A system for an aircraft includes a first fluid circuit extending from a first end to a second end, and a network comprising a plurality of networked heater assemblies disposed along the first fluid circuit between the first end and the second end. Each of the networked heater assemblies includes at least one temperature sensor, a heater element, and a local controller. The at least one temperature sensor is in communication with the first fluid circuit for periodically measuring a temperature in the first fluid circuit and generating a corresponding local temperature signal. The heater assembly selectively applies heat to the first fluid circuit based on the local temperature signal or another temperature signal on the network. The local controller receives the local temperature signal or another networked temperature signal and operates the heater assembly in response thereto to maintain the local temperature signal above a predetermined threshold.

The invention is directed to an article with a liquid-impregnated surface, the surface having a matrix of features thereupon, spaced sufficiently close to stably contain a liquid therebetween or therewithin, and preferable also a thin film thereupon. The surface provides the article with advantageous non-wetting properties. Compared to previous non-wetting surfaces, which include a gas (e.g., air) entrained within surface textures, these liquid-impregnated surfaces are resistant to impalement and frost formation, and are therefore more robust.

The invention is directed to an article with a liquid-impregnated surface, the surface having a matrix of features thereupon, spaced sufficiently close to stably contain a liquid therebetween or therewithin, and preferable also a thin film thereupon. The surface provides the article with advantageous non-wetting properties. Compared to previous non-wetting surfaces, which include a gas (e.g., air) entrained within surface textures, these liquid-impregnated surfaces are resistant to impalement and frost formation, and are therefore more robust.

The invention relates to an aircraft provided with at least one piece of aeronautic equipment fastened to the outside skin of the aircraft and a heater for heating the piece of aeronautic equipment. The heater is in the form of a thermodynamic closed circuit loop circulating heat-transfer fluid and including an evaporator and a heat source located inside the aircraft and a condenser located in the piece of aeronautic equipment or an appendage thereto. Fasteners in the form of tubular tabs include tubular channels for circulating the heat-transfer fluid.

The invention relates to an aircraft provided with at least one piece of aeronautic equipment fastened to the outside skin of the aircraft and a heater for heating the piece of aeronautic equipment. The heater is in the form of a thermodynamic closed circuit loop circulating heat-transfer fluid and including an evaporator and a heat source located inside the aircraft and a condenser located in the piece of aeronautic equipment or an appendage thereto. Fasteners in the form of tubular tabs include tubular channels for circulating the heat-transfer fluid.

A system for an aircraft includes a first fluid circuit extending from a first end to a second end, and a network comprising a plurality of networked heater assemblies disposed along the first fluid circuit between the first end and the second end. Each of the networked heater assemblies includes at least one temperature sensor, a heater element, and a local controller. The at least one temperature sensor is in communication with the first fluid circuit for periodically measuring a temperature in the first fluid circuit and generating a corresponding local temperature signal. The heater assembly selectively applies heat to the first fluid circuit based on the local temperature signal or another temperature signal on the network. The local controller receives the local temperature signal or another networked temperature signal and operates the heater assembly in response thereto to maintain the local temperature signal above a predetermined threshold.

A system comprises a heat source. The system also comprises a bladder comprising opposing thin-walled sheets and a fluid flow conduit defined between the opposing thin-walled sheets. The fluid flow conduit comprises an inlet and an outlet. The system further comprises a first fluid line coupled to the heat source and the inlet of the bladder. The system additionally comprises a second fluid line coupled to the heat source and the outlet of the bladder. The system also comprises fluid flowable through the first fluid line from the heat source to the inlet, from the inlet through the fluid flow conduit to the outlet, and through the second fluid line from the outlet to the heat source.

Disclosed is an aqueous deicing and/or anti-icing composition, and the use thereof on areas in need of deicing and/or anti-icing, exhibiting substantially improved corrosion inhibition, conductivity inhibition and/or hydrogen embrittlement inhibition. Said composition comprises 40-60% by weight of at least one alkali metal carboxylate, 0.1-0.5% by weight of benzoic acid and/or at least one alkali metal benzoate, 0.05-0.5% by weight of at least one alkali metal phosphate, 0.005-0.05% by weight of at least one alkali metal metasilicate, and 0.01-0.15% by weight of succinic acid and/or at least one alkali metal succinate. Balance to 100% by weight is water and said composition is pH adjusted to pH 9-12 by addition of at least one alkali metal hydroxide and/or carbonate. Disclosed is also a method of obtaining corrosion inhibition, conductivity inhibition and/or hydrogen embrittlement inhibition by addition of 0.01-0.15% by weight of succinic acid and/or at least one alkali metal succinate to an aqueous deicing and/or anti-icing composition.

A device for deicing a wall of an aircraft, comprising a closed circuit. The closed circuit comprises at least one condenser, positioned in the environment of the wall that is to be deiced, and in which a heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, at least one evaporator positioned in the environment of a heat source sited remotely with respect to the wall, and in which the heat-transfer fluid evaporates, absorbing energy in the form of latent heat coming from the heat source. At least part of the closed circuit is facing, in contact with, or positioned in, the wall that is to be deiced, being made of a material transparent to electromagnetic fields.

A device for deicing a wall of an aircraft, comprising a closed circuit. The closed circuit comprises at least one condenser, positioned in the environment of the wall that is to be deiced, and in which a heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, at least one evaporator positioned in the environment of a heat source sited remotely with respect to the wall, and in which the heat-transfer fluid evaporates, absorbing energy in the form of latent heat coming from the heat source. At least part of the closed circuit is facing, in contact with, or positioned in, the wall that is to be deiced, being made of a material transparent to electromagnetic fields.