CN102464107A

CN102464107A - Novel theory and method for eliminating buffeting of helicopter wing and increasing flight speed

Info

Publication number: CN102464107A
Application number: CN2010105540760A
Authority: CN
Inventors: 曹铁生; 王臻
Original assignee: Individual
Current assignee: Individual
Priority date: 2010-11-18
Filing date: 2010-11-18
Publication date: 2012-05-23
Anticipated expiration: 2030-11-18
Also published as: CN102464107B

Abstract

The invention solves the problem of force balance caused by unequal blade lift force when a rotor wing faces the wind or follows the wind in a level flight of a helicopter so as to greatly improve the flight speed and stability. A mechanics principle is as follows: as shown in figures, the helicopter is supposed to be located in a space coordinate X,Y and Z; the gravity vector OG-G of the helicopter is vertically downward along the Y axis; the helicopter flies forwards at a speed vf; two blades are in same vertical plane with the X axis; and the X axis is supposed to rotate along with the blades. The blades at two sides are connected into a whole through a pitch axis and can make pitch motion around the axis, and the action points O and O' of the lift force of the two blades are located behind the X axis. In this way, the lift forces F1 and F1' generated by the blades at two sides when the rotor wing rotates are kept to be equal. When the helicopter takes-off and lands vertically, the blades do not make the pitch motion. When the helicopter is in level flight (vf), the blades at two sides automatically regulate angles of pitch to keep the balance of the lift force. The blades in a motion mode of sine wave pitching are synchronous with the rotating period of the rotor wing, and the pitch amplitude is increased along with the speed of the helicopter.

Description

Eliminate new theory and method that the helicopter wing is trembled shake and promoted flying speed

Affiliated technical field

Patent of the present invention relates to a kind of new theory and implementation method, can eliminate the wing that helicopter exists and tremble the shake problem in flight course, and purpose is to promote flying speed and having a smooth flight property.This patent can directly be applied in military and civilian autogyro field.

Background technology

Autogyro has had the history in more than 100 year since 1907 are born, its groundwork is to utilize the rotor acquisition lift that has the elevation angle of high speed rotating to make aircraft lift-off and flight.Though revolutionary improvement has all taken place in its each item technology and material; But; By unequal the trembling the shake problem and still can't eliminating of bringing of both wings lift in the flight course that its basic flight theory produced, so until today, the flying speed of autogyro still is not very high.It is reported; The present the fastest helicopter of the employed flying speed in countries in the world; F-Zero is generally in 250 kilometers/hour to 350 kilometers/hour scope; Even the newly designed X2 helicopter of the U.S. (its F-Zero will be 463 kilometers/hour), its flying speed does not reach the goal pace (900 kilometers/hour) of helicopter yet.So the flying speed that how to promote autogyro has greatly become the focus of countries in the world research.Our invention has been eliminated this with a kind of new ultromotivity equilibrium principle with unique method influences the factor of flying speed, can promote the flying speed of helicopter greatly.

Summary of the invention

For eliminate present autogyro in flight course when rotor goes to windward side lift greater than side with the wind and take place periodically to tremble shake and the problem that influences flying speed; We utilize the ultromotivity equilibrium principle and the rotor design that has pitch axis of patent of the present invention, and this problem is resolved.

The ultromotivity equilibrium principle that patent of the present invention relates to is meant in the helicopter rotor rotating process; The lift of both sides rotor is owing to the connection of pitch axis can turn an angle around this axle; Through a kind of sinusoid periodic synchronous ground size of both sides lift that changed elevation angle self-equalizing; Make the both sides lift to equate constantly, thus kept autogyro in flight course steadily.The key Design of patent of the present invention is the existence of the pitch axis between two rotors.We establish a three-dimensional rotation system of axes for convenience of description: establish the initial point that the helicopter rotor center is in this system of axes; Its direction that moves ahead is the Z axle; Horizontal vertical is the X axle in the Z axle; Along the antigravity direction perpendicular to X, the Z axle be the Y axle, suppose that simultaneously aircraft two rotor blades overlap with the X axle and the X axle rotates with blade.At this moment, two rotors connect and can turn an angle around pitch axis (because pitch axis overlaps with the X axle, so can think that two rotor blades can turn an angle around the X axle) through the pitch axis of centre; And design the time makes the point of action of lift rotor blade in both sides drop on the rear (sensing of rotation is decided to be the place ahead) of X axle, this moment aircraft with certain speed along Z axially before flight, the lift on the rotor blade of both sides owing to exist facings the wind with the wind the time mutually; So both sides lift does not wait, in this case, the lift of the blade of windward side produces the big moment of side more with the wind for pitch axis (X axle); Under the effect of this moment, rotor blade turns an angle around pitch axis, thereby the blade elevation angle of windward side is diminished; Lift diminishes; Make the elevation angle of side with the wind become big, it is big that lift becomes, and equates until final.So the existence of pitch axis can make the lift of both sides rotor be adjusted into equal everywhere.Can prove that in rotor uniform rotation process, blade can be synchronous with sinusoidal waveform pitch mode and rotor rotation period around pitch axis, the pitching amplitude then increases with helicopter speed.

