Ziad Bin Abdul Awal
@bsmraau.edu.bd
Assistant Professor, Department of Aeronautical Engineering (Aerospace)
Bangabandhu Sheikh Mujibur Rahman Aviation and Aerospace University (BSMRAAU)
Ziad Bin Abdul Awal is an Aeronautical and Mechanical Engineer who specializes in VTOL / STOL & Rotary-wing aircrafts. He completed his Master of Engineering by Research from the Universiti Teknologi Malaysia (UTM) under the Department of Aeronautics, Automotive & Ocean Engineering of Fakulti Kejuruteraan Mekanikal in 2017. Prior to that, in 2014, He received his Bachelor Degree in Mechanical - Aeronautical Engineering from UTM as well.
For well over half a decade, Ziad has been involved in the extensive research and development of rotorcrafts coalescing the field of Advanced Aerodynamics, Structural Mechanics and Safety Analysis. His research has led to the publication of several Books, Journal Papers and International Conference Proceedings.
Ziad’s research area includes Theoretical and Experimental Aerodynamics, Computational Fluid Mechanics, Unmanned Air Vehicle (UAV) Design, Structural Integrity Analysis and Rocket Propulsion.
EDUCATION
B. Eng. (Mech-Aero) (UTM, Malaysia)
[BACHELOR OF ENGINEERING IN MECHANICAL - AERONAUTICAL ENGINEERING]
M. Eng. (Mech) (UTM, Malaysia)
[MASTER OF ENGINEERING (By Research) IN MECHANICAL ENGINEERING]
RESEARCH, TEACHING, or OTHER INTERESTS
Aerospace Engineering, Mechanical Engineering, Multidisciplinary
Scopus Publications
Scholar Citations
Scholar h-index
Scopus Publications
Ziad Bin Abdul Awal
International Journal of Geomate
Unmanned rotary-wing aircrafts or rotorcrafts are often prone to diverse atmospheric turbulences, and undeniably, abrupt gusts are reckoned to be the most acquainted commotion of them. Time and again, gust turbulence have dictated being the regulating trigger for countless mishaps concerning micro aerial vehicles. Given that the core/main rotor provides principal lift along with governing directional control and dynamic stability for any rotorcraft, the demeanors of thrust or induced air-flow through the gyrating blades largely signify the barebones of its functionality. This paper presents an idiosyncratic approach towards reviewing the impact of wind gust on rotor induced aerodynamic flow performance of an unmanned rotorcraft. Artificial gusts have been generated through the inherent concept of forced pitched oscillation without the use of any conventional wind tunnel. Gust air-speed and the rotor induced air-speed are gauged through the same contraption to provide homogeneous quantitative valuation. Each rotor-halves have been assessed `root-to-tip' across designated span-wise positions against selected strengths of gust. Comparative analysis with normal atmospheric condition indicated gradual loss of cumulative thrust during hover (15-40%) and forward flight (10-30%) within the stipulated gust range and infers the risk of declining altitude. Protuberant imbalance of thrust across the rotor disk during hover indicated the likelihood of lackadaisical half-pitched rolling motion. However, during forward flight, the reduced discrepancy of thrust between the rotor halves signified gradual loss of cruising speed with regards to the increasing gust strength for the specific rotorcraft model. Experimental findings in this study exhibited prospect of appraisal with full-scale rotorcrafts.
Y. Azeez, Azmi Shah Suratman, H. Salamon, Ramli Awang and Ziad Bin Abdul Awal
Postmodernism may be viewed as an era in which the mass media was integral to an immense proliferation of artistic styles that projected the ideations of postmodernism and its several movements. This paper examines the historical development of postmodernism as an imaginative intellectual interest group throughout the 1960s and '70s. An attempt is made to critically assess both positive and negative effects of postmodernism on the mass media in addition to the latter's influence(s) on Islam within the context of postmodernism.
Ziad Bin Abdul Awal and Mohd Shariff bin Ammoo
Trans Tech Publications, Ltd.
The aerodynamics of the helicopter rotor is one of the most elating and exigent tribulations faced by the aerodynamicists today. Study through flow visualization process plays a key role in understanding the airflow distinctiveness and vortex interaction of the helicopter main rotor blade. Inspecting and scrutinizing the effects of wake vortices during operation is a great challenge and imperative in designing effective rotor system. This study aimed to visualize the main rotor airflow pattern of the Hirobo-FALCON 505 controllable subscale helicopter and seek for the vortex flow at the blade tip. The experimental qualitative data is correlated with quantitative data to perform scrupulous study on the airflow behavior and characteristics along with its distinctiveness spawned by the main rotor blade. Simulation using design software is performed in analogous stipulations to endow with comparability between the flow visualization results. Throughout the blade span several dissimilar flow patterns have been identified. The main rotor hub has turbulent flow at its center due to low energy of air amassed in this region whereas in the middle portion of the rotor blade, the air encompasses high kinetic energy with a clear straight streamline pattern.
Mohd Shariff Ammoo, Ziad Abdul Awal, and Norhidayah Mat Sangiti
Penerbit UTM Press
Balancing is a rotating component is critical in any mechanism. Devoid of proper balancing, any vehicle - be it in air, land or sea, it will affect stability, control and safety. The same goes for rotor crafts. Imbalance of the helicopter tail rotor system leads to vibrations in the entire vehicle and may cause accident. Typically, for the tail rotor of a helicopter, the blade is a source of vibration on the tail boom. This not only causes inconvenience to the pilot but also reduces the life span of the helicopter. There is a certain amount of vibration in the helicopter rotor systems especially the tail rotor. Hence, balancing procedure for rotating mass was conducted to reduce the vibration. This research focuses on balancing of the tail rotor for UTM Single Seat Helicopter. Experiments have been conducted in order to study the vibration level of the tail rotor. Adding and removing masses separately on the tail rotor exhibited different vibration levels. The responses were analyzed and used for balancing the tail of rotor system. The balancing effort was considered successful, although there was still some residual unbalance in the tail rotor.
Mohd Shariff Ammoo, Ziad Abdul Awal, and Khairul Shamil Khairudin
Penerbit UTM Press
Structural strength is just as important as any other measures for a performance vehicle - let it be in air, land or water. Chassis is the most critical constituent in keeping the integrity of a vehicular structure. Likewise, helicopter chassis is like its skeleton. Devoid of it, the helicopter will neither take shape nor conserve the structural strength necessary. This research took the liberty of appraising the structural stiffness of the chassis for UTM Single-Seat Helicopter which is being developed at Universiti Teknologi Malaysia (UTM). This helicopter uses space frames as the main chassis structure. The material used for this chassis is AISI 4130 steel. Static analysis of the chassis was conducted specifically during hovering condition. The analysis started with modelling and simulating the chassis using Finite Element Analysis (FEA) software. Data obtained through FEA simulation were then tested and verified using the experimental data. The results obtained were intriguing and in line with the FAA standard Regulation.