CN213566457U

CN213566457U - Central variable-pitch propeller helicopter

Info

Publication number: CN213566457U
Application number: CN202022705839.9U
Authority: CN
Inventors: 江富余
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-11-20
Filing date: 2020-11-20
Publication date: 2021-06-29
Anticipated expiration: 2030-11-20

Abstract

A helicopter with central variable-pitch propeller is composed of four propellers, three identical fixed-pitch propellers whose rotary centers are projected on horizontal plane and connected by an equilateral triangle, three propellers arranged at left, right and back of helicopter body, another variable-pitch propeller whose rotary center is projected on horizontal plane and whose center is projected on horizontal plane, three identical engines for driving left, right and tail propellers, and another engine for driving central propeller, the propeller keeps high efficiency in a large speed range and is suitable for occasions needing high-speed flight.

Description

Central variable-pitch propeller helicopter

Technical Field

The utility model relates to a do not rely on the airport to adopt the realization vertical lift that three the same distance screw and a variable pitch screw are constituteed, hover, fly around all around central variable pitch screw helicopter.

Background

The prior known successful method for realizing the helicopter capable of vertically lifting, flying front, back, left and right and hovering is a four-propeller helicopter which has the advantages of simple structure, flexible operation and high reliability, but the four-propeller helicopter adopts four identical fixed-pitch propellers with smaller pitches, the efficiency of the fixed-pitch propellers is high only in a narrower speed range due to the efficiency of the fixed-pitch propellers, the efficiency of the fixed-pitch propellers is reduced when the efficiency is lower than or higher than the speed, the flying efficiency of the four-propeller helicopter adopting the four identical fixed-pitch propellers with smaller pitches is high only in a narrower speed range, and the flying efficiency of the four-propeller helicopter is reduced when the flying speed deviates from the high efficiency.

Disclosure of Invention

In order to improve the flight efficiency of the four-propeller helicopter, the utility model provides a central variable pitch propeller helicopter realizes this target.

The utility model provides a technical scheme that its technical problem adopted is: the left side of the machine body is provided with a forward swept left arm close to the front, the front end of the left arm is provided with a left propeller, the rotating surface of the left propeller is horizontal, symmetrically, the right side of the machine body is provided with a forward swept right arm close to the front, the front end of the right arm is provided with a right propeller, the rotating surface of the right propeller is horizontal, and the longitudinal tail of the machine body is provided with a tail propeller and the rotating surface of the tail propeller is horizontal.

The projection connecting lines of the rotation centers of the right propeller, the left propeller and the tail propeller on the horizontal plane are equilateral triangles, the elevation of the vertex angle of the projection of the rotation center of the tail propeller on the horizontal plane is overlapped with the projection of the longitudinal line of the central variable-pitch propeller helicopter on the horizontal plane, and the projection of the center of the equilateral triangle on the horizontal plane is overlapped with the gravity center of the central variable-pitch propeller helicopter.

The upper side of the center of gravity of the top of the machine body is provided with a central propeller, the rotating surface of the central propeller is horizontal, and the projection of the rotating center of the central propeller on the horizontal plane is on the center of an equilateral triangle formed by connecting the rotating centers of the right propeller, the left propeller and the tail propeller on the projection of the horizontal plane.

The height of the rotating surface of the left propeller is the same as that of the rotating surface of the right propeller, the height of the rotating surface of the central propeller is greater than or equal to that of the rotating surfaces of the left propeller and the right propeller, and the height of the rotating surface of the tail propeller is greater than that of the rotating surface of the central propeller.

An undercarriage is arranged under the fuselage near the center of gravity.

The left propeller, the right propeller and the tail propeller are identical fixed-distance propellers, the central propeller is a variable-pitch propeller with the pitch different from that of the left propeller, the right propeller and the tail propeller, and the pitch of the central propeller is controlled and changed by a pitch controller.

The projections of the rotating surface of the left propeller, the rotating surface of the right propeller, the rotating surface of the tail propeller and the rotating surface of the central propeller on the horizontal plane are not overlapped.

The left propeller, the right propeller and the tail propeller are arranged to rotate in the same direction, and the rotating directions of the left propeller, the right propeller and the tail propeller are opposite to the rotating direction of the central propeller.

Three same engines are arranged to drive the left propeller, the right propeller and the tail propeller respectively, another engine is arranged to drive the central propeller, and the power of the engine for driving the central propeller is larger than that of the engines for driving the left propeller, the right propeller and the tail propeller.

The flight principle of the central variable-pitch propeller helicopter is as follows: the left propeller, the right propeller and the tail propeller are all provided with the same fixed-distance propellers, the central propeller is a variable-pitch propeller with the pitch different from that of the left propeller, the right propeller and the tail propeller, the pitch of the central propeller is controlled and changed by a pitch controller, the left propeller, the right propeller and the tail propeller rotate clockwise, and the central propeller rotates anticlockwise.

When the left propeller, the right propeller, the tail propeller and the central propeller rotate, the sum of the reactive torques of the left propeller, the right propeller and the tail propeller is equal to the reactive torque of the central propeller, the reactive torques of the left propeller, the right propeller, the tail propeller and the central propeller are opposite to each other, the reactive torques of the left propeller, the right propeller, the tail propeller and the central propeller are offset with each other, and the central variable-pitch propeller helicopter keeps stable course.

