CN210027900U

CN210027900U - Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment

Info

Publication number: CN210027900U
Application number: CN201920671149.0U
Authority: CN
Inventors: 蔡建东; 张丹
Original assignee: Zhijiang Laboratory
Current assignee: Zhijiang Laboratory
Priority date: 2019-05-13
Filing date: 2019-05-13
Publication date: 2020-02-07
Anticipated expiration: 2029-05-13

Abstract

The utility model discloses a battery compartment of many rotors manned vehicle, the battery compartment includes upper flip apron, skeleton upper edge base plate, divide the electric module, field style of calligraphy metal framework, the battery module, fly to control module and lower floor's base plate, upper flip apron and skeleton upper edge base plate set up at field style of calligraphy metal framework upper surface, lower floor's base plate is fixed at field style of calligraphy metal framework lower surface, four enclose into the inner space of four quadrants, four group's battery modules are fixed mounting respectively in the inner space of every quadrant, two divide the electric module of fixed mounting on the upper flip apron that each group battery module corresponds, be provided with the electrically conductive copper bar on every divides the electric module, upper flip apron and field style of calligraphy metal framework's both sides rotatable coupling, after upper flip apron turns down, the electrically conductive copper bar can communicate with the electrically conductive copper bar on the divide the electric module; the flight control module is fixed on the lower surface of the lower substrate. This battery compartment sound construction, the simple operation, it is convenient to maintain.

Description

Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment

Technical Field

The utility model relates to an aircraft technical field especially relates to a many rotors manned vehicle's battery compartment and contain this battery compartment's manned vehicle.

Background

The multi-rotor manned aircraft has wide application prospect in the low-altitude traffic field. The existing multi-rotor manned aircraft is mainly divided into electric drive and oil-electricity hybrid drive according to the form of power energy. The electric-driven multi-rotor manned aircraft has the advantages of cleanness, environmental protection, convenience in maintenance and the like. The whole structure and the battery bin layout of the electric-driven multi-rotor aircraft are dense and inseparable, and the existing structure scheme is mainly divided into two types by taking the relative position of a cabin and a paddle plane as a basis: one type is that the cabin is above the battery compartment, the battery compartment is wrapped in a main frame, the main frame is connected with a machine arm provided with a lift assembly (a motor and a propeller), and is represented by CN 205311899U; the other type is that the cabin is under the battery compartment, the battery compartment is designed together with a main frame, and similarly, the main frame is connected with a machine arm provided with a lifting assembly, represented by CN 206750136U. In the first type of complete machine framework, the cabin is distributed above the battery cabin, the advantage is that the maneuverability and the operation performance are good, and the disadvantage is that great fatal potential safety hazards exist, for example, the cabin can be directly hit when the paddle is shot in the air, and passengers are inconvenient to escape when the rotating speed of the paddle is out of control. In the second type of framework, the cabin is distributed below the battery cabin, and the aircraft has the advantages of good attitude stability and high safety level, and has the defects of inconvenient taking and placing of the battery and high structural design difficulty.

SUMMERY OF THE UTILITY MODEL

The utility model provides a not enough to prior art, the utility model provides a many rotors manned vehicle's battery compartment and contain this battery compartment's manned vehicle, this aircraft mechanical properties is good, long voyage time, carry great, the security is better.

The purpose of the utility model is realized through the following technical scheme:

a battery compartment of a multi-rotor manned aircraft is characterized by comprising an upper-layer flip cover plate, a framework upper-layer edge substrate, power distribution modules, a grid-shaped metal framework, battery modules, a flight control module and a lower-layer substrate, wherein the upper-layer flip cover plate and the framework upper-layer edge substrate are arranged on the upper surface of the grid-shaped metal framework, the lower-layer substrate is fixed on the lower surface of the grid-shaped metal framework, the upper-layer flip cover plate, the framework upper-layer edge substrate, the grid-shaped metal framework and the lower-layer substrate enclose an inner space with four quadrants, four groups of battery modules are respectively and fixedly arranged in the inner space of each quadrant, two power distribution modules are fixedly arranged on the upper-layer flip cover plate corresponding to each group of battery modules, a conductive copper bar is arranged on each power distribution module, and the upper-layer flip cover plate is rotatably connected with two sides of the grid-shaped metal framework, when the flip cover plate on the upper layer is turned down, the conductive copper bar can be communicated with the conductive copper bar on the distribution module; the flight control module is fixed on the lower surface of the lower substrate.

