CN211969725U

CN211969725U - Wind-resistant unmanned aerial vehicle flight system

Info

Publication number: CN211969725U
Application number: CN202020111283.8U
Authority: CN
Inventors: 丁武轩
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-01-17
Filing date: 2020-01-17
Publication date: 2020-11-20
Anticipated expiration: 2030-01-17

Abstract

The utility model discloses an anti-wind type unmanned aerial vehicle flight system, including unmanned aerial vehicle body, flight structure, feather wing, fixed axle, pivot, protective structure, kicking block, gasbag, lug, fixing base and air duct. The utility model has the advantages that: rotate in fixed cover inside through the pivot, make four wings rotate simultaneously, make unmanned aerial vehicle body flight, make unmanned aerial vehicle body work, the pivot drives two kicking blocks when fixed cover inside pivoted and rotates, the kicking block rotates and supports the back with the arch, make the inside wall that the protruding slip got into the fixing base, make the gasbag compression, blow gas to the both sides of fixed cover through two air ducts after the gasbag compression, dispel the heat between countershaft and the fixed cover, the air duct that lies in the top simultaneously blows off the top of fixed cover and the dust of pivot junction, prevent that the dust from getting into the inside of fixed cover, thereby do benefit to the pivot and rotate the wing and drive the flight of unmanned aerial vehicle body, do benefit to unmanned aerial vehicle work.

Description

Wind-resistant unmanned aerial vehicle flight system

Technical Field

The utility model relates to an unmanned aerial vehicle flight system specifically is an anti-wind type unmanned aerial vehicle flight system, belongs to unmanned aerial vehicle flight technical field.

Background

The unmanned plane is an unmanned plane for short, which is an unmanned plane operated by 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, and the unmanned plane is a general name of the unmanned plane in practice, and can be defined as follows from the technical point of view: unmanned fixed wing aircraft, unmanned VTOL aircraft, unmanned dirigible, unmanned helicopter, unmanned many rotor crafts, unmanned parachute-wing aircraft etc. unmanned aerial vehicle flight system is the part that is used for unmanned aerial vehicle flight.

However, in the conventional flying wing for unmanned aerial vehicle, the rotating shaft connected to the wing contacts with air during operation, which easily causes dust to adhere to the rotating shaft to increase friction force, increases the burden of wing rotation, and easily causes damage to the wing and the rotating shaft.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an anti-wind type unmanned aerial vehicle flight system just in order to solve above-mentioned problem, do benefit to unmanned aerial vehicle's feather wing work and make unmanned aerial vehicle effectively fly, prevent that unmanned aerial vehicle's pivot from getting into the dust and rotating the difficulty.

The utility model achieves the above purpose through the following technical scheme, an anti-wind type unmanned aerial vehicle flight system, comprises an unmanned aerial vehicle body, the unmanned aerial vehicle body is connected with a flight structure, the flight structure comprises wings, fixed shafts and a rotating shaft, the unmanned aerial vehicle body is fixed with four fixed shafts, the fixed shafts are rotationally connected with the rotating shafts, the rotating shafts extend to the inside of the unmanned aerial vehicle body, the side walls of the rotating shafts are fixed with the wings, the fixed shafts are connected with a protective structure, the protective structure comprises ejector blocks, air bags, convex blocks, fixed seats and air guide pipes, the outer side walls of the rotating shafts are fixed with two ejector blocks, the inner side walls of the fixed shafts are fixed with the fixed seats, the inner side walls of the fixed shafts are fixed with the air bags, the side walls of the air bags are fixed with the convex blocks with triangular cross sections, and the convex, the air bag is fixed with two air guide tubes, and one ends of the two air guide tubes face to two ends of the fixed shaft respectively.

Preferably, in order to drive the wing through motor work and rotate and make the unmanned aerial vehicle body fly, flight structure still includes bearing and motor, the unmanned aerial vehicle body is fixed with the motor, the pivot is connected the motor, the pivot with be connected with between the fixed axle the bearing.

