DE102011101142A1 - Device for varying temperature of electrical resistance layer for de-icing aircraft component e.g. wing, has support surface made of glass fiber reinforced fabric or aluminum honeycomb plates and coated with carbon nano tube dispersion - Google Patents

Device for varying temperature of electrical resistance layer for de-icing aircraft component e.g. wing, has support surface made of glass fiber reinforced fabric or aluminum honeycomb plates and coated with carbon nano tube dispersion Download PDF

Info

Publication number
DE102011101142A1
DE102011101142A1 DE201110101142 DE102011101142A DE102011101142A1 DE 102011101142 A1 DE102011101142 A1 DE 102011101142A1 DE 201110101142 DE201110101142 DE 201110101142 DE 102011101142 A DE102011101142 A DE 102011101142A DE 102011101142 A1 DE102011101142 A1 DE 102011101142A1
Authority
DE
Germany
Prior art keywords
wing
resistance layer
glass fiber
support surface
fiber reinforced
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Withdrawn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
DE201110101142
Other languages
German (de)
Inventor
wird später genannt werden Erfinder
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.)
BEIER GERHARD M
Original Assignee
BEIER GERHARD M
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 BEIER GERHARD M filed Critical BEIER GERHARD M
Priority to DE201110101142 priority Critical patent/DE102011101142A1/en
Publication of DE102011101142A1 publication Critical patent/DE102011101142A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/12De-icing or preventing icing on exterior surfaces of aircraft by electric heating

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Surface Heating Bodies (AREA)

Abstract

The device has a geometrically predetermined support surface made of glass fiber reinforced fabric or aluminum honeycomb plates and coated with specifically mixed components of a carbon nano tube (CNT) dispersion or matrix. The surface is electrically contacted, digitally controlled and regulated and acts against icing of aircraft wings. The support surface is formed of the glass fiber reinforced fabric with different spatial expansions such that active and passive heating of icing prone wing segments occurs during takeoff and landing of the aircraft. The electrical resistance layer is made of polymer composite. An independent claim is also included for a method for varying temperature of an electrical resistance layer.

Description

Jedes Luftfahrzeug ist bei bestimmten Wetterbedingungen auf ein zuverlässiges Enteisungs-System angewiesen. Die Tragflächen sind durch ihre aerodynamische Bedeutung ein hochsensibler Bereich, der unabdingbar von Eis und Schnee frei zu halten ist.Every aircraft relies on a reliable de-icing system in certain weather conditions. Due to their aerodynamic significance, the wings are a highly sensitive area, which is essential for keeping ice and snow clear.

Nach dem Stand der Technik wird zu diesem Zweck warme Luft durch die Tragflächen-Vorderkante gepumpt, die dem Verdichter der Triebwerke entnommen und ventilgesteuert durch ein Rohrleitungssystem geleitet wird. Dabei wird die korrekte Funktion überwacht und auf Undichtigkeit geprüft.In the prior art, for this purpose warm air is pumped through the airfoil leading edge, which is taken from the compressor of the engines and valve controlled passed through a piping system. The correct function is monitored and checked for leaks.

Nachteil dieses Systems ist die aufwendige Konstruktion, ihr hohes Gewicht, die mangelnde Leistung und die Fehleranfälligkeit. Die Zapfluft wird dem Verdichter entnommen, also verringert sich die Leistungsbilanz des Triebwerkes. Optimal wäre, wenn die Luft ausschließlich für die Schuberzeugung verbraucht wird.Disadvantage of this system is the complex construction, its high weight, the lack of performance and the susceptibility to errors. The bleed air is taken from the compressor, thus reducing the power balance of the engine. It would be optimal if the air is used exclusively for thrust generation.

Vereisung an den Tragflächen tritt dann ein, wenn Luftfeuchtigkeit mit tiefen Temperaturen zusammentreffen. Beim Start kann die bordeigene Enteisungsanlage wegen Schubveringerung nicht benutzt werden, sie bleibt inaktiv. Beim Durchflug durch Wolken gibt es keine Probleme, abgesehen von erhöhten Treibstoffverbrauch. Beim Landeanflug sinkt die Drehzahl der Triebwerke, dennoch bleibt das System aktiv und Zapfluft wird dem Verdichter entnommen um gegebenenfalls durchstarten zu können.Icing on the wings occurs when humidity coincides with low temperatures. At startup, the on-board de-icing system can not be used due to thrust reduction, it remains inactive. When passing through clouds, there are no problems, except for increased fuel consumption. When approaching the speed of the engines, but the system remains active and bleed air is taken from the compressor to start if necessary.

