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WO1994026590A1 - Systeme anti-glace monte sur une aile d'avion - Google Patents

Systeme anti-glace monte sur une aile d'avion Download PDF

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Publication number
WO1994026590A1
WO1994026590A1 PCT/US1994/005167 US9405167W WO9426590A1 WO 1994026590 A1 WO1994026590 A1 WO 1994026590A1 US 9405167 W US9405167 W US 9405167W WO 9426590 A1 WO9426590 A1 WO 9426590A1
Authority
WO
WIPO (PCT)
Prior art keywords
heating device
layer
wing
aircraft
heater
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/US1994/005167
Other languages
English (en)
Inventor
George H. Grauer
David C. Wensley
Robert Erik Bylin
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.)
TECHNOLOGY DYNAMICS GROUP Inc
Original Assignee
TECHNOLOGY DYNAMICS GROUP Inc
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 TECHNOLOGY DYNAMICS GROUP Inc filed Critical TECHNOLOGY DYNAMICS GROUP Inc
Priority to AU68295/94A priority Critical patent/AU6829594A/en
Publication of WO1994026590A1 publication Critical patent/WO1994026590A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating

Definitions

  • the present invention is directed to an economical device for preventing formation of ice on aircraft wings and other aerodynamic surfaces.
  • Ice is a constant threat to the safety of aircraft operations and passengers. Numerous aircraft accidents have been attributed to ice, and aircraft designers are constantly in search of improved protection from this threat.
  • Ice on aerodynamic surfaces can cause roughness, increasing drag and decreasing lift, possibly to the point that the aircraft stalls. Ice formation may occur in many locations, including the top and the underside of wing surfaces. This happened on March 12, 1992 when an F-28 took off from La Guardia airport in New York City with an excess accumulation of ice. The plane could not develop sufficient lift and plunged into the icy East River. Twenty-seven of the 51 persons on board the flight died in this accident. Accumulated ice may shed or fall off during takeoff or flight and strike parts of the aircraft. This foreign object damage (FOD) can damage aircraft. This is a particular problem in certain aircraft configurations. If a jet engine is in a slip stream downstream of accumulated ice, there is a significant chance of damage to the engine at some time.
  • FOD foreign object damage
  • Ice build up has led to many devastating accidents and even incidents which cause aircraft damage but no deaths.
  • an SAS MD-80 took off in February 1992 and ice shedding from the wing surfaces was ingested by both engines, causing a flame out and complete loss of engine power. The plane crashed during takeoff into some trees, then skidded and ultimately broke in half. Fortunately, no lives were lost in this incident. Icing has also caused loss of life in many instances. This happened in January 1992 when a Boeing 737 took off in a snowstorm from runway 36 of Washington National Airport, struck the 14th Street Bridge and then plunged into the Potomac River. Seventy-four of 769 persons on board plus four others on the bridge lost their lives.
  • Ice can form on an aircraft on the ground if the right matrix or combination of conditions is present.
  • Moisture is often present in the form of rain, hail, snow, or freezing rain, fog or even humidity. Wind conditions may affect icing, particularly on the ground - moving air tends to increase the amount of ice formation.
  • Some aircraft designs result in certain areas of an aircraft potentially acting as a cold thermal reservoir.
  • the aircraft's recent operating history may affect the temperature of such a cold reservoir, and current environmental factors may influence the tendency to form ice on the aircraft.
  • the fuel in a wing can be an important thermal reservoir.
  • a long flight, e.g. more than two hours at altitude, tends to lower fuel temperatures. Jet fuel temperatures can drop below -35° F and still be useable but jet fuel starts to become sludge at -45° F. This freezing point can be lowered with additives if needed.
  • the cold soaked fuel remaining in tanks may provide a significant cold thermal mass.
  • Ice can build up to a thickness of more than one inch over large areas of a wing surface. This region is generally coincident with a large thermal mass, e.g. on wings over or under fuel tanks containing cold-soaked fuel. As discussed above, this is a particular problem with MD-80 aircraft.
  • Residual glycol may be shed as the aircraft takes off, resulting in distribution of glycol over the area under the flight path. This can result in a serious environmental contamination.
  • Miami, for example, has a very high water table and does not allow use of any glycol, yet the humid environment can cause icing problems, even on warm days.
  • the present invention provides a low profile heater coupled with a good insulator mounted directly on the aircraft skin on an area of concern. It is especially helpful when mounted on an aerodynamic surface.
  • the present invention has a low aerodynamic profile, resulting in only a 0.004% increase in drag.
  • the new device is mounted over the aluminum wing panel, over a wing tank which sometimes contains cold soaked fuel.
  • Fasteners and/or a sealant on the wing panel attaches the insulated heating assembly to the aircraft wing.
  • the heating device itself consists of a lower metal skin bonded to an insulator layer which in turn is bonded to a central metal skin, a heater element assembly, and an upper metal skin. Each element of the assembly may be made from a variety of materials.