Preferably, in order to make the unmanned aerial vehicle body normally fly, the fixed axle is equipped with four, four the fixed axle about unmanned aerial vehicle body symmetric distribution, four the fixed axle all rotates and is connected with the pivot, four the pivot all is fixed with the wing.

Preferably, in order to make the gasbag can reset after compressing, protective structure still includes the spring, the inside wall of fixed axle is fixed with two the gasbag, two the gasbag is about fixed axle symmetric distribution, two the inside wall of gasbag all is fixed with the spring, two the lateral wall of gasbag all is fixed with the lug, the lug with the perpendicular distance between the lateral wall of pivot is less than one end with the distance between the lateral wall of pivot.

Preferably, in order to carry out the inside part protection of unmanned aerial vehicle body, the unmanned aerial vehicle body is fixed with the protecting crust, the protecting crust is the cylinder structure, the inside wall of fixed axle with be connected with four between the pivot the bearing, four the bearing is about fixed axle symmetric distribution.

Preferably, in order to facilitate supporting the unmanned aerial vehicle body, this body coupling auxiliary structure of unmanned aerial vehicle, auxiliary structure includes dead lever, bracing piece and gasket, the unmanned aerial vehicle body deviates from the lateral wall of wing is fixed with four the dead lever, four the lateral wall of dead lever all is fixed with the gasket, wherein two are a set of be fixed with between the dead lever the bracing piece.

Preferably, in order to improve the radiating effect of unmanned aerial vehicle body internals during operation, auxiliary structure still includes the heat dissipation window, the unmanned aerial vehicle body has been seted up a plurality of the heat dissipation window is a plurality of the heat dissipation window all is the arc structure.

Compared with the prior art, the beneficial effects of the utility model are that: the four wings rotate simultaneously through the rotating shaft in the fixed sleeve, so that the unmanned aerial vehicle body flies and works, the rotating shaft drives the two ejector blocks to rotate while rotating in the fixed sleeve, after the ejector blocks rotate and abut against the bulges, the bulges slide to enter the inner side wall of the fixed seat, the air bag is compressed after the bulges slide, after the air bag is compressed, the air is blown to the two sides of the fixed sleeve through the two air guide pipes, the heat is dissipated between the rotating shaft and the fixed sleeve, meanwhile, the air guide pipe positioned at the top end blows away the dust at the joint of the top end of the fixed sleeve and the rotating shaft, the dust is prevented from entering the inside of the fixed sleeve, the rotating shaft is favorable for rotating to drive the wings to rotate so that the unmanned aerial vehicle body flies, the unmanned aerial vehicle works, after the ejector blocks rotate away from the bulges, the air bag is reset and inflated through the elasticity, the rotating effect of the rotating shaft in the fixed sleeve is improved.

Drawings

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

fig. 2 is a schematic view of a connection structure between the main body of the unmanned aerial vehicle and the protective structure shown in fig. 1;

FIG. 3 is a schematic view of the connection of the flight structure and the protective structure shown in FIG. 1;

fig. 4 is a schematic structural view of the protective structure shown in fig. 2.

In the figure: 1. unmanned aerial vehicle body, 2, protective housing, 3, flight structure, 31, wing, 32, fixed axle, 33, pivot, 34, bearing, 35, motor, 4, auxiliary structure, 41, dead lever, 42, bracing piece, 43, gasket, 44, radiator window, 5, protective structure, 51, kicking block, 52, gasbag, 53, spring, 54, lug, 55, fixing base, 56, air duct.

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. 1-4, an anti-wind type unmanned aerial vehicle flight system includes an unmanned aerial vehicle body 1, the unmanned aerial vehicle body 1 is connected with a flight structure 3, the flight structure 3 includes wings 31, fixing shafts 32 and a rotating shaft 33, the unmanned aerial vehicle body 1 is fixed with four fixing shafts 32, the fixing shafts 32 are rotatably connected with the rotating shaft 33, the rotating shaft 33 extends to the inside of the unmanned aerial vehicle body 1, the wings 31 are fixed on the side wall of the rotating shaft 33, the fixing shaft 32 is connected with a protection structure 5, the protection structure 5 includes top blocks 51, air bags 52, convex blocks 54, fixing seats 55 and air ducts 56, the two top blocks 51 are fixed on the outer side wall of the rotating shaft 33, the fixing seats 55 are fixed on the inner side wall of the fixing shaft 32, the air bags 52 are fixed on the inner side wall of the fixing shaft 32, the convex blocks 54 with triangular cross sections are fixed on the side walls of the, the protruding block 54 is slidably connected with the fixing base 55, the air bag 52 is fixed with two air ducts 56, and one end of each air duct 56 faces to two ends of the fixing shaft 32.

