CN211055365U

CN211055365U - Big many rotor unmanned aerial vehicle of load

Info

Publication number: CN211055365U
Application number: CN201921166778.4U
Authority: CN
Inventors: 王路
Original assignee: Foshan Yunzhan Intelligent Technology Co ltd
Current assignee: Foshan Yunzhan Intelligent Technology Co ltd
Priority date: 2019-07-24
Filing date: 2019-07-24
Publication date: 2020-07-21
Anticipated expiration: 2029-07-24

Abstract

The utility model relates to a many rotor unmanned aerial vehicle of big load, including organism, driving system, flight control system, power supply system and undercarriage, its characterized in that: the machine body consists of an engine room and six support arms, and the support arms are connected with the engine room through threaded parts to form an easily-assembled and disassembled structure; a screw structure is arranged at the bottom of the engine room and is used for connecting a mounting platform to form a multi-mounting large-load structure; the power system comprises six groups of driving structures to form independent driving structures of each support arm; the driving structure is composed of an electrically adjusted motor and a propeller; each driving structure forms a large-load multi-rotor driving structure; the flight control system is integrated at the bottom in the cabin and comprises a GPS antenna, a signal receiver, a main controller, an IMU sensor and a power supply manager, and the control output end of the flight control system is connected with the power system and the undercarriage to form an integral control structure; the power supply system is integrated in the cabin and comprises a lithium battery and a distribution board. The aircraft has the characteristics of strong loading capacity, multiple integrated mounting, high strength, long service life, high flight safety, good balance and the like.

Description

Big many rotor unmanned aerial vehicle of load

Technical Field

The utility model relates to a many rotor unmanned aerial vehicle especially relates to a many rotor unmanned aerial vehicle of big load. Belong to unmanned aerial vehicle technical field.

Background

At present, along with the gradual maturity of unmanned aerial vehicle research and development technology, manufacturing cost reduces by a wide margin, and unmanned aerial vehicle has obtained wide application in each field, and besides military use, still include civilian fields such as agricultural plant protection, electric power inspection, police law enforcement, geological exploration, environmental monitoring, forest fire prevention and movie & TV aerial photograph, civilian field mainly divide into industrial grade application and consumption level application. And prior art's many rotor unmanned aerial vehicle of industrial grade, owing to there is structural defect, most industrial grade many rotor unmanned aerial vehicle's load all is no longer than 5KG, though through the carry of many integrations, big mass, its loading capacity can exceed 5KG, nevertheless need supporting corresponding flight platform, and lack general suitable flight platform again in the reality, consequently be difficult to extensively popularize and apply. In addition, the following technical problems of the existing unmanned aerial vehicle generally exist: (1) the pulling force of the aircraft is not enough, and the requirement of large pulling force of large load cannot be met; (2) the number of portable batteries and the takeoff weight limit, the flight distance and the dead time are insufficient, the effective endurance time is about 20 minutes, and the ideal working efficiency cannot be achieved; (3) the load capacity is low, so that the integrated mounting can not be met, and the integrated mounting is particularly not suitable for the flight requirement of heavy load; (4) the body structure has strong splicing feeling, insufficient strength and short service life; (5) the safety coefficient of flight is low, and the equilibrium is poor, and take off and land unsafe, can not handle the emergency of big load.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the problems that the existing unmanned aerial vehicle has low load capacity, can not satisfy the load of multiple integrations and has insufficient strength, short service life, low flight safety factor, poor balance and unsafe taking off and landing, and provides a large-load multi-rotor unmanned aerial vehicle. The integrated aircraft has the outstanding substantive characteristics and the obvious technical progress of strong loading capacity, capability of meeting multiple integrated mounting, high strength, long service life, high flight safety coefficient, good balance, safe take-off and landing and the like.

The purpose of the utility model can be realized by adopting the following technical scheme:

the utility model provides a many rotor unmanned aerial vehicle of big load, includes organism, driving system, flight control system, power supply system and undercarriage, its structural feature lies in: the machine body consists of an engine room and six support arms, and the support arms are connected with the engine room through threaded parts to form an easily-assembled and disassembled structure; the bottom of the engine room is provided with a screw structure and is used for connecting a mounting platform so as to mount multi-integration and large-mass load equipment to form a multi-mounting large-load structure; the power system comprises six groups of driving structures, and the six groups of driving structures are correspondingly arranged in the six support arms to form independent driving structures of the support arms; the driving structure is composed of an electrically adjusted motor and a propeller; each driving structure is electrically connected with the flight control system respectively so as to control the motor and the propeller to move through electric regulation to form a large-load multi-rotor driving structure; the flight control system is integrated at the bottom in the cabin and comprises a GPS antenna, a signal receiver, a main controller, an IMU sensor and a power supply manager, and the control output end of the flight control system is connected with the power system and the undercarriage to form an integral control structure; the power supply system is integrated in the engine room and comprises a lithium battery and a distribution board for supplying power to the power system and the flight control system.

further, cabin and six support arms adopt carbon fiber integrated into one piece, but the biggest bearing 25KG, and the undercarriage comprises the carbon fiber pipe, and the intensity can support 30 KG.

