Static Aeroelasticity in the Design of Modern Fighters
Abstract
Static aeroelastic effects are manifested in the form of changes in the total load or lift on the aircraft, or in changes in the overall distribution of load or lift. These changes affect the structural integrity of the vehicle, its static stability, the effectiveness of various control surfaces, and the overall flight performance. The characteristics and magnitude of these aeroelastic effects are dependent on the aerodynamic shape of the vehicle, the structural orientation, the structural stiffness, and the particular flight condition in terms primarily of Mach number and dynamic pressure. A review of fighter aircraft development programs over the past 30 years indicates a trend of increasing emphasis on the consideration of static aeroelastic effects. While early concerns addressed only the impact on air vehicle structural integrity, current design philosophy recognizes and addresses aeroelasticity as a primary design parameter affecting structural optimization, vehicle aerodynamic stability, control effectiveness, and overall performance. Examples from wind tunnel testing, analytical studies and operational aircraft applications are presented to justify this emphasis illustrate current methodology and analysis techniques, and make a case for an integrated approach to the consideration of static aeroelastic effects at all stages of the design process.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1986
- Accession Number
- ADP005049
Entities
People
- E. G. Wilson Jr.
Organizations
- McDonnell Aircraft Corporation