The B. F. Goodrich Company

Goodrich Corporation

Other

James C Putt

Ronald W Phillips, Ii

James A Briscoe

Kevin L Leffel

Richard L Rauckhorst

Robert N Hohenshil

Michael John Giamati

David B Sweet

Tommy Maurice Wilson, Jr

John M Fisher

Alan John Fahrner

Michael M Kugelman

James Thomas Hindel

Terry Lee Sluss

Andrew Taylor

David M Ronyak

Kyle H Deiwert

Gary V Tenison

Michael J Dorsey

James Crist

Kevin L Lefeel

Alan J Fahrner

A de-icing assembly for a surface of an aircraft includes a carcass, seams, inflation passages, a manifold, and a reinforcement stitchline. The carcass includes a first layer, a second layer, and a carcass centerline. The seams are sewn into the carcass and join the first and second layers of the carcass together. The inflation passages are formed by the seams and are disposed between the first and second layers of the carcass. The manifold includes a width and a manifold centerline oriented approximately perpendicular to the carcass centerline and is fluidly connected to and is disposed beneath the carcass. The first reinforcement stitchline is sewn into the carcass adjacent to one of the plurality of seams and is disposed at a location on the carcass overlapping with the manifold. The first reinforcement stitchline is disposed approximately perpendicular to the manifold centerline and extends across the width of the manifold.

Sewn reinforcement features for prevention of stitch breakage in a pneumatic de-icer

A method of removing a delay-induced ice accumulation (e.g., an ice cap) from an airfoil's leading-edge region with a zoned electrothermal device. The method comprises delay-rectifying steps which are performed prior to routine-deicing steps. The delay-rectifying steps comprise continuously heating the parting strip (PS), continuously heating the upper fore zone (UF), and continuously heating the lower fore zone (LF). These steps efficiently and effectively remove the delay-induced ice accumulation, whereby routine deicing can be resumed.

Aircraft ice protection method

An aircraft fluid delivery device ( ) including a piston assembly ( ), a pilot assembly ( ), and a control assembly ( ). The control assembly ( ) includes non-contact proximity sensors (S , S ) that sense the position of the piston ( ) and a controller ( ) that controls the pilot assembly ( ), and thus the piston assembly ( ), based on information received from the sensors (S ,S ). Specifically, the controller ( ) energizes a solenoid ( ) to cause fluid to flow through the pilot assembly ( ) into a large portion of the piston chamber ( ) during the compression stroke of the piston ( ). When the solenoid ( ) is deenergized during the return stroke of the piston ( ), or when the delivery device is electrically turned off, an ejector ( ) in the pilot assembly ( ) generates a vacuum on the pressure side of the wide portion of the piston chamber ( ).

Aircraft fluid delivery device

A deicer is provided for breaking up and removing accumulated ice on an airfoil surface. The deicer includes a bondside surface that is bonded to the airfoil surface, a breezeside surface on which the ice will accumulate, and passage-defining surfaces therebetween. The passage-defining surfaces define a plurality of expansible and contractible inflation passages and include a moisture-impervious coating whereby moisture within the inflation passages will not be absorbed by the surfaces. The bondside, breezeside and passage-defining surfaces may be contained on a deicer panel and means may be provided for introducing inflation fluid to and evacuating inflation fluid from the passages to expand and contract the inflation passages to break up and remove the accumulated ice.

Deicer for aircraft

A deicer comprises a skin heating means immediately subjacent an outer skin overlying an apex of a leading edge, and a skin deflection means immediately subjacent the outer skin chordwise aft of the apex. The skin heating means prevents the formation of ice over the apex and the skin deflection means deflects the outer skin to expulse ice formed chordwise aft of the apex. A controller controls the heating and deflection cycles to minimize power consumption of the deicer.

Hybrid deicer with element sequence control

A deicer comprises a skin heating device immediately subjacent an outer skin overlying an apex of a leading edge, and a skin deflection device immediately subjacent the outer skin chordwise aft of the apex. The skin heating device prevents the formation of ice over the apex and the skin deflection device deflects the outer skin to expulse ice formed chordwise aft of the apex. A controller controls the heating and deflection cycles to minimize power consumption of the deicer.

