WO2017031945A1

WO2017031945A1 - Multi-shaft manned aircraft

Info

Publication number: WO2017031945A1
Application number: PCT/CN2016/072097
Authority: WO
Inventors: 陶亮; 申守健; 秦立新
Original assignee: 河南三和航空工业有限公司
Priority date: 2015-08-21
Filing date: 2016-01-26
Publication date: 2017-03-02
Also published as: CN105151296A

Abstract

Provided is a multi-shaft manned aircraft, comprising a machine frame (1), and a powered apparatus (4), transmission apparatus (42), rotor apparatuses (2), variable-pitch apparatus, seat (5), and control apparatus (6) mounted on the machine frame; the transmission apparatus (42) is connected to the powered apparatus (4) and the rotor apparatuses (2); a rotor apparatus (2) comprises a rotor head (21) and a rotor blade (22); the rotor head (21) is symmetrically mounted on the machine frame (1), the rotor blade (22) is mounted on the rotor head (21), and the number of sets of rotor heads (21) and rotor blades (22) is at least three; the variable-pitch apparatus is connected to the rotor apparatuses (2); the seat (5) and operation apparatus are correspondingly arranged on the middle part of the machine frame structure, and are connected to the powered apparatus (4) and the rotor apparatuses (2); the control apparatus (6) is connected to the powered apparatus (4), the rotor apparatus (2), and the operation apparatus. Operation during flight is made simpler, and when faced with various states of flight, the invention is able to respond with ease; its structure is simple, yet it has a comprehensive set of capabilities.

Description

Multi-axis manned aircraft

Technical field

The present application relates to a multi-axis manned aircraft.

Background technique

At present, the traditional helicopter is a single-rotor with tail rotor layout, which provides lift by the rotation of the main rotor, and the high speed rotation of the tail rotor produces a lateral push-pull force for overcoming the counter torque generated by the main propeller. This layout is simple in structure and mature in technology, and can be flexibly used to manufacture helicopters of various specifications, and the operation is relatively simple. However, the tail beam leads to a large parking area, and the tail beam and the long-distance tail rotor drive shaft are easily damaged, the collision risk is high, the hovering performance is unstable, the tail rotor is easily damaged by foreign matter, causing a major accident, and the tail rotor needs to be consumed. About 15% of engine power.

In addition to single-rotor helicopters, many research institutes at home and abroad are also researching and developing multi-rotor aircraft, such as coaxial twin-rotor helicopters, tandem twin-rotor helicopters, cross-rotor helicopters, cross-rotor helicopters, tilt-rotor aircraft, etc. .

In recent years, with the development of electronic technology and control technology, the electric four-rotor small aircraft has been rapidly developed, and each rotor has a separate motor control. However, this type of aircraft is mainly used for aerial photography, RC flight performances, and the like. However, due to the electric drive mode, the horsepower and battery life of the aircraft are greatly restricted, and it is still difficult to get practical promotion. And the four propellers of the traditional four-axis aircraft are simple mechanisms of direct motor connection, the cross-shaped layout, the aircraft obtains the force of rotating the fuselage by changing the motor speed, thereby adjusting the flight attitude.

Due to the limitations of the structure and control principles, the four-axis aircraft has two problems that are difficult to solve. The first is the heavy load, and the second is the long-haul, because of the weight and efficiency of the battery, these two points are difficult to break, which limits the application of multi-axis aircraft.

Therefore, there is an urgent need for a multi-axis manned aircraft with a large load and long flight time.

Summary of the invention

The object of the present invention is to provide a multi-axis manned aircraft with a large load, a long flight time and a variety of applications, so as to solve the technical problem that the existing multi-axis manned aircraft is suitable for single and easy damage.

Therefore, in order to effectively solve the above problems, the present invention discloses a multi-axis manned aircraft with a large load, a long flight time, and a variety of applications, and the technical solution thereof is as follows:

A multi-axis manned aircraft comprising a frame and a power unit mounted on the frame, a transmission, a rotor device, a distance changing device, a seat and a control device, wherein

The transmission device connects the power device and the rotor device;

The rotor device includes a rotor head and a propeller, the rotor head is symmetrically mounted on the frame, and the propeller is mounted on the rotor head, and the number of the rotor head and the propeller is at least three groups;

The variable distance device is connected to the rotor device;

The seat and the operating device are correspondingly disposed in a middle portion of the frame structure, and the power device is connected to the rotor device;

The control device is coupled to the power unit, the rotor device, and the operating device, respectively.

Preferably, the control device comprises a three-axis gyroscope for calculating an adjustment value of the variable pitch device to the rotor head pitch.

