CN1472113A - Helicopper - Google Patents

Abstract

A novel rotary-wing aircraft features technically that the rotary wings with torsion regulatable wings, switch linkage control, automatic limitation of distance between wings, upward elevated crossed dual rotary wings, and propeller for horizontal drive are used. Its advantages are vertical taking-off or landing, low noise, less fuel consumption, and low cost.

Description

Helicopper

The invention belongs to the aeronautical technology field, is a kind of Helicopper.

The appearance of aircraft for the mankind have opened up aerial passage, has enlarged the people's activities space.Along with science and technology development, aircraft is also in development gradually.The controllable pitch propeller of prior art, be that fixedly oar axle with ordinary fixed pitch blade changes the pitch adjusting shaft into and constitutes, the shortcoming of this controllable pitch propeller is: the efficient operation setting range of pitch is little, and entire blade is all rotated with equal angular during adjustment, and it is only setting pitch ability efficient operation; It is adjusted to when departing from optimum value, has only a certain section efficient height of blade, other position stagger angle error increases, and efficient obviously reduces.Because the deficiency of existing controllable pitch propeller, thereby the various development that utilize the aircraft of controllable pitch propeller work have been limited.

Prior art shown in Figure 7 is a kind of rotor that has servo-flaps 1, the conventional blade that its twist has been fixed, and its twist can't be adjusted; This oar is equipped with servo-flaps 16, and these servo-flaps 16 are to be used for adjusting by a small margin the lift of rotor, and can not change its blade is the basic feature that negative twist is changeed, and its efficient pitch setting range is little.

Though the cyclogyro of routine techniques and helicopter are two kinds of comparatively outstanding aircraft, their all deficiencies separately, still can not satisfy people simultaneously and wish: landing is flexibly, efficient, safe and reliable, economic and practical various requirement flies.

The rotor blade of the fuselage outer side of the intersection bispin wing type of prior art, the blade degree of sag is bigger, and the probability that collide mutually on its outside rotor blade and ground is bigger, and the safety of its landing is on the hazard.

Conventional rotor craft, isonomic type variation pattern is few, thereby has influenced its segmentation to market, and its remodeling development of overslaugh reduced field of application, thereby the reduction of its cost is restricted, and the developing the economy property of its series model is restricted.

Conventional cyclogyro advances with speed V by the horizontal drive of forebody or rear portion screw propeller, windstream passes through rotor plane with the speed V with respect to cyclogyro, flow level is passed the rotor rotational plane and is driven the rotation of rotor high speed, make rotor obtain lift and fly, blade is changed a job and is made the state (see figure 3) for negative pitch, positive twist.It is substantially parallel with the course that air communication is crossed the later air wake flow of rotor, and with the crossing disturbing flow of fuselage, the interference wake flow of screw propeller generation is also not less in-flight, so the efficient of cyclogyro cruising flight is higher, oil consumption is lower.Fig. 1, Fig. 2 are the rotor and the wake flow scheme drawings thereof of cyclogyro, and the curved arrow of rotor rotational plane is represented the rotor rotation direction among the figure.Its rotor when cruising is in the rotation mode of operation, does not have the pitch Adjustment System, does not also have main reduction gear, and this organizational security has been held lower noise and fault rate.After this machine aloft ran out of steam, aerodynamic requirement when the stagger angle of rotor blade still can meet its forced landing was in just reversing of needing, and has the normal work angle of attack, keeps higher pneumatic efficiency, and its fall off rate is low, and safety performance is good during forced landing; This machine breaks down, and can cause the parts of significant impact to have only rotor, connect the main shaft and the fuselage load-carrying construction of rotor inherently safe, so its safety factor is big, reliability is high; But it can not vertical takeoff and landing, and pad is bigger, thereby has influenced its widespread use.

Pure helicopter drives rotor flight by power through main reduction gear, and air-flow is passed down through the rotor rotational plane by the top of oar dish, changes (see figure 5) so blade is positive pitch, negative twist.The following gas washing stream that rotor produces during flight, the large tracts of land that is subjected to downward projection direction fuselage hinders, and produces bigger aerodynamic force loss; Fig. 5 is that the rotor and the following gas washing stream thereof of helicopter in the prior art is subjected to the scheme drawing that fuselage hinders.The single rotor type that is in the great majority in helicopter, the horizontal racemization air-flow that its tail-rotor produces is vertical with the course incoming flow, also can increase the aerodynamic force loss.These two kinds of phenomenons all can reduce the aerodynamic efficiency of its cruising flight, increase consumption of fuel.Helicopter is when flight, and in operation, the noise of work is big, safety factor is low all the time for feathering system, main reduction gear.This machine is if aloft run out of steam, it can only utilize: design is at the change a job rotor blade A (shown in Figure 75) of the state of doing of positive pitch, negative twist, pressing down the pitch joystick makes rotor blade be adjusted to negative pitch, its rotor goes to the angle of blade A ' by the angle of blade A, carries out the unpowered forced landing of windmill autorotating rotor.The blade A ' and the rotor blade B of the cyclogyro of best mode of operation compare (seeing Fig. 6 and Figure 49), its blade point is near zero angle of attack even be in the negative angle of attack of low-angle, have only the angle of attack of middle front part of blade normal substantially, the mid blade then angle of attack is excessive, the angle of attack of propeller shank is too big even may produce the local air flow separation, the pneumatic efficiency, the descending speed that have reduced the rotor that rotates with autorotation are bigger, easily the occupant are damaged poor safety performance during forced landing.It makes the people be difficult to it is forgotten only with tempting vertical takeoff and landing ability.

The main difference of above-mentioned pure helicopter and conventional cyclogyro is:

1, the rotor difference of lift is provided: the rotor of helicopter belongs to positive pitch, negative twist is changeed.The rotor of cyclogyro belongs to negative pitch, just reverses.

2, type of drive difference: the power of helicopter drives rotor through main reduction gear, needs feathering system cooperating, main reduction gear and feathering system et out of order, and it can only emergency landing; Cyclogyro cruises by the horizontal drive screw propeller, and its rotor is the rotation by the effect of the air-flow in front, and it does not have main reduction gear and feathering system, has also eliminated the fault rate that causes therefrom.

3, the helicopter main shaft is perpendicular to fuselage or turn forward a little.The cyclogyro main shaft then recedes slightly.

4, the empennage of helicopter does not generally have controlled rudder face, and the rudder face of cyclogyro empennage is controlled.

5, run out of steam when forced landing, the rotor blade that helicopter is had to utilize its negative twist to change replaces the work requirements just reversed, and inefficiency, rate of descent are big, poor safety performance.Cyclogyro when forced landing during with normal flight relatively, it is identical to the job requirement of rotor, each position of blade still is in the normal operation angle of attack, high efficiency, the safety performance that force-lands are good.

The present invention's Helicopper, at the problems referred to above, proposed solution, had pure helicopter and conventional cyclogyro advantage concurrently, it be a kind of can vertical takeoff and landing, the oil consumption of cruising is low, noise is little, chase after and fall safety, low, the function admirable " Helicopper " of integrated cost.

Be somebody's turn to do " Helicopper ", the pitched scope of its rotor is big, and its operable nothing is turned round oar, can take into account its different needs at positive pitch and two kinds of mode of operations of negative pitch, has avoided the low excessively pneumatic efficiency of the permanent time rotational of pure helicopter rotor; When it had satisfied vertical takeoff and landing, requiring rotor was positive pitch, required the need of work of rotor for negative pitch when cruising.The present invention can also use " adjusting the twist oar ", should " adjust the twist oar " and can adjust to just reversing of negative pitch by the negative twist commentaries on classics of positive pitch, has further improved pneumatic efficiency.This machine can vertical takeoff and landing when being adjusted to the power rotor state of positive pitch; When it flies before under the promotion of screw propeller, the rotor pitch is adjusted to the autorotating rotor state of negative pitch, can cruises by high efficiency.This machine has used " pitch automatic spacing " system, has guaranteed that its rotor has the reliability close with the rotor of conventional cyclogyro, and its safe reliability can match in excellence or beauty mutually with cyclogyro.For intersecting bispin wing type, its rotor 1 is the last backstroke intersection bispin wing 1, guaranteeing that inboard two rotors of its fuselage have under the situation of identical angle with the routine techniques type, the sagging degree of its outside rotor blade reduces, thus the probability that collide mutually on rotor blade and ground outside having reduced.One group of rotor craft series of design-calculated of the present invention with type formation of different loads ability, its type variation range is wide, and universal component is many, with lower development cost, just can satisfy the various demands of different user, help the segmentation and the exploitation in market, be with a wide range of applications.The present invention is a kind of safety, low noise, efficient, cheap " Helicopper ".The present invention's technology can also partly be applied on other the rotor craft such as helicopter or cyclogyro, is a kind of outstanding Helicopper.

In order to realize the purpose of foregoing invention, Helicopper has adopted following technical scheme:

A kind of Helicopper, by the main shaft 2 of fuselage 5, power system, empennage 4, alighting gear 8, back, the rotor 1 of main shaft 2 upper ends, horizontal drive screw propeller 3 etc. are partly formed; Rotor 1 service adjustment twist oar or nothing are turned round oar; It is adjusted twist oar and is turned round oar 43, become and turn round group, oar axle 26, adjusting lever 27 and form by change; Its main shaft 2 slightly recedes; Steerable rudder face is arranged on the empennage 4; The blade of rotor 1 can be adjusted between positive and negative pitch; Its change is turned round oar 43 and is gone to negative pitch, just adjusts between reversing in positive pitch, negative twist; This machine can utilize the rotor 1 of the positive pitch of power driven and vertical takeoff and landing; Adopt the negative pitch rotor 1 of rotation, cruise or short take-off and landing (STOL) by screw propeller 3 horizontal drive.For the type of setting up the feathering system, its screw propeller 3 also can use the spacing oar, and this oar should link to each other with driving engine 13 by special clutch after the use spacing oar.For always only being provided with apart from the type of control system, its screw propeller 3 also can use the displacement oar.

A kind of Helicopper partly is made up of fuselage 5, power system, rotor 1, pitch automatic spacing system, alighting gear 8 etc.; Pitch automatic spacing system is made up of rotor blade, oar axle 26, pitch drive link 65, limiting stopper 59, locating dowel pin 55, connection controller 56; The centre of lift of its blade is positioned at oar axle 26 position after a while, is provided with pitch limiting stopper 59 near near the rotor blade root, is used for limiting the stroke of minimum pitch; Limiting stopper 59 is limited in minimum pitch the stagger angle position of the negative pitch of the required mode of operation of autorotating rotor; The centre of its pitch drive link 65 by connecting controller 56, is delivered to blade with the pitch control torque; Its locating dowel pin 55 be connected controller 56 and link to each other, locating dowel pin 55 is subjected to the control of chaufeur, locating dowel pin 55 can place the position of locking and the position of release respectively; Locating dowel pin 55 is placed the position of locking, can make to connect controller 56 its pitch control torques of connection; Locating dowel pin 55 is placed the position of release, can make to connect controller 56 its pitch control torques of disconnection.The design of " pitch automatic spacing " system of utilization can be cut off the pitch control torque in long cruising flight process, the aerodynamic force that utilizes blade to be subjected to is kept its needed negative pitch.It continue cruise in can cancel the operating torque of pitch control system, the advantage of bringing thus is: the rolling fatigue that first, has significantly alleviated the pitch Adjustment System; Two, in faults such as pitch Adjustment System generation transmission fractures, and can't transmit operating torque the time, can be by discharging locating dowel pin 55, disconnect the pitch control torque that connects controller 56, utilize the effect of aerodynamic force to blade, make it the automatic steering required negative pitch state that cruises, can not influence its and when cruising flight or forced landing, obtain enough rotor lifts, thereby improve the flight safety of this machine significantly.

