CN102336269A - Vertical taking off and landing (VTOL) technology of full-thrust vertical taking off and landing vector fighter airplane - Google Patents

Abstract

The invention provides a vertical taking off and landing (VTOL) technology of a full-thrust vertical taking off and landing vector fighter airplane, comprising an engine air inlet passageway and an engine tail spray pipe. The engine air inlet passageway consists of a pipeline which is similar to a tee joint, an upper air inlet baffle plate and a front air inlet baffle plate which is taken as a front air inlet pressurization bag; and the engine tail spray pipe consists of a connection part and a power device, wherein the connection part is used for connecting three sections of circular pipes, one section of straight pipe and four sections of spray pipes in proportion, and the power device consists of three planetary speed reducers, four universal joints, two telescopic links, a power guide rod and a driver. The two parts are combined with the existing airplane engine, so that the directions of an air inlet and an air outlet of the airplane engine are changed, the direction of a gravitational force and a reverse thrust of the airplane engine are changed, the gravitational force and the reverse thrust are wholly changed into a lift force of the airplane, and the whole output power of the airplane becomes the vertical taking off and landing power of the airplane.

Description

Full thrust VTOL vector fighter plane VTOL technology

Technical field

Mechanical device, transportation.B64F is used to install to the equipment on the aircraft, advances the device of aircraft transmission.

Background technology

This technology is the revolutionary innovation to prior art; Why well-known aircraft can fly is to utilize the atmospheric pressure up and down of wing poor; Power is from aero-engine; The aircraft situation smaller in the space thereby being the reaction thrust of aero-engine, forming process make the aircraft forward movement make the wing on the go produce pressure difference, because of can't have enough spaces to satisfy the distance that aircraft moves ahead.

My technology is to utilize atmospheric pressure; Promptly upwards change 90 degree (can be different angles as required) to the gravitation of driving engine nose air intake generation pressure difference; Thereby realize changing the whole power of fighter engine into the lift of fighter plane, principle is the same with the wing pressure difference, and difference is the existence of breaking away from wing; Be under the enough good situation of engine performance; Can cut down two wings of aircraft and can fly in the same old way fully, and maneuvering performance be superior, thereby realize abandoning the aircraft influence of wing of when high-speed maneuver, fighting the aircraft high-speed maneuver

Thereby my technology is to utilize prior art to increase the lift and the high-speed maneuvering capability of the driving engine nose air intake path and the full horsepower output of air nozzle path, back direction modifier realization driving engine.

Summary of the invention

Full thrust VTOL vector fighter plane VTOL technology comprises two parts:

One, the admission port baffle plate is gone up and a nose air intake baffle plate that had both served as the effect of nose air intake supercharging bag is formed by the pipeline of a similar threeway and one in engine inlet port path.

Two, nozzle is formed by three proportional pitch circle pipes and a joint straight tube and four joint jet pipe connecting bridges and by the engine installation that three planetary reduction gears, four universal-joints, two expansion links, power export bar and driving machines are formed.

Thereby realize changing the direction of engine inlet port and air nozzle by above two parts and the combination of existing aero-engine; Thereby realize changing aero-engine gravity direction and reaction thrust direction; Make gravitation and reaction thrust all transform the lift of aircraft, the whole horsepower output that reaches aircraft becomes the VTOL power of aircraft.

  

Concrete design comprises three parts:

One, vector VTOL tail spray design.

Two, vector VTOL opportunity of combat nose air intake design part.

Three, the design of vector spray and admission port is applied to large-scale early warning plane and fuel charger makes it have the design part of short distance and VTOL.

  

First, jet pipe design comprise the realization of four steps:

1, vector spray pipe design.

2, the vector spray pipeline partial design that is rotationally connected.

3, vector spray crooked with stretch the rotational power mode and design.

4, the spacing design of vector spray rotation.

     

1, vector spray pipe design:

Vector spray is under the situation of case of bending, is exactly a pipe that becomes certain angle of bend in fact.

(1), crooked vector spray cuts open from central cross, section is two camber lines that radian is identical.Existing the radius called after of little camber line: r; The radius called after of big camber line: R.

When the vector spray rotation makes its bending or straight configuration; Jet pipe must be divided into the number joint; Existing is that three joints are told about with vector spray, becomes two sections camber lines that radian is identical when vector spray as described above becomes case of bending, is divided into three joints because of vector spray again; Be that every camber line is formed by three sections, and big or small camber line is connected to three sectors along plane of rotation.Shown in (Fig. 1).

  

If the radian of former and later two sectors is: α (so because these two sector radians must equate to be made as identical α); The radian of intermediate sectors is: β; The design-calculated maximum flexion of vector spray: θ. the diameter of vector spray mouth is: ι; The total length of vector spray straight configuration: L is shown in (Fig. 2).

