CN213473503U

CN213473503U - Effectual unmanned aerial vehicle of descending shock attenuation

Info

Publication number: CN213473503U
Application number: CN202022256721.2U
Authority: CN
Inventors: 蔡锦辉; 梁明峰
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-10-12
Filing date: 2020-10-12
Publication date: 2021-06-18
Anticipated expiration: 2030-10-12

Abstract

The utility model discloses an effectual unmanned aerial vehicle of descending shock attenuation, the reciprocating impact tunnel drilling machine comprises a machine body, the equal fixed mounting in both sides of fuselage has the wing, the top of wing is rotated and is connected with the dwang, the both sides of dwang are provided with the flabellum, the equal fixed mounting in four corners of fuselage bottom has the steady rest. The utility model discloses a set up the fuselage and be used for installing the wing and fixed, be used for installing and fixing the dwang through setting up the wing, be used for installing and fixing the flabellum through setting up the dwang, be used for installing and fixing the fuselage through setting up the steady rest, improve the stability of fuselage, make the descending that the fuselage can be steady, be used for installing and fixing damping spring through setting up the barrel, play limiting displacement to the telescopic link simultaneously, it is relatively poor to have solved current unmanned aerial vehicle descending shock attenuation effect simultaneously, cause the damage to it very easily when unmanned aerial vehicle descends, the problem that the user demand can not be satisfied.

Description

Effectual unmanned aerial vehicle of descending shock attenuation

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is an unmanned air vehicle that descending shock attenuation is effectual.

Background

Unmanned aerial vehicle is called unmanned aerial vehicle for short, and is an unmanned aerial vehicle operated by utilizing a radio remote control device and a self-contained program control device, or is completely or intermittently and autonomously operated by a vehicle-mounted computer, compared with the unmanned aerial vehicle, the unmanned aerial vehicle is more suitable for tasks too easy, dirty or dangerous, and can be divided into military use and civil use according to the application field, the unmanned aerial vehicle is divided into a reconnaissance plane and a target plane, and the civil use, unmanned aerial vehicle and industrial use are really just needed by the unmanned aerial vehicle; at present, in the application in fields such as aerial photography, agriculture, plant protection, miniature autodyne, express delivery transportation, disaster relief, observe wild animal, control infectious disease, survey and drawing, news report, electric power inspection, relief, movie & TV is shot, make romantic, great expansion unmanned aerial vehicle's use itself, developed country is also actively expanding the industry application and developing unmanned aerial vehicle technique, 9 months in 2018, world customs organization coordination system committee 62 th meeting decides, classify unmanned aerial vehicle as "the camera that can fly", unmanned aerial vehicle need slow down the shock attenuation to it when descending, current unmanned aerial vehicle descends the shock attenuation effect relatively poor, cause the damage to it very easily when unmanned aerial vehicle descends, can't satisfy the user demand.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an effectual unmanned aerial vehicle of descending shock attenuation possesses the effectual advantage of descending shock attenuation, and it is relatively poor to have solved current unmanned aerial vehicle descending shock attenuation effect, causes the damage to it very easily when unmanned aerial vehicle descends, has not satisfied the problem of user demand.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an unmanned aerial vehicle that landing shock attenuation is effectual, includes the fuselage, the equal fixed mounting in both sides of fuselage has the wing, the top of wing is rotated and is connected with the dwang, the both sides of dwang are provided with the flabellum, the equal fixed mounting in four corners of fuselage bottom has the steadying frame, the bottom fixed mounting of steadying frame has the barrel, barrel inner chamber's top fixed mounting has damping spring, damping spring's bottom has the telescopic link through fixed block fixed mounting, the top of telescopic link is located the inside of barrel, the spout has all been seted up to barrel inner chamber's both sides, the equal fixed mounting in top of telescopic link both sides has the slider, the slider is located the inside of spout and spout sliding.

Preferably, the top of the wing is fixedly provided with a mounting ring, and the mounting ring is sleeved on the surface of the rotating rod.

