CN1108253C - Spherical crown helicopter with single rotary wing and no tail paddle - Google Patents

Abstract

The present invention relates to a spherical crown helicopter with a single rotary wing and no tail rotor according to the principles of aerodynamics and flight. The present invention is characterized in that the body of the helicopter is in the shape of a spherical crown or a polygon which is similar to the shape of a spherical crown, a plurality of guide blades are arranged around a lower circular ring of the body of the helicopter, the guide blades can generate annular torque to balance the autorotation torque of the body of the helicopter when the helicopter flies in order to keep the stability and the directions of the body of the helicopter. In addition, a center under a bottom board of the body of the helicopter is provided with an omnidirectional rotary jet engine, and thus, the aims of vibration, noise and volume reduction, stable flight, simple manipulation, flexible maneuver, high speed, safety and reliability are obtained for the flight of the helicopter.

Description

Spherical crown helicopter with single rotary wing and no tail paddle

The invention belongs to the autogyro technical field, particularly a kind of spherical crown helicopter with single rotary wing and no tail paddle.

Existing single rotor helicopter is that back is equipped with a secondary huge main rotor, and in cant beam one side of back minister long-tail beam end, a secondary slight tail-rotor is housed, and the plane of rotation of tail-rotor is vertical with the plane of rotation of main rotor.Because it is simple in structure, can vertical lift, also can arbitrarily aloft hover, flight forward, left, to the right and backward, maneuverability does not need the necessary long runway of general aircraft especially, can be on any fritter level land or ships vertical and landing takeoff.Thereby since first practicality autogyro of early forties is born, developed rapidly, use also very extensive.

But publish by the shady chief editor's of kingly way " the air science technology of the 21 century of the marching toward " book of etc.ing from magazine such as " aviation knowledge ", " international airline " and aircraft industry press and to learn that having single rotor helicopter now also has following shortcomings to have much room for improvement:

By focus such as helicopter main rotor, tail-rotor and driving engines to the excitation of body and bring very big vibrations to helicopter.Thereby influence the traveling comfort of taking, also influenced the helicopter body, the durability of parts and instrument, time one length will endurance failure and reduce life-span of helicopter, reduces the accuracy rate that armed helicopter hits unfriendly target.

2. no matter take off, landing or cruising flight, noise is all very big.

3. because the main rotor and the tail-rotor of high speed revolution, the object around the collision and cause aberdeen cutlet easily when low-latitude flying.

4. though can adopt main rotor spin emergency landing during the driving engine accidental shutdown, this moment, tail-rotor can not be controlled fuselage, when falling fuselage still can from then unstability fall.

Flying speed than the flying speed of general aircraft relatively slowly many.

Wherein first and second shortcomings mainly are focus---due to driving engine, main rotor and tail-rotor rotate.The vibrations that driving engine itself produces, main by driving engine technology is improved.And the helicopter main rotor is circular because of the track of its rotation, and it produces downward thrust body horizontal projection also is circular.And the fuselage of existing helicopter mostly is strip shape greatly, and this fuselage shape is useful to the resistance that reduces flight forward, but because the horizontal projection of strip shape fuselage is asymmetric with circular main rotor thrust body horizontal projection.Whenever blade of main rotor all can fly down during through forebody or afterbody or tail move downward.And when this blade flew away from fuselage, this thrust was from the fuselage disappearance and affact air layer, so head or tail upwards reset again.Just cause the fuselage vertical tremor so repeatedly.Horizontal tail on the existing tail boom of other also is located at outer edge in the helicopter thrust field, and the downward pressure of outer rim is parabola along radial direction and becomes big than inner big many.Therefore tailplane has more aggravated head and tail boom vertical tremor, promptly produces frequency and becomes the cycle of multiple to shake (pulsation) with the number of blade with rotating speed.

