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WO2010006354A2 - Système d'entraînement de rotor pour hélicoptère, et procédé de décollage vertical d'un hélicoptère - Google Patents

Système d'entraînement de rotor pour hélicoptère, et procédé de décollage vertical d'un hélicoptère Download PDF

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Publication number
WO2010006354A2
WO2010006354A2 PCT/AT2009/000280 AT2009000280W WO2010006354A2 WO 2010006354 A2 WO2010006354 A2 WO 2010006354A2 AT 2009000280 W AT2009000280 W AT 2009000280W WO 2010006354 A2 WO2010006354 A2 WO 2010006354A2
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
masses
main rotor
moving
controlled
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/AT2009/000280
Other languages
German (de)
English (en)
Other versions
WO2010006354A3 (fr
Inventor
Herfried Exl
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of WO2010006354A2 publication Critical patent/WO2010006354A2/fr
Publication of WO2010006354A3 publication Critical patent/WO2010006354A3/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/02—Gyroplanes
    • B64C27/021—Rotor or rotor head construction
    • B64C27/025—Rotor drives, in particular for taking off; Combination of autorotation rotors and driven rotors

Definitions

  • the invention relates to a rotor drive for gyroplane with a rotating main rotor system with rotor blades and with the same masses whose distance from a rotation axis is synchronously changeable.
  • the invention further relates to a method for vertically starting a gyroplane with a rotor drive with a rotating main rotor system with rotor blades and with the same masses whose distance from a rotation axis is synchronously changeable.
  • Gyroplanes do not have a main rotor driven by a motor in flight, but use only the horizontal movement to gain lift via the rotating main rotor.
  • the start takes place after a short pre-acceleration phase of the main rotor z. B. by the engine of a forward thrust propeller and a taxiway on the ground.
  • the predetermined small main rotor blade pitch angle and the speed of the aircraft further rotation of the rotor in flight is ensured and the lift is generated by the rotor surface.
  • the gyrocopter Since the gyrocopter has no main rotor driven in flight, movement of the aircraft through the surrounding air is absolutely necessary in order to achieve the "helicopter effect" for the main rotor, so that a vertical take-off or vertical landing of the gyrocopter in calm conditions is not possible.
  • a gyroplane of the type mentioned is known in which additional masses are arranged in the rotor blades, which can be moved in the longitudinal direction of the rotor blades.
  • the masses are located near the free ends of the rotor blades, so that the rotor blades can store as much kinetic energy as possible.
  • the additional masses are displaced in the longitudinal direction of the rotor blades towards the hub. ben.
  • a disadvantage of the system known from DE 650 648 C is, on the one hand, that with the technical requirements and safety regulations given today, no additional masses should or should be arranged in the rotor blades, since this can lead to unacceptably high loads on the rotor blades and Moreover, the jump starting ability can be improved.
  • the invention is therefore based on the object to solve these problems.
  • This object is achieved in a rotor drive of the type mentioned by a mounted in addition to the rotor blades on the main rotor head device for moving the masses with a motor to move the masses during start from an outer position to an inner position.
  • This object is further achieved in a method of the type mentioned above in that the masses are controlled during the start of a motor mounted on a device in addition to the rotor blades on the main rotor head and moved synchronously to the rotational axis from an outer position to an inner position, whereby a change in the main rotor speed is effected.
  • a rotating main rotor additionally mounted device with (eg orthogonal to a two-bladed rotor arranged) guides on which symmetrically each same masses are arranged radially displaceable.
  • the masses may be moved synchronously with the center of rotation by a motor (eg, an electric motor via a gearbox and a spindle drive). If this occurs immediately after the pre-acceleration phase of the main rotor and disengagement of this drive on the ground, then taking the same masses after the angular momentum conservation set causes an increase in the angular velocity (main rotor speed).
  • the period of time of the buoyancy phase thus achieved is sufficient to accelerate the gyroplane to the necessary height and by means of a conventional, known per se, driven propeller, the necessary horizontal speed, so that a further flight is possible as a gyroplane with low blade pitch.
  • the invention differs from various known gyroplane jump starting solutions, which increase the speed of the main rotor on the ground excessively or influence only the rotational energy by adjustable (DE 650 648 C) or stationary masses at the blade tips themselves.