As a technical optimization scheme of the utility model, flight structure 3 still includes bearing 34 and motor 35, unmanned aerial vehicle body 1 is fixed with motor 35, pivot 33 is connected motor 35, pivot 33 with be connected with between the fixed axle 32 bearing 34.

As a technical optimization scheme of the utility model, the fixed axle 32 is equipped with four, four the fixed axle 32 about 1 symmetric distribution of unmanned aerial vehicle body, four the fixed axle 32 all rotates and is connected with pivot 33, four pivot 33 all is fixed with wing 31.

As a technical optimization scheme of the utility model, protective structure 5 still includes spring 53, the inside wall of fixed axle 32 is fixed with two gasbag 52, two gasbag 52 about fixed axle 32 symmetric distribution, two the inside wall of gasbag 52 all is fixed with spring 53, two the lateral wall of gasbag 52 all is fixed with lug 54, lug 54 with vertical distance between the lateral wall of pivot 33 is less than one end with distance between the lateral wall of pivot 33.

As a technical optimization scheme of the utility model, unmanned aerial vehicle body 1 is fixed with protecting crust 2, protecting crust 2 is the cylinder structure, the inside wall of fixed axle 32 with be connected with four between the pivot 33 bearing 34, four bearing 34 about fixed axle 32 symmetric distribution.

As a technical optimization scheme of the utility model, the auxiliary structure 4 is connected to unmanned aerial vehicle body 1, auxiliary structure 4 includes dead lever 41, bracing piece 42 and gasket 43, unmanned aerial vehicle body 1 deviates from the lateral wall of feather wing 31 is fixed with four dead lever 41, four the lateral wall of dead lever 41 all is fixed with gasket 43, wherein two are a set of be fixed with between the dead lever 41 bracing piece 42.

As the utility model discloses a technical optimization scheme, auxiliary structure 4 still includes heat dissipation window 44, unmanned aerial vehicle body 1 has been seted up a plurality of heat dissipation window 44 is a plurality of heat dissipation window 44 all is the arc structure.

When the utility model is used, firstly, a user turns on the power supply of the unmanned aerial vehicle body 1 to enable the motor 35 to work to drive the rotating shaft 33 to rotate, after the rotating shaft 33 rotates in the fixed sleeve 32, the four wings 31 rotate simultaneously to enable the unmanned aerial vehicle body 1 to fly, the unmanned aerial vehicle body 1 works, the bearing 34 is connected between the rotating shaft 33 and the fixed sleeve, the rotating effect of the rotating shaft 33 is improved, the rotating shaft 33 is beneficial to the wing 31 to rotate to enable the unmanned aerial vehicle body 1 to fly, the rotating shaft 33 drives the two top blocks 51 to rotate while rotating in the fixed sleeve 32, after the top blocks 51 rotate and the bulges 54 are abutted, the bulges 54 slide into the inner side wall of the fixed seat 55, the air bag 52 is compressed after the bulges 54 slide, the spring 53 is contracted to generate elasticity, after the air bag 52 is compressed, the air is blown to the two sides of the fixed sleeve 32 through the two air ducts 56, the air duct 36 that lies in the top simultaneously blows off the top of fixed cover 32 and the dust of pivot 32 junction, prevent that the dust from getting into the inside of fixed cover 32, thereby do benefit to pivot 32 and rotate and drive wing 31 and rotate and make unmanned aerial vehicle body 1 flight, do benefit to unmanned aerial vehicle 1 work, kicking block 51 rotates and keeps away from behind protruding 54, make gasbag 52 restore to the throne and aerify through the elasticity of gasbag 52 self and the elasticity of spring 53, thereby make gasbag 52 can compress again and blow to the inside wall of pivot 33 and fixed cover 32, improve the pivot 33 at the inside rotation effect of fixed cover 32, do benefit to the unmanned aerial vehicle body 1 during operation through a plurality of heat dissipation windows 44 and dispel the heat, through the gasket of being connected with four dead levers 41, support when doing benefit to unmanned aerial vehicle body 1 and stopping flight, increase the fastness between two dead.