Between the above-mentioned variable from following mathematical relation:

R-r=ι

2α=β

2α+β=θ

4R*sin(α/2)cos(α/2)+2r*sin(β/2)=L

2, the vector spray pipeline partial design that is rotationally connected:

Optimal in theory vector spray is: R=ι, and r=0. but need the rotating disk of two activities between three sections jet pipes causes the radius of r to be 0, and the rotating disk hinge portion is shown in (Fig. 3).

  

The rotating disk Installation Considerations:

The teeth of two gear rings are the angle of (90+ α) and (90-α) respectively with gear ring; So that drive shaft; Must make stage casing jet pipe hinge portion be positioned at the inboard, the jet pipe hinge portion at two ends is positioned at the outside and gear ring is adhered in its outside, makes the two ends jet pipe become the middle driven jet pipe of jet pipe; Thereby realization is fixed in driving engine with one section jet pipe and can't be rotated; Cause terminal jet pipe under the driving of coaxial drive axle, also can't rotate, and middle jet pipe is done the rotation of opposite end jet pipe under the rotation of axle drive shaft, thus the bending that realizes vector spray with stretch.

  

3, vector spray crooked with stretch the rotational power mode and design:

4, rotational power is designed with two kinds of designs:

(1) external drive mode is shown in (Fig. 4)

(2) the centre-driven mode is shown in (Fig. 5, Fig. 6)

External drive mode benefit simplicity of design realizes simple; Thereby being driving machine, weak point must increase the space between jet pipe and the fuselage so that have no obstruction during the rotation of stage casing jet pipe in that vector spray is outside; Driving machine is if need to install the hydraulic bidirectional locking additional in the import and export of driving machine hydraulic oil with hydraulic driving machine; Hydraulic bidirectional locking like the crane supporting leg; Oneself rotate under the air-flow effect of driving engine with shooting nipple assembly, the rotation of stage casing jet pipe is realized on multi-shaft interlocked technology of also available China lathe or hydraulic pressure hilllock.

  

The centre-driven mode obviously is the mode that is superior to external drive; Thereby utilize three planetary reduction gears to make three joint vector sprays do relative motion and realize stretching of vector spray with crooked; Make the gap between vector spray and the fuselage compact more, during rotation only jet pipe rotating, and driving machine self does not rotate; Thereby can fixed drive machine pipeline and circuit, be difficult for causing the wearing and tearing of pipeline more because of the rotation of vector spray with respect to first kind of mode.And can 360 any rotation of degree.

  

5, the spacing design of vector spray rotation:

At first section and stage casing jet pipe rotating element sensor or a travel switch, prevent that jet pipe from rotating the position.Multimode is arranged in the middle of the reality, all can use, so not at this Ao Shu.So far vector spray design is accomplished, and this vector spray can not only use also available naval vessel of various fighter plane and submarine to increase naval vessels and submarine high-speed maneuver on narrow and small navigation channel.

  

Second portion, vector VTOL opportunity of combat nose air intake design part: be divided into two types four kinds:

1, admission port design plan on admission port and the many baffle plates on single baffle plate of single-shot fighter plane.

2, admission port design plan on admission port and the many baffle plates on single baffle plate of two fighter planes.

  

1, admission port and many baffle plates admission port design plan on single baffle plate of single-shot fighter plane.

(1) on single baffle plate the admission port design plan shown in (Fig. 7),

According to aerodynamics; Changing driving engine nose air intake direction makes the gravitation forward of engine inlet port generation become fighter plane lift fully; Be to solve to comprise Britain's sparrow hawk formula VTOL and the forced gravitation that the preceding spray of jet pipe balanced engine admission port is produced of U.S. F-35 now, and make the reason of the most of forfeiture of engine efficiency.Desiring head it off must make driving engine nose air intake direction change as required; Even open admission port when engine inlet port can be closed nose air intake as required; Can not close preceding import simply according to aerodynamics and open an admission port to aircraft top; Because the air of motion has certain rigid; For preventing that air-flow from running into vertical body and being rebounded, must become a ball cambered surface to preceding import baffle design, thereby be implemented in the effect that the suction quantity that does not change engine inlet port in the process of flapper closure plays an air baffle simultaneously again.During admission port, spherical nose air intake baffle plate plays the effect of nose air intake air compression bag again on closing.

(2) on many baffle plates the admission port design plan shown in (Fig. 8),

Single upper inlet baffle plate is opened in the aircraft flight process or when upwards climbing at a high speed, thereby baffle plate the place ahead area of contact is excessive to cause to baffle plate that thereby the power of overstocking is excessive to be damaged easily, but how to go up admission port baffle plate head it off, with two upward the admission port baffle plate be example:

Before go up the admission port baffle plate need be the back go up the admission port baffle plate 1/2nd, therefore can when not opening fully, not block the suction quantity that admission port on the back influences upper inlet because of two baffle plates in top because of admission port baffle plate on preceding.

