CN211618067U

CN211618067U - Durable type unmanned aerial vehicle aircraft

Info

Publication number: CN211618067U
Application number: CN202021826281.3U
Authority: CN
Inventors: 罗娟
Original assignee: Shenzhen Suyitong Technology Co ltd
Current assignee: Shenzhen Suyitong Technology Co ltd
Priority date: 2020-08-27
Filing date: 2020-08-27
Publication date: 2020-10-02
Anticipated expiration: 2030-08-27

Abstract

The utility model discloses a durable unmanned aerial vehicle aircraft, which comprises an aircraft main body internally provided with a computer control system; the surface of aircraft main part is provided with at least two sets of rotors, and the rotor of every group all contains the support that links firmly in the aircraft main part outside, links firmly the motor on the support end and installs the durable type screw on motor drive axle. The utility model has the characteristics of sound construction, durable, the installation is simple, high durability and convenient use, can improve the structural firmness of screw, reduce when the aircraft uses the connecting axle and prop up the platform and take place not hard up the separation condition and the screw takes place to break cracked probability, produced contact and rock wearing and tearing have been reduced between connecting axle and the platform, the life of screw has been prolonged, the durability of screw has been improved, and then the life of unmanned aerial vehicle aircraft has been prolonged, let this unmanned aerial vehicle aircraft durable more.

Description

Durable type unmanned aerial vehicle aircraft

Technical Field

The utility model relates to an unmanned aerial vehicle aircraft field especially relates to the screw of aircraft rotor, specifically is a durable type unmanned aerial vehicle aircraft.

Background

Unmanned aircraft, commonly known as: unmanned aerial vehicles or unmanned aerial vehicles; the system is a wide range of remote control aircrafts without the need of boarding and driving by a driver; the aircraft mostly comprises an aircraft body and a propeller, wherein the propeller comprises a connecting shaft connected with a motor transmission shaft and a support platform with blades, and the support platform is installed on the connecting shaft.

The existing screw, the connecting axle is the axle hole department of direct mount in a platform, cause screw monolithic connection steadiness poor, the aircraft is when long-time aviation flight, the condition of skew aversion and not hard up separation takes place for high-speed rotatory connecting axle easily with a platform, make connecting axle and a platform can't keep steady rotation, easily produce a large amount of contacts and rock the wearing and tearing between the platform of connecting axle and screw this moment, and external factors cause direct striking injury to the screw such as sand blown by the wind often, lead to the screw to take place the problem that the rupture takes place, influence the holistic life of screw, and then the influence has prolonged unmanned aerial vehicle's life.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a durable type unmanned aerial vehicle aircraft to the screw body coupling steadiness that proposes among the solution above-mentioned background art is poor, the screw easily receives a large amount of wearing and tearing and takes place the rupture to break, screw life low influence unmanned aerial vehicle aircraft life's problem.

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

a durable unmanned aerial vehicle aircraft comprises an aircraft body with a built-in computer control system; the outer surface of the aircraft body is provided with at least two groups of rotor wings, and each group of rotor wings comprises a bracket fixedly connected to the outer side of the aircraft body, a motor fixedly connected to the tail end of the bracket and a durable propeller arranged on a motor transmission shaft; a protective ring is arranged on the periphery of the propeller, and the bottom end of the protective ring is fixedly connected to the support; the propeller comprises a supporting platform, blades arranged on the periphery of the supporting platform, a protecting platform arranged on the supporting platform, a connecting shaft arranged at the bottom end of the supporting platform and provided with a screw hole at the upper part, and a shaft body reinforcing mechanism arranged above the supporting platform and used for firmly combining the connecting shaft, the protecting platform and the supporting platform into a whole; the bottom of the connecting shaft is in transmission connection with the top end of a motor transmission shaft through a coupler.

Preferably, the top end of the supporting platform is provided with a groove, the top end of the supporting platform is positioned in the middle of the groove and is provided with a shaft hole through which the connecting shaft vertically passes, and the top end of the supporting platform is positioned on two sides of the shaft hole and is provided with guide holes; four groups of arrangement grooves are formed in the positions, located in the grooves, above the supporting platform, the arrangement grooves of each group are arranged along the periphery of the shaft hole, and the groove cavities of the arrangement grooves are communicated with the hole cavity of the shaft hole.

Preferably, the shaft body reinforcing mechanism comprises a reinforcing plate positioned on the supporting platform, guide columns which are fixedly connected to the bottom end of the reinforcing plate at intervals and vertically inserted into the guide holes, a first connecting piece which is positioned above the reinforcing plate and connects the reinforcing plate and the upper part of the connecting shaft into a whole, and a second connecting piece which is positioned on the reinforcing plate and connects the reinforcing plate and the protecting platform into a whole; the second connector comprises a screw or a screw.

