CN217533237U

CN217533237U - Self-driven undercarriage system of electric vertical take-off and landing aircraft

Info

Publication number: CN217533237U
Application number: CN202221234420.2U
Authority: CN
Inventors: 金君; 陈修贤; 党铁红; 董明
Original assignee: Shanghai Volant Aerotech Ltd
Current assignee: Shanghai Volant Aerotech Ltd
Priority date: 2022-05-23
Filing date: 2022-05-23
Publication date: 2022-10-04
Anticipated expiration: 2032-05-23

Abstract

The utility model discloses an electronic VTOL aircraft self-driven undercarriage system, including ground taxi control lever, aircraft controller, machine controller, aircraft battery, self-swing formula front wheel and band pulley hub motor drive's rear wheel, the self-swing formula front wheel is installed in aircraft nose portion, band pulley hub motor drive's rear wheel is installed at aircraft fuselage middle and rear portion, machine controller, aircraft battery and aircraft controller are all installed inside the aircraft fuselage. For traditional can be gliding navigation class aircraft by oneself, need open the propeller, the wheeled undercarriage of drive slides, and navigation class aircraft is open screw generally, if there is foreign matter such as stone metal on the slip path, flies up easily, hits screw or fuselage. If ground service personnel are nearby, injuries are easily caused. The hub motor is used for driving the aircraft to slide on the ground, so that the aircraft is safer and more reliable.

Description

Self-driven undercarriage system of electric vertical take-off and landing aircraft

Technical Field

The utility model relates to an aeronautical equipment technical field, concretely relates to electronic VTOL aircraft self-driven undercarriage system.

Background

The Electric VTOL (Vertical Take-Off and Landing) aircraft is fully called Electric Vertical Take-Off and Landing, the Electric VTOL aircraft realizes Vertical Take-Off and Landing through multiple rotors through a pure Electric engine, and simultaneously flies in a long distance through a fixed wing without depending on a runway, so that the operation site requirement is low, the low-noise flying aircraft completely meets the high-density urban air traffic requirement, and the Electric VTOL aircraft is a mainstream scheme of the urban air traffic in the future.

The electric vertical take-off and landing aircraft is compatible with the characteristics of two types of the rotor wing aircraft and the fixed wing aircraft, and comprises a multi-rotor wing flight mode, a fixed wing flight mode and an intermediate conversion stage.

Since the eVTOL takes off without running, the taking off and landing mode is close to that of a helicopter. Thus, skid landing gear may be arranged, as may wheel landing gear. The aircraft needs to move and rotate after landing, so that the aircraft provided with the skid type landing gear is generally dragged by a small wheel vehicle after being lifted. An aircraft equipped with a wheeled undercarriage can generally start a thrust paddle and move by itself. The wheel type undercarriage of the existing navigation aircraft generally comprises an undercarriage, undercarriage wheels, a hydraulic or mechanical brake and a steering mechanism. The wheel type undercarriage of the fixed wing aircraft needs to support running takeoff and running landing, so that the design requirement on the whole undercarriage system is high, and the consideration factors comprise load strength, damping and buffering design during landing, steering design and the like. The whole undercarriage system is relatively complex in design, particularly in steering design, and a hydraulic system or a steering engine and other rotating mechanisms are needed. When the aircraft runs on the ground, the thrust propeller needs to be started, and the aircraft is pushed to run on the ground by the thrust of the thrust propeller. There is a certain danger of personnel in areas where personnel are somewhat dense near airports and hangars, and the comparative energy efficiency is low. When the aircraft is moved without turning on the thrust device, the aircraft needs to be moved using the ground tractor.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an electronic VTOL aircraft self-driven undercarriage system to solve the problem that mentions in the background art. In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an electronic VTOL aircraft self-driven undercarriage system, includes ground sliding control lever, aircraft controller, machine controller, aircraft battery, self-swing formula front wheel and band pulley in-wheel motor driven rear wheel, install in aircraft nose portion from the pendulum-type front wheel, band pulley in-wheel motor driven rear wheel installs rear portion in the aircraft fuselage, machine controller, aircraft battery and aircraft controller are all installed inside the aircraft fuselage, ground sliding control lever connects the aircraft controller, machine controller is connected to the aircraft controller, machine controller connects the aircraft battery, machine controller connects the in-wheel motor driven rear wheel.