A kind of Helicopper partly is made up of fuselage 5, power system, switching coordinated control system, alighting gear 8, rotor 1 etc.; Its switch coordinated control system by pitch joystick 6, handle and spacingly turn round, switching controls 7, driving engine 13, power-transfer clutch 20, main reduction gear 11, main shaft 2, handle interlock and servo-unit I, pitch interlock J, adjusting lever 27 etc. and form; Under the manipulation of pitch joystick 6, switching controls 7 is carried out coordinated control with power break-make and total variation apart from size; In positive pitch interval, switching controls 7 is connected main shaft 2 and power; In negative pitch interval, switching controls 7 disconnects main shaft 2 and power; It is handled spacing turning round and is normally closed switch, it when make position, pitch joystick 6 or be limited in the positive pitch interval that power connects and carry out pitch control or be limited in the open circuited negative pitch of power interval carrying out pitch control; Handle spacing turning round when open position, its pitch joystick 6 can switch between power connection and power disconnection.

A kind of Helicopper, by the main shaft 2 on fuselage 5, power system, empennage 4, alighting gear 8, top, rotor 1 grade of main shaft 2 upper ends is partly formed; Its rotor 1 is that last backstroke is intersected the bispin wing 1, and the stagger angle between the coupled main shaft 2 of every rotor 1 be that (90+A) spends; For the rotor that uses rigidity flapping hinge bearing, angle A is equal to or slightly less than the minimum angle of flap of rotor greater than zero degree; And for the hingeless rotor that uses flexible flapping hinge, angle A is between the minimum angle of flap and maximum angle of flap of rotor.Make it intersect the rotor blade of fuselage outer side of bispin wing type, the sagging degree of blade is less, thereby has reduced the probability that collide mutually on outside rotor blade and ground.

A kind of Helicopper, it is the rotor craft series that is made of one group of type with different loads ability, it is one group of power system, rotor radius that geometric ratio increases progressively by engine power and is one group of rotor that geometric ratio increases progressively and makes up, and forms the series model that load capacity increases progressively; It is one group of power system, rotor radius that geometric ratio increases progressively by engine power and is one group of rotor that geometric ratio increases progressively and makes up, and forms the series model that load capacity increases progressively; One group of above-mentioned rotor of a kind of " low power power system " corresponding use constitutes " several type " that load capacity increases progressively respectively; Another kind of increase progressively the power system of power in turn than above-mentioned " low power power system ", the corresponding one group of above-mentioned rotor that uses of this power system constitutes " several types in addition " that load capacity increases progressively respectively; Should " several types in addition " compare mutually, form the series model that load capacity increases progressively in turn with aforesaid " several type ".

Helicopper has following characteristics than prior art:

Helicopper has been concentrated the advantage of pure helicopter and conventional cyclogyro, and its rotor is under the state of power operated positive pitch, and adjusting the horizontal drive screw propeller is little pitch, and this machine is taken off vertically; For this machine that is equipped with the feathering system, only need adjustment cycle displacement system that it is taken off vertically, and do not need the participation of horizontal drive screw propeller.Treat that it rises in the air, utilize the driving of horizontal drive screw propeller, forward flight; Its slightly sweptback main shaft, can be the rotor rotational plane gives and establishes a positive stagger angle, again the pitch of rotor is adjusted to the negative pitch state of deciding angle of giving, cuts off the power of rotor simultaneously, make rotor under the driving of windstream, produce lift along same direction rotation, utilize controlled empennage 4 to handle its cruising flight.The centre of lift of its rotor blade slightly relies on oar axle rear, limits the stroke of pitch near blade root by limiting stopper, minimum pitch is limited in the position of the stagger angle of required negative pitch when cruising.Equip the High Performance Helicopper of feathering control system, also have the high maneuverability of helicopter horizontal flight.Use aerodynamic arrangements such as the bispin wing (intersect, coaxial, line, the file bispin wing, also can use single rotor to add tail-rotor), under the vertical takeoff and landing mode of operation of power driven rotor, the anti-torsional moment that balance is required.

The rotor of this machine has overcome the deficiency of conventional roll adjustment rotor, and it can use not have and turn round oar, and the autorotating rotor that the power rotor of its positive pitch state carries out vertical takeoff and landing and negative pitch state cruises, and the different demand of reversing of these two kinds of rotor states is taken into account.It can also service adjustment twist oar, and this oar is turned round group by change and adjusted each position compatibility torsion of blade, has enlarged the setting range of pitch, blade can be changeed by the negative twist of positive pitch adjust to just reversing of negative pitch.Cruising with helicopter mode vertical takeoff and landing or the rotation of cyclogyro mode, the demand that it reverses two kinds of differences of rotor is met, and has brought into play operational advantages separately.

For intersecting bispin wing type, its rotor 1 be that last backstroke is intersected the bispin wing 1, and the stagger angle between the coupled main shaft 2 of every rotor 1 is spent greater than 90; Guaranteeing that inboard two rotors of its fuselage have under the situation of identical angle with the routine techniques type, it is little that the sagging degree of its fuselage outer side rotor blade compares the conventional sagging degree of the bispin wing of intersecting, thereby reduced the probability that collide mutually on outside rotor blade and ground, the flight safety of its landing further improves.

This Helicopper, it is the type that has the different loads ability by a group, has constituted rotor craft series, it obtains more type variation with less changing of design, more general-purpose device, thereby has increased its potential user group.This measure has promptly reduced the type variable costs, has increased the Applicable scope of this machine again, has wide development space.

Overall application of the present invention not only can be for Helicopper brings technical marked improvement, even use the present invention's technology on ground, rotor craft top, also can bring improvement on the performance for it.

Below in conjunction with drawings and Examples, the present invention is done one is described in detail:

Fig. 1, Fig. 3, Fig. 4 and Fig. 8, Fig. 9, draw briefly wherein a slice blade and the section-drawing of sectional position, three places, the indication of curved arrow in each figure rotor rotational plane be the direction that rotor rotates.

Fig. 1, Fig. 2 are the rotor and the wake flow scheme drawings thereof of prior art cyclogyro, and cyclogyro flies forward with speed V; Fig. 1 uses, and what be that tractor airscrew, Fig. 2 use is pusher propeller.Its air-flow is to pass the oar dish from front to back, and for oar dish plane, air-flow is from bottom to top to pass the oar dish, so the rotor of cyclogyro is the positive twisting states that is operated in negative pitch;

Fig. 3 signal be air communication air V flow path scheme drawing when crossing the rotor rotational plane of cyclogyro; Air-flow V passes oar dish plane and drives the rotor rotation, and therefore rotor obtains lift F;

Fig. 4 is the scheme drawing of the positive pitch rotor of pure helicopter at the stagger angle at different radii place;

Fig. 5 is that gas washing stream is subjected to the scheme drawing that fuselage hinders under the pure helicopter; Air-flow is to pass the oar dish down by preceding going up to the back;

Fig. 6 is the prior art helicopter, the permanent autorotating rotor A ' of the rotor A of the positive pitch of its power, unpowered negative pitch, and the negative pitch rotor B of they and prior art cyclogyro is scheme drawing relatively.With reference to rotor radius among Figure 49 and stagger angle graph of relation, dotted line wherein is the relation curve of desirable blade radius and stagger angle, and solid line wherein is the relation curve of linear torsion blade radius and stagger angle.A is the positive pitch of the normal dynamically working state of helicopter, the blade that negative twist is changeed among two figure; A ' makes helicopter blade go to the autorotating rotor state of negative pitch for pressing down collective-pitch lever when running out of steam; B is the negative pitch of cyclogyro normal working, just reverses blade; Shown in Figure 49, its stagger angle of rotor A and B is normal substantially, uses rotor A ' to be used for negative pitch state when having to, and this negative pitch state should be the normal operation interval of rotor B.Use rotor A ' to replace rotor B, the real work efficient of its rotor A ' will obviously reduce.

Fig. 7 is in the prior art, a kind of rotor blade scheme drawing that has servo-flaps 16, and helicopters such as intersection bispin wing K-MAX have used servo-flaps on its rotor.

Fig. 8 is to use the intersection bispin wing Helicopper side schematic view of pusher propeller;

Fig. 9 is to use the intersection bispin wing Helicopper side schematic view of tractor airscrew;

Fig. 8, Fig. 9 are two kinds of Helicoppers, and it is made up of steerable rudder face, fuselage 5, alighting gear 8, output shaft 12 etc. on rotor 1, main shaft 2, horizontal drive screw propeller 3, the empennage 4; The two states that blade changed when this figure showed its work: the rotor of the helicopter mode state of flight of the power driven rotor when the positive pitch negative twist of solid line rotor 1 expression among the figure is changeed, the rotor of the cyclogyro mode state of flight of the autorotating rotor when the negative pitch of dotted line rotor 1 expression is just reversing;

Figure 10 is the scheme drawing of pitch manipulation and switching controls, it is switched shift fork 19, power-transfer clutch 20, oar axle 26, adjusting lever 27, is handled and spacingly turn round, handle interlock and servo-unit I, pitch interlock J etc. partly form by rotor 1, main shaft 2, pitch joystick 6, switching controls 7, main reduction gear 11, output shaft 12, driving engine 13, retracing spring 17, elasticity, it is handled spacing turning round and is normally closed switch (this figure will handle spacing turn round omission do not draw): under the manipulation of pitch joystick 6, switching controls 7 changes power break-make and total distance, carries out coordinated control; Handle spacing turning round when being shown in an open position, its pitch joystick 6 can switch between power connection and power disconnection; On draw pitch joystick 6, when its power was connected, rubber-like powershift shift fork 19 at first made umbrella tooth A and umbrella tooth B engagement in the main reduction gear 11, makes power-transfer clutch 20 connection power again; Press down pitch joystick 6, when its power was disconnected, power-transfer clutch 20 at first separated, and then umbrella tooth A, B separate fully.Handle spacing turning round when being in the close position, draw or press down when its pitch joystick 6 is positioned on the positive pitch interval, can be in the interval size that changes pitch of positive pitch, its power still keeps good connection; Draw or press down when its pitch joystick 6 is positioned on the negative pitch interval, can be in the interval size that changes pitch of negative pitch, its power still keeps open circuited state.