Preferably, the whole appearance of the reinforcing plate is of a cylindrical structure, and the middle part of the top end of the reinforcing plate is provided with a through hole; the first connecting piece comprises a screw or a bolt, and the bottom end of the first connecting piece penetrates through the through hole and is screwed into the hole cavity of the screw hole.

Preferably, the periphery of the top end of the connecting shaft is annularly distributed with a lug, and the lug is arranged in a groove cavity of the placing groove.

Preferably, the main appearance of the protection platform is in an isosceles triangle or equilateral triangle structure, and the outer surface of the protection platform is a smooth surface.

Compared with the prior art, the beneficial effects of the utility model are that: the utility model has the characteristics of firm structure, firmness and durability, simple installation and convenient use, can firmly combine the connecting shaft and the supporting platform of the screw into a whole when the aircraft flies so as to avoid the situation that the connecting shaft generates skew displacement in the supporting platform, ensure that the connecting shaft and the supporting platform always keep stable rotation, improve the connection firmness between the supporting platform and the connecting shaft, further improve the structure firmness of the screw, effectively reduce the probability of loosening and separating between the connecting shaft and the supporting platform when the aircraft uses, and form a protective ring at the periphery of the screw under the action of the protective ring to protect the periphery of the screw, prevent external factors such as wind sand from directly impacting and damaging the screw, reduce the probability of breaking and breaking of the screw when the aircraft uses, and reduce the contact and shaking abrasion generated between the connecting shaft and the supporting platform of the screw, the holistic life of screw has been prolonged, has improved the durability of screw, and then has prolonged the life of unmanned aerial vehicle aircraft, makes this unmanned aerial vehicle aircraft durable more.

Drawings

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

fig. 2 is a top view of the propeller of the present invention;

FIG. 3 is a perspective view of the propeller of the present invention;

FIG. 4 is a sectional view of the structure of the support of the present invention;

FIG. 5 is a perspective view of the whole structure of the platform and blade assembly of the present invention;

FIG. 6 is a perspective view of the connecting shaft of the present invention;

FIG. 7 is an exploded view of a partial structure of the propeller of the present invention;

fig. 8 is a perspective view of the structure of the shaft body reinforcing mechanism of the present invention.

In the figure: the aircraft comprises an aircraft body 1, a bracket 2, a protective ring 3, a motor 4, a propeller 5, a platform 51, a 511 groove, a 512 shaft hole, a 513 guide hole, a 514 placing groove, a 52 blade, a 53 protective platform, a 54 connecting shaft, 541 screw holes, 542 lugs, a 55 shaft body reinforcing mechanism, a 551 reinforcing plate, a 552 guide post, 553 through holes, a 554 first connecting piece and a 555 second connecting piece.

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. 1-8, the present invention provides a technical solution: a durable unmanned aerial vehicle aircraft comprises an aircraft body 1 with a built-in computer control system; the outer surface of the aircraft body 1 is provided with at least two groups of rotor wings, and each group of rotor wings comprises a bracket 2 fixedly connected to the outer side of the aircraft body 1, a motor 4 fixedly connected to the tail end of the bracket 2 and a durable propeller 5 arranged on a transmission shaft of the motor 4; a protective ring 3 is arranged on the periphery of the propeller 5, and the bottom end of the protective ring 3 is fixedly connected to the support 2; under the action of the protective ring 3, a protective ring can be formed at the periphery of the propeller 5 to protect the periphery of the propeller 5, so that external factors such as wind and sand are prevented from directly impacting and damaging the propeller 5, and the probability of breakage and fracture of the propeller 5 when the aircraft is used is reduced; the structure of the guard ring 3 can be a circular ring structure or a rectangular frame structure.

The aircraft is a flight device with at least two power unit rotors, the power unit rotors rotate in different directions to perform flight, hovering, steering and other actions, and the flight structure has the advantages of stable flight, flexible control, strong load capacity, vertical lifting and descending and the like; the state and position change of the aircraft can be changed by achieving different lift forces through different rotating speeds of the rotors in different directions; the power unit rotor consists of a bracket 2, a propeller 5 and a motor 4.

