Design, Control Surface Optimization and Stability Analysis of a Blended Wing Body Aircraft (BWB) Unmanned Aerial Vehicle

In this paper, a study of aerodynamic characteristics of UiTM's Blended-Wing-Body Unmanned Aerial Vehicle (BWB-UAV) Baseline-II in terms of side force, drag force and yawing moment coefficients are presented through Computational Fluid Dynamics (CFD) simulation. A vertical rudder is added to the aircraft at the rear centre part of the fuselage as yawing control surface. The study consists of varying the side slip angles for various rudder deflection angles and to plot the results for each aerodynamic parameter. The comparison with other yawing control surface for the same aircraft obtained previously are also presented. For validation purpose, the lift and drag coefficients are compared with the results obtained from wind tunnel experiments.

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Aerodynamic Analysis of Blended Wing Body - Unmanned Aerial Vehicle (BWB-UAV) Equipped with Horizontal Stabilizers

MATEC Web of Conferences ◽

10.1051/matecconf/201925602004 ◽

2019 ◽

Vol 256 ◽

pp. 02004

Author(s):

Nornashiha Mohd Saad ◽

Wirachman Wisnoe ◽

Rizal Effendy Mohd Nasir ◽

Zurriati Mohd Ali ◽

Ehan Sabah Shukri Askari

Keyword(s):

Unmanned Aerial Vehicle ◽

Cfd Simulation ◽

Lift Coefficient ◽

Angle Of Attack ◽

Flight Test ◽

Longitudinal Direction ◽

Static Stability ◽

Pitching Moment ◽

Aerial Vehicle ◽

Blended Wing Body

This paper presents an aerodynamic characteristic study in longitudinal direction of UiTM Blended Wing Body-Unmanned Aerial Vehicle Prototype (BWB-UAV Prototype) equipped with horizontal stabilizers. Flight tests have been conducted and as the result, BWB experienced overturning condition at certain angle of attack. Horizontal stabilizer was added at different location and size to overcome the issue during the flight test. Therefore, Computational Fluid Dynamics (CFD) analysis is performed at different configuration of horizontal stabilizer using Spalart - Allmaras as a turbulence model. CFD simulation of the aircraft is conducted at Mach number 0.06 or v = 20 m/s at various angle of attack, α. The data of lift coefficient (CL), drag coefficient (CD), and pitching moment coefficient (CM) is obtained from the simulations. The data is represented in curves against angle of attack to measure the performance of BWB prototype with horizontal stabilizer. From the simulation, configuration with far distance and large horizontal stabilizer gives steeper negative pitching moment slope indicating better static stability of the aircraft.

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Dynamic Stability and Control of a Manipulating Unmanned Aerial Vehicle

International Journal of Aerospace Engineering ◽

10.1155/2018/3481328 ◽

2018 ◽

Vol 2018 ◽

pp. 1-13 ◽

Cited By ~ 2

Author(s):

Yunping Liu ◽

Xijie Huang ◽

Yonghong Zhang ◽

Yukang Zhou

Keyword(s):

Stability Analysis ◽

Lyapunov Exponent ◽

Dynamic Stability ◽

Unmanned Aerial Vehicle ◽

Impedance Control ◽

System Stability ◽

Constructive Method ◽

Aerial Vehicle ◽

And Control ◽

The Impact

This paper focuses on the dynamic stability analysis of a manipulator mounted on a quadrotor unmanned aerial vehicle, namely, a manipulating unmanned aerial vehicle (MUAV). Manipulator movements and environments interaction will extremely affect the dynamic stability of the MUAV system. So the dynamic stability analysis of the MUAV system is of paramount importance for safety and satisfactory performance. However, the applications of Lyapunov’s stability theory to the MUAV system have been extremely limited, due to the lack of a constructive method available for deriving a Lyapunov function. Thus, Lyapunov exponent method and impedance control are introduced, and the Lyapunov exponent method can establish the quantitative relationships between the manipulator movements and the dynamics stability, while impedance control can reduce the impact of environmental interaction on system stability. Numerical simulation results have demonstrated the effectiveness of the proposed method.

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