The four engines are accelerated to increase the rotating speed of the left propeller, the right propeller, the tail propeller and the central propeller, the lift force of the four propellers is increased, and when the total lift force is larger than the weight of the central variable-pitch propeller helicopter, the central variable-pitch propeller helicopter vertically rises.

And reducing the throttle of the four engines to reduce the rotating speed of the left propeller, the right propeller, the tail propeller and the central propeller, reducing the lift force of the four propellers, and hovering the central variable-pitch propeller helicopter when the total lift force is equal to the weight of the central variable-pitch propeller helicopter.

And continuously reducing the throttles of the four engines to reduce the rotating speeds of the left propeller, the right propeller, the tail propeller and the central propeller, reducing the lift force of the four propellers, and vertically descending the central variable-pitch propeller helicopter when the total lift force is less than the weight of the central variable-pitch propeller helicopter.

When the central variable-pitch propeller helicopter is in the air, the rotating speed of the left propeller is increased, the lift force of the left propeller is increased, meanwhile, the rotating speed of the right propeller is reduced, the lift force of the right propeller is reduced, so that the helicopter body rolls to the right, in the process of controlling the right roll, the rotating speed of the left propeller is increased, the lift force is increased, the reaction torque is increased, the rotating speed of the right propeller is reduced, the lift force is reduced, the reaction torque of the left propeller and the right propeller is unchanged, and the course is kept stable when the right roll is controlled; the rotating speed of the left screw propeller is reduced, the lifting force of the left screw propeller is reduced, meanwhile, the rotating speed of the right screw propeller is increased, the lifting force of the right left screw propeller is increased, the machine body rolls leftwards, in the process of controlling the left screw propeller, the rotating speed of the left screw propeller is reduced, the lifting force is reduced, the reaction torque is reduced, the rotating speed of the right screw propeller is increased, the lifting force is increased, the reaction torque of the left screw propeller and the right screw propeller is not changed, the course is kept stable when the left screw propeller is controlled to roll, and the roll control.

When the central variable-pitch propeller helicopter is in the air, the rotating speed of the tail propeller is increased, the lift force of the tail propeller is increased, meanwhile, the rotating speeds of the left propeller and the right propeller are reduced, the lift force of the left propeller and the right propeller is reduced, so that the helicopter body is forward bent, in the process of forward bending operation, the rotating speed of the tail propeller is increased, the lift force is increased, the reaction torque is increased, the rotating speeds of the left propeller and the right propeller are reduced, the lift force is reduced, the reaction torque of the tail propeller, the left propeller and the right propeller is not changed, and the course is kept stable when the helicopter is forward bent; the rotating speed of the tail propeller is reduced, the lifting force of the tail propeller is reduced, meanwhile, the rotating speeds of the left propeller and the right propeller are increased, the lifting force of the left propeller and the right propeller is increased, the machine body is enabled to lean backwards, in the process of controlling the backward lean, the rotating speed of the tail propeller is reduced, the lifting force is reduced, the reaction torque is reduced, the rotating speeds of the left propeller and the right propeller are increased, the lifting force is increased, the reaction torque of the tail propeller, the left propeller and the right propeller is unchanged, the course is kept stable when the backward lean is controlled, and the pitching control is achieved.

When the central variable-pitch propeller helicopter is in the air, the pitch controller for operating the pitch of the central propeller increases the pitch of the central propeller, the lift force of the central propeller is increased, the reaction torque is increased, meanwhile, the rotating speeds of the left propeller, the right propeller and the tail propeller are reduced, the lift force of the left propeller, the right propeller and the tail propeller is reduced, the reaction torque of the central propeller is greater than the sum of the reaction torques of the left propeller, the right propeller and the tail propeller, because the central propeller rotates anticlockwise, the reaction torque enables the central variable-pitch propeller helicopter to rotate clockwise, the helicopter is rotated rightwards, in the process of controlling the rightwards rotating direction, the pitch of the central propeller is increased, the lift force is increased, the rotating speeds of the left propeller, the right propeller and the tail propeller are reduced, the lift force is reduced, the total lift force is unchanged, and the central variable pitch propeller helicopter keeps the stability in the vertical direction; a propeller pitch controller for operating the central propeller to reduce the propeller pitch of the central propeller, the lift force of the central propeller is reduced, the reaction torque is reduced, and simultaneously, the rotating speeds of the left propeller, the right propeller and the tail propeller are increased, the lift force of the left propeller, the right propeller and the tail propeller is increased, the reaction torque of the central propeller is less than the sum of the reaction torques of the left propeller, the right propeller and the tail propeller, because the left propeller, the right propeller and the tail propeller rotate clockwise, the reaction torque enables the central variable-pitch propeller helicopter to rotate anticlockwise, namely, in the left rotating direction, in the process of operating the left rotating direction, the propeller pitch of the central propeller is reduced, the lift force is reduced, the rotating speeds of the left propeller, the right propeller and the tail propeller are increased, the lift force is increased, the total lift force is unchanged, and, and realizing course control.

