This work presents a proposed framework intended to be used for the optimization of highlift devices, namely Flaps and Slats for the present study. From the conceptual design up to flight test, as fidelity and design maturity increases, a robust and yet fast tool is needed to assist engineers to optimize and make better decisions regarding Flap and Slat deflection definitions in order to satisfy the multitude of design challenges such as take-off performance, climb performance, landing performance, deployment times, kinematics, icing effects, failures, only to name a few. Without such a tool or framework, one can be easily overwhelmed and the best solution or trade-offs cans be lost or obliterated by the huge amounts of possibilities, constraints and design goals. The proposed framework can used with multiple fidelity data such as physics based models, CFD models and semi-empirical ones, in order to accomadate the learning curve that exists under any product development timeline. For an initial approach, the takeoff performance calculation is conducted using statistical models constructed from wind tunnel test data and then optimized, having as main design goal the maximization of the MTOW for a certain runway and having 2nd segment gradient as main constraint. Other constraints can and will be added as needed, in order to assist in a robust decision. Once the framework is set, a multitude of design studies can be done, including design robustness, sensitiveness, design changes and many others. Not only a direct result in airplane performance is expected, but also an expressive reduction in development cycle times from conceptual design to flight test, since the framework will hugely speed up the design process.
展开▼
