CN215155583U

CN215155583U - Lightweight high strength multiaxis unmanned aerial vehicle structure

Info

Publication number: CN215155583U
Application number: CN202121160450.9U
Authority: CN
Inventors: 魏智尚
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-05-27
Filing date: 2021-05-27
Publication date: 2021-12-14
Anticipated expiration: 2031-05-27

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a lightweight high-strength multi-shaft unmanned aerial vehicle structure, which comprises a longitudinal arm, a large-size tube fixing clamp and a landing gear V-shaped connecting piece, wherein the middle part of the longitudinal arm is fixedly connected with the large-size tube fixing clamp, the top part of the large-size tube fixing clamp is fixedly connected with an aircraft center fixing piece, the inner part of the aircraft center fixing piece is fixedly connected with a pin, the top part of the aircraft center fixing piece is fixedly connected with a transverse arm, the transverse arm and the longitudinal arm are both integrated carbon tubes and are used as the arms, the integrated design is adopted, the impact resistance of the arms is enhanced by avoiding the separation and cutting between the arms, the practicability of the device is improved, the horizontal force of a landing gear supporting rod can be shared, thereby the possibility of deformation of the landing gear supporting rod is reduced, the practicability of the device is improved, the supporting rod can form a triangular stable support with a contact surface, the bending of the V-shaped structure at the root of the undercarriage is effectively reduced, and the practicability of the device is improved.

Description

Lightweight high strength multiaxis unmanned aerial vehicle structure

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is a lightweight high strength multiaxis unmanned aerial vehicle structure.

Background

The pilotless aircraft is an unmanned aircraft operated by a radio remote control device and a self-contained program control device, and can be divided into the following technical definitions: compared with manned aircraft, the unmanned fixed wing aircraft has the advantages of small volume, low manufacturing cost, convenient use, low requirement on the operational environment, strong battlefield viability and the like.

Four rotors of tradition need be cut two carbon pipes respectively, connect again, make the intensity of unmanned aerial vehicle horn receive the influence, thereby influenced unmanned aerial vehicle to the resistance of assaulting, make unmanned aerial vehicle lead to the condition greatly increased that the horn is rolled over and is reduced because external force strikes, unmanned aerial vehicle's use quality has been influenced, current unmanned aerial vehicle carry department only uses four spinal branch vaulting poles to carry out the shore of rising and falling simultaneously, do not consolidate the bracing piece, make the bracing piece buckle easily after receiving impact many times, unmanned aerial vehicle's durability has been reduced.

Therefore, how to design a lightweight high strength multiaxis unmanned aerial vehicle structure becomes the problem that we need to solve at present.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a lightweight high strength multiaxis unmanned aerial vehicle structure to the intensity of the formula of cutting apart unmanned aerial vehicle horn that provides reduces to some extent in solving above-mentioned background art, and the deformation scheduling problem takes place easily for the bracing piece that does not consolidate.

In order to achieve the above object, the utility model provides a following technical scheme: a lightweight high-strength multi-axis unmanned aerial vehicle structure comprises a longitudinal horn, a large-size tube fixing clamp and an undercarriage V-shaped connecting piece, wherein the large-size tube fixing clamp is fixedly connected to the middle part of the longitudinal horn, an aircraft center fixing piece is fixedly connected to the top of the large-size tube fixing clamp, a pin is fixedly connected to the inside of the aircraft center fixing piece, a transverse horn is fixedly connected to the top of the aircraft center fixing piece, the undercarriage V-shaped connecting piece is fixedly connected to the outer wall of the transverse horn, an undercarriage supporting rod is fixedly connected to the outer wall of the undercarriage V-shaped connecting piece, an undercarriage T-shaped connecting piece is fixedly connected to the outer wall of the undercarriage supporting rod, an undercarriage cross rod is fixedly connected to the inside of the undercarriage T-shaped connecting piece, a medium-size tube fixing clamp is fixedly connected to the middle part of the undercarriage cross rod, and a fixing clamp connecting piece is fixedly connected to the outer wall of the medium-size tube fixing clamp, the top of horizontal horn fixedly connected with aircraft power assembly, aircraft power assembly are equipped with four altogether, and distribute respectively at the top both ends of vertical horn and horizontal horn.

Preferably, the length of the longitudinal horn is connected with the length of the transverse horn through a central fixing piece of the airplane, the longitudinal horn and the transverse horn are not at the same height and are fixed in a crossed manner, and the longitudinal horn and the transverse horn are two integral carbon tubes.

