Abstract
The Aeroelastic Design and Test Validation of the F-22 is presented. Emphasis is placed on the various elements of the aeroelastic analysis design process and the ground and flight verification testing conducted on the F-22. Covered are early aeroelastic design issues, and the process to address them leading to a successful aeroelastic design of the F-22. The analysis/aeroelastic design process used a balanced mix of parametric and aeroelastic design optimization tools. Covered also is an overview/description of the ground and flight-testing conducted to verify the flutter characteristics of the aircraft, final analysis leading to the certification of the F-22, and considerations for force management. The aeroelastic stability process is an integral part the Aircraft Structural Integrity Program (ASIP) for the F-22. Consequently, the presentation of the aeroelastic analysis, design and testing is presented in the general organization of ASIP, which is a systematic approach to ensure aircraft structural integrity. Summarized is the process to implement airframe structural integrity during the F-22 Engineering and Manufacturing Development (EMD), with emphasis on flutter and aeroelastic stability.
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