The flight control system further comprises a main controller, a power supply manager, an IMU sensor, a GPS antenna, L ED indicator lamps and a signal receiver, wherein the power supply manager converts high voltage power provided by the power distribution board into a voltage-stabilized low-voltage power supply and provides working voltage for the main controller, satellite signals received by the GPS antenna are converted into flight attitude information through the IMU sensor and provided for the main controller, the L ED indicator lamps are directly connected with the main controller to display the working state of the flight control system, and the signal receiver is directly connected with the main controller and establishes a communication relation with a ground station or a remote controller through a wireless transmission mode.

Furthermore, the engine room and the engine arm are integrally formed by mould pressing and are formed by mould pressing of at least three layers of 3K carbon fiber cloth.

Furthermore, the electric regulator is fixed on a framework of the cabin, the control input end is connected with the main controller, the power supply input end is connected with the distribution board, the main controller provides a control signal, and the distribution board provides power supply voltage; the output end of the electric controller is connected with a male plug of a plug terminal of the upper machine arm through a silica gel line, and then is connected with a female plug of a plug terminal of the lower machine arm through a plug mode, the female plug terminal is connected with a motor through a silica gel line, and the propeller is fixedly installed on the motor through a propeller clamp and four screws.

Furthermore, the motor is a high-power and high-energy-efficiency motor, and a lead of the motor is wound by a silver wire, so that current can rapidly pass through the surface of the silver wire. The current overflows that bigger response is faster, reduces the copper loss simultaneously, effectively reduces the motor temperature.

Further, the sine wave drive signal is connected to the signal input part that electricity was transferred to the input does not have clutter drive current, forms FOC sine wave drive, can effectively reduce self and generate heat, and intelligent algorithm makes motor control more high-efficient, accurate, stable.

Furthermore, the propeller adopts a foam hollow structure, so that the weight is effectively reduced, and the working efficiency of the blades is improved.

The utility model has the following outstanding substantive characteristics and beneficial effect:

1. the machine body of the utility model consists of an engine room and six support arms, and the support arms are connected with the engine room through threaded parts to form an easily-assembled and disassembled structure; the bottom of the engine room is provided with a screw structure and is used for connecting a mounting platform so as to mount multi-integration and large-mass load equipment to form a multi-mounting large-load structure; the power system comprises six groups of driving structures, and the six groups of driving structures are correspondingly arranged in the six support arms to form independent driving structures of the support arms; the driving structure is composed of an electrically adjusted motor and a propeller; each driving structure is electrically connected with the flight control system respectively so as to control the motor and the propeller to move through electric regulation to form a large-load multi-rotor driving structure; therefore, the unmanned aerial vehicle can solve the problems that the existing unmanned aerial vehicle is low in load capacity, cannot meet multi-integrated mounting, is insufficient in strength, short in service life, low in flight safety factor, poor in balance, unsafe in taking off and landing and the like, and has the outstanding substantive characteristics and obvious technical progress that the unmanned aerial vehicle is high in load capacity, can meet multi-integrated mounting, is high in strength, long in service life, high in flight safety factor, good in balance, safe in taking off and landing and the like.

3. The utility model discloses because flight control system is integrated in cabin bottom, including GPS antenna, signal receiver, master controller, IMU sensor and power manager, its control output end is connected with driving system and undercarriage, forms the overall control structure, consequently can solve current unmanned aerial vehicle and have that flight safety factor is low, the equilibrium is poor and take off and land unsafe scheduling problem, have that flight safety factor is high, the equilibrium is good and take off and land outstanding substantive characteristics such as safety and showing technological progress.

