Pusat Pengajian Kejuruteraan Aeroangkasa - Monograf

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Satellite attitude determination by using gps
(2008-04-01)
Wahidon, Noor Rasyidah
Global Positioning System (GPS) has been used successfully to determine position and attitude of a spacecraft. A direct calculation method of position and attitude determination for a satellite is described. The satellite position and attitude is calculated and presented via the Graphical User Interface (GUI) by using the MATLAB 7.0. In general, this GUI will show the satellite position in ECEF XYZ coordinates and geodetic coordinates (latitude, longitude and altitude), satellite attitude (yaw angle, pitch angle and roll angle) and basic theory of GPS. The satellite position is determined by knowing the GPS satellite coordinates in ECEF XYZ, GPS satellite pseudoranges in meters and receiver position estimate in ECEF XYZ. In this thesis, the GPS receiver will detect four GPS satellites visible on the orbit in order to determine satellite position. A direct calculation method using the WGS 84 transformations is described. Satellite attitude is determined by using three antenna systems which are master antenna and two slave antennas. According to the relations between the local coordinates and the body frame coordinates, the formulas for computing yaw, pitch and roll can be derived directly. A direct calculation method to determine the satellite attitude by knowing the two local coordinates of the slave antennas are described.
Modeling of hydraulic components in rotorcraft systems
(2008-04-01)
Saruji, Mohamad Ismail
This research is involving studies of hydraulic components in rotorcraft and the effect of pressure, velocity and displacement of piston in hydraulic cylinder to rotorcraft maneuver. Research also cover the real mechanism of hydraulic components in rotorcraft especially helicopter. Hydraulic components equations and parameters also had been study in creating physical modeling of hydraulic components. Real helicopter hydraulic system had been study using manuals and production magazines. SimHydraulics® software in MATLAB® 7.5 (2007b) is use in build up the physical model for hydraulic system simulations. Through this research new hydraulic system physical model been recreated as simplify to the complicated hydraulic system in real working condition of helicopter maneuver. Physical modeling will simulate the real working system as better understanding to the people who want to learn hydraulic in rotorcraft. Result from this research should give people enough basic information on how real hydraulic system in rotorcraft works especially system that controls the main rotor. The effects of changing certain area in hydraulic cylinder also will show how pressure, velocity and piston displacement also change. Hydraulic system for helicopter Eurocopter AS350 will be the reference of actual hydraulic system in this research.
Airlines and airport operation and management in malaysia (amo)
(2008-04-01)
Ibrahim, Muhammad Hafidz
This paper express about the study of airport and airlines management and operation in Malaysia (AMO). It is used to implement the good system to the airport and airlines. The studies on the subjects of these papers are to gain some idea, knowledge and finding the problems due to the airport and airlines especially in Malaysia. The airlines and airport is interconnected among its’ management and operation. This title it is focuses about the flight schedule, gate assignment, cargo ground and baggage handling, and ground handling. In aviation, flight schedule play a central part in the aircraft business for airlines and aircraft operation and management. The main crisis for this flight schedule is when the aircraft delay to reach to the destination airport which can give an effect to the entire management and operation for airlines and aircraft. The way to solve this problem is to minimize the time used for the whole aircraft operation by defining the factor to create the delay and to solve it by analysis. Gate assignment is to make sure the aircraft management and operation system is in control at the airport. The problem with gate assignment is when there are many numbers of ungated flights at the airport. The main purpose of flight to gate assignment is to properly assign the aircraft to suitable gates, so that passengers can conveniently embark and disembark. The alternative is to define the number of gate that applied at the airport and reconstruct the gate assignment schedule to make sure there are no ungated flights at the apron of the terminal. Cargo ground handling operation is located at the cargo terminal and it is used to pack all things in the pallet before we put it into the aircraft. The problem about cargo handling is not very important because it is related to the big size of the pack. So that the probability to be lost during handling is less if compare to baggage handling. Baggage handling operation is located the passenger terminal or main terminal. It is related to the passenger baggage which is probability to be lost is high because of the size and misconduct by the baggage handler.
