CN214241209U - Electronic big many rotor unmanned aerial vehicle fuselage of load - Google Patents
Electronic big many rotor unmanned aerial vehicle fuselage of load Download PDFInfo
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- CN214241209U CN214241209U CN202022550115.1U CN202022550115U CN214241209U CN 214241209 U CN214241209 U CN 214241209U CN 202022550115 U CN202022550115 U CN 202022550115U CN 214241209 U CN214241209 U CN 214241209U
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Abstract
The utility model belongs to the technical field of unmanned aerial vehicle, a many rotor unmanned aerial vehicle fuselages of electronic big load are disclosed, are provided with the girder, contain two girders in the fuselage structure, run through aircraft nose to tail, and the centre contains a plurality of lightening holes and relevant strengthening rib. Wherein the lightening hole can be used for structural lightening and matching with avionics wiring. The main beam is connected with the frame, the bottom plate, the connecting angle sheet, the connecting assembly and the connecting piece to form an integral structure of the machine body. The main beam is riveted with the frame by a plurality of rivets, the main beam is riveted with the bottom plate by a plurality of rivets, the main beam is riveted with the connecting angle piece by a plurality of rivets, the main beam is connected with the connecting component by a plurality of screws, and the main beam is connected with the connecting component by a plurality of screws. The utility model discloses the main material of fuselage is the aluminum alloy, has workable, the light, the high performance characteristics of intensity of quality, has that structural performance is good, stability is strong, the technology is ripe, the processing cost is low, easily advantages such as assembly and later stage maintenance simultaneously.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, especially, relate to an electronic big load many rotor unmanned aerial vehicle fuselage.
Background
Currently, an unmanned aircraft, referred to as an unmanned aerial vehicle (uav) or uas (unmanned airborne system), is an unmanned aircraft that is operated by a radio remote control device and an autonomous program control device. Compared with manned aircraft, unmanned aerial vehicle's application can effectively enlarge the home range, improves operating time, all has very big application space in fields such as military affairs, scientific research, government, commercial activities and individual consumer goods. Wherein many rotor unmanned aerial vehicle because simple structure, it is with low costs, and can the VTOL activity convenient, therefore have a lot of application scenes and very big development prospect.
Due to the vigorous development of brushless motors and lithium batteries in recent years, electric multi-rotor unmanned aerial vehicles have been rapidly developed and widely used. Most of the electric multi-rotor unmanned aerial vehicles on the market are electric multi-rotor unmanned aerial vehicles with the maximum takeoff weight of below 100kg and have a small amount of 300 kg-level electric multi-rotor unmanned aerial vehicles. In order to ensure light weight, the main material of the structure is carbon fiber composite material, but the main problems of high mold processing cost, complex composite material processing technology, incapability of ensuring quality and the like are caused, and the carbon fiber composite material part can not be maintained after being damaged once and can only be scrapped as a whole.
The fuselage of the existing large-scale electric multi-rotor unmanned aerial vehicle is made of carbon fiber composite materials, and has the following defects.
a. The processing cost is high: the carbon cloth or the prepreg cloth is complex to manufacture and high in cost in the aspect of raw materials, a mold is needed in the aspect of molding and manufacturing, the mold is generally made of metal materials and needs to be designed and processed independently, and the large-scale mold has high processing cost. The processing equipment cost and a large amount of labor cost of the carbon fiber composite material are also high;
b. the processing technology is complex: the composite material product is normally processed and manufactured on a mould and needs to undergo the process links of pretreatment, cutting, paving, sealing, vacuum pressurization, heating and fixation, demoulding, polishing and trimming, forming by a tool, paint spraying and the like, the process flow links are numerous and can not be separated from a large amount of manpower, and the processing technology is relatively complex;
c. quality problems are as follows: the method is influenced by more complicated processing technology and manual participation, and the rejection rate of finished products made of the composite material of the whole machine is higher;
d. difficulty in inspection and maintenance: the carbon fiber composite material can be designed in a diversified manner according to the shape of a finished product due to the easy processability, so that the finished product of the carbon fiber composite material is integrally paved and molded when the whole machine is manufactured, and the whole carbon fiber composite material is lagged behind in the aspects of inspection and maintenance of the carbon fiber composite material in the technical aspect. This causes that once the structural part is damaged, effective maintenance can not be carried out, and only the complete machine is scrapped, which causes great waste.