3. The utility model discloses a strengthen body structure, the high-power electricity of customization is transferred, driving system modules such as motor, screw, reaches the optimization of high load length when navigating through the equilibrium stability of adjusting six axles. Has the following substantial effects: high efficiency and large pulling force, and the maximum pulling force is improved to 7.3kg from common 5 kg; the operation time is increased from the conventional 30 minutes to more than 60 minutes, so that the operation efficiency is further improved; the load capacity reaches 10kg, which is enough to meet the requirements of multi-integration and large-mass mounting; the airplane body is integrally formed, so that the airplane is light in weight and high in strength, the load capacity is increased under the condition of further reducing the takeoff weight, and the service life of equipment is prolonged; over 50% of power redundancy, flight safety and stability are effectively guaranteed.

Drawings

Fig. 1 is a schematic view of the overall structure of embodiment 1 of the present invention.

Fig. 2 is a schematic diagram of the explosion of the whole device according to embodiment 1 of the present invention.

Fig. 3 is a schematic diagram of the explosion of the cabin according to embodiment 1 of the present invention.

Fig. 4 is a schematic structural view of a horn according to embodiment 1 of the present invention.

Fig. 5 is an exploded view of the boom according to embodiment 1 of the present invention.

Fig. 6 is a schematic view of a holder structure according to embodiment 1 of the present invention.

Fig. 7 is an exploded view of a holder according to embodiment 1 of the present invention.

Detailed Description

The present invention will be described in further detail with reference to the following drawings and specific embodiments.

Specific example 1:

the names of all parts in the drawing correspond to the reference numbers of 1-cabin, 2-arm, 3-pylon platform, 4-lifting and falling feet, 101-cabin cover, 102-GPS antenna, 103-lithium battery, 104-cabin clapboard, 105-cabin framework, 106-signal receiver, 107-electric regulation, 108-main controller, 109-IMU sensor, 110-power manager, 111-distributor, 112-GPS bracket, 113-GPS bracket fixing ring, 114-signal receiver antenna, 115-plug terminal male head, 116-L ED indicator lamp, 117-upper arm, 201-plug terminal female head, 202-arm screw lock, 203-lower arm, 204-motor, 205-propeller, 206-paddle clamp, 207-metal screw, 301-lower arm, 302-carbon plate, 303-metal pipe clamp, 304-plastic pipe plug, 305-stainless steel screw.

Referring to fig. 1 to 7, the large-load multi-rotor unmanned aerial vehicle according to the embodiment includes a body, a power system, a flight control system, a power supply system, and an undercarriage 4, wherein the body includes a nacelle 1 and six support arms 2, and the support arms 2 are connected with the nacelle 1 through threaded parts to form an easily detachable structure; the bottom of the engine room 1 is provided with a screw structure and is used for connecting a mounting platform so as to mount multi-integration and large-mass load equipment to form a multi-mounting large-load structure; the power system comprises six groups of driving structures which are respectively and correspondingly arranged in the six support arms 2 to form independent driving structures of the support arms; the driving structures are respectively composed of a motor 204 and a propeller 205 of the electric controller 107; each driving structure is electrically connected with a flight control system respectively so as to control the motor 204 and the propeller 205 to move through the electric regulator 107, and a large-load multi-rotor driving structure is formed; the flight control system is integrated at the bottom in the cabin 1, comprises a GPS antenna 102, a signal receiver 106, a main controller 108, an IMU sensor 109 and a power supply manager 110, and the control output end of the flight control system is connected with the power system and the undercarriage 4 to form an integral control structure; the power supply system is integrated in the cabin 1, and comprises a lithium battery 103 and a distribution board 111 for supplying power to the power system and the flight control system.

In this embodiment:

cabin 1 and six support arms all adopt carbon fiber integrated into one piece, but the biggest bearing 25KG, and undercarriage 4 comprises the carbon fiber pipe, and 30KG can be supported to intensity.

The flight control system comprises a main controller 108, a power manager 110, an IMU sensor 109, a GPS antenna 102, L ED indicator lamps 116 and a signal receiver 106, wherein the power manager 110 converts high voltage power provided by a distributor 11 into voltage-stabilized low voltage power to provide working voltage for the main controller 108, satellite signals received by the GPS antenna 102 are converted into flight attitude information through the IMU sensor 109 and provided for the main controller 108, the L ED indicator lamps 116 are directly connected with the main controller 108 to display the working state of the flight control system, and the signal receiver 106 is directly connected with the main controller 108 and establishes a communication relation with a ground station or a remote controller through a wireless transmission mode.

The motor 204 is a high-power and high-energy-efficiency motor, and a lead of the motor is wound by a silver wire, so that current can rapidly pass through the surface of the silver wire. The current overflows that bigger response is faster, reduces the copper loss simultaneously, effectively reduces the motor temperature.