Preferably, the undercarriage supporting rod uses an undercarriage V-shaped connecting piece as a center, and the undercarriage V-shaped connecting piece is obliquely and externally fixed, four undercarriage T-shaped connecting pieces are arranged, and the undercarriage T-shaped connecting pieces are respectively fixed on the outer wall of the undercarriage supporting rod.

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

1. according to the light-weight high-strength multi-shaft unmanned aerial vehicle structure, the high-strength arm mechanism is arranged, so that the upper carbon tube and the lower carbon tube are used as a longitudinal arm and a transverse arm, no gap exists in the arm in a single direction, the impact resistance of the arm is greatly enhanced, and as the central fixing piece of the airplane is positioned at the center of the unmanned aerial vehicle structure, only a small amount of positive stress and z-direction torsional stress need to be overcome, so that the strength requirement of a machined part is greatly reduced, the separate cutting of the arm can be avoided, and the impact resistance of the arm is increased;

2. this kind of lightweight high strength multiaxis unmanned aerial vehicle structure, through setting up branch strengthening mechanism, overlap the outer wall at horizontal horn with undercarriage V type connecting piece, embolia the outer wall of undercarriage bracing piece with undercarriage T type connecting piece, fasten undercarriage V type connecting piece and undercarriage T type connecting piece respectively through the screw again, thereby fix the undercarriage horizontal pole on unmanned aerial vehicle, share undercarriage bracing piece atress through the undercarriage horizontal pole, can strengthen the atress limit of unmanned aerial vehicle built-in components, avoid the bracing piece to take place deformation easily.

Drawings

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

FIG. 2 is a schematic top view of the device body of the present invention;

fig. 3 is a schematic front view of the device body of the present invention;

fig. 4 is a schematic side view of the device body of the present invention.

In the figure: 1. a longitudinal horn; 2. a transverse horn; 3. an undercarriage support bar; 4. a landing gear cross bar; 5. an aircraft power assembly; 6. landing gear V-shaped connectors; 7. a landing gear T-connector; 8. a fixation clamp connector; 9. an aircraft center mount; 10. a large-size pipe fixing clamp; 11. a medium-sized tube fixing clamp; 12. a pin.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, rather than all embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative work belong to the protection scope of the present invention based on the embodiments of the present invention.

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

Furthermore, the terms "first", "second" are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated, whereby features defined as "first", "second" may explicitly or implicitly include one or more such features, in the description of the invention "plurality" means two or more unless explicitly and specifically defined otherwise.

Referring to fig. 1-4, the present invention provides a technical solution: a lightweight high-strength multi-axis unmanned aerial vehicle structure comprises a longitudinal horn 1, a large-size tube fixing clamp 10 and an undercarriage V-shaped connecting piece 6, wherein the middle part of the longitudinal horn 1 is fixedly connected with the large-size tube fixing clamp 10, the top part of the large-size tube fixing clamp 10 is fixedly connected with an airplane center fixing piece 9, the inside of the airplane center fixing piece 9 is fixedly connected with a pin 12, the top part of the airplane center fixing piece 9 is fixedly connected with a transverse horn 2, the outer wall of the transverse horn 2 is fixedly connected with the undercarriage V-shaped connecting piece 6, the outer wall of the undercarriage V-shaped connecting piece 6 is fixedly connected with an undercarriage supporting rod 3, the outer wall of the undercarriage supporting rod 3 is fixedly connected with an undercarriage T-shaped connecting piece 7, the inside of the undercarriage T-shaped connecting piece 7 is fixedly connected with an undercarriage cross rod 4, the middle part of the undercarriage cross rod 4 is fixedly connected with a medium-size tube fixing clamp 11, and the outer wall of the medium-size tube fixing clamp 11 is fixedly connected with a fixing clamp connecting piece 8, the top of the transverse horn 2 is fixedly connected with four airplane power assemblies 5, and the four airplane power assemblies 5 are respectively distributed at two ends of the top of the longitudinal horn 1 and the top of the transverse horn 2.

