CN1906086A - Aircraft - Google Patents

Abstract

The invention relates to an aircraft comprising a fuselage (1) and a propulsion device (2) that is coupled to the fuselage (1) and that generates a definable lift. Said propulsion device (2) comprises several impeller blades (3) and the latter (3) can be pivoted through a pre-definable blade angle about a pivoting axis (4). The aircraft has been configured and developed in such a way that the impeller blades (3) are mounted to rotate about a rotational axis (5), the blade angle can be modified during the rotation of the impeller blades to generate lift and the respective pivoting axes (4) of the impeller blades (3) run substantially parallel to the rotational axis (5).

Description

Aircraft

Technical field

All embodiment of the present invention relate to an aircraft, it have a fuselage and and with the fuselage coupling so that produce a kind of propelling unit of lift of regulation, propelling unit comprises a plurality of propeller blades, and propeller blade can be around an axis with predetermined blade angle rotation.

Background technology

This class aircraft of prior art has various forms and size.Specifically, autogyro is well-known, wherein, by the axle rotation of one or more rotors around a perpendicular, produces a power (rotor thrust) thus.The normal component of this power provides lift to autogyro.Location by the control propeller blade can draw rotor thrust from vertical axis, it can produce the horizontal component of rotor thrust.This horizontal component of rotor thrust is as a propulsive force, and it also can be used to laterally or mobile backward autogyro.All blades can be around the predetermined angle of a rotational to, to produce a feathering effect.One rotor of going straight up to aircraft is radially arranged with respect to its rotation axis usually.

The aircraft of all prior arts has one or more rotors, respectively has rotor leaf or blade that two or more are radially arranged, and an end of each blade is fixed on a S. A. and/or the rotor head.The blade of rotor turns round on a border circular areas, the normal of border circular areas with along the common vertical axis line parallel of the vertical or horizontal axis of helicopter hull and/or coaxial, or the blade of rotor only turns over the vertical axis several years.This essential structure principle produces the shortcoming of all flight statics and flight dynamics in existing autogyro.

A shortcoming of prior art autogyro is that the fuselage of these autogyros can only forward, backward or laterally be handled, and the luffing of this kind motion and fuselage or rolling coupling.Therefore, when keeping fuselage to be in a vertical orientation (that is, fuselage does not tilt), can not be along all directional control fuselages.

When autogyro is handled, at least two total run-off the straights of position axis of fuselage.Under the contrast, a satellite can be realized such motion manipulation, wherein, and three positions of all of satellite axis keeping parallelism.Autogyro for prior art can not have so " displacement is handled ".

Another shortcoming of prior art autogyro is that they comprise above-mentioned so-called " rotor that carries on the crown ", and wherein, the border circular areas that propeller blade and propeller blade moved through all extends beyond autogyro front and side greatly.Its result, these autogyros must keep enough distances with obstacle, therefore, can not be abutted against mutually with target (for example, with people or cargo loading in autogyro).People or cargo loading can only be carried out below fuselage in autogyro so far.This has limited the ability of autogyro in rescue and rescue work.

Moreover many prior art autogyros only use the rotor of a crown formula.This causes air that the resistance that helicopter blade produced is caused reversal of stress and produces torque.This torque attempts to make autogyro for good and all to rotate around the vertical axis of fuselage.For this reason, use one second rotor (for example a, anti-torque rotor) to compensate this torque usually.This anti-torque rotor is easy to cause trouble, usually is the reason that autogyro crashes and lands and crash.

Also there are problems in the autogyro of prior art, because in flight course, some blade of autogyro is resisted aviation air-flow and moved, and other blades then move with the aviation air-flow, and like this, air just differently passes through each blade of autogyro.Therefore, the variation of air-flow velocity has changed the flight dynamics characteristic of autogyro in directed flight course.Especially when autogyro flew very soon forward, the front edge that the motion of propeller blade opposing aviation air-flow causes air-flow to depart from propeller blade began.The kinematic velocity of propeller blade has become the circular path speed of propeller blade and the combination of aviation air-flow velocity in the air.

This has limited the possibility of autogyro speed and the combination of load-carrying capacity practicality, limited the combination of blade revolution and air-flow velocity practicality, they are limited in such scope, that is, the end of propeller blade does not enter ultrasonic scope yet therefore can not be by the degree that shock wave damaged.

With towards the blade of aviation air motion (from the inside of rotor circle) partly from the lagging dege reverse flow of propeller blade.This is applicable to all parts of following situation propeller blade: promptly, and towards the circular path speed of the propeller blade of aviation air-flow all parts less than the flow velocity of aviation air-flow itself.Along with the increase of air-flow velocity, these blades little by little reduce the contribution to autogyro lift, and cause the rolling movement that depends on air velocity on autogyro flight capsule and/or fuselage, and this must have influence on the characteristic of autogyro.

This problem causes prior art autogyro representative type maximum speed limit at about 400km/h.Along with the increase of autogyro air-flow velocity, it also causes energy consumption to increase, and this air velocity or load-carrying capacity for autogyro is all unfavorable.Therefore, the autogyro of today energy consumption on its flight characteristics is very uneconomical, and thus, its flight range is only in 1000km.

Autogyro is to control by the angle of attack of regulating propeller blade, and some experimental autogyro is controlled autogyro also by the rotor axis (for example, rotation axis) of inclination autogyro.Unfortunately, owing to propeller blade must be regulated periodically and jointly, so, the rotating wobble plate control of a costliness and the rotor head structure of a complexity must be arranged unfriendly.This labyrinth makes the rotor head that provides at present can't surpass 8 blades, and makes the load-carrying capacity of rotor head be no more than 60 tons.

On the representative type autogyro principle is pendulum, and wherein, fuselage is sagging from rotor head, and swings below rotor head.The flight attitude of fuselage depend on dynamic flying condition (for example, look autogyro be engaged in forward, backward, crabbing or orbit).The flight attitude of fuselage can not be independent of dynamic flying condition to be set, and for example, autogyro can not become 90 degree to fling.Yet, the autogyro with tiltable rotor head is tested.Yet these attempt still to cause more perishable and complicated drive configuration.

Brief summary of the invention

The purpose of this invention is to provide an aircraft, wherein, at least one problem is eliminated in the above-mentioned problems, and can be achieved by a simple structure.

According to the present invention, there is this task to be solved to be solved by an aircraft as claimed in claim 1.One aircraft with these features is performed such equipment and formation: propeller blade is positioned to make them to rotate around a S. A..When propeller blade was rotated, also scalable propeller blade angle was to produce lift.Propeller blade pivotal axis separately also is arranged essentially parallel to the S. A. location.

In the present invention, the aircraft that has realized that the above-mentioned type need not be the autogyro that is equipped with crown formula rotor, and wherein, the pivotal axis of propeller blade and propeller blade is radially arranged around the S. A. of autogyro basically.In addition, recognize also that because the location of propeller blade can make them rotate around S. A., thus, the pivotal axis of propeller blade is arranged essentially parallel to the S. A. location, so, can realize the simple especially propelling unit of a structure.In other words, pivotal axis and S. A. are positioned to make propeller blade when rotating substantially parallelly, in a parallel manner around same S. A. motion.When propeller blade rotates around S. A., can change blade angle systems to produce a controlled lift.Power and thrust direction depend on the setting at propeller blade angle.

Aircraft embodiment according to the present invention needn't use the rotor of crown formula, and is far because this kind crown formula rotor extends beyond aircraft fuselage usually, and therefore, inaccessible fuselage also hinders fuselage and for example realizes the possibility of being abutted against mutually near a building.

The pivotal axis of propeller blade can be located basically each other equidistantly.This makes propeller blade to have one uniformly and the motion process of balance around S. A..Moreover along same thinking, the pivotal axis of propeller blade can be positioned to make it to locate equidistantly with respect to S. A. separately basically.

The pivotal axis of propeller blade can be positioned to not only be arranged essentially parallel to S. A., and can be substantially parallel each other.Therefore, can realize the embodiment of propeller blade chip architecture around all even accurate symmetry of S. A..