Blade is at fuselage in addition, and is also different with the noise that is produced above blade leaves fuselage and tail during the tail top.This is bigger to people's stimulation than the light of Chang Liang just as the light that flashes, and the noise of therefore existing autogyro also is the cycle pulsation relevant with rotating speed and number of blade.The noise of pulsing during with noise intensity more has a strong impact on the traveling comfort that people take than sound intensity unmodified noise.

To the 3rd shortcoming, main rotor can't overcome real the genus unavoidably.But tail-rotor is because it is installed in the back segment of tail beam, and chaufeur is difficult for seeing and controlling, and causes aircraft accident than object such as massif, building and trees around the easier collision of main rotor when low-latitude flying.

After the 4th shortcoming mainly be the driving engine accidental shutdown, due to the tail-rotor rotating speed can not be controlled.

To the 5th shortcoming, existing autogyro flying speed be slowly because the helicopter main rotor turns forward and the upwards thrust that produces when rotating in, most of thrust is used for the gross weight of rest body and load, and only a fraction of component flies autogyro forward, thereby speed is slower than general aircraft.

Goal of the invention of the present invention is exactly the deficiency at above-mentioned situation, and from flight theory and pneumatics angle, a kind of structure and performance to existing single rotor helicopter of developing carried out improved spherical crown helicopter with single rotary wing and no tail paddle.

The present invention is made up of fuselage 1, main rotor driving engine 3, main rotor 5, alighting gear 13.The polygon bodily form that is shaped as spherical or approximate spherical crown of described fuselage 1, described main rotor 5 suspension centres are positioned at fuselage 1 top center place.Because of no matter the main rotor blades of autogyro installs several, it all is relative center of circle symmetric arrangement, so no matter the main rotor of autogyro is in which angle, the spherical relatively fuselage of these blades is always dynamically symmetrical, spherical in addition fuselage just in time is positioned at the position of main rotor thrust body center thrust minimum, so that main rotor pushes away the strength of fuselage downwards is minimum and symmetrical.Thereby the relative existing general autogyro with noise of the vibrations of fuselage is little.In order to be suitable for parking of hangarette, reduce body and take up an area of size, main rotor 5 can be made into folding shape.

The tail-rotor of existing autogyro is the moment of torsion that makes hull rotation when rotating for the balance main rotor.Traditional tail-rotor rotating speed is very high, is positioned at the end of tail boom again, and chaufeur be difficult for to be observed, thereby tail slurry easily bumps against and has an accident with object on every side during low-latitude flying.For this reason, the present invention cancels this tail-rotor, changes the movable guide vane 8 and the fixed guide vane 15 of some plane of bendings of garden ring periphery installation under spherical fuselage into, and the periphery is provided with the annular retaining ring 9 that a circle is supported by annular stator support 23.The downdraft that produces when helicopter main rotor rotates will produce the hoop moment of torsion when passing the stator of these plane of bendings, and the main rotor rotating speed is high more, and hull rotation is fast more.In order to keep fuselage plane stability and direction, just need the control stator to produce the size of moment of torsion.But be not that whole stators all need to rotate, can be positioned at a part heads up display under and hatch door below stator make fixed guide vane.Other stators are then made can be around the movable guide vane of guide vane teunnion rotation.These movable guide vanes its kinematic velocity and amplitude in being conditioned process is all very little, and people almost do not feel variation.Angle by regulating these movable guide vanes is with regard to may command fuselage balance and fuselage sense of motion.The helicopterist can handle the anglec of rotation of these stators by the electric hydraulic type of drive, thereby the size that changes the hoop moment of torsion reaches the rotation that the balance helicopter hull produces when flight, keep the in-plane of fuselage.Certainly also can change the circular rector size, and realize handling fuselage cw or inhour rotation by the corner of these stators of control.