  • adjustable DE 650 648 C
  • stationary masses at the blade tips themselves.
  • These known solutions operate at the expense of the kinetic energy stored in the rotating rotor system and cause strong critical blade tip movements, especially on landing and in flight, as the rotor blade center of mass is disadvantageously located in the outer region near the blade tips and the rotor blades therefore have strong blade movements, deflections and twisting are exposed.
  • external kinetic energy is supplied to the rotating rotor system for moving the masses inwardly by means of a motor.
  • This energy comes for example from a battery on board the gyrocopter and is the pilot controlled and individually controllable for a short time for the additional buoyancy available, while the masses mounted by means of, for example, orthogonal to the rotor blades mechanical movement device synchronously to the center of rotation to be moved.
  • the additionally available energy or increase in the angular velocity is converted by a controlled, collective increase in the pitch of the rotor blades in buoyancy for a vertical takeoff or a vertical landing.
  • the advantage of the invention is, inter alia, the fact that the rotor speed can be kept as described by the additional energy supplied in a safe high range and no torque must be compensated as the helicopter.
  • FIG. 1 shows a first schematic embodiment of the invention
  • FIG. 2 shows a plan view of a second embodiment of the invention
  • FIG. 3 shows a detail of FIG. 2 in the region of the rotor axis
  • Fig. 5 shows a further detail of Fig. 2 in the region of the end of a guide for a
  • Fig. 6 is a view of the detail of Fig. 5 from the left and
  • Fig. 7 shows a further detail in the region of the rotor axis.
  • FIG. 1 is a schematic plan view of a first preferred embodiment of a rotor according to the invention of a trolley, in which on a rotatable about a rotation axis 5 rotor head or main rotor head 26 two rotor blades 1, 2 are collectively mounted in a known manner collectively.
  • two guides 13 are mounted on the rotor head 26 on which masses 3 between an outer position (shown in solid lines in FIG. 1) and an inner position (shown in dashed lines in FIG. 1) are displaceable ,
  • the displacement of the masses 3 takes place in the illustrated embodiment by means of a device with a motor, not shown, for example, an electric motor via a gear 7 and gimbaled threaded spindles 14.
  • the reduction gear 7 is designed so that the two transmission output shafts rotate equally fast and the Masses 3 are thus moved synchronously in and out.
  • the electrical supply of the electric motor is done for example by a hollow rotor mast.
  • FIGS. 2 to 7 A second embodiment of a rotor drive for gyroplane according to the invention is shown in more detail in FIGS. 2 to 7.
  • a mechanical device for moving the masses 3 in the rotating main rotor system with the rotor blades 1, 2 and the rotor head 26 is arranged on the rotor head 26, a mechanical device for moving the masses 3 has a mounting device 27 fastened to the rotor head 26, on which guides 13 for the masses 3 are arranged orthogonally to the rotor blades 1, 2. At the opposite end of the mounting device 27, the guides 13 are mounted in holes 16 at an end portion 18. For safety reasons, a mechanical stop 20 for the masses 3 is located on the inside of the end parts 18.
  • a threaded spindle 14 is arranged, which on the side of the end part 18 in a support bearing 17, which receives the centrifugal forces, and on the Side of the mounting device 27 is mounted via a universal joint 8 in a reduction gear 7.
  • the masses 3 may have about the same weight as the rotor blades 1, 2.
  • the ratio of the rotor circle diameter to the outer diameter of the guides 13 is preferably about 4: 3.
  • the cone angle of the guides 13 is preferably about zero degrees.
  • the guides 13 are hollow inside and have in the region of the end portion 18 limit switch 12, preferably inductive switches, which are actuated by the respective mass 3 when they are at or near their outermost position.
  • limit switch 12 preferably inductive switches, which are actuated by the respective mass 3 when they are at or near their outermost position.
  • electrical cable 19 from the limit switches 12 to a controller, not shown, which turns off a threaded spindle 14 driving motor 23 when the masses 3 actuate the switch 12.
  • inductive limit switches 12 In the area of the inner end of the guides 13 there are also two corresponding inductive limit switches 12. For safety reasons, there is still an electrical emergency switch 11, which is actuated by an actuating pin 10 fastened to a holder 9, after the inner limit switches 12 located near the rotor rotation center and, if the normal shutdown function fails, the power supply to the motor 23 and mechanically biased brake clutches 21 interrupts. When the power supply is interrupted, the brake clutches 21 are actuated, whereby the masses 3 are instantly secured in position. The pilot gets a transmitted warning signal.
