CN209889084U

CN209889084U - Fuselage hypoplastron with prevent falling structure

Info

Publication number: CN209889084U
Application number: CN201920623943.8U
Authority: CN
Inventors: 张雷
Original assignee: Jiangxi Zhongyitu Aviation Technology Co Ltd
Current assignee: Jiangxi Zhongyitu Aviation Technology Co Ltd
Priority date: 2019-05-03
Filing date: 2019-05-03
Publication date: 2020-01-03
Anticipated expiration: 2029-05-03

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a fuselage hypoplastron with anti-falling structure, which comprises a fuselage, the central position around the fuselage is provided with a concave hole, the lower part of the fuselage is provided with an anti-falling mechanism which comprises a box body, the upper surface of the box body is provided with an inner cavity, the inner wall around the inner cavity is connected with a connecting plate, the connecting plate is provided with a damping spring, the fuselage hypoplastron with anti-falling structure enables the staff to be in direct collision with the ground after the misoperation through the arranged anti-falling mechanism, the bottom of the unmanned aerial vehicle can not directly collide with the ground, the fuselage hypoplastron of the unmanned aerial vehicle is protected, the phenomenon that the fuselage hypoplastron of the unmanned aerial vehicle is damaged because the fuselage hypoplastron of the unmanned aerial vehicle directly collides with the ground after the past misoperation is avoided, the anti-falling mechanism arranged, the practicability is enhanced, and the market competitiveness is improved.

Description

Fuselage hypoplastron with prevent falling structure

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is a fuselage hypoplastron with prevent falling structure.

Background

The unmanned plane is an unmanned plane which is operated by utilizing a radio remote control device and a self-contained program control device, or is completely or intermittently and autonomously operated by an on-board computer, compared with the unmanned plane, the unmanned plane is more suitable for tasks which are too dull, dirty or dangerous, and in the civil aspect, the unmanned plane + industrial application is really just needed by the unmanned plane; at present at the aerial photography, agriculture, plant protection, miniature autodyne, express delivery transportation, disaster relief, observe wild animal, control infectious disease, survey and drawing, the news report, electric power is patrolled and examined, the relief of disaster, the film and television is shot, make the application in fields such as romantic, great expansion unmanned aerial vehicle's own usage, because unmanned aerial vehicle is through radio remote control, need higher horizontal operation when unmanned aerial vehicle whereabouts, the staff often can appear not controlling and lead to unmanned aerial vehicle's bottom plate and ground to take place stronger collision, make unmanned aerial vehicle's fuselage hypoplastron cause the damage, we provide one kind and have the fuselage hypoplastron of preventing falling the structure in view of this.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a fuselage hypoplastron with prevent falling the structure to the error of controlling that proposes in solving above-mentioned background art makes unmanned aerial vehicle's fuselage hypoplastron cause the damage scheduling problem.

In order to achieve the above object, the utility model provides a following technical scheme:

the utility model provides a fuselage hypoplastron with prevent falling structure, includes the organism, the shrinkage pool has all been seted up to the outer central point all around of organism puts, the below of organism is equipped with prevents falling the mechanism, prevent falling the mechanism and include the box body, the inner chamber has been seted up to the upper surface of box body, the inner chamber all is connected with the connecting plate all around, be equipped with damping spring on the connecting plate.

Preferably, the bottom surface of the box body is provided with a plurality of round holes, and the round holes penetrate through the box body and are communicated with the inner cavity.

Preferably, the connecting plate is matched with the concave hole in shape and size, and the connecting plate and the concave hole are in sliding connection.

Preferably, one end of the damping spring is welded and fixed with the connecting plate, and the other end of the damping spring is welded and fixed with the concave hole.

Preferably, the box body and the connecting plate are both made of ABS plastic.

Preferably, the damping spring is made of high-carbon steel.

Preferably, the connecting plate and the box body are fixedly bonded through glue.

Compared with the prior art, the beneficial effects of the utility model are that: this fuselage hypoplastron with prevent falling structure makes the staff after misoperation through what set up prevents falling the mechanism, unmanned aerial vehicle's bottom can not directly take place direct collision with ground, unmanned aerial vehicle's fuselage hypoplastron has been protected, after misoperation in the past has been avoided, unmanned aerial vehicle's fuselage hypoplastron is direct to collide with ground and cause unmanned aerial vehicle's fuselage hypoplastron to take place the phenomenon of damage, the round hole that sets up through preventing falling the mechanism makes what set up prevent falling the mechanism and also can use with rainy weather, the practicality is strengthened, market competitiveness is improved.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention;

fig. 2 is a schematic view of the structure of the body of the present invention;

fig. 3 is a schematic structural view of the anti-falling mechanism of the present invention.