In order especially simply and safely to demarcate the angle of propeller blade, the pivotal axis of propeller blade can position according to the barycenter of propeller blade.Pivotal axis can extend through the barycenter of the shape of cross section of propeller blade exactly.

The neutral position of propeller blade, in this position, propeller blade is not producing thrust or air transfer in the S. A. rotation process, and this neutral position can produce according to the depression profile of propeller blade with respect to the shape of cross section of S. A..The shape of cross section of blade can be almost entirely located in the imaginary columniform cylindrical wall.The cylindrical of such rotation can not produce thrust and air transfer.

The pivotal axis of each blade can vertically be stretched out from the shape of cross section of propeller blade, therefore, but quasi-parallel or coaxial in the longitudinal axis of propeller blade.

For control and rotatable propeller blade shroud safely around the rotation of pivotal axis, propeller blade comprises an actuating spindle on can be at least at one end.Actuating spindle can be used as the contact point that propeller blade rotates around pivotal axis.Actuating spindle can extend and be positioned at front or back (direction of rotating from propeller blade around rotation axis is watched) of pivotal axis perpendicular to the propeller blade shape of cross section.Blade can connect by actuating spindle, and passes through the angle of attack (or blade angle) of actuating spindle scalable propeller blade.Can adopt the blade angle (with respect to the neutral position of propeller blade) of positive and negative.As mentioned above, the neutral position of propeller blade means when propeller blade rotates around S. A., do not have dacker to shift from propeller blade.But propeller blade can directly pass air.Translation ratio when the distance between actuating spindle and the pivotal axis has stipulated that the propeller blade angle is regulated.

In order to store especially safely and the motion propeller blade, an end of propeller blade is attached on the drive element rotationally, or is installed in rotation in the drive element.Therefore, drive element can rotate in simple mode on the structure around rotation axis, or is rotatably positioned on rotation axis.For this purpose, drive element can comprise a reach or a quill shaft, and it can align with a side that departs from propeller blade.

In a fairly simple embodiment, drive element can be configured to a drive pulley, driving disk or driving ring, and propeller blade is attached on such drive element pivotly.

Pivotal axis or blade can be perpendicular to drive element, drive pulley, driving disk or driving ring location.And propeller blade or pivotal axis can be positioned on the opposite side of reach.In addition, pivotal axis can be arranged to along the edge of drive element, drive pulley, driving disk or driving ring and be arranged in the circle.Pivotal axis can preferably be positioned to them equally spaced from opening.The structure of parallel propeller blade can form a columniform rotor assemblies thus.

In principle, can there be any a plurality of blade to be positioned on the drive element as requested or on the cylindrical rotor assemblies, this decides on the diameter of drive element and the width of propeller blade.Each blade can be positioned to its pivotal axis perpendicular to drive element, like this, it can be pivoted around its pivotal axis.

The reach of drive element or quill shaft can extend from drive element or from the Surface Vertical of drive pulley and/or driving disk ground.Operate safely in order to ensure drive element, drive element can with the gear coupling of odontoid belt, chain or round tooth.For this reason, drive element can comprise that one is adjacent to the circumference or the circular edge of drive element or is positioned at round tooth structure on the girth of reach.Therefore, reach can be configured to the form of an axle drive shaft.

In order safely propeller blade to be coupled on the drive element, drive element can comprise depression or passage, so that store the pivot of propeller blade.Perhaps, drive element can comprise depression or the passage that is used for the propeller blade actuating spindle.The size of actuating spindle can be decided to be depression or the passage that extends through in the drive element.Depression or passage can be configured to otch, hole or groove.Specifically, be used for the depression of propeller blade actuating spindle or passage and can be configured to elongated hole (preferably being arc).

In order to limit the weight of drive element, drive element can comprise groove, depression, passage, otch, hole or slit, so that drive element can have the appearance of a star, circle or spoke shape.

In order to regulate the propeller blade angle safely, drive element can be worked together in conjunction with a control member, to regulate the propeller blade around its pivotal axis.By means of the motion of actuating spindle, control member can cause the attitude at propeller blade angle individually.Thus, control member can break away from from the rotation of propeller blade and/or drive element.In other words, control member does not rotate around the rotation of rotation axis with propeller blade.In a fairly simple embodiment, control member can be installed on the rotation axis.

In order to control pivotal axis safely, control member can comprise a cycloidal gear.In principle, control member can be with respect to S. A. displacement in a guides, so that reach the security settings at propeller blade angle or preset.Control member also can be installed and/or be directed to and can move a certain distance or amplitude along all directions perpendicular to rotation axis.

In a special simple embodiment, for the guiding of this cross table, guides can comprise two linear steering devices that are perpendicular to one another and arrange.Perhaps, in a same simple embodiment, guides can comprise that one is connected to the rotation ways (form that for example, is an extendible pivot rods guides) of a linear steering member.

As another preferred embodiment, control assembly can comprise two rotating control parts, and they are the form of a pair of eccentric disk control member.All elements of above-described control member can be described as control panel.The advantage of eccentric disk member is that it can directly be positioned on the reach or quill shaft of drive element, or is supported by reach or quill shaft.

For the eccentric disk of control or mobile eccentric disk control member independently of one another and safely, each eccentric disk can be connected to an actuator.Specifically, two of the eccentric disk control member eccentric disks respectively are connected on the actuator discriminably.

One eccentric disk control member can comprise two eccentric disks: an interior eccentric disk, it can make its eccentric cam hole by bearing installation on the reach of drive element; And an outer eccentric disk, it can around or be adjacent in the outside of eccentric disk be installed on the bearing.The eccentric cam hole of outer eccentric disk can comprise interior eccentric disk.Control member can be installed on the bearing on (or operating in) outer eccentric disk, and/or can be with respect to heart location in the outer eccentric disk.In a kind of like this structure, two eccentric disks can freely rotate around ground and/or rotate in each other each other.Reversed if eccentric disk becomes, then control member can address this problem.The degree of eccentricity of eccentric disk should be selected like this: for a relative angle attitude of eccentric disk, the fulcrum of outer eccentric disk is corresponding to the fulcrum of the reach of drive element.If when the reach around drive element rotated, the eccentric disk in this relative angle attitude can successfully move each other, then the state of control member remains unchanged, and is in the direction of non-migration.

The eccentric disk control member can be used to produce control action as described below: when control member is thrown off, because the orientation of angle each other of eccentric disk, although not engagement each other, eccentric disk turns to a special angle, and this angle is corresponding to the desired direction of the deflection of rotor assemblies blade.Thereafter, two eccentric disks relative to each other rotate mutually, and wherein, the angle that outer eccentric disk turns over is the twice that interior eccentric disk turns over angle approximately.Therefore, the velocity of rotation of outer eccentric disk is the twice of interior eccentric disk velocity of rotation.Thus, produce a deflection along desired direction, it is proportional to the corner T azimuth of eccentric disk.Therefore the control of this pair eccentric disk be a vector controlled, wherein, at first sets the deflection direction of bend angle, then, sets the size of bend angle.Each control command and/or each predetermined control position (" control stalk position ") can be endowed the angle of a deflection and/or deflection direction.

Now can implement control like this: control is divided into discrete in succession a plurality of control positions.When the bend angle of giving is transferred to the bend angle that the next one gives, and the bend angle size of giving is when being transferred to the bend angle size that the next one gives, have one from a control position continuously to the transformation gradually of next control position.

The discrete division of selecting is accurate more, and the control that then provides is just accurate more and/or synchronous.Eccentric disk can be regulated by two actuators thus, for example, and two stepping motors.An actuator keeps, and eccentric disk in rotating simultaneously, and another actuator keeps, and rotates outer eccentric disk simultaneously.In addition, each eccentric disk can be provided with a rim of gear, wherein, and the engageable miniature gears of actuator.When propeller blade rotated in the control program outside, eccentric disk did not move.

