Abstract:
An energy harvesting system for an aircraft includes an energy storage device, and an energy harvesting member electrically connected to the energy storage device and mechanically linked to the aircraft. The energy harvesting member is configured and disposed to generate an electrical energy output in response to one of a change in altitude of, or turbulence on, the aircraft.

Description:
BACKGROUND OF THE INVENTION 
       [0001]    Exemplary embodiments pertain to the art of motor vehicles and, more particularly, to an energy harvesting system for a motor vehicle. 
         [0002]    Motor vehicles including land vehicles, water vehicles, and air vehicles include multiple electrical loads that are often powered by a battery. Oftentimes, the electrical loads are connected to the battery through long runs of electrical conductors or wires. As motor vehicles grow in complexity, the use of electrical components and, by extension, the need for more electrical conductors and connectors increases. The number of electrical conductors and connectors added to a motor vehicle represents a significant weight load that may impact performance. For example, the weight associated with the electrical conductors may have a negative impact on gas mileage for motor vehicles, or load maximums for air based vehicles. Also, the long runs of electrical conductors are exposed to harsh environments, including vibration, that could create open circuits that are hard to locate and repair. 
       BRIEF DESCRIPTION OF THE INVENTION 
       [0003]    Disclosed is an energy harvesting system for an aircraft including an energy storage device, and an energy harvesting member electrically connected to the energy storage device and mechanically linked to the aircraft. The energy harvesting member is configured and disposed to generate an electrical energy output in response to one of a change in altitude of, or turbulence on, the aircraft. 
         [0004]    Also disclosed is an aircraft including a body having an exterior surface and one or more interior surfaces, an energy storage device arranged in the body, and an energy harvesting member electrically connected to the energy storage device and mechanically linked to the body. The energy harvesting member is configured and disposed to generate an electrical energy output in response to one of a change in altitude of, or turbulence on, the body of the aircraft. 
         [0005]    Still further disclosed is a method of harvesting electrical energy in an aircraft. The method includes exposing an energy harvesting member mounted to a surface of the aircraft to one of a change in altitude or turbulence, generating an electrical energy in the energy harvesting member in response to the one of the change in altitude or turbulence, passing the electrical energy from the energy harvesting member to an electrical storage device, and storing the electrical energy in the electrical storage device. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0006]    The following descriptions should not be considered limiting in any way. With reference to the accompanying drawings, like elements are numbered alike: 
           [0007]      FIG. 1  is a perspective view of an aircraft including an energy harvesting system, in accordance with an exemplary embodiment; 
           [0008]      FIG. 2  is a schematic view of the energy harvesting system of  FIG. 1 ; 
           [0009]      FIG. 3  is a schematic view of an energy harvesting system, in accordance with another aspect of an exemplary embodiment; and 
           [0010]      FIG. 4  is a schematic view of an energy harvesting system, in accordance with yet another aspect of the exemplary embodiment. 
       
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
       [0011]    A detailed description of one or more embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the Figures. 
         [0012]    An aircraft, in accordance with an exemplary embodiment, is indicated generally at  2 , in  FIG. 1 . Aircraft  2  includes a body  4  having a forward or nose portion  6  and an aft or tail portion  8 . Tail portion  8  includes a vertical stabilizer  10 , a first horizontal stabilizer  12 , and a second horizontal stabilizer  14 . Aircraft  2  also includes a first wing  16  extending from a port side (not separately labeled) of body  4  and a second wing  18  extending from a starboard side (also not separately labeled) of body  4 . Body  4  includes an exterior or lower pressure surface  22  and an interior surface  24  ( FIG. 2 ). Interior surface  24  defines an area of high or steady pressure  26  and exterior surface  22  defines an area of lower or fluctuating pressure  28 . 