Figure 11 (a) is a structural representation of adjusting the twist oar; It is adjusted twist oar and is turned round oar 43, become and turn round group 25, oar axle 26, adjusting lever 27 and form by change;

Figure 11 (b) becomes to turn round oar 43 and become the structural representation of turning round oar for oblique wing flap formula, it by main blade 21, preceding oblique wing flap 22, the wing flap 23 that retreads, blade root 24, become to turn round and organize 25 and form; The section-drawing of the A-A among the figure, B-B, C-C three place's profile positions is seen Figure 19, shown in Figure 20 respectively;

Figure 12 is mounted in the change of blade root in-to-in gear change kink structure and turns round the group scheme drawing; Its gear change is turned round group and is made up of gear E, F, G, H; Its R _E, R _F, R _G, R _EThe radius of representing gear E, F, G, H respectively; Both are coaxial together fixedly connected for its gear F, G, are installed on the fixedly pedestal 33 on the blade root 24 inner rib frameworks; Gear E and gear F engagement, gear H and gear G engagement; Its gear E maintains static; Gear H is captiveed joint with main blade 21 by axle sleeve 30, and main blade 21 rotates with gear H; Its change is turned round than equaling (R _G/ R _B) and (R _E/ R _F) product; Oblique wing flap 22 is connected with blade root 24 by preceding protruding pin 28, back protruding pin 29, forward recess 31, rearward recess 32 respectively with the wing flap 23 that retreads before it.

Figure 13 is the generalized section of forward and backward oblique wing flap linkage structure, and what the figure shows is the generalized section of B-B profile position among Figure 11 (b); The lagging dege of preceding tiltedly wing flap 22 and the front edge of the wing flap 23 that retreads are connected with the lagging dege hinge is corresponding with the front edge hinge of main blade 21 with preceding hinge axis 34, back hinge axis 35 respectively again; Before near the hinge axis 34, back hinge axis 35 go up interlock front axle 36, on link rear axle 37 and interlock front axle 38, the rear axle 39 that links down down, respectively by their last gangbar 45, gangbar 44 is continuous down.

The oblique wing flap formula that Figure 14 is to use the lever change to turn round group becomes turns round oar; Among this figure tiltedly the wing flap formula become the preceding oblique wing flap of turning round oar and be omitted, blade root 24 combines with the wing flap 23 that retreads, and has drawn propeller hub 57 among the figure, but its flapping hinge with lead lag hinge omit and draw.What the right side of figure was illustrated is that group is turned round in the change of exposing outside blade root, its structure installation processing convenience; The change of the left side signal of figure is turned round group and has been inserted within the blade root, and this can reduce aerodynamic drag, and the oar axle mounting frame 64 that the oar axle of this oar passes through links to each other with propeller hub.

Figure 15 is that lever becomes the partial schematic diagram turn round group, and it is that a kind of gear of distortion becomes and turns round group: its fixed conveyor axle 60 to the distance of oar axle 26 axis equals R _E, it plays the effect of gear E; Its main oar transmission shaft 61 to the distance of oar axle 26 axis equals R _H, it plays the effect of gear H; Its blade root transmission shaft 62 is equal to the axle center of gear F, G; Its fixed conveyor axle 60 to the distance of blade root transmission shaft 62 equals R _F, it plays the effect of gear F; Its main oar transmission shaft 61 to the distance of blade root transmission shaft 62 equals R _G, it plays the effect of gear G; The hinged place of interlock 63 is turned round in its fixed conveyor axle 60 and change, and is identical with the engagement of gear E and gear F; The hinged place of interlock 63 is turned round in its main oar transmission shaft 61 and change, and is identical with the engagement of gear H and gear G.This figure turns round group with the change among Figure 14, the scheme drawing that has amplified.

Figure 16 is that a kind of gear becomes the oblique wing flap formula of turning round group and becomes and turn round oar: its change is turned round group and is made up of gear E, gear H, gear F, gear G.One end of its axle sleeve 30 and oar axle mounting frame 64 are fixedly linked, and the other end of axle sleeve 30 and gear E are fixedly linked; One end and the main blade 21 of oar axle 26 are fixedly linked, and after gear H penetrated oar axle 26 and is fixedly linked with it, the other end of oar axle 26 penetrated axle sleeve 30 and is rotatedly connected with oar axle mounting frame 64; This figure is that a kind of tiltedly the blade structural representation of oar is turned round in wing flap and the oblique wing flap formula change that main blade is integrated, blade root and the wing flap that retreads are integrated before it;

Figure 17 is that the oblique wing flap formula that preceding oblique wing flap and main blade are integrated becomes the blade structural representation of turning round oar;

Figure 18 is that a kind of oblique wing flap formula becomes the connecting rod of turning round oar and becomes the scheme drawing of turning round group, and the connecting rod of this figure becomes that to turn round group be that a kind of gear of distortion becomes and turns round group: its main shaft frame 41a maintains static; The bearing fixing of the rotating shaft of drive plate 40 is installed on the rib framework of blade root 24; Main rowlock 41b is fixed on the inner of axle sleeve 30, and axle sleeve 30 outer ends and main blade 21 are fixedly linked; Its main shaft frame 41a is hinged by reel connecting rod 42a and drive plate 40; Drive plate 40 is hinged by main blade connecting rod 42b and main rowlock 41b; Each connecting rod that its change is turned round in the group also can use the interlock rope; For oar was turned round in multistage change, its cascade drive link 46 can be turned round group with forward and backward level change and link together; The point of connection of its drive plate 40 and reel connecting rod 42a equals R to the distance of drive plate rotating shaft _F, it plays the effect of gear F; The point of connection of drive plate 40 and main blade connecting rod 42b equals R to the distance of drive plate rotating shaft _G, it plays the effect of gear G; The point of connection of main shaft frame 41a and reel connecting rod 42a equals R to the distance of the diad of main shaft frame 41a _E, it plays the effect of gear E; The point of connection of connecting rod 42b equals R to the distance of the diad of main rowlock 41b when main rowlock 41b and main oar _H, it plays the effect of gear H; The F-F section is seen Figure 21 among the figure; Its reel connecting rod 42a, it is identical with the engagement of gear E, F; Its main blade connecting rod 42b, it is identical with the engagement of gear H, G.Figure cascade drive link 46 has all been opened a through hole when positions such as the root of the inner that need pass blade root 24 and the wing flap 23 that retreads and relevant rib (not drawing among Figure 18) or last sub level master blade 21 ', be convenient to the transmission work of cascade drive link 46.

Figure 19 is the section-drawing of profile position shown in Figure 11 (b), and graphic is the section-drawing of each section of blade when being in positive pitch, negative twist commentaries on classics;

Figure 20 is the section-drawing of profile position shown in Figure 11 (b), graphic be in negative pitch, the section-drawing of each section of blade when just reversing;

Figure 19, shown in Figure 20, it is the propeller-blade section figure that the oblique wing flap torsional mode of working in negative, positive pitch scope is adjusted the twist oar, it can suitably change the blade twist because of it when adjusting pitch, so be operated in positive pitch or negative pitch when it, all have very high work efficiency.

Figure 21 is the F-F generalized section among Figure 18;

Figure 26 is that oar assembling scheme drawing is turned round in the oblique wing flap formula change of secondary; The parts that each band is cast aside among the figure are parts of the oblique wing flap of last sub level;

Figure 27 is that the paddle structure scheme drawing is turned round in the oblique wing flap formula change of secondary that blade root and forward and backward oblique wing flap are connected as a single entity;

Figure 28 is a blade root and retread that wing flap is connected as a single entity, preceding oblique wing flap is turned round the paddle structure scheme drawing with the oblique wing flap formula change of secondary that main blade 21 is integrated;

Figure 31 is the pusher bispin wing that intersects, the Helicopper schematic side view;

Figure 32 is the pusher bispin wing that intersects, the Helicopper front elevational schematic;

Figure 33 is the pusher bispin wing that intersects, the Helicopper schematic top plan view;

Figure 34 is the pusher coaxial bispin wing, the Helicopper schematic side view;

Figure 35 is the pusher coaxial bispin wing, the Helicopper schematic top plan view;

Figure 36 is that drawing-in type list rotor adds tail-rotor, the Helicopper scheme drawing;

Figure 37 is that pusher single rotor adds tail-rotor, the Helicopper scheme drawing;

Figure 38 is the pusher line bispin wing, the schematic side view of Helicopper;

Figure 39 is the pusher line bispin wing, the schematic top plan view of Helicopper.

Figure 40, Figure 41 are the lateral plan and the front elevations of Helicopper series: one group of rotor that its uses rotor radius to be geometric ratio to increase progressively, be equipped with engine power in it and be one group of power system that geometric ratio increases progressively, fuselage length with the extraordinarily long family machine body structure combination of the Integer n of occupant's distance between seats, make it be combined into the different type of machines of multiple load change, obtain numerous type variations with less changing of design, more universal component, thereby reduced the productive costs of different types of machines significantly.

Figure 41 is a kind of conventional bispin wing that intersects, and the stagger angle between the coupled main shaft 2 of its rotor 1 is for equaling 90 degree or spending less than 90;

Figure 42 is a kind of Helicopper that intersects the bispin wing, and its rotor 1 is that last backstroke is intersected the front elevation of the bispin wing 1.As seen contrast Figure 41 and Figure 42 are guaranteeing that inboard two rotors of its fuselage have under the situation of identical angle with the routine techniques type, and the sagging degree of its outside rotor blade is less, thus the probability that collide mutually on rotor blade and ground outside having reduced.The difference of it and Figure 41 is, the stagger angle between the coupled main shaft 2 of rotor 1 is (90+a) degree, and its angle a is greater than zero degree; For the rotor that uses rigidity flapping hinge bearing, angle a is slightly less than the minimum angle of flap of rotor greater than zero degree; And for the hingeless rotor that uses flexible flapping hinge, angle a is between the minimum angle of flap and maximum angle of flap of rotor.The rotor blade of fuselage outer side, the sagging degree of blade is less, thereby has reduced the probability that collide mutually on outside rotor blade and ground.

Figure 43 is the partial elevational scheme drawing of the last backstroke intersection bispin wing 1 of Helicopper; Stagger angle between the coupled main shaft 2 of rotor 1 is (90+a) degree; Angle b among the figure goes to horizontal, inboard omiting to the blade and the horizontal angle that raise up, and this angle generally should be greater than 8 degree, less than 20 degree; Angle c is the main shaft 2 of rotor and the angle between the vertical line, satisfies between its angle c and angle a and the angle b: c=b-a; Angle d goes to horizontal, a sagging blade and the horizontal angle in the outside, satisfies between its angle d and angle a and the angle b: d=b-2a.

It goes to horizontal inboard rotor blade slightly to facing upward Figure 43, and it and horizontal angle b have reflected the size of blade and adjacent rotor hub spacing indirectly; Its size that goes to horizontal rotor blade angle, outside d can reflect the degree that rotor blade is sagging.Angle b=12 degree in this figure, when angle a=0 spent, angle c and angle d equaled angle b=12 degree respectively; This moment, promptly the technical scheme with shown in Figure 41 was identical.When the angle of Figure 43 b=12 degree, when angle a=4 spends, angle c=8 degree, angle d=4 degree.This shows that when the angle b of Figure 41 scheme and Figure 42 scheme was identical, the probability of collision avoidance was close between two pairs of rotors, but the angle of hanging down under the blade of its outside rotor there is obvious difference.The vertical angle of inboard rotor blade is all under the situation of 12 degree in two figure schemes, the sagging angle of the blade of its outside rotor: its prior art scheme is 12 degree, and the present invention program is 4 degree, and tangible difference is arranged.So the scheme of Figure 42, Figure 43 has remarkable advantages aspect rotor blade contacts to earth outside avoiding downwards.

