Finless UCAS flight control with active flow control effectors and advanced maneuver development
Abstract
The proposed research uses active flow control effectors on a finless UCAV for flight control. Flight tests with a delta-wing subsc,ale aircraft will use Coanda-type trailing edge control effectors for pitch and roll control. A novel apex control effector will us,e slot-jets at the nose for yaw control. System identification processing of flight test data will be used to create an aero-databa,se of the active flow control effectors control authority. The database will be used in Simulink-based flight simulations to predi,ct the flight performance of the UCAV aircraft and explore complex maneuvers based on multiple active flow control effectors, such a,s, yaw-pointing. An extreme flight direction reversal maneuver will be explored using foam versions of the UCAV aircraft. In this,maneuver the UCAV aircraft makes a 180 degree change in flight direction in approximately 1 second. Assuming sufficient yaw control,authority is produced on the active flow control aircraft, then the maneuver will be demonstrated in the third year of the program.A,pproved for Public Release
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Sep 03, 2022
- Source ID
- N000142212552
Entities
People
- David R. Williams
Organizations
- Illinois Institute of Technology
- Office of Naval Research
- United States Navy