Through the above analysis, the problems and defects of the prior art are as follows:
(1) the processing cost is high;
(2) the processing technology is complex;
(3) the rejection rate is high;
(4) inspection and maintenance are difficult.
(5) There is no better choice of machine body mechanical structure for molding.
The difficulty in solving the above problems and defects is:
at present, the composite material structure of the body of a large multi-rotor unmanned aerial vehicle is difficult to reduce the cost, the complexity of a processing process, the rejection rate and the maintenance difficulty and the maintenance cost, and a better formed mechanical structure of the body is not available.
The significance of solving the problems and the defects is as follows:
can provide one kind and have workable, with low costs, the quality is light, intensity is high, structural performance is good, stability is strong, the technology is ripe, the processing cost is low, easily advantages such as assembly and later stage maintenance fill some technical vacancies of current large-scale many rotor unmanned aerial vehicle fuselage structure.
SUMMERY OF THE UTILITY MODEL
In order to solve the problem that prior art exists, the utility model provides an electronic many rotor unmanned aerial vehicle fuselage of big load.
The utility model discloses a realize like this, a many rotor unmanned aerial vehicle fuselage of electronic big load is provided with:
a main beam;
two ends of the frame are riveted and fixed with the two main beams through rivets;
the bottom plate is riveted and fixed at the lower parts of the two main beams through rivets;
coupling assembling is fixed in through rivet riveting bottom plate lower part corner, this coupling assembling is used for installing the unmanned aerial vehicle undercarriage, like common skid formula undercarriage.
The connecting piece is fixed in through rivet riveting in the girder outside, this connecting piece is used for installing unmanned aerial vehicle rotor support arm or duct.
The fuselage material of the utility model is not limited to aluminum alloy material, but also can be metal or nonmetal materials such as titanium alloy, steel, nylon and the like.
Furthermore, two main beams are arranged and arranged in parallel and penetrate through the machine head to the machine tail; and the middle part of the main beam is provided with lightening holes and reinforcing ribs.
Furthermore, eight frames are arranged and distributed in sequence from the machine head to the machine tail, and a plurality of lightening holes are formed in the middle of the frames. The space enclosed by the frame and the main beam can prevent avionics equipment.
Furthermore, the upper part of the joint of the frame and the main beam is fixedly provided with ten connecting angle pieces through rivet riveting, and the connecting angle pieces are arranged.
Furthermore, the upper parts of the connecting angle pieces at the paired angle positions are fixedly riveted with supporting rods through rivets, and the number of the supporting rods is four.
Furthermore, the lower part of the bottom plate is riveted with six mounting cross beams through rivets, and the mounting cross beams are uniformly and orderly arranged from the machine head to the machine tail. The mounting beam can be used for mounting the battery pack.
Furthermore, the connecting components are four in number and are riveted at the corners of the lower part of the floor respectively through rivets.
Furthermore, the six connecting pieces are arranged in the middle of the machine body structure and on the outer sides of the two main beams, and are uniformly and symmetrically arranged at the head, the center and the tail of the main beams.
Another object of the utility model is to provide an utilize unmanned aerial vehicle of above-mentioned unmanned aerial vehicle fuselage manufacturing.
