteristics of flexibility, high efficiency, rapidness, fineness, accuracy, low operation cost, wide application range, short production period and the like, the method has obvious advantages in the aspect of fast acquisition of high-resolution images in small areas and areas with difficult flight, and with the development of aircraft and digital camera technologies, the digital aerial photography technology based on the aircraft platform has shown unique advantages, the combination of aerial photogrammetry makes the 'aircraft digital low altitude remote sensing' become a brand-new development direction in the field of aerial remote sensing, the aircraft aerial photography can be widely applied to aspects such as national major engineering construction, disaster emergency and treatment, territorial monitoring, resource development, new rural areas and small town construction, and the like, and has wide prospects in aspects such as basic mapping, land resource investigation and monitoring, dynamic monitoring of land utilization, digital city construction and acquisition of emergency relief mapping data.

The landing leg impact to the aircraft is great when current aerial survey aircraft falls to the ground, easy damage, can lean on gravity to fall to the ground when the aircraft breaks down when flight, makes the aircraft break down, and unable work makes its life reduce.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the defects existing in the prior art and providing a novel aerial survey aircraft.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

a novel aerial survey aircraft comprises supporting legs, supporting columns, fixing blocks, sliders, a box body, a storage battery, a controller and a signal receiver, wherein the supporting columns are arranged at the top ends of the supporting legs, the bottom ends of the supporting columns are fixedly connected with the top ends of the supporting legs, the bottom ends of the fixing blocks are fixedly connected with the top ends of the supporting columns, grooves are formed in the left front side, the left rear side, the right front side and the right rear side of the bottom end of the box body respectively, a baffle is arranged on the inner side of the bottom end of each groove, the sliders are arranged above the baffle on the inner sides of the grooves, the sliders are slidably connected with the grooves, the top ends of the fixing blocks penetrate through the baffle and extend into the grooves to be fixedly connected with the bottom ends of the sliders, compression springs are arranged above the sliders on the inner sides of the grooves, the top ends of the compression springs abut against the, the top of box is provided with the parachute device that runs through to the box inboard, and the left front side at the top of box, left rear side, right front side and right rear side all are provided with the extension board, and the bottom of extension board is provided with driving motor, and driving motor's output runs through the one end that the extension board extends to the top of extension board and sets up the rotor, and the left side on the inside top of box is provided with the controller, and the inside top right side of box is provided with signal receiver, and the bottom side front end of box is provided with the camera.

Furthermore, the side ends of the supporting legs are in an upward arc shape.

Furthermore, the top of box is provided with solar panel around the parachute device, solar panel and battery electric connection.

Furthermore, one end of the support plate, which is far away from the box body, is provided with a sensor, and the sensor is electrically connected with the controller.

Furthermore, a balance block is arranged in the box body.

Furthermore, a position display lamp is arranged on the box body.

Furthermore, waterproof layers are coated on the box body, the driving motor and the rotor wing.

The utility model has the advantages that:

1. when the aircraft lands, the landing legs are buffered through the compression springs, the landing legs are protected, and the service life of the landing legs is prolonged.

2. Through inductor response surrounding environment, when the aircraft will hit the building, the inductor gives the controller with the signal transmission who senses, and the controller control rotor is rotatory, makes the aircraft keep away from the building, has improved the security of the flight of aircraft.

3. The storage battery is charged through the solar panel, so that the electric energy required by the aircraft in the flight process is sufficient, and the environment is saved.

4. When the aircraft breaks down and can not fly in the flight process, the aircraft can fall freely, and when the aircraft falls to a certain speed, the parachute device can be started, pops out the parachute from the top end of the box body, so that the descending speed of the aircraft is reduced, the aircraft is protected from being broken, and the flying safety of the aircraft is improved.

Drawings

Fig. 1 is a schematic structural view, partially in section, of a novel aerial survey aircraft according to the present invention;

fig. 2 is a schematic structural diagram of a novel aerial survey aircraft provided by the present invention;

fig. 3 is a schematic structural diagram of a top view of the novel aerial survey aircraft provided by the invention;

fig. 4 is a schematic diagram of the landing leg and the box body of the novel aerial survey aircraft according to the present invention.

In the figure: the system comprises 1-supporting legs, 2-supporting columns, 3-fixing blocks, 4-sliding blocks, 5-box bodies, 6-storage batteries, 7-controllers, 8-signal receivers, 9-grooves, 10-baffles, 11-compression springs, 12-parachute devices, 13-supporting plates, 14-driving motors, 15-rotary wings, 16-cameras, 17-solar panels, 18-inductors, 19-balance blocks, 20-position display lamps and 21-waterproof layers.

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.

In the description of this patent, it is noted that unless otherwise specifically stated or limited, the terms "mounted," "connected," and "disposed" are to be construed broadly and can include, for example, fixedly connected, disposed, detachably connected, disposed, or integrally connected and disposed. The specific meaning of the above terms in this patent may be understood by those of ordinary skill in the art as appropriate.

