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-
- Inventor(s):
- Mehul Patel, Thomas C. Corke
- Patent Number:
- US 7954768 B2
- 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 f…
- Date Issued:
- 2011-06-07
- Title
- Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators
- 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.
- Creator
- Mehul Patel, Thomas C. Corke
- Publisher
- United States Patent and Trademark Office
- Language
- eng
- Rights
- http://creativecommons.org/publicdomain/zero/1.0/
- Resource Type
- Patent
-
- Inventor(s):
- Mehul Patel, Thomas C. Corke
- Patent Number:
- US 7624941 B2
- Description:
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 mod…
- Date Issued:
- 2009-12-01
- Title
- Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators
- Description
- 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.
- Creator
- Mehul Patel, Thomas C. Corke
- Publisher
- United States Patent and Trademark Office
- Language
- eng
- Rights
- http://creativecommons.org/publicdomain/zero/1.0/
- Resource Type
- Patent
-
- 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
- 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
-
- Inventor(s):
- Mehul Patel, Thomas C. Corke
- Patent Number:
- US 8267355 B2
- 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 f…
- Date Issued:
- 2012-09-18
- Title
- Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators
- 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 and or ground vehicle. These methods also provide alternative aerodynamic control using low-power hingeless plasma actuator devices.
- Creator
- Mehul Patel, Thomas C. Corke
- Publisher
- United States Patent and Trademark Office
- Language
- eng
- Rights
- http://creativecommons.org/publicdomain/zero/1.0/
- Resource Type
- Patent
-
- 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
- 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