  • the preferred metal skin is aluminum, the preferred insulator is a honeycomb.
  • the layers are preferably bonded with a structural adhesive.
  • Figure 1 illustrates an aircraft and areas of an airframe which may require ice protection.
  • Figure 2 illustrates a jet aircraft and potentially sensitive ice-forming areas.
  • Figures 3A, 3B and 3C illustrate cross-sections of prior electric heaters.
  • Figure 4 illustrates the heating assembly of the present invention.
  • the new device prevents ice formation on cold aircraft components, and to some extent can melt existing ice on the components.
  • Prior art devices require too much power and add too much aerodynamic drag to be commercially satisfactory.
  • Figure 1 illustrates an aircraft and areas of an airframe which may require ice protection.
  • aircraft 10 includes several sensitive areas: wing leading edges 11; propellers 12; windshield 13; radome 14; essential instruments 15 (which may be positioned in a variety of locations); auxiliary air inlets 16; engine air inlets 17; balance horns 18 on wing or tail tips, antenna 19; and empennage leading edges 20. Ice may form on any of these areas, particularly during flight, but also on the ground and can dangerously impair aircraft performance.
  • Ice may also accumulate over cold thermal masses, such as fuel stored in wing fuel tanks.
  • aircraft 25 has wings 26 with fuel tanks 28 (inside wing, not shown) near root 27 of wing 26. If ice accumulates over a fuel tank 28, it may be loosened or shed at any time, including during takeoff, and may be sucked directly into the intake of an engine 24.
  • a standard NACA heater construction requires 22 watts per square inch and can be bonded to an aerodynamic surface.
  • Aluminum skin 30 is covered by a
  • FIG. 3B illustrates a more efficient system, a typical heater construction with a metal overshoe, which requires 18-22 watts per square inch.
  • This construction typically is laminated to a basic aircraft structure. In this heater, 25 mil (0.635 mm) aluminum skin 30 is covered by 12 mil insulation 36, 3 mil ribbon heater 37, 12 mil insulation 38, and 5 mil (0.127 mm) stainless steel layer 39.
  • Another typical surface heater molded as a structural member requires still less energy (16-20 watts per square inch).
  • one or more 10 mil (0.254 mm) layers 40 of epoxy-impregnated glass cloth are covered by 2 mil (0.051 mm) expanded metal heating element 41, then 8 mil (0.203 mm) outer layer 42 (which may be two 4 mil (0.102 mm) layers) of epoxy- impregnated glass cloth, covered by 5 mil stainless steel layer 43.
  • the new device offers significant improvements over old devices. It is mounted over an aluminum wing panel, preferably over a wing tank which may contain cold soaked fuel.
  • One particularly useful location is on each wing over the bulkhead between the center fuel tank and the outboard fuel tank on an MD-80. Heating an area of about forty sq. feet (3.7 m 2 ) on each wing provides satisfactory de-icing. The heating assembly should not be too thick (high) or it will adversely impact aerodynamic performance.
  • a preferred embodiment has overall thickness (height) of 0.128" (3.18 mm).
  • a particularly useful range is 0.010"-.250" (0.025 cm - 0.635 cm).
  • the heating assembly consists of a lower metal skin bonded to an insulator which in turn is bonded to a central metal skin, a heater element, and an upper metal skin.
  • Each element of the assembly may be made from a variety of materials.
  • the preferred metal skin is aluminum, the preferred insulator is a honeycomb.
  • the layers are preferably bonded with a structural adhesive.
  • the heating assembly is finished on all edges with an aerodynamic extrusion to provide an aerodynamic profile and smooth transition from the wing surface to the heating assembly. This minimizes drag so air flowing over the wing surface is essentially undisturbed when passing from the wing panel to the mounted heating assembly.
  • the entire assembly is designed so that wing loading is unchanged when the heating assembly is secured to the wing.
  • sealant 52 between wing skin or panel 51 and heating assembly 70 may be any of a number of sealants used commercially in the aircraft industry.
  • One preferred sealant is PR-1422, formerly known as PRC-1422, available from Products Research & Chemical Corporation, 5454 San Fernando Rd., PO Box 1800, Glendale, CA 91209. This material is ductile down to about -65° F and up to 250° F, and widely used on aircraft, e.g. sealing fuel tanks. In prior art heating devices, composites tend to absorb water, which can lead to potential corrosion problems in the skin. Sealant 52 provides corrosion inhibition, useful in case any moisture is condensed or trapped between heating assembly 70 and the surface of wing panel 51.
  • the structural adhesive used for adhesive layers 54, 56, 58 and 60 should inhibit corrosion and provide good mechanical properties with low water absorption properties.
  • the structural adhesive transfers loads from one layer to the next, and provides shear strength between different materials. This is particularly important when materials with different coefficients of thermal expansion are held at different temperatures.
  • a preferred implementation uses AF-163-2K, 2U and 2M, available from 3M, which are often used for bonding structural layers of composite materials.