Preferably, take in-wheel motor driven rear wheel to be equipped with 2, take in-wheel motor driven rear wheel includes the in-wheel motor, be equipped with cavity ratchet axle on the in-wheel motor, the in-wheel motor is installed on the wheel, the in-wheel motor is worn out motor control cable through cavity ratchet axle and is connected motor controller.

Preferably, the number of the motor controllers is 2, and the motor controllers are motor controllers with forward and reverse rotation control capability.

Preferably, the number of the self-swinging front wheels is 1, and the self-swinging front wheels are unpowered self-swinging front wheels.

Preferably, the ground sliding control lever is a cross-shaped direction lever.

Preferably, the self-driven landing gear system of the electric vertical take-off and landing aircraft further comprises a manual wheel brake mechanism, and the manual wheel brake mechanism is installed on a rear wheel driven by a wheel hub motor.

The utility model discloses a technological effect and advantage: the safety is high: for traditional can be gliding navigation class aircraft by oneself, need open the propeller, the driving wheel formula undercarriage slides, and navigation class aircraft is open screw generally, if have foreign matters such as stone metal on the slip path, flies up easily, hits screw or fuselage. If ground staff exists nearby, the injury is easily caused. The hub motor is used for driving the aircraft to slide on the ground, so that the aircraft is safer and more reliable; energy conservation: compared with the traditional aircraft which uses a propeller to slide on the ground, the landing gear system which uses the hub motor to carry out self-driving has smaller power consumption; the structure is simple: for the aircraft that the tradition used propeller drive ground to slide, the utility model discloses use in-wheel motor driven undercarriage mechanism, need not arrange the steering mechanism of nose landing gear or rear landing gear. The related driving control mechanism is omitted. Since the eVTOL is light in weight and the power requirements for the drive wheels are low, there is no need for a gearbox mechanism in the carrier wheel that is complex in design. The eVTOL aircraft does not need to run on the ground to take off, so the structural load of the whole landing gear system is small, and an over-complicated buffer mechanism is not needed to be designed. The whole landing gear structure is simpler than the traditional navigation aircraft or the published electric drive landing gear wheel structure and is easy to produce; the use is convenient: compared with an aircraft adopting a skid or a traditional propeller to drive to slide, the eVTOL driven by the hub motor can slide on the ground automatically, does not need facilities in an airport to pull the aircraft, and has high flexibility.

Drawings

FIG. 1 is a control diagram of a self-propelled landing gear system of an electric VTOL aircraft;

FIG. 2 is a schematic view of a self-powered landing gear system of an electric VTOL aircraft;

FIG. 3 is an exploded view of the rear wheel driven by the hub motor of the present invention;

fig. 4 is a perspective view of the rear wheel shaft driven by the hub motor of the present invention.

In the figure: 1. a rear wheel driven by a hub motor; 2. a self-swinging front wheel; 3. a hub motor; 4. a ratchet shaft; 5. a wheel.

Detailed Description

In order to make the technical means, the creative features, the objectives and the functions of the present invention easily understood and appreciated, the present invention will be further described with reference to the specific drawings, and in the description of the present invention, unless otherwise specified or limited, the terms "mounted," connected "and" connected "should be understood broadly, and for example, the terms" fixed connection, "detachable connection," integral connection, mechanical connection, and electrical connection may be used; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements.

Examples

As shown in fig. 1 and 2, the self-driven landing gear system of the electric vertical take-off and landing aircraft comprises a ground sliding control lever, an aircraft controller, 2 independent motor controllers with forward and reverse rotation control capability, an aircraft battery, 1 unpowered self-swinging

front wheel

2, 2 rear wheels 1 with hub motor drive and a hand-operated wheel brake mechanism. The manual airplane wheel brake mechanism is arranged on a rear wheel 1 driven by a wheel hub motor, 1 unpowered self-swinging front wheel 2 is arranged on the head part of the aircraft, and a steering mechanism is not required to be designed; 2 a rear wheel driven by a motor with a hub is arranged at the middle rear part of the aircraft body; the motor controller with positive and negative rotation control capability, the aircraft battery and the aircraft controller are all arranged in the aircraft body; the ground sliding control rod cross direction rod is connected with an airplane controller, the airplane controller is connected with a motor controller with forward and reverse rotation control capability, the motor controller with forward and reverse rotation control capability is connected with an aircraft battery, and the motor controller with forward and reverse rotation control capability is connected with a rear wheel 1 driven by a hub motor.