Combine foretell all technical scheme, the utility model discloses the advantage that possesses and positive effect are:
(1) the utility model provides a many rotor unmanned aerial vehicle of electronic big load structure scheme. The main material of the machine body is aluminum alloy which has the performance characteristics of easy processing, light weight and high specific strength, but is not limited to aluminum alloy materials, and the materials can be replaced according to actual load. The steel plate is manufactured by production and assembly processes such as machining, metal plate machining, riveting and the like, and has the advantages of good structural performance, strong stability, mature process, light weight, low processing cost, easiness in assembly, later maintenance and the like.
(2) The cost is reduced: the aluminum alloy material mainly adopts electrolytic aluminum technology at present, and raw and other materials low cost, and aluminium in the trade the utility model discloses a processing technology be machining and panel beating, and processing technology is simple and ripe. The utility model discloses assembly process is rivet riveting and bolt spiro union, assembles simple low cost.
(3) The processing technology is simplified, and the production efficiency is improved: compared with composite materials, the utility model discloses a fuselage overall assembly can be accomplished to only need a small amount of frock location to the structure after the spare part shaping, adopts riveting and spiro union to be ripe simple and convenient assembly process, can effectively simplify processing technology and improve production efficiency.
(4) The quality is ensured: the quality control can be distributed in two links through the utility model, the first link is a part processing link, and the finished parts processed by machining and sheet metal processing are subjected to quality inspection to ensure the quality; the second link is a machine body assembly link, and timely quality inspection is carried out in the machine body assembly link to ensure quality. The quality inspection link is clear and effective, and the product quality can be ensured.
(5) Convenient inspection and maintenance: the utility model discloses a structure is based on the metal property of aluminum alloy material itself and locking when assembling etc. mark location, can carry out quick inspection discovery problem through forms such as range estimation, hand touch, strike. When partial damage occurs, effective maintenance can be performed by directly disassembling and replacing the relevant parts.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments of the present application will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings can be obtained from the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a fuselage of an electric heavy-load multi-rotor unmanned aerial vehicle provided by an embodiment of the present invention;
fig. 2 is a schematic structural view of the other side of the body of the electric heavy-load multi-rotor unmanned aerial vehicle provided by the embodiment of the present invention;
in the figure: 1. a main beam; 2. framing; 3. a base plate; 4. connecting the corner pieces; 5. a support bar; 6. mounting a cross beam; 7. a connecting assembly; 8. a connecting member.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Problem to prior art existence, the utility model provides a many rotor unmanned aerial vehicle fuselage of electronic big load, it is right to combine the figure below the utility model discloses do detailed description.
As shown in fig. 1-2, the utility model provides an electronic many rotor unmanned aerial vehicle fuselage of big load includes: girder 1, frame 2, bottom plate 3, connection angle piece 4, bracing piece 5, carry crossbeam 6, coupling assembling 7, connecting piece 8.
Example 1
The machine body structure of the embodiment comprises two main beams 1 which penetrate through a machine head to a machine tail and are integrally machined and manufactured by aluminum alloy blocks, and the middle of each main beam comprises a plurality of lightening holes and related reinforcing ribs. Wherein the lightening hole can be used for structural lightening and matching with avionics wiring. The main beam 1 is connected with the frame 2, the bottom plate 3, the connecting angle sheet 4, the connecting component 7 and the connecting component 8 to form an integral structure of the machine body, and mainly bears the bending moment and the torsion of the whole machine. The main beam 1 is riveted with the frame 2 by a plurality of rivets, the main beam 1 is riveted with the bottom plate 3 by a plurality of rivets, the main beam 1 is riveted with the connecting angle piece 4 by a plurality of rivets, the main beam 1 is connected with the connecting component 7 by a plurality of screws, and the main beam 1 is connected with the connecting component 8 by a plurality of screws.
Example 2
On the basis of the embodiment 1, the fuselage structure of the embodiment comprises eight frames 2 which are orderly arranged from the nose to the tail and are made of aluminum alloy sheet metal, and the middle of the fuselage structure comprises a plurality of lightening holes, wherein the lightening holes can be used for structural lightening and are matched with avionic wiring. The frame 2 is connected with the main beams 1 and the connecting angle pieces 4 to form an integral structure of the machine body, mainly supports the transverse width of the machine body, enhances the bending resistance and torsion resistance of the machine body structure, and transmits the moment between the two main beams 1. The frame 2 is riveted with the main beam 1 by a plurality of rivets, and the frame 2 is riveted with the connecting angle piece 4 by a plurality of rivets.