Figure 44, Figure 49, Figure 50, Figure 51, Figure 53, Figure 60, Figure 63, Figure 67, Figure 68 are the radius of several rotors and the comparison scheme drawing of stagger angle relation curve;

Figure 44 is the desirable blade A of positive pitch, B and the desirable blade state of the negative pitch of the autorotating rotor A ' of cyclogyro, the rotor radius of B ' and the comparison diagram of stagger angle relation that helicopter takes off vertically at power;

Figure 49 is that the linear negative twist of helicopter is changeed the comparison scheme drawing that oar A and A ' and the linearity of cyclogyro are just being reversed oar B.A among the figure is the positive pitch graph of a relation of the linear negative twist switch rotor of helicopter, and A ' is the graph of a relation that this blade of helicopter is depressed into negative pitch among the figure; B then is the negative pitch graph of a relation of the linear positive twist switch rotor of conventional cyclogyro among the figure;

Figure 50 first half is the rotor that works in the positive pitch of power, and it is in the vertical takeoff and landing process, and the linear negative twist commentaries on classics oar A and the nothing of being somebody's turn to do " Helicopper " of its pure helicopter turned round the comparison scheme drawing of oar C.Use not have and turn round oar (the straight line C among the figure), it is amid a sharp increase that the linear negative twist of its stagger angle error ratio is changeed oar (the oblique line A among the figure); The pneumatic efficiency that its nothing is turned round oar changes the efficient of oar under this state than the linear negative twist of 12 degree and has reduced and be about 4%; What D partly represented among the figure is negative stagger angle error, and the expression of D ' part is that angular error just is being installed among the figure.

Figure 50 lower part is the rotor that works in the negative pitch of rotation, and it turns round the comparison scheme drawing that oar C ' and conventional cyclogyro linearity are just being reversed oar B in the nothing of " Helicopper " of cruising condition.Use not have and turn round oar (the straight line C ' among the figure), it is amid a sharp increase that its stagger angle error ratio linearity is just being reversed oar (the oblique line B among the figure); The pneumatic efficiency that its nothing is turned round oar also will reduce by 4% than the linear efficient of just reversing oar of 12 degree; What D partly represented among the figure is negative stagger angle error, and the expression of D ' part is that angular error just is being installed among the figure.

What Figure 51 lower part was represented is the rotor that works in the negative pitch of rotation, the comparison that the linear negative twist commentaries on classics oar A ' of the permanent rotation of pure helicopter and conventional cyclogyro linearity are just being reversed oar B when this pitch state.Use linear negative twist to change oar (the oblique line A ' among the figure), the error that its stagger angle error ratio linearity is just being reversed the stagger angle (the straight line B among the figure) of oar obviously strengthens, and this error is two times of Figure 51 cathetus error that C ' produces.Because the rotor induced drag is non-linear quick growth with the increase of the angle of attack, so changeing the efficient of oar (the oblique line A ' among the figure), the linear negative twist shown in Figure 51 reduces, will be that Figure 50 does not have and turns round oar (figure cathetus C ') and reduced by 4% more than two times.What D partly represented among the figure is negative stagger angle error, and the expression of D ' part is that angular error just is being installed among the figure.

Maximum rotor equivalent 1ift-drag ratio according to pure helicopter is close with maximum permanent rotation 1ift-drag ratio, so both complete machine pneumatic efficiencies are close.And under the positive pitch state of power, nothing is turned round oar C and is decreased than negative twist oar A; Under the negative pitch state of rotation, the nothing of " Helicopper " is turned round oar C ' and is increased than the efficient of the negative twist oar A ' (corresponding its maximum permanent rotation 1ift-drag ratio) of pure helicopter again---and the efficient height when promptly " Helicopper " nothing of cruising is turned round oar and cruised (its maximum equivalent 1ift-drag ratio of correspondence) than pure helicopter (is seen Figure 50, Figure 51; Explanation referring to Figure 73, Figure 74, Figure 75).So when its " Helicopper " used nothing to turn round oar, the efficient of its vertical takeoff and landing can decrease, the efficient when cruising can increase again.Its " Helicopper " with compare mutually with the helicopter of equipower and weight class, decrease load reduced for remedying vertical takeoff and landing efficient, can suitably increase the rotor radius of " Helicopper "; It after suitably increasing the rotor radius, the increasing of induced drag when cruising, higher being compensated of pneumatic efficiency that can be owing to cruising in the cyclogyro mode.So, turn round oar " Helicopper " with the nothing of equipower and weight class and compare mutually with pure helicopter, as long as the rotor radius of suitably extend " Helicopper ", both can have close vertical takeoff and landing load capacity and cruising flight performance.

Figure 52 is that a kind of oblique wing flap becomes and turns round oar, its blade root 24 with retread that two combine into one for wing flap 23, it has the wing flap 23 ' that retreads of a last sub level at blade tip, this wing flap 23 ' that retreads is opposite with the torsional direction of the wing flap 23 that retreads of blade root portion;

Figure 53 is the rotor radius of blade shown in Figure 52 and the relation curve of stagger angle; The section of its different radii position is seen Figure 54, Figure 55;

The top of Figure 54 is expressed as positive pitch stack scheme drawing, and the bottom of figure is expressed as negative pitch stack scheme drawing; Figure 54 intermediate representation be the scheme drawing of zero degree stagger angle;

Figure 55 is each section decomposing schematic representation; The top of figure is the decomposing schematic representation that positive pitch, negative twist are changeed, the decomposing schematic representation of the bottom of figure for bearing pitch, just reversing;

Figure 56 is that oar is turned round in a kind of oblique wing flap formula change, and oblique wing flap and main blade 21 are combined into body before it, and its wing flap 23 that retreads merges into a single whole with blade root, and its gear change is turned round to organize and is placed within the blade root;

Figure 57 is that the structural representation of oar when using the connecting rod change to turn round group turned round in the oblique wing flap change shown in Figure 52; The parts that each band is cast aside among the figure are parts of the oblique wing flap of last sub level;

Figure 58 is the structural representation of a kind of pitch automatic spacing system; Its aerodynamic force acts on the rear of blade spindle, shown in figure arrow vertically upward; Its limiting stopper 59 is made up of moving limiting stopper 59a and quiet limiting stopper 59b; Its quiet limiting stopper 59b is fixed on the oar axle mounting frame 64, and its moving limiting stopper 59a is installed on the blade root 24; When this machine need carry out the vertical takeoff and landing of power rotor, on push away adjusting lever 27, make rotor blade go to positive pitch interval.When it carries out the cruising flight of autorotating rotor,, the rotor pitch is adjusted to negative pitch state except can drop-down adjusting lever 27; Can also cancel the moment of control adjusting lever 27, its blade goes to the required negative pitch position of autorotating rotor automatically under the effect of aerodynamic force, and its moving limiting stopper 59a is stopped by quiet limiting stopper 59b and spacing just.Locating dowel pin 55 among the figure, connection controller 56 can place the position of locking and the position of release respectively with locating dowel pin 55 by chaufeur, are used for controlling the control torque that is switched on or switched off pitch; Pitch joystick 6 is depressed into the minimal negative pitch, inwardly pushes away locating dowel pin 55, then can locking positioning pin 55, make locating dowel pin 55 place the position (Figure 58 A) of locking, connect the pitch control torque; Extract locating dowel pin 55 (Figure 58 B), locating dowel pin 55 is placed the position of release, can make to connect controller 56 its pitch control torques of disconnection.

Figure 59 is that a kind of oblique wing flap that uses the wing flap that retreads at the blade root place becomes and turn round oar, and this oar is simplified to some extent than blade shown in Figure 52; Its blade radius and stagger angle concern figure line shown in Figure 60, and near the oar section of 1.2X to 2.2X, the compensation of the wing flap that retreads is bigger than normal, and makes its foline angle of attack error amid a sharp increase as seen from the figure; Figure 56 is to use gear to become the scheme drawing that oar is turned round in this change of turning round group;

Figure 61 is the improvement to blade shown in Figure 59, it can correct the excessive compensation of the wing flap that retreads, the wing flap that retreads of the linear portion that the trailing edge stage casing compensation of wing flap of here it being retreaded is excessive is cut down, change it into curve, near the torsional error that makes it 1.2X to 2.2X reduces, and its blade radius and stagger angle concern that figure line is shown in Figure 63.Also because, the curve of the trailing edge of the wing flap that retreads at blade root place is little to blade pitch regulating characteristic influence, Figure 62 changes its wing flap that retreads into straight line near the curve of the trailing edge of blade root part, its pitch regulating characteristic is also substantially shown in Figure 63.

Figure 64 is that oar 43 is turned round oar into the aerodynamic force change scheme drawing is turned round in a kind of change.This oar is designed to: blade principal part 43a is for just reversing; The 43b of its blade tip portion is sweepback, and this sweepback is partly changeed for negative twist and do not had and reverse (seeing shown in the A ' of Figure 67 bottom).When rotor was operated in the negative pitch state of the rotation of cruising, its lift was provided by blade principal part 43a; The stagger angle of the 43b of blade tip portion is very little, and its lift also obviously reduces, and aerodynamic moment is not enough to reverse the twisting states when oar 43 maintenance designs are turned round in change so that oar 43 is turned round in change.During the power driven rotor, change is turned round oar 43 and is adjusted to positive pitch, make the 43b of blade tip portion obtain the bigger angle of attack, the 43b of its blade tip portion obtains enough pneumatic negative twist torques thus, this aerodynamic moment mainly acts on the root of blade principal part 43a and the 43b of blade tip portion, and making two parts obtain bigger negative twist changes (seeing shown in the A of Figure 67 top).Its blade satisfied positive pitch, negative twist change and bear pitch, the basic work requirement of two kinds of different conditions just reversing.Figure 67 then is that the described pneumatic change of Figure 64 is turned round oar in negative pitch curve A ' with the characteristic map of positive pitch curve A.

Figure 65 is that oar is turned round in a kind of aerodynamic force change that has blade tip auxiliary flap 16; This oar has been continued to use the basic design shown in Figure 64, but it is improved.It has increased auxiliary flap 16 at the 43b of blade tip portion of its sweepback.Its objective is: 1, when it works in cruising condition, can control the lift of blade tip exactly, the moment of torsion that its lift produces is less than the degree that makes blade twist (see among the A ' of Figure 68 shown in the B ').2, when the power vertical takeoff and landing, the auxiliary flap 16 that utilizes the 43b of blade tip portion to increase again makes blade tip increase lift, obtains enough negative torques, makes blade principal part 43a just reverse (seeing shown in the B among the A of Figure 68).

Figure 66 a kind ofly has the pneumatic change of auxiliary flap 16 to turn round oar, and this oar has increased the wing flap that retreads in blade root district simultaneously.In it, anterior less reversing, be to become by aerodynamic force to turn round oar and finish; What its rear portion was bigger reverses, and then is to be finished by the wing flap that retreads.This oar has further been gathered aerodynamic force and has been become and turn round oar and become the advantage of turning round oar with oblique wing flap, and its aeroperformance better improved.

Figure 67 then is that the curve A of oar at negative pitch state turned round in the pneumatic change shown in Figure 64 ' with the characteristic map of the curve A of positive pitch state.