In order to improve the speed of autogyro, no matter and make helicopter, to the right or backward during inverted flight left, also can be steady when flying forward, the center of the present invention below fuselage chassis 12 be provided with one can 360 the jet engine 24 that horizontally rotates of degree, and make helicopter at vertical lift or when hovering by devices such as computer and electric liquid transmissions, can this jet engine of SELF CL.When autogyro when the ground, jet engine 24 front and back all can automatic sealing, avoids the dust that flies upward and little sandstone to enter in the jet engine and causes damage.Analyze from flight theory, generally be positioned at the center on close floor, cabin because of the center of gravity Q of autogyro.When main rotor dish some angles that turn forward, the upwards component F1 balance fuselage of its lift F and load weight G and hold up autogyro, i.e. F1=G; The F2 of component forward of its lift F, then spurring helicopter hull flies forward, but the suspension centre of this component is positioned at the fuselage top, away from center of gravity Q, and the moment of torsion M1 that generation turns forward to fuselage (M1=F2 * L1), so when the main rotor dish turned forward suddenly, fuselage also and then turned forward, and magnitude of inclination is very big.This also is to take general autogyro not take one of comfortable reason of conventional airplane.The present invention is owing to installed a jet engine additional in the center of spherical fuselage lower plane, (the turn forward moment of torsion M1 direction of generation of M2=F3 * L2) and main rotor is opposite to moment of torsion M2 that fuselage produced for the thrust F3 that its produces, size is close or identical, i.e. M1 ≈ M2.Two kinds of equilibrium of torquess make the existing autogyro of fuselage much steady.Because of jet engine shorter from center-of-gravity position to center-of-gravity position than main rotor suspension centre, if fuselage up and down two kinds of moment of torsion M1 and M2 balance.This engine thrust F3 will be bigger than the main rotor maximum component F2 that leans forward.General existing helicopter has only F2 promotion helicopter to advance, and the present invention is that F2 and F3 unite propelling, and F3＞F2, so about the speed of autogyro of the present invention can be twice than existing autogyro.Even and swerve in-flight and speed, fuselage also can compare steadily.

Because the present invention can not want tail boom.So its manoevreability can be better.Make progress, forward, backward, all very flexible to the left or to the right.Area is big under the circular fuselage base plate, and the various weapons of fine discharging need need not be set up flat beam in addition and hang weapon as existing autogyro, be well suited for doing military type helicopter.But to maneuverability requirement not high to when flight direction very steady, take and want comfortable civilian autogyro, then can behind spherical fuselage, add a tailstock 26.The tailstock end refills establishes vertical fin 28 and horizontal tail 27, but No Tail Rotor.

Alighting gear of the present invention can make 3 wheeled 13, also can be made into skid formula 29.

In sum, the performance of the existing relatively general outstanding wing autogyro of list of the present invention has following improvement and raising:

1, airworthiness improves a lot, and promptly the amplitude of complete machine oscillation can more obviously reduce.

2, the complete machine noise can decrease, especially pulsations.

3, because vibration and noise reduce, can improve civilian traveling comfort of taking and army-accepted pointing accuracy, slow down the endurance failure of structure, member and the instrument and meter of complete machine, improve the safe reliability and the economic serviceability of flight.

4, the tail slurry that does not have high speed revolution, only the stator by semisphere fuselage periphery obtains circular rector balance hull rotation.The mode of this electrohydraulic control stator is simple, and is reliable, sensitive and do not have high-speed moving part, the No Tail Rotor accident, so safety is improved, fuselage length and volume also can reduce.

5, stopping accident occurs, in the time of need utilizing the rotation emergency landing of main rotor, can manually control stator corner balance and stable fuselage, thereby improve the possibility that emergency landing is saved oneself.

6, because fuselage is the polygon bodily form of spherical or approximate spherical crown, top-surface camber lower plane aerodynamic produces the principle (similar aircraft wing produces the principle of lift) of lift, but the saving in power and the energy.

7, install the jet engine in a controlled orientation under body additional, flying speed and steering stability can obtain bigger raising.

8, the thrust of general helicopter tail rotor is perpendicular to heading, and permanent effect is got off the plane and can be drifted off the course, and must come balance by a small amount of inclination angle that appropriateness is adjusted main rotor.And the present invention is by stator balance hull rotation, can not influence the autogyro driftage.

The present invention is further described below in conjunction with drawings and Examples.