Preferably, the length of the longitudinal arm 1 is connected with the transverse arm 2 through the central fixing part 9 of the airplane, the longitudinal arm 1 and the transverse arm 2 are not at the same height and are fixed in a crossed manner, the longitudinal arm 1 and the transverse arm 2 are two integral carbon tubes, a high-strength arm mechanism is composed of the longitudinal arm 1, the transverse arm 2, the central fixing part 9 of the airplane, a large-size tube fixing clamp 10 and a pin 12, the conventional quadrotor needs to divide and connect the arms, so that a gap exists between the arms of the unmanned aerial vehicle, the strength of the arms is further influenced, the impact resistance of the unmanned aerial vehicle to impact is reduced, the breakage of the arms caused by external impact of the unmanned aerial vehicle is greatly increased, the use quality of the unmanned aerial vehicle is influenced, by arranging the high-strength arm mechanism, the upper integral carbon tube and the lower integral carbon tube are respectively used as the longitudinal arm 1 and the transverse arm 2, namely, the arms in two directions are designed in an integrated manner, so that the separation and cutting between the arms are avoided, no gap exists in the arms in a single direction, the impact resistance of the arms is greatly enhanced, the weight is reduced and the strength of the arms is also increased by using an integral carbon tube as the arms, meanwhile, the longitudinal arms 1 and the transverse arms 2 are connected through the airplane center fixing piece 9 and the large-size tube fixing clamp 10, the airplane center fixing piece 9 is positioned at the center of the unmanned aerial vehicle structure, so that only a small amount of positive stress and z-direction torsional stress are overcome, the bending moment with the largest influence on the strength is borne by the uncut carbon tube, the strength requirement of a machined part is greatly reduced, wherein the large-size tube fixing clamp 10 is 22mm, the size of the pin 12 is phi 2.5 x 8, the mechanism can avoid the separation and cutting of the arms, and further increases the impact resistance of the arms, and the whole carbon tube is used as the horn, so that the strength of the horn is increased, the mass of the horn is reduced, the bending strength is increased, and the practicability of the device is improved.

Preferably, the undercarriage supporting rod 3 takes an undercarriage V-shaped connecting piece 6 as a center and is obliquely and externally fixed, four undercarriage T-shaped connecting pieces 7 are arranged and are respectively fixed on the outer wall of the undercarriage supporting rod 3, the undercarriage cross rod 4, the undercarriage V-shaped connecting piece 6, the undercarriage T-shaped connecting piece 7, a fixing clamp connecting piece 8 and a hollow pipe fixing clamp 11 form a supporting rod reinforcing mechanism, the existing unmanned aerial vehicle hanging part only uses four supporting rods for carrying out lifting jacking, the supporting rods are not reinforced, so that the supporting rods are easy to bend after being impacted for multiple times, the durability of the unmanned aerial vehicle is reduced, the undercarriage V-shaped connecting piece 6 is sleeved on the outer wall of the transverse arm 2 by the supporting rod reinforcing mechanism, namely, the undercarriage T-shaped connecting piece 7 can be sleeved on the outer wall of the undercarriage supporting rod 3, and the undercarriage supporting rod 3 is obliquely and externally fixed for supporting, the undercarriage supporting rods 3 and the contact surface can form triangular stable support, then the undercarriage V-shaped connecting piece 6 and the undercarriage T-shaped connecting piece 7 are respectively fastened through screws, so that the undercarriage cross rod 4 is fixed on the unmanned aerial vehicle, the transverse stress of the undercarriage supporting rods 3 is shared through the undercarriage cross rod 4, the possibility of deformation of the undercarriage cross rod 4 is reduced, meanwhile, the undercarriage supporting rods 3 have larger bottom space and can be hung on a large object, even a fixed wing aircraft is hung to assist vertical takeoff, the high-cost vertical takeoff and landing fixed wing aircraft is replaced to a certain extent, the mechanism can form stable triangular support, the bending of a V-shaped structure at the root part of the undercarriage is effectively reduced, the light weight is ensured, the load capacity of the undercarriage is increased, the practicability of the device is improved, and meanwhile, the bottom space of the unmanned aerial vehicle is larger, can be used to hold polytype mount, realize unmanned aerial vehicle's multipurpose nature, improve the practicality of device.

The working principle is as follows: firstly, by arranging a high-strength horn mechanism, an upper integral carbon tube and a lower integral carbon tube are respectively used as a longitudinal horn 1 and a transverse horn 2, namely, the horns in two directions are designed in an integrated mode, so that the separation and cutting between the horns are avoided, no gap exists in the inner part of the horn in a single direction, the impact resistance of the horn is greatly enhanced, the integral carbon tube is used as the horn, the weight is reduced, the strength of the horn is increased, meanwhile, the longitudinal horn 1 and the transverse horn 2 are connected through an airplane center fixing piece 9 and a large-size tube fixing clamp 10, as the airplane center fixing piece 9 is positioned in the center of an unmanned aerial vehicle structure, only a small amount of positive stress and z-direction torsional stress need to be overcome, and the bending moment with the largest influence on the strength is borne by the uncut carbon tube, the strength requirement of a machined part is greatly reduced, wherein the large-size tube fixing clamp 10 is 22mm, the size of the pin 12 is phi 2.5 x 8, the mechanism can avoid the separation and cutting of the horn, thereby increasing the shock resistance of the horn, and the whole carbon tube is used as the horn, so that the strength of the horn is increased, the mass of the horn is reduced, the bending strength is increased, and the practicability of the device is improved;