         [0013]    In accordance with an exemplary embodiment, aircraft  2  includes an energy harvesting member  40  mounted to body  4 . In the exemplary aspect shown, energy harvesting member  40  may take the form of a pressure transducer  46  mounted to exterior surface  22 . Pressure transducer  46  is electrically coupled to an energy storage device  50  which may take the form of an ultracapacitor  52 . Energy storage device  50  may be electrically coupled to an electrical load  54  which may take the form of a light  56 , such as an LED. Of course it should be understood that one or more electrical control devices, such as a switch (not shown), may be electrically connected between energy harvesting member  40  and electrical storage device  50 ; and between electrical storage device  50  and electrical load  54 . 
         [0014]    In accordance with an exemplary embodiment, aircraft  2  experiences variations in pressure between high pressure zone  26  and low pressure zone  28  during various points of flight. Pressure changes occur during changes in altitude both on ascent and decent, as well as during periods of turbulence. The pressure changes lead to pressure fluctuations that create a zone of fluctuating pressure  60  about pressure transducer  46 . The pressure fluctuations act upon pressure transducer  46  resulting in generation of an electrical current that is passed to energy storage device  50 . The energy may be used to power light  56 . In this manner, power may be provided for an electrical load without the need for long runs of conductors that increase complexity, manufacturing costs, and an overall weight of the aircraft. The number of energy harvesting devices may vary and can be located on any surface of body  4 . 
         [0015]    Reference will now be made to  FIG. 3  in describing an energy harvesting member  68 , in accordance with another aspect of the exemplary embodiment. Energy harvesting member  68  may take the form of a micro-turbine  70  provided in body  4  between exterior surface  22  and interior surface  24 . Micro-turbine  70  responds to flows of air currents by creating electrical energy. Micro-turbine  70  is operatively connected to an energy storage device  72  which may take the form of a battery  74 . Energy storage device  72  is electrically coupled to an electrical load  76  that may be a speaker or a Wi-Fi connection  78 . 
         [0016]    During flight, and in particular during altitude changes, air is expressed from high pressure zone  26  to low pressure zone  28 . In accordance with the exemplary embodiment, at least a portion of the air is passed through one or more micro-turbines  70  to generate electrical energy for operating electrical load  76 . In this manner, power may be provided for an electrical load without the need for long runs of conductors that increase complexity, manufacturing costs and an overall weight of the aircraft. The number of energy harvesting devices may vary and can be located on any surface of body  4 . 
         [0017]    Reference will now be made to  FIG. 4  in describing an energy harvesting member  88 , in accordance with another aspect of the exemplary embodiment. Energy harvesting member  88  takes the form of a piezo-electric element  90  that is mounted to interior surface  24 . Of course it should be understood that piezo-electric element  90  may also be mounted to exterior surface  22 . Piezo-electric element  90  is electrically connected to an energy storage device  92  which may take the form of a coiled spring and/or a flywheel  94 . Energy storage device  92  is electrically connected to an electrical load  96  that may take the form of a sensor  98 . 
         [0018]    During flight, changes in altitude of and/or turbulence on, an aircraft  2  may result in dimensional changes to exterior surface  22  and/or interior surface  24  or other parts of body  4 . The dimensional changes are realized by piezo-electric element  90 . In response to the dimensional changes, piezo-electric element  90  generates a flow of electrical energy that is passed to energy storage device  92  and used to power electrical load  96 . In this manner, power may be provided for an electrical load without the need for long runs of conductors that increase complexity, manufacturing costs, and an overall weight of the aircraft. The number of energy harvesting devices may vary and can be located on any surface of body  4 . 
         [0019]    At this point it should be understood that the exemplary embodiments describe a system for harvesting electrical energy from an aircraft resulting from changes in altitude and/or turbulence. Harvested electrical energy is passed to a local energy storage device and used to power electrical loads. In this manner, long runs of electrical cables that carry electrical energy from a central electrical source to loads may be reduced. The reduction in cabling leads to increased operational capacity and efficiencies of the aircraft. It should also be understood that the number and type of energy harvesting members may vary. Also, an aircraft may include various types of energy harvesting members. In addition, the number and type of electrical storage devices and electrical loads may vary, and some loads or storage devices may be located in low pressure zone  28  attached to exterior surface  22 . 
         [0020]    While the invention has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this invention, but that the invention will include all embodiments falling within the scope of the claims.