A de-icing assembly for a surface of an aircraft includes a carcass with a first layer and a second layer, a plurality of seams sewn into the carcass, and a bonded region. The plurality of seams join the first and second layers of the carcass together. Each of the plurality of seams comprises two or more stitchlines. The bonded region is disposed between the two or more stitchlines and seals a portion of the first layer of the carcass to a portion of the second layer of the carcass.

A pneumatic de-icer includes an externally facing weathering surface that includes a low-friction additive in the rubber mixture. The low-friction additive has a coefficient of friction of 0.10 or less, and promotes ice shedding because the additive has low ice adhesion compared to typical rubber materials used for pneumatic de-icer assemblies.

A pneumatic deicer includes a base layer, a forming layer, a first chamber, and a first sensor. The base layer has an inlet, a first side, and a second side. The forming layer is connected to the base layer along at least two seams and has inner side and an outer side with the outer side being distant from the base layer. The first chamber is formed between the base layer and the forming layer and configured to be inflated by air passing into the first chamber through the inlet in the base layer. The first sensor is situated within the first chamber.

A pneumatic deicer assembly includes a first stretch fabric with a first edge opposite a second edge. The first edge is positioned proximate the second edge such that the first stretch fabric forms a tube. A non-stretch fabric covers a seam formed between the first edge and the second edge of the first stretch fabric. A second stretch fabric covers the non-stretch fabric and a portion of the first stretch fabric.

An aircraft turbojet engine low-pressure compressor or booster, comprising an inlet structure de-iced by a pressurized hot fluid circulation coming from the high-pressure compressor. The de-icing structure comprises a deformable membrane through the thickness of which the pressurized fluid circulation passes. When there is a build-up of ice on the membrane, the pressurized fluid circulation is blocked, resulting in its pressure deforming the membrane in such a manner as to crack the build-up of ice.

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.

Examples described herein provide a computer-implemented method that includes receiving static data about an aircraft. The method further includes receiving dynamic data about flight conditions for a flight of the aircraft. The method further includes determining, based on the static data and the dynamic data, an amount of air pressure and a volumetric air flow to apply from an electric pump to a deicing device. The method further includes controlling the electric pump to cause the electric pump to apply the amount of air pressure and the volumetric air flow to the deicing device.

The present disclosure provides for methodologies for height measurement in pneumatic deicer boots for aircraft, and related models, systems and methods of use. More particularly, the present disclosure provides for methods, models, systems and applications to detect the life or failure of pneumatic deicer boots for aircraft. A method for detecting the life or failure of pneumatic deicer boots for aircraft is provided.

The present disclosure provides for pneumatic deicer boot assemblies, and related methods of fabrication and use. More particularly, the present disclosure provides for bartack stitched pneumatic deicer boot assemblies for aircraft or the like, with the bartack stitched pneumatic deicer boot assemblies having an inflatable carcass formed by two layers (e.g., a stretchable layer and a non-stretchable layer) stitched together using bartack stitches.

Ice may form along the leading edge of an aircraft wing or horizontal and vertical stabilizers. A pneumatic deicer system may be configured to inflate and dislodge ice along the leading edge of lift and control surfaces. The pneumatic deicer system may comprise a laser welded deicing boot attached to the leading edge. The compressed air can be directed to the deicing boot, inflating the deicing boot along inflatable tubes formed by laser welds, which can crack and dislodge the ice. A method of manufacturing a laser welded pneumatic deicer boot is also disclosed.