FLOW BODY FOR AN AIRCRAFT WITH A SELECTIVELY ACTIVATABLE SHOCK BUMP

A flow body for an aircraft includes a skin having a first flow surface, having a flow influencing section with at least one first layer, at least one separator layer, at least one third layer, and at least one base layer. The first layer includes lithiated carbon fibers embedded into a matrix to fo...

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Bibliographische Detailangaben
Hauptverfasser:	MACHUNZE, Wolfgang, LINDE, Peter
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIRCRAFT AVIATION BLASTING COSMONAUTICS HEATING HELICOPTERS LIGHTING MACHINES OR ENGINES FOR LIQUIDS MECHANICAL ENGINEERING MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOTOTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISEPROVIDED FOR OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR PERFORMING OPERATIONS PRODUCING MECHANICAL POWER SPRING, WEIGHT, INERTIA OR LIKE MOTORS TRANSPORTING WEAPONS WIND, SPRING WEIGHT AND MISCELLANEOUS MOTORS
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Beschreibung
Zusammenfassung:	A flow body for an aircraft includes a skin having a first flow surface, having a flow influencing section with at least one first layer, at least one separator layer, at least one third layer, and at least one base layer. The first layer includes lithiated carbon fibers embedded into a matrix to form a negative electrode. The third layer includes carbon fibers with an electrode active material coating to form a positive electrode. The separator layer includes a non-conductive material for electrically isolating the first layer and the third layer from each other. The flow influencing section is configured for selectively raising a region of the arrangement of first layer, separator layer and third layer from the base layer upon application of a voltage between the first and third layers to form a bump on the flow body.