WO2013107944A2 - Regulating of vortex sheets - Google Patents

Regulating of vortex sheets Download PDF

Info

Publication number
WO2013107944A2
WO2013107944A2 PCT/FR2012/000024 FR2012000024W WO2013107944A2 WO 2013107944 A2 WO2013107944 A2 WO 2013107944A2 FR 2012000024 W FR2012000024 W FR 2012000024W WO 2013107944 A2 WO2013107944 A2 WO 2013107944A2
Authority
WO
WIPO (PCT)
Prior art keywords
structures
product
electrical
paint
electromagnetic
Prior art date
Application number
PCT/FR2012/000024
Other languages
French (fr)
Other versions
WO2013107944A3 (en
Inventor
Jose Buendia
Georges-Marc RIVIERE
Christophe Schultz
Claude Annie Perrichon
Pierre Piccaluga
François Giry
Bruno Fochesato
Original Assignee
Jose Buendia
Riviere Georges-Marc
Christophe Schultz
Claude Annie Perrichon
Pierre Piccaluga
Giry Francois
Bruno Fochesato
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 Jose Buendia, Riviere Georges-Marc, Christophe Schultz, Claude Annie Perrichon, Pierre Piccaluga, Giry Francois, Bruno Fochesato filed Critical Jose Buendia
Priority to PCT/FR2012/000024 priority Critical patent/WO2013107944A2/en
Priority to PCT/FR2012/000137 priority patent/WO2013107945A2/en
Priority to PCT/FR2012/000244 priority patent/WO2013107946A2/en
Publication of WO2013107944A2 publication Critical patent/WO2013107944A2/en
Publication of WO2013107944A3 publication Critical patent/WO2013107944A3/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
    • C09D5/00—Coating compositions, e.g. paints, varnishes or lacquers, characterised by their physical nature or the effects produced; Filling pastes
    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
    • C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
    • C09D7/40—Additives
    • C09D7/60—Additives non-macromolecular
    • C09D7/61—Additives non-macromolecular inorganic
    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
    • C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
    • C09D7/40—Additives
    • C09D7/66—Additives characterised by particle size
    • C09D7/69—Particle size larger than 1000 nm
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/12—Boundary layer controls by using electromagnetic tiles, fluid ionizers, static charges or plasma
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K3/00—Use of inorganic substances as compounding ingredients
    • C08K3/02—Elements
    • C08K3/08—Metals
    • C08K2003/0812—Aluminium
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K3/00—Use of inorganic substances as compounding ingredients
    • C08K3/02—Elements
    • C08K3/08—Metals
    • C08K2003/085—Copper
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K3/00—Use of inorganic substances as compounding ingredients
    • C08K3/18—Oxygen-containing compounds, e.g. metal carbonyls
    • C08K3/20—Oxides; Hydroxides
    • C08K3/22—Oxides; Hydroxides of metals
    • C08K2003/2234—Oxides; Hydroxides of metals of lead
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K3/00—Use of inorganic substances as compounding ingredients
    • C08K3/18—Oxygen-containing compounds, e.g. metal carbonyls
    • C08K3/20—Oxides; Hydroxides
    • C08K3/22—Oxides; Hydroxides of metals
    • C08K2003/2237—Oxides; Hydroxides of metals of titanium
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K3/00—Use of inorganic substances as compounding ingredients
    • C08K3/02—Elements
    • C08K3/04—Carbon
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K3/00—Use of inorganic substances as compounding ingredients
    • C08K3/02—Elements
    • C08K3/08—Metals
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Definitions

