EP2464566A2 - Stabilized safety gyroplane - Google Patents

Stabilized safety gyroplane

Info

Publication number
EP2464566A2
EP2464566A2 EP09740163A EP09740163A EP2464566A2 EP 2464566 A2 EP2464566 A2 EP 2464566A2 EP 09740163 A EP09740163 A EP 09740163A EP 09740163 A EP09740163 A EP 09740163A EP 2464566 A2 EP2464566 A2 EP 2464566A2
Authority
EP
European Patent Office
Prior art keywords
ecrt
self
rotary wing
autogyro
aircraft
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.)
Withdrawn
Application number
EP09740163A
Other languages
German (de)
French (fr)
Inventor
Claude Annie Perrichon
François Giry
Pierre Piccaluga
José BUENDIA
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
Priority claimed from PCT/FR2009/001006 external-priority patent/WO2010103194A2/en
Application filed by Individual filed Critical Individual
Publication of EP2464566A2 publication Critical patent/EP2464566A2/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/02—Gyroplanes
    • 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 transport model of tomorrow is an enigma, both on the problem of consumption, pollution and security, for everyone who travels.
  • the displacement is an obligation for the active people who do not sell that virtual but also concrete benefits, which requires a certain reactivity, which by the speed restrictions lengthens the operations and the decision-making.
  • the autogyro is a particular aircraft that needs to be developed, generally towards flight safety, and respect for the environment. Several factors of noise and pollution have opened us to a translation on the ground, to a transport at a low cost.
  • the present application takes various known processes that we assemble in a particular way and which in this application is the integration of a double rotary wing which itself is coupled to a launch engine, which exempts us from a propeller against couple that presents many dangers. This device is put in place, the time that the natural effect of self-lift is sufficient.
  • a specific compilation introduces new technologies assembled for the first time in the principle of a self-gyrating technology, which represents the eCRT technology which brings a complement of security.
  • Fig. 1 autogyra consisting of two helices (1, 2), rotating wings whose blades turn in opposite directions to obtain a balance of levitation forces not requiring a helix active counter-torque.
  • the engine (5) to launch the light propellers (1, 2) before the auto-levitation takes effect, which strongly secures the takeoff.
  • This device also allows with a low wind, less than 20 knots, to take off virtually in vertical without damage and loss of balance, or rolling too long.
  • the torque converter controlled from the pilot cell activates in reverse mechanical rotation (6) the propellers (1.2) until the autorotation suspends the aircraft. This converter makes it possible to transmit the minimum useful energy of the motor (5) to ensure the lift.
  • the engine (5) translates its power to the propeller (4) of horizontal thrust, which gives the speed of translation and allows to advance the autogyra which takes its lift without the need for energy input on its pale which naturally underlie the aircraft (1, 2).
  • the blades are constant pitch, which tends to create a drag decreasing the speed of flight, but provides significant security.
  • the step could be variable but identical for the two pale constituting dynamic wing, like fixed-wing aircraft propellers, with variable pitch propeller. Obviously both propellers (1,2) are concerned. From cell (3) commands allow actions for the right flight with high visibility. This stability by providing integration of two propellers constituting the rotary wing constitutes an important stability and with the engine connection in relatively low speed of advancement provides lift without autorotating the aircraft.
  • This device is a safety assurance by self stabilization of the aircraft on the spot of its flight. This characteristic is not the regime nor the function but a momentary temporary solution of flight safety, that the autogyrists do not have for the moment, and which certainly requires energy.
  • the mechanical noise and propellers are reduced by the contribution of eCRT technology which is one of the claimed applications on mechanical parts, constituting a mechanical organ, of flight, linking the engine, the structure of the cell, the axes propellers of the dynamic wing and the power converter to pale which are regulated at launch of the aircraft.
  • the noise gain is at least 5 decibels and the power output with a traditional piston engine or type Wanckel or turbine, a non-limiting example of possibilities will be very effective with 110 horsepower to launch the set of propellers effortlessly.
  • the mechanical friction is extremely reduced, which brings a reliability and an available power gain very important given this multi-axis mechanical organization assisted by intelligent eCRT technology which regulates the voltages, the stresses of the mechanical parts.
  • the aerial activity of the machines is extremely sensitive and the dynamic wing becomes "more bearing" by the eCRT realization which orders the polarities and the electromagnetic fluxes managed even canceled, which eliminates the inconveniences of the electromagnetic incompatibilities generated by the effects of mechanical stresses, influencing the flight characteristics, increasing the flight performance and leaving the mechanical powers free without effort.
  • the eCRT probes erase these incidences of fluctuating electromagnetic charges contrary to the ideal stable conditions for the flight of an aircraft, without parasite and without fluctuating counterforce, equipped with at least one dynamic rotary wing, in this case of example non-exhaustive realization.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The present application takes various known processes and assembles the latter in a particular manner, said application relating to the integration of a double rotating wing which is in turn coupled to a launching engine, which dispenses with a counter-torque propeller, which can be dangerous. The device is arranged such that the time for the natural effect of self-containment is sufficient. A specific compilation introduces novel technologies brought together for the first time with the principle of gyroplane technology, which is the eCRT technology providing additional safety. An aircraft with a rotating wing is assisted by "radio controlled" eCRT performed by eCRT sensors which impede the effects of fluctuating electromagnetic incompatibilities generated by the mechanical parts under stress, thus increasing flight performances, and freeing the available power from stresses, parasites or fluctuating counterforces.