Furthermore, the metal framework shaped like a Chinese character 'tian' is made of aluminum alloy, magnesium aluminum alloy or carbon steel.

Further, the upper layer edge substrate and the lower layer substrate are both made of carbon fiber composite materials.

Furthermore, the metal framework shaped like a Chinese character 'tian' is composed of a peripheral circle of framework side plates, framework longitudinal beams, framework cross beams and a cross, and all the components are detachably connected.

Furthermore, a plurality of framework hangers are uniformly arranged on the inner side surface of the framework side plate and used for being connected with the cabin.

Furthermore, a plurality of battery mounting positions are further arranged on the inner side surfaces of the framework side plate and the cross.

The multi-rotor manned aircraft is characterized by comprising the battery bin, and further comprising a power module, the battery bin, a cabin and an undercarriage, wherein the power module is directly connected with the battery bin and arranged at the same height to form a flying platform; the cabin is fixed below the battery cabin, and the landing gear is installed at the bottom of the cabin.

The utility model has the advantages as follows:

the battery compartment of the multi-rotor manned aircraft adopts the metal framework shaped like the Chinese character 'tian', so that the whole structure of the battery compartment is firm, the rigidity and the strength are high, the battery module 25 can be more conveniently taken and placed through the upper layer flip cover plate, and the flight control module is fixed on the lower surface of the lower layer substrate, so that the maintenance is convenient; and the battery compartment can be directly connected with the power module, so that the length of the power cable is shortened.

Drawings

FIG. 1 is a schematic view of the overall structure of the multi-rotor manned vehicle of the present invention;

FIG. 2 is a side view of the overall structure of the multi-rotor manned vehicle of the present invention;

FIG. 3 is a schematic view of the folded horn;

FIG. 4 is a schematic structural view of a battery compartment;

FIG. 5 is a schematic view of the battery compartment after the battery cover is opened;

FIG. 6 is a schematic structural view of a battery compartment grid-shaped framework;

in the figure, 1-power module, 2-battery cabin, 3-cabin, 4-undercarriage, 11-power assembly, 12-horn assembly, 21-upper layer flip cover plate, 22-framework upper layer edge base plate, 23-distribution module, 24-field-shaped metal framework, 25-battery module, 26-flight control module, 27-lower layer base plate, 31-seat, 111-motor seat, 112-motor, 113-electric regulation, 114-propeller, 121-horn tube, 122-Y-shaped connecting piece, 241-framework side plate, 242-framework longitudinal beam, 243-framework cross beam, 244-cross frame, 245-framework suspension lug and 246-battery installation position

Detailed Description

The present invention will be described in detail below with reference to the accompanying drawings and preferred embodiments, and the objects and effects of the present invention will become more apparent, and the present invention will be further described in detail below with reference to the accompanying drawings and 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.

As shown in fig. 1, the multi-rotor manned aircraft comprises four parts, namely a power module 1, a battery compartment 2, a cabin 3 and an undercarriage 4, wherein the power module 1 is directly connected with the battery compartment 2 and is positioned at the same height in layout to form a flying platform; the cabin 3 is located below the battery compartment 2 and the landing gear 4 is mounted below the cabin 3. The overall layout ensures that the paddle plane is positioned above the cabin, thereby avoiding the damage caused by the ejection of potential paddles; meanwhile, the gravity center of the whole aircraft can be lower than the plane of the propeller, which is beneficial to the stability of the flight attitude; in addition, the length of the power cable can be shortened, and the power cable has the advantages of being modular in design, convenient to maintain and the like.