  • the drag contributes to the resistance to the advancement, decreasing it is the fundamental principle which we bring by the present application of PCT, a solution for at least 10%, completely new, because it is a new approach based on fundamental principles of magnetic reactivities, electrical, electromagnetic structures.
  • the profile of a wing causes movement of air, between the front of the wing, the leading edge and the trailing edge at the rear of the wing. At the ends appear swirling marginal layers that disturb the wings. There are phase displacements between the different air flows originating under the wings, on the wings and on the ends of the wings, which are totally out of phase at the ends and at the meeting points with vectors of different forces generating twists between swirling sheets.
  • the modeled sectorization of electrical tensions distributed over the entire surface of the wings is a new approach, because it highlights magnetic and electromagnetic reactivities by the friction of the air flows and the effects of the air flows generated by the air. on the structure of the whole plane.
  • the method and the product make it possible to limit the counter-reactions identified in order to stabilize the flight in a significant way in order to improve the operating cost by attenuating the effects of the vortex layers around profiles, and especially the effects of phase shift on structures that electrically polarize structures.
  • a quantum product which stops or smooths, or erases the deviations of electrical tensions thus decreasing the phase displacements of the vortex layers, by an electric self induction which reverses the phases of polarizations, damping the effects.
  • the product (1) is applied on the trailing edge (2) and / or also on the salmon (3) of the wing following the possibility of the profile.
  • the product paint / aero gel is made of piezo powder, titanium oxide, lead for example, which allows to reverse the electrical information and finally to cancel.
  • the piezo principle of Pierre and Marie Curie transposes the electrical energy in mechanical mode making the electric voltage disappear, or reversing it of phase.
  • Another component makes it possible to capture the electrical information, such as metal powder, aluminum, copper or gold, for example not limited to the possibilities that will be chosen by those skilled in the art, for the electrical sensitivity to capture the electrons.
  • the two components equal weight 50/50 are mixed in an excipient, water paint for example 30% by volume, to apply the product on the structures.
  • the particle sizes are very fine to be sensitive, of the order of ten microns, for example non-limiting embodiment by those skilled in the art.
  • Those skilled in the art following the rate of regularization of the electrical charges will determine the appropriate mixture with powdered carbon particle size ⁇ , which introduces a notion of quantum information in three-dimensional instantaneous 3 to 5% of the paint product, to obtain a quantum paint regulation of phase shifts in 3 dimensions.
  • the product concerns the stability of helicopter blades, airplane or boat propellers, wind turbines, fans of electrical or mechanical machines, air conditioners or refrigerators, all that is dynamic profile in a fluid medium.
  • the product can be applied wherever the profiles need to clean the polarizations, electrical sectoring found on the structures, generated by the friction of the air.
  • the quantum product distributes by spray or brush on the structure immediately stabilizes the turbulence of the flight.
  • the flutter effect is particularly concerned, because the generated vibrations, generate variations of electromagnetic tensions of the structures, which are damped by the presence of gel / quantum paint.

Abstract

In the world of aeronautics, the modes of aerodynamic behaviour are complex and come as much from experimentation as computations for modelling the principles of flight. The behaviour of the flight is realized in three dimensions in the actual dynamics of the behaviour of the profiles of aircraft, thereby complicating the intellectual approaches of engineers on the ground. The technical approach is the reducing of drag, this being the most penalizing factor requiring thorough study. Indeed, the drag contributes to the resistance to forward motion, and decreasing it is the fundamental principle by which we afford through the present PCT application, a solution for at least 10%, which is totally new, since it is a novel approach based on fundamental principles of magnetic, electrical and electromagnetic reactivities of structures. These various fluxes around the profile exist through the viscosity of the air, which allows different directions and speeds which impose different voltage constraints on the structure. The method and the product make it possible to limit the counter-reactions identified so as to stabilize the flight in a significant manner in order to improve the operating cost thereof, by attenuating the effects of vortex sheets around the profiles, and especially the effects of phase shift on the structures which electrically polarize the structures. To regulate the phase shifts and electrical polarizations of the structures, we use a quantum product which stops or smoothes, or expunges the voltage deviations.

