CN216834283U

CN216834283U - Aircraft anti-resistance structure for aerial photography measurement

Info

Publication number: CN216834283U
Application number: CN202122931392.1U
Authority: CN
Inventors: 郭富翔; 罗忠成; 李国峰
Original assignee: Yunnan Runya Engineering Technology Consulting Co ltd
Current assignee: Yunnan Runya Engineering Technology Consulting Co ltd
Priority date: 2021-11-26
Filing date: 2021-11-26
Publication date: 2022-06-28
Anticipated expiration: 2031-11-26

Abstract

The utility model relates to the field of aerial photography measuring equipment, in particular to an aircraft anti-resistance structure for aerial photography measurement. The aircraft anti-resistance structure for aerial photography measurement can resist resistance flight, effectively improves the stability of the aircraft during flight, and brings better use prospect.

Description

Aircraft anti-resistance structure for aerial photography measurement

Technical Field

The utility model relates to the field of aerial photography measuring equipment, in particular to an aircraft anti-resistance structure for aerial photography measurement.

Background

Engineering survey has vital function in the aspect of the control of engineering quality, need leading condition measurement, accurate unwrapping wire proof before each link of construction begins, the in-process needs real-time supervision, need check and acceptance retest after the completion, in the whole process of construction, accomplish measuring accuracy and full coverage according to the standard requirement, can eliminate construction error's leaving behind and accumulation, avoid serious quality problems and major economic loss, in time master construction information comprehensively simultaneously, create the condition for high-efficient dispatch and management.

Chinese patent discloses an unmanned aerial vehicle for measurement (grant No. CN 212890912U), and this patent technology can accomplish tasks such as various geodetic survey and drawing, professional survey and drawing or engineering survey, and application scope is big, the operation precision is high, but, the device is stable inadequately when using, can not realize the anti-wind resistance when using to stability when the device that takes photo by plane influences the flight, influences the accuracy of measurement, thereby comparatively inconvenient. Accordingly, those skilled in the art have provided an anti-drag structure for an aircraft for aerial survey that solves the problems set forth in the background above.

Disclosure of Invention

The present invention is directed to an anti-drag structure for an aerial vehicle for aerial survey, which solves the above problems of the background art.

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

the utility model provides an anti resistance structure of aircraft for take photo by plane measuring, includes the aircraft main part, department is provided with the camera in the middle of the front side of aircraft main part, department is provided with the gravity box in the middle of the bottom of aircraft main part, the bottom of aircraft main part is close to the position department of gravity box and installs the fixing base, department fixed mounting has the arc hoop in the middle of the outside of fixing base, the department all rotates in the middle of the upper and lower both ends of arc hoop and is connected with first axis of rotation, two fixed mounting has the rolling circle between the inboard of first axis of rotation, the second axis of rotation, two are installed to the inside bilateral symmetry of rolling circle fixed mounting has the regulation seat between the second axis of rotation, four wind direction guide plates are installed to the top equidistance of adjusting the seat.

As a further scheme of the utility model: the four wind direction guide plates are internally provided with wind guide holes in a penetrating mode, waterproof paint is coated on the inner walls of the wind guide holes, and two streamline side wings are symmetrically arranged on two sides of the outer portions of the four wind direction guide plates.

As a still further scheme of the utility model: four equal fixed mounting in the middle of the back top of wind direction guide plate locates the connecting rod, and the shape of connecting rod is the tapered, the equal fixed mounting in top of connecting rod has the fin, and the wind direction guide plate passes through the connecting rod and is connected with the fin.

As a still further scheme of the utility model: the top of gravity center box is provided with the top cap, the bottom cover of top cap is equipped with the sealing washer, the department meshing is connected with the connecting seat in the middle of the top of top cap, the shape of connecting seat is circular.

As a still further scheme of the utility model: department is connected with the connection rope in the middle of the bottom of connecting seat, the bottom fixed mounting who connects the rope has the focus hammer, and connects the rope and install department in the middle of the top of focus hammer, the connecting seat is connected with the focus hammer through connecting the rope.

As a still further scheme of the utility model: the gravity center box is characterized in that a protective sleeve is fixedly mounted in the middle of the interior of the gravity center box, the connecting rope is arranged on the inner side of the protective sleeve, two connecting lugs are symmetrically mounted on two sides of the top cover, and connecting holes are formed in the middle of the interior of each connecting lug in a penetrating mode.

As a still further scheme of the utility model: four equal fixed mounting in corner in top of gravity center box have fixed fixture block, fixed slot has all been seted up to the inside position department that corresponds fixed fixture block of top cap, and the gravity center box passes through fixed fixture block and is connected with fixed slot block.