In order to install and/or lead actuating spindle safely, control member can have and comprises that a circular groove or circular trough are so that admit the actuating spindle of propeller blade.When propeller blade rotated around rotation axis, actuating spindle can turn round in circular groove or circular trough.In another simple embodiment, control member can be configured to a control loop or control panel.In this embodiment, a circular groove or a circular trough can be formed in the perimeter of control loop or control panel.

Now when drive element during in rotation, if control member moves along a specific direction by the guiding of control member, then the actuating spindle of propeller blade (it can turn round in a circular groove or circular trough) will be followed this deflection circularly.This has formed an on-cycle blade adjustments.When turning round one time, the actuating spindle of propeller blade was once moving to the maximum forward position from its neutral position, was also once moving to its maximum negative sense position.Between these two extreme deflected position, the actuating spindle of propeller blade passes through its neutral position twice.In two neutral positions (they are intersected with each other on the circular groove path of control member), dacker does not shift from propeller blade.Because the sense of motion of propeller blade is reverse along circular path, dacker shifts along equidirectional two extreme positions the biglyyest.

The extreme position of propeller blade is to be positioned on the mobile axis or along the position of control member sense of motion.Its result, neutral position appear at they be shifted each other 90 the degree positions.If the actuating spindle of propeller blade is positioned at the front (watching from the propeller blade rotation direction) of propeller blade pivotal axis at the propeller blade place, then the moving direction of control member is with identical by the predetermined thrust direction of air transfer.If the actuating spindle of propeller blade is positioned at the back of pivotal axis, then the result is opposite.

In order to increase the efficient of propelling unit, circular groove or control loop can have the structure that departs from a circle.Therefore, do not force its circular groove that must have circular configuration or control loop.For example, other structure can provide the function of an angle of attack, and it depends on angle of rotation, or the angle of attack function of stack.Such technology can be used to change the efficient of propelling unit.In addition, angle of attack function can be proportional to expression formula a-cos (x) w, and wherein, " a " is the number of degrees of the propeller blade angle of attack, and " w " is preferably an integer, and preferably is 11.

In other words, the form of control loop or circular groove can further be optimized, so that improve the efficient that propeller blade rotates around a rotating shaft, or the efficient of a cylindrical rotor assemblies.For this purpose, in another embodiment, it provides angle a-cos (x) w who depends on the angle of attack function of corner.The control loop that this can be used to substitute the circular groove of a circle or substitutes a circle.This only is an example of ability of optimizing the efficient of the propeller blade that rotates around a rotating shaft or cylindrical rotor assemblies.In fact, the form of circular groove is more suitable.They provide the angle of attack function of stack, because the efficient of the efficient of cylindrical rotor assemblies or the propeller blade that rotates around a S. A. is not optimized the cost of maximum cylindricality revolution rotor assemblies or blade.

This circular groove form or control loop form or blade track can be on a circle (basic circle) and the circle two or four periodicity and symmetric " giving prominence to " be overlapping and form.Like this, the curve of the crossover function that basic circle is possible can inscribe, and a square can be circumscribed.Therefore, just have a plurality of curves.In informal being similar to, can conceiving and consider a square around circle.

The simplified example of this crossover curve is as follows: for (projection) ellipse of two projections, and for the epicycloid and the astroid of four projectioies, or have the simple square or the rectangle of fillet.If adopt and circular very different non-circular control loop or circular grooves, then change is should give in the control of propeller blade or cylindrical rotor assemblies.Can adopt two control members, they close to each other or one or adopt identical or multi-form slightly flute profile ring in another front, they can be used for the place, one or both ends of cylindrical rotor assemblies.Blade pivot axis (blade rotation axis) extends in grooved ring, and described grooved ring is adjacent to driving disk and/or positioning disk and fixing with respect to dish.What extend in another grooved ring (control loop) is propeller blade actuating spindle or blade coupling axle.This grooved ring still can be with respect to driving disk or positioning disk rotation and displacement.

If need not be the boring of the usefulness of being located the propeller blade pivot, driving disk and positioning disk can be equipped radial slot or slotted hole separately, and the propeller blade pivot can radially slide in this hole.Thereby driving disk and positioning disk have the feature of driving/attached dish.Comprise among the embodiment of double-type control member and/or grooved ring that at this propeller blade pivot and propeller blade actuating spindle can Be Controlled and radially mobile.Obviously, replace cylindrical rotor assemblies or blade construction, propeller blade can move on a cylindrical rotor assemblies, and this assembly can be ellipsoid, epicycloid and astroid for example, or has the square of fillet or have the cross-sectional plane path of the rectangle of fillet.

In a simple embodiment, heart extended through control member during the reach of drive element or quill shaft preferably can be configured to.But so the control member concentrated area be positioned at the drive element back or below.The reach of drive element (it can be used as axle drive shaft simultaneously) can pass through control member.Therefore drive element and control member can be located in parallel with each other.In as the drive element of driving disk and the embodiment as the control member of control loop, the border circular areas of driving disk can be positioned to and control loop plane parallel of living in or copline.

When driving disk rotates, the end of the actuating spindle of propeller blade can be in the circular groove of control member or circular trough motion and do not have play.In this embodiment, actuating spindle inserts by drive element or driving disk.This zero-lash insertion for example can be arranged on wherein a suitable belt pulley by the end of actuating spindle and support and realize.In simple embodiment, this belt pulley supporting can form by means of the bearing of two friction resistant of radially transmitting easily, and two bearings are arranged on the end of actuating spindle.The bearing of a friction resistant keep-ups pressure with one of them circular groove inwall and contacts, the contact and another anti-friction bearing and relative another circular groove inwall keep-up pressure.

The circulation of propeller blade is regulated can be by means of the known cycloidal gear formation that oar is drawn driving that is used for, and described oar is drawn and driven the Push Technology that originates from boats and ships, and for example, the Schneider-Voith formula drives.Yet these well-known aufbauprinciples are not suitable for the rotor assemblies of twirl, because oar is drawn the quality that control mechanism is controlled high inertia, its on-cycle acceleration/accel causes high reversal of stress and vibration.Yet the present invention guarantees minimum mass acceleration, because propeller blade only quickens circularly around its longitudinal axis, and does not have other control mechanism to quicken circularly.

For stable especially flight characteristic, propeller system can comprise at least two structures around the rotating propeller blade of a S. A..Thus, can avoid N/R to center on the moment of torsion of the vertical axis of aircraft.

In order to produce the lift of a safety, rotation axis can be positioned in the plane of an approximate horizontal.This can realize maximum thrust conversion along a vertical direction.

In one of aircraft narrow especially structure, rotation axis can be parallel to fuselage longitudinal axis location along heading forward.In another embodiment, rotation axis can be located perpendicular to the fuselage longitudinal axis along heading forward.In principle, two of above-mentioned rotation axis kinds of arrangement structures all help the flight stability of aircraft.

In a special simple embodiment, a plurality of propeller blades can form the rotating rotor that centers on a rotation axis respectively, and thus, propeller system can comprise at least two such rotors.

In order to form stable flight attitude, rotor axis direction is along the longitudinal arranged alternately.At least one such rotor can be positioned on each vertical side of fuselage.Yet, also can conceive like this, can there be many rotors to be positioned on each vertical side of fuselage.Have among the embodiment of a plurality of rotors one, can produce the lift of the last one, thus, utilize this aircraft can transport heavier load.

For fear of undesirable moment of torsion, at least two rotors can rotate along relative direction.

In a simple embodiment, at least two rotors are positioned on each vertical side of fuselage, and all rotation axiss can traverse rotor alignment himself.Therefore, last, realize a kind of structure of rotor, its rotation axis is perpendicular to along the fuselage longitudinal axis of heading forward.

For many-sided ground and controlling aircraft individually, each rotor can be controlled individually, simplifies in the situation of control one, and a plurality of rotors can be controlled in an identical manner together.