Die Erfindung sieht deshalb vor, das vorhandene Anti Icingsystem durch eine hochsichere elektrische Tragflächenbeheizung zu ersetzen. Das Rohrsystem wird durch unmittelbare Beschichtung der vorderen Tragflächeninnenseite mit einer nanoskaligen, elektrisch leitenden Matrix ersetzt. Dieses Material kann sowohl direkt auf das vorher isolierte Tragflächematerial im Spritzverfahren aufgebracht werden oder durch vorhergefertigte Inlets in die Vorderkante der Tragfläche mittels Halterungen montiert werden.The invention therefore provides to replace the existing anti-icing system by a highly secure electric hydrofoil heating. The pipe system is replaced by direct coating of the front wing inside with a nanoscale, electrically conductive matrix. This material can either be applied directly to the previously isolated support material by spraying or by prefabricated inlets into the leading edge of the support surface by means of brackets.

Sowohl die erforderliche Temperatur als auch die Zeitdauer des Einteisungsvorganges wird dabei elektronisch gesteuert. Die technischen Möglichkeiten können durch die Leistungsparameter der Matrix hinsichtlich Stromstärke, Leistung und Amperè sowie Temperatur den Erfordernissen der einzelnen Flugzeugtypen angepasst werden. Die Dichte der nanoskaligen Matrix aus Carbo Nano Tubes und anderen conduktiven Partikeln ist regelbar und richtet sich nach den Erfordernissen bei Start. Durchflug und Landung. Dabei ist die Zeitdauer der Tragflächenerwärmung sensorisch entsprechend der Witterungsverhältnisse gesteuert.Both the required temperature and the duration of the Einteisungsvorganges is controlled electronically. The technical possibilities can be adapted to the requirements of the individual aircraft types by means of the power parameters of the matrix with regard to current intensity, power and ampere as well as temperature. The density of the nanoscale matrix of Carbo Nano Tubes and other conductive particles is adjustable and depends on the requirements at startup. Flight and landing. The duration of the wing warming is sensory controlled according to the weather conditions.

Die elektrischen Werte können entsprechend der Spezifikation der nanoskaligen Matrix von 12 Volt bis 230 Volt gewählt werden. Auch Gleichstrombetrieb aus Akkus ist möglich. Der extrem hohe Wärmedurchgangswert der Matrix von 6000 Watt/Messeinheit übertrifft alle, als stromleitende Materialien bekannten Werkstoffe um ein Vielfaches.The electrical values can be chosen according to the specification of the nanoscale matrix from 12 volts to 230 volts. Also DC operation from batteries is possible. The extremely high heat transfer value of the 6000 watt / meter matrix surpasses all materials known as current-conducting materials by a multiple.

Gleiches trifft auch auf geometrisch andere Formgebungen zu, etwa auf röhrenförmig in die Tragflächennase eingelegte Heizmodule oder im Halbradius ausgeführte GfK-Formteile, die mit der nanoskaligen Matrix beschichtet sind.The same applies to geometrically different shapes, such as heating modules inserted tubularly in the wing nose or GfK molded parts designed in the half-radius, which are coated with the nanoscale matrix.

Die Vorteile der Erfindung:The advantages of the invention:

  • – Leistungsreserve im Landeanflug falls Durchstarten erforderlich wird- Power reserve in landing approach if take-off is required
  • – Kraftstoffersparnis gegenüber Zapfluftsystemen- Fuel savings compared to bleed air systems
  • – Gewichtsersparnis gegenüber dem Zapfluftsystem und seiner Ventile- Weight savings compared to the bleed air system and its valves
  • – bei grenzwertiger Wetterlage entfällt externe Enteisung mit chemischen Stoffen- in borderline weather, external de-icing with chemicals is not required
  • – Triebwerke ohne Zapfluftanlage werden leichter und sicherer, ökologischer Vorteil- Engines without bleed air system become lighter and safer, ecological advantage
  • – Kostenminderung bei der Konstruktion neuer Flugzeuge und Kraftstoffersparnis- Reduced costs in the construction of new aircraft and fuel economy
  • – Umweltfreundlich durch wesentlich geringere Belastung mit Enteisungsflüssigkeit bei externer Enteisung- Environmentally friendly due to significantly lower stress with de-icing fluid in external de-icing

Politische Situation:Political situation:

  • Die IATA will bis 2020 25% Kraftstoff einsparenIATA wants to save 25% fuel by 2020
  • Bis 2050 sollen Emissionen um 50% gesenkt werdenBy 2050 emissions are to be reduced by 50%
  • Ab 2012 sollen nur nach 97% Emissionen erlaubt werden, 2013 nur noch 95%From 2012 only 97% of emissions are to be allowed, in 2013 only 95%
  • Ab 2013 sollen 15% Emissionszertifikate versteigert werden (Euro-Parlament)From 2013, 15% emission allowances will be auctioned (Euro-Parliament)