Referring to fig. 1, 2, 3, 4 and 6, the propeller 5 includes a supporting platform 51, blades 52 disposed at the periphery of the supporting platform 51, a protecting platform 53 disposed on the supporting platform 51, a connecting shaft 54 disposed at the bottom end of the supporting platform 51 and having a screw hole 541 at the upper side thereof, and a shaft body reinforcing mechanism 55 disposed above the supporting platform 51 and firmly combining the connecting shaft 54, the protecting platform 53 and the supporting platform 51 into a whole; the bottom end of the connecting shaft 54 is in transmission connection with the top end of a transmission shaft of the motor 4 through a coupler, a lug 542 is annularly distributed on the periphery of the top end of the connecting shaft 54, and the lug 542 is arranged in a groove cavity of the placing groove 514; the main view appearance of the guard table 53 is an isosceles triangle or equilateral triangle structure, the outer surface of the guard table 53 is a smooth surface, and the arrangement of the smooth surface can smooth the surface of the guard table 53 and prevent external dust and moisture from being retained on the guard table 53 to corrode the guard table 53; the protection platform 53 can form a protection mechanism at the top end of the propeller 5, so that external dust and moisture are prevented from entering the propeller 5 along the top surface of the support platform 51 to corrode the inside of the propeller 5, and the service life of the propeller 5 is further prolonged; the overall shape of the guard 53 is a conical or pyramid structure.

Referring to fig. 3, 4 and 5, a groove 511 is formed at the top end of the supporting platform 51, a shaft hole 512 for the connecting shaft 54 to vertically pass through is formed at the middle position of the groove 511 at the top end of the supporting platform 51, and guide holes 513 are formed at the two sides of the shaft hole 512 at the top end of the supporting platform 51; four sets of placing grooves 514 are formed in the positions, located in the grooves 511, above the supporting table 51, the placing grooves 514 of each set are arranged along the periphery of the shaft hole 512, and the groove cavities of the placing grooves 514 are communicated with the hole cavity of the shaft hole 512.

Referring to fig. 4, 5, 7 and 8, the shaft body reinforcing mechanism 55 includes a reinforcing plate 551 on the support platform 51, a guide post 552 fixed to the bottom end of the reinforcing plate 551 at an interval and inserted into the guide hole 513 vertically, a first connecting member 554 above the reinforcing plate 551 and connecting the reinforcing plate 551 and the connecting shaft 54 integrally, and a second connecting member 555 above the reinforcing plate 551 and connecting the reinforcing plate 551 and the support platform 53 integrally; the second connector 555 comprises a screw or a screw; the overall shape of the reinforcing plate 551 is a cylindrical structure, and a through hole 553 is formed in the middle of the top end of the reinforcing plate 551; the first connecting member 554 comprises a screw or a bolt, and the bottom end of the first connecting member 554 passes through the through hole 553 and is screwed into the cavity of the screw hole 541; the reinforcing plate 551 may have a circular, rectangular or elliptical shape, and the perforations 553 may have a circular or rectangular structure.

In the above scheme, the support platform 51 and the connecting shaft 54 can be firmly combined into a whole through the shaft body reinforcing mechanism 55 formed by the reinforcing plate 551, the guide post 552, the first connecting piece 554 and the second connecting piece 555, so that the connecting shaft 54 and the support platform 51 are firmly combined into a whole when the aircraft flies, the connecting shaft 54 and the support platform 51 are prevented from generating skew displacement in the support platform 51, the connecting shaft 54 is always kept to stably rotate, the firmness of the connection between the connecting shaft 54 and the propeller 5 is improved, the probability of loosening and separating between the connecting shaft 54 and the support platform 51 when the aircraft is in use is effectively reduced, the contact and shaking abrasion generated between the connecting shaft 54 and the support platform 51 is reduced, the connecting shaft 54 and the support platform 51 are tightly combined into a whole, the service life of the whole propeller 5 is prolonged, the durability of the propeller 5 is improved, and the service life of the unmanned aerial vehicle is further prolonged, make unmanned aerial vehicle aircraft durable more.

Wherein, through arranging the projection 542 in the arranging groove 514, the connecting shaft 54 can be horizontally reinforced by a first layer, so that the connecting shaft 54 is firmly arranged in the shaft hole 512 in advance; through the cooperation of first connecting piece 554, gusset plate 551 and screw 541, carry out the perpendicular reinforcement of second layer to connecting axle 54, tightly restrict connecting axle 54 in shaft hole 512 through double-deck reinforcing effect to let connecting axle 54 and a platform 51 combine firmly in an organic whole, increase connecting axle 54 and the stability and the fastness of being connected of a platform 51 with this, improve the holistic structure fastness of screw 5.