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

1. Install the fixing base in the bottom of aircraft main part, first axis of rotation through arc hoop department drives the rolling circle and carries out the horizontal angle rotation, angle rotation about the regulation seat is carried out in the drive of second axis of rotation, then can realize that the wind direction guide plate follows the change of wind direction and carry out the wind-guiding, the realization reduces the windage, the wind direction guide plate has set up the wind-guiding hole, the flight effect that can effectual improvement aircraft main part, fin through streamlined flank and the installation of connecting rod top, then can effectual improvement reduce the windage, improve aircraft main part flight measurement's precision, improve the device's practicality, the user of being convenient for uses, better for the conventional mode.

2. In order to improve the flight focus of aircraft main part, then can install the bottom at the connecting seat with connecting the rope, install the focus hammer on connecting the rope, then can improve the focus of aircraft main part flight through the focus hammer, avoid being blown the back focus unstability by wind and lead to the crash, effectual improvement the device's result of use, the user of being convenient for uses, better for traditional mode.

Drawings

FIG. 1 is a schematic view of an aircraft anti-drag structure for aerial survey;

FIG. 2 is a schematic view of a wind deflector in a resistive structure of an aircraft for aerial surveying;

fig. 3 is a schematic structural diagram of a center of gravity box in an aircraft anti-drag structure for aerial photography measurement.

In the figure: 1. an aircraft body; 2. a camera; 3. a gravity center box; 4. a fixed seat; 5. an arc-shaped hoop; 6. a first rotating shaft; 7. rotating the ring; 8. a second rotating shaft; 9. an adjusting seat; 10. a wind direction deflector; 11. a wind guide hole; 12. streamline flanks; 13. a connecting rod; 14. a tail wing; 15. a top cover; 16. a connecting seat; 17. connecting ropes; 18. a center of gravity hammer; 19. a protective sleeve; 20. and (5) connecting lugs.

Detailed Description

Referring to fig. 1 to 3, in the embodiment of the present invention, an aircraft anti-resistance structure for aerial photography measurement includes an aircraft main body 1, a camera 2 is disposed in the middle of the front side of the aircraft main body 1, a gravity center box 3 is disposed in the middle of the bottom of the aircraft main body 1, a fixed seat 4 is mounted at a position of the bottom of the aircraft main body 1 close to the gravity center box 3, an arc-shaped hoop 5 is fixedly mounted in the middle of the outside of the fixed seat 4, first rotating shafts 6 are rotatably connected to the middle of the upper and lower ends of the arc-shaped hoop 5, a rotating ring 7 is fixedly mounted between the inner sides of the two first rotating shafts 6, second rotating shafts 8 are symmetrically mounted on two sides of the inside of the rotating ring 7, an adjusting seat 9 is fixedly mounted between the two second rotating shafts 8, and four wind direction deflectors 10 are equidistantly mounted on the top of the adjusting seat 9.

In FIGS. 1-2: four wind direction guide plate 10's inside all runs through and is provided with wind-guiding hole 11, and waterproof paint has all been smeared to the inner wall in wind-guiding hole 11, two streamlined flanks 12 are installed to four wind direction guide plate 10's outside bilateral symmetry, install fixing base 4 in the bottom of aircraft main part 1, first axis of rotation 6 through arc hoop 5 department drives swivel becket 7 and carries out the horizontal angle rotation, it carries out the rotation of upper and lower angle to drive regulation seat 9 through second axis of rotation 8, then can realize that wind direction guide plate 10 follows the change of wind direction and carry out the wind-guiding, the realization reduces the windage.

In FIGS. 1-2: department's equal fixed mounting has connecting rod 13 in the middle of four wind direction guide plates 10's the back top, and connecting rod 13's shape is the tapered type, the equal fixed mounting in top of connecting rod 13 has fin 14, and wind direction guide plate 10 is connected with fin 14 through connecting rod 13, wind direction guide plate 10 has set up wind-guiding hole 11, can effectual improvement aircraft body 1's flight effect, fin 14 through installation of streamlined flank 12 and connecting rod 13 top, then can effectual improvement reduce the windage, improve aircraft body 1 flight measurement's precision.

In fig. 1 and 3: top cap 15 is provided with at the top of focus box 3, and the bottom cover of top cap 15 is equipped with the sealing washer, and department's meshing is connected with connecting seat 16 in the middle of the top of top cap 15, and connecting seat 16's shape is circular, improves through the sealing washer and is connected the leakproofness between top cap 15 and the focus box 3.

In fig. 3: connecting rope 17 is connected to the bottom centre department of connecting seat 16, and the bottom fixed mounting of connecting rope 17 has focus hammer 18, and connects rope 17 and install in the middle of the top of focus hammer 18, and connecting seat 16 is connected with focus hammer 18 through connecting rope 17, installs focus hammer 18 on connecting rope 17, then can improve the focus of aircraft main part 1 flight through focus hammer 18, avoids being blown the unstable crash that leads to of focus after.

In fig. 1 and 3: department fixed mounting has lag 19 in the middle of the inside of gravity center box 3, connects rope 17 to set up in the inboard of lag 19, and two engaging lugs 20 are installed to the top bilateral symmetry of top cap 15, and the department all runs through in the middle of the inside of engaging lug 20 and has seted up the connecting hole, improves the intensity of gravity center box 3 through lag 19.