  • Lower metal layer or skin 53, center metal skin 57 and upper metal skin 61 may be made of a number of materials. Standard aircraft aluminum is a well known and proven material that provides durability and good impact strength at a reasonable cost. In a preferred embodiment, the thickness of each of lower skin 53, center skin 57, and upper skin 61 is 12 mils (0.305 mm). Upper skin 61 should be thick enough to resist impact damage, for example if a tool is dropped on the surface, but it is desireable to make the material as thin as possible. The skin is an effective conductor of thermal energy, acting as a dead thermal short for thermal conductivity, so the thickness of each skin should be minimized. The metal skins, particularly upper skin 61, also provide lightning protection by passing electrical current to the wing structure.
  • the entire heating assembly 70 is electrically bonded to the wing, that is, it doesn't change the electrical characteristics of the wing.
  • Many other metals were studied for use as a skin but were more costly. In general, the material should have a low coefficient of thermal expansion.
  • Other useful materials include titanium, stainless and other steels, graphite-epoxy composites, other epoxies, thermoplastic composites and other materials known to one skilled in the art.
  • Insulating layer 55 should be very light weight with good insulating properties, yet provide some structural rigidity.
  • insulating layer 55 is a honeycomb material.
  • Other insulators also useful as structural materials include syntactic type foams of which closed cell polyurethane foams are candidates. A vacuum might be used, but no useful systems are currently known. Glass or plastic bubbles might also be incorporated in honeycomb to provide insulation.
  • One useful honeycomb is Nomex, from DuPont, with a 1/8" (0.318 cm) cell size and "9 lb" (9 lb/ft 3 ) density (weight per cubic foot, 144.17 kg/m 3 ).
  • This cell size provides a good balance of insulating and structural properties. A larger cell size provides better insulation but lower shear strength, while a small cell size provides the opposite properties.
  • Cell size refers to the dimension of each honeycomb cell, with 1/8" the smallest currently available cell size from DuPont.
  • the cells are formed from paper or aramid fiber, then impregnated phenolic resin.
  • the cells in the finished honeycomb are hollow, which provides insulating properties. A density of 6 lb (96.11 kg/m 3 ) is useable but higher densities are preferable.
  • Blocks of honeycomb can be cut to varying thicknesses.
  • a thickness of 60 mil (0.15 cm) to which a 0.6 W/in 2 (930 W/m 3 ) heat flux is applied to one surface provides a 50° F (27.8° C) thermal gradient, with the honeycomb yielding a thermal conductivity of 0.104 BTU/hr ft °F (0.06 W/m °K).
  • One skilled in the art may choose to use 20-200 mil (0.051 - 0.51 cm) thick honeycomb. Thicker slabs would be useful but the overall dimension of heating assembly 70 is limited by other constraints, such as aerodynamic drag.
  • Heater element 59 can be made from a variety of materials well known in the art.
  • heater element 59 is etched foil (30% copper, 70% nickel) surrounded by epoxy glass dielectric skins.
  • epoxy glass dielectric skins Such an element is available from Tayco Engineering, Inc., 10874 Hope St., Cypress, CA 90630.
  • the epoxy skins provide electric insulation and some incidental thermal insulation.
  • Other suitable metals can be used for the heater, and other dielectric materials can be used in place of the epoxy material.
  • the epoxy glass provides good impact resistance and structural strength.
  • a preferred embodiment of the heater has the capacity to deliver 10 W/in 2 (15.5 kW/m 2 ) although only 0.6 W/in 2 (930 W/m 2 ) is required.
  • the heater element is approximately the size of the heater assembly, 40 ft 2 (3.7 m 2 ).
  • Heater assembly 70 is secured over a fuel tank (not shown) containing cold soaked fuel 50 to wing panel 51 by sealant 52 and mechanical fasteners.
  • the assembly can be installed using conventional techniques well known in the industry. Electrical power leads and resistive temperature device (RTD) sensors are positioned throughout the assembly and routed through slots cut in the honeycomb, then pulled down through an access panel, preferably an existing access panel already designed into the wing. The wires are routed along the trailing edge side of the rear spar of the wing and into the fuselage where the heater control units are mounted in the aft cargo pit, adjacent to the access door.
  • a heater control unit provides closed loop heat control, turning the heater on and off as needed to maintain a preset temperature.
  • the preset temperature is set to 80° F (26.7° C).
  • Cockpit controls include only an indicator light and an on-off switch to activate the unit.
  • Alternative switches or electrical lockouts detect whether there is weight on the wheels so that the heating assembly cannot be activated when the plane is not on the ground.
  • Other sensors detect throttle position to turn off the heating assembly when the throttles are advanced past a certain minimum position, as in takeoff.
  • a preferred embodiment requires watt densities of only 0.6 Watts per square inch (930 W/m 2 ), the lowest watt density that has been used in previous devices for anti-icing or de-icing.
  • the insulating layer In general, the better the insulator, the less power is required. Other insulation configurations should lead to still lower watt densities. The improved efficiency of the new device does not prevent using higher power, and higher watt densities let the heating assembly operate under harsher conditions. Under extreme conditions, with low temperatures or large temperature gradients, die preferred embodiment can handle 5 W/sq. in.
  • the current device can prevent ice formation in 10° F (-12.2° C) ambient temperatures with fuel temperature as low as -24° C (-11° F) for winds from 0 to 30 mph (0 to 13.4 m/s).