It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented 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

1. The utility model provides a wind-resistant type unmanned aerial vehicle flight system, includes unmanned aerial vehicle body (1), its characterized in that: the unmanned aerial vehicle body (1) is connected with a flight structure (3), the flight structure (3) comprises wings (31), a fixed shaft (32) and a rotating shaft (33), the unmanned aerial vehicle body (1) is fixed with four fixed shafts (32), the fixed shaft (32) is rotatably connected with the rotating shaft (33), the rotating shaft (33) extends to the inside of the unmanned aerial vehicle body (1), the side wall of the rotating shaft (33) is fixed with the wings (31), the fixed shaft (32) is connected with a protection structure (5), the protection structure (5) comprises ejector blocks (51), air bags (52), convex blocks (54), fixing seats (55) and air guide tubes (56), the outer side wall of the rotating shaft (33) is fixed with two ejector blocks (51), the inner side wall of the fixed shaft (32) is fixed with the fixing seats (55), the inner side wall of the fixed shaft (32) is fixed with the air bags (52), the lateral wall of gasbag (52) is fixed with the cross-section and is triangle-shaped structure lug (54), lug (54) with sliding connection between fixing base (55), gasbag (52) are fixed with two air duct (56), the one end of two air duct (56) is towards respectively the both ends of fixed axle (32).

2. A wind-resistant unmanned aerial vehicle flight system according to claim 1, wherein: flight structure (3) still include bearing (34) and motor (35), unmanned aerial vehicle body (1) is fixed with motor (35), pivot (33) are connected motor (35), pivot (33) with be connected with between fixed axle (32) bearing (34).

3. A wind-resistant unmanned aerial vehicle flight system according to claim 2, wherein: fixed axle (32) are equipped with four, four fixed axle (32) about unmanned aerial vehicle body (1) symmetric distribution is four fixed axle (32) all rotates and is connected with pivot (33), four pivot (33) all are fixed with wing (31).

4. A wind-resistant unmanned aerial vehicle flight system according to claim 1, wherein: protective structure (5) still include spring (53), the inside wall of fixed axle (32) is fixed with two gasbag (52), two gasbag (52) about fixed axle (32) symmetric distribution, two the inside wall of gasbag (52) all is fixed with spring (53), two the lateral wall of gasbag (52) all is fixed with lug (54), lug (54) with the vertical distance between the lateral wall of pivot (33) is less than one end with the distance between the lateral wall of pivot (33).

5. A wind-resistant unmanned aerial vehicle flight system according to claim 3, wherein: unmanned aerial vehicle body (1) is fixed with protecting crust (2), protecting crust (2) are the cylinder structure, the inside wall of fixed axle (32) with be connected with four between pivot (33) bearing (34), four bearing (34) about fixed axle (32) symmetric distribution.

6. A wind-resistant unmanned aerial vehicle flight system according to claim 1, wherein: auxiliary structure (4) is connected in unmanned aerial vehicle body (1), auxiliary structure (4) are including dead lever (41), bracing piece (42) and gasket (43), unmanned aerial vehicle body (1) deviates from the lateral wall of feather wing (31) is fixed with four dead lever (41), four the lateral wall of dead lever (41) all is fixed with gasket (43), wherein two are a set of be fixed with between dead lever (41) bracing piece (42).

7. A wind-resistant unmanned aerial vehicle flight system according to claim 6, wherein: auxiliary structure (4) still include radiator window (44), unmanned aerial vehicle body (1) has been seted up a plurality of radiator window (44), a plurality of radiator window (44) all are the arc structure.