Validation of flight dynamic stability optimization constraints with flight tests

Abstract

Numerical optimization in aerospace sciences and industry is now used on a daily basis. Since, aircrafts are very complicated objects, analyzing multiple disciplines and using Multidisciplinary Design Optimization became a regular practice. Coupling both aerodynamic and structural analyses in the optimization framework is classical example. On the other hand, flight dynamic stability analyses are very rarely incorporated into the optimization process, or if so, in very limited way. Yet, having appropriate flight dynamic stability characteristics is crucial for the aircraft handling qualities, which are regulated by the airworthiness regulations. Methodology for the design and optimization coupled with dynamic stability constraints has been previously established by the authors of this article. This paper presents validation of this design methodology by comparing data acquired from the design and optimization process with the test flight data of UAV aircraft, which was designed basing solely on the developed methodology of the multidisciplinary optimization framework.