Because the principle of work of rotor, it is by operating around a rotation axis moving vane, so generation one is along lift and/or propulsive force perpendicular to rotor longitudinal axis and/or rotation axis direction.Therefore rotor (as drive) and/or its rotation axis can be parallel to and/or the axis of pitch location of coaxial aircraft in the fuselage place.Yet,, should adopt at least two rotors in order on static(al), to reach desirable state of flight and to realize a stable especially system.All rotors should arrange promptly have a rotor to be positioned on each side of fuselage alternately along the direction of the longitudinal axis of fuselage.For fear of undesirable moment of torsion, two rotor assemblies can be rotated along relative direction.Be positioned at the barycenter place that two rotors on the longitudinal axis sustained height can be positioned on aircraft.According to rotor assemblies is to rotate along equidirectional or along relative direction, can produce a moment of torsion around the axis of pitch of fuselage or around the vertical axis of fuselage.In such circumstances, necessary flight statical stability will do not provided.

When considering the possibility that the forfeiture rotor assemblies is used, of the present invention one ultra-safe embodiment comprises four rotor assemblies of use.Per two rotor assemblies can be arranged on the both sides of fuselage, and traverse each other, and/or can form the longitudinal axis and/or the rotation axis of a public rotor assemblies.A pair of like this rotor assemblies can be imagined and is used for forebody and rear portion.

By using two and/or four rotor assemblies along fuselage longitudinal axis direction, aircraft can be carried out forward and manipulation backward and do not have luffing.For this reason, preceding and back rotor or rotor must be controlled equably to the thrust that is produced.On the other hand, the manipulation before or after can be achieved by the variation thrust from front or rear driving.Then, this causes a moment of torsion around the fuselage axis of pitch once more, therefore, causes well-known luffing, by the parallelogram of force decomposition analysis of thrust vectoring, can produce the edge component of direction forward or backward.

Above-mentioned being used for forward and the same manipulation of manipulation backward applicable to side direction of the present invention.The manipulation of side direction can be achieved by the thrust that changes a left side or dextrorotation airfoil assembly and/or a left side or right actuator.Therefore, cause a moment of torsion around the fuselage longitudinal axis, then, can produce the thrust vectoring of side direction from consequential rolling movement.

In another embodiment, can produce a sideway movement of aircraft, and not have a rolling movement.For this reason, propeller blade is installed in away from the end of drive element by means of an axle drive shaft following current with handing over distance and locates, and is positioned at guide piece place or guide piece.Such guide piece can absorb the bending force distance of the moving vane that produces from the on-cycle air transfer, and can absorb the centnifugal force of rotation.The structure of propeller blade or cylindrical rotor assemblies can be with the quite high revolution of guide piece rotation.Guide piece also can absorb more thrust reversal of stress and/or produce more forward thrust and lift thrust.

Guide piece can be similar to the mode of (preferably disk-shaped) drive element basically and construct.At this moment, guide piece can be the form of a positioning disk.

Guide piece can be by the supporting of a central support shaft or a quill shaft, and hollow support shaft is between drive element and guide piece and be coupled on the drive element.Therefore, guide piece can be configured to rotate with drive element.Guide piece and drive element can be by means of one or S. A. realization couplings.The longitudinal axis of bolster, quill shaft, axis or rotation axis can extend by the center of drive element and guide piece, and thus, the longitudinal axis of bolster or quill shaft is consistent with the longitudinal axis of rotor assemblies and/or rotation axis.

The bolster of guide piece or positioning disk is corresponding to the reach of drive element or driving disk.Bolster can be seen as the portion that extends laterally of guide piece of the reach of drive element.Because bolster or quill shaft carrying and/or propelling guide piece, it also can play the axle drive shaft of guide piece.

Do not cause rolling movement in order to make aircraft produce simple especially sideway movement, guide piece can be provided with a guiding rotor that comprises rotor blade.This rotor blade can structure on simple mode be connected to guide piece.Rotor blade can radially be positioned between the edge of the hub of guide piece and guide piece.For this reason, guide piece can comprise suitable passage and/or load bearing seat.Such guiding rotor can be corresponding to the anti-torque rotor of conventional helicopter and structurally principle is identical.

The guiding rotor can advance around an attaching parts that extends through rotation axis.Such attaching parts can comprise a pipe link, and the reach of its support shaft and drive element leads.The guiding rotor can be undertaken attached by pipe link and crank.The guiding rotor of rotor assemblies can make aircraft do sideway movement and not cause rolling movement.In addition, all guiding rotors can carry out identical control with respect to its thrust.

The rotation that aircraft is done around the vertical axis of fuselage is handled, and both can also can realize by the guiding rotor by the inhomogeneous thrust of rotor assemblies.In addition, thrust only needs from two rotor assemblies or guiding rotor, and they are positioned on the opposite side, and do not belong to a pair of rotor assemblies.

For aircraft being risen or descending the rising thrust that drives before and after controlling equably.The increase of the thrust of climbing can be by increasing the propeller blade angle and/or realizing by the revolution that increases rotor assemblies.Here it is makes difference between the present invention and the conventional helicopter tangible place that becomes.Conventional helicopter is to produce its thrust of climbing on the revolution that jointly increases propeller blade angle and/or increase rotor.Yet according to the present invention, the thrust of climbing is controlled by means of the on-cycle blade and is reached.

In order to control fuselage flight attitude and/or trim, thrust front or rear and/or that side direction drives can differently be controlled.No matter the space vehicle dynamic state of flight how, the present invention can keep different flight attitudes by the trim ability.

One embodiment of the present of invention can reach the identical flight dynamic condition of conventional helicopter, and need not utilize the blade control of associating.Therefore, aircraft of the present invention has much simple significantly a structure.In addition, this embodiment of the present invention can realize that the mode of separating idol motion and/or pure flat shifting movement fully realizes handling, or the manipulation of realization and pitching and/or the irrelevant displacement of rolling.Such manipulation or motion are impossible for conventional helicopter.In addition, the flight attitude of fuselage can trim.Autogyro can stably be in all positions in the complete 360 ° of total sizes of fuselage axis of pitch.Because aircraft can have two or four rotor assemblies according to an embodiment of the invention, and the propeller blade that can have any amount basically for each rotor assemblies, so can reach higher lift thrust, therefore, compare with traditional autogyro, can transport higher effective load.

In one embodiment, wherein, the longitudinal axis of rotor assemblies and/or rotating shaft parallel and/or coaxial with the fuselage axis of pitch, but still a distinct disadvantage arranged, be that air-flow is advertised on propeller blade, the contrary aviation air-flow of all blades moves, and they are not really effectively to move towards the aviation air-flow with the mode that changes, and this decides on revolution and air velocity.In addition, also have the other shortcoming that has for this kind structure, air velocity is added on the path velocity of propeller blade, and like this, maximum air velocity is still very limited.These shortcomings can be solved among the embodiment below the present invention.For this reason, the longitudinal axis of rotor assemblies and/or rotation axis are located no longer abreast and with the fuselage axis of pitch coaxially.But they can be parallel to and/or locate coaxially with the fuselage axis of pitch.Such propelling unit can be used at least two rotor assemblies, and they are arranged and share a rotor assemblies longitudinal axis and/or a rotation axis in front and back each other, to produce necessary manipulation moment of torsion.When only using two rotor assemblies, two rotors are located on ground, front and back each other, and are positioned on the top of fuselage.When only using four rotor assemblies, four rotors also can laterally be arranged, two rotors are arranged on fuselage one side to front and back each other.Each can be adjacent one another are and/or intersected with each other to the rotor assemblies of location before and after each other, can rotate to avoid undesirable moment of torsion along relative direction then.

In of the present invention one special actv. embodiment, blade or rotor adjacent one another are or location, ground, front and back can be located in the mode of accurate minute surface symmetric arrangement.Here, we can say that also " each other " that rotor assemblies is a bonded assembly and reflection arrange.For this embodiment, two rotor assemblies only need a director element.And, because rotor assemblies can coupling on a public direction device, and/or the coupling each other securely of reversible supporting axis, so it is just enough only to drive a drive element.Yet, have among the embodiment of a driving at this, have only by the on-cycle blade adjustments and no longer control revolution, just can realize the moment of torsion handled to two rotors.In addition, no longer rotate by the moment of torsion that causes facing to the air resistance of rotor blade and compensate by the relative propelling of the separation of rotor assemblies.