Figure 68 becomes with the mutually cooresponding a kind of aerodynamic force that has blade tip auxiliary flap 16 of Figure 65 to turn round oar, it be the aerodynamic force that increased auxiliary flap 16 become turn round the curve A of oar at negative pitch state ' with the characteristic map of the curve A of positive pitch state.The lift of this blade tip is easier to control as seen from the figure, makes it obtain weak lift at an easy rate in negative pitch interval; And also be easier to increase at interval its lift of positive pitch, it obtains bigger negative torque, can make its torsional error become littler.The negative twist of its blade tip part is changeed, and why Figure 68 can suitably reduce than the degree shown in Figure 67, has increased the adjustment remaining of the pneumatic stagger angle of blade tip exactly because this oar has used auxiliary flap 16.

In the scheme of Figure 65 and Figure 68: when the negative pitch that cruises,, then can reduce (seeing B ' the section thick dashed line in the negative pitch of Figure 68) by the adjustment of auxiliary flap 16 if the lift of its blade tip is excessive; When the positive pitch of power vertical takeoff and landing, when the lift of its blade tip is not enough, the angle (seeing the B section thick dashed line in the positive pitch of Figure 68) that can also transfer big auxiliary flap 16 to open.

In the scheme shown in Figure 64 and Figure 67, because of it does not have the auxiliary flap that can regulate, the installation of determining when it can only utilize design is reversed, and takes into account the different demands of negative, positive pitch.Though this scheme has some shortcomings, turns round oar compared with nothing, its aeroperformance still has some improvement.

Figure 70, Figure 71, Figure 72 and Figure 66 are several scheme drawings that the blade tip auxiliary flap 16 of different pneumatic structures is housed.

What Figure 73 illustrated is that in order to increase the transition voyage of helicopter, the aircraft that the someone carries out draws the flight test of helicopter.They place autorotation with rotor, draw its flight by fixed wing aircraft then.Test results shows: during fixed wing aircraft traction helicopter flight, navigate by water alone than fixed wing aircraft and to have consumed fuel more, the fuel that has consumed this and the own solo hop of helicopter equally apart from institute's consume fuel quantity identical (referring to 17 pages of " aviation knowledge " 1997 3 phases) more.

State shown in Figure 74, can prove indirectly by the experiment of Figure 73: in the experiment of Figure 73, if the fixed-wing aircraft that the cancellation front is used to draw, to be used for fixing wing aircraft fwd screw propeller, directly be contained in the front of helicopter, and utilize this screw propeller of power driven of helicopter self to carry out " traction ", and the rotor that helicopter oneself is original places autorotation equally, when its during with self cruising flight of screw propeller " traction ", the consumption of fuel when its consumption of fuel will be with the independent cruising flight of former helicopter is basic identical.

The positive pitch state of power rotor when the rotor A of the pure helicopter shown in Figure 75 is the helicopter normal operation, cooresponding 1ift-drag ratio are " rotor equivalent 1ift-drag ratios "; Its rotor A ' is the negative pitch state of helicopter when unpowered autorotative glide, and cooresponding 1ift-drag ratio is " a permanent rotation equivalent 1ift-drag ratio ".The experimental result of Figure 73, with the maximum rotor equivalent 1ift-drag ratio in another helicopter illustration be 6, maximum permanent rotation 1ift-drag ratio is 6.3 description similar (referring to the 267th page of R.W. Pu Laodi work, aircraft industry press " helicopter performance and stability and road-holding property "), thereby further confirmed the experimental result of Figure 73.

Figure 76 is the structural representation that rotor 1 is provided with pitch automatic spacing system; The difference of Figure 76 and Figure 58 is that locating dowel pin 55 is different with the structure that is connected controller 56.Locating dowel pin among Figure 76 (55) can place the position of release and the position of locking respectively, and rotor should upwards be moved the pull bar shown in Figure 76 B and it is fixed at time rotational, discharges locating dowel pin 55, can make to connect controller 56 disconnection pitch control torques; At needs rotor is carried out pitch when handling, remove the pull bar shown in Figure 76 A downwards and it is fixed, then can locking positioning pin 55, make to connect controller 56 and connect the pitch control torques, thereby recover manipulation again pitch.

Should " Helicopper " can adopt the intersection bispin wing, the coaxial bispin wing, the line bispin wing or the file bispin wing, single rotor to add aerodynamic arrangements such as tail-rotor, Fig. 8 be that pusher it " Helicopper " side schematic view of the intersection bispin wing, Fig. 9 are it " Helicopper " side schematic views of the drawing-in type intersection bispin wing.The positive pitch of solid line rotor 1 expression, negative twist are changeed state among Fig. 8, Fig. 9, are used for vertical takeoff and landing; Dotted line rotor 1 its blade of expression is adjusted to negative pitch, positive twisting states, is used for cruising flight.Main shaft 2 is installed in fuselage 5 tops and slightly recedes, and is the positive stagger angle that is provided with for the autorotating rotor oar dish that cruises.The adjustment twist oar that its rotor uses, can broadening pitch setting range efficiently; It changes and bears pitch, works in the scope just reversed in positive pitch, negative twist, and it has obviously expanded high efficiency operation interval at the conventional roll adjustment rotor of this scope internal ratio.

A kind of Helicopper, by the main shaft 2 of fuselage 5, power system, empennage 4, alighting gear 8, back, the rotor 1 of main shaft 2 upper ends, horizontal drive screw propeller 3 etc. are partly formed; Its main shaft 2 slightly recedes; Steerable rudder face (seeing shown in Fig. 8,9) is arranged on the empennage 4; The blade of rotor 1 can be adjusted between positive and negative pitch; Its rotor 1 service adjustment twist oar or nothing are turned round oar; It is adjusted twist oar and is turned round oar 43, become and turn round group, oar axle 26, adjusting lever 27 and form (seeing shown in Figure 11 a) by change; Its change is turned round oar 43 and is gone to negative pitch, just adjusts between reversing in positive pitch, negative twist; The blade of rotor 1 also can be selected for use not have and turn round oar; This machine can utilize the rotor 1 of the positive pitch of power driven and vertical takeoff and landing; Adopt the negative pitch rotor 1 of rotation, cruise or short take-off and landing (STOL) by screw propeller 3 horizontal drive.For always only being provided with apart from the type of Adjustment System, the structure of the pitch Adjustment System of its rotor is simplified, and its horizontal drive screw propeller need use controllable pitch propeller.For the type of setting up the feathering system, not only for it has brought crossrange maneuvering, and vertical on its empennage, horizontal rudder face and feathering system constitute separate, mutually redundant pair maneuvering system, improved the reliability of maneuvering system significantly; At this moment, its screw propeller 3 also can use the spacing oar, and this oar should interconnect by special clutch and driving engine 13 after the use spacing oar.

A kind of Helicopper partly is made up of fuselage 5, power system, rotor 1, pitch automatic spacing system, alighting gear 8 etc.; Pitch automatic spacing system is made up of blade, oar axle 26, pitch drive link 65, limiting stopper 59, locating dowel pin 55, connection controller 56; The centre of lift of its blade is positioned at oar axle 26 position after a while, is provided with pitch limiting stopper 59 near near the rotor blade root, limits the stroke of minimum pitch; Limiting stopper 59 is limited in minimum pitch the stagger angle position of the negative pitch of the required mode of operation of autorotating rotor; The centre of its pitch drive link 65 by connecting controller 56, is delivered to blade with the pitch control torque; Its locating dowel pin 55 be connected controller 56 and link to each other, locating dowel pin 55 is subjected to the control of chaufeur, locating dowel pin 55 can place the position of locking and the position of release respectively; Locating dowel pin 55 is placed the position of locking, can make to connect controller 56 its pitch control torques of connection; Locating dowel pin 55 is placed the position of release, can make to connect controller 56 its pitch control torques of disconnection.

Its rotor is at the time rotational that cruises, it does not keep the control torque of bearing pitch because do not need the pitch Adjustment System to apply, can only utilize the effect of aerodynamic force to blade, can make blade be in the position of the negative pitch stagger angle of required mode of operation this moment, and do not need chaufeur to apply the operating torque of keeping negative pitch by pitch control system, can alleviate the rolling fatigue of pitch control system.For the scheme shown in Figure 58, when needs carry out the pitch manipulation to rotor, pitch joystick 6 is depressed into the minimal negative pitch, insert and locking positioning pin 55, can make to connect controller 56 its pitch control torques of connection; Outwards extract locating dowel pin 55, can make to connect controller 56 its pitch control torques of disconnection.For Figure 76 scheme, at needs rotor is carried out pitch when handling, remove the pull bar shown in Figure 76 A downwards it is fixed, then can locking positioning pin 55, can make to connect controller 56 and connect the pitch control torques, can recover manipulation again to pitch.Rotor should upwards be removed pull bar at time rotational, discharges locating dowel pin 55, can make to connect controller 56 disconnection pitch control torques.

So utilize the design of pitch automatic spacing, eliminated aircraft and in cruising for a long time, kept the negative required control torque of pitch.The advantage of bringing thus is: the rolling fatigue that first, has significantly alleviated the pitch Adjustment System; Two, just in case pitch Adjustment System transmission fault takes place, in the time of can't transmitting operating torque, can utilize and connect the control that controller 56 disconnects its pitch maneuvering system, because of aerodynamic force makes it the cruise negative pitch state of required autorotating rotor of automatic steering to the effect of blade, though at this moment can not arbitrarily change the mode of operation of pitch, but still can obtain the work angle of attack of normal autorotating rotor, can utilizing still normally, the rotor of rotation continues to cruise or force-land.Thereby improved the flight safety of this machine significantly.

A kind of Helicopper of the present invention partly is made up of fuselage 5, power system, switching coordinated control system, alighting gear 8, rotor 1 etc.; Its switch coordinated control system by pitch joystick 6, handle and spacingly turn round, switching controls 7, driving engine 13, power-transfer clutch 20, main reduction gear 11, main shaft 2, handle interlock and servo-unit I, pitch interlock J, adjusting lever 27 etc. and form; Under the manipulation of pitch joystick 6, switching controls 7 is carried out coordinated control with power break-make and total variation apart from size; In positive pitch interval, switching controls 7 is connected main shaft 2 and power; In negative pitch interval, switching controls 7 disconnects main shaft 2 and power; It is handled spacing turning round and is normally closed switch, it when make position, pitch joystick 6 or be limited in positive pitch interval that power connects and carry out pitch and handle or be limited in the open circuited negative pitch of power interval and carry out pitch and handle; Handle spacing turning round when being shown in an open position, its pitch joystick 6 can switch between power connection and power disconnection.Main reduction gear 11 is made up of umbrella tooth A, B and separately rotating shaft, switch back spring 17; Umbrella tooth A and B can mesh or separate; Umbrella tooth A is fixed on the lower end of main shaft 2; Along with rubber-like powershift shift fork 19 sway, umbrella tooth B and A in conjunction with or separate.When power need be connected, on draw pitch joystick 6, switching controls 7 clockwise rotates, powershift shift fork 19 is to moving to left, and at first promotes umbrella tooth B and A engagement, power-transfer clutch 20 closures then.When power disconnects at needs, press down pitch joystick 6, switching controls 7 rotates counterclockwise, and powershift shift fork 19 moves right, and power-transfer clutch 20 at first separates under the effect of switch back spring 17, umbrella tooth B separates (see figure 10) with A then.