Description

- AUTOGYRE SECURISE STABILISE - - SECURE AUTOGYRE STABILIZED -
Le modèle de transport de demain est une énigme, tant sur le problème de la consommation, de la pollution et de la sécurité, pour tout le monde qui voyage. Nous avons longuement réfléchi et regardé les différentes solutions, qui avec les restrictions de circulation, nous ont porté vers une solution plus rapide, efficace et qui demande une plus grande attention envers la sécurité. En effet, le déplacement est une obligation pour les gens actifs qui ne vendent pas que du virtuel mais aussi des prestations concrètes, ce qui demande une certaine réactivité, qui par les restrictions de vitesse allonge les opérations et les prises de décisions. L'autogyre est un aéronef particulier qui demande à être développé, de façon générale vers une sécurité de vol, et un respect de l'environnement. Plusieurs facteurs de bruits et de pollutions nous ont ouvert à une translation sur la terre, à un transport à un faible coût. La sécurité avant tout nous oblige à prendre en compte le problème des avions qui atterrissent avec une vitesse élevée et en des endroits spécifiques. L'hélicoptère est très onéreux mais aussi fait du bruit et un indice de sécurité nous inquiète, de par les pâles du rotor qui subissent par un jeu de bielles, des inclinaisons différentes à chaque tour. The transport model of tomorrow is an enigma, both on the problem of consumption, pollution and security, for everyone who travels. We spent a lot of time thinking and looking at the different solutions, which together with the traffic restrictions, brought us to a faster, more efficient solution that requires more attention to security. Indeed, the displacement is an obligation for the active people who do not sell that virtual but also concrete benefits, which requires a certain reactivity, which by the speed restrictions lengthens the operations and the decision-making. The autogyro is a particular aircraft that needs to be developed, generally towards flight safety, and respect for the environment. Several factors of noise and pollution have opened us to a translation on the ground, to a transport at a low cost. Safety first and foremost requires us to take into account the problem of planes landing at high speeds and in specific places. The helicopter is very expensive but also noise and a security index worries us, because of the blades of the rotor which undergo by a set of rods, different inclinations at each turn.
La présente demande prend différents processus connus que nous assemblons de façon particulière et qui dans cette demande est l'intégration d'une double voilure tournante qui elle-même est couplée à un moteur de lancement, ce qui nous dispense d'une hélice de contre couple qui présente de nombreux dangers. Ce dispositif est mis en place, le temps que l'effet naturel de l'auto-portance soit suffisant. Une compilation spécifique introduit de nouvelles technologies assemblées pour la première fois au principe d'une technologie d'autogyre, que représente la technologie eCRT qui apporte un complément de sécurité.  The present application takes various known processes that we assemble in a particular way and which in this application is the integration of a double rotary wing which itself is coupled to a launch engine, which exempts us from a propeller against couple that presents many dangers. This device is put in place, the time that the natural effect of self-lift is sufficient. A specific compilation introduces new technologies assembled for the first time in the principle of a self-gyrating technology, which represents the eCRT technology which brings a complement of security.