Can realize the bigger simplification of aircraft according to one embodiment of the invention, operate because each control member at place, propeller blade two ends can be independent of each other control member respectively.For example, can only use a rotor assemblies, but this assembly comprises two control members or control loop certainly.Then, its each end of blade is attachable on a drive element, or is attached on the control setup, and its each end that has in control member or lead in the circular groove.In this uses, perpendicular to the manipulation moment of torsion of rotor assemblies longitudinal axis and/or rotation axis, can reverse by the circulation of propeller blade and realize, can twist by two control members or a control loop relative displacement relative to each other.Therefore, the thrust of the selection of propeller blade angle and propeller blade will change consistently from the end to end of propeller blade.In the foregoing description of aircraft, be to handle one of moment of torsion by the different total thrust vector generation of indivedual rotor assemblies to have the rotor assemblies work that the rotor assemblies of reversing control can be similar to two independent controls.

The thrust relevant with flight control produces with the longitudinal axis of the rotor assemblies of parallel and/or coaxial longitudinal axis in fuselage or revolves aliging and changing of axis.Lateral displacement is handled or is handled no longer around the rotation of fuselage vertical axis and realizes by means of the guiding rotor, and they now can be only realized by means of the Thrust Control of rotor assemblies.Yet displacement is forward handled no longer by means of rotor assemblies, and they now can only be carried out by the guiding rotor.Can avoid reaching the common way of aircraft thrust by the luffing of coupling.On the contrary, in the method for the Energy Efficient more that obtains aircraft thrust, more weak relatively guiding rotor (in the situation of true motion of translation) can be replaced by strong change pitch propelling unit.

In this embodiment of the present invention, comprise that a transmission system of drive element can comprise: the propelling unit of a variable pitching; One has the shaft drying turbo-machine attached with fuselage, control member or preceding control loop before the turbo-shaft one that moves back and forth; The actuator or the driving disk of preceding rotor assemblies, preceding parallel blade, one has the guide piece or the positioning disk of two-way bolster; Back parallel blade; One drive element or the driving disk of back rotor assemblies; One back control member or back control loop; And the back carrying that has the fuselage attachment of admitting the actuator driving disk of back rotor assemblies is coupling and receives part, thus, but the propelling unit of change pitch is positioned at the front on the turbo-shaft, and the reach of first drive element or first driving disk also is coupled on the turbo-shaft of running of turbine back.Turbine on the drive-system has replaced being used for before driving parts or the necessary reach female part that has the fuselage attachment of forerunner's Moving plate.

Perhaps, drive turbine and can be positioned in the fuselage or on the fuselage, and advance drive-system by a transmission device.In this embodiment, one drives turbine can advance two side direction drive-systems, and perhaps, when using two driving turbines, they can be simply and a driving device coupling, so that prevent to drive losing of turbine.

In one embodiment of this invention, at least one driving turbine can be positioned in the fuselage of aircraft.This can guarantee that driving turbine is protected.

The driving turbine is arranged in has further advantage in the fuselage, that is, turbine exhaust can laterally directly be directed to rotor or rotor top from fuselage.Above rotor and from wherein obtaining balance partly by the introducing of turbine exhaust thus from the negative pressure that produces.The necessary driving power that produces certainly can reduce the consumption of driving power slightly.The turbine exhaust of heat can prevent possible the freezing of rotor assemblies, and simultaneously, the turbine exhaust of heat can form vortex and shunting downwards, so that they can not arrive any other turbine inlet of other turbine, and causes the out of service of other turbine.

The propelling unit of variable pitching must be arranged like this: two forward and thrust backward can regulate and obtain by means of its propeller blade.In order further to reduce the consumption of power, the propelling unit of a variable pitching or a propelling unit can be positioned on the front of rotor assemblies and the back of this rotor assemblies.Forward propeller can arrange to become the propelling unit of a pulling, and after propeller can arrange to become a pressure propelling unit.Between variable pitching propelling unit or propelling unit, for example, between pulling propelling unit and pressure propelling unit, two or more rotor assemblies are location, ground, front and back each other.

In the orbit of aircraft, can operate above-mentioned two propelling units, so that they are pushed against each other.Two propelling units can be regulated orbit, so that their propelling effect compensates mutually, but have applied the added air mass of rotor assemblies or rotor assemblies separately.

Propelling unit also can be used to partly compensation torque.It compensates a remaining moment of torsion basically.Surplus torque comes from the rotation of rotor and/or the resistance of reaction air.Basically the moment of torsion that does not give compensation is (the seeing as mentioned above) that produces when the rotor assemblies of only using a control to reverse.In addition, propelling unit rotates and can set the relative direction rotation of rotating along rotor assemblies for by means of a counter gear mechanism.For a less aircraft that one embodiment of the invention of individual drive-system are arranged only, the mediation of this moment of torsion is significant especially.

In another embodiment of the present invention, can comprise at least one wing or auxiliary wing at the fuselage place, rotor assemblies is attached on the described wing, or rotor assemblies can be suspended from described wing.

Come from the moment of torsion that air resistance causes or do not give compensation, on according to the aircraft of the embodiment of the invention, do not have having a strong impact on as on conventional helicopter.In a traditional autogyro, this moment of torsion must be compensated utterly, uses one second rotor usually, for example is an anti-torque rotor, so that prevent that fuselage from centering on its vertical axis and rotating continuously.In an embodiment of the present invention, the such moment of torsion around vertical axis can not take place.Cooresponding moment of torsion only takes place around the longitudinal axis of fuselage, and all at the most torques cause the side on oscillation skew of fuselage entirely.One is much more stable than conventional helicopter on flight statics according to the aircraft of one embodiment of the invention.

Because the longitudinal axis of rotor assemblies or rotation axis are parallel and/or coaxial orientation with respect to the longitudinal axis of fuselage, so autogyro is in the process of travelling forward, the speed component of the actuating speed of autogyro is cancelled together with the rotor path velocity.This is because two speed components are the causes that are perpendicular to one another.

Therefore, aircraft can obtain significantly high maximum air velocity than traditional autogyro according to an embodiment of the invention.In principle, the maximum air velocity of turbo-propeller aircraft also is possible for aircraft according to an embodiment of the invention.And according to the aircraft of the embodiment of the invention also be expected than the turbo-propeller aircraft with identical driving power fly in addition faster, because the aircraft according to the embodiment of the invention does not comprise the tail units of aircraft or the wing of aircraft, the latter can produce additional air resistance, and not like this according to the aircraft of the embodiment of the invention.Have the flight dynamic characteristics of conventional helicopter and conventional airplane according to the aircraft of the embodiment of the invention, therefore, can go straight up to fly an aircraft or the aircraft (from the angle of flight dynamic characteristics) as one.The flight operation of aircraft is more energy-conservation basically than conventional helicopter according to an embodiment of the invention, because along with the increase of air velocity, can not cause the increase of rolling moment.Therefore, all well-known shortcomings of described conventional helicopter in preface part have been avoided according to the aircraft of the embodiment of the invention.In addition, can be parallel to and/or coaxial ability of arranging rotor assemblies in fuselage longitudinal axis ground because have, so, two or more rotor assemblies can be each other before and after the ground lateral register, and laterally adjoin mutually each other and be adjacent to fuselage.Therefore, can form big fuselage and have about 200 tons load-carrying capacity, perhaps, carry the above ability of 200 passengers.