then, by arranging a support rod reinforcing mechanism, the landing gear V-shaped connecting piece 6 is sleeved on the outer wall of the transverse horn 2, namely the landing gear T-shaped connecting piece 7 is sleeved on the outer wall of the landing gear supporting rod 3, the landing gear supporting rod 3 is obliquely and externally fixed for supporting, so that the two landing gear supporting rods 3 and a contact surface form triangular stable support, then the landing gear V-shaped connecting piece 6 and the landing gear T-shaped connecting piece 7 are respectively fastened through screws, so that the landing gear cross rod 4 is fixed on the unmanned aerial vehicle, the transverse stress of the landing gear supporting rod 3 is shared through the landing gear cross rod 4, the possibility of deformation of the landing gear cross rod 4 is reduced, meanwhile, the bottom space of the landing gear supporting rod 3 is large, the landing gear supporting rod can be hung on an object with large volume, even a fixed wing aircraft is hung for assisting vertical takeoff, and a high-cost vertical take-off and landing fixed wing aircraft is replaced to a certain extent, this mechanism can form comparatively stable triangular supports, and the effectual burden of reducing undercarriage root V type structure is bent, increases the load capacity of undercarriage when guaranteeing the light weight, has improved the practicality of device, and unmanned aerial vehicle's bottom space is great simultaneously, can be used to hold multiple type carry, realizes unmanned aerial vehicle's multipurpose nature, has improved the practicality of device, and this kind is the theory of operation of this kind of lightweight high strength multiaxis unmanned aerial vehicle structure.

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 a lightweight high strength multiaxis unmanned aerial vehicle structure, includes vertical horn (1), tubaeform fixing clamp (10) and undercarriage V type connecting piece (6), its characterized in that: the middle part of the longitudinal machine arm (1) is fixedly connected with a large-size pipe fixing clamp (10), the top of the large-size pipe fixing clamp (10) is fixedly connected with an aircraft center fixing part (9), the inside of the aircraft center fixing part (9) is fixedly connected with a pin (12), the top of the aircraft center fixing part (9) is fixedly connected with a transverse machine arm (2), the outer wall of the transverse machine arm (2) is fixedly connected with an undercarriage V-shaped connecting part (6), the outer wall of the undercarriage V-shaped connecting part (6) is fixedly connected with an undercarriage supporting rod (3), the outer wall of the undercarriage supporting rod (3) is fixedly connected with an undercarriage T-shaped connecting part (7), the inside of the undercarriage T-shaped connecting part (7) is fixedly connected with an undercarriage cross rod (4), the middle part of the undercarriage cross rod (4) is fixedly connected with a medium-size pipe fixing clamp (11), the outer wall of the medium-sized tube fixing clamp (11) is fixedly connected with a fixing clamp connecting piece (8).

2. The structure of claim 1, wherein the unmanned aerial vehicle structure is characterized in that: the top of the transverse horn (2) is fixedly connected with four airplane power assemblies (5), and the four airplane power assemblies (5) are respectively distributed at the two ends of the top of the longitudinal horn (1) and the two ends of the top of the transverse horn (2).

3. The structure of claim 1, wherein the unmanned aerial vehicle structure is characterized in that: the length of the longitudinal machine arm (1) is connected with the transverse machine arm (2) through a central fixing piece (9) of the airplane, and the longitudinal machine arm (1) and the transverse machine arm (2) are not at the same height and are fixed in a crossed mode.

4. The structure of claim 1, wherein the unmanned aerial vehicle structure is characterized in that: the longitudinal machine arm (1) and the transverse machine arm (2) are two integral carbon tubes.

5. The structure of claim 1, wherein the unmanned aerial vehicle structure is characterized in that: the undercarriage supporting rod (3) takes an undercarriage V-shaped connecting piece (6) as a center and is obliquely and externally fixed.

6. The structure of claim 1, wherein the unmanned aerial vehicle structure is characterized in that: the undercarriage T-shaped connecting pieces (7) are four in number and are respectively fixed on the outer wall of the undercarriage supporting rod (3).