The beneficial effect of patent of the present invention is, can eliminate the shake problem of trembling that two rotor lifts in the autogyro flight course do not wait the limited flight speed of bringing, and can promote the flying speed and the flight stability of autogyro greatly.

Description of drawings

Below in conjunction with accompanying drawing patent of the present invention is further specified: the accompanying drawing specific aim has shown the mechanical balance principle of patent of the present invention simplifiedly.Mutually perpendicular X in the diagram shown in the dotted line, Y, Z axle constitute a space three-dimensional rotating coordinate system (referring to that the X axle rotates with rotor blade); Wherein Z-direction is the direction that autogyro flies forward; The direction that the Y direction representative makes progress perpendicular to level ground; Aircraft gravity G drops on this axle and goes up and be directed downwards, and the X axle horizontal is perpendicular to heading Z axle, and overlaps with aircraft rotary wing and to rotate with rotor.In the diagram; Vf representes the speed that autogyro flies forward, and on behalf of windward side (left side), Fl and Fl ' reach the lift of side (right side) two rotors generation with the wind respectively, and O and O ' represent the point of action of both sides lift on rotor respectively; D is the distance of both sides lift point of action to pitch axis (X axle), G and O _GRepresent aircraft gravity and point of action thereof respectively, the rotation arrow is represented the rotor clickwise in the diagram.

In rotor (with the X axle) rotation process; If there is not blade can rotate around it the pitch axis of certain angle; The side lift Fl ' of the lift Fl that autogyro windward side blade produces＞with the wind, the vane stress of both sides does not wait, and the shake problem is trembled in generation under the lift effect that does not wait that airframe can change in the cycle; It is obvious more that aircraft flight speed is trembled shake more greatly, and this point has influenced the flying speed of autogyro.Connected into as a wholely in this patent between two rotor blades of aircraft by pitch axis, and two blades can rotate in the certain limit angle around pitch axis, make the point of action O of lift rotor blade in both sides and the rear (sensing of rotation is decided to be the place ahead) that O ' drops on the X axle during design; At this moment, two rotors are respectively Fld and Fl ' d for the moment that pitch axis (X axle) produces, because Fld＞Fl ' d; So rotor blade will rotate an angle around pitch axis; Make the windward side elevation angle diminish, Fl diminishes, and the sidespin wing elevation angle becomes big with the wind; Fl ' change is big, finally makes Fl=Fl '.When both sides rotor (X axle) turns to when overlapping with the Z axle, both sides lift equates that this moment, pitch axis did not rotate, the state when rotor rotates when being equivalent to autogyro and taking off vertically.In rotor uniform rotation process, blade can be synchronous with sinusoidal waveform pitch mode and rotor rotation period around pitch axis, and the pitching amplitude then increases with helicopter speed.

The specific embodiment

The core technology of patent of the present invention is the design that connects the pitch axis of two rotors.In the practical implementation process; The blade pass of both sides rotor is crossed pitch axis connect into as a wholely, on the one hand this integral body drives down at the copter engine axle and rotates, on the other hand; Rotor blade can rotate around pitch axis within the specific limits in this is whole, thereby changes the blade elevation angle.In addition, in the practical implementation process, the point of action that also will make two rotors drop on the lift that produces in the rotation drops on the rotation rear of pitch axis, and so just can make lift is a stabilization system for the mechanical system of pitch axis.

Claims

1. eliminate new theory and method that the autogyro wing is trembled shake and promoted flying speed.Patent of the present invention is different from the rotor design and the structure of general autogyro; It is characterized in that: according to the ultromotivity level theory; In two rotor junctions one pitch axis is set, lift makes rotor rotate within the specific limits changing the rotor elevation angle around pitch axis to the moment of pitch axis, the size of the mode self-equalizing both sides blade lift through a kind of sinusoid periodically-varied elevation angle; Make both sides lift keep equating, to increase substantially flying speed and stability.

2. pitch axis according to claim 1; It is characterized in that: in the practical implementation process; The blade pass of both sides rotor is crossed horizontal pitch axis connect into as a wholely, on the one hand this integral body drives down at the copter engine axle and rotates, on the other hand; Rotor blade can rotate around pitch axis within the specific limits in this is whole, thereby changes the blade elevation angle.

3. rotor according to claim 1; It is characterized in that: rotor with fixed elevation; Connect in aggregates through horizontal pitch axis; And the lift point of action that two rotors are produced in rotation drops on the rotation rear of pitch axis, and making lift is a stabilization system for the mechanical system of pitch axis.

4. ultromotivity level theory according to claim 1 is characterized in that: in the process of autogyro flight, the lift that the windward side rotor produces will be greater than the lift that side produced with the wind; The lift of windward side blade for the moment of pitch axis greater than side with the wind; Two rotor blades will rotate an angle forward around pitch axis under to the effect of moment at this, thereby the windward side rotor elevation angle is diminished, and lift diminishes; It is big that the leeward side elevation angle becomes; It is big that lift becomes, and when both sides lift equated, the effect that moment is rotated stopped.In rotor uniform rotation process, blade can be synchronous with sinusoidal waveform pitch mode and rotor rotation period around pitch axis, and the pitching amplitude then increases with helicopter speed.