The working principle is as follows: when the unmanned aerial vehicle is used, firstly, the propeller 5 is assembled, then, the propeller 5 is installed on the aircraft main body 1 through the coupler, after the propeller 5 is installed, the motor 4 in the rotor wing is controlled to operate through the computer control system arranged in the aircraft main body 1, and when the motor 4 operates, the propeller 5 is driven to rotate circumferentially by the circumferential rotation of the transmission shaft of the motor 4, so that the aerial flight of the unmanned aerial vehicle is realized; when the propeller 5 is assembled, the connecting shaft 54 can be inserted into the shaft hole 512 from top to bottom, the convex blocks 542 at two sides of the top end of the connecting shaft 54 are arranged in the arranging grooves 514, then the reinforcing plate 551 is fixedly connected to the connecting shaft 54 tightly by the matching of the first connecting piece 554 and the screw hole 541, the guide post 552 is vertically inserted into the guide hole 513, and the bottom surface of the reinforcing plate 551 is tightly attached to the supporting platform 51; the protective platform 53 is arranged on the reinforcing plate 551 through the second connecting piece 555 to complete the assembly of the propeller 5, and after the assembly is finished, the bottom end of the connecting shaft 54 is connected with the top end of the transmission shaft of the motor 4 into a whole through a coupling in a transmission way, so that the assembly of the aircraft can be completed; the computer control system and the motor 4 built in the aircraft body 1 are necessary technical structures in the aircraft, and the structural principle thereof is the prior known technology, so that the details are not described herein.

Wherein, the aircraft of types such as four rotor crafts, many rotors also can be applicable to the utility model discloses a durable type screw 5 technical scheme is last.

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. A durable unmanned aerial vehicle aircraft comprising an aircraft body (1) with a built-in computer control system; the method is characterized in that: the outer surface of the aircraft main body (1) is provided with at least two groups of rotor wings, and each group of rotor wings comprises a bracket (2) fixedly connected to the outer side of the aircraft main body (1), a motor (4) fixedly connected to the tail end of the bracket (2) and a durable propeller (5) arranged on a transmission shaft of the motor (4); a protective ring (3) is arranged on the periphery of the propeller (5), and the bottom end of the protective ring (3) is fixedly connected to the support (2); the propeller (5) comprises a supporting platform (51), blades (52) arranged on the periphery of the supporting platform (51), a protecting platform (53) arranged on the supporting platform (51), a connecting shaft (54) arranged at the bottom end of the supporting platform (51) and provided with a screw hole (541) above, and a shaft body reinforcing mechanism (55) arranged above the supporting platform (51) and used for firmly combining the connecting shaft (54), the protecting platform (53) and the supporting platform (51) into a whole; the bottom end of the connecting shaft (54) is in transmission connection with the top end of a transmission shaft of the motor (4) through a coupler.

2. The durable drone aircraft of claim 1, wherein: the top end of the supporting platform (51) is provided with a groove (511), the top end of the supporting platform (51) is positioned in the middle of the groove (511) and is provided with a shaft hole (512) through which the connecting shaft (54) vertically passes, and the top end of the supporting platform (51) is positioned on two sides of the shaft hole (512) and is provided with guide holes (513); four sets of arrangement grooves (514) are formed in the positions, located in the grooves (511), above the supporting platform (51), the arrangement grooves (514) of each set are arranged along the periphery of the shaft hole (512), and a groove cavity of each arrangement groove (514) is communicated with a hole cavity of the shaft hole (512).

3. The durable drone aircraft of claim 1, wherein: the shaft body reinforcing mechanism (55) comprises a reinforcing plate (551) positioned on the supporting platform (51), guide columns (552) which are fixedly connected to the bottom end of the reinforcing plate (551) at intervals and are vertically inserted into the guide holes (513), first connecting pieces (554) which are positioned above the reinforcing plate (551) and connect the reinforcing plate (551) and the connecting shaft (54) into a whole, and second connecting pieces (555) which are positioned on the reinforcing plate (551) and connect the reinforcing plate (551) and the protecting platform (53) into a whole; the second connector (555) comprises a screw or a screw.

4. The durable drone aircraft of claim 3, wherein: the whole appearance of the reinforcing plate (551) is of a cylindrical structure, and a through hole (553) is formed in the middle of the top end of the reinforcing plate (551); the first connecting piece (554) comprises a screw or a bolt, and the bottom end of the first connecting piece (554) penetrates through the through hole (553) and is screwed into the hole cavity of the screw hole (541).

5. The durable drone aircraft of claim 1, wherein: and the periphery of the top end of the connecting shaft (54) is annularly distributed with a lug (542), and the lug (542) is arranged in the groove cavity of the placement groove (514).

6. The durable drone aircraft of claim 1, wherein: the main appearance of the protection platform (53) is in an isosceles triangle or equilateral triangle structure, and the outer surface of the protection platform (53) is a smooth surface.