When the central variable-pitch propeller helicopter is in the air, the helicopter body is controlled to bow forwards, the throttles of the four engines are increased simultaneously, and the central variable-pitch propeller helicopter flies forwards; the helicopter body is controlled to tilt backwards, the throttle of the four engines is increased simultaneously, and the central variable-pitch propeller helicopter flies backwards; the forward pitch and leftward rotation directions of the helicopter body are controlled, the accelerator of the four engines is increased, and the central variable-pitch propeller helicopter flies leftward and forward; the front pitch and the right rotation directions of the helicopter body are controlled, the accelerographs of the four engines are increased simultaneously, and the central variable-pitch propeller helicopter flies to the right front; the helicopter body is controlled to roll leftwards, the throttle of the four engines is increased simultaneously, and the central variable-pitch propeller helicopter flies leftwards; the helicopter body is controlled to roll rightwards, the throttle of the four engines is increased simultaneously, and the central variable-pitch propeller helicopter flies rightwards.

The left and right forward swept arms of the central variable pitch propeller helicopter can be changed into left and right backward swept arms, meanwhile, the tail propeller is arranged in front, and the position of the central propeller is unchanged, and the specific method comprises the following steps: the left side of the top of the airplane body is provided with a left arm swept backward, the rear end of the left arm is provided with a left propeller, the rotating surface level of the left propeller is symmetrically arranged on the right side of the top of the airplane body, the rear end of the right arm is provided with a right arm swept backward, the rear end of the right arm is provided with a right propeller, the rotating surface level of the right propeller is provided with a front arm extending forward in the longitudinal front part of the airplane body, and the front end of the front arm is provided with a front propeller and the rotating surface level of the front propeller.

The projection connecting lines of the rotation centers of the left propeller, the right propeller and the front propeller on the horizontal plane are equilateral triangles, the elevation of the vertex angle of the projection of the rotation center of the front propeller on the horizontal plane is overlapped with the projection of the longitudinal line of the central variable-pitch propeller helicopter on the horizontal plane, and the projection of the center of the equilateral triangle on the horizontal plane is overlapped with the gravity center of the central variable-pitch propeller helicopter.

The upper side of the center of gravity of the top of the machine body is provided with a central propeller, the rotating surface of the central propeller is horizontal, and the projection of the rotating center of the central propeller on the horizontal plane is arranged on the center of an equilateral triangle formed by connecting the rotating centers of the left propeller, the right propeller and the front propeller on the projection of the horizontal plane.

The height of the rotating surface of the left propeller is the same as that of the rotating surface of the right propeller, the height of the rotating surfaces of the left propeller and the right propeller is greater than that of the rotating surface of the central propeller, and the height of the rotating surface of the central propeller is greater than that of the rotating surface of the front propeller.

An undercarriage is arranged under the fuselage near the center of gravity.

The left propeller, the right propeller and the front propeller are the same fixed-distance propellers, the central propeller is a variable-pitch propeller with the pitch different from that of the left propeller, the right propeller and the front propeller, and the pitch of the central propeller is controlled and changed by a pitch controller.

The projections of the rotating surface of the left propeller, the rotating surface of the right propeller, the rotating surface of the front propeller and the rotating surface of the central propeller on the horizontal plane are not overlapped.

The left propeller, the right propeller and the front propeller are arranged to rotate in the same direction, and the rotating directions of the left propeller, the right propeller and the front propeller are opposite to the rotating direction of the central propeller.

Three same engines are arranged to drive the left propeller, the right propeller and the front propeller respectively, another engine is arranged to drive the central propeller, and the power of the engine for driving the central propeller is larger than that of the engines for driving the left propeller, the right propeller and the front propeller.

The flight control method of the left arm and right arm sweepback central variable pitch propeller helicopter is the same as the flight control method of the left arm and right arm sweepforward central variable pitch propeller helicopter.

The utility model has the advantages that the left propeller, the right propeller and the tail propeller (or the front propeller) are the same fixed-distance propellers, the central propeller is the variable-pitch propeller which is different from the pitches of the left propeller, the right propeller and the tail propeller (or the front propeller), the pitch of the central propeller is variable, when the flying speed is low, the left propeller, the right propeller and the tail propeller (or the front propeller) are fixed-pitch propellers with smaller pitches, the pitch of the central variable-pitch propeller flies under smaller pitches, the left propeller, the right propeller, the tail propeller (or the front propeller) and the central variable-pitch propeller work in a high-efficiency state, when flying at high speed, the pitch of the central variable-pitch propeller flies under larger pitches, the central variable-pitch propeller works in a high-efficiency state, so that the helicopter with the central variable-pitch propeller has higher overall efficiency in a larger range of flying speed, the speed differential operation of the left propeller and the right propeller rolls, the speed differential operation pitching of the tail propeller, the left propeller and the right propeller, the pitch variation of the central propeller, the speed variation combination of the left propeller, the right propeller and the tail propeller operate course jointly, and the helicopter with the central variable pitch propeller has the advantages of simple structure and light dead weight and is suitable for flying in narrow places.