The difficulty of manipulation of being abutted against mutually and transportation, rescue and relief is handled, and all can realize according to the aircraft of the embodiment of the invention, because have above-mentioned advantage also because of the rotor of not uphanging, carry on the crown.Handle for the transportation of difficulty, rescue and relief, fuselage can be equipped an assembly that joins, and it can be used to loading or unloading institute's handling load and/or permission personnel and takes advantage of and be loaded in the aircraft or from aircraft.In the relatively simple embodiments of the invention of a structure, this is abutted against assembly mutually can comprise a tunnel, a crane span structure or a basket.In order to allow cockpit can observe the assembly that is abutted against mutually easily, the assembly that is abutted against mutually can be positioned on the front end of fuselage.

Can be equipped with a pipe for escaping or a receiving pit at the first place of its nose according to aircraft of the present invention, they can be used to allow escape personnel, animal or goods to enter into aircraft.It can also be after being abutted against mutually, be convenient to auxiliary or rescue strength and or goods get off the plane.This is a very big advantage, because for example in multi-story structure, for reasons of safety, auxiliary and rescue strength can not used elevator, if necessary, can only be forced to use stair transportation device between many floors.

Consider that aircraft security ground is abutted against mutually with a building, an assembly that is abutted against mutually can preferably comprise the guiding device of a tunnel shape.The guiding device of the type is attachable on the building, and is configured to be coupled on the aircraft, to be used as the inlet that enters aircraft.This can be convenient to being abutted against mutually effectively of aircraft.

Consider that aircraft can especially stably be coupled to a building or inlet, this assembly that is abutted against can comprise a lockout mechanism.This lockout mechanism can comprise the blocking device member that for example is positioned at the sun that is abutted against mutually on the assembly and be positioned at the blocking device member of the moon on the inlet.

In other words, an aircraft can comprise that one is abutted against assembly mutually, and it is fitted in the guide piece or in the inlet or be used in the blocking device of this purpose exactly.These guide piecees, inlet, or blocking device can for example be arranged on escape window, Emergency door, escape entrance, or be positioned at the Emergency Exit of any other form of high building outside.Aircraft can be abutted against self mutually and be anchored at these positions, opens appropriate emergency or escape outlet, and unloading personnel, animal, or goods are evacuated discharged personnel, animal then, or car and boat on the goods.

This is abutted against assembly mutually can comprise a tunnel shape guide piece, and it is suitable for admitting fully one by nose head.In the time of in being abutted against the guide piece of tunnel shape that nose head slips into the locking component that has sun, can be imported into the cloudy locking component that is positioned at place, shape guide piece end, tunnel to being abutted against nose head.For example, this moon locking component can be three dot structures or 4 dot structures of a symmetry, and they are arranged around the periphery that enters opening at place, shape guide piece end, tunnel.The locking of lockout mechanism and/or unblank and can operate dynamo-electricly by aircraft of the present invention, or mechanically operate by connecting rod.For example, blocking device can be blocking device, flute profile lock, a bolt-lock of hook-type lock, an expansion, or a horizontal lever lock, and for example, they are the form of a roller, pin or fork lock.

The inlet of tunnel shape guide piece can be closed by a hatch cover, one or wind glass, and they can be opened from the outside.Guide piece can be transferred in the building, and like this, it outside the building locks onto to the face connection front of building, does not therefore hinder vision.In towering building, such guide piece can be installed on all sides of building, and can be installed on the floor of predetermined quantity.Similarly, guide piece can be installed on the arm fixing or that rotate.Such structure more seems favourable in drilling platform, mine platform, originating firm or the marine large ship of offshore.For normal transport personnel or goods, these guide piecees can similarly can be used in high building or the high tower such as the terminal on airport.According to the above-mentioned technological merit of aircraft of the present invention, the civil and military flight operation for traditional can bring economically, in the logistics and strategic advantage.

Because the cargo weight that aircraft according to the present invention is can transportation on principle identical with intermediate range or long-range vehicle or the passenger of equal number, and also manifest high relatively air speed and voyage, aircraft according to the present invention should play a cooresponding competitor effect in the flight field of intermediate range and long-range vehicle, simultaneously, provide on the cooresponding ecology, economically with logistics on plurality of advantages.Aircraft according to the present invention can drop on the runway from cooresponding height by vertical descending flight, and can also take off with the same manner.This has been avoided the well-known noise pollution that dwelling district produced of conventional airplane around contiguous runway.

Do not need the surface structures of both expensive according to aircraft of the present invention, for example, have the airport installation of roomy airstrip.Therefore, can reduce and the relevant traffic cost of aircraft according to the present invention, can fly city that any hope arrives and directly arrive the down town of aircraft is not even the city has the airport can achieve the goal yet.The network of air route can form with minimum surface structures.This is for the economic development advantageous particularly that does not have condition to develop to comprise the country on traditional airport.

Long-distance flight (for example, trans-oceanic) in service, different with conventional airplane, can land on the aviation lash ship in the ocean according to aircraft of the present invention, so that safeguard, refuel or do forced landing.Aircraft of the present invention can be implemented in waterborne or land forced landing by low speed, thus, avoided damaging based on the relevant aircraft of forced landing waterborne, and the recurrent aircraft relevant on the ground with forcing landing damages.Aircraft of the present invention is safer than traditional intermediate range and long-range aircraft, long-haul aircraft.

Because aircraft of the present invention has advantages of high bearing capacity, high road-holding property and being abutted against property, it can finish relief and rescue operation, and this is impossible for conventional helicopter.Utilize the present invention, the person of being hurt during the New York World Trade Center attacks then can rescue in the maccessiable thenceforth floor.Compare to the transportation means that can supply at present, utilize the present invention, can better and more finish supply or evacuation with accelerating critical or devastated.

In Military Application, that aircraft of the present invention makes is new, more efficient operation and strategy become possibility basically.For example, according to aircraft of the present invention, a large amount of goods and materials or army move through and transport directly to the military target area and can realize quickly basically, and this has only the haulway that makes up by slowly in present technology, for example, use ship and/or large aircraft and/or terrain transportation just may realize.And can have the importance of huge military strategy by directly being transported to saving that military target area reaches time and money quickly by aircraft of the present invention.For example, in operational framework, no longer need to occupy and safeguard the airport.Anywhere on high sea can be supplied large-scale navigation naval vessels, need not wait for the supply ship, perhaps enables the supply ship and transports.

Description of drawings

Exist all possibilities of using in an advantageous manner and expanding the technology of the present invention.For this purpose, on the one hand, appended claims can be consulted, on the other hand, the explanation of being done of following preferred embodiment according to an aircraft of the present invention can be consulted with reference to the accompanying drawings.In conjunction with explanation, the general preferred embodiment of the present invention and other aspects are described with reference to the accompanying drawings to the preferred embodiment of aircraft of the present invention.In following accompanying drawing:

Fig. 1 illustrates schematic front elevation, back view, birds-eye view and the lateral plan according to first example embodiment of an aircraft of the present invention,

Fig. 2 illustrates schematic front elevation, back view, birds-eye view and the lateral plan according to second example embodiment of an aircraft of the present invention,

Fig. 3 illustrates schematic front elevation, birds-eye view and the lateral plan of the aircraft of Fig. 2, and among the figure, aircraft has an assembly that is abutted against that is arranged on forebody,

Fig. 4 is the schematic section drawing of the propeller blade of propeller system,

Fig. 5 is the planar view that is used for the driving disk of propeller blade,

Fig. 6 one has the planar view of the control loop of an annular groove and an eccentric disk guides,

Fig. 7 shows that (with dashed lines) is in the planar view of the driving disk that has control loop of its neutral position,

Fig. 8 shows that (also with dashed lines) is in the planar view of the driving disk that has control loop of an operating position, and thus, thrust is towards the direction of arrow,

Fig. 9 is the schematic lateral plan according to another example embodiment of an aircraft of the present invention, and

Figure 10 is the schematic forward sight and the back view of the example embodiment of Fig. 9.

