Electro-Expulsive De-Icing System for Aircraft and Other Applications

Abstract

An apparatus for removing ice from an object (e.g., in-flight ice removal from the skin of an aircraft) includes an actuator assembly that forms an elongated electrically conductive loop. The actuator is mounted in a position enabling it to impact the object to be de-iced in response to movement of the loop that is produced by electric current pulses flowing in opposite directions in two mechanically independent loop subassemblies. The loop subassemblies include multiple electrically conductive elements interconnected at their ends using elongated flexible connectors in order to introduce a physically discontinuity that reduces any restriction of relative movement of the subassembly ends caused by the connectors, thereby achieving enhanced operation and less fatigue failure as compared to a rigid structure having encapsulated element

1 . A de-icing system comprising:
 an object having an outer skin disposed over at least one supporting structure;   an electroexpulsive actuator comprising:
 a plurality of sub-assemblies each comprised of at least one electrically conductive element coupled to an electrical input at a first end thereof, 
 at least one electrically conductive flexible connector interconnecting a second end of each of the plurality sub-assemblies, thereby creating a conductive loop from the electrical input of each conductive element to an electrical output thereof, 
 wherein the flexible connectors are configured to allow relative movement along the entire length of each of the sub-assemblies, including the ends thereof, and 
 wherein the sub-assemblies are disposed in an orientation relative to each other such that when electrical current flows through the conductive loop formed thereby a magnetic field is created in the plurality of sub-assemblies and the sub-assemblies are urged apart relative to one another under the influence said magnetic fields; and 
   wherein the electroexpulsive actuator is positioned beneath the outer skin of the object such that the relative movement of the subassemblies causes the electroexpulsive actuator to deliver a force to the outer skin of the object that creates a de-icing shockwave therein.   
     
     
         2 . The system of  claim 1 , wherein the electrically conductive elements are in a substantially parallel configuration, and wherein the relative movement is lateral to the longitudinal axis of the conductive elements. 
     
     
         3 . The system of  claim 1 , wherein the connector is one of a plurality of connectors connecting second ends of pairs of electrically conductive elements, each pair comprising an electrically conductive element from the first sub-assembly element from the second sub-assembly and an electrically conductive element from the second sub-assembly. 
     
     
         4 . The system of  claim 1 , wherein the connector is selected from the group consisting of one of either a stranded aircraft wire or a U-shaped loop. 
     
     
         5 . The system of  claim 1 , wherein a longitudinal axis of the connector is one of either parallel to or perpendicular to a longitudinal axis of the conductive elements. 
     
     
         6 . The system of  claim 1 , wherein each of the ends of the sub-assemblies are encapsulated. 
     
     
         7 . The system of  claim 1 , further comprising an inner shell enclosed by the outer skin of the object. 
     
     
         8 . The system of  claim 7 , wherein the actuator is mounted between the inner surface of the outer skin and the outer surface of the inner shell. 
     
     
         9 . The system of  claim 7 , wherein the actuator is mounted to the outer surface of the inner shell. 
     
     
         10 . The system of  claim 7 , wherein the actuator is mounted to the inner surface of the outer skin. 
     
     
         11 . The system of  claim 7 , further comprising an actuator support structure attached to one or both of the inner shell or outer skin. 
     
     
         12 . The system of  claim 11 , wherein the actuator is mounted adjacent to the actuator support structure. 
     
     
         13 . The system of  claim 12 , wherein the actuator support structure comprises a first and second support structure, and the actuator is mounted between the first and second support structure. 
     
     
         14 . The system of  claim 12 , wherein multiple actuators are mounted between the actuator support structure and the inside surface of the skin;
 wherein the first actuator is mounted between one end of the actuator support structure and the inner surface of the skin, the second actuator is mounted between the opposite end of the actuator support structure and the inner surface of the skin.   
     
     
         15 . The system of  claim 1 , wherein multiple actuators are mounted at spatially separated points along the object. 
     
     
         16 . A method comprising:
 disposing an electroexpulsive actuator beneath the outer skin of an object in actuating relation thereto, the actuator comprising:
 a plurality of sub-assemblies each comprised of at least one electrically conductive element coupled to an electrical input at a first end thereof, 
 at least one electrically conductive flexible connector interconnecting a second end of each of the plurality sub-assemblies, thereby creating a conductive loop from the electrical input of each conductive element to an electrical output thereof, 
 wherein the flexible connectors are configured to allow relative movement along the entire length of each of the sub-assemblies, including the ends thereof, and 
 wherein the sub-assemblies are disposed in an orientation relative to each other such that when electrical current flows through the conductive loop formed thereby a magnetic field is created in the plurality of sub-assemblies and the sub-assemblies are urged apart relative to one another under the influence said magnetic fields; and 
   inducing an electrical current in the actuator such that current flows through the sub-assemblies thereby creating a magnetic field in the plurality of sub-assemblies thereby creating a relative movement of the subassemblies, said relative movement being sufficient to deliver a force to the outer skin of the object thereby creating a de-icing shockwave therein.   
     
     
         17 . The method of  claim 16 , wherein the actuator is mounted between the inner surface of the outer skin and the outer surface of the inner shell. 
     
     
         18 . The method of  claim 16 , wherein the actuator is mounted to the outer surface of the inner shell. 
     
     
         19 . The method of  claim 16 , wherein the actuator is mounted to the inner surface of the outer skin. 
     
     
         20 . The method of  claim 16 , further comprising an actuator support structure attached to one or both of the inner shell or outer skin. 
     
     
         21 . The method of  claim 20 , wherein the actuator is mounted adjacent to the actuator support structure. 
     
     
         22 . The method of  claim 21 , wherein the actuator support structure comprises a first and second support structure, and the actuator is mounted between the first and second support structure. 
     
     
         23 . The method of  claim 21 , wherein multiple actuators are mounted between the actuator support structure and the inside surface of the skin;
 wherein the first actuator is mounted between one end of the actuator support structure and the inner surface of the skin, the second actuator is mounted between the opposite end of the actuator support structure and the inner surface of the skin.