Multipurpose helicopter
(2008-04-01)
Abu Nawas, Sayeda Nafisah
Helicopters are the most popular type of aircraft being used widely in various tasks. Nowadays, light helicopter with multipurpose mission seems to be one of the major trends in the aircraft design. There are used for air ambulance, search and rescue operation, take photographs, film movies, air transportation, and fire detection. The main features that makes the helicopters in high demand is it can take off and land vertically. They do no need a runaway but just a helipod required and they are very ideal transports for operation in very limited space and suitable to use in major place in Malaysia especially in rural area where there is no airstrip. The ability of helicopter to hover means that it can land almost anywhere fairly flat firm surface exists and can move freely from a spot to another spot. Referring to the situation in Malaysia, there is a high demanding for helicopter use especially by the government, industry, and corporate sector. Therefore, it is expedient to design the light multipurpose helicopter that may be used to fulfill the requirements of nowadays and future, and suit the topography of Malaysia. The final year project entitle “Light Multipurpose Helicopter’ is a very interesting project because there a lot of opportunities for innovation and highly multidisciplinary nature of helicopter engineering problems.
Analysis for the structural integrity of deployable truss
(2008-04-01)
Yu, Kok Hwa
The purpose of this project is to design an ideal single module deployable truss structure for space application. It is a structure which capable of large configuration changes in an autonomous way. The configuration can changes from a packaged, compact state to a deployed, large state. There are several structural aspects were taken into consideration, i.e. geometry, stiffness, loading, weight, rigidity and stability, in order to design an optimum deployable truss. In this final year project, it outlines the methodology to design, model, analyse and obtain an ideal deployable truss through optimization. The designed truss structure should be able to support two solar arrays weighted 1000kg each in the space environment and able to retract for easy storage. Stress and buckling analysis were conducted using Finite Element Method for simplified model before complicated three-dimensional model were analysed in widely used computer-aided software like MSC. PATRAN with MSC. NASTRAN. A MATLAB program implementing Direct Stiffness Method is established for analytical and computational verification. An optimum design structure is obtained through parametric optimization in the latter part of design process. Hopefully, this multi purpose structural element will be a crucial structure element in the future for the benefit of mankind.
Design, fabricate and test a solid propellant rocket motor
(2009-03-01)
Teh, Lloyd Tzer Tong
The study of a small solid propellant rocket motor is presented in this report. A rocket motor is designed, fabricated and tested in static test rig to obtain experimental results. The solid fuel consists of a composite propellant that utilizes Potassium Nitrate, Epoxy and Ferric Oxide. The addition of Ferric Oxide serves as a burn rate modifier to increase the propellant burning rate. The use of composite propellant allows the propellant to be cold casted which makes it safer to fabricate. The cartridge loaded propellant grain configuration makes it possible for several firing tests using the same motor to obtain a good result. Burn-rate tests show that propellant burn-rate depends on the voids present in the propellant and the mixing ratio of epoxy resin and hardener. By minimizing the voids present in the propellant grain and increasing the resin to hardener ratio, faster burn-rate is possible which in turn increases the average thrust of the motor. Experimental result shows that the motor has a lower total impulse. Investigation suggested that the lower density of the propellant grain prepared is the cause of it. As for the specific impulse, experimental result lies near the expected value.
Design of multipurpose helicopter for malaysia condition
(2009-03-01)
Abdul Razak, Siti Noorseri
Multipurpose helicopter seems to be one of the major trends in the aircraft design for the rotorcraft categories due to the market demand. There are used for air ambulance, search and rescue operasion, take photographs, film movies, air transportation, and fire detection. The main features that makes the helicopter in high demand is it can take off and landing vertically, no need a runway but just a heliport required. They are very ideal transport for operation in very limited space and suitable to use in major place in Malaysia especially in rural area where there is no airstrip. Referring to the situation in Malaysia, there is a high potential for helicopter use demand by the government, industry and corporate sector. Therefore it is expedient to design the multipurpose helicopter that may be used to fulfill the requirements of nowadays and future, and suit the Malaysia landform and environment. The main objective of this project is to design a helicopter at the same time can handle multipurpose missions that are most needed and suitable for Malaysia condition in terms of temperature and altitude above sea level at places in Malaysia. Some method and calculation were using to achieve the objective. The first step is collecting the data about Malaysian fleet such as the types and number of helicopter, temperature and average altitude. After that, the helicopter prototyope was chosen to use the initial data to find the estimation of weight. Analysis about the performances of helicopter between the Europe condition and Malaysia condition was done and the requirement for the design heliocpter so that the objective of every production is to produce very economical cost of helicopter and at the same time very high performance of the helicopter can be achieved. As conclusion, there are many of differences performance of helicopter in Europe and Malaysia condition because it has the different temperature. Besides that, the numbers of blades also influence the performance and cost of the helicopter.