Vor diesem Hintergrund werden kraftstoffsparende und emissionsgeminderte Antriebssysteme immer wichtigerAgainst this background, fuel-efficient and emission-reduced drive systems are becoming increasingly important

Die vorliegende Erfindung entspricht genau diesen VorgabenThe present invention corresponds exactly to these specifications

Claims (3)

Vorrichtung zur Veränderung der Temperatur einer in großflächigem Auftrag auf ein Trägermaterial aufgebrachten elektrischen Widerstandsschicht aus einer Matrix aus Kohlenstoff Nano-Röhrchen (CNT) und weiteren definierten Zusätzen chemischer Natur zum Zweck der Erwärmung von Flugzeugbestandteilen, vornehmlich die Enteisung von Flugzeugtragflächen, Propeller und Lufteintrittskanälen an den Triebwerken unterschiedlicher Konstruktionsmerkmale, dadurch gekennzeichnet, dass eine geometrisch vorgegebene Trägerfläche aus GFK-Gewebe oder Aluminiumwabenblechen mit spezifisch gemischten und prozentual unterschiedlichen Bestandteilen einer CNT-Dispersion oder Matrix beschichtet, elektrisch kontaktiert und digital gesteuert und geregelt wird und einer Vereisung von Flugzeugtragflächen entgegen wirkt.Device for changing the temperature of an electrical resistive layer of a matrix of carbon nanotubes (CNT) and further defined additions of a chemical nature for the purpose of heating aircraft components, mainly the deicing of aircraft wings, propellers and air intake ducts on a carrier material in a large-area application Engines of different design features, characterized in that a geometrically predetermined carrier surface made of GRP fabric or aluminum honeycomb sheets coated with specifically mixed and percentage different components of a CNT dispersion or matrix, electrically contacted and digitally controlled and regulated and counteracts icing of aircraft wings. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass bei einer Anordnung der elektrisch leitenden Widerstandsschicht aus einer Kohlenstoff-Nano-Röhrchen Dispersion oder Matrix in einem Flugzeugtragflächen-Innenraum unterschiedlicher räumlicher Ausdehnung gemäß den Konstruktionsvorgaben des Herstellers durch elektrisch angeregte Molekularschwingung und Eigenschwingungsverhalten des Konstruktionsmaterials durch geeignete Auswahl eines infraroten Strahlungsspektrums die Erwärmung der vereisungsgefährteten Tragflächensegmente sowohl passiv als aktiv im Flugbetrieb bei Start und Landung als auch bei der Startvorbereitung erfolgt.A method according to claim 1, characterized in that in an arrangement of the electrically conductive resistance layer of a carbon nanotubes dispersion or matrix in an aircraft wing interior of different spatial extent according to the design specifications of the manufacturer by electrically excited molecular vibration and natural vibration behavior of the construction material by appropriate selection an infrared radiation spectrum, the heating of the icebound wing segments both passive and active in flight during takeoff and landing as well as during the launch preparation. Verfahren nach Anspruch 1 und 2, dadurch gekennzeichnet, dass zur Temperatur-Veränderung durch die elektrisch leitende Widerstandschicht aus Kohlenstoff-Nano-Röhrchen weitere Komponenten, bestehend aus Mineralien, Polymeren Compositen und Flüssigkeiten eine nanoskalige Dispersion bilden, die eine elektromagnetische definierte Welle mit einer Frequenz abstrahlt, die zu einem Resonanzverhalten der Tragflächeninnenseite und damit zu einer vorbestimmten Temperaturerhöhung führt, die, durch Beifügung von conduktiven Partikeln BaTiO3 einen positiven Temperaturkoeffizienten erzeugt, der selbstregelnd aufwendige Steuer- und Regeleinrichtungen überflüssig macht.A method according to claim 1 and 2, characterized in that the temperature change by the electrically conductive resistive layer of carbon nanotubes further components consisting of minerals, polymers composites and liquids form a nanoscale dispersion having an electromagnetic defined wave with a frequency radiates, which leads to a resonance behavior of the wing inside and thus to a predetermined increase in temperature, which generates by adding conductive particles BaTiO3 a positive temperature coefficient, which makes self-regulating complex control and regulation superfluous.
DE201110101142 2011-05-11 2011-05-11 Device for varying temperature of electrical resistance layer for de-icing aircraft component e.g. wing, has support surface made of glass fiber reinforced fabric or aluminum honeycomb plates and coated with carbon nano tube dispersion Withdrawn DE102011101142A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE201110101142 DE102011101142A1 (en) 2011-05-11 2011-05-11 Device for varying temperature of electrical resistance layer for de-icing aircraft component e.g. wing, has support surface made of glass fiber reinforced fabric or aluminum honeycomb plates and coated with carbon nano tube dispersion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE201110101142 DE102011101142A1 (en) 2011-05-11 2011-05-11 Device for varying temperature of electrical resistance layer for de-icing aircraft component e.g. wing, has support surface made of glass fiber reinforced fabric or aluminum honeycomb plates and coated with carbon nano tube dispersion

