Flight Performance Evaluation of the Flying-V

This study evaluates the flight performance of a Flying-V aircraft designed for transonic passenger transport. The Flying-V is a disruptive aircraft configuration that has shown to possess promising aerodynamic performance during preliminary design. It is compared to a competitor aircraft reminiscent of the Airbus A350-1000, for the same thrust...

Impact of Control Allocation Methods on the Design of Control Surface Layouts for Box-Wing Aircraft under Flying Qualities Constraints

This paper compares optimum control surface layouts designed and sized to obtain the same Flying Qualities (FQs) performance with different Control Allocation (CA) methods, and proposes novel layouts for staggered box-wing aircraft aimed at transonic commercial flight. Box-wings allow the installation of redundant control surfaces for which no...

Flight Mechanics and Performance of Direct Lift Control: Applying Control Allocation Methods to a Staggered Box-Wing Aircraft Configuration

The objective of the present dissertation is to show how redundant control surfaces can be exploited to shape an aircraft dynamic behavior and obtain desired flight mechanics performance. This is achieved by introducing novel approaches and methods for flight mechanics and control, mainly revolving around original implementations of traditional...

A generalized approach to operational, globally optimal aircraft mission performance evaluation, with application to direct lift control

A unified approach to aircraft mission performance assessment is presented in this work. It provides a detailed and flexible formulation to simulate a complete commercial aviation mission. Based on optimal control theory, with consistent injection of rules and procedures typical of aeronautical operations, it relies on generalized...

Assessment of Sub-scale Designs for Scaled Flight Testing

Sub-scale Flight Testing (SFT) is potentially useful in predicting aircraft flight behaviour, especially in the case of unconventional designs for which legacy information is unavailable and wind tunnel tests are unable to predict aircraft dynamics. A necessary condition for SFT is the design of properly scaled models. However, even in case of...