A kind of Helicopper, by the main shaft 2 on fuselage 5, power system, empennage 4, alighting gear 8, top, rotor 1 grade of main shaft 2 upper ends is partly formed; Its rotor 1 is the last backstroke intersection bispin wing 1; Stagger angle between the coupled main shaft 2 of every rotor 1 is (90+a) degree; For the rotor that uses rigidity flapping hinge bearing, angle a is equal to or slightly less than the minimum angle of flap of rotor greater than zero degree; And for the hingeless rotor that uses flexible flapping hinge, angle a is between the minimum angle of flap and maximum angle of flap of rotor.The rotor blade of fuselage outer side, the sagging degree of blade is less, thereby has reduced the probability that outside rotor blade and ground collide.As seen from Figure 43, go to horizontal inboard rotor blade slightly to facing upward, it and horizontal angle b have reflected the size of blade and adjacent rotor hub spacing indirectly; It goes to horizontal outside rotor blade, and the size of its angle d can reflect the degree that rotor blade is sagging.Angle b=12 degree in this figure, when angle a=0 spent, angle c and angle d equaled angle b=12 degree respectively; This moment, Figure 43 promptly was converted into technical scheme shown in Figure 41.If when angle b=12 degree, and when establishing angle a=4 and spending, angle c=8 degree then, angle d=4 degree.This shows that when the angle b of Figure 41 scheme and Figure 42 scheme was identical, the probability of collision avoidance was close between two pairs of rotors, but because of its angle a is 4 degree angles, the angle of hanging down under the blade of its outside rotor promptly there is obvious difference in Figure 42 scheme.The vertical angle of inboard rotor blade is all under the situation of 12 degree in two figure schemes, and the sagging angle of the blade of its outside rotor: for the scheme angle d=12 degree of Figure 41, for Figure 42 scheme angle d=4 degree, both have tangible difference.So the scheme of Figure 42 has remarkable advantages aspect rotor blade contacts to earth outside avoiding downwards.

A kind of Helicopper, it is the rotor craft series that is made of one group of type with different loads ability, it is one group of power system, the rotor radius that geometric ratio increases progressively by engine power and is one group of series model that rotor constitutes that geometric ratio increases progressively; It is by engine power, and one group of power system, rotor radius that geometric ratio increases progressively are one group of rotor that geometric ratio increases progressively, one group of airframe structure of the corresponding lengthening of fuselage length makes up, and form the series model that load capacity increases progressively; One group of above-mentioned rotor of a kind of " low power power system " corresponding use constitutes " several type " that load capacity increases progressively respectively; Another kind of increase progressively the power system of power in turn than above-mentioned " low power power system ", the corresponding one group of above-mentioned rotor that uses of this power system constitutes " several types in addition " that load capacity increases progressively respectively; Should " several types in addition " compare mutually, form the series model that load capacity increases progressively in turn with aforesaid " several type ".(seeing Figure 40, Figure 41).

A kind of adjustment twist oar of Helicopper is that aerodynamic force becomes and to turn round oar, and its change is turned round oar 43 and is made up of the 43b of blade tip portion of blade principal part 43a and sweepback; Its blade principal part 43a is for just reversing; The 43b of its blade tip portion is sweepback, and this sweepback is not partly reversed and the negative twist commentaries on classics for having; The 43b of blade tip portion of its sweepback has an auxiliary flap 16; Change is turned round oar 43 and is nonrigid elastomeric material, and elastomeric torsional deformation can take place under the twist moment effect.When 1, rotor was operated in the negative pitch state of the rotation of cruising, its lift was provided by blade principal part 43a, and the adjustment of auxiliary flap 16 can guarantee that the lift of the 43b of blade tip portion is very little; At this moment, the aerodynamic moment of the 43b of blade tip portion is not enough reverses the twisting states when oar 43 maintenance designs are turned round in change so that oar 43 is turned round in change.2, when power driven rotor state, change is turned round oar 43 and is adjusted to positive pitch, the auxiliary flap 16 of the 43b of blade tip portion also synchronously produces certain angle simultaneously downwards, the angle of attack of the 43b of blade tip portion is strengthened, the 43b of its blade tip portion obtains enough pneumatic negative twist torques thus, this aerodynamic moment mainly acts on the root of blade principal part 43a and the 43b of blade tip portion, changes (seeing Figure 68) thereby make two parts obtain enough negative twists.Its aerodynamic force becomes to be turned round oar technology and oblique wing flap and becomes and turn round the oar technology and mutually combine, and makes the performance of blade or structure further be improved (seeing Figure 66).

Figure 64 is that a kind of aerodynamic force of having simplified becomes and turns round oar, and this oar is not installed auxiliary flap, and its structure is comparatively simple: blade principal part 43a is for just reversing; The 43b of its blade tip portion is sweepback, and this sweepback is partly changeed for negative twist and do not had and reverse (seeing shown in the A ' of Figure 67 bottom).When rotor was operated in the negative pitch state of the rotation of cruising, its lift was provided by blade principal part 43a; The stagger angle of the 43b of blade tip portion is very little, and its lift also obviously reduces, and aerodynamic moment is not enough to reverse the twisting states A ' when oar 43 maintenance designs are turned round in change so that oar 43 is turned round in change.During the power driven rotor, change is turned round oar 43 and is adjusted to positive pitch, make the 43b of blade tip portion obtain the bigger angle of attack, the 43b of its blade tip portion obtains enough pneumatic negative twist torques thus, this aerodynamic moment mainly acts on the root of blade principal part 43a and the 43b of blade tip portion, and making two parts obtain bigger negative twist changes (seeing shown in the A of Figure 67 top).Its blade satisfied positive pitch, negative twist change and bear pitch, the basic work requirement of two kinds of different conditions just reversing.Figure 67 then is that the described pneumatic change of Figure 64 is turned round oar in negative pitch curve A ' with the characteristic map of positive pitch curve A.In the scheme shown in Figure 64 and Figure 67, because of it does not have the auxiliary flap that can regulate, the installation of determining when it can only utilize design is reversed, and takes into account the different demands of negative, positive pitch.Though the aeroperformance of this scheme has some shortcomings, its structure simplifies to some extent, turns round oar compared with nothing, and its aeroperformance still has some improvement.

A kind of adjustment twist oar of Helicopper is that oar is turned round in oblique wing flap change, and its change is turned round oar 43 and is made up of main blade 21, oblique wing flap, blade root 24, hinge axis, protruding pin, groove; The width at its oblique wing flap two ends is obviously unequal, and it has two pairs to lay respectively at leading edge one side and trailing edge one side that oar 43 is turned round in change, links to each other the oblique wing flap 22 and the wing flap 23 that retreads before being called respectively with main blade 21 by hinge axis; Blade root 24 and main blade 21 coaxial being installed on the oar axle 26, oar axle 26 passes the blade root 24 that both ends of the surface have through hole, and oar axle 26 inserts main blade 21 and is attached thereto; Have the groove that the protruding pin with blade root 24 inner side ends mates mutually, coincide on oblique wing flap root end face, this protruding pin and groove are used for transmitting the twist moment (seeing Figure 12) of change blade twist.

This oar can be only with the wing flap 23 that retreads, before it tiltedly wing flap 22 be integrated (seeing Figure 14,16,17,28,52,56,57,59,61,62) with main blade 21, this moment blade root 24 also can with the wing flap 23 that retreads be integrated (seeing Figure 14,16,27,28,52,56,57,59,61,62); Blade root 24 also can be respectively and the preceding oblique wing flap 22 and the wing flap 23 that retreads be integrated (seeing Figure 27); When blade root 24 was integrated with the wing flap 23 that retreads, protruding pin between the two and groove are also corresponding to be omitted.The variation of blade tip stagger angle is to become to turn round ratio than the variation of blade root 24 stagger angles, and its value should be less than 1, greater than 1/5; Variation with pitch between the stagger angle of main blade 21 and the oblique stagger angle of wing flap, two stagger angles changes.This oar can be become by some sub levels turn round that oar is formed secondary or oar is turned round in multistage change, and the blade root of prime blade links to each other with the blade tip of back grade blade, and continuing step by step forms.

In order further to improve the aerodynamic performance of rotor, aerodynamic force can be become and turn round oar and oblique wing flap and become and turn round oar and combine (seeing Figure 66), this oar is turned round on the basis of oar in the aerodynamic force change, has increased the wing flap that retreads in blade root district simultaneously.In it, anterior less reversing, be to become by aerodynamic force to turn round oar and finish; What its rear portion was bigger reverses, and then is to be finished by the wing flap that retreads.This oar has further been gathered aerodynamic force and has been become and turn round oar and become the advantage of turning round oar with oblique wing flap, and its aeroperformance better improved.

Group is turned round in a kind of change of this Helicopper, and the gear that adopts gear to become the kink structure becomes turns round group 25, and it is made up of gear E, F, G, H; Its R _E, R _F, R _G, R _HThe radius of representing gear E, F, G, H respectively; Group is turned round in its lever change and group is turned round in the connecting rod change, is that group is turned round in the gear change of two kinds of distortion.Gear becomes turns round group, and both are coaxial together fixedly connected for its gear F, G, are installed on the fixedly pedestal 33 on the blade root 24 inner rib frameworks; Gear E and gear F engagement, gear H and gear G engagement; Its gear E maintains static; Gear H is captiveed joint with main blade 21, and main blade 21 rotates with gear H; Become turn round than be oar the variation of stagger angle is than the variation of blade root stagger angle slightly, its change is turned round than equaling (R _G/ R _H) and (R _E/ R _F) product.Group is turned round in its lever change and group is turned round in the connecting rod change, and there all have corresponding part and gear to become each gear of turning round in the group in them to be corresponding mutually; Its change turn round group in transmission process, promptly do not take place the pine spacious, jam does not appear yet.

The gear that is rotatedly connected for oar axle 26 and main blade 21 becomes to be turned round for the group: axle sleeve 30 1 ends and the axle sleeve hole that main blade 21 is captiveed joint, the other end pierces into blade root 24 its right end face, insert gear H centre hole again, and captive joint with gear H; Oar axle 26 right-hand members insert the oar axis hole, pass gear E centre hole again from blade root 24 left end face, and captive joint with gear E, oar axle 26 right-hand members continue to inject 30 li on the axle sleeve that gear H has been housed, can relatively rotate between oar axle 26 and the axle sleeve 30, can not move axially (seeing Figure 12).

The gear that is fixedly linked for oar axle 26 and main blade 21 becomes to be turned round for the group: axle sleeve 30 1 ends are captiveed joint with oar axle mounting frame 64, and the other end pierces into the axle sleeve hole of blade root 24, insert gear E centre hole again and captive joint with gear E; Oar axle 26 1 ends and oar axle mounting frame 64 are rotationally connected, and the other end passes axle sleeve 30, penetrate gear H centre hole again captives joint with gear H, and oar axle 26 other ends continue to pass blade root 24, inject main blade 21 and captive joint (seeing Figure 16) with it.