Publications (1)

Publication Number Publication Date
DE102011101142A1 true DE102011101142A1 (en) 2012-11-15

Family

ID=47070462

Family Applications (1)

Application Number Title Priority Date Filing Date
DE201110101142 Withdrawn DE102011101142A1 (en) 2011-05-11 2011-05-11 Device for varying temperature of electrical resistance layer for de-icing aircraft component e.g. wing, has support surface made of glass fiber reinforced fabric or aluminum honeycomb plates and coated with carbon nano tube dispersion

Country Status (1)

Country Link
DE (1) DE102011101142A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180257756A1 (en) * 2013-11-18 2018-09-13 Rohr, Inc. Virtual aerodynamic surface systems
CN110963045A (en) * 2019-12-24 2020-04-07 南京航空航天大学 Automatic anti-icing and deicing device for fuel wing of aircraft and working method of automatic anti-icing and deicing device

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180257756A1 (en) * 2013-11-18 2018-09-13 Rohr, Inc. Virtual aerodynamic surface systems
US11072413B2 (en) * 2013-11-18 2021-07-27 Rohr, Inc. Virtual aerodynamic surface systems
CN110963045A (en) * 2019-12-24 2020-04-07 南京航空航天大学 Automatic anti-icing and deicing device for fuel wing of aircraft and working method of automatic anti-icing and deicing device
CN110963045B (en) * 2019-12-24 2024-02-13 南京航空航天大学 Automatic deicing device for fuel wing of quoted aircraft and working method of automatic deicing device

Similar Documents

Publication Publication Date Title
EP2714516B1 (en) Composite structure having an ice protection device, and production method
US10457404B2 (en) Carbon nanotube anti-icing and de-icing means for aircraft
US9511562B2 (en) Nanoreinforced films and laminates for aerospace structures
Chu et al. FDTS‐modified SiO2/rGO wrinkled films with a micro‐nanoscale hierarchical structure and anti‐icing/deicing properties under condensation condition
CN110856290A (en) Graphene composite membrane for preventing and removing ice, composite material structural member and preparation method
US8662452B2 (en) Article with de-icing/anti-icing function
US10472977B2 (en) Erosion strip integrated with carbon allotrope-based deicing/ anti-icing elements
DE12702329T1 (en) Aircraft anti-icing, de-icing and heating configuration, integration and powering systems, as well as aerodynamic and complex surfaces
BR102014002158B1 (en) structural substrate for an aircraft structure and process for forming a structural substrate
EP3333080B1 (en) Carbon allotrope heater material with resistivity ranges suited for aircraft ice protection
DE102008006523A1 (en) Fiber composite component for an aircraft or spacecraft
US20140014776A1 (en) System containing an electric heating element and method for installation and use thereof
Müller et al. UAV icing: Development of an ice protection system for the propeller of a small UAV
DE102011101142A1 (en) Device for varying temperature of electrical resistance layer for de-icing aircraft component e.g. wing, has support surface made of glass fiber reinforced fabric or aluminum honeycomb plates and coated with carbon nano tube dispersion
Brampton et al. Actuation of bistable laminates by conductive polymer nanocomposites for use in thermal-mechanical aerosurface de-icing systems
Park Aircraft De-Icing System Using Thermal Conductive Fibers
CN104727945A (en) De-icing system of aircraft engine inlet
CN110723294A (en) Aircraft anti-icing system and method of making same
Gao et al. An experimental investigation on an electric-thermal strategy for wind turbines icing mitigation
Jingxin et al. Experimental Investigation of Super-hydrophobic/Electro-thermal Synergistically Anti-icing/De-icing Strategy in Ice Wind Tunnel.
Laroche Comparative evaluation of embedded heating elements as electrothermal ice protection systems for composite structures
Wang et al. A New Class of Carbon-Nanotube-Based, Self-Heating Superhydrophobic Coatings for UAV Icing Mitigation
Affonso et al. Carbon Nanotube (CNT) based Ice Protection System applied to a small aircraft
Idzikowski et al. Ground and in-fligh testing of cooling efficiency of turboprop engine compartment
Schutzeichel Multiphysical and multi scale modelling of composite materials for aircraft De-Icing

Legal Events

Date Code Title Description
R086 Non-binding declaration of licensing interest
R119 Application deemed withdrawn, or ip right lapsed, due to non-payment of renewal fee

Effective date: 20131203