Aerospace and Mechanical Engineering

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  • 1

    Patent

    Plasma optimized aerostructures for efficient flow control
    Thumbnail
    Inventor(s):
    Mehul Patel, Thomas C. Corke, Alan B. Cain
    Patent Number:
    US 9541106 B1
    Description:

    The present invention relates to a method of designing or optimizing a control surface for use with plasma actuators for controlling an aircraft, missile, munition or automobile, and more particularly to controlling fluid flow across their surfaces or other surfaces using plasma actuators, which would benefit from such a method. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and automobiles. The method of flow control also provides a mean…

    Date Issued:
    2017-01-10
    Record Visibility:
    Public
    Title
    Plasma optimized aerostructures for efficient flow control
    Description
    The present invention relates to a method of designing or optimizing a control surface for use with plasma actuators for controlling an aircraft, missile, munition or automobile, and more particularly to controlling fluid flow across their surfaces or other surfaces using plasma actuators, which would benefit from such a method. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and automobiles. The method of flow control also provides a means for reducing aircraft, missile's, munition's and automobile's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices.
    Creator
    Mehul Patel, Thomas C. Corke, Alan B. Cain
    Publisher
    U.S. Patent and Trademark Office
    Language
    English
    Rights
    All rights reserved
    Resource Type
    Patent
  • 2

    Patent

    Method of increasing the performance of aircraft, missiles, munitions and ground vehicles with plasma actuators
    Thumbnail
    Inventor(s):
    Thomas C. Corke, Mehul Patel
    Patent Number:
    US 9,834,301 B1
    Description:

    A method of increasing the performance of an aircraft, missile, munition or ground vehicle with plasma actuators, and more particularly of controlling fluid flow across their surfaces or other surfaces which would benefit from such a method, includes the design of an aerodynamic plasma actuator for the purpose of controlling airflow separation over a control surface of a aircraft, missile, or a ground vehicle, and a method of determining a modulation frequency for the plasma actuator for the …

    Date Issued:
    2017-12-05
    Record Visibility:
    Public
    Title
    Method of increasing the performance of aircraft, missiles, munitions and ground vehicles with plasma actuators
    Description
    A method of increasing the performance of an aircraft, missile, munition or ground vehicle with plasma actuators, and more particularly of controlling fluid flow across their surfaces or other surfaces which would benefit from such a method, includes the design of an aerodynamic plasma actuator for the purpose of controlling airflow separation over a control surface of a aircraft, missile, or a ground vehicle, and a method of determining a modulation frequency for the plasma actuator for the purpose of fluid flow control over these vehicles. Various embodiments provide steps to increase the efficiency of aircraft, missiles, munitions and ground vehicles. The method of flow control reduces the power requirements of the aircraft, missile, munition or ground vehicle. These methods also provide alternative aerodynamic control using low-power hingeless plasma actuator devices.
    Creator
    Thomas C. Corke, Mehul Patel
    Publisher
    U.S. Patent and Trademark Office
    Language
    English
    Rights
    All rights reserved
    Resource Type
    Patent
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