Preferably, the power unit is a gasoline engine.

Preferably, the distance changing device comprises a pitch change rod and a servo motor, the variable distance rod is connected to the servo motor, and the variable distance rod is connected to the rotor head.

Preferably, the rotor apparatus further includes a rotor guard ring and a hub, the rotor guard ring being mounted on a periphery of the propeller, the hub for positioning a propeller and sleeved on the rotor head.

Preferably, the transmission device comprises a belt, a transmission shaft and a gear box, the gear box being connected to the power device through the belt and the transmission shaft, the number of the gear boxes being the same as the number of the rotor devices and a pair A corresponding connection.

Preferably, the number of the rotor devices is four, respectively located at the four corners of the frame.

Preferably, the operating device comprises an instrument panel, a joystick and a throttle pusher, the instrument panel is disposed in front of the seat, and the joystick and the throttle pusher are disposed on two sides of the seat.

Preferably, the control device is a programmable controller or a central processing unit.

Preferably, the engine is mounted in the middle of the multi-axis manned aircraft.

Compared with the prior art, the multi-axis manned aircraft provided by the present invention achieves the following effects:

1) The multi-axis manned aircraft provided by the present invention has a simple structure and is not expensive to manufacture, and the number of the rotor heads 21 can be set according to actual power requirements to meet different actual needs;

2) The multi-axis manned aircraft provided by the present invention uses a high-powered engine to make the actual application value of the aircraft higher, and can be used in agricultural spraying, forest fire fighting, police patrol, anti-terrorism, The implementation of various projects in the field of search and rescue, power inspection, oil pipeline inspection, disaster investigation, aerial aerial survey, air travel, etc.

3) The multi-axis manned aircraft provided by the present invention, the sub-control device 62 is connected with the variable-distance rods one-to-one correspondingly, thereby realizing separate control of the pitch of each rotor to achieve the purpose of controlling the flight attitude. Easy to operate and flexible to control;

4) The multi-axis manned aircraft provided by the present invention, the use of the servo motor enables the multi-axis manned aircraft provided by the invention to have small mass, high energy efficiency, stable function and long service life;

5) The multi-axis manned aircraft provided by the present invention, the number of the rotor devices 2 is set to four to meet the needs of most flights, effectively reducing the weight of the multi-axis manned aircraft itself, and facilitating passage in flight Adjusting the pitch of each rotor 22 to achieve various flight postures and changes in flight state, so that the multi-axis manned aircraft is stable in structure and has a wide field of view;

6) The multi-axis manned aircraft provided by the present invention can meet the requirements for reducing the quality of the aircraft by using the three-axis gyroscope, and the use efficiency is high, the result is accurate, and the flight control is ensured accurately and stably.

7) The multi-axis manned aircraft provided by the present invention, the use of the rotor retainer 23, the hub 24 and the variable pitch lever 25 enables the pilot to operate more easily during flight using the multi-axis manned aircraft provided by the present invention It can be easily handled in the face of various flight conditions, and the structure is simple but the functions are comprehensive.

DRAWINGS

The drawings described herein are provided to provide a further understanding of the present application and constitute the present application. In part, the illustrative embodiments of the present application and the description thereof are used to explain the present application and do not constitute an undue limitation of the present application. In the drawing:

1 is a schematic structural view of a multi-axis manned aircraft provided by the present invention;

2 is a schematic structural view of a rotor device of a multi-axis manned aircraft provided by the present invention;

among them,

1-rack 2-rotor device

3-operating device 4-power device

5-seat 6-control unit

7-Dashboard 8-Operator

9-throttle pusher 21-rotor head

22-propeller 23-rotor retainer

24-paddle hub 25-variable rod

42-transmission 421-belt

43-gearbox 422-drive shaft

62-servo motor

detailed description

Certain terms are used throughout the description and claims to refer to particular components. Those skilled in the art will appreciate that hardware manufacturers may refer to the same component by different nouns. The present specification and the claims do not use the difference in the name as the means for distinguishing the components, but the difference in function of the components as the criterion for distinguishing. The word "comprising" as used throughout the specification and claims is an open term and should be interpreted as "including but not limited to". "Substantially" means within the acceptable tolerances, those skilled in the art The technician can solve the technical problem within a certain error range, and basically achieve the technical effect. In addition, the term "coupled" is used herein to include any direct and indirect electrical coupling means. Therefore, if a first device is coupled to a second device, the first device can be directly electrically coupled to the second device, or electrically coupled indirectly through other devices or coupling means. Connected to the second device. The description of the specification is intended to be illustrative of the preferred embodiments of the invention. The scope of protection of the application is subject to the definition of the appended claims.