Preliminary design of long endurance uav
(2009-03-01)
Tang, Sing Peng
Currently, the longest flight endurance achieved by Malaysian made UAV‟s is no longer than 8 hours. The focus of this project is to research a new UAV design capable of achieving more than 10 hours of unmanned flight with a maximum take-off weight of 40 kg at a cruising speed of 120 km/h and altitude of 1000 m. In addition, the UAV should have a take-off distance of about 150 m and landing distance of about 200 m. To define the UAV configuration, a method as described by Roskam was used in the form of aircraft design software called AAA software together with the use of other additional software like DATCOM, XFOIL and others along the design process. The design process starts with an initial weight sizing in terms of payload system, empty weight and fuel weight. With this the maximum take-off weight was found and through the use of AAA software it was possible to define a suitable power loading (W/P) and wing loading (W/S). These two parameters are important since it will allow one to proceed to the other steps of the design process, namely airfoil selection & wing sizing, and engine selection. From the power loading selected, the required horsepower is defined and the suitable engine was researched from the market. With the observation of various types of airfoils, it was found that the NASA LS 0413 was the most suitable airfoil to fulfill the requirements of the UAV‟s design lift coefficient. Fuselage sizing was then carried out by considering the fuselage size to ensure the required payload and fuel tanks are accommodated. Wing body sizing is then carried out by combining the wing and fuselage and ensuring the design lift coefficient is met. Next, the horizontal tail design was established with the NACA 0012 airfoil. Wing-body-tail analysis was then carried out using DATCOM to find the best position of the wing and horizontal tail with respect to fuselage. After meeting the requirements, sizing of the vertical tail was determined according to recommended tail volume ratio. Roskam‟s analytical approach was used to generate the aerodynamic data needed for twin vertical tails since DATCOM is unable to accomplish this task. The landing gear selection, layout and its tire sizing was carried out according to Raymer‟s approach. The vertical tail, tail boom, and landing gear, influence only the drag coefficient without any effect on lift and moment coefficient; thus the full UAV clean configuration is generated by adding their drag coefficient into previous wing-body-tail data. To increase the lift coefficient for takeoff and landing, the high lift devices are then designed. The deflection of the flaps influences the moment coefficient of the UAV. As a result, the UAV becomes untrimmable, thus requiring control devices such as elevators. Flap deflection and elevator deflection will be studied here. Lastly, an aerodynamic analysis, longitudinal stability analysis and performance analysis was done on the full UAV configuration to check if the design requirements are met. The results show that the main objective to fly at least 10 hours is achieved as the UAV can fly for 26 hours at constant 1000 m altitude with constant speed of 120 km/hr. The designed UAV is then drawn in CATIA V5 software.
Conceptual design of hand-launch uav in preliminary sizing
(2009-03-01)
Tang, Kia Wei
Nowadays, there is still no one standard procedure to design Unmanned Aerial Vehicles. The design approach varies according people and criteria to be considered. In this Hand Launch UAV design project, book of Airplane Design by Dr. Jan Roskam used as primary reference approach. According to Airplane Design, Preliminary sizing is the very first of in conceptual design of airplane as well as UAV. Preliminary Sizing is the first phase to be carried before further design process going on. The overall result of preliminary sizing can be divided into to two categories, which are weight and performance. The results of weight sizing are gross take-off weight, empty weight, mission fuel weight of UAV. Whereas, the performance sizing are to find the maximum required take-off power and wing area for UAV by determine the maximum lift coefficient at different mission profile. This thesis describes the method and process of governing of relationship for UAV empty weight and takeoff weight, and “matching plot” at given requirement to be fulfilled. The design method in initial sizing for the Hand launch UAV is described in Airplane design: Preliminary sizing book by Dr Jan Roskam. The result of the preliminary sizing has met the assigned technical requirements in which the maximum take off weight of the UAV do not more than 5kg with empty weight of 3.4kg. The UAV flies at height of 100m with speed 50km/h and maximum cruise speed of 80km/h.