Example 3
On the basis of embodiment 1, the fuselage structure of this embodiment comprises a bottom plate 3, which is arranged below the main beams 1 and the frames 2 and is manufactured from a single thin aluminum plate. The bottom plate 3 can be provided with the avionics equipment and the cable routing, and the inertial force caused by the avionics equipment when the unmanned aerial vehicle flies is borne. The bottom plate 3 is connected with the main beams 1 and the connecting angle pieces 4 to form an integral structure of the machine body, the bottom plate 3 seals the lower bottom surface of the machine body structure, the rigidity of the whole machine can be effectively improved, the bending and torsion resistance of the whole machine can be enhanced, and the torque between the two main beams 1 and the machine body frame 2 can be transferred. The bottom plate 3 is riveted with a plurality of rivets on the main beam 1, and the bottom plate 3 is riveted with a plurality of rivets on the connecting angle piece 4.
Example 4
On the basis of embodiment 1, the fuselage structure of this embodiment contains ten connecting angle pieces 4, and the connecting angle pieces 4 are distributed in order along with the position of the frame 2 and are made of aluminum alloy sheet metal. The connecting angle piece 4 is connected with the main beam 1, the frame 2 and the support rod 5 to form an integral structure of the machine body and transfer the moment among the main beam 1, the frame 2 and the support rod 5. The connecting angle piece 4 is riveted with a plurality of rivets on the main beam 1, the connecting angle piece 4 is riveted with a plurality of rivets on the frame 2, and the connecting angle piece 4 is connected with a plurality of screws on the support rod 5.
Example 5
On the basis of embodiment 1, the fuselage structure of this embodiment contains four bracing pieces 5, arranges the top at the fuselage structure, by the manufacturing of aluminum alloy sheet metal. The supporting rod 5 is connected with the connecting angle piece 4 to form an integral structure of the machine body, the supporting rod 5 can improve the rigidity of the whole machine, meanwhile, the opening structure of the machine body can be guaranteed, and the mounting of avionics equipment inside the machine body structure and the arrangement of cable routing are facilitated. The support rod 5 is connected with the corner pieces through a plurality of bolts.
Example 6
On the basis of embodiment 1, the fuselage structure of this embodiment contains six carry crossbeams 6, and the aircraft nose is to the even orderly arrangement of tail, by the manufacturing of aluminum alloy sheet metal. The mounting cross beam 6 is connected with the bottom plate 3 to form an integral structure of the machine body, and mainly used for mounting the power battery. The mounting cross beam 6 is riveted with the bottom plate 3 by a plurality of rivets.
Example 7
On the basis of embodiment 1, the fuselage structure of this embodiment includes four connecting assemblies 7, which are arranged at four ends of the bottom of the fuselage structure and machined from aluminum alloy blocks. The connecting assembly 7 is connected with the main beam 1 to form an integral structure of the airplane body and mainly used for connecting an undercarriage structure. The connecting component 7 is connected with the main beam 1 through a plurality of screws.
Example 7
On the basis of the embodiment 1, the fuselage structure of the embodiment comprises six connecting pieces 8 which are arranged in the middle of the fuselage structure and outside the two main beams 1, are uniformly and symmetrically arranged at the head, the center and the tail of the main beams 1, and are machined and manufactured by aluminum alloy blocks. Connecting piece 8 is connected with girder 1, constitutes fuselage overall structure, and the main effect is the power pack of connecting, lift, torsion, vibrations that produce by single power pack when transmission unmanned aerial vehicle flies and the gravity of power pack when unmanned aerial vehicle stews. The connecting piece 8 is connected with the main beam 1 through a plurality of screws.