Referring to fig. 1-4, a novel aerial survey aircraft comprises a supporting leg 1, a supporting column 2, a fixed block 3, a sliding block 4, a box body 5, a storage battery 6, a controller 7 and a signal receiver 8, wherein the supporting column 2 is arranged at the top end of the supporting leg 1, the bottom end of the supporting column 2 is fixedly connected with the top end of the supporting leg 1, the bottom end of the fixed block 3 is fixedly connected with the top end of the supporting column 2, grooves 9 are respectively arranged at the left front side, the left rear side, the right front side and the right rear side of the bottom end of the box body 5, a baffle 10 is arranged at the inner side of the bottom end of each groove 9, the sliding block 4 is arranged above each baffle 10 at the inner side of each groove 9, each baffle 10 prevents the sliding block 4 from sliding out of each groove 9, the sliding block 4 is slidably connected with each groove 9, the top end of the fixed block 3 extends into each groove 9 to be, the top end of a compression spring 11 is tightly abutted with the top end of a groove 9, the bottom end of the compression spring 11 is tightly abutted with the top end of a sliding block 4, the compression spring 11 plays a role of buffering when an aircraft lands, a storage battery 6 is arranged at the bottom end of the inner side of a box body 5 and provides electric energy, a parachute device 12 penetrating through the box body 5 is arranged at the top end of the box body 5, support plates 13 are arranged on the left front side, the left rear side, the right front side and the right rear side of the top of the box body 5, a driving motor 14 is arranged at the bottom end of each support plate 13, a rotor 15 is arranged at one end, penetrating through the support plates 13, of the output end of the driving motor 14 and extending to the upper side of each support plate 13, the rotor 15 rotates to enable the aircraft to fly stably, a controller 7 is arranged on the left side of the inner top end of the box body 5, a signal receiver 8 is, and aerial surveying the surrounding environment.

It should be further noted that the side ends of the supporting legs 1 are upward arc-shaped, so as to prevent the aircraft from side turning over and damaging the aircraft when landing, the top end of the box body 5 is provided with the solar panels 17 around the parachute device 12, the solar panels 17 are electrically connected with the storage battery 6, the solar panels 17 provide electric energy for the storage battery 6, one end of the supporting plate 13, which is far away from the box body 5, is provided with the sensor 18, the sensor 18 is electrically connected with the controller 7, the surrounding environment is met through the sensor 18, when the aircraft is about to collide with a building, the sensor 18 transmits the sensed signal to the controller 7, the controller 7 controls the rotor 15 to rotate, so that the aircraft is far away from the building, the box body 5 is internally provided with the balance weight 19, so as to ensure that the center of gravity of the aircraft is on the central axis, the box body 5 is provided, the box body 5, the driving motor 14 and the rotor wing 15 are coated with waterproof layers 21, so that water is prevented from entering and damaging equipment of the aircraft.

The working principle of the embodiment is as follows: during the use, through the operation of remote control driving motor 14, driving motor 14 drives rotor 15 rotatory, and rotor 15 is rotatory to drive the aircraft flight to control the height, direction and the speed of aircraft, when flying to the assigned position, camera 16 carries out the aerial survey around on the control box 5, and camera 16 passes to the display screen of control to the information of aerial survey on.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. The utility model provides a novel aircraft for aerial survey which characterized in that: comprises supporting legs (1), supporting columns (2), fixing blocks (3), sliding blocks (4), a box body (5), a storage battery (6), a controller (7) and a signal receiver (8), wherein the supporting columns (2) are arranged at the top ends of the supporting legs (1), the bottom ends of the supporting columns (2) are fixedly connected with the top ends of the supporting legs (1), the bottom ends of the fixing blocks (3) are fixedly connected with the top ends of the supporting columns (2), grooves (9) are formed in the left front side, the left rear side, the right front side and the right rear side of the bottom end of the box body (5), a baffle (10) is arranged on the inner side of the bottom end of each groove (9), the sliding blocks (4) are arranged on the inner side of each groove (9) above the corresponding baffle (10), the sliding blocks (4) are slidably connected with the grooves (9), the top ends of the fixing blocks (3) penetrate through the baffle (10) and extend into, a compression spring (11) is arranged on the inner side of the groove (9) above the sliding block (4), the top end of the compression spring (11) is tightly abutted to the top end of the groove (9), the bottom end of the compression spring (11) is tightly abutted to the top end of the sliding block (4), a storage battery (6) is arranged at the bottom end of the inner side of the box body (5), a parachute device (12) penetrating through the inner side of the box body (5) is arranged at the top end of the box body (5), supporting plates (13) are arranged on the left front side, the left rear side, the right front side and the right rear side of the top of the box body (5), a driving motor (14) is arranged at the bottom end of each supporting plate (13), a rotor wing (15) is arranged at one end, extending to the upper side of each supporting plate (13), of the output end of each driving motor (14) penetrates through each supporting plate (13), a controller (7) is arranged on the left, the front end of the bottom side of the box body (5) is provided with a camera (16).

2. The novel aerial survey aircraft as claimed in claim 1, wherein: the side ends of the supporting legs (1) are in an upward arc shape.

3. The novel aerial survey aircraft as claimed in claim 1, wherein: the top of box (5) is provided with solar panel (17) around parachute device (12), solar panel (17) and battery (6) electric connection.

4. The novel aerial survey aircraft as claimed in claim 1, wherein: and one end of the support plate (13) far away from the box body (5) is provided with an inductor (18), and the inductor (18) is electrically connected with the controller (7).

5. The novel aerial survey aircraft as claimed in claim 1, wherein: a balance block (19) is arranged in the box body (5).

6. The novel aerial survey aircraft as claimed in claim 1, wherein: and a position display lamp (20) is arranged on the box body (5).

7. The novel aerial survey aircraft as claimed in claim 1, wherein: waterproof layers (21) are coated on the box body (5), the driving motor (14) and the rotor wing (15).