Method of increasing the performance of aircraft, missiles, munitions and ground vehicles with plasma actuators

Patent

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.

Attributes

Attribute NameValues
Title
  • Method of increasing the performance of aircraft, missiles, munitions and ground vehicles with plasma actuators

Patent Number
  • US 9,834,301 B1

USPTO Link
Inventor
  • Thomas C. Corke

  • Mehul Patel

Inventor From Local Institution
  • Thomas C. Corke

Other Application
  • 13/570,684

Claims
  • 13

Cooperative Patent Classification codes
  • B62D 35/007 (20130101); B64C 23/005 (20130101); F42B 10/40 (20130101); F42B 10/38 (20130101); F42B 10/668 (20130101); Y02T 50/166 (20130101); B64C 2230/12 (20130101)

International Patent Classification codes
  • F42B 10/38 (20060101); B64C 23/00 (20060101); B62D 35/00 (20060101)

Language
  • English

Date Issued
  • 2017-12-05

Publisher
  • U.S. Patent and Trademark Office

Assignee
  • University of Notre Dame Du Lac

  • Orbital Research Inc. (Cleveland, OH)

Record Visibility and Access Public
Content License
  • All rights reserved

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