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)

Abstract

Un dispositif de réchauffement à profil bas (11) associé à un isolant (36) est monté directement sur la carlingue de l'avion (30), de préférence, sur une surface aérodynamique. Le dispositif de réchauffement (11) présente un profil aérodynamique bas, ce qui ne provoque que 0,004 % d'augmentation de traînée. Le dispositif de réchauffement (11) peut se monter au-dessus d'un panneau d'aile en aluminium (30), en particulier, au-dessus d'un réservoir d'aile qui contient parfois du carburant à basse température. Un matériau d'étanchéité (52) sur le panneau d'aile fixe l'ensemble de réchauffement isolé (70). Le dispositif de réchauffement lui-même est constitué par une plaque inférieure de métal (53) adhérant à une couche isolante (55) qui adhère à son tour à une plaque centrale de métal (57), par un ensemble d'éléments de réchauffement (59), ainsi que par une plaque supérieure de métal (61). Chaque élément de l'ensemble peut être fabriqué à partir d'une pluralité de matériaux. Le métal préféré est l'aluminium et l'isolant préféré est une structure alvéolée. On fait adhérer les couches, de préférence, au moyen d'un adhésif structurel.
PCT/US1994/005167 1993-05-11 1994-05-10 Systeme anti-glace monte sur une aile d'avion Ceased WO1994026590A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU68295/94A AU6829594A (en) 1993-05-11 1994-05-10 Overwing anti-ice system

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US6003093A 1993-05-11 1993-05-11
US08/060,030 1993-05-11

Publications (1)

Publication Number Publication Date
WO1994026590A1 true WO1994026590A1 (fr) 1994-11-24