As shown in fig. 3 and 4, the rear wheel 1 driven by the wheel hub motor includes a wheel hub motor 3, the wheel hub motor 3 is provided with a hollow ratchet shaft 4, the wheel hub motor 3 is mounted on the wheel 5, and the wheel hub motor 3 penetrates out of a motor controller with forward and reverse rotation control capability through the hollow ratchet shaft 4 to control a cable connection belt.

A control method of a self-driven landing gear system of an electric vertical take-off and landing aircraft is disclosed as the following steps in figure 1: after the aircraft lands, a pilot opens a ground sliding function button; the control system of the aircraft judges whether the aircraft is on the ground first, if the aircraft is identified to be on the ground, 2 motor controllers with forward and reverse rotation control capability work; the pilot pushes the ground sliding control lever forwards, and after the airplane controller obtains an instruction, the hub motor controller sends out a control signal to drive the 2 hub motors 3 to synchronously rotate forwards at the same time, so that the aircraft moves forwards. When the pilot needs to turn, the pilot presses the control lever leftwards or rightwards, the aircraft controller sends a signal to drive the 2 motor controllers, so that the hub motor on one side is decelerated or even stalled, and the hub motor 3 on the other side keeps rotating speed or rotates in an accelerated manner to form differential turning; the self-swinging front wheel 2 can automatically match with the swinging direction according to the driving force of the rear wheel 1 driven by the belt wheel hub motor, and the swinging amplitude can be defined by bolts or stoppers. When braking, the pilot presses the brake button, and the aircraft controller sends a signal to make the motor controller send an electronic braking instruction, and 2 motor controllers simultaneously output small reverse current to make 2 in-wheel motors 3 brake. When the aircraft is backed, a pilot pulls the ground sliding control lever backwards, the aircraft controller drives the 2 motor controllers to output large reverse current at the same time, and drives the 2 hub motors 3 to synchronously rotate reversely at the same time, so that the aircraft backs up; after the aircraft slides to a designated place, a pilot or ground staff locks an undercarriage on the ground, and a manual airplane wheel brake mechanism is locked to perform manual braking, so that the aircraft is fixed; when carrying out ground trailer and dragging, wheel hub motor 3 does not have the electric current to pass through, can the free rotation, combines from pendulum formula front wheel 2 can conveniently accomplish to turn to and drag the line.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications and variations can be made in the embodiments or in part of the technical features of the embodiments without departing from the spirit and the scope of the invention.

Claims

1. The utility model provides an electronic VTOL aircraft self-driven undercarriage system which characterized in that: including ground taxi control lever, aircraft controller, machine controller, aircraft battery, from pendulum-type front wheel and band pulley hub motor drive's rear wheel, install in aircraft nose portion from pendulum-type front wheel, band pulley hub motor drive's rear wheel is installed in aircraft fuselage middle and rear portion, machine controller, aircraft battery and aircraft controller are all installed inside aircraft fuselage, ground taxi control lever connects the aircraft controller, machine controller connects machine controller, machine controller connects the aircraft battery, machine controller connects in-wheel motor drive's rear wheel.

2. The self-propelled landing gear system of the electric VTOL aerial vehicle of claim 1, wherein: the rear wheel of the wheel hub motor drive is provided with 2, the rear wheel of the wheel hub motor drive comprises a wheel hub motor, a hollow ratchet shaft is arranged on the wheel hub motor, the wheel hub motor is installed on the wheel, and the wheel hub motor penetrates out of the hollow ratchet shaft and is connected with a motor control cable to be connected with a motor controller.

3. The self-propelled landing gear system of claim 1, wherein: the motor controller is provided with 2, and the motor controller is provided with forward and reverse rotation control capability.

4. The self-propelled landing gear system of claim 1, wherein: the number of the self-swinging front wheels is 1, and the self-swinging front wheels are unpowered self-swinging front wheels.

5. The self-propelled landing gear system of the electric VTOL aerial vehicle of claim 1, wherein: the ground sliding control rod is a cross-shaped direction rod.

6. The self-propelled landing gear system of claim 1, wherein: the self-driven landing gear system of the electric vertical take-off and landing aircraft further comprises a manual wheel brake mechanism, and the manual wheel brake mechanism is installed on a rear wheel driven by a wheel hub motor.