A kind of lever of Helicopper becomes turns round group (seeing shown in Figure 15), it by oar axle 26, blade root 24, fixed conveyor axle 60, main oar transmission shaft 61, blade root transmission shaft 62, interlock 63 is turned round in change, oar axle mounting frame 64 is formed; Lever becomes that to turn round group be that a kind of gear of distortion becomes and turns round group, and its fixed conveyor axle 60 is fixedly mounted on the oar axle mounting frame 64; Its main oar transmission shaft 61 is fixed on the oar axle 26 through trace; Its blade root transmission shaft 62 is fixed on the blade root 24; Its fixed conveyor axle 60, main oar transmission shaft 61, blade root transmission shaft 62, three pass driving hole and change, and to turn round interlock 63 hinged and can not separate; Become among three driving holes turning round on the interlock 63, it is circular hole that a hole is arranged: this circular hole and cooresponding transmission shaft are accurate lubricious to coincide; It is bar hole (seeing shown in Figure 15 left side) that two other on the interlock 63 holes are turned round in change, and two driving hole width guarantee with cooresponding transmission shaft accurate lubricious identical.Its fixed conveyor axle 60 to the distance of oar axle 26 axis is equal to R _E, its fixed conveyor axle 60 to the distance of blade root transmission shaft 62 is equal to R _F, its main oar transmission shaft 61 to the distance of blade root transmission shaft 62 is equal to R _G, its main oar transmission shaft 61 to the distance of oar axle 26 axis is equal to R _HIts blade root transmission shaft 62 is equal to the axle center of gear F, G; The hinged place of interlock 63 is turned round in its fixed conveyor axle 60 and change, and is identical with the engagement of gear E and gear F; The hinged place of interlock 63 is turned round in its main oar transmission shaft 61 and change, and is identical with the engagement of gear H and gear G.

A kind of connecting rod of Helicopper becomes turns round group (seeing Figure 18, Figure 57), and it is made up of main shaft frame 41a, main rowlock 41b, reel connecting rod 42a, main blade connecting rod 42b, drive plate 40, the rotating shaft of drive plate 40, cascade drive link 46; Its main shaft frame 41a is fixed on the oar axle 26 and can not rotates; The bearing fixing of the rotating shaft of drive plate 40 is installed on the rib framework of blade root 24; Main rowlock 41b is fixed on the inner of axle sleeve 30, and axle sleeve 30 outer ends and main blade 21 are fixedly linked; Its main shaft frame 41a is hinged by reel connecting rod 42a and drive plate 40; Drive plate 40 is hinged by main blade connecting rod 42b and main rowlock 41b; Each connecting rod that its change is turned round in the group also can use the interlock rope; For oar was turned round in multistage change, its cascade drive link 46 can be turned round group with forward and backward level change and link together.

It is that group is turned round in another kind of gear change of being out of shape that group is turned round in the connecting rod change, and the point of connection of its main shaft frame 41a and reel connecting rod 42a is equal to R to the distance of the diad of main shaft frame 41a _E, drive plate 40 and reel connecting rod 42a point of connection be equal to R to the distance of the rotating shaft of drive plate 40 _F, drive plate 40 and main blade connecting rod 42b point of connection be equal to R to the distance of the rotating shaft of drive plate 40 _G, main rowlock 41b and main blade connecting rod 42b point of connection be equal to R to the distance of the diad of main rowlock 41b _HThe rotating shaft of its drive plate 40 is equal to the rotating shaft of gear F, G; Its main blade connecting rod 42a, it is identical with the engagement of gear E, F; Its main blade connecting rod 42b, it is identical with the engagement of gear H, G;

When adjusting lever 27 changes in positive and negative pitch scope, its change turn round group in transmission process, promptly do not take place the pine spacious, jam does not appear yet.

Become and to turn round oar 43 and can form secondary or oar is turned round in multistage change by some sub level blades, the blade root of last sub level blade links to each other with the back blade tip of a sub level blade, and continuing step by step forms.For multi-rate torsional becomes oar, use cascade drive link 46 that drive plate 40 is linked to each other with prime drive plate 40 '; Each connecting rod that its change is turned round in the group also can use the interlock rope.

The oar of gear turn round to(for) secondary or multistage change becomes turns round group, has the axle sleeve hole that inserts last sub level blade axle sleeve 30 ' on the end face of ground level blade tip; The left end of last sub level blade axle sleeve 30 ' is inserted in the axle sleeve hole 30 of ground level blade, and the gear cluster 25 ' of packing into is fixed on gear H ' left end of axle sleeve 30 '; 26 on oar axle passes main blades 21 at different levels from left end, passes gear E, H and the axle sleeve 30 of main blade 21 inner teeth wheels 25 simultaneously, and gear E at different levels are fixed on the oar axle 26 (see Figure 26).

The rotor of this Helicopper, not only can service adjustment twist oar and nothing turn round oar, it can also directly utilize the negative twist of pure helicopter to change oar.Shown in Figure 73, the flight test of the aircraft traction helicopter that the someone carries out: its rotor is placed autorotation, draw its flight by fixed wing aircraft then.Test results shows: during fixed wing aircraft traction helicopter flight, navigate by water alone than fixed wing aircraft and to have consumed fuel more, the fuel that has consumed this identical apart from institute's consume fuel quantity equally with the own solo hop of helicopter more.This experiment is proof indirectly: in the experiment of Figure 73, if the fixed-wing aircraft that the cancellation front is used to draw, to be used for fixing wing aircraft fwd screw propeller, directly be contained in the front of helicopter, and utilize this screw propeller of power driven of helicopter self to carry out " traction ", and the rotor that helicopter oneself is original places autorotation equally.When its during with self cruising flight of screw propeller " traction " (shown in Figure 74), the consumption of fuel when its consumption of fuel will be with the independent cruising flight of former helicopter is basic identical.This explanation, this Helicopper is when using conventional negative twist to change oar, the vertical takeoff and landing of the consumption of fuel of its vertical takeoff and landing when cruising and pure helicopter and the consumption of fuel that cruises are basic identical, though this moment, its rotation forced landing performance was identical with pure helicopter, and did not possess better odds for effectiveness.But it utilizes the present invention, and its main gearbox and pitch Adjustment System are not all worked when cruising flight, the high reliability of its pitch automatic spacing system is very high, and it is after the negative twist of using pure helicopter is changeed oar, and the safety performance of its complete machine still has tangible raising.

A kind of family machine scheme of this Helicopper:

This machine is by the main shaft 2 on the power system of fuselage 5, fuselage interior and fuel and maneuvering system, top, and the rotor 1 of main shaft 2 upper ends (coaxial, arranged side by side, file and intersect the bispin wing or single rotor add the anti-aerodynamic arrangement such as turn round of tail-rotor isoequilibrium), the screw propeller 3 of horizontal drive, the controlled empennage 4 at rear portion, the alighting gear 8 of bottom etc. are partly formed; Main shaft 2 slightly recedes; Rotor 1 has used takes into account positive and negative " adjusting the twist oar " of reversing; Rotor 1 also can use not have and reverse oar except can using adjustment twist oar of the present invention, even can use the conventional negative twist of little twist to change oar.Its rotor is provided with pitch automatic spacing system.Its high maneuverability type, the feathering system then is set, this feathering system is not only for it has brought crossrange maneuvering, and vertical on its empennage, horizontal rudder face and separate, the mutually redundant pair maneuvering system of feathering system formation, has improved the reliability of maneuvering system effectively; Each type leaves bigger power reserve.For intersecting bispin wing type, its rotor 1 is the last backstroke intersection bispin wing 1.The data of the rotor radius of listing below are the types that is applied to the bispin wing; Add the type of tail-rotor for single rotor, the rotor radius of its 1 type can increase to 5.9 meters by 4.2 meters, and the rotor radius of its 2 type can increase to 7.7 meters by 5.5 meters, and the rotor of its 3 type can increase to 10 meters by 7.1 meters:

Microlight-type, 40 horsepowers: A1: rotor radius R=4.2 meter, take off vertically heavy 340 kilograms.

A2: rotor radius R=5.5 meter, take off vertically heavy 445 kilograms.

A3: rotor radius R=7.1 meter, take off vertically heavy 580 kilograms.

Scaled-down version, 100 horsepowers: B1: rotor radius R=4.2 meter, take off vertically heavy 670 kilograms.

B2: rotor radius R=5.5 meter, take off vertically heavy 790 kilograms.

B3: rotor radius R=7.1 meter, take off vertically heavy 930 kilograms.

Basic type, 250 horsepowers: C1: rotor radius R=4.2 meter, take off vertically heavy 1200 kilograms.

C2: rotor radius R=5.5 meter, take off vertically heavy 1480 kilograms.

C3: rotor radius R=7.1 meter, take off vertically heavy 1780 kilograms.

Standard form, 625 horsepowers: D1: rotor radius R=4.2 meter, take off vertically heavy 2200 kilograms.

D2: rotor radius R=5.5 meter, take off vertically heavy 2660 kilograms.

D3: rotor radius R=7.1 meter, take off vertically heavy 3200 kilograms.

Extended type, 1560 horsepowers: E1, E2, E3

In above example, its power system is that five kinds of power series, rotor are three kinds of rotor radiuses, cooperatively interacts with several airframe structures of fuselage length with the integral multiple of occupant's distance between seats lengthening again, the type that goes out 15 kinds of different loads abilities capable of being combined at least.This type series changes with small construction, brings more type and changes.It has, and universal accessories is many, and the type variation range is wide, and the variation less with component series constitutes various supply capacity, for the type that different user's requests provides diversified economy to be suitable for is selected.The various machine of above family machine because of it has enough power headroom, and makes its airworthiness that cooresponding assurance be arranged, or makes its load capacity also have certain elasticity leeway.

The following describes taking off and the manoeuvre process of " Helicopper ":

The take-off process of Helicopper:

For taking off apart from the Helicopper of displacement system always only is set: drive rotors 1 by driving engine 13 earlier and rotate, upwards draw pitch joystick 6, produce lift for positive pitch to rotor 1, horizontally tracting screw propeller 3 is adjusted to suitable little pitch, make its balance rotor 1 backward component and vertical built on stilts.Strengthen the pitch of screw propeller 3, increasing traction and before fly, when the speed of a ship or plane during, fly state before rotor 1 is transformed into the rotation that windstream drives by power operated state of flight near cruising speed.In this switching process, constant, the stabilization of speed of rotor 1 rotation direction, the conversion operations process is: strengthen the pitch increasing traction of screw propeller 3, press down pitch joystick 6 simultaneously, the negative pitch that rotor is in just reversing; Its bispin wing type cut off automatically rotor 1 power, add the tail-rotor type for single rotor and also the power of tail-rotor will be cut off in the lump.

For the power operated type of height, need the power driven rotor, handle the feathering system and take off vertically; Drive and fly before its screw propeller makes it, during feathering is returned, rotor is depressed into negative pitch, cuts off the power that leads to rotor, is converted to average flight state smoothly.