As shown in fig. 1 and 2, the number of the power modules 1 is four, the power modules are respectively fixed at four right angles of the battery compartment 2, each power module 1 includes a power assembly 11 and an arm assembly 12, each arm assembly 12 includes a Y-shaped connecting piece 122 and two arm pipes 121 connected to two forks of the Y-shaped connecting piece 122, one set of power assembly 11 is fixed at the end of each arm pipe 121, each power assembly 11 includes a motor base 111, a motor 112, an electric controller 113 and a propeller 114, the motor base 111 is fixed at the end of each arm pipe 121, the electric controller 113 is installed inside the motor base 111, the motor 112 is respectively installed on the upper end surface and the lower end surface of the motor base 111, each motor 112 drives one propeller 114, and therefore the power modules are configured into an eight-shaft sixteen-propeller. The tail end of each group of power components 11 adopts a mode of coaxially installing two sets of motor propellers up and down, so that great improvement of navigation time and load is brought within the limited design size range of the aircraft, and safety redundancy of a power system is achieved.

In order to facilitate the storage and transportation of the aircraft, as shown in fig. 3, two arm tubes 121 connected to two branches of the Y-shaped connecting piece 122 can be folded downwards relative to the Y-shaped connecting piece 122, the aircraft is in a flying state when the arms are unfolded, the aircraft is in a storage state when the arms are folded downwards, the size of the folded whole aircraft is greatly reduced, and the packaging and transportation on the ground are facilitated, an included angle between the two arm tubes 121 is related to design parameters such as the overall axle distance, the arm length, the blade diameter and the like, preferably, the angle is greater than or equal to 45 degrees and less than or equal to α degrees, in order to maintain the rigidity and the light weight, the arm tubes 121 are made of carbon fiber composite materials.

The utility model discloses a battery compartment 2 of aircraft directly links to each other with power module 1 and passenger cabin 3, and it not only needs to undertake the huge moment of flexure that power module 1 produced, but also receives the dead weight of bearing the battery and passenger cabin and passenger's weight, still needs to satisfy the lightweight requirement of aircraft design simultaneously, compromises the simple operation nature simultaneously.

As shown in fig. 4-6, the battery compartment 2 includes an upper flip cover plate 21, a frame upper edge substrate 22, a sub-module 23, a metal frame 24 shaped like a Chinese character tian, a battery module 25, a flight control module 26 and a lower substrate 27, the upper flip cover plate 21 and the frame upper edge substrate 22 are disposed on the upper surface of the metal frame 24 shaped like a Chinese character tian, the lower substrate 27 is fixed on the lower surface of the metal frame 22 shaped like a Chinese character tian, the upper flip cover plate 21, the frame upper edge substrate 22, the metal frame 24 and the lower substrate 27 enclose a four-quadrant internal space, four sets of battery modules 23 are respectively and fixedly mounted in the internal space of each quadrant, two sub-modules 23 are fixedly mounted on the upper flip cover plate 21 corresponding to each set of battery modules 23, each sub-module is provided with a conductive copper bar, the upper flip cover plate 21 is rotatably connected with two sides of the metal frame 24 by hinges, when the upper layer flip cover plate 21 is turned down, the conductive copper bar can be communicated with the conductive copper bar on the power distribution module 23 through a screw, and the battery module 25 and an external motor are conducted with conductive confluence; the flight control module 26 is fixed to the lower surface of the lower base plate 27 to facilitate maintenance thereof from the cabin 3.

The utility model discloses a stress is all participated in to battery compartment 2's upper marginal base plate 22, lower floor's base plate 27 and field style of calligraphy metal framework 24, need to undertake huge moment of flexure that power module 1 produced, the dead weight of battery, passenger cabin and passenger's weight, possess certain rigid strength, will satisfy the light-weighted requirement of aircraft again simultaneously, consequently, field style of calligraphy metal framework 24 is made by aluminum alloy, magnalium, carbon steel etc. upper marginal base plate 22, lower floor's base plate 27 adopt carbon-fibre composite to make. The design of the upper flip cover 21 also facilitates the access of the battery module 25.

The metal framework 24 in the shape of a Chinese character 'tian' is composed of framework side plates 241, framework longitudinal beams 242, framework cross beams 243 and a cross 244 which are arranged in a circle at the periphery, a split component mode is adopted, and in order to conveniently and fixedly install the cabin 3 below, a plurality of framework hanging lugs 245 are uniformly arranged on the inner side surface of each framework side plate 241, so that the weight of the cabin 3 and passengers is uniformly distributed on the metal framework 22 in the shape of a Chinese character 'tian', and meanwhile, the cabin structure of the cabin 3 can also be used for strengthening the rigidity of the battery cabin 2; in order to fix the battery module 25, the inner surfaces of the framework side plates 241 and the plurality of battery mounting positions 246 on the side of the cross 244 prevent the battery module 25 from shaking during the flight of the aircraft.

