CN210822723U - Integrated machine body for multi-rotor unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses an integrated body for a multi-rotor unmanned aerial vehicle, which comprises a hollow and communicated body, a first central support arm, a second central support arm and a plurality of rotor mounting arms arranged at the periphery of the body; first central support arm and second central support arm all are unanimous with the width direction of organism body, and the organism body has been separated in proper order along length direction by first central support arm and second central support arm and has formed electronic compartment, fuel oil cabin and engine compartment, and rotor installation arm is solid of revolution structure and free end tip is formed with the installation location breach. The machine body is integrally formed by a carbon fiber material through a die pressing process, the whole machine body is of an integrated structure, the strength of the machine body is high, and the manufacturing process is convenient; and the organism has separated in proper order and has formed electronic cabin, fuel oil cabin and engine compartment, divides the organism into different modules like this for follow-up unmanned aerial vehicle's modularization installation operation is simple more, convenient and quick.

Description

Integrated machine body for multi-rotor unmanned aerial vehicle

Technical Field

The utility model relates to an organism, concretely relates to integral type organism that many rotor unmanned aerial vehicle used belongs to unmanned air vehicle technical field.

Background

The unmanned aerial vehicle is an unmanned aerial vehicle controlled by a radio remote control device or an onboard computer program control system, has the advantages of simple structure, small volume, good maneuverability, low manufacturing cost, strong environment adaptability and the like, can complete a plurality of tasks which are difficult to be completed by piloted aircrafts, and has an expanded application range to various fields such as military use, civil use and the like.

However, due to the limitation of the structure of the traditional material and the processes of gluing, curing and the like, the impact damage tolerance of the unmanned aerial vehicle is generally low, the unmanned aerial vehicle can easily damage the body structure after landing and recovery, and the application of the unmanned aerial vehicle in quick response of individual combat in a complex environment is limited. The existing unmanned aerial vehicle body structure and the connection mode are as follows: the machine body is fixed by the upper and lower center plates by screws; the machine arm is formed by connecting an upper plate and a lower plate or is formed by a carbon fiber pipe; the motor base is also formed by fixing two plates through screws; the machine body and the machine arm, and the motor base and the machine arm are all fixed through screw connection.

The Chinese patent with application number 2015107020602 discloses an unmanned aerial vehicle body, which comprises a cabin, a central support arm, a cantilever, an undercarriage, a buoy, a rotor wing and an anti-collision ring, wherein the central support arm is arranged on the periphery of the cabin and is of a cross hollow structure, the cantilever is of a Y-shaped hollow structure, one end of the cantilever is inserted into the central support arm and is connected with the cabin through the central support arm, and the other two ends of the cantilever are connected with the inner periphery of the anti-collision ring through the anti-collision support arm; the upper end of the landing gear is connected with the central support arm, and the lower end of the landing gear is fixed with the buoy; the rotor wing driven by the motor is arranged on the cantilever, and the unmanned aerial vehicle has the advantages of light weight, high strength, amphibious property and the like when being applied to the manufacture of an unmanned aerial vehicle body.

The unmanned aerial vehicle organism structure on the existing market is that the aggregate erection constitutes, all needs to use a large amount of instruments at installation, dismantlement in-process, and the installation is wasted time and energy with the dismantlement process, work efficiency is low, the operation is inconvenient. In view of the above, there is a need for an improved structure of the machine body.

Disclosure of Invention

The utility model aims at providing a novel integral type organism for many rotors unmanned aerial vehicle to the above-mentioned problem that exists among the prior art.

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

the utility model provides an integral type organism for many rotors unmanned aerial vehicle, includes inside cavity and link up: the aircraft comprises an aircraft body, a first central support arm, a second central support arm and a plurality of rotor wing mounting arms which are respectively arranged on the periphery of the aircraft body; first central authorities support arm and second central authorities support arm all are unanimous with the width direction of organism body, and this organism body has been separated in proper order along length direction by first central authorities support arm and second central authorities support arm and has formed electronic compartment, fuel oil cabin and engine compartment, rotor installation arm is formed with installation location breach for solid of revolution structure and free end tip.

Preferably, the second central arm and the right side edge of the machine body parallel to the second central arm are provided with a protruding part in the direction towards the installation of the engine, so that the installation position of the engine can be effectively limited when the engine is installed.

Preferably, the cross section of the main body of the machine body is square, so that the whole strength of the machine body is higher.

More preferably, the quantity of aforementioned rotor installation arm is 6, and wherein four set up respectively in four edges of organism body, and two set up in organism body length direction's intermediate position in addition, have guaranteed unmanned aerial vehicle at the stationarity of the whole organism of during operation.

Still preferably, the junction of aforementioned rotor installation arm and organism body is formed with arc transition portion, has strengthened the joint strength of rotor installation arm and organism body looks junction.