The manoeuvre of Helicopper:

One, the manoeuvre of power driven rotor state: upwards spur pitch joystick 6, this moment, cyclogyro was in the state of power driven rotor: 1, for intersecting or coaxial bispin wing type, because of its two pairs of rotors are the symmetry counter-rotating, get final product change of direction as long as adjust the pitch difference of two pairs of rotors; Add the type of tail-rotor for single rotor, the pitch that can adjust tail-rotor changes change of direction.2, vertical lift is as long as adjust total distance of rotor.3, on the High Performance type that the feathering control system is housed and line or file bispin wing type,, just can realize crossrange maneuvering by adjustment cycle pitch control bar; Its feathering system is not only for this machine brings good manoevreability, and vertical on its empennage, horizontal rudder face and separate, the mutually redundant pair maneuvering system of feathering system formation, has improved the reliability of maneuvering system significantly.Two, the manoeuvre of autorotating rotor state: it flies in the cyclogyro mode, utilizes the control rudder face of tailplane and vertical tail, handles it and laterally reaches longitudinal maneuver.

In sum, the present invention has the advantage of pure helicopter and conventional gyroplane concurrently, and it is a kind of rising and falling flexibly, can sliding race of level rise and fall, again The energy VTOL; It when cruising decelerator, the pitch Adjustment System is lossless, noise is little, oil consumption economizes, integrated cost is low, the scope of application is wide. It Running out of steam or pitch control when damaging, automatically control the autorotating rotor that blade goes to negative pitch by aerodynamic force, can efficiently rotate, its forced landing Rate of descent is low, has good security performance, is a kind of Helicopper of superior performance.

Claims (10)

1, a kind of Helicopper, by the main shaft (2) of fuselage (5), power system, empennage (4), alighting gear (8), back, parts such as the rotor (1) of main shaft (2) upper end, horizontal drive screw propeller (3) are formed; Its rotor (1) service adjustment twist oar or nothing are turned round oar; It is adjusted twist oar and is turned round oar 43, become and turn round group, oar axle (26), adjusting lever (27) and form by change; Feature is:

Its main shaft (2) slightly recedes; Empennage has steerable rudder face on (4); The blade of rotor (1) can be adjusted between positive and negative pitch; Its rotor (1) service adjustment twist oar or nothing are turned round oar; Its change is turned round oar 43 and can be gone to negative pitch, just adjust between reversing in positive pitch, negative twist; This machine can utilize power system to drive the rotor (1) of positive pitch and vertical takeoff and landing; Adopt the negative pitch rotor (1) of rotation, cruise by screw propeller (3) horizontal drive.

2, a kind of Helicopper is made up of fuselage (5), power system, rotor (1), pitch automatic spacing system, alighting gear parts such as (8); It is characterized in that:

Pitch automatic spacing system is made up of blade, oar axle (26), pitch drive link (65), limiting stopper (59), locating dowel pin (55), connection controller (56); The centre of lift of its blade is positioned at oar axle (26) position after a while, is provided with pitch limiting stopper (59) near near the rotor blade root, is used for limiting the stroke of minimum pitch; Limiting stopper (59) is limited in minimum pitch the stagger angle position of the negative pitch of the required mode of operation of autorotating rotor; The centre of its pitch drive link (65) by connecting controller (56), is delivered to blade with the pitch control torque; Its locating dowel pin (55) be connected controller (56) and link to each other, locating dowel pin (55) can place the position of locking and the position of release respectively; Locating dowel pin (55) is placed the position of locking, can make connection controller (56) connect its pitch control torque; Locating dowel pin (55) is placed the position of release, can make connection controller (56) disconnect its pitch control torque.

3, a kind of Helicopper is made up of fuselage (5), power system, switching coordinated control system, alighting gear (8), rotor parts such as (1); Its switch coordinated control system by pitch joystick (6), handle and spacingly turn round, switching controls (7), driving engine (13), power-transfer clutch (20), main reduction gear (11), main shaft (2), handle interlock and servo-unit (I), pitch interlock (J), adjusting lever (27) etc. and form; It is characterized in that:

Under the manipulation of pitch joystick (6), switching controls (7) is carried out coordinated control with power break-make and total variation apart from size; In positive pitch interval, switching controls (7) is connected main shaft (2) and power; In negative pitch interval, switching controls (7) disconnects main shaft (2) and power; It is handled spacing turning round and is normally closed switch, it when make position, pitch joystick (6) or be limited in the positive pitch interval that power connects and carry out pitch control or be limited in the open circuited negative pitch of power interval carrying out pitch control; Handle spacing turning round when open position, its pitch joystick (6) can switch between power connection and power disconnection.

4, a kind of Helicopper, by the main shaft (2) on fuselage (5), power system, empennage (4), alighting gear (8), top, the parts such as rotor (1) of main shaft (2) upper end are formed; Feature is: its rotor (1) is the last backstroke intersection bispin wing (1):

Stagger angle between the coupled main shaft (2) of every rotor (1) is (90+a) degree; For the rotor that uses rigidity flapping hinge bearing, angle a is equal to or slightly less than the minimum angle of flap of rotor greater than zero degree; And for the hingeless rotor that uses flexible flapping hinge, angle a is between the minimum angle of flap and maximum angle of flap of rotor.

5, a kind of Helicopper, it is the rotor craft series that is made of one group of type with different loads ability, it is one group of power system, the rotor radius that geometric ratio increases progressively by engine power and is one group of series model that rotor constitutes that geometric ratio increases progressively, and it is characterized in that:

It is one group of power system, rotor radius that geometric ratio increases progressively by engine power and is one group of rotor that geometric ratio increases progressively and makes up, and forms the series model that load capacity increases progressively; One group of above-mentioned rotor of a kind of " low power power system " corresponding use constitutes " several type " that load capacity increases progressively respectively; Another kind of increase progressively the power system of power in turn than above-mentioned " low power power system ", the corresponding one group of above-mentioned rotor that uses of this power system constitutes " several types in addition " that load capacity increases progressively respectively; Should " several types in addition " compare mutually, form the series model that load capacity increases progressively in turn with aforesaid " several type ".

6, according to the described Helicopper of claim 1, it adjusts twist oar is that aerodynamic force becomes and turns round oar, and this change is turned round oar (43) and is made up of the blade tip portion (43b) of blade principal part (43a) and sweepback; It is characterized in that:

Its blade principal part (43a) is for just reversing; Its blade tip portion (43b) is sweepback, and this sweepback is not partly reversed and the negative twist commentaries on classics for having; There is an auxiliary flap (16) in the blade tip portion (43b) of its sweepback; Change is turned round oar 43 and is nonrigid elastomeric material, and elastomeric torsional deformation can take place under the twist moment effect;

When the cruising condition of negative pitch, its lift is provided by blade principal part (43a), and auxiliary flap (16) can guarantee that the lift of blade tip portion (43b) is very little, and the aerodynamic moment of its blade tip portion (43b) is not enough to reverse the twisting states when oar 43 maintenance designs are turned round in change so that oar 43 is turned round in change;

When power driven rotor state, change is turned round oar 43 and is adjusted to positive pitch, blade tip portion (43b) synchronously opens auxiliary flap (16) downwards, the angle of attack of blade tip portion (43b) is strengthened, its blade tip portion (43b) obtains enough pneumatic negative twist torques thus, this aerodynamic moment mainly acts on the root of blade principal part (43a) and blade tip portion (43b), and making two parts obtain enough negative twists changes.

7, according to the described Helicopper of claim 1, it adjusts the twist oar is that oar is turned round in oblique wing flap change, and the feature that oar 43 is turned round in its change is: its change is turned round oar 43 and is made up of main blade (21), oblique wing flap, blade root (24), hinge axis, protruding pin, groove; The width at its oblique wing flap two ends is obviously unequal, and it has two pairs to lay respectively at leading edge one side and trailing edge one side that oar 43 is turned round in change, links to each other oblique wing flap (22) and the wing flap that retreads (23) before being called respectively with main blade (21) by hinge axis; Blade root (24) is installed on the oar axle (26) with main blade (21) is coaxial, and oar axle (26) passes the blade root (24) that both ends of the surface have through hole, and oar axle (26) inserts main blade (21) and is attached thereto; On oblique wing flap root end face, have the groove that the protruding pin with blade root (24) inner side end mates mutually, coincide;

This oar can be only with the wing flap that retreads (23), and oblique wing flap (22) is integrated with main blade (21) before it, and blade root this moment (24) also can be integrated with the wing flap that retreads (23); Blade root (24) also can be integrated with preceding oblique wing flap (22) and the wing flap that retreads (23) respectively; This oar can be become by some sub levels turn round that oar is formed secondary or oar is turned round in multistage change, and the blade root of prime blade links to each other with the blade tip of back grade blade, and continuing step by step forms.

8, according to the described Helicopper of claim 1, its change is turned round group and is turned round group (25) into gear becomes, and it is characterized in that:

Gear becomes turns round group by gear (E), (F), (G), (H), and fixedly pedestal (33) is formed; Both are coaxial together fixedly connected for gear (F), (G), are installed on the fixedly pedestal (33) on the inner rib framework of blade root (24); Gear (E) and gear (F) engagement, gear (H) and gear (G) engagement; Its gear (E) maintains static; Gear (H) is captiveed joint with main blade (21), and main blade (21) rotates with gear (H);

Group is turned round in its lever change and group is turned round in the connecting rod change, is that group is turned round in the gear change of two kinds of distortion, and there all have corresponding part and gear to become the function of turning round each gear in the group in them to be corresponding mutually.

9, according to claim 1 or 8 described Helicoppers, its lever becomes the feature of turning round group and is:

Lever become turn round group by oar axle (26), blade root (24), fixed conveyor axle (60), main oar transmission shaft (61), blade root transmission shaft (62), interlock (63) is turned round in change, oar axle mounting frame (64) is formed;

Its fixed conveyor axle (60) is fixedly mounted on the oar axle mounting frame (64); Its main oar transmission shaft (61) is fixed on the oar axle (26) through trace; Its blade root transmission shaft (62) is fixed on blade root (24)) on; Its fixed conveyor axle (60), main oar transmission shaft (61), blade root transmission shaft (62), three pass driving hole and change, and to turn round interlock (63) hinged; Become among three driving holes turning round on the interlock (63), it is circular hole that a hole is arranged: this circular hole and cooresponding transmission shaft are accurate lubricious to coincide; Change is turned round interlock (63) and upward is bar hole in two other holes, and the width of two driving holes guarantees with cooresponding transmission shaft accurate lubricious identical.

10, according to claim 1 or 8 described Helicoppers, its connecting rod becomes the feature of turning round group and is:

It is made up of rotating shaft, the cascade drive link (46) of main shaft frame (41a), main rowlock (41b), reel connecting rod (42a), main blade connecting rod (42b), drive plate (40), drive plate (40);

Its main shaft frame (41a) is fixed on the oar axle (26) and can not rotates; The bearing fixing of the rotating shaft of drive plate (40) is installed on the rib framework of blade root (24); Main rowlock (41b) is fixed on the inner of axle sleeve (30), and axle sleeve (30) outer end and main blade (21) are fixedly linked; Its main shaft frame (41a) is hinged by reel connecting rod (42a) and drive plate (40); Drive plate (40) is hinged by main blade connecting rod (42b) and main rowlock (41b); Each connecting rod that its change is turned round in the group also can use the interlock rope; For oar was turned round in multistage change, its cascade drive link (46) can be turned round group with forward and backward level change and link together.

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