Preferably, the surface of the rotating rod is fixedly provided with a fixing ring, and the surface of the fixing ring is fixedly connected with the fan blade.

Preferably, the bottom fixed mounting of telescopic link has the support frame, the support frame includes landing leg, shock pad and slipmat, the bottom fixed mounting of telescopic link has the landing leg, the bottom fixed mounting of landing leg has the shock pad, the bottom fixed mounting of shock pad has the slipmat.

Preferably, the main material of shock pad is yielding rubber, the main material of slipmat is anti-skidding rubber.

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

1. the utility model discloses a set up the fuselage and be used for installing and fixing the wing, be used for installing and fixing the dwang through setting up the wing, be used for installing and fixing the flabellum through setting up the dwang, be used for installing and fixing the fuselage through setting up the steady rest, improve the stability of fuselage, make the fuselage descend that can be steady, be used for installing and fixing damping spring through setting up the barrel, play limiting displacement to the telescopic link simultaneously, be used for carrying out the shock attenuation to the telescopic link through setting up damping spring, the damage takes place when preventing the fuselage from descending, be used for sliding and spacing the telescopic link through setting up spout and slider mutually supporting, it is relatively poor to have solved current unmanned aerial vehicle descending shock attenuation effect simultaneously, cause the damage to it very easily when unmanned aerial vehicle descends, the problem of user demand can not be satisfied.

2. The utility model discloses a set up the collar and be used for fixing the dwang and spacing, improve the stability of dwang, be used for installing and fixing the flabellum through setting up solid fixed ring, improve the stability of flabellum when rotating, prevent that the condition of skew from appearing in the flabellum, be used for installing and fixing the telescopic link through setting up the support frame, strengthen the stability between support frame and the telescopic link, through setting up the landing leg, shock pad and slipmat mutually support and be used for improving the stability of fuselage when descending, play support and absorbing effect to whole device simultaneously, the stability of whole device has been improved.

Drawings

FIG. 1 is a front view of the present invention;

FIG. 2 is a schematic view of the cross-sectional structure of the barrel of the present invention;

fig. 3 is a schematic view of the supporting frame of the present invention.

In the figure: 1. a body; 2. a fan blade; 3. rotating the rod; 4. an airfoil; 5. a stabilizer frame; 6. a barrel; 7. a telescopic rod; 8. a support frame; 81. a support leg; 82. a shock pad; 83. a non-slip mat; 9. a damping spring; 10. a chute; 11. a slide block.