Drawings

The present invention will be further explained with reference to the drawings and examples.

Fig. 1 is a three-dimensional view of a first embodiment of the present invention.

Fig. 2 is a schematic view of the flight of the first embodiment of the present invention.

Fig. 3 is a third view of a second embodiment of the present invention.

Fig. 4 is a schematic view of the flight of a second embodiment of the present invention.

Fig. 5 is an oblique view of the first embodiment of the present invention.

In the figure, 1 is a central propeller, 2 is a pitch controller of the central propeller, 3 is a right propeller, 4 is a left propeller, 5 is a tail propeller, 6 is a left arm, 7 is a right arm, 8 is a machine body, 9 is a landing gear, 10 is a longitudinal direction and a forward flying direction of the machine body, 11 is an equilateral triangle formed by connecting the projection of the rotation centers of the left propeller, the right propeller and the tail propeller on a horizontal plane, 12 is a height of an equilateral triangle formed by connecting the projection of the rotation centers of the left propeller, the right propeller and the tail propeller on the horizontal plane, 13 is an equilateral triangle formed by connecting the projection of the rotation centers of the left propeller, the right propeller and the front propeller on the horizontal plane, 14 is a height of an equilateral triangle formed by connecting the projection of the rotation centers of the left propeller, the right propeller and the front propeller on the horizontal plane, 15 is a front arm extending longitudinally, 16. the front propeller rotates clockwise S, the propeller rotates anticlockwise N, and the center of gravity is P.

Detailed Description

In the embodiment shown in fig. 1, a forward swept left arm 6 is arranged near the front of the left side of the top of a fuselage 8, a left propeller 4 is arranged at the front end of the left arm 6, the rotating surface of the left propeller 4 is horizontal, symmetrically, a forward swept right arm 7 is arranged near the front of the right side of the top of the fuselage 8, a right propeller 3 is arranged at the front end of the right arm 7, the rotating surface of the right propeller 3 is horizontal, a tail propeller 5 is arranged at the longitudinal tail of the fuselage 8, and the rotating surface of the tail propeller 5 is horizontal.

The connecting line of the projections of the rotation centers of the left propeller 4, the right propeller 3 and the tail propeller 5 on the horizontal plane is an equilateral triangle 11, referring to fig. 2, the height 12 of the vertex angle of the triangle of the projection of the rotation center of the tail propeller 5 on the horizontal plane is overlapped with the projection of the longitudinal line 10 of the central variable-pitch propeller helicopter on the horizontal plane, and the projection of the center of the equilateral triangle 11 on the horizontal plane is overlapped with the gravity center P of the central variable-pitch propeller helicopter.

The upper side of the center of gravity of the top of the machine body 8 is provided with a central propeller 1, the rotating surface of the central propeller 1 is horizontal, and the projection of the rotating center of the central propeller 1 on the horizontal plane is arranged on the center of an equilateral triangle 11 formed by connecting the rotating centers of the left propeller 4, the right propeller 3 and the tail propeller 5 on the projection of the horizontal plane.

The height of the rotating surface of the left propeller 4 is the same as the height of the rotating surface of the right propeller 3, the height of the rotating surface of the center propeller 1 is greater than or equal to the height of the rotating surfaces of the left propeller 4 and the right propeller 3 (fig. 1 shows an example in which the height of the rotating surface of the center propeller 1 is greater than the height of the rotating surfaces of the left propeller 4 and the right propeller 3), and the height of the rotating surface of the tail propeller 5 is greater than the height of the rotating surface of the center propeller 1.

An undercarriage 9 is provided under the fuselage 8 near the centre of gravity P.

The left propeller 4, the right propeller 3 and the tail propeller 5 are the same fixed-distance propellers, the central propeller 1 is a variable-pitch propeller different from the left propeller 4, the right propeller 3 and the tail propeller 5, and the pitch of the central propeller 1 is controlled and changed by the pitch controller 2.

The projections of the rotating surface of the left propeller 4, the rotating surface of the right propeller 3, the rotating surface of the tail propeller 5 and the rotating surface of the central propeller 1 on the horizontal plane do not overlap with each other.

The left propeller 4, the right propeller 3 and the tail propeller 5 rotate clockwise S, and the central propeller 1 rotates anticlockwise N.

Three same engines are arranged to respectively drive the left propeller 4, the right propeller 3 and the tail propeller 5, another engine is arranged to drive the central propeller 1, and the power of the engine for driving the central propeller 1 is greater than that of the engines for driving the left propeller 4, the right propeller 3 and the tail propeller 5.

When the left propeller 4, the right helical propeller 3, the tail propeller 5 and the central propeller 1 rotate, the sum of the reactive torques of the left propeller 4, the right helical propeller 1 and the tail propeller 5 is equal to the reactive torque of the central propeller 1, the directions are opposite, the reactive torques of the left propeller 4, the right helical propeller 3, the tail propeller 5 and the central propeller 1 are mutually offset, and the course of the helicopter with the central variable pitch propeller is kept stable.

