A study was conducted under Drones for Aerodynamic and Structural Testing (DAST) program to accomplish the final design and hardware fabrication for four active control systems compatible with and ready for installation in the NASA Aeroelastic Research Wing No. 2 (ARW-2) and Firebee II drone flight test vehicle. The wing structure was designed so that Active Control Systems (ACS) are required in the normal flight envelope by integrating control system design with aerodynamics and structure technologies. The DAST ARW-2 configuration uses flutter suppression, relaxed static stability, and gust and maneuver load alleviation ACS systems, and an automatic flight control system. Performance goals and criteria were applied to individual systems and the systems collectively to assure that vehicle stability margins, flutter margins, flying qualities and load reductions are achieved.
Design Verification and Fabrication of Active Control Systems for the DAST ARW-2 (Drones for Aerodynamic and Sructural Testing Aeroelastic Research Wing No. 2) High Aspect Ratio Wing. Part 1
1986
329 pages
Report
No indication
English
Aeroelastic Characteristics of High-Aspect-Ratio Wing According to Wing Shape
British Library Conference Proceedings | 2013
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