The signal input end of the electric controller 107 is connected with a sine wave driving signal to input clutter-free driving current, FOC sine wave driving is formed, self heating can be effectively reduced, and an intelligent algorithm enables the motor to be controlled more efficiently, accurately and stably.

The propeller 205 adopts a foam hollow structure, so that the weight is effectively reduced, and the working efficiency of the blades is improved.

The engine room 1 and the engine arm 2 are integrally formed by mould pressing and are formed by mould pressing of at least three layers of 3K carbon fiber cloth.

The principle of action of the present invention is described below:

referring to fig. 1-7, compared with a four-axis unmanned aerial vehicle, the utility model can effectively decompose the overall mass of the unmanned aerial vehicle by adding two power systems of the arms; by quickly adjusting the power output of each motor, more refined attitude control is achieved, so that the stability of the attitude of the unmanned aerial vehicle is ensured; the efficiency of the propeller is adjusted by enhancing the power of the motor, and the power supply is increased, so that the load capacity of the unmanned aerial vehicle is increased, and the unmanned aerial vehicle can achieve the effect of long endurance; the screw rod structure is arranged at the bottom of the unmanned aerial vehicle cabin and used for connecting the mounting platform, so that the universal hanger can be conveniently connected to form an easily-assembled and easily-disassembled connecting structure; and load equipment with multiple integration, large mass and the like can be mounted by assembling the universal hanging racks with different structures.

The utility model discloses an adopt carbon fiber compression molding, have the characteristics of matter light and high strength. The conventional two-layer carbon fiber cloth structure is adjusted into a three-layer carbon fiber cloth structure, so that the integral strength is increased by 1/3, and the maximum bearing capacity of the machine body is up to 25 KG; in addition, the number of parts and fasteners can be effectively reduced by the die pressing integral forming process, the weight of the machine body can be reduced on one hand, and the connection strength of the machine body is improved on the other hand, so that the machine body structure is strengthened.

By fixing the electric regulator 107 on the framework 105 of the cabin 1, the control input end is connected with the main controller 108, the power input end is connected with the distribution board 111, the main controller 108 provides a control signal, and the distribution board 111 provides a power supply voltage; the output end of the electronic controller 107 is connected with the male plug terminal 115 of the upper horn through a silica gel line, and then is connected with the female plug terminal 201 of the lower horn through a plug mode, the female plug terminal 201 is connected with the motor 204 through a silica gel line, and the propeller 205 is fixedly installed on the motor 204 through the paddle clamp 206 and the four screws 207.

The motor 204 is a high-power and high-energy-efficiency motor, and a lead of the motor is wound by a silver wire, so that current can rapidly pass through the surface of the silver wire, the overcurrent of the current is larger, the response is faster, the copper loss is reduced, and the temperature of the motor is effectively reduced; the electric controller 107 is driven by FOC sine waves, drives clutter-free current, effectively reduces self heating, and enables the motor to be controlled more efficiently, accurately and stably through an intelligent algorithm. The device has the characteristics of quick response, large driving force, long service life and the like.

The propeller 205 adopts a foam hollow structure, so that the weight is effectively reduced, and the working force effect of the blades is improved.

The organism comprises a cabin and six support arms, all adopts carbon fiber integrated into one piece, but the biggest bearing 25KG, and the support arm passes through threaded component with the cabin and is connected, can dismantle independent transportation, reduces organism transportation volume, and the cabin bottom is equipped with the screw rod that is used for connecting the carry platform, and the different stores pylons of accessible assembly, load equipment such as the many integrations of carry, big quality. The landing gear is formed by the carbon fiber tube, and is simple in structure and capable of supporting 30KG in strength.

The utility model relates to a big load rotor unmanned aerial vehicle is based on being optimized by conventional four-axis to six, through organism structural optimization, uses the industrial scale casing of integrated into one piece processing, and the high-power electricity of cooperation customization is transferred, driving system modules such as motor, screw, and implementation scheme is simple reliable, has solved technical problem such as industrial scale unmanned aerial vehicle load is low, short, factor of safety is low, life weak point during navigation, but make it wide application in the load flight task of many integrated devices.

The universal hanging rack 3 is connected with a screw rod at the bottom of the cabin through a metal pipe clamp 303 and is locked through screws, the mounting structure is simple, and the overall strength is high. The mounting platform can be adapted to most of load hangers on the market, and simultaneously, different hangers can be assembled to mount load equipment with multiple integration, large mass and the like.