The four engines are accelerated to increase the rotating speed of the left propeller 4, the right propeller 3, the tail propeller 5 and the central propeller 1, the lift force of the four propellers is increased, and when the total lift force is larger than the weight of the central variable-pitch propeller helicopter, the central variable-pitch propeller helicopter vertically rises.

And reducing the throttle of the four engines to reduce the rotating speed of the left propeller 4, the right propeller 3, the tail propeller 5 and the central propeller 1, reducing the lift force of the four propellers, and hovering the central variable-pitch propeller helicopter when the total lift force is equal to the weight of the central variable-pitch propeller helicopter.

And continuously reducing the throttle of the four engines to reduce the rotating speed of the left propeller 4, the right propeller 3, the tail propeller 5 and the central propeller 1, reducing the lift force of the four propellers, and vertically descending the central variable-pitch propeller helicopter when the total lift force is less than the weight of the central variable-pitch propeller helicopter.

When the central variable-pitch propeller helicopter is in the air, the rotating speed of the left propeller 4 is increased, the lift force of the left propeller 4 is increased, meanwhile, the rotating speed of the right propeller 3 is reduced, the lift force of the right propeller 3 is reduced, so that the helicopter body 8 rolls rightwards, in the process of controlling the rolling rightwards, the rotating speed of the left propeller 4 is increased, the lift force is increased, the reaction torque is increased, the rotating speed of the right propeller 3 is reduced, the lift force is reduced, the reaction torque of the left propeller 4 and the right propeller 3 is unchanged, and the course is kept stable when the right rolling is controlled; the rotating speed of the left screw propeller 4 is reduced, the lifting force of the left screw propeller 4 is reduced, meanwhile, the rotating speed of the right screw propeller 3 is increased, the lifting force of the right left screw propeller 1 is increased, the machine body 8 rolls leftwards, in the process of controlling the left rolling, the rotating speed of the left screw propeller 4 is reduced, the lifting force is reduced, the reaction torque is reduced, the rotating speed of the right screw propeller 3 is increased, the lifting force is increased, the reaction torque of the left screw propeller 4 and the reaction torque of the right screw propeller 3 are unchanged, the course is kept stable when the left rolling is controlled, and the rolling control is realized.

When the central variable-pitch propeller helicopter is in the air, the rotating speed of the tail propeller 5 is increased, the lift force of the tail propeller 5 is increased, meanwhile, the rotating speeds of the left propeller 4 and the right propeller 3 are reduced, the lift force of the left propeller 4 and the right propeller 3 is reduced, so that the helicopter body 8 is pitched forwards, in the process of pitching before operation, the rotating speed of the tail propeller 5 is increased, the lift force is increased, the reaction torque is increased, the rotating speeds of the left propeller 4 and the right propeller 3 are reduced, the lift force is reduced, the reaction torque sum of the tail propeller 5, the left propeller 4 and the right propeller 3 is unchanged, and the course is kept stable when pitching before operation; the rotating speed of the tail propeller 5 is reduced, the lift force of the tail propeller 5 is reduced, meanwhile, the rotating speeds of the left propeller 4 and the right propeller 3 are increased, the lift force of the left propeller 4 and the right propeller 3 is increased, the machine body 8 is made to face backwards, in the process of operating the backward facing, the rotating speed of the tail propeller 5 is reduced, the lift force is reduced, the reaction torque is reduced, the rotating speeds of the left propeller 4 and the right propeller 3 are increased, the lift force is increased, the reaction torque of the tail propeller 5, the left propeller 4 and the right propeller 3 is unchanged, the course is kept stable when the backward facing is operated, and pitching operation is achieved.

When the central variable pitch propeller helicopter is in the air, the pitch controller 2 of the central propeller is operated to increase the pitch of the central propeller 1, the lift force of the central propeller 1 is increased, the reaction torque is increased, meanwhile, the rotating speeds of the left propeller 4, the right propeller 3 and the tail propeller 5 are reduced, the lift forces of the left propeller 4, the right propeller 3 and the tail propeller 5 are reduced, the reaction torque is reduced, the reaction torque of the central propeller 1 is greater than the sum of the reaction torques of the left propeller 4, the right propeller 3 and the tail propeller 5, as the central propeller 1 rotates anticlockwise N, referring to figure 2, the reaction torque enables the central variable pitch propeller helicopter to rotate clockwise S, namely to rotate rightwards, in the process of operating the rightwards rotating direction, the pitch of the central propeller 1 is increased, the lift force is increased, the rotating speeds of the left propeller 4, the right propeller 3 and the tail propeller 5 are reduced, the lift force is reduced, the total lift force is unchanged, and the central variable-pitch propeller helicopter keeps the stability in the vertical direction; the propeller pitch controller 2 of the central propeller is operated to reduce the propeller pitch of the central propeller 1, the lift force of the central propeller 1 is reduced, the counter torque is reduced, simultaneously, the rotating speeds of the left propeller 4, the right propeller 3 and the tail propeller 5 are increased, the lift forces of the left propeller 4, the right propeller 3 and the tail propeller 5 are increased, the counter torque is increased, the counter torque of the central propeller 1 is smaller than the sum of the counter torques of the left propeller 4, the right propeller 3 and the tail propeller 5, because the left propeller 4, the right propeller 3 and the tail propeller 5 rotate clockwise S, the counter torque enables the central variable propeller helicopter to rotate anticlockwise N, namely, the left rotating direction, in the process of operating the left rotating direction, the propeller pitch of the central propeller 1 is reduced, the lift force is reduced, the rotating speeds of the left propeller 4, the right propeller 3 and the tail propeller 5 are increased, the lift force is increased, and the, the central variable-pitch propeller helicopter keeps the stability in the vertical direction and realizes course control.