Description

REGULATION DES NAPPES TOURBILLONNAIRES  REGULATION OF THE TOURBILLONNAIRE NAPPES
Dans le monde de l'aéronautique, les modes de l'aérodynamisme sont complexes et relèvent autant de l'expérimentation que des calculs de modélisations des principes de vol. Le comportement du vol se réalise en trois dimensions dans la dynamique réelle du comportement des profils des aéronefs, ce qui complique les approches intellectuelles au sol des ingénieurs. C'est ainsi que les performances s'améliorent, mais aussi les coûts d'exploitations financières exigent des performances encore meilleures, dans la rentabilité, et la clientèle demande le confort, la stabilité, tout comme les pilotes. C'est ainsi que les winglets ont apporté la stabilité de vol, mais aussi une réduction de consommation de 1 ,5%. L'approche technique est la réduction de la traînée, facteur le plus pénalisant à parfaire. En effet, la traînée contribue à la résistance à l'avancement, la diminuer est le principe fondamental auquel nous apportons par la présente demande de PCT, une solution pour au moins 10%, totalement inédite, car elle est une approche nouvelle basée sur des principes fondamentaux de réactivités magnétiques, électriques, électromagnétiques des structures. Le profil d'une aile provoque dans son déplacement des mouvements d'air, entre l'avant de l'aile, le bord d'attaque et le bord de fuite à l'arrière de l'aile. Aux extrémités apparaissent des nappes marginales tourbillonnaires qui perturbent les ailes. Il y a des déphasages entre les différents flux d'air prenant naissance sous les ailes, sur les ailes et sur les extrémités des ailes qui se retrouvent en total déphasage aux extrémités et aux points de rencontres avec des vecteurs de forces différents engendrant les torsions entre les nappes tourbillonnaires. Les rencontres des nappes tourbillonnaires du dessus et du dessous de l'aile avec des vitesses et des pressions différentes s'exerçant sur le bord de fuite, entraînent des traînées résistant à l'avancement du vol, idem sur l'empennage. Ces différents flux autour du profil existent par la viscosité de l'air, qui permet des vitesses et des directions différentes qui imposent à la structure des contraintes de tensions différentes. Ainsi, par les frottements différents de l'air sur les structures, des tensions de surface s'imposent sur les structures des ailes, et créent des tensions électriques différentes par réactivités de secteur par secteur. Le but est de diminuer autour des profils les déphasages entre les nappes tourbillonnaires et les tourbillons marginaux en bout d'aile. Ces tensions déterminent, sur les structures des ailes, des forces de tensions importantes et des secteurs de tensions électriques que Boeing identifie comme d'autres opérateurs. La sectorisation modélisée de tensions électriques réparties sur toute la surface des ailes est une nouvelle approche, car elle met en évidence des réactivités magnétiques et électromagnétiques par les frottements des flux d'air et des effets des écoulements de l'air engendrés par l'air sur la structure de tout l'avion. Le procédé et le produit permettent de limiter les contre-réactions identifiées afin de stabiliser le vol de façon importante pour en améliorer le coût d'exploitation, en atténuant les effets des nappes tourbillonnaires autour des profils, et surtout les effets de déphasage sur les structures qui polarisent électriquement les structures. Pour réguler les déphasages et les polarisations électriques des structures, nous utilisons un produit quantique qui stoppe ou lisse, ou gomme les écarts de tensions électriques diminuant ainsi les déphasages des nappes tourbillonnaires, par une auto induction électrique qui inverse les phases de polarisations, amortissant les effets. Fig.l, Le produit (1) est appliqué sur le bord de fuite (2) et/ou aussi sur le saumon (3) de l'aile suivant la possibilité du profil. Le produit peinture/gel aéro est constitué de poudre de piézo, oxyde de titane, de plomb par exemple, qui permet d'inverser l'information électrique et enfin de l'annuler. Le principe piézo de Pierre et Marie Curie transpose l'énergie électrique en mode mécanique faisant disparaître la tension électrique, ou l'inversant de phase. Un autre composant permet de capter