Abstract: An airfoil device (10) for attachment to the wing (14) of an aircraft (12). The airfoil device (10) has a chamber (30) which is inflatable to provide a lift-enhancing airfoil geometry to the wing (14) and other chambers (32) which are inflatable to provide deicing forces to remove ice accumulation on the wing (14). When installed on the wing (14), the airfoil device (10) closely conforms to the wing's airfoil geometry (e.g., low camber, sharp leading edge) when the lift-enhancing chamber (30) and the deicing chambers (32) are in a deflated condition. The lift-enhancing chamber (30) can be inflated during take-off and landing to provide a high camber and less sharp airfoil geometry. If ice accumulates on the wing (14) during high speed flight, the deicing chambers (32) can be repeatedly inflated/deflated for ice removal purposes.

Abstract: A de-icer module especially adapted for installment on the inner surface of an airfoil is provided. The structural member has an outer surface upon which ice accumulates. The de-icer module comprises a support sheet delimited by a support area, a single pancake shaped separation means for developing a transient electro-mechanical separation force between the support sheet and the structural member distributed over the support area, the separation means being adjacent the support sheet, attachment means for connecting the support sheet to the inner surface of the structural member with the support sheet in close proximity to the inner surface of the structural member and the separation means sandwiched between the support sheet and the structural member. The invention provides a simplified mounting arrangement.

Abstract: A deicer for attachment to an airfoil substructure includes a segmented outer shell, with adjacent segments being decoupled from one another utilizing elastomeric decoupling members. The outer edges of the outer periphery shell segments are likewise decoupled from the airfoil structure utilizing elastomeric decoupling members. Each segment of the deicer is deflected by a respective deflection means which are provided energy from a controller.

Abstract: Apparatus and method for providing a pneumatic de-icer structure having a replaceable environment resistant surface are disclosed. A separable adhesive impermanently bonds the environment resistant surface to the de-icer structure. The environment resistant layer can be repeatedly replaced until the cycle life of the pneumatic de-icer structure is depleted.

Abstract: A pneumatic deicing system for deicing an airfoil includes a flexible deicing member having inflatable tube-like passages provided therein for being inflated with a pressurized fluid, wherein the deicing member is bonded to a shell having a snap type connector for mating with another connector either on the airfoil or integrated into another part of the shell. An air connector extends through the shell and is utilized for putting the deicing member in fluid connection with the fluid source. Radar absorptive material may be disposed between the shell and the deicing member for reducing the radar cross section of the airfoil.

Abstract: A pneumatic deicing distribution valve 10 includes a body 12, a cap assembly 14 and a rotary member 30 contained therein. Rotary member 30 selectively connects an input port 18 with a plurality of output ports 20 for selectively pressurizing one of a number of deicing apparatuses. A vacuum port 24 places all output ports not being pressurized under vacuum.

Abstract: A pneumatic deicer assembly 32 for attachment to an airfoil includes a pair of plies 52, 54 which are stitched together with a zig-zag stitch line which periodically crosses over the airfoil leading edge.

Abstract: A deicer assembly 32 for attachment to an airfoil includes a plurality of substantially parallel tube-like passages 36 formed by stitching parallel lines 78 through a pair of intermediate plies 52, 54. A zig-zag stitch line 76 criss-crosses the parallel tube lines 78 so that when the deicer is inflated by pressurized fluid a dimple matrix inflation pattern is formed.

Abstract: A pneumatic deicing system includes a deicer assembly 32 comprised of an outer ply 52, an inner ply 54, and a plurality of inflatable tube-like members 36 provided therebetween. The deicer assembly is disposed directly on top of and bonded to the airfoil 34. Pressurized fluid is provided to the tube-like members via a manifold 40 in the deicer assembly which is positioned directly over a plurality of ducts 42 provided through the airfoil.

Abstract: A planar coil construction, especially adapted for use in a force-producing device such as a de-icer, includes first and second sheet-like members, each defined by a continuous electrical conductor having a plurality of turns and first and second ends. The first end of the first conductor defines an electrical input to the coil, while the second end of the second conductor defines an electrical output from the coil. The second end of the first conductor and the first end of the second conductor are electrically connected. The sheet-like members are superimposed such that current flow through adjacent turns of the conductors is in the same direction. Within each sheet-like member, adjacent conductors also have current flow in the same direction. The invention includes a technique for spacing the conductors by means of a dielectric layer, and a technique for encapsulating the sheet-like members.

Abstract: A planar coil construction, especially adapted for use in a force-producing device such as a de-icer, includes first and second sheet-like members, each defined by a continuous electrical conductor having a plurality of turns and first and second ends. The first end of the first conductor defines an electrical input to the coil, while the second end of the second conductor defines an electrical output from the coil. The second end of the first conductor and the first end of the second conductor are electrically connected. The sheet-like members are superimposed such that current flow through adjacent turns of the conductors is in the same direction. Within each sheet-like member, adjacent conductors also have current flow in the same direction. The invention includes a technique for spacing the conductors by means of a dielectric layer, and a technique for encapsulating the sheet-like members.