Further preferably, a plurality of observation guide holes are formed on the surface of the machine body, so that the machine body is more convenient to operate and observe when a lead is arranged in the machine body.

Still further preferably, the bottom of aforementioned second central support arm is formed with power line interface, and first central support arm is provided with the signal line interface in the direction towards the electron cabin, can make the holistic wiring design of unmanned aerial vehicle more convenient and conceal like this, has improved the compactness of whole overall arrangement.

Still further preferably, the machine body is made of carbon fiber materials through a die pressing process in an integrated mode, the integral manufacturing process is more convenient, the obtained machine body is of an integrated structure, and the integral strength is higher.

And, above-mentioned organism is inside to be provided with a plurality of pre-buried inserts to further optimize the mechanical properties of organism, satisfied high-end market's demand.

The utility model discloses an useful part lies in:

i) the machine body of the utility model is made of carbon fiber material through mould pressing process, the whole machine body is of an integral structure, the strength of the machine body is high, and the manufacturing process is convenient;

ii) the integrated unmanned aerial vehicle body is sequentially divided by the first central support arm and the second central support arm to form an electronic cabin, a fuel cabin and an engine cabin, and the integrated unmanned aerial vehicle body is divided into different modules, so that the subsequent modularized installation operation of the unmanned aerial vehicle is simpler, more convenient and faster;

iii) an installation positioning notch is formed at the end part of the free end of the rotor wing installation arm, so that a reliable and accurate positioning reference is provided for the positioning of the rotor wing installation, and the installation is faster and the position is more accurate;

iv) the pipeline cross-sectional shape of organism main part is square, and the organism material is carbon fiber material, and this material has characteristics such as high temperature resistant, antifriction, electric conduction, heat conduction and corrosion resistance, and density is little, therefore the specific strength and the specific modulus of organism are high, have given the more excellent mechanical properties of unmanned aerial vehicle organism.

Drawings

Fig. 1 is a perspective view of an embodiment of an integrated body for a multi-rotor unmanned aerial vehicle according to the present invention;

FIG. 2 is a bottom view of the embodiment of FIG. 1;

FIG. 3 is a front view of the embodiment shown in FIG. 1;

FIG. 4 is a side view of the embodiment shown in FIG. 1;

FIG. 5 is a cross-sectional view A-A of FIG. 2;

FIG. 6 is a cross-sectional view taken along line B-B of FIG. 3

The meaning of the reference symbols in the figures:

the method comprises the following steps of 1-a first central support arm, 2-a second central support arm, 3-an electronic cabin, 4-a fuel cabin, 5-an engine cabin, 6-an observation guide hole, 7-a rotor wing installation arm, 8-a signal line interface, 9-a pre-embedded insert, 10-an arc transition part, 11-a power line interface, 12-a machine body, 13-a protruding part and 14-an installation positioning notch.

Detailed Description

The invention will be further described with reference to the following drawings and specific examples:

in the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used merely for convenience of description and for 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 therefore, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

The integrated body for a multi-rotor unmanned aerial vehicle according to the present embodiment is, as shown in fig. 1 to 4, composed of a body 12, a first central arm 1, a second central arm 2, and a rotor mounting arm 7. Unmanned aerial vehicle organism is made through mould pressing technology integrated into one piece by carbon fiber material, its inside structure for cavity and link up, first central authorities support arm 1 and second central authorities support arm 2 are unanimous with organism body 12's width direction, and organism body 12 has been separated into electronic compartment 3 in proper order along length direction by first central authorities support arm 1 and second central authorities support arm 2, fire oil compartment 4 and engine compartment 5, so, adopt the modularization operation when just making things convenient for follow-up unmanned aerial vehicle integral erection, improve installation convenience and reliability. Second central authorities support arm 2 and the organism body 12 right side limit parallel with second central authorities support arm are formed with protruding portion 13 in the direction of orientation engine installation, conveniently carry on spacingly to the mounted position of oil commentaries on classics electric unmanned aerial vehicle's generator and engine.

As shown in fig. 1 and 2, specifically in the present embodiment, there are 6 rotor mounting arms 7 provided around the body, so that the body is suitable for a six-rotor drone. If set up the quantity of its rotor installation arm 7 into 4, then the organism can be applicable to four rotor unmanned aerial vehicle, and this is that the very ability of technical personnel in the field understands and implements, also falls into the utility model discloses a protection scope, the no longer redundance here. In this embodiment, wherein 4 rotor installation arms 7 set up respectively in 4 edges of organism body 12, and 2 set up in organism body 12 length direction's intermediate position in addition, make the position distribution of rotor even, and whole unmanned aerial vehicle's stationarity is higher.

