NASA NTRS · 19740003694
Analysis and testing of aeroelastic model stability augmentation systems
Abstract
Testing and evaluation of a stability augmentation system for aircraft flight control were performed. The flutter suppression system and synthesis conducted on a scale model of a supersonic wing for a transport aircraft are discussed. Mechanization and testing of the leading and trailing edge surface actuation systems are described. The ride control system analyses for a 375,000 pound gross weight B-52E aircraft are presented. Analyses of the B-52E aircraft maneuver load control system are included.
Keep this discovery
Explore connections, maps & timelines
Sevart, F. D., Patel, S. M.. 1973-10-15. Analysis and testing of aeroelastic model stability augmentation systems. https://ntrs.nasa.gov/citations/19740003694
Cite the original work for its findings. Save a collection to share your selection of sources.