The working principle of the power system is as follows: the electric modulator receives and analyzes a signal from the main controller, and then controls the rotating speed of the motor in a mode of converting direct current into specific pulse alternating current, the motor is a converter for converting electric energy into mechanical energy, and the propeller 205 is a device for converting the rotating power of the motor into propelling force or lifting force.

The power supply system is directly formed by connecting two high-capacity lithium batteries in series, and the lithium batteries are arranged in the engine room and fixed on a partition board of the engine room. The power distribution board is connected through a silica gel wire to provide power for the flight control system and the power system.

The universal hanger 3 is designed at the bottom of the cabin and comprises two carbon tubes 301, four metal tube clamps 303, two fixed carbon plates 302, stainless steel screws 305 and a plastic pipe plug 304.

Claims

1. The utility model provides a many rotor unmanned aerial vehicle of big load, includes organism, driving system, flight control system, power supply system and undercarriage (4), its characterized in that: the machine body consists of an engine room (1) and six support arms (2), wherein the support arms (2) are connected with the engine room (1) through threaded parts to form an easily-assembled and disassembled structure; the bottom of the engine room (1) is provided with a screw structure and used for connecting a mounting platform so as to mount multi-integration and large-mass load equipment to form a multi-mounting large-load structure; the power system comprises six groups of driving structures, and the six groups of driving structures are correspondingly arranged in the six support arms (2) to form independent driving structures of the support arms; the driving structures are respectively composed of a motor (204) and a propeller (205) of an electric regulator (107); each driving structure is electrically connected with a flight control system respectively so as to control the motor (204) and the propeller (205) to move through an electric regulator (107) to form a large-load multi-rotor driving structure; the flight control system is integrated at the bottom in the cabin (1), comprises a GPS antenna (102), a signal receiver (106), a master controller (108), an IMU sensor (109) and a power supply manager (110), and the control output end of the flight control system is connected with the power system and the undercarriage (4) to form an integral control structure; the power supply system is integrated in the cabin (1), comprises a lithium battery (103) and a distribution board (111) and supplies power to the power system and the flight control system.

2. A heavy load multi-rotor drone according to claim 1, characterized in that: cabin (1) and six support arms (2) adopt carbon fiber integrated into one piece, but the biggest bearing 25KG, and undercarriage (4) comprise the carbon fiber pipe, and intensity can support 30 KG.

3. The large-load multi-rotor unmanned aerial vehicle as claimed in claim 1 or 2, wherein the flight control system comprises a main controller (108), a power manager (110), an IMU sensor (109), a GPS antenna (102), L ED indicator lamps (116) and a signal receiver (106), the power manager (110) converts high voltage power provided by the power distribution board (11) into voltage-stabilized low voltage power to provide working voltage for the main controller (108), satellite signals received by the GPS antenna (102) are converted into flight attitude information through the IMU sensor (109) and provided for the main controller (108), L ED indicator lamps (116) are directly connected with the main controller (108) to display the working state of the flight control system, and the signal receiver (106) is directly connected with the main controller (108) and then establishes a communication relationship with a ground station or a remote controller through a wireless transmission mode.

4. A heavy load multi-rotor drone according to claim 1 or 2, characterized in that: the engine room (1) and the support arm (2) are integrally formed by mould pressing and are formed by mould pressing of at least three layers of 3K carbon fiber cloth.

5. A heavy load multi-rotor drone according to claim 3, characterized in that: the electric regulator (107) is fixed on a framework (105) of the cabin (1), a control input end is connected with the main controller (108), a power supply input end is connected with the distribution board (111), the main controller (108) provides a control signal, and the distribution board (111) provides power supply voltage; the output end of the electric adjusting (107) is connected with a male plug terminal (115) of the upper support arm through a silica gel line, the female plug terminal (201) of the lower support arm is connected through a plug mode, the female plug terminal (201) is connected with a motor (204) through a silica gel line, and a propeller (205) is fixedly installed on the motor (204) through a paddle clamp (206) and four screws (207).

6. A heavy load multi-rotor drone according to claim 1, characterized in that: the motor (204) is a high-power and high-energy-efficiency motor, and a lead of the motor is wound by a silver wire, so that current can rapidly pass through the surface of the silver wire.

7. A heavy load multi-rotor drone according to claim 1, characterized in that: the signal input end of the electric regulator (107) is connected with a sine wave driving signal so as to input a clutter-free driving current.

8. A heavy load multi-rotor drone according to claim 1, characterized in that: the propeller (205) adopts a foam hollow structure, so that the weight is effectively reduced, and the working efficiency of the blades is improved.