Referring to fig. 1, the organism is formed with installation location breach 14 all around the free end tip of 6 rotor installation arms 7 that set up, and the reference location position when providing the rotor installation is used for installing the unmanned aerial vehicle rotor for the installation is faster, more reliable and the position is more accurate. And, be formed with arc transition portion 10 at the department that rotor installation arm 7 is connected with organism body 12, so can further optimize the bulk strength of organism.

As described above, the interior of the unmanned aerial vehicle body of the utility model is a hollow structure, which is convenient for arranging various electric wires, signal lines and other flat cables of the unmanned aerial vehicle, wherein the first central support arm 1 is provided with an electronic cabin signal wiring port 8 in the direction towards the electronic cabin 3; the bottom of the second central support arm 2 is formed with a power cord interface 11. Meanwhile, a plurality of observation guide holes 6 are formed on the surface of the machine body 12, so that the flat cable in the machine body can be observed, guided and adjusted conveniently.

On concrete this integral type organism, electronic cabin 3 is the position of installation unmanned aerial vehicle electronic components, and unmanned aerial vehicle electronic components installs the back, is connected with the inside wire of organism body 12 through electronic cabin signal wiring mouth 8 that first central authorities support arm 1 set up in the direction towards electronic cabin 3 to control unmanned aerial vehicle and accomplish various works. Fuel oil cabin 4 is the required fuel position of installation unmanned aerial vehicle when flying, and the fuel provides the energy for the work of unmanned aerial vehicle machine oil commentaries on classics electric engine, guarantees that unmanned aerial vehicle can normally work. The engine compartment 5 is a place where the oil-to-electricity engine is installed, and works by fuel delivered through the fuel compartment 4. The power line interface 11 that the oil changes 2 bottoms of support arm and forms through the second after the installation of electricity engine links to each other with the wire in organism body 12, and the electric current that the oil in the engine cabin 5 changes the electricity engine and produces passes through power line interface 11 and carry unmanned aerial vehicle's corresponding part, provides lasting power for unmanned aerial vehicle's work.

In order to further optimize the mechanical performance of the machine body, a plurality of embedded inserts 9 are arranged inside the machine body 12, as shown in fig. 5 and 6, the embedded inserts 9 are reinforcing components embedded in carbon fiber materials in advance during die pressing, the specific arrangement positions of the embedded inserts 9 can be flexibly adjusted according to the actual requirements of the machine body, and the embedded inserts are mainly arranged at the positions of joints with weak mechanical performance, the middle positions of longer components and the like.

To sum up, the utility model discloses an organism is an integral type organism for many rotor unmanned aerial vehicle, and the whole material of organism adopts the material of carbon fiber, makes through mould pressing technology integrated into one piece, and the line is walked to inside, plays the guard action to the wire, 6 rotors of symmetric distribution for unmanned aerial vehicle can be more steady when flying. The modularized organism makes the operation more simple and convenient, has satisfied unmanned aerial vehicle to organism stability and simple installation's demand.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It should be understood by those skilled in the art that the above embodiments do not limit the present invention in any way, and all technical solutions obtained by adopting equivalent replacement or equivalent transformation fall within the protection scope of the present invention.

Claims (10)

1. An integrated machine body for a multi-rotor unmanned aerial vehicle is characterized by comprising a machine body, a first central support arm, a second central support arm and a plurality of rotor wing mounting arms, wherein the machine body is hollow and penetrates through the interior of the machine body; first central authorities support arm and second central authorities support arm all are unanimous with the width direction of organism body, and this organism body has been separated in proper order along length direction by first central authorities support arm and second central authorities support arm and has formed electronic compartment, fuel oil cabin and engine compartment, rotor installation arm is formed with installation location breach for solid of revolution structure and free end tip.

2. The airframe as recited in claim 1, wherein the second center arm and a right side of the airframe body parallel to the second center arm are formed with protrusions in a direction toward engine mounting.

3. The airframe of claim 1, wherein the main body portion of the airframe body is square in cross-section.

4. The airframe according to claim 1, wherein the number of said rotor arms is 6, four of said arms are disposed at four corners of the airframe body, and the other two arms are disposed at the middle of the airframe body in the length direction.

5. The airframe as recited in claim 4, wherein said rotor mounting arms are formed with curved transitions at the junction with the airframe body.

6. The airframe of claim 1, wherein a plurality of viewing guide holes are formed in a surface of the airframe body.

7. The airframe as recited in claim 1, wherein a power cord interface is formed on a bottom portion of said second center arm.

8. The airframe as recited in claim 1, wherein said first center arm is configured with a signal wire interface in a direction toward the electronics compartment.

9. The airframe as recited in claim 1, wherein the airframe is formed from a carbon fiber material by a molding process.

10. The integrated airframe of claim 9, wherein a plurality of pre-embedded inserts are disposed inside the airframe.

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