The seat is arranged in the cabin 3, the top surface of the cabin 3 is the lower surface of the battery cabin 2, and the landing gear 4 is symmetrically arranged on two sides of the cabin 3.

The utility model discloses an in the implementation, structural design combines finite element simulation analysis, carries out the emulation of rigidity intensity under the atress condition to battery compartment 2. And combining the results of finite element analysis, materials can be accumulated on the part with larger stress and the key energy transmission path as much as possible during design, and the rest parts are hollowed to achieve the aim of light weight.

The utility model realizes the compatibility of long-endurance and heavy load on the power framework and the structural layout of the multi-rotor manned aircraft, and has certain safety performance and attitude stability performance; through the structural design of the Y-shaped folding arm and the metal framework shaped like a Chinese character tian, the structural design is compatible with the requirements of structural compactness and mechanical property, meanwhile, the modular layout is achieved, the maintenance is simple and convenient, and the engineering realization value is very high.

It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention and is not intended to limit the invention, and although the present invention has been described in detail with reference to the foregoing examples, it will be apparent to those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof. All modifications and equivalents made within the spirit and principles of the invention are intended to be included within the scope of the invention.

Claims

1. A battery compartment of a multi-rotor manned aircraft is characterized in that the battery compartment (2) comprises an upper-layer flip cover plate (21), a framework upper-layer edge substrate (22), a power distribution module (23), a grid-shaped metal framework (24), a battery module (25), a flight control module (26) and a lower-layer substrate (27), the upper-layer flip cover plate (21) and the framework upper-layer edge substrate (22) are arranged on the upper surface of the grid-shaped metal framework (24), the lower-layer substrate (27) is fixed on the lower surface of the grid-shaped metal framework (24), the upper-layer flip cover plate (21), the framework upper-layer edge substrate (22), the grid-shaped metal framework (24) and the lower-layer substrate (27) enclose four-quadrant inner spaces, and four groups of battery modules (25) are respectively and fixedly installed in the inner spaces of each quadrant, two power distribution modules (23) are fixedly installed on the upper layer flip cover plate (21) corresponding to each group of battery modules (25), each power distribution module is provided with a conductive copper bar, the upper layer flip cover plate (21) is rotatably connected with two sides of the metal framework (24) shaped like a Chinese character tian, and the conductive copper bars can be communicated with the conductive copper bars on the power distribution modules (23) after the upper layer flip cover plate (21) is flipped down; the flight control module (26) is fixed on the lower surface of the lower layer substrate (27).

2. The battery compartment of the multi-rotor manned vehicle of claim 1, wherein the metal frame (24) is made of aluminum alloy, magnesium aluminum alloy or carbon steel.

3. The battery compartment of a multi-rotor manned vehicle according to claim 1, wherein the upper edge substrate (22) and the lower edge substrate (27) are both made of carbon fiber composite.

4. The battery compartment of the multi-rotor manned vehicle according to claim 1, wherein the metal framework (24) is composed of framework side plates (241) with a circle of periphery, framework longitudinal beams (242), framework cross beams (243) and a cross frame (244), and all the components are detachably connected.

5. The battery compartment of the multi-rotor manned vehicle of claim 4, wherein the inner side of the framework side plate (241) is uniformly provided with a plurality of framework lugs (245) for connecting with the cabin (3).

6. The battery compartment of the multi-rotor manned aircraft according to claim 4 or 5, wherein the inner side surfaces of the framework side plates (241) and the cross (244) are further provided with a plurality of battery mounting positions (246).

7. A multi-rotor manned vehicle, characterized in that it comprises a battery compartment according to any one of claims 1 to 6, said vehicle further comprising four parts, namely a power module (1), a battery compartment (2), a cabin (3) and a landing gear (4), said power module (1) being directly connected to said battery compartment (2) and both being arranged at the same height to form a flight platform; the cabin (3) is fixed below the battery compartment (2), and the landing gear (4) is arranged at the bottom of the cabin (3).