CN210338280U

CN210338280U - Many rotors manned vehicle

Info

Publication number: CN210338280U
Application number: CN201920671177.2U
Authority: CN
Inventors: 蔡建东; 姜红建; 黄冠宇; 谢安桓; 张丹
Original assignee: Zhejiang Lab
Current assignee: Zhejiang Lab
Priority date: 2019-05-13
Filing date: 2019-05-13
Publication date: 2020-04-17
Anticipated expiration: 2029-05-13

Abstract

The utility model discloses a multi-rotor manned aircraft, which comprises four parts, namely a power module, a battery compartment, a cabin and an undercarriage, wherein the power module is directly connected with the battery compartment, and the power module and the battery compartment are 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 discloses a many rotors manned vehicle mechanical properties is good, long voyage time, carry great, the security is better.

Description

Many rotors manned vehicle

Technical Field

The utility model relates to an aircraft technical field especially relates to a many rotors manned vehicle of big load.

Background

The multi-rotor manned aircraft has wide application prospect in the low-altitude traffic field. Many rotor manned vehicles on the market are the form that is four-axis eight oar on the complete machine design, for example CN205311899U, and this all has great restriction on time of flight and load, and power redundancy is not enough moreover, has great potential safety hazard. At the level of the layout architecture of the aircraft, the passenger cabin of CN205311899U is located at the upper part of the fuselage main body, which means that the center of gravity of the whole aircraft is higher than the plane of the paddles, which is not only unfavorable for stabilizing the attitude of the aircraft, but also causes the passengers to be injured by the paddles.

SUMMERY OF THE UTILITY MODEL

Not enough to prior art, the utility model provides a many rotors 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:

the multi-rotor manned aircraft is characterized by comprising four parts, namely a power module, a 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.

Further, power module have four, fix respectively four right angle departments of battery compartment, power module include power component and horn subassembly, the horn subassembly include Y type connecting piece and connect two horn pipes on the Y type connecting piece, the one set of power component of tip fixation of every horn pipe, power component include motor cabinet, motor, electricity accent and screw, the motor cabinet fix the tip of horn pipe, motor cabinet internally mounted electricity accent, the upper and lower terminal surface of motor cabinet install a motor respectively, every motor drives a screw to the configuration becomes the form of eight sixteen oars of eight.

Furthermore, the Y-shaped connecting piece is connected with the arm tube in a foldable mode.

Further, the horn pipe is made of carbon fiber composite.

Furthermore, the included angle of the two branches of the Y-shaped connecting piece is α, wherein the included angle is more than or equal to 45 degrees and less than or equal to α degrees and less than or equal to 135 degrees.

The utility model has the advantages as follows:

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.

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 24 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.

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. The multi-rotor manned aircraft is characterized by comprising 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 arranged at the same height to form a flying 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).

2. The multi-rotor manned aircraft according to claim 1, wherein the number of the power modules (1) is four, and the power modules are respectively fixed at four corners of the battery compartment (2), the power modules (1) comprise power assemblies (11) and arm assemblies (12), each arm assembly (12) comprises a Y-shaped connecting piece (122) and two arm tubes (121) connected to the Y-shaped connecting piece (122), a set of power assemblies (11) is fixed at the end of each arm tube (121), each power assembly (11) comprises a motor base (111), a motor (112), an electric controller (113) and a propeller (114), the motor bases (111) are fixed at the ends of the arm tubes (121), the electric controllers (113) are installed in the motor bases (111), and the motors (112) are respectively installed on the upper end surface and the lower end surface of the motor bases (111), each motor (112) drives a propeller (114) and is thus configured in the form of eight-axis, sixteen-propeller.

3. A multi-rotor manned vehicle according to claim 2 wherein the Y-shaped connection (122) is foldably connected to the arm tube (121).

4. The multi-rotor manned vehicle according to claim 2, wherein the boom tubes (121) are made of carbon fiber composite material.

5. A multi-rotor manned vehicle according to claim 2 wherein the two divergent angles of the Y-shaped link (122) are α, with 45 ° α ° 135 °.