les informations électriques, telle que de la poudre métallique, d'aluminium, de cuivre, d'or par exemple non limitatif de possibilités qui seront choisies par l'homme de l'art, pour la sensibilité électrique à capter les électrons. Les deux composants à parité égale en poids 50/50 sont mélangés dans un excipient, de la peinture à l'eau pour 30% volumique par exemple, pour appliquer le produit sur les structures. Les granulométries sont très fines pour être sensibles, de l'ordre d'une dizaine de microns par exemple non limitatif de réalisation par l'homme de l'art. L'homme de l'art suivant la vitesse de régularisation des charges électriques déterminera le mélange idoine avec du carbone en poudre de granulométrie du μ, qui introduit une notion d'information quantique en trois dimensions instantanées pour 3 à 5 % du produit peinture, pour obtenir une peinture quantique de régulation des déphasages en 3 Dimensions. Pour un « Falcon 10 » 300 à 500 grammes de produit fini suffisent pour être efficace, répartis sur le bord de fuite sur ses deux faces, supérieure et inférieure, et les deux saumons. Ce principe est valable pour tout profil se déplaçant dans un milieu fluide. Ce principe s'applique pour les bateaux, les sous-marins, les voitures, comme les formules 1. Le principe du produit s'adapte et permet l'effacement des polarisations de l'effet aérodynamique 3D, des effets de nappes tourbillonnaires sur tout profil évoluant dans un milieu fluide. Les aubes des turbines d'avion sont concernées par l'aspect à deux dimensions du fait de leur carénage, cela permet d'adapter les rendements et d'harmoniser les étages de compressions. Le produit concerne la stabilité des pales d'hélicoptère, des hélices d'avion ou de bateau, les éoliennes, les ventilateurs des machines électriques ou mécaniques, les climatisations ou les frigos, tout ce qui est profil dynamique dans un milieu fluide. Le produit peut s'appliquer partout où les profils ont besoin de nettoyer les polarisations, sectorisations électriques constatées sur les structures, générées par les frottements de l'air. Le produit quantique répartit au pistolet ou au pinceau sur la structure stabilise immédiatement les turbulences du vol. L'effet flutter est notamment concerné, car les vibrations engendrées, engendrent des variations de tensions électromagnétiques des structures, qui sont amorties par la présence de gel/peinture quantique. In the world of aeronautics, aerodynamic modes are complex and come as much from experimentation as calculations of modeling of the principles of flight. The behavior of the flight is realized in three dimensions in the real dynamics of the behavior of the profiles of the aircraft, which complicates the intellectual approaches on the ground of the engineers. This is how performance improves, but also the costs of financial operations require even better performance, in terms of profitability, and customers demand comfort and stability, just like pilots. This is how the winglets brought flight stability, but also a reduction of consumption of 1, 5%. The technical approach is the reduction of drag, the most penalizing factor to perfect. Indeed, the drag contributes to the resistance to the advancement, decreasing it is the fundamental principle which we bring by the present application of PCT, a solution for at least 10%, completely new, because it is a new approach based on fundamental principles of magnetic reactivities, electrical, electromagnetic structures. The profile of a wing causes movement of air, between the front of the wing, the leading edge and the trailing edge at the rear of the wing. At the ends appear swirling marginal layers that disturb the wings. There are phase displacements between the different air flows originating under the wings, on the wings and on the ends of the wings, which are totally out of phase at the ends and at the meeting points with vectors of different forces generating twists between swirling sheets. The meeting of the swirling sheets of the top and the bottom of the wing with different speeds and pressures acting on the trailing edge, cause streaks resistant to the advance of the flight, ditto on the empennage. These different flows around the profile exist by the viscosity of the air, which