Accompanying drawing 1 is the pneumatic force analysis comparison diagram of the present invention and existing single rotor helicopter.

Accompanying drawing 2 is comprehensive force analysis figure of the present invention.

Accompanying drawing 3 is stator force diagrams in main rotor thrust field among the present invention.

Accompanying drawing 4 is structure longitudinal sectional drawings of the present invention.

Accompanying drawing 5 is structure level section-drawings of the present invention.

Accompanying drawing 6 is constructionals drawing of first embodiment of the invention.

Accompanying drawing 7 is constructionals drawing of second embodiment of the invention.

Accompanying drawing 8 is constructionals drawing of third embodiment of the invention.The meaning of various letter representatives is as follows among Fig. 1 and Fig. 2:

O---the planar central of main rotor dish is the center of thrust body simultaneously

R---main rotor dish radius, both main paddle radius

P---main rotor thrust body wind pressure value radially

The application force that f---rotor air-flow produces stator

F1---the hoop thrust that the main rotor air-flow produces when passing stator

The component downward vertically that f2---main rotor air-flow produces when passing stator

F---the main rotor life force when leaning forward

The main rotor of F1---rest helicopter deadweight and the load vertical component that makes progress

F2---promote the main rotor horizontal component of force that helicopter advances

The horizontal thrust that F3---jet engine produces

Q---the total centre of gravity of body deadweight and load

L1---main rotor suspension centre is to the distance of center of gravity

L2---the jet engine horizontal thrust is to the distance of center of gravity under the fuselage

M1---when main rotor leans forward to the moment of torsion of fuselage

M2---jet engine is to the moment of torsion of fuselage

G---each position and each component names are as follows among gross weight Fig. 4 to Fig. 8 of body deadweight and load: 1. fuselage 11. movable guide vane axles and tumbler 21. cabins 2. engine intakes, 12. fuselage chassis, 22. cabin doors, 3. main rotor engines, 13. wheel undercarriages, 23. annular retaining ring supports, 4. swashpiston mechanisms 14. heads up displays, 24. jet engines, 5. main rotors, 15. fixed guide vanes, 25. folding main rotor 6. engine gas outlets 16. floor observation windows, 26. tailstocks, 7. seats, 17. steering wheels, 27. horizontal tails, 8. movable guide vanes, 18. driver seats, 28. vertical fins, 9. annular retaining rings, 19. driving cabins, 29. slide-type undercarriages, 10. luggage equipment compartments, 20. fuel tanks, 30. driving cabins hang down window 31. controllable sealings lid

The fuselage 1 of autogyro is made spherically as shown in Figure 4 and Figure 5, and one or two whirlpool axles or piston engine are installed in the top of fuselage 1.In order to make autogyro when flight resistance minimum, offer the admission port 2 and the air extractor duct 6 of main rotor driving engine 3 on spherical fuselage 1 top.Main rotor driving engine 3 drives main rotor blades 5 rotations and produces life force F lifting body.Chaufeur flies helicopter by control main rotor the vert inclination angle and the orientation of disc mechanism 4 forward, left, to the right and backward.Main rotor do not tilt then helicopter in hover, vertical uplift or vertical decline.

