Test Cases for the Benchmark Active Controls Model: Spoiler and Control Surface Oscillations and Flutter
Abstract
As a portion of the Benchmark Models Program at NASA Langley (Ref 1-2). a simple generic model was developed for active controls research and was called BACT for Benchmark Active Controls Technology model. This model was based on the previously-tested Benchmark Models rectangular wing with the NACA 0012 airfoil section that was mounted on the Pitch and Plunge Apparatus (PAPA) for flutter testing (Ref 1, 3-5) The BACT model had an upper surface spoiler, a lower surface spoiler and a trailing edge control surface for use in flutter suppression and dynamic response excitation. Previous expenence with flutter suppression (Ref 6-7) indicated a need for measured control surface aerodynamics for accurate control law design Three different types of flutter instability boundaries had also been determined for the NACA 00l2)PAPA model, a classical flutter boundary, a transonic stall flutter boundary at angle of attack. and a plunge instability near M = O%9 (Ref I Therefore an extensive Set of steady and control surface oscillation data was generated spanning the range of the three types of instabilities (Ref 8). This information was subsequently used to design control laws to suppress each flutter instability.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 2000
- Accession Number
- ADP010714
Entities
People
- Robert M. Bennett
Organizations
- National Aeronautics and Space Administration