In fig. 1 and 3: the equal fixed mounting in four corners in top of gravity center box 3 has fixed fixture block, and fixed slot has all been seted up to the inside position department that corresponds fixed fixture block of top cap 15, and gravity center box 3 is connected with fixed slot block through fixed fixture block, through fixed fixture block and fixed slot's cooperation, convenient dismantlement gravity center box 3, convenient to use personnel overhauls gravity center hammer 18.

The working principle of the utility model is as follows: the fixed seat 4 is arranged at the bottom of the aircraft body 1, the rotating ring 7 is driven by the first rotating shaft 6 at the arc hoop 5 to rotate horizontally, the adjusting seat 9 is driven by the second rotating shaft 8 to rotate up and down angularly, so that the wind direction guide plate 10 can guide wind along with the change of the wind direction, and the wind resistance is reduced, the wind direction guide plate 10 is provided with a wind guide hole 11, the flight effect of the aircraft body 1 can be effectively improved, the wind resistance can be effectively improved and reduced by the streamline side wing 12 and the tail wing 14 arranged at the top of the connecting rod 13, the precision of the flight measurement of the aircraft body 1 is improved, the practicability of the device is improved, the top cover 15 is arranged at the bottom of the aircraft body 1 by penetrating through the connecting lug 20 by an external connecting bolt, in order to improve the flight gravity center of the aircraft body 1, the connecting rope 17 can be arranged at the bottom of the connecting seat 16, install the focus hammer 18 on connecting rope 17, then can improve the focus that aircraft main part 1 flies through focus hammer 18, avoid being blown the unstable crash that leads to of focus after the wind, effectual improvement the device's result of use, convenient to use personnel use, and is comparatively practical.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the scope of the present invention, and the technical solutions and the utility model concepts of the present invention are equivalent to or changed within the scope of the present invention.

Claims

1. The utility model provides an aircraft anti-drag structure for take photo by plane measurement, includes aircraft main part (1), its characterized in that, department is provided with camera (2) in the middle of the front side of aircraft main part (1), department is provided with gravity core box (3) in the middle of the bottom of aircraft main part (1), the position department that the bottom of aircraft main part (1) is close to gravity core box (3) installs fixing base (4), the outside middle department fixed mounting of fixing base (4) has arc hoop (5), department all rotates in the middle of the upper and lower both ends of arc hoop (5) is connected with first axis of rotation (6), two fixed mounting has rotating ring (7) between the inboard of first axis of rotation (6), second axis of rotation (8) are installed to the inside bilateral symmetry of rotating ring (7), two fixed mounting has regulation seat (9) between second axis of rotation (8), four wind direction guide plates (10) are installed at the top of the adjusting seat (9) at equal intervals.

2. The aircraft drag resistance structure for aerial photography measurement according to claim 1, wherein air guiding holes (11) are formed through the insides of the four wind direction guiding plates (10), waterproof paint is coated on the inner walls of the air guiding holes (11), and two streamline side wings (12) are symmetrically arranged on the two sides of the outsides of the four wind direction guiding plates (10).

3. The aircraft drag resistance structure for aerial photography measurement according to claim 1, wherein the middle of the rear top of each of the four wind direction deflectors (10) is fixedly provided with a connecting rod (13), the connecting rods (13) are in a conical shape, the top of each of the connecting rods (13) is fixedly provided with a tail wing (14), and the wind direction deflectors (10) are connected with the tail wings (14) through the connecting rods (13).

4. The aircraft anti-drag structure for aerial photography measurement according to claim 1, wherein a top cover (15) is arranged at the top of the gravity center box (3), a sealing ring is sleeved at the bottom of the top cover (15), a connecting seat (16) is engaged and connected to the middle of the top cover (15), and the connecting seat (16) is circular.

5. The aircraft drag resistance structure for aerial photography measurement according to claim 4, wherein a connecting rope (17) is connected to the bottom middle of the connecting base (16), a gravity hammer (18) is fixedly installed at the bottom of the connecting rope (17), the connecting rope (17) is installed at the top middle of the gravity hammer (18), and the connecting base (16) is connected with the gravity hammer (18) through the connecting rope (17).

6. The aircraft resistance structure for aerial photography measurement according to claim 5, wherein a protective sleeve (19) is fixedly installed in the middle of the inside of the gravity center box (3), the connecting rope (17) is arranged on the inner side of the protective sleeve (19), two connecting lugs (20) are symmetrically installed on two sides of the top cover (15), and a connecting hole penetrates through the middle of the inside of each connecting lug (20).

7. The aircraft drag resistance structure for aerial photography measurement according to claim 4, wherein fixed clamping blocks are fixedly installed at four corners of the top of the gravity center box (3), fixed clamping grooves are formed in the top cover (15) at positions corresponding to the fixed clamping blocks, and the gravity center box (3) is connected with the fixed clamping grooves in a clamping mode through the fixed clamping blocks.