If do not use upper inlet during as the power operated power of aerial high-speed and only as the fighter plane landing, single baffle plate and many baffle plates difference are little.

  

2, admission port design plan on admission port and the many baffle plates on single baffle plate of two fighter planes

Two fighter planes can also be gone up admission port to two of two fighter planes and unite two into one except can solving with two single-shot fighter plane admission port schemes, Qi Ding, preceding and sectional view shown in (Fig. 9, Figure 10),

Two send out baffle plate many on admission port design plan and single-shot Ao Shu roughly the same no longer, so far full thrust vectoring VTOL vector opportunity of combat design is accomplished, if you add thinking, possibly also can find two problems, that is exactly:

When jet pipe rotates, be not only to change air flow line up and down, side direction also has small change, and this can revise through fighter plane empennage and the terminal fine setting of jet pipe.This is the defective of external drive, and there is not this problem in centre-driven.Centre-driven, the one or three joint jet pipe is done relative motion with respect to second joint, and when one or three joints were spent with respect to body movement 90, jet pipe reached maximum flexion, and motion then recovers straight configuration again.

The nose air intake baffle plate is different with the cireular frequency of last admission port baffle plate and jet pipe rotation; Be nose air intake rotation 45 degree, the upper inlet baffle plate needs ROT13 5 degree, and jet pipe needs the Rotate 180 degree, and we must let two the admission port baffle plates in front synchronously and can reach self-movement synchronously with jet pipe for fighter plane is aloft grappled; Given this, can be at that operating handle of cabin design, a VTOL operating handle; Another high-speed maneuver operating handle, this handle can be integrated on the airplane operation handle.By top we obtain the cireular frequency of admission port and jet pipe.The driven wheel radius ratio of nose air intake baffle plate and last admission port baffle plate is 3:1.If upper inlet is carried out 135 degree for two baffle plates and one; Another carries out 90 degree; The driven wheel radius ratio of two baffle plates of admission port is an import barrier driving tooth radius before 3:2:1. jet pipe Rotate 180 degree and rotating disk radius are far longer than on the nose air intake baffle plate; Just can close the admission port baffle plate if promptly must let jet pipe stretch earlier in the opportunity of combat takeoff condition; Opportunity of combat changes vertical 45 degree into by horizontal attitude and changes level once again into and become normal sortie attitude like this, makes opportunity of combat head download fatal crass under jet pipe makes progress thrust otherwise can cause aircraft just to go up in the air slowly because of jet pipe changes.Head it off is if automatically controlled push button control can install one by one on the power supply of import before switching that delayed startup solves reforming.But open the upper inlet power supply and must get around the delayed startup device; Make aircraft like this and be in a safe attitude all the time no matter take off or land.

  

The designs of third part, vector spray and admission port are applied to large-scale early warning plane and fuel charger makes it have the design part of short distance and VTOL:

We know: large-scale early warning plane, bomber and fuel charger self gravitation excessive on aircraft carrier landing certain difficulty is arranged; Fwd vector jet pipe has been arranged; Under the situation that does not have the aircraft carrier JATO engine; We also can solve, because their driving engine is all on wing, it is unworkable that the preceding import of fighter plane changes the mode of gravitation; But we can one in front and one in back be installed in the driving engine two ends with two vector jet pipes and solve, at this section-drawing of only drawing driving engine and vector spray shown in (Figure 11, Figure 12).

Description of drawings:

Fig. 1 is a jet pipe case of bending section-drawing

Fig. 2 is a jet pipe straight configuration section-drawing

Fig. 3 is jet pipe connecting bridge section-drawing and gear ring

Fig. 4 is jet pipe external drive mode figure

Fig. 5 is a jet pipe internal drive case of bending section-drawing

Fig. 6 is a jet pipe internal drive straight configuration section-drawing

Fig. 7 is single admission port baffle plate admission port path section-drawing of going up

Fig. 8 goes up admission port baffle plate path section-drawing

Fig. 9 be two send out, admission port path section-drawing on two admission port list

Figure 10 goes up the half-open and full-gear section-drawing of gas port baffle plate

Figure 11 is that two jet pipes are applied to fuel charger straight configuration air movement scheme drawing

Figure 12 is that two jet pipes are applied to fuel charger case of bending air movement scheme drawing.

Claims (1)

1. one kind is contained in the change aircraft aerodynamic arrangement realization high-speed maneuver at existing aero-engine two ends and the device of VTOL, is made up of two parts:

One, the admission port baffle plate is gone up and a nose air intake baffle plate that had both served as the effect of nose air intake supercharging bag is formed by the pipeline of a similar threeway and one in engine inlet port path.

Two, nozzle is formed by three proportional pitch circle pipes and a joint straight tube and four joint jet pipe connecting bridges and by the engine installation that three planetary reduction gears, four universal-joints, two expansion links, power export bar and driving machines are formed.

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