allows different speeds and directions which impose different stress stresses on the structure. Thus, by the different friction of the air on the structures, surface tensions are imposed on the wing structures, and create different electrical voltages sector reactivities by sector. The aim is to reduce around the profiles the phase shifts between the vortex sheets and the marginal vortices at the end of the wing. These voltages determine, on wing structures, large voltage forces and electrical voltage sectors that Boeing identifies as other operators. The modeled sectorization of electrical tensions distributed over the entire surface of the wings is a new approach, because it highlights magnetic and electromagnetic reactivities by the friction of the air flows and the effects of the air flows generated by the air. on the structure of the whole plane. The method and the product make it possible to limit the counter-reactions identified in order to stabilize the flight in a significant way in order to improve the operating cost by attenuating the effects of the vortex layers around profiles, and especially the effects of phase shift on structures that electrically polarize structures. To regulate the phase shifts and the electric polarizations of the structures, we use a quantum product which stops or smooths, or erases the deviations of electrical tensions thus decreasing the phase displacements of the vortex layers, by an electric self induction which reverses the phases of polarizations, damping the effects. Fig.l, The product (1) is applied on the trailing edge (2) and / or also on the salmon (3) of the wing following the possibility of the profile. The product paint / aero gel is made of piezo powder, titanium oxide, lead for example, which allows to reverse the electrical information and finally to cancel. The piezo principle of Pierre and Marie Curie transposes the electrical energy in mechanical mode making the electric voltage disappear, or reversing it of phase. Another component makes it possible to capture the electrical information, such as metal powder, aluminum, copper or gold, for example not limited to the possibilities that will be chosen by those skilled in the art, for the electrical sensitivity to capture the electrons. The two components equal weight 50/50 are mixed in an excipient, water paint for example 30% by volume, to apply the product on the structures. The particle sizes are very fine to be sensitive, of the order of ten microns, for example non-limiting embodiment by those skilled in the art. Those skilled in the art following the rate of regularization of the electrical charges will determine the appropriate mixture with powdered carbon particle size μ, which introduces a notion of quantum information in three-dimensional instantaneous 3 to 5% of the paint product, to obtain a quantum paint regulation of phase shifts in 3 dimensions. For a "Falcon 10" 300 to 500 grams of finished product are enough to be effective, distributed on the trailing edge on both sides, upper and lower, and the two salmon. This principle is valid for any profile moving in a fluid medium. This principle applies to boats, submarines, cars, as formulas 1. The principle of the product adapts and allows the erasure of the polarizations of the 3D aerodynamic effect, the effects of vortices on all profile evolving in a fluid medium. The blades of the aircraft turbines are affected by the two-dimensional aspect because of their fairing, it allows to adapt the yields and harmonize the stages of compressions. The product concerns the stability of helicopter blades, airplane or boat propellers, wind turbines, fans of electrical or mechanical machines, air conditioners or refrigerators, all that is dynamic profile in a fluid medium. The product can be applied wherever the profiles need to clean the polarizations, electrical sectoring found on the structures, generated by the friction of the air. The quantum product distributes by spray or brush on the structure immediately stabilizes the turbulence of the flight. The flutter effect is particularly concerned, because the generated vibrations, generate variations of electromagnetic tensions of the structures, which are damped by the presence of gel / quantum paint.

