Abstract: A de-icing assembly includes an aircraft with an airfoil. A de-icer is disposed on a leading edge of the airfoil. A tab extends from the de-icer in an aft direction from an aft edge of the de-icer. The de-icer and the tab are adhesively attached onto an outer skin of the airfoil. A supercooled large droplet sensor is built into the tab. The supercooled large droplet sensor is positioned in a location aft of the aft edge of the de-icer.

Abstract: 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 (UF1), and continuously heating the lower fore zone (LF1). These steps efficiently and effectively remove the delay-induced ice accumulation, whereby routine deicing can be resumed.

Abstract: 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 (UF1), and continuously heating the lower fore zone (LF1). These steps efficiently and effectively remove the delay-induced ice accumulation, whereby routine deicing can be resumed.

Abstract: An aircraft fluid delivery device (10) including a piston assembly (20), a pilot assembly (22), and a control assembly (24). The control assembly (24) includes non-contact proximity sensors (S1, S2) that sense the position of the piston (28) and a controller (80) that controls the pilot assembly (22), and thus the piston assembly (20), based on information received from the sensors (S1,S2). Specifically, the controller (80) energizes a solenoid (72) to cause fluid to flow through the pilot assembly (22) into a large portion of the piston chamber (30) during the compression stroke of the piston (28). When the solenoid (72) is deenergized during the return stroke of the piston (28), or when the delivery device is electrically turned off, an ejector (60) in the pilot assembly (22) generates a vacuum on the pressure side of the wide portion of the piston chamber (30).

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A chattering valve for use in a pulse pneumatic de-icer.

Abstract: 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.

Abstract: A valve having a valve housing for mounting on a high pressure fluid container. A cartridge is mounted in a fluid conduit in the valve housing leading to the fluid container. A metallic disc is crushed by the cartridge against a valve seat in the conduit to provide a reliable lasting seal. Opening of the valve is provided by releasing a trigger pin connected to a latch in the cartridge for removing a support from a portion of the disc permitting it to rupture under the high pressure and communicating the high pressure gas to a pressure regulator chamber in cross configuration with the valve conduit in the valve housing. A pressure regulator member in the chamber controls the size of a discharge orifice for lowering the pressure and introducing the gas into an inflatable body. Filling of the high pressure fluid container may be done by introducing high pressure fluid into the regulator for passage into the fluid conduit of the valve with the cartridge carrying the disc spaced from the valve seat.