Hybrid deicer with element sequence

A structural member having integral surface de-icing capability and method of manufacture are described. The structural member includes a non-metallic high tensile modulus fiber-reinforced matrix structural backing, thin force and displacement generation means, and a thin high tensile modulus outer skin bonded to said backing and said force and displacement generation means which is postioned between the backing and the skin. The force and displacement generation means may include one or more inflatable tubular members and/or electromagnetic apparatus. The structural member may be substituted for the aluminum alloy leading edge structural skin typically employed on modern aircraft.

Structural airfoil having integral expulsive system

An improved high pressure impulse valve includes a pilot section, an intermediate section, and an output section which are pressurized to approximately equilibrium with the inlet pressure during a load portion of the operating cycle and which cooperate to provide extremely rapid full opening of the output section to release fluid under pressure from an accumulator through an output section piston seat. The valve is particularly suitable for use in combination with pneumatic impulse separation systems such as those employed for deicing aircraft surfaces.

Pneumatic impulse valve and separation system

A rapid acting valve capable of delivering a high pressure impulse of compressible fluid has a pilot section, and an output section. The output section is pressurized to approximately equilibrium with the inlet pressure during the load portion of the operating cycle. During the dump portion of the operating cycle, the pilot section and output section cooperate to provide extremely rapid full opening of the output section to release fluid under pressure from an accumulator through an output section piston seat. The valve is particularly suitable for use in combination with pneumatic impulse separation systems such as those employed for deicing aircraft surfaces. A plurality of valves may be arranged in series such that dumping of the first tier valve initiates dumping of one or more second tier valves in the series each of which in turn initiates dumping of one or more third tier valves, and so forth until all valves in the series have been actuated, each by its preceding valve.

Cascaded pneumatic impulse separation system and valves therefor

A structural member having integral surface de-icing capability and method of manufacture are described. The structural member includes a non-metallic high tensile modulus fiber-reinforced matrix structural backing, thin force and displacement generation means, and a thin high tensile modulus outer skin bonded to said backing and said force and displacement generation means which is positioned between the backing and the skin. The force and displacement generation means may include one or more inflatable tubular members and/or electromagnetic apparatus. The structural member may be substituted for the aluminum alloy leading edge structural skin typically employed on modern aircraft.

A rapid acting valve capable of delivering a high pressure impulse of compressible fluid has a pilot section, an intermediate section and an output section which are pressurized to approximately equilibrium with the inlet pressure during the load portion of the operating cycle and which cooperate to provide extremely rapid full opening of the output section to release fluid uner pressure from an accumulator through an output section piston seat. The valve is particularly suitable for use in combination with pneumatic impulse separation systems such as those employed for deicing aircraft surfaces.

An airfoil deicer and method for deicing an airfoil wherein the deicer has an outer skin having an elevated modulus of elasticity and a means for introducing a small deflection into the outer skin thereby creating substantial chord-wise tension in the outer skin, the deflection being induced in less than 0.250 seconds. In the method of deicing, the deflection is induced periodically and being completed within a time span of about 0.250 seconds to remove accumulations of ice as thin as 0.06 centimeters.

Method and apparatus for deicing a leading edge

A de-icer for de-icing those ice accreting surfaces of a skin formed of a material having a substantially elevated modulus, wherein the de-icer is positioned between a support surface and a surface of the skin obverse to the ice accreting surface and inflated to produce a deformation in the skin sufficient to detach and dislodge accumulations of ice on the ice accreting surface but insufficient to exceed an endurance limit for the material from which the skin is formed. The invention finds use in de-icing aircraft surfaces such as wings, tail surfaces, propellers, rotors such as rotating wings, tail rotors and nose cones.

De-icer

A three-stage compressor wherein the housing proper has a central bore with two adjacent bores that are co-axial therewith. A first piston is cooperative with the central bore to define a first stage compression chamber. A second piston smaller than the first piston but integral therewith is received by one of the adjacent bores to define a second stage compression chamber that receives its pressurized air from the first chamber. A third piston smaller than the second piston is received by the remaining one of the adjacent bores to define a third stage compression chamber that receives its pressurized air from the second chamber for further compression.

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Doylestown, OH, United States of America

James C Putt