Yaw Stability Analysis for UiTM's BWB Baseline-II UAV E-4

Abstract

This paper presents a study about yaw stability analysis for UiTMs Blended-Wing-Body (BWB) Baseline-II E-4. This aircraft is equipped with split drag flaps in order to perform directional motion. One of the split drag flaps will be deflected to generate yawing moment. This yawing moment is generated through the drag that is produced upon deflection of flaps. The study was carried out using Computational Fluid Dynamics (CFD) for various sideslip angles (β) and various flaps deflection angle (δT). The simulation was conducted at 0.1 Mach number (35 m/s) and results in terms of coefficient such yawing and rolling moment are tabulated in order to determine the stability of the aircraft. The result reveals that the aircraft is directionally unstable. This is as expected because the aircraft does not have any vertical tail configuration to provide the yawing moment. However, high deflection of split flaps can still generate adequate restoring moment for the aircraft.

A Robust Control Scheme for a PVTOL System Subject to Wind Disturbances

“…with m 1 being the slope and θ 1 being the roll angle of the PVTOL system in degrees. It is important to mention that this linear approximation was determined from the results of C l , obtained with respect to the variation of the roll angle of an aircraft similar to the PVTOL system, by using a wind Complexity chamber [34]. Furthermore, the air speed U was generated as follows:…”