Nous illustrons un autogyre Fig.l, constitué de deux hélices (1, 2), voilures tournantes dont les pâles tournent en sens inverse l'une de l'autre afin d'obtenir un équilibre des forces de sustentation ne nécessitant pas d'hélice active de contre couple. En effet, pour le lancement de l'aéronef nous utilisons le moteur (5) afin de lancer les pâles hélices (1, 2) avant que l'auto-sustentation prenne effet, ce qui sécurise fortement le décollage. Ce dispositif permet aussi avec un vent faible, moins de 20 nœuds, de décoller pratiquement en verticale sans dommage et perte d'équilibre, ou de roulage trop long. Le convertisseur de couple commandé depuis la cellule du pilote, active en inverse de rotation mécanique (6) les hélices (1.2) jusqu'à ce que l'autorotation sustente l'aéronef. Ce convertisseur permet de transmettre l'énergie minimum utile du moteur (5) pour assurer la sustentation. Le moteur (5) translate sa puissance à l'hélice (4) de poussée horizontale, ce qui donne la vitesse de translation et permet de faire avancer l'autogyre qui prend sa sustentation sans avoir besoin d'apport d'énergie sur ses pâles qui sous- tendent naturellement l'aéronef (1, 2). Les pâles sont à pas constant, ce qui tend à créer une traînée diminuant la vitesse de vol, mais apporte une sécurité importante. Le pas pourrait être variable mais identique pour les deux pâles constituant la voilure dynamique, comme les hélices d'avion à voilure fixe, avec hélice à pas variable. Evidemment les deux hélices (1,2) sont concernées. Depuis la cellule (3) les commandes permettent les actions pour le bon vol avec une grande visibilité. Cette stabilité par apport d'intégration de deux hélices constituant la voilure tournante constitue une stabilité importante et avec la liaison moteur en vitesse relativement faible d'avancement assure une sustentation sans mettre en autorotation l'aéronef. We illustrate a Fig. 1 autogyra, consisting of two helices (1, 2), rotating wings whose blades turn in opposite directions to obtain a balance of levitation forces not requiring a helix active counter-torque. Indeed, for the launch of the aircraft we use the engine (5) to launch the light propellers (1, 2) before the auto-levitation takes effect, which strongly secures the takeoff. This device also allows with a low wind, less than 20 knots, to take off virtually in vertical without damage and loss of balance, or rolling too long. The torque converter controlled from the pilot cell, activates in reverse mechanical rotation (6) the propellers (1.2) until the autorotation suspends the aircraft. This converter makes it possible to transmit the minimum useful energy of the motor (5) to ensure the lift. The engine (5) translates its power to the propeller (4) of horizontal thrust, which gives the speed of translation and allows to advance the autogyra which takes its lift without the need for energy input on its pale which naturally underlie the aircraft (1, 2). The blades are constant pitch, which tends to create a drag decreasing the speed of flight, but provides significant security. The step could be variable but identical for the two pale constituting dynamic wing, like fixed-wing aircraft propellers, with variable pitch propeller. Obviously both propellers (1,2) are concerned. From cell (3) commands allow actions for the right flight with high visibility. This stability by providing integration of two propellers constituting the rotary wing constitutes an important stability and with the engine connection in relatively low speed of advancement provides lift without autorotating the aircraft.
Ce dispositif est une assurance de sécurité par une auto stabilisation de l'aéronef sur place de son vol. Cette caractéristique n'est pas le régime ni la fonction mais une solution transitoire momentanée de sécurité de vol, que les autogyres n'ont pas pour l'instant, et qui nécessite certes de l'énergie. This device is a safety assurance by self stabilization of the aircraft on the spot of its flight. This characteristic is not the regime nor the function but a momentary temporary solution of flight safety, that the autogyrists do not have for the moment, and which certainly requires energy.