  • the brake clutches 21 are activated in such a way that they brake automatically without power supply and automatically secure the input shaft to the reduction gear 7, thereby keeping the masses 3 securely in synchronous distance position relative to the rotational axis 5 of the main rotor.
  • the motor 23 shown schematically in Fig. 7 is preferably a with its axis of rotation 24 coaxial with the axis of rotation 5 of the rotor mounted electric motor which drives via the reduction gear 7 via a respective universal joint 8, a threaded spindle 14 with a low pitch. Since the electric motor rotation axis 24 is coaxial with the main rotor axis of rotation 5, unnecessary centrifugal forces are avoided during operation and the bearings of the electric motor running at a different rotational speed than the main rotor are relieved.
  • the masses are mounted with plain bearings 4 on the guides 13 and have an internal thread 28 for the threaded spindles 14.
  • a second electric motor can be used with the same direction of rotation, which is exactly opposite to the mounted on the side of the rotor mast 25 on the reduction gear 7 electric motor 23. These two electric motors together drive the reduction gear 7 and work in parallel.
  • the electric motor 23 is designed so that it is de-energized when the brake clutches 21 are active or de-energized.
  • the pilot instantly receives an optical and acoustic warning signal requesting a collective rotor blade adjustment, which is connected to the rotor blades 1, 2 at 6 to bring about the conventionally known collective control lever immediately to the minimum or Tragschraubergna.
  • the warning is turned off and the position of the masses 3 is displayed to the pilot.
  • this conventional helicopter position there is a mechanical lock on the collective control lever which can only be unlocked mechanically and deliberately by the pilot if he / she wants the collective pitch to be adjusted, e.g. wants to operate for a vertical takeoff or a vertical landing.
  • the masses 3 When the masses 3 are moved inwards or outward in a controlled manner, no torque is generated, as in the case of a helicopter, for example, which must be compensated.
  • the pilot's controlled mechanical device for moving the masses 3 is supplied on the ground and in flight from the electrical system via an on-board battery, for example by an electrical line in the hollow rotor mast 25 with energy.
  • the cell of the gyroplane is conventionally the electrically negative pole and the electric plus pool is guided via a slip ring through the hollow rotor mast 25 to the electric motor 23 upwards.
  • the slip ring may also be located on the rotor head 26 or on a pinion on the rotor head side via which the pre-acceleration of the rotor takes place on the ground.
  • the actual end positions of the masses 3 are brought to the pilot by means of the double existing limit switch 12 via the wiring 19 and through the hollow rotor mast 25 via an electrical control unit for display.
  • the retraction speed of the masses 3 can be controlled via a control unit in dependence on the collective control specification for the rotor blade position of the pilot so that the masses 3 are moved inward with linear or non-linear, increasing or decreasing or with constant speed.
  • This speed profile ensures that the rotor speed remains in a safe, usable high range during the start or drive-up phase and that the safe transition to the conventionally known gyroplane flight is ensured.
  • the synchronous movement of the masses 3 away from the center of rotation is only possible after mechanical unlocking of an electrical safety switch in the cockpit by the pilot on the ground or in flight. Furthermore, as described previously, the collective blade adjustment lever must be mechanically released by the pilot. The rotor speed must be in a safe high range. The synchronous movement of the masses 3 takes place in this mode only at minimum speed. For safety reasons, the slow movement of the masses 3 outwards during flight avoids that the inverse effect as at the start, that is to say in this case an excessive reduction of the main rotor speed, occurs. Since this process is deliberately initiated by the pilot during flight in gyrocopter mode and he expects the inevitable slight reduction in the speed of the main rotor, this flight situation can be controlled and controlled by the pilot. For reasons of safety, the synchronous movement of the masses 3 outwards during the flight can generally or only be blocked under certain conditions.
  • the described rotor drive for gyroplane is intended or suitable for man-bearing but also for aircraft models.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Preparation Of Clay, And Manufacture Of Mixtures Containing Clay Or Cement (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
  • Toys (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

