Plasma optimized aerostructures for efficient flow control

Patent

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.

Attributes

Attribute NameValues
Title
  • Plasma optimized aerostructures for efficient flow control

Patent Number
  • US 9541106 B1

USPTO Link
Inventor
  • Mehul Patel

  • Thomas C. Corke

  • Alan B. Cain

Inventor From Local Institution
  • Thomas C. Corke

Other Application
  • 11/710,750

Claims
  • 20

Cooperative Patent Classification codes
  • F15D 1/0065 (20130101); B64C 21/00 (20130101); B64C 15/14 (20130101); F15D 1/0075 (20130101); Y02T 50/166 (20130101); B64C 2230/12 (20130101)

International Patent Classification codes
  • B64C 29/00 (20060101); F15D 1/00 (20060101); B64C 21/00 (20060101)

Language
  • English

Date Issued
  • 2017-01-10

Publisher
  • U.S. Patent and Trademark Office

Assignee
  • Orbitel Research Inc. (Cleveland, OH)

  • University of Notre Dame du Lac

Record Visibility and Access Public
Content License
  • All rights reserved

Departments and Units
Member of

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