Claims

REVENDICATIONS
l"-Procédé qui est d'amortir les polarisations électriques/électromagnétiques des structures et de réguler les nappes tourbillonnaires, des structures des ailes des avions, basé sur des principes fondamentaux de réactivités magnétiques, électriques, électromagnétiques des structures identifiées en trois dimensions, en gommant les polarisations par un produit gel/peinture quantique à information quantique qui appliqué sur le bord de fuite et le saumon, stabilise le vol et en diminue la traînée apportant performance et diminuant le coût d'exploitation.  l "-Process that is to dampen the electric / electromagnetic polarizations of the structures and to regulate the vortex sheets, wing structures of the aircraft, based on fundamental principles of magnetic, electrical, electromagnetic reactivities of structures identified in three dimensions, in erasing the polarizations by a quantum information gel / quantum paint product that applies on the trailing edge and the salmon, stabilizes the flight and reduces the drag bringing performance and decreasing the cost of exploitation.
2°- Procédé suivant la revendication 1 caractérisé par le fait que toute polarisation électrique sur la structure de l'avion peut être amortie, notamment pour stabiliser l'effet flutter. 2 ° - A method according to claim 1 characterized in that any electric polarization on the structure of the aircraft can be damped, in particular to stabilize the flutter effect.
3°- Procédé suivant la revendication 1 ou 2 caractérisé pour toute application du produit par secteur polarisé pour stabiliser tout profil circulant dans un milieu fluide. 3 ° - A method according to claim 1 or 2 characterized for any application of the product by polarized sector to stabilize any profile flowing in a fluid medium.
4°- Produit basé sur des principes fondamentaux de réactivités magnétiques, électriques, électromagnétiques des structures en réactivité sur trois dimensions générées par les contraintes des nappes tourbillonnaires, produit qui régularise, stoppe, lisse, ou gomme en grande partie les écarts de tensions électriques des structures sur trois dimensions, diminuant ainsi les déphasages des nappes tourbillonnaires, par une auto induction électrique en information quantique qui inverse les phases de polarisations, secteur par secteur et les amortit, le produit est constitué de deux produits, l'un piézo suivant les principes de Pierre et Marie Curie absorbant les charges électriques ou les mettant en inverse de phase et l'autre des poudres métalliques, sensibles captant les électrons, mélangés à part égale et ensuite mélangés dans un excipient, de la peinture à raison de 30%, pour le produit gel/peinture où est introduit du carbone en poudre de granulométrie du μ, pour 3 à 596 du produit gel/peinture qui devient peinture quantique qui est appliquée sur le bord de fuite et du saumon de l'aile, exemple non limitatif de réalisation. 4 ° - Product based on fundamental principles of magnetic reactivities, electromagnetic, electromagnetic structures in reactivity on three dimensions generated by the stresses of vortex layers, product which regularizes, stops, smooths, or gum largely the differences of electrical voltages of structures on three dimensions, thus decreasing the phase shifts of vortices, by an electrical self induction in quantum information that reverses the phases of polarizations, sector by sector and depreciates them, the product consists of two products, one piezo according to the principles Pierre and Marie Curie absorbing electrical charges or putting them in reverse phase and the other metal powders, sensitive capturing electrons, mixed equal parts and then mixed in an excipient, paint at a rate of 30%, for the product gel / paint where is introduced carbon powder granulometry of the μ, for 3 to 596 of the gel / paint product that becomes quantum paint which is applied to the trailing edge and the wing's salmon, a non-limiting example of embodiment.
5° Produit suivant la revendication 4 caractérisé pour amortir les effets flutters. 5 ° Product according to claim 4 characterized for damping effects flutters.
6°-Produit suivant la revendication 4 caractérisé pour tout profil dynamique évoluant dans un milieu fluide comme les pales d'hélicoptère, les aubes de turbines, les bateaux, les sous-marins, les voitures, les éoliennes, les ventilateurs des appareils électriques et mécaniques et les climatisations, exemples non limitatifs de réalisation. 6 ° -Product according to claim 4 characterized for any dynamic profile evolving in a fluid medium such as helicopter blades, turbine blades, boats, submarines, cars, wind turbines, fans of electrical appliances and mechanical and air conditioning, non-limiting examples of implementation.
7°- Produit suivant la revendication 4 est utile pour toutes les structures polarisées par les contraintes des nappes tourbillonnaires, aérodynamiques des fluides.  7 ° - Product according to claim 4 is useful for all the structures polarized by the stresses of vortex, aerodynamic fluids.
PCT/FR2012/000024 2012-01-17 2012-01-17 Regulating of vortex sheets WO2013107944A2 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
PCT/FR2012/000024 WO2013107944A2 (en) 2012-01-17 2012-01-17 Regulating of vortex sheets
PCT/FR2012/000137 WO2013107945A2 (en) 2012-01-17 2012-04-10 Wavefront reduction
PCT/FR2012/000244 WO2013107946A2 (en) 2012-01-17 2012-06-14 Arlequin

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/FR2012/000024 WO2013107944A2 (en) 2012-01-17 2012-01-17 Regulating of vortex sheets

Publications (2)

Publication Number Publication Date
WO2013107944A2 true WO2013107944A2 (en) 2013-07-25
WO2013107944A3 WO2013107944A3 (en) 2014-07-10

Family

ID=46614502

Family Applications (3)

Application Number Title Priority Date Filing Date
PCT/FR2012/000024 WO2013107944A2 (en) 2012-01-17 2012-01-17 Regulating of vortex sheets
PCT/FR2012/000137 WO2013107945A2 (en) 2012-01-17 2012-04-10 Wavefront reduction
PCT/FR2012/000244 WO2013107946A2 (en) 2012-01-17 2012-06-14 Arlequin

Family Applications After (2)

Application Number Title Priority Date Filing Date
PCT/FR2012/000137 WO2013107945A2 (en) 2012-01-17 2012-04-10 Wavefront reduction
PCT/FR2012/000244 WO2013107946A2 (en) 2012-01-17 2012-06-14 Arlequin

Country Status (1)

