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

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posted on 2016-06-07, 00:00 authored by Mehul Patel, Thomas C. Corke
The present invention relates to a method of controlling an aircraft, missile, munition or ground vehicle with plasma actuators, and more particularly to controlling fluid flow across their surfaces or other surfaces, which would benefit from such a method. The 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 more particularly to the method of determining a modulation frequency for the plasma actuator for the purpose of fluid flow control over these vehicles. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and ground vehicles. The method of flow control provides a means for reducing aircraft, missile's, munition's and ground vehicle's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices.

History

Patent Number

US 7624941 B2

Other Application

11/415,535

Inventor

Mehul Patel Thomas C. Corke

Inventor from Local Institution

Thomas C. Corke

Assignee

University of Notre Dame Du Lac

Date Modified

2017-08-01

Language

  • English

Claims

20

Publisher

United States Patent and Trademark Office

Cooperative Patent Classification Codes

B62D 35/007 (20130101); B64C 23/005 (20130101); F42B 10/668 (20130101); F42B 10/40 (20130101); Y02T 50/166 (20130101)

Contributor

Thomas C. Corke

International Patent Classification Codes

F41G 7/00 (20060101)

US Patent Classification Codes

244/3.22; 244/200.1; 244/205;

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