The specific embodiment

Fig. 1 illustrates schematic front elevation, back view, birds-eye view and the lateral plan according to first example embodiment of an aircraft of the present invention.Aircraft comprises a fuselage 1 and one and the propeller system 2 that is used for producing the lift that can stipulate of fuselage 1 coupling.Propeller system 2 comprises a plurality of propeller blades 3, and propeller blade 3 can be pivoted to a predetermined blade angle systems around a pivotal axis 4.Propeller blade 3 is mounted to around a S. A. 5 and rotates, and when propeller blade rotates, can regulate to produce lift the propeller blade angle.In addition, the cooresponding pivotal axis 4 of propeller blade 3 is arranged essentially parallel to rotation axis 5 location.The pivot axis 4 of propeller blade 3 is also located basically in parallel with each other.

In addition, pivotal axis 4 is located each other equidistantly, and is arranged to equating from rotation axis 5 distances.

One end of blade 3 is attached on the drive element 7 rotationally by its pivotal axis 4, or is installed in rotation in the drive element 7.Each blade 3 comprises one as the actuating spindle 6 of attacking a little, so that around pivotal axis 4 pivot propeller blades 3.Drive element 7 comprises a reach 8.

In example embodiment as shown in the figure, propeller blade 3 forms a rotor assemblies 15, that is, rotatable accordingly around a rotation axis 5, thus, this propelling unit 2 comprises that one adds up to such rotor assemblies 15 of four.Two rotor assemblies 15 are positioned on each vertical side of fuselage 1.Thus, rotation axis 5 relatively aligns with rotor assemblies 15.

Fig. 2 illustrates front elevation, back view, birds-eye view and the lateral plan of the signal of second example embodiment of one aircraft according to the present invention.In the embodiment of this demonstration, rotor assemblies 15 is parallel to the longitudinal axis location along the fuselage 1 of heading extension forward.The torque controlled system of the blade 3 of rotor assemblies 15, and the at both ends place comprises a control member, so that control described actuating spindle.

There is a guiding rotor 17 to be adjacent to guide piece 16 location, so that travel forward or motion backward.Guiding rotor 17 comprises a plurality of rotor blades 18.For the example embodiment shown in the figure, two shaft powers drive the turbo-machine location atop.

Fig. 3 illustrates schematic front elevation, birds-eye view and the lateral plan of the example embodiment of an aircraft shown in Fig. 2, and wherein, one is abutted against assembly 19 is attached to fuselage 1, so that handling goods and/or loading and unloading personnel.Be abutted against assembly 19 and be designed to an escape tube.

Fig. 4 illustrates the scheme drawing of the cross-sectional profile of a propeller blade 3.Pivot axis 4 visible its in the drawings is positioned on the side, and as seen actuating spindle 6 is positioned on the opposite side.

Fig. 5 illustrates a schematic plan view that is designed to the drive element 7 of a driving disk, and driving disk comprises a reach 8.Drive element 7 comprises that one is used for admitting the passage 9 of the pivot axis 4 of propeller blade 3.In addition, drive element 7 comprises the path 10 of the actuating spindle 6 that is used for propeller blade 3.Path 10 is designed to the elongated hole of arc.For the reason of expendable weight, drive element 7 has passage 11.

Fig. 6 is the schematic plan view of a control member 12, and this control member 12 is one and has the form of the control loop of a circular groove 14, and this circular groove extends in the outer peripheral zone of control loop, so that control the actuating spindle 6 of a propeller blade 3.In order to make control element 12 removable with respect to rotation axis 5, control member 12 can move in a guides, and this guides is the form of an eccentric disk guides 13.In the embodiment of a demonstration, control element 12 is parallel to drive element 7 location, and like this, the actuating spindle 6 of a propeller blade 3 extends through the path 10 in the drive element 7, and enters in the circular groove 14 of control element 12.

Fig. 7 illustrates the schematic plan view of a structure of drive element 7, and the control member 12 of rotor assemblies 15 is positioned at rotor assemblies 15 back.Control member 12 only dots, and only in its exterior boundary zone.Control member 12 among Fig. 7 is in its neutral position, thus, does not produce thrust and air transfer by propeller blade 3.The cross-sectional profile of propeller blade 3 is arcs of recesses down towards S. A. 5.Blade 3 be arranged in basically one imaginary cylindrical in, it is formed by the curvature of propeller blade 3.

In Fig. 8, control member 12 is shifted with respect to S. A. 5 by means of guides.One thrust produces along thrust direction 20.By means of control member 12, can recognize the principle of circulation fan regulating control among Fig. 8, thus, propeller blade 3 is in the once circle rotation process of drive element 7 with respect to control member 12, and feathering is once between its extreme amount of deflection.In fact two extreme deflected position of propeller blade 3 are positioned on the straight line, and this straight-line extension is limited by rotation axis 5 and by thrust direction 20.When the position moves past 90 when spending, propeller blade 3 is in its neutral position once more, and wherein, they do not produce a thrust or any air transfer.The rotation direction of the propeller blade 3 in the example embodiment shown in Fig. 8 is clockwise directions.

Fig. 9 illustrates the diagrammatic side view according to another example embodiment of an aircraft of the present invention, this aircraft has a fuselage 1, thus, a pulling propelling unit 21 is positioned at the front of rotor assemblies 15, and a pressure propelling unit 22 is positioned at the back of another rotor assemblies 15.In addition, turbine outlet 23 is adjacent to the interior location, zone of rotor assemblies 15.

Figure 10 illustrates the front schematic view and the back view of the example embodiment of Fig. 9, and thus, wing 24 or auxiliary wing are adjacent to fuselage 1 location.Rotor assemblies 15 is attached to wing 24 or suspended from wing.Pulling propelling unit 21 is positioned at the front of rotor assemblies 15, and pressure propelling unit 22 is positioned at the back of rotor assemblies 15.

About other further advantageous embodiments of aircraft of the present invention, for fear of repetition, general part and appended claims in visible the description.

At last, what reaffirm is that above-mentioned all examples according to aircraft of the present invention are in order to be used for discussing and illustrating device of the present invention.Yet the present invention is not limited to these embodiment.

Claims (62)

1. an aircraft has a fuselage (1) and one and the propeller system that is used for producing the lift that can stipulate (2) of fuselage (1) coupling, at this, propeller system (2) comprises a plurality of propeller blades (3), and propeller blade (3) can be pivoted to a predetermined blade angle systems around a pivotal axis (4)

It is characterized in that, propeller blade (3) is mounted to and can rotates around a rotation axis (5), when propeller blade rotates, can regulate to produce lift the propeller blade angle, the cooresponding pivotal axis (4) of propeller blade (3) is arranged essentially parallel to rotation axis (5) location.

2. aircraft as claimed in claim 1 is characterized in that, the cooresponding pivotal axis (4) of propeller blade (3) is located basically each other equidistantly.

3. aircraft as claimed in claim 1 or 2 is characterized in that, the pivotal axis (4) of propeller blade (3) is located accordingly from the identical distance of rotation axis (5) basically.

4. as the described aircraft of claim 1 to 3, it is characterized in that the pivotal axis (4) of propeller blade (3) is located basically in parallel with each other.

5. as the described aircraft of claim 1 to 4, it is characterized in that the pivotal axis (4) of each corresponding propeller blade (3) is positioned to the barycenter by propeller blade (3).

6. as the described aircraft of claim 1 to 5, it is characterized in that the shape of cross section of propeller blade (3) is the arc towards the depression of rotation axis (5).

7. as the described aircraft of claim 1 to 6, it is characterized in that propeller blade (3) comprises an actuating spindle (6) at least at one end, actuating spindle is as the contact point that propeller blade (3) is rotated around pivotal axis (4).

8. as the described aircraft of claim 1 to 7, it is characterized in that propeller blade (3) is installed in rotation on an end place that is adjacent to drive element (7) or is positioned at drive element (7).

9. aircraft as claimed in claim 8 is characterized in that, drive element (7) rotates around rotation axis (5), or is installed in rotation on the rotation axis (5).

10. aircraft as claimed in claim 8 or 9 is characterized in that drive element (7) comprises a reach (8) or quill shaft.

11., it is characterized in that drive element (7) is a drive pulley, driving disk or driving ring as the described aircraft of claim 8 to 10.