In the figure: 1. a body; 11. concave holes; 2. an anti-falling mechanism; 21. a box body; 211. an inner cavity; 212. a circular hole; 22. a connecting plate; 23. a shock absorbing spring.

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.

In the description of the present invention, it is to be understood that the terms "center", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the equipment or components referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.

In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.

Referring to fig. 1-3, the present invention provides a technical solution:

the utility model provides a fuselage hypoplastron with prevent falling structure, includes organism 1, and shrinkage pool 11 has all been seted up to organism 1's outer central point all around puts, and the below of organism 1 is equipped with prevents falling mechanism 2, prevents falling mechanism 2 and includes box body 21, and inner chamber 211 has been seted up to the upper surface of box body 21, and inner chamber 211's inner wall all around all is connected with connecting plate 22, is equipped with damping spring 23 on the connecting plate 22.

Specifically, a plurality of round holes 212 have been seted up to the bottom surface of box body 21, and round hole 212 passes box body 21 and is linked together with inner chamber 211, and when rainy weather, unmanned aerial vehicle is at external during operation, and the rainwater can directly flow from round hole 212 after getting into box body 21, has avoided the weight that unmanned aerial vehicle bore, has reduced the electric energy of unmanned aerial vehicle consumption.

In this embodiment, the shape and size of the connecting plate 22 and the concave hole 11 are matched, and the connecting plate 22 and the concave hole 11 are connected in a sliding manner, so that the connecting plate 22 can move up and down in the concave hole 11, and the box body 21 can move up and down on the machine body 1.

In addition, damping spring 23's one end and connecting plate 22 welded fastening, damping spring 23's the other end and shrinkage pool 11 welded fastening, guaranteed damping spring 23 stability in shrinkage pool 11, when the staff carelessly operate when controlling unmanned aerial vehicle whereabouts when mistaking, at this moment box body 21 just can directly fall subaerial, under damping spring 23's effect, make organism 1's hypoplastron can not produce powerful collision with ground, make organism 1's hypoplastron can obtain the protection.

In this embodiment, box body 21 and connecting plate 22 all adopt ABS plastics to make, and damping spring 23 adopts the high carbon steel material to make, has fully alleviateed the whole weight of preventing falling mechanism 2, has avoided unmanned aerial vehicle to consume too much electric energy.

In addition, the connecting plate 22 is fixed to the box body 21 through glue bonding, so that the stability between the connecting plate 22 and the box body 21 is ensured.

The fuselage hypoplastron with prevent falling the structure of this embodiment is when using, after unmanned aerial vehicle work is accomplished, regardless of whether misoperation appears in the staff, at this moment box body 21 at first with ground contact, under damping spring 23's effect, and can absorb some kinetic energy, unmanned aerial vehicle's hypoplastron can not take place violent collision with ground to unmanned aerial vehicle's hypoplastron has been protected.

The foregoing shows and describes the general principles, essential features, and advantages of the invention. It should be understood by those skilled in the art that the present invention is not limited by the above embodiments, and the description in the above embodiments and the description is only preferred examples of the present invention, and is not intended to limit the present invention, and that the present invention can have various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications all fall into the scope of the claimed invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. The utility model provides a fuselage hypoplastron with prevent falling structure, includes organism (1), its characterized in that: shrinkage pool (11) have all been seted up to outer central point all around of organism (1), the below of organism (1) is equipped with prevents falling mechanism (2), prevent falling mechanism (2) including box body (21), inner chamber (211) have been seted up to the upper surface of box body (21), the inner wall all around of inner chamber (211) all is connected with connecting plate (22), be equipped with damping spring (23) on connecting plate (22).

2. The lower fuselage panel with an anti-drop structure according to claim 1, characterized in that: the bottom surface of the box body (21) is provided with a plurality of round holes (212), and the round holes (212) penetrate through the box body (21) and are communicated with the inner cavity (211).

3. The lower fuselage panel with an anti-drop structure according to claim 1, characterized in that: the connecting plate (22) is matched with the concave hole (11) in shape and size and is in sliding connection with the concave hole.

4. The lower fuselage panel with an anti-drop structure according to claim 1, characterized in that: one end of the damping spring (23) is fixedly welded with the connecting plate (22), and the other end of the damping spring (23) is fixedly welded with the concave hole (11).

5. The lower fuselage panel with an anti-drop structure according to claim 1, characterized in that: the box body (21) and the connecting plate (22) are both made of ABS plastic.

6. The lower fuselage panel with an anti-drop structure according to claim 1, characterized in that: the damping spring (23) is made of high-carbon steel.

7. The lower fuselage panel with an anti-drop structure according to claim 1, characterized in that: the connecting plate (22) and the box body (21) are fixedly bonded through glue.