Country Link
WO (3) WO2013107944A2 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018206860A1 (en) * 2017-05-11 2018-11-15 Jose Buendia Optimized helicopter - aeroplane - wing- propeller/rotor profiles
WO2020002724A1 (en) * 2018-06-27 2020-01-02 Santos Alonso Buron Ivan Sustainable painting system for vehicles

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107936644A (en) * 2017-11-30 2018-04-20 安徽卓尔航空科技有限公司 A kind of properller blade acrylate paint

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3722830A (en) * 1971-02-12 1973-03-27 G Barber Helicopter type vehicle
US5892476A (en) * 1984-05-21 1999-04-06 Spectro Dynamics Systems, L.P. Electromagnetic radiation absorptive composition containing inorganic coated microparticles
US5370341A (en) * 1994-04-05 1994-12-06 Leon; Ross Ultralight helicopter and control system
DE10017492B4 (en) * 2000-04-07 2007-05-24 Daimlerchrysler Ag Coating for passive surface damping of vibrating surfaces of components and method for producing the coating
WO2009019326A1 (en) * 2007-08-08 2009-02-12 Picy Gestion S.A.S. Reducing the boundary layer of aerodynamic effects
JP2011131861A (en) * 2009-12-25 2011-07-07 Ihi Corp Vertical takeoff/landing aircraft

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018206860A1 (en) * 2017-05-11 2018-11-15 Jose Buendia Optimized helicopter - aeroplane - wing- propeller/rotor profiles
WO2020002724A1 (en) * 2018-06-27 2020-01-02 Santos Alonso Buron Ivan Sustainable painting system for vehicles

Also Published As

Publication number Publication date
WO2013107946A3 (en) 2014-07-24
WO2013107944A3 (en) 2014-07-10
WO2013107945A2 (en) 2013-07-25
WO2013107946A2 (en) 2013-07-25
WO2013107945A3 (en) 2014-06-26

Similar Documents

Publication Publication Date Title
Liebeck Design of subsonic airfoils for high lift
Kojima et al. Large-eddy simulation of low-Reynolds-number flow over thick and thin NACA airfoils
O'meara et al. Laminar separation bubble characteristics on an airfoil at low Reynolds numbers
Melton et al. Active flow control via discrete sweeping and steady jets on a simple-hinged flap
WO2013107944A2 (en) Regulating of vortex sheets
US20160167791A1 (en) Plated polymer aviation components
Schloesser et al. Active separation control at the pylon-wing junction of a real-scale model
Sasaki et al. Gate rudder
Thien et al. Effects of leaders position and shape on aerodynamic performances of V flight formation
Watanabe et al. A study on reduction of air resistance acting on a large container ship
Durante et al. Simplified hydrodynamic models for the analysis of marine propellers in a wake-field
Jeon et al. Analysis of maneuverability of X-rudder submarine considering environmental disturbance and jamming situations
Crivoi et al. Some experimental results on Coanda effect with application to a flying vehicle
Nguyen et al. Numerical studies on air resistace reduction methods for a large container ship with fully loaded deck-containers in oblique winds
Ma et al. Multi-objective optimization design of low-Reynolds-number airfoils S1223
Van Nguyen et al. 2017A-GS1-21 Development of Practical Gap Covers to Reduce Air Resistance Acting on Deck Containers of a Ship
Lv et al. Conceptual analysis of boundary-layer ingestion towards aircraft propulsion integration
Miklosovic et al. Measurements of midspan flow interactions of a low-aspect-ratio circulation control wing
Chu et al. Investigation of micro vortex generators on controlling flow separation over SCCH high-lift configuration
Salam et al. Numerical analysis of effect of leading-edge rotating cylinder on NACA0021 symmetric airfoil
Van Nguyen et al. Reynolds number and propeller effects on lift and drag forces on a high lift rudder with wedge tail
Perlin et al. Numerical study of reverse thrust generation using co-flow jet
Banuti et al. Steady shock refraction in hypersonic ramp flow
Kaygan et al. Computational Analysis of Adaptable Winglets for Improved Morphing Aircraft Performance
Cui et al. Comparison studies for inverted and no-inverted supersonic inlets

Legal Events

Date Code Title Description
122 Ep: pct application non-entry in european phase

Ref document number: 12707822

Country of ref document: EP

Kind code of ref document: A2