Par ailleurs, les bruits mécaniques et des hélices sont diminués par l'apport de la technologie eCRT qui est une des applications revendiquées sur les pièces mécaniques, constituant un organe mécanique, de vol, liant le moteur, la structure de la cellule, les axes des hélices de la voilure dynamique et le convertisseur de puissances aux pâles qui sont régulées au lancement de l'aéronef. Le gain de bruit est d'au moins 5 décibels et la puissance utile avec un moteur à pistons traditionnel ou de type Wanckel ou turbine, exemple non limitatif de possibilités sera très efficace avec 110 chevaux afin de lancer l'ensemble des hélices sans effort. En effet, les frottements mécaniques sont extrêmement réduits, ce qui apporte une fiabilité et un gain de puissance disponible très important compte tenu de cette organisation mécanique multi-axes assistés par la technologie eCRT intelligente qui régule les tensions, les contraintes des pièces mécaniques. Nous revendiquons l'antériorité du brevet PCT/FR 2009/ 001006 du 14 Août 2009. Ce PCT de par sa technologie apporte un silence de fonctionnement ainsi qu'une fiabilité déconcertante, tout en libérant du couple moteur, nous supprimons également 15 à 20% de consommation de carburant et plus de 35 à 40% de NOX en moins. Les palpeurs eCRT sont placés sur les axes et sur la cellule (3) de l'autogyre, eCRT (7 ; 8 ; 9 ) par exemple, palpeurs de radio autorégulation collés, ce qui donne toutes les positions relatives auto gérées par « radio autorégulation » des mouvements des pièces mécaniques en contraintes contribuant aux mouvements de l'aéronef. L'activité aérienne des machines est d'une sensibilité extrême et la voilure dynamique devient « plus portante » par la réalisation eCRT qui ordonne les polarités et les flux électromagnétiques gérés voire annulés, ce qui supprime les inconvénients des incompatibilités électromagnétiques générées par les effets de contraintes mécaniques, venant influer sur les caractéristiques de vol, augmentant les performances de vol et laissant libres les puissances mécaniques sans effort. Ainsi, les palpeurs eCRT viennent gommer ces incidences de charges électromagnétiques fluctuantes contraires aux conditions idéales stables pour le vol d'un aéronef, sans parasite et sans contre force fluctuante, muni au moins d'une voilure tournante dynamique, dans ce cas d'exemple de réalisation non exhaustif.  Moreover, the mechanical noise and propellers are reduced by the contribution of eCRT technology which is one of the claimed applications on mechanical parts, constituting a mechanical organ, of flight, linking the engine, the structure of the cell, the axes propellers of the dynamic wing and the power converter to pale which are regulated at launch of the aircraft. The noise gain is at least 5 decibels and the power output with a traditional piston engine or type Wanckel or turbine, a non-limiting example of possibilities will be very effective with 110 horsepower to launch the set of propellers effortlessly. Indeed, the mechanical friction is extremely reduced, which brings a reliability and an available power gain very important given this multi-axis mechanical organization assisted by intelligent eCRT technology which regulates the voltages, the stresses of the mechanical parts. We claim the prior art of the patent PCT / FR 2009/001006 of August 14, 2009. This PCT by its technology brings a silence of operation as well as a disconcerting reliability, while freeing of the engine torque, we also remove 15 to 20% fuel consumption and over 35 to 40% less NOX. The eCRT probes are placed on the axes and on the cell (3) of the autogyro, eCRT (7; 8; 9) for example, self-regulating radio probes glued, which gives all the relative positions self managed by "radio self-regulation Movements of the mechanical parts in constraints contributing to the movements of the aircraft. The aerial activity of the machines is extremely sensitive and the dynamic wing becomes "more bearing" by the eCRT realization which orders the polarities and the electromagnetic fluxes managed even canceled, which eliminates the inconveniences of the electromagnetic incompatibilities generated by the effects of mechanical stresses, influencing the flight characteristics, increasing the flight performance and leaving the mechanical powers free without effort. Thus, the eCRT probes erase these incidences of fluctuating electromagnetic charges contrary to the ideal stable conditions for the flight of an aircraft, without parasite and without fluctuating counterforce, equipped with at least one dynamic rotary wing, in this case of example non-exhaustive realization.