When the central variable-pitch propeller helicopter is in the air, the helicopter body 8 is controlled to bow forwards, the throttles of the four engines are increased simultaneously, and the central variable-pitch propeller helicopter flies forwards; the helicopter body 8 is controlled to tilt backwards, the throttle of the four engines is increased simultaneously, and the central variable-pitch propeller helicopter flies backwards; the front pitch and left rotation directions of the helicopter body 8 are controlled, the throttle of the four engines is increased, and the central variable-pitch propeller helicopter flies left forwards; operating the front 11 of the helicopter body to pitch and rotate to the right, simultaneously increasing the accelerographs of the four engines, and enabling the central variable-pitch propeller helicopter to fly to the right front; the helicopter body 8 is controlled to roll leftwards, the throttle of the four engines is increased simultaneously, and the central variable-pitch propeller helicopter flies leftwards; the helicopter body 8 is controlled to roll rightwards, simultaneously the throttle of the four engines is increased, and the central variable-pitch propeller helicopter flies rightwards.

In the embodiment shown in fig. 3, a left sweepback arm 6 is arranged at the left side of the top of the body 8, a left propeller 4 is arranged at the rear end of the left arm 6, the rotating surface of the left propeller 4 is horizontal, symmetrically, a right sweepback arm 7 is arranged at the right side of the top of the body 8, a right propeller 3 is arranged at the rear end of the right arm 7, the rotating surface of the right propeller 3 is horizontal, a front arm 15 extending forwards is arranged at the longitudinal front part of the body 8, a front propeller 16 is arranged at the front arm 15, and the rotating surface of the front propeller 16 is horizontal.

The line connecting the projections of the rotation centers of the left propeller 4, the right propeller 3 and the front propeller 16 on the horizontal plane is an equilateral triangle 13, see fig. 4, the high-line 14 of the vertex angle of the triangle of the projection of the rotation center of the front propeller 16 on the horizontal plane overlaps with the projection of the longitudinal line 10 of the central variable pitch propeller helicopter on the horizontal plane, and the projection of the center of the equilateral triangle 13 on the horizontal plane overlaps with the center of gravity P of the central variable pitch propeller helicopter.

The upper side of the center of gravity of the top of the machine body 8 is provided with the central propeller 1, the rotating surface of the central propeller 1 is horizontal, and the projection of the rotating center of the central propeller 1 on the horizontal plane is on the center of an equilateral triangle 13 formed by connecting the rotating centers of the left propeller 4, the right propeller 3 and the front propeller 16 on the horizontal plane.

The height of the rotating surface of the left propeller 4 is the same as that of the rotating surface of the right propeller 3, the height of the rotating surfaces of the left propeller 4 and the right propeller 3 is greater than that of the rotating surface of the central propeller 1, and the height of the rotating surface of the central propeller 1 is greater than that of the front propeller 16.

The left propeller 4, the right propeller 3 and the front propeller 16 are identical fixed-distance propellers, the central propeller 1 is a variable-pitch propeller different from the left propeller 4, the right propeller 3 and the front propeller 16, and the pitch of the central propeller 1 is controlled and changed by the pitch controller 2.

The projections of the rotating surface of the left propeller 4, the rotating surface of the right propeller 3, the front propeller 16, and the rotating surface of the center propeller 1 on the horizontal plane do not overlap each other.

The left propeller 4, the right propeller 3 and the front propeller 16 turn counterclockwise N, and the center propeller 1 turns clockwise S.

Three same engines are arranged to respectively drive the left propeller 4, the right propeller 3 and the front propeller 16, another engine is arranged to drive the central propeller 1, and the power of the engine for driving the central propeller 1 is greater than that of the engines for driving the left propeller 4, the right propeller 3 and the front propeller 16.

When the left propeller 4, the right helical blade 3, the front propeller 16 and the central propeller 1 rotate, the sum of the reactive torques of the left propeller 4, the right helical blade 1 and the front propeller 16 is equal to the reactive torque of the central propeller 1, and the reactive torques are opposite, the reactive torques of the left propeller 4, the right helical blade 3, the front propeller 16 and the central propeller 1 are mutually offset, and the course of the helicopter with the central variable pitch propeller is kept stable.

The four engines are throttled to increase the rotating speed of the left propeller 4, the right propeller 3, the front propeller 16 and the central propeller 1, the lift force of the four propellers is increased, and when the total lift force is larger than the weight of the central variable-pitch propeller helicopter, the central variable-pitch propeller helicopter vertically rises.

