Reactive Flow Control System Using Intelligent Control Modules for Virtual Aerodynamic Shaping
Abstract
A proof-of-concept closed-loop reactive flow control methodology using discrete intelligent control modules for virtual aerodynamic shaping of air vehicles is developed. Discrete suction control technique integrated with dynamic pressure sensors and a closed- loop controller forms the basis of the intelligent control modules, which are then coordinated by a higher-level controller to enable a desired flow effect on the surface of the air vehicle. Static and dynamic wind tunnel tests at Mach 0.08 on a two-dimensional airfoil with discrete suction control embedded via a series of holes on the upper surface near the trailing edge has been conducted. Apart from increased aerodynamic efficiency using discrete suction control, information about timescales related to the actuator response time and the flow dynamics time is obtained from a series of dynamic tests for both, constant alpha and pitching maneuvers. Data from these static tests, dynamic tests and computational studies is being used to develop a closed- loop control algorithm to form the basis of the intelligent control module operation. A number of intelligent control modules located discretely on the surface of the air vehicle will then be coordinated by a higher level controller enabling a desired maneuver of the air vehicle. A collaborative effort to demonstrate the effectiveness of the prototype system via experimental and computational studies is under way.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 2002
- Accession Number
- ADA409289
Entities
People
- Alan B. Cain
- Mehul P. Patel
- Richard M. Kolacinski
- T. T. Ng
- Troy S. Prince