Garden ring periphery is installed the movable guide vane 8 and the fixed guide vane 15 of some plane of bendings under the spherical machine.Below the heads up display 14 of driving compartment 19 and cabin door 22 places, because inconvenient installation and control stator rotating mechanism is just made fixed guide vane 15, all the other stators are then made movable guide vane 8.Chaufeur just can change the hoop thrust that these movable guide vanes 8 produce by the corner of electric hydraulic driving system control movable guide vane 8 in the following gas washing stream of main rotor 5 rotations.But fuselage 1 rotation that total torque balance main rotor 5 rotations that 8 pairs of fuselages of fixed guide vane 15 and movable guide vane 1 produce cause keeps the horizontal direction of fuselage 1 stable.Control movable guide vane 8 and fixed guide vane 15 moment of torsion total amounts are greater than or less than the moment of torsion of fuselage 1 rotation, turn to the left or to the right with regard to may command fuselage 1.In order to protect these stators and to reduce flight resistance, the stator periphery that hoop is arranged adds the annular retaining ring 9 that a circle is supported by annular stator support 23.Heads up display 14 and bearing circle 17 are installed in the place ahead in the driving compartment 19, are thereafter driver seat 18.Driver seat is respectively opened an observation window 16 on 18 the right and left floors, and heads up display 14 belows two sides are respectively opened the low window 30 of a driving compartment and observed state of ground in order to landing or when taking off.Because of fuselage 1 is the spherical crown shape, seat also can be arranged in parallel except that ring-type is arranged in the cabin 21.Fuel tank 20 and luggage equipment compartment 10 can be established in ring-type seat 7 back on movable guide vane axle and the wheel word 11.As for cargo helicopter, seat is not installed in the cabin, only several seats that can fold up and down are installed and both can at the cabin inside circumference.If cabin 21 divides into interlayer, the interlayer end face flushed with 22 ends of cabin door, passed in and out more conveniently, and fuel tank 20 also can be located in the interlayer.The below of spherical fuselage 1 base plate is equipped with 3 wheel undercarriages 13.

In order to improve that helicopter is flown forward by the unexpected startup of floating state and awing when flip-flop heading or state, avoid fuselage 1 phenomenon of knockdown to occur and improve the speed of autogyro.The turbofan jet engine 24 that can do 360 degree rotations is installed in center below fuselage chassis 12.This driving engine is by computer control rotational angle and orientation, and the orientation is corresponding with the main rotor dish 4 bevelled orientation of verting all the time.If the moment of torsion M1 that moment of torsion M2 that the size of the thrust F3 that jet engine 24 produces and L2 form and main rotor component F2 and L1 form is approximate or equate that then helicopter is just steady.The big I of F3 is obtained by the oil inlet quantity of computer control jet engine 24.

As shown in Figure 6, jet engine 24 is not installed below the fuselage chassis 12, this form and existing autogyro relatively, velocity contrast is few, but performances such as vibration and noise have improvement.The No Tail Rotor overall dimension reduces, and safe and reliable.

As shown in Figure 7, the main rotor 5 of this autogyro is made into collapsible main rotor 25.This more reduces autogyro plane overall dimensions, also just reduces the hangar size.When main rotor driving engine 3 does not start, when only opening jet engine 24, autogyro just can run on ground as automobile, also can conveniently pass in and out the autogyro storehouse.

As shown in Figure 8, this type is bigger, and the rear portion of fuselage 1 adds tailstock 26, and its end also is equipped with horizontal tail 27 and vertical fin 28.In order to make the suppressing action that gas washing flows tailstock under the main rotor reduce to minimum, thereby reduce the pulsation vibrations that cause by long and thick tail boom as common autogyro, tailstock is only made truss-like with aluminium alloy extrusions, length extends to outside the main rotor dish horizontal projection garden, and horizontal tail or vertical fin are in outside the thrust field of helicopter main rotor generation.Like this, directivity is stronger during autogyro flight, and fuselage is also more steady.Skid formula alighting gear 29 is installed under the base plate of fuselage 1.

Claims (1)

1. spherical crown helicopter with single rotary wing and no tail paddle of being formed by fuselage (1), main rotor driving engine (3), main rotor (5), alighting gear (13), its fuselage (1) is the polygon bodily form of spherical or approximate spherical crown, the following annulus periphery of fuselage (1) is provided with movable guide vane (8) and fixed guide vane (15), it is characterized in that: the center below the fuselage chassis (12) is provided with a jet engine that can horizontally rotate (24), and controlled seal cover cap (31) is installed before and after it; Described fixed guide vane (15) is positioned at heads up display (14) and cabin door (22) below, and other stators can be made movable guide vane (8); The periphery of its fixed guide vane (15) and movable guide vane (8) is provided with the annular retaining ring (9) that a circle is supported by annular stator support (23).

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