The four engines are throttled down so that the rotational speed of the left propeller 4, the right propeller 3, the front propeller 16 and the central propeller 1 is reduced and the lift of the four propellers is reduced, the central variable pitch propeller helicopter hovering when the total lift equals the weight of the central variable pitch propeller helicopter.

And continuously reducing the throttle of the four engines to reduce the rotating speed of the left propeller 4, the right propeller 3, the front propeller 16 and the central propeller 1, reducing the lift force of the four propellers, and vertically descending the central variable-pitch propeller helicopter when the total lift force is less than the weight of the central variable-pitch propeller helicopter.

When the central variable-pitch propeller helicopter is in the air, the rotating speed of the left propeller 4 is increased, the lift force of the left propeller 4 is increased, meanwhile, the rotating speed of the right propeller 3 is reduced, the lift force of the right propeller 3 is reduced, so that the helicopter body rolls rightwards, in the process of controlling the rolling rightwards, the rotating speed of the left propeller 4 is increased, the lift force is increased, the reaction torque is increased, the rotating speed of the right propeller 3 is reduced, the lift force is reduced, the reaction torque sum of the left propeller 4 and the right propeller 3 is unchanged, and the course is kept stable when the right propeller is controlled to roll rightwards; the rotating speed of the left screw propeller 4 is reduced, the lifting force of the left screw propeller 4 is reduced, meanwhile, the rotating speed of the right screw propeller 3 is increased, the lifting force of the right left screw propeller 1 is increased, the machine body rolls leftwards, in the process of controlling the left screw propeller to roll leftwards, the rotating speed of the left screw propeller 4 is reduced, the lifting force is reduced, the reaction torque is reduced, the rotating speed of the right screw propeller 3 is increased, the lifting force is increased, the reaction torque of the left screw propeller 4 and the reaction torque of the right screw propeller 3 are unchanged, the course is kept stable when the left screw propeller is controlled to.

When the central variable-pitch propeller helicopter is in the air, the rotating speed of the front propeller 16 is increased, the lift force of the front propeller 16 is increased, meanwhile, the rotating speeds of the left propeller 4 and the right propeller 3 are reduced, the lift force of the left propeller 4 and the right propeller 3 is reduced, the helicopter body tilts backwards, in the process of controlling the backward tilting, the rotating speed of the front propeller 16 is increased, the lift force is increased, the reaction torque is increased, the rotating speeds of the left propeller 4 and the right propeller 3 are reduced, the lift force is reduced, the reaction torque of the front propeller 16, the reaction torque of the left propeller 4 and the reaction torque of the right propeller 3 are not changed, and the course is kept stable when the backward; the rotational speed of screw 16 before reducing, the lift of preceding screw 16 reduces, and simultaneously, the rotational speed of increase left screw 4, right screw 3, the lift increase of left screw 4, right screw 3, make the fuselage bow before the manipulation, the in-process that bows before the manipulation, the rotational speed of preceding screw 16 reduces, the lift reduces, the reaction torque reduces, the rotational speed increase of left screw 4, right screw 3, the lift increase, the reaction torque increases, preceding screw 16 and left screw 4, the reaction torque of right screw 3 and unchangeable, course remain stable when bowing before the manipulation, realize the every single move manipulation.

When the central variable pitch propeller helicopter is in the air, the pitch controller 2 of the central propeller is operated to increase the pitch of the central propeller 1, the lift force of the central propeller 1 is increased, the reaction torque is increased, meanwhile, the rotating speeds of the left propeller 4, the right propeller 3 and the front propeller 16 are reduced, the lift forces of the left propeller 4, the right propeller 3 and the front propeller 16 are reduced, the reaction torque is reduced, the reaction torque of the central propeller 1 is greater than the sum of the reaction torques of the left propeller 4, the right propeller 3 and the front propeller 16, because the central propeller 1 rotates clockwise S, referring to figure 4, the reaction torque enables the central variable pitch propeller helicopter to rotate anticlockwise N, namely to rotate left, in the process of operating the left rotating direction, the pitch of the central propeller 1 is increased, the lift force is increased, and the rotating speeds of the left propeller 4, the right propeller 3 and the front propeller 16 are reduced, the lift force is reduced, the total lift force is unchanged, and the central variable-pitch propeller helicopter keeps the stability in the vertical direction; the pitch controller 2 of the central propeller is operated to reduce the pitch of the central propeller 1, the lift force of the central propeller 1 is reduced, the reaction torque is reduced, simultaneously, the rotating speeds of the left propeller 4, the right propeller 3 and the front propeller 16 are increased, the lift forces of the left propeller 4, the right propeller 3 and the front propeller 16 are increased, the reaction torque is increased, the reaction torque of the central propeller 1 is smaller than the sum of the reaction torques of the left propeller 4, the right propeller 3 and the front propeller 16, because the left propeller 4, the right propeller 3 and the front propeller 16 rotate anticlockwise N, referring to figure 4, the reaction torque enables the central variable pitch propeller helicopter to rotate anticlockwise S, namely to the right rotating direction, in the process of operating the right rotating direction, the pitch of the central propeller 1 is reduced, the lift force is reduced, the rotating speeds of the left propeller 4, the right propeller 3 and the front propeller 16 are increased, the lift force is increased, the total lift force is unchanged, the central variable-pitch propeller helicopter keeps the stability in the vertical direction, and the course control is realized.