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 herein, it is to be understood that the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings to facilitate the description of the patent and to simplify the description, but do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus are not to be considered limiting of the patent. In the description of the present application, it should be noted that unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "disposed" are to be construed broadly and can, for example, be 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. 1-3, an unmanned aerial vehicle with good landing and damping effects comprises a fuselage 1, wings 4 are fixedly mounted on both sides of the fuselage 1, a rotating rod 3 is rotatably connected to the tops of the wings 4, fan blades 2 are arranged on both sides of the rotating rod 3, stabilizing frames 5 are fixedly mounted on four corners of the bottom of the fuselage 1, a barrel 6 is fixedly mounted at the bottom of the stabilizing frame 5, a damping spring 9 is fixedly mounted at the top of an inner cavity of the barrel 6, an expansion link 7 is fixedly mounted at the bottom of the damping spring 9 through a fixing block, the top of the expansion link 7 is positioned inside the barrel 6, sliding grooves 10 are formed in both sides of the inner cavity of the barrel 6, sliding blocks 11 are fixedly mounted at the tops of both sides of the expansion link 7, the sliding blocks 11 are positioned inside the sliding grooves 10 and are slidably connected with the sliding grooves 10, the fuselage 1 is used for mounting and fixing, the rotating rod 3 is used for installing and fixing the fan blade 2, the stabilizing frame 5 is used for installing and fixing the machine body 1, the stability of the machine body 1 is improved, the machine body 1 can stably descend, the barrel 6 is used for installing and fixing the damping spring 9 and simultaneously limiting the telescopic rod 7, the damping spring 9 is used for damping the telescopic rod 7 to prevent the machine body 1 from being damaged when descending, the sliding chute 10 and the sliding block 11 are arranged to be matched with each other for sliding and limiting the telescopic rod 7, the mounting ring is fixedly installed at the top of the wing 4 and sleeved on the surface of the rotating rod 3, the mounting ring is used for fixing and limiting the rotating rod 3, the stability of the rotating rod 3 is improved, the fixing ring is fixedly installed on the surface of the rotating rod 3, and the surface of the fixing ring is fixedly connected with the fan blade 2, the fan blade 2 is installed and fixed by arranging the fixing ring, the stability of the fan blade 2 during rotation is improved, the situation that the fan blade 2 deviates is prevented, the supporting frame 8 is fixedly installed at the bottom of the telescopic rod 7, the supporting frame 8 comprises supporting legs 81, a shock absorption pad 82 and a non-slip pad 83, the supporting legs 81 are fixedly installed at the bottom of the telescopic rod 7, the shock absorption pad 82 is fixedly installed at the bottom of the supporting legs 81, the non-slip pad 83 is fixedly installed at the bottom of the shock absorption pad 82, the telescopic rod 7 is installed and fixed by arranging the supporting frame 8, the stability between the supporting frame 8 and the telescopic rod 7 is enhanced, the stability of the machine body 1 during falling is improved by arranging the supporting legs 81, the shock absorption pad 82 and the non-slip pad 83 to be matched with each other, meanwhile, the whole device is supported and damped, the stability of the whole, the main material of the anti-slip pad 83 is anti-slip rubber.

During the use, when whole device descends, because slipmat 83 effect for the frictional force increase between support frame 8 and the ground, effectually stablize whole device get off, when descending, because the factor of gravity extrudees telescopic link 7, under damping spring 9's effect, cushions telescopic link 7 and stabilizes telescopic link 7 get off, reaches the shock attenuation to whole device.

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 effectual unmanned aerial vehicle of landing shock attenuation, includes fuselage (1), its characterized in that: wings (4) are fixedly arranged on both sides of the fuselage (1), the tops of the wings (4) are rotatably connected with rotating rods (3), the two sides of the rotating rod (3) are provided with fan blades (2), four corners of the bottom of the machine body (1) are fixedly provided with stabilizing frames (5), a cylinder body (6) is fixedly arranged at the bottom of the stabilizing frame (5), a damping spring (9) is fixedly arranged at the top of the inner cavity of the cylinder body (6), the bottom of the damping spring (9) is fixedly provided with a telescopic rod (7) through a fixed block, the top of the telescopic rod (7) is positioned inside the cylinder body (6), sliding grooves (10) are respectively arranged on the two sides of the inner cavity of the cylinder body (6), the top parts of the two sides of the telescopic rod (7) are fixedly provided with sliding blocks (11), the sliding block (11) is positioned in the sliding groove (10) and is in sliding connection with the sliding groove (10).

2. The effectual unmanned aerial vehicle of landing shock attenuation according to claim 1, its characterized in that: the top fixed mounting of wing (4) has the collar, and the collar cover is located the surface of dwang (3).

3. The effectual unmanned aerial vehicle of landing shock attenuation according to claim 1, its characterized in that: the fixed surface of dwang (3) installs solid fixed ring, and solid fixed ring's surface and flabellum (2) fixed connection.

4. The effectual unmanned aerial vehicle of landing shock attenuation according to claim 1, its characterized in that: the bottom fixed mounting of telescopic link (7) has support frame (8), support frame (8) include landing leg (81), shock pad (82) and slipmat (83), the bottom fixed mounting of telescopic link (7) has landing leg (81), the bottom fixed mounting of landing leg (81) has shock pad (82), the bottom fixed mounting of shock pad (82) has slipmat (83).

5. An unmanned aerial vehicle that landing shock attenuation is effectual according to claim 4, its characterized in that: the main material of shock pad (82) is yielding rubber, the main material of slipmat (83) is anti-skidding rubber.