Claims

REVENDICATIONS
.."-Procédé qui sécurise et stabilise un autogyre par une intégration mécanique d'une double voilure tournante en sens inverse couplée à un moteur de lancement, le temps que l'auto-sustentation naturelle prenne le relais, ce qui dispense d'une hélice de contre couple, et permet un décollage vertical par vent faible.  .. "- A method that secures and stabilizes an autogyro by a mechanical integration of a double rotary wing in the opposite direction coupled to a launch engine, the time that the natural self-levitation takes over, which exempts a counter torque propeller, and allows a vertical takeoff in low wind.
2° Procédé selon la première revendication additionné d'une hélice de poussée qui permet l'avancement de l'autogyre et l'auto portance par translation de l'autogyre suivant l'axe horizontal.  2 ° Method according to the first claim plus a thrust propeller that allows the advancement of the autogyra and self-lift by translating the autogyra along the horizontal axis.
3° Appareil de vol à voilure tournante suivant le principe de l'autogyre, qui est constitué d'une double voilure tournante en sens inverse couplée à un convertisseur de puissance qui transfert la puissance du moteur de l'autogyre pour le lancement, par un convertisseur mécanique qui assure l'énergie de sustentation, et qui transpose par la commande de la cellule, la puissance à l'hélice de poussée horizontale, l'aéronef par la vitesse de translation se met en auto sustentation naturelle, principe de fonctionnement qui assure le décollage à faible vent et ne pouvant pas se mettre en auto rotation, exemple non limitatif de réalisation..  (3) Rotary wing flight apparatus using the principle of the autogyro, which consists of a double rotary wing in the opposite direction coupled to a power converter which transfers the power of the engine of the autogyro for launch, by a mechanical converter which provides lift energy, and which transposes the power to the horizontal thrust propeller by the control of the cell, the aircraft by the translational speed goes into self-sustaining operation, which principle of operation ensures takeoff at low wind and can not be self-rotating, a non-limiting example of realization ..
4° Appareil de vol à voilure tournante suivant la revendication 3 est assisté de « radio régulation » eCRT réalisé par des palpeurs eCRT qui gomment les effets d'incompatibilités électromagnétiques générées par les pièces mécaniques en contraintes, augmentant ainsi les performances de vol, et laissant libres les puissances disponibles sans effort, sans parasite et de contre force. 4 ° rotary wing flight apparatus according to claim 3 is assisted by "radio regulation" eCRT performed by eCRT probes that erase the effects of electromagnetic incompatibilities generated by the mechanical parts in constraints, thus increasing flight performance, and leaving free available powers without effort, without parasite and against force.
EP09740163A 2009-08-14 2009-08-20 Stabilized safety gyroplane Withdrawn EP2464566A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
PCT/FR2009/001006 WO2010103194A2 (en) 2009-03-12 2009-08-14 Mechanical movements adjusted by electromagnetic probe
PCT/FR2009/001017 WO2011018559A2 (en) 2009-08-14 2009-08-20 Stabilized safety gyroplane

Publications (1)

Publication Number Publication Date
EP2464566A2 true EP2464566A2 (en) 2012-06-20

Family

ID=43587046

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09740163A Withdrawn EP2464566A2 (en) 2009-08-14 2009-08-20 Stabilized safety gyroplane

Country Status (8)

Country Link
EP (1) EP2464566A2 (en)
JP (1) JP2013501675A (en)
KR (1) KR20120040713A (en)
CN (1) CN102811904A (en)
BR (1) BR112012003387A2 (en)
CA (1) CA2770944A1 (en)
RU (1) RU2012109561A (en)
WO (1) WO2011018559A2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9776713B2 (en) 2015-01-21 2017-10-03 Jaime G. Sada-Salinas Off-board gyrocopter take-off systems and associated methods

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JP2015123961A (en) * 2013-12-26 2015-07-06 郁徳 新原 Helicopter of body of rotation type

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JPS52135200A (en) * 1976-05-04 1977-11-11 Satoru Nakagome Helicopter autogyro convertible plane
CH666664A5 (en) * 1985-10-09 1988-08-15 Hans Berger High speed helicopter fitted with propeller - has clutch to uncouple main rotor at speed of 150 kilometres an hour
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FR2869754A1 (en) * 2004-04-29 2005-11-04 Francois Giry Sound reproducing method, for use with e.g. television set, involves generating sound by magnetic field that induces variable electric current which mechanically vibrates silica or silica compound structures e.g. molded plaster
EP1724192A1 (en) * 2005-05-04 2006-11-22 Mauro Achille Nostrini Structure and control system of an aircraft equipped with rotors for lift and vertical flight, and with a pusher-propeller for horizontal thrust
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EP2027761A1 (en) * 2006-06-02 2009-02-25 Claude Annie Perrichon Management of active electrons
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9776713B2 (en) 2015-01-21 2017-10-03 Jaime G. Sada-Salinas Off-board gyrocopter take-off systems and associated methods
US10112705B2 (en) 2015-01-21 2018-10-30 Jaime G. Sada-Salinas Off-board gyrocopter take-off systems and associated methods

Also Published As

Publication number Publication date
CA2770944A1 (en) 2011-02-17
KR20120040713A (en) 2012-04-27
CN102811904A (en) 2012-12-05
JP2013501675A (en) 2013-01-17
BR112012003387A2 (en) 2016-02-16
WO2011018559A2 (en) 2011-02-17
RU2012109561A (en) 2013-09-20
WO2011018559A3 (en) 2012-08-23

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