12., it is characterized in that pivotal axis (4) is arranged to a circle in the edge of drive element (7) or drive pulley or driving disk or the edge of driving ring as the described aircraft of claim 8 to 11.

13., it is characterized in that drive element (7) comprises depression or passage (9), the pivotal axis (4) that is used for admitting propeller blade as the described aircraft of claim 8 to 12.

14., it is characterized in that drive element (7) comprises depression or passage (10) as the described aircraft of claim 8 to 13, be used for the actuating spindle (6) of propeller blade (3).

15. aircraft as claimed in claim 14 is characterized in that, is used for the depression of actuating spindle (6) of propeller blade (3) or passage (10) and is configured to microscler, curved hole preferably.

16., it is characterized in that drive element (7) comprises depression, otch or passage (11) as the described aircraft of claim 8 to 15.

17., it is characterized in that drive element (7) is worked together in conjunction with a control member (12) as the described aircraft of claim 8 to 16, to regulate propeller blade (3) around its pivotal axis (4).

18. aircraft as claimed in claim 17 is characterized in that, by the rotation of propeller blade (3) and/or drive element (7), control member (12) is broken away from.

19., it is characterized in that control member (12) is installed on the rotation axis (5) as claim 17 or 18 described aircraft.

20., it is characterized in that control member (12) comprises a cycloidal gear as the described aircraft of claim 17 to 19.

21., it is characterized in that control member (12) can move with respect to rotation axis (5) as the described aircraft of claim 17 to 20 in a guides.

22. aircraft as claimed in claim 21 is characterized in that, guides comprises two vertically arranged linear steering devices, and they are the form of cross table guides.

23. aircraft as claimed in claim 21 is characterized in that, guides comprises that one is connected to the rotating guides of a linear steering device, and it is the form of an extendible and pivotable guides.

24. aircraft as claimed in claim 21 is characterized in that, guides comprises two rotating control parts, and they are the form of a pair of eccentric disk control member (13).

25. aircraft as claimed in claim 24 is characterized in that, each links to each other two eccentric disks of eccentric disk control member (13) with an actuator.

26., it is characterized in that control member (12) comprises a circular groove (14) or circular trough as the described aircraft of claim 17 to 25, be used for admitting the actuating spindle (6) of propeller blade (3).

27., it is characterized in that control member (12) is a control loop or a control panel as the described aircraft of claim 17 to 26.

28., it is characterized in that circular groove (14) or control loop comprise a non-circular portion as claim 26 or 27 described aircraft.

29. aircraft as claimed in claim 28 is characterized in that, non-circular portion provides one to depend on the angle of attack function of corner, or the angle of attack function of a stack is provided.

30. aircraft as claimed in claim 29 is characterized in that, angle of attack function is proportional to expression formula a-cos (x) w, and wherein, " a " is the number of degrees of the angle of attack of propeller blade (3), and " w " is an integer, and preferably is 11.

31., it is characterized in that heart was extended by control member (12) during the reach (8) of drive element (7) or quill shaft can preferably be configured to as the described aircraft of claim 17 to 30.

32., it is characterized in that drive element (7) and control member (12) are located in parallel with each other as the described aircraft of claim 17 to 31.

33., it is characterized in that actuating device (2) comprises around at least two structures of the rotatable propeller blade (3) of a rotation axis (5) as the described aircraft of claim 1 to 32.

34., it is characterized in that one or more rotation axiss (5) are positioned substantially in the horizontal plane as the described aircraft of claim 1 to 33.

35., it is characterized in that one or more rotation axiss (5) are parallel to the longitudinal axis location of the fuselage of heading (1) forward as the described aircraft of claim 1 to 34.

36., it is characterized in that one or more rotation axiss (5) are perpendicular to the longitudinal axis location of the fuselage of heading (1) forward as the described aircraft of claim 1 to 34.

37., it is characterized in that a plurality of propeller blades (3) form a rotor (15) around a rotation axis (5) rotation as the described aircraft of claim 1 to 36, thus, propeller system (2) comprises at least two such rotors (15).

38. aircraft as claimed in claim 37 is characterized in that, rotor (15) is staggered along the longitudinal axis.

39., it is characterized in that at least one rotor (15) is positioned on each vertical side of fuselage (1) as claim 37 or 38 described aircraft.

40., it is characterized in that at least two rotors (15) rotate along relative direction each other as the described aircraft of claim 37 to 39.

41., it is characterized in that at least two rotors (15) are positioned on each vertical side of fuselage (1) as the described aircraft of claim 37 to 40, the rotation axis (5) of cooresponding rotor (15) is aligned on the corresponding vertically side of aircraft.

42., it is characterized in that each rotor (15) is controlled individually as the described aircraft of claim 37 to 41.

43., it is characterized in that a plurality of rotors (15) are controlled together with the same manner as the described aircraft of claim 37 to 42.

44. as the described aircraft of claim 8 to 43, it is characterized in that, propeller blade (3) by means of a pivot (4) following current hand over apart from be installed in a side place away from drive element (7), or be installed in the guide assemblies (16).

45. aircraft as claimed in claim 44 is characterized in that, guide assemblies (16) basically with the identical form of drive element (7), preferably disk-shaped shape.

46., it is characterized in that guide assemblies (16) is positioned to rotate with drive element (7) as claim 44 or 45 described aircraft.

47., it is characterized in that guide assemblies (16) and drive element (7) are by means of one or S. A. (5) and coupling as the described aircraft of claim 44 to 46.

48. as the described aircraft of claim 44 to 47, it is characterized in that, guide assemblies (16) with comprise that the guides rotor (17) of a plurality of rotor blades (18) interrelates.

49. aircraft as claimed in claim 48 is characterized in that, rotor blade (18) is connected to guide assemblies (16).

50., it is characterized in that guides rotor (17) extends through the attaching parts of rotation axis (5) and is pushed into around one as claim 48 or 49 described aircraft.

51. as the described aircraft of claim 1 to 50, it is characterized in that, the propeller blade (3) or the rotor (15) that are close to the location or locate to front and back each other, in fact they become accurate minute surface to locate symmetrically.

52., it is characterized in that at the place, two ends of propeller blade (3), each control member (12) is independent of each control member (12) and operates as the described aircraft of claim 17 to 51.

53., it is characterized in that at least one drives turbine and is positioned in the fuselage (1) of aircraft as the described aircraft of claim 37 to 52.

54. aircraft as claimed in claim 53 is characterized in that, the blow down gas of turbine laterally guides directly from fuselage (1), towards rotor (15) or cross rotor (15).

55., it is characterized in that the propelling unit of a variable spacing (21,22) is positioned at the front of rotor assemblies (15) and in the back of this rotor assemblies (15) as the described aircraft of claim 37 to 54.

56. aircraft as claimed in claim 55 is characterized in that, between the propelling unit or a plurality of propelling unit (21,22) of a plurality of variable spacings, two or more rotor assemblies (15) are location, ground, front and back each other.

57. as the described aircraft of claim 37 to 56, it is characterized in that, the attached fuselage (1) that is adjacent to of a wing or auxiliary wing (24), one or more rotor assemblies (15) are attached to or are suspended on wing or auxiliary wing.

58., it is characterized in that fuselage (1) is equipped with a pair of connected components (19) as the described aircraft of claim 1 to 57, handling load is abutted against assembly (19) from this and loads and unloads, and/or personnel are abutted against assembly by this and enter or withdraw from aircraft.

59. aircraft as claimed in claim 58 is characterized in that, is abutted against assembly (19) and is a tunnel, a crane span structure or a basket.

60. as claim 58 or 59 described aircraft, it is characterized in that, be abutted against the front end that assembly (19) is positioned at fuselage (1).

61. as the described aircraft of claim 58 to 60, it is characterized in that, connected components (19) be provided with the inlet of tunnel shape roughly.

62. as the described aircraft of claim 58 to 61, it is characterized in that, be abutted against assembly (19) and comprise that one is used for being coupled to the lockout mechanism of a building or inlet.

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