The present application is further described in detail below with reference to the accompanying drawings, but is not to be construed as limiting.

Embodiment 1:

1 is a schematic structural view of a multi-axis manned aircraft provided by the present invention, and FIG. 2 is a schematic structural view of a rotor device of a multi-axis manned aircraft provided by the present invention. The multi-axis manned aircraft is characterized by including a frame 1 and a power unit 4, a transmission unit 42, a rotor device 2, a distance changing device, a seat 5 and a control device 6 mounted on the frame 1, wherein

The transmission device 42 is connected to the power unit 4 and the rotor device 2;

The rotor device 2 includes a rotor head 21 and a propeller 22, the rotor head 21 being symmetrically mounted on the frame 1, the propeller 22 being mounted on the rotor head 21, the rotor head 21 and the propeller 22 The number is at least three groups;

The variable distance device is connected to the rotor device 2;

The seat 5 and the operating device are correspondingly disposed in the middle of the structure of the frame 1, and the power device 4 is connected to the rotor device 2;

The control device 6 is connected to the power unit 4, the rotor device 2 and the operating device 3, respectively.

The invention has simple structure, low manufacturing cost, and the number of the rotor head 21 and the propeller 22 can be set according to actual power requirements to meet different practical needs.

Further, the control device 61 includes a three-axis gyroscope for calculating an adjustment value of the pitch distance of the rotor head 21 by the variable distance device. The gyroscope English name is Gyroscope, defined as a device for measuring angle and maintaining direction. A single axis can only measure the amount in two directions, that is, one system requires three gyroscopes, and one three-axis gyroscope It can replace three single-axis gyroscopes, and the three-axis gyroscope can simultaneously measure the position, movement trajectory and acceleration in six directions. The three-axis gyroscope is small in size, light in weight, simple in structure and reliable in reliability; The multi-axis manned aircraft can meet the requirements for reducing the quality of the aircraft by using the three-axis gyroscope, and the use efficiency is high, the result is accurate, and the accurate control and stable safety of the flight are guaranteed.

Further, the power unit 41 is a gasoline engine. Since the power unit 61 adopts a gasoline engine, the problem of large load and long flight time can be solved. For example, a 100 hp aero engine, with 60 liters of gasoline at a time, can work continuously for 4-5 hours, 100 hp takeoff. The weight can reach 350-400 kg at least, and a 150 kg aircraft can fly for 5 hours continuously, which makes the actual application value of the aircraft higher. It can be used in agricultural spraying, forest fire fighting, police patrol, anti-terrorism, field search and rescue, electric power. Various projects such as inspection lines, oil pipeline inspections, disaster investigations, aerial aerial surveys, and air travel are carried out.

Further, the transmission device 42 includes a belt 421, a transmission shaft 422, and a gear box 43. The gear box 43 is connected to the power unit 41 through the belt 421 and the transmission shaft 422. The number of the gear box 43 is The number of the rotor devices 2 are the same and are connected one-to-one; the control device 6 is a programmable controller or a central processing unit.

Further, the variable pitch device includes a pitch change lever 25 and a servo motor 62, the variable pitch lever 25 is coupled to the servo motor 62, and the variable pitch lever 25 is coupled to the rotor head 21. The setting of the variable pitch lever 25 can adjust the pitch of the propeller 22, using a high distance at a high speed, a low distance at a low speed, and gradually increasing the pitch angle at a later time to accommodate more flight states. The driver can change the speed of the engine and the propeller 22 by controlling the regulator and the throttle, and on the one hand, adjust the tension of the propeller 22 while keeping the propeller 22 in an optimal working state. Therefore, the use of the rotor retainer 23, the hub 24 and the variable pitch lever 25 enables the pilot to operate more easily during flight using the multi-axis manned aircraft provided by the present invention, and can be easily operated in various flight states. Coping, the structure is simple but the functions are comprehensive.

The servo motor 62 is an automatic control system that enables an output control amount such as an object's position, orientation, state, and the like to follow an arbitrary change of an input target (or a given value). The servo motor can control the speed and position accuracy very accurately, and can convert the voltage signal into torque and speed to drive the control object. The servo motor rotor speed is controlled by the input signal and can react quickly. It is used as an actuator in the automatic control system, and has the characteristics of small electromechanical time constant, high linearity, low starting voltage and so on. The signal is converted to an angular displacement or angular velocity output on the motor shaft. As a reliable control system, it has the following advantages: volume Small, light weight, large output, fast response, high speed, small inertia, smooth rotation and stable torque. The control is complicated, easy to realize intelligence, high efficiency, low operating temperature, small electromagnetic radiation, long life, and can be used in various environments; and the use of the servo motor 62 enables the multi-axis manned aircraft provided by the present invention itself Small quality, high energy efficiency, stable function and long service life.