L'invention concerne un hélicoptère comprenant un système à rotor principal entraîné en rotation, à pales de rotor (1, 2) et à masses égales (3), dont la distance par rapport à un axe de rotation (5) peut varier de manière synchronisée et contrôlée. L'invention est caractérisée en ce qu'il est prévu, en plus des pales de rotor (1, 2), un dispositif (7, 13, 14) monté sur la tête de rotor principal (26), destiné au déplacement des masses (3), muni d'un moteur, de telle sorte que les masses (3) puissent être déplacées, lors du décollage, d'une position extérieure en une position intérieure, permettant ainsi d'accélérer le rotor.
PCT/AT2009/000280 2008-07-17 2009-07-16 Système d'entraînement de rotor pour hélicoptère, et procédé de décollage vertical d'un hélicoptère Ceased WO2010006354A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AT11092008A AT506694B1 (de) 2008-07-17 2008-07-17 Rotorantrieb für tragschrauber und verfahren zum senkrechten starten eines tragschraubers
ATA1109/2008 2008-07-17

Publications (2)

Publication Number Publication Date
WO2010006354A2 true WO2010006354A2 (fr) 2010-01-21
WO2010006354A3 WO2010006354A3 (fr) 2010-03-11

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/AT2009/000280 Ceased WO2010006354A2 (fr) 2008-07-17 2009-07-16 Système d'entraînement de rotor pour hélicoptère, et procédé de décollage vertical d'un hélicoptère

Country Status (2)

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AT (1) AT506694B1 (fr)
WO (1) WO2010006354A2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016002231A1 (de) 2016-02-25 2017-08-31 Robert Cwalina Fluggerät mit aktiv betriebenen schwenkbaren Rotoren und passiv betriebenen Hauptrotor

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE650648C (de) * 1935-07-20 1937-09-29 E H Claude Dornier Dr Ing Sprungstartsteilschrauber
DE1270408B (de) * 1958-09-30 1968-06-12 Bell Helicopter Corp Daempfungseinrichtung fuer den Rotor eines Hubschraubers mit halbstarrem Blattanschluss
FR1404752A (fr) * 1964-06-27 1965-07-02 Dispositif destiné à améliorer les performances au décollage d'engins à hélicesustentatrice
US3814351A (en) * 1972-12-06 1974-06-04 United Aircraft Corp Coaxial rotor yaw control

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016002231A1 (de) 2016-02-25 2017-08-31 Robert Cwalina Fluggerät mit aktiv betriebenen schwenkbaren Rotoren und passiv betriebenen Hauptrotor
DE102016002231A9 (de) 2016-02-25 2019-05-02 Ramin Assisi Fluggerät mit aktiv betriebenen schwenkbaren Rotoren und passiv betriebenen Hauptrotor
DE102016002231B4 (de) 2016-02-25 2021-10-07 Ramin Assisi Fluggerät mit aktiv betriebenen schwenkbaren Rotoren und passiv betriebenen Hauptrotor

Also Published As

Publication number Publication date
WO2010006354A3 (fr) 2010-03-11
AT506694A4 (de) 2009-11-15
AT506694B1 (de) 2009-11-15

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