Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators

Patent

Description

A method of controlling 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 controlling aircraft, missiles, munitions and ground vehicles with plasma actuators

Patent Number
  • US 7954768 B2

USPTO Link
Inventor
  • Mehul Patel

  • Thomas C. Corke

Inventor From Local Institution
  • Thomas C. Corke

Other Application
  • 12/604,903

Claims
  • 20

Classification (US Patent)
  • 244/205; 244/3.21;

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

International Patent Classification codes
  • B64C 23/00 (20060101); B64C 21/00 (20060101); F42B 15/01 (20060101)

Language
  • eng

Date Issued
  • 2011-06-07

Publisher
  • United States Patent and Trademark Office

Assignee
  • University of Notre Dame Du Lac

  • Orbital Research Inc. (Cleveland, OH)

Access Rights Open Access
Content License
Departments and Units

Files

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