The utility model discloses coupling assembling is used for installing the undercarriage, and the connecting piece position can satisfy the installation of multiple horn according to design requirement arbitrary adjustment position and quantity, and the carry crossbeam can be hung at group battery and other task equipment. Each part of the utility model is machined, the machining process is simple and mature, and the cost is low; the assembly process is rivet riveting and bolt screwing, the assembly is simple, the cost is low, the processing process is effectively simplified, and the production efficiency is improved; the utility model discloses the structure is connected based on machined part and conventional connecting piece, when the part damage appears, can effectively maintain through the form of direct dismantlement and the relevant spare part of replacement, and the maintenance cost is low.
In the description of the present invention, "a plurality" means two or more unless otherwise specified; the terms "upper", "lower", "left", "right", "inner", "outer", "front", "rear", "head", "tail", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be covered within the protection scope of the present invention by those skilled in the art within the technical scope of the present invention.
Claims (8)
1. The utility model provides a many rotor unmanned aerial vehicle fuselage of electronic big load, its characterized in that, many rotor unmanned aerial vehicle fuselage of electronic big load is provided with:
a main beam;
two ends of the frame are riveted and fixed with the two main beams through rivets;
the bottom plate is riveted and fixed at the lower parts of the two main beams through rivets;
the connecting assembly is riveted and fixed at the lower corner of the bottom plate through a rivet;
and the connecting piece is riveted and fixed on the outer side of the main beam through a rivet.
2. The fuselage of the electric heavy-duty multi-rotor unmanned aerial vehicle of claim 1, wherein there are two main beams, and the two main beams are arranged in parallel and run through the fuselage to the tail; and the middle part of the main beam is provided with lightening holes and reinforcing ribs.
3. The fuselage of an electric heavy-duty multi-rotor unmanned aerial vehicle according to claim 1, wherein the frames are arranged and distributed in an orderly manner from the nose to the tail, and a plurality of lightening holes are formed in the middle.
4. The fuselage of an electric heavy-load multi-rotor unmanned aerial vehicle according to claim 1, wherein the upper part of the joint of the frame and the main beam is fixed with a connecting fillet by riveting with a rivet.
5. The airframe of an electric heavy load multi-rotor unmanned aerial vehicle of claim 4, wherein the upper portion of said connecting gusset in the pair of angular positions is riveted with a support rod by a rivet.
6. The fuselage of the electric heavy-load multi-rotor unmanned aerial vehicle of claim 1, wherein the lower part of the bottom plate is riveted with a mounting cross beam through rivets, and the mounting cross beam is uniformly and orderly arranged from the nose to the tail.
7. The airframe of claim 1 wherein there are four of said attachment assemblies, each riveted at a lower corner of the floor by a rivet, for mounting the landing gear of the drone.
8. The fuselage of an electric heavy-duty multi-rotor unmanned aerial vehicle according to claim 1, wherein the connecting pieces are arranged in the middle of the fuselage structure, outside the two main beams, at the head, the center and the tail of the main beams, and are symmetrically arranged, and the connecting pieces are used for installing rotor arms or ducts of the unmanned aerial vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022550115.1U CN214241209U (en) | 2020-11-06 | 2020-11-06 | Electronic big many rotor unmanned aerial vehicle fuselage of load |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022550115.1U CN214241209U (en) | 2020-11-06 | 2020-11-06 | Electronic big many rotor unmanned aerial vehicle fuselage of load |
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| CN214241209U true CN214241209U (en) | 2021-09-21 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112298523A (en) * | 2020-11-06 | 2021-02-02 | 一飞智控(天津)科技有限公司 | Electronic big many rotor unmanned aerial vehicle fuselage of load |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112298523A (en) * | 2020-11-06 | 2021-02-02 | 一飞智控(天津)科技有限公司 | Electronic big many rotor unmanned aerial vehicle fuselage of load |
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