Effects of cross flow on flapping wing performance
(2009-03-01)
Husin, Surianurhaiza
The creation of micro air vehicles (MAVs) of the same general sizes and weight as natural fliers has spawned renewed interest in flapping wing flight. With a wingspan of approximately 15 cm and a flight speed of a few meters per second, MAVs experience the same low Reynolds number (104–105). Although the flapping wing is good for aircraft maneuver in a still air, but the effect of cross wing on the aerodynamic performance is lacking. Due to the low flight speeds, any disturbance such as gusts or wind will dramatically change the aerodynamic conditions around the flapping wings. This thesis uses the bat type flapping wing and the analysis of flow around the wing was simulate by using FLUENT and GAMBIT software package. The lift and drag force produced from the simulation were examined and compared with the experimental result from the recent research. The lift force will increase with the increasing of wind speed and the wind speed also increases when flapping frequency increases. With the increasing of angle of attack also influence the lift produced from the flapping wing motion.
Structural analysis of conventional wing
(2009-03-01)
Wong, Wei Sheng
Finite Element Analysis (FEA) is a computer based mathematical techniques to obtain approximate numerical solutions for the study of structures physical behaviors in response to external influences. This project was about setting up a tapered wing finite element model by using MSC Patran and analyzing it with MSC Nastran. Before modeling could be done, the air loading that acted on wing during cruise flight condition was first determined. Thereafter, the wing model which was consisting of 1D and 2D elements was built for computational analysis. In order to ensure the model built in Patran was representing the reality, hand calculations were done for verifications. From the results obtained, the verification of constraint forces acting on the model differ 7.39% from that in theoretical calculation. Meanwhile, the direct stresses due to bending moments and axial loads for a typical cross-sectional structural members were having percentage difference ranging from 9% to 31%. Hence, the wing model was verified to be generally close to reality.
Aircraft of the light sport aircraft category. Common problems of conceptual design; development of aircraft layout; choice of structure; design of main airframe units
(2009-03-01)
Ting, Wen Ong
The purpose of this project is to choose a suitable structure of LSA, and design its main airframe units. The high humidity of Malaysia climate condition and geographical location of Malaysia which is surrounded and near the sea pose a great challenge for LSA designers. Another reason to design a LSA is that Malaysia has market potential for LSA since the concept of experimental aircrafts has been well established in Malaysia. This project started by comparing different kind of structures and materials. It is found that the aluminum-tube-and fabric construction is the best choice. The reason behind it simply because of the excellent corrosion resistance properties of aluminum alloy 6061-T6, which is widely used in aviation industry. After that, the aircraft configuration is determined. High wing, flapless wing and tricycle landing gear are the main features of this LSA. Another feature of the LSA is light weight. It is light because the material is aluminum alloy, and the LSA is covered by fabric. The fuselage is designed based on the concept of ultralight, with a tail-boom fuselage structure. This is another cost saving design. Besides that, at the tail part of LSA, rudder is designed to have a similar tube structure as elevator, while vertical stabilizer has a similar tube structure as horizontal stabilizer. This will save the cost of manufacturing of LSA. The final parts are designing and drawing of main airframe units of the aircraft using CATIA. Because there is no structural analysis is done on the aircraft parts, without accurate dimension of the LSA, I find it difficult to coordinate and assemble the airframe units together.