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WO (1) WO1994026590A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2298114A (en) * 1995-02-15 1996-08-21 Dunlop Ltd Ice protection assembly
WO1999015405A1 (fr) * 1997-09-22 1999-04-01 Northcoast Technologies Systeme degivreur et anti-givre et procede pour surfaces d'avions
US6237874B1 (en) 1997-09-22 2001-05-29 Northcoast Technologies Zoned aircraft de-icing system and method
US6279856B1 (en) 1997-09-22 2001-08-28 Northcoast Technologies Aircraft de-icing system
GB2438389A (en) * 2006-05-23 2007-11-28 Gkn Aerospace Transparency Sys Heating system for leading edge of aircraft
EP3162711A1 (fr) * 2015-10-30 2017-05-03 ITT Manufacturing Enterprises LLC Ensembles de bord d'attaque métalliques et composites

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2762897A (en) * 1951-06-28 1956-09-11 Lockheed Aircraft Corp De-icing means for aircraft and the like
US3178560A (en) * 1960-11-18 1965-04-13 Dowty Rotol Ltd Electrical de-icing devices
US3204084A (en) * 1963-05-07 1965-08-31 Gen Dynamics Corp Electrical deicer
US3697728A (en) * 1968-12-13 1972-10-10 Air Plastic Service Gmbh Heating devices
US4942078A (en) * 1988-09-30 1990-07-17 Rockwell International Corporation Electrically heated structural composite and method of its manufacture
US5143325A (en) * 1991-01-03 1992-09-01 Electroimpact, Inc. Electromagnetic repulsion system for removing contaminants such as ice from the surfaces of aircraft and other objects

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2762897A (en) * 1951-06-28 1956-09-11 Lockheed Aircraft Corp De-icing means for aircraft and the like
US3178560A (en) * 1960-11-18 1965-04-13 Dowty Rotol Ltd Electrical de-icing devices
US3204084A (en) * 1963-05-07 1965-08-31 Gen Dynamics Corp Electrical deicer
US3697728A (en) * 1968-12-13 1972-10-10 Air Plastic Service Gmbh Heating devices
US4942078A (en) * 1988-09-30 1990-07-17 Rockwell International Corporation Electrically heated structural composite and method of its manufacture
US5143325A (en) * 1991-01-03 1992-09-01 Electroimpact, Inc. Electromagnetic repulsion system for removing contaminants such as ice from the surfaces of aircraft and other objects
US5143325B1 (en) * 1991-01-03 2000-09-05 Electroimpact Inc Electromagnetic repulsion system for removing contaminants such as ice from the surface of aircraft and other objects

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2298114A (en) * 1995-02-15 1996-08-21 Dunlop Ltd Ice protection assembly
GB2298114B (en) * 1995-02-15 1997-10-08 Dunlop Ltd Ice protection device
US5765779A (en) * 1995-02-15 1998-06-16 Dunlop Limited Ice protection device
WO1999015405A1 (fr) * 1997-09-22 1999-04-01 Northcoast Technologies Systeme degivreur et anti-givre et procede pour surfaces d'avions
US5934617A (en) * 1997-09-22 1999-08-10 Northcoast Technologies De-ice and anti-ice system and method for aircraft surfaces
US6194685B1 (en) 1997-09-22 2001-02-27 Northcoast Technologies De-ice and anti-ice system and method for aircraft surfaces
US6237874B1 (en) 1997-09-22 2001-05-29 Northcoast Technologies Zoned aircraft de-icing system and method
US6279856B1 (en) 1997-09-22 2001-08-28 Northcoast Technologies Aircraft de-icing system
US6330986B1 (en) 1997-09-22 2001-12-18 Northcoast Technologies Aircraft de-icing system
GB2438389A (en) * 2006-05-23 2007-11-28 Gkn Aerospace Transparency Sys Heating system for leading edge of aircraft
EP3162711A1 (fr) * 2015-10-30 2017-05-03 ITT Manufacturing Enterprises LLC Ensembles de bord d'attaque métalliques et composites
US10321519B2 (en) 2015-10-30 2019-06-11 Itt Manufacturing Enterprises Llc Metal and composite leading edge assemblies
US11310872B2 (en) 2015-10-30 2022-04-19 Itt Manufacturing Enterprises Llc Metal and composite leading edge assemblies

Also Published As

Publication number Publication date
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