When the central variable-pitch propeller helicopter is in the air, the helicopter body 8 is controlled to bow forwards, the throttles of the four engines are increased simultaneously, and the central variable-pitch propeller helicopter flies forwards; the helicopter body 8 is controlled to tilt backwards, the throttle of the four engines is increased simultaneously, and the central variable-pitch propeller helicopter flies backwards; the front pitch and left rotation directions of the helicopter body 8 are controlled, the throttle of the four engines is increased, and the central variable-pitch propeller helicopter flies left forwards; the front 7 of the helicopter body is controlled to pitch and rotate to the right, the throttle of the four engines is increased simultaneously, and the central variable-pitch propeller helicopter flies to the right front; the helicopter body 8 is controlled to roll leftwards, the throttle of the four engines is increased simultaneously, and the central variable-pitch propeller helicopter flies leftwards; the helicopter body 8 is controlled to roll rightwards, simultaneously the throttle of the four engines is increased, and the central variable-pitch propeller helicopter flies rightwards.

Fig. 5 is a side view of the first embodiment of the present invention, a left arm 6 sweepforward is arranged on the left side of the top of the fuselage 8, a left screw 4 is arranged at the front end of the left arm 6, the rotating surface level of the left screw 4 is symmetrically arranged on the right side of the top of the fuselage 8, a right arm 7 sweepforward is arranged on the right side of the top of the fuselage 8, a right screw 3 is arranged at the front end of the right arm 7, the rotating surface level of the right screw 3 is arranged on the vertical tail of the fuselage 8, and a tail screw 5 and the rotating surface level of the tail screw 5 are arranged on the vertical tail of the fuselage 8.

The height of the rotating surface of the left propeller 4 is the same as that of the rotating surface of the right propeller 3, the height of the rotating surface of the central propeller 1 is greater than that of the rotating surfaces of the left propeller 4 and the right propeller 3, and the height of the rotating surface of the tail propeller 5 is greater than that of the rotating surface of the central propeller 1.

When the reaction torque of the central propeller 1 is greater than the sum of the reaction torques of the left propeller 4, the right screw 1 propeller and the tail propeller 5, the machine body 8 turns to the right, and when the reaction torque of the central propeller 1 is less than the sum of the reaction torques of the left propeller 4, the right screw 1 propeller and the tail propeller 5, the machine body 8 turns to the left.

Claims

1. A central variable propeller pitch helicopter is characterized in that a forward swept left arm is arranged on the left side of a helicopter body close to the front, a left propeller is arranged at the front end of the left arm, the rotating surface of the left propeller is horizontal, symmetrically, a forward swept right arm is arranged on the right side of the helicopter body close to the front, a right propeller is arranged at the front end of the right arm, the rotating surface of the right propeller is horizontal, a tail propeller is arranged at the longitudinal tail part of the helicopter body, the rotating surface of the tail propeller is horizontal, the connecting line of the rotating centers of the right propeller, the left propeller and the tail propeller on the horizontal plane is an equilateral triangle, the elevation line of the vertex angle of the triangle of the rotating center of the tail propeller on the horizontal plane is overlapped with the projection of the longitudinal line of the central variable propeller pitch helicopter on the horizontal plane, the projection of the center of the equilateral triangle on the horizontal plane is overlapped with the gravity center of the central variable propeller, the rotating surface of the central propeller is horizontal, the projection of the rotating center of the central propeller on the horizontal plane is on the center of an equilateral triangle formed by connecting the projection of the rotating centers of the right propeller, the left propeller and the tail propeller on the horizontal plane, the height of the rotating surface of the left propeller is the same as that of the rotating surface of the right propeller, the height of the rotating surface of the central propeller is greater than or equal to that of the rotating surfaces of the left propeller and the right propeller, the height of the rotating surface of the tail propeller is greater than that of the rotating surface of the central propeller, an undercarriage is arranged under the aircraft body near the center of gravity, the projections of the rotating surfaces of the left propeller, the right propeller, the tail propeller and the central propeller on the horizontal plane are not overlapped with each other, the rotating directions of the left propeller, the right propeller and the tail propeller are the same, and the rotating directions of the left propeller, the right propeller and the tail propeller are opposite, set up three the same engine and drive left screw, right screw, tail screw respectively, set up another engine drive center screw, the power of the engine of drive center screw is greater than the power of the engine of drive left screw, right screw, tail screw, characterized by: the three propellers of the right propeller, the left propeller and the tail propeller are the same fixed-distance propellers, the central propeller is a variable-distance propeller different from the left propeller, the right propeller and the tail propeller, the pitch of the central propeller is controlled and changed by a pitch controller, or the three propellers of the right propeller, the left propeller and the front propeller are the same fixed-distance propellers, the central propeller is a variable-distance propeller different from the left propeller, the right propeller and the front propeller, the pitch of the central propeller is controlled and changed by the pitch controller, and the pitch change of the central propeller, the speed change combination of the left propeller, the right propeller and the tail propeller control the course together.