Further, the rotor device 2 further includes a rotor guard 23 and a hub 24, the rotor retainer 23 being mounted on the periphery of the propeller 22, the hub 24 for positioning the propeller 22 and socketing it On the rotor head 21, the rotor retainer 23 is used to protect the propeller 22.

Further, the number of the rotor devices 2 is four, which are respectively located at the four corners of the frame 1. In actual use, the rotor device 2 can be set to other numbers and balancedly disposed on the central axis of the frame 1. On both sides, the number of the rotor devices 2 is set to four to meet the needs of most flights, effectively reducing the weight of the multi-axis manned aircraft itself, and facilitating various adjustments by adjusting the individual rotor heads 21 in flight. The change of the flight posture and the flight state makes the multi-axis manned aircraft structurally stable and has a wide field of view.

Further, an instrument panel 7, an operating lever 8 and a throttle push rod 9 are provided, the instrument panel 7 is disposed in front of the seat 5, and the operating lever 8 and the throttle push rod 9 are disposed in the seat 5 sides. The multi-axis manned aircraft provided by the present invention uses the above arrangement, and the pilot can conveniently perform various operations.

Further, the engine is mounted in the middle of the multi-axis manned aircraft.

Compared with the prior art, the multi-axis manned aircraft described in the present application achieves the following effects. fruit:

1) The multi-axis manned aircraft provided by the present invention has a simple structure and a low manufacturing cost, and the number of the rotor heads 21 can be set according to actual power requirements to meet different actual needs;

2) The multi-axis manned aircraft provided by the present invention uses a high-powered engine to make the actual application value of the aircraft higher, and can be used in agricultural spraying, forest fire fighting, police patrol, anti-terrorism, field search and rescue, power line inspection, oil pipeline inspection, Implementation of various projects in disaster investigation, aerial aerial survey, and air travel;

The above description shows and describes several preferred embodiments of the present application, but as described above, it should be understood that the application is not limited to the forms disclosed herein, and should not be construed as Other combinations, modifications, and environments are possible and can be modified by the above teachings or related art or knowledge within the scope of the application concept described herein. All changes and modifications made by those skilled in the art are intended to be within the scope of the appended claims.

Claims

A multi-axis manned aircraft, comprising: a frame and a power unit mounted on the frame, a transmission device, a rotor device, a distance changing device, a seat and a control device, wherein the transmission device and the connection device a power unit and the rotor apparatus; the rotor apparatus including a rotor head and a propeller, the rotor head being symmetrically mounted on the frame, the propeller being mounted on the rotor head, the rotor head and a propeller The number of the at least three groups; the distance changing device, the distance changing device is connected to the rotor device; the seat and the operating device are correspondingly disposed in a middle portion of the frame structure, the power device and the device The rotor device is connected; the control device is respectively connected to the power device, the rotor device and the operating device.
The multi-axis manned aircraft according to claim 1, wherein said control means comprises a three-axis gyroscope for calculating an adjustment value of said variable pitch means to said rotor head pitch.
The multi-axis manned aircraft of claim 2 wherein said power unit is a gasoline engine.
The multi-axis manned aircraft according to claim 3, wherein said distance changing device comprises a pitch lever and a servo motor, said variable pitch lever is coupled to said servo motor, and said variable pitch lever is coupled to On the rotor head.
The multi-axis manned aircraft of claim 4 wherein said rotor assembly further comprises a rotor retainer and a hub, said rotor retainer being mounted to a periphery of said propeller, said hub for seating The propeller is sleeved onto the rotor head.
A multi-axis manned aircraft according to claim 5, wherein said transmission comprises a belt, a drive shaft and a gearbox, said gearbox being coupled to said power unit via said belt and drive shaft, said The number of gearboxes is the same as the number of said rotor devices and is connected one-to-one.
A multi-axis manned aircraft according to any one of claims 1 to 6, wherein the number of said rotor means is four, respectively located at four corners of said frame.
The multi-axis manned aircraft according to claim 7, wherein said operating device comprises an instrument panel, a joystick and a throttle pusher, said instrument panel being disposed in front of said seat, said joystick and said The throttle push rod is disposed on both sides of the seat.
The multi-axis manned aircraft of claim 8 wherein said control device is a programmable controller or a central processor.
A multi-axis manned aircraft according to claim 9 wherein said engine is mounted in the middle of said multi-axis manned aircraft.