Design optimization for a new vertical flight technique

Abstract

The economy of military aircrafts during mission is very bad, especially at takeoff followed by climb. Also, it is clear that, the value of any military aircraft evaluated by its maneuverability and capabilities. This project is a chance and step to improve all of the military aircrafts economy, maneuverability and capabilities that is by invent new technique to achieve a vertical flight depend on the wing lift itself and by the aid of additional device. SU-35S, the military supermaneuverable aircraft was used in this project. After the field studies and data collection, this project start with a setup stage which include analysis and modeling for the SU-35S. This models includes: the aerodynamic model, the stability model, the structural model and prop-fan model. Using the models at the selected flight circumstances, MATLAB codes have been written to calculate the lift, check the stability, the structural strength and the axial momentum produced by the prop-fans. The second stage include the design optimization and consist for main two parts: the sliding part design optimization and the prop-fans rescale. It was approved that, a considerable lift value can be produced by the fixed wing aircraft at zero forward speed using the designed vertical flight device which consist of series of small prop-fans and sliding part. The aircraft is not stable which is expected result for fighter. Due to the shortness of time, the structural analysis results is not completed. But it is expected that, there is no structural deformation because the applied load is less than the aircraft maximum load. Also, the produced momentum by the prop-fans is not enough to accelerate the aircraft in the forward direction. The consumed power by the prop-fans had been found much less than the consumed power by the other techniques to achieve vertical takeoff normal to the aircraft wing.