Abstract: An attachable electro-impulse de-icer for de-icing an aircraft structural member includes an inductor coil disposed in proximity with the outer surface of the structural member. The coil is supported by a flexible, ice-accumulating support member (surface ply) that permits the coil to move relative to the structural member. Preferably the coil and support member are formed in an integral construction that can be attached to the leading edge of the structural member. The coil and support member are rapidly, and forcefully, displaced away from the structural member upon passing a short-duration, high-current pulse through the coil. The current flow creates an electromagnetic field that induces eddy currents in the support member (if made of metal), and the structural member (if made of metal). Upon collapse of the electromagnetic field in the coil, the support member is pulled rapidly to its rest position adjacent the structural member.

Abstract: An inflatable deicer having deicing tubes formed by adjacent rows of stitching between inner and outer plies with a manifold tube intersecting and extending across the deicing tubes. The stitching of the deicing tubes is turned at the edges of the manifold to reinforce the edges of the manifold tube. The deicing tubes are narrow and the inflation pressure is high for a short activation time at relatively long intervals to shed thin ice.

Abstract: A deicer control system for a pneumatic deicer wherein a solenoid operated valve directs either pressurized air or creates and pulls a vacuum on the inlet port of a control valve. The inlet port communicates to an outlet port in the control valve post moveable piston which in one position maintains communication between the ports and in a second position is operative to block communication between the ports. The piston has one face of the piston with two distinct effective surface areas, wherein one surface area communicates at all times with the inlet port and upon a predetermined force on such one surface area such piston is moved to expose both effective surface areas and block communication between the inlet port and the outlet ports of the control valve.

Abstract: A pressure limiter valve for regulating the inflation and deflation of inflatable tubes of a deicer wherein such valve has a housing with a central chamber with inlet and outlet ports communicating therewith. The inlet port is selectively subjected to a vacuum or a fluid pressure. An annular shoulder with a central aperture separates the ports so that a piston moveable within the bore between a first position and a second position can seat on the shoulder and isolate the ports. The one face of the piston has a first and second operative surface wherein the first operative surface communicates at all times to the inlet port via a passageway so that when the force on such first operative surface is slightly greater than a piston biasing force the piston is in a first position which causes the piston to expose both operative surfaces to the fluid pressure from the inlet port.

Abstract: An electroexpulsive separation apparatus suitable for deicing of the leading edges of aircraft includes a pair of sheet-like arrays each containing in spaced-apart relationship a plurality of parallel ribbon-shaped electrically conductive members. The electrically conductive members are electrically interconnected such that any electrical current flowing in the conductive members flows in the same direction in adjacent electrically conductive members in the first sheet like member and also flows in adjacent electrically conductive members of the second sheet-like array in a direction opposite. The first and second sheet-like arrays are coextensive and superposed proximate to each other such that the electrically conductive members of the first and second sheet-like members are substantially parallel. The electrically conductive members are electrically insulated from one another.

Abstract: A deicer pad for use on an aircraft wing wherein the deicer pad is constructed to have an intermediate portion and two spaced apart portions. The pad is a composite member of at least two plies of materials stitched along the intermediate portion to provide two spanwise passageways, and stitched in a zig-zag pattern along the spaced apart portions to form chordwise passageways. Alternate chordwise passageways communicate directly with the spanwise passageways while the remaining chordwise passageways communicate with the adjacent spanwise passageways around the stitching. The remaining chordwise passageways also communicate with the adjacent alternate chordwise passageways around the stitching which stitching forms the separation between alternate chordwise passageways.

Abstract: An article and method for measuring the extent, location and rate of water vapor droplet impingements on various surfaces exposed to multi-dimensional and turbulent flow fields. The article and method are employed in a non-icing atmospheric environment, and the results are used to prognosticate not only the areas where ice would accumulate if the water droplets were supercooled but also the concentration thereof. The invention is accomplished by removably adhering a droplet impingement recorder (10) to a surface to be tested, such as an airfoil (20). The droplet impingement recorder (10) incorporates a water soluble gelatin coating (13) bonded to a substrate (11). Droplets suspended in the flow field impact upon the recording surface (18) of the droplet impingement recorder (10).

Abstract: A deicer pad mounted on the leading edge of a helicopter blade. The deicer pad is a composite structure having two layers stitched together to form spanwise passageways on the intermediate portion that is essentially located on the intermediate portion of the blade and chordwise passageways on the spaced apart end portions that form the upper and lower portion of the deicer pad. The upper and lower portions are located rearwardly of the leading edge and are on the upper and lower portions of the helicopter blade.

Abstract: An attachable electro-impulse de-icer for de-icing an aircraft structural member includes an inductor coil disposed in proximity with the outer surface of the structural member. The coil is supported by a flexible, ice-accumulating support member (surface ply) that permits the coil to move relative to the structural member. Preferably the coil and support member are formed in an integral construction that can be attached to the leading edge of the structural member. The coil and support member are rapidly, and forcefully, displaced away from the structural member upon passing a short-duration, high-current pulse through the coil. The current flow creates an electromagnetic field that induces eddy currents in the support member (if made of metal), and the structural member (if made of metal). Upon collapse of the electromagnetic field in the coil the support member is pulled rapidly to its rest position adjacent the structural member.