Roll and yaw actuation for momentum biased satellite by magnetic torquers
(2009-04-01)
Chong, Chia Ye
The control of the satellite attitude is very important because for certain satellite, they need to fix to a point throughout their operation. The tolerance on the attitude errors are small, so we need to choose a control technique to be used on the satellite. Several control methods have been developed since the first satellite was launched, and the control techniques can be classified as active or passive. Active techniques are needed for missions where high pointing accuracy is crucial but very expensive. Magnetic technique is attractive for controlling small satellites in Low Earth Orbits (LEO). Magnetic control systems are relatively lightweight, require low power consumption and inexpensive compared to the other control methods. In this thesis, the magnetic torque rods have been selected as the actuator to control the satellite attitude. This is due its characteristic which can generate magnetic dipole moment thus creating torque when interact with the earth magnetic field. The simulation work has been carried out by Matlab 7.0. Performances from simulations show that the attitude steady-state error is achieved within two orbital periods with values of 0.3 and comply with the mission requirement. Controllers are structured using ordinary PD (Proportional Derivative) controller to control roll and yaw axis of a small momentum biased satellite in nominal attitude operation.
Design and optimization of an aeronautical composite laminated panel
(2009-04-01)
Idris, Nur Hidayah
A rectangular composite laminated panel is optimized in terms of mass (weight reduction) using MATLAB programming code. The first level of optimization process deals with failure resistance and defining the minimum thickness of the overall plies and percentage in each fibre orientation. The fibre orientation used are only limited to a sets of (0°, 45°, -45°, and 90°). Rounding process was done after obtaining the minimum thickness of the overall plies and percentage in each fibre orientation. The final results of the entire optimization process program are number of the plies in each fibre orientation.
Robot manipulator with 2-degrees of freedom (dof) using air muscles
(2009-04-01)
Saharudin, Siti Noraini
This project investigates the use of air muscle as an actuator for robot manipulators. Air muscles are soft pneumatic devices for ideally suited for robotics and animatronics. Air muscles contract when pressurized with gas air. Simple systems use a small air pump or compressor. The size of the air muscle and the air pressure determines the weight of the load it can pull when it contracts. For this work, simple robot manipulator has been created. Using some knowledge of engineering field, the procedures was developed in order to determine entire mechanism of air muscle movements. As an Aerospace Engineering student, these experience and knowledge is very useful in aircraft application especially because pneumatic power with its simplified and cleaner has found success in many industrial applications where there is a need for low cost, low-precision but high-power operation. Therefore, the mini-human-arm to show the mechanism of the movements has been fabricated. In order to achieve these goals, an experimental was carried out by different length of air muscle and different pressure has been applied to determine the behavior of air muscles with various loads. Therefore, a literature survey, a discussion of the theoretical and experimental that will work along with an outline for future have been selected to designed this work.
Stress analysis and sizing of an aeronautical composite sandwich panel (secondary structure)
(2009-04-01)
Abdullah, Siti Aminah
Nowadays, structural sandwich construction is used in many air and space vehicles, cargo containers, boats and ships. In fact, honeycomb sandwich panels revolutionized the aerospace industry over 40 years ago, making aircraft lighter, stronger and faster and allowing them to carry more weight and improve fuel efficiency. This report will be focused on sizing the panel of a secondary structure for commercialaircraft. After modeling the panel, stress analysis will be performed. The model of panel for commercial aircraft is being chosen for the typical example analysis as a critical sandwich structure. The analysis of the panel will be guided by some assumptions which one of the assumption is both end of the panel is simply fixed with clamp. The load when aircraft is cruising will be used for this analysis. There are several mode of failure in analyzing the stress such as deflection, transverse shear failure, local crushing of core, shear crimping, face wrinkling, intracellular buckling, core unglue, facing failure and general buckling. However, for this project, the analyses that will be performed are deflection and face wrinkling. By using manual calculation, the answer will be generated. From the result obtained, further studies to enhance the understanding of sandwich panel structure can be decided.
Study on bubble rising behavior in water column using piv system
(2009-04-01)
Shari, Abdul Azim
Gas injection into the bath of reactors has been widely used in variety fields of engineering in order to promote mixing or chemical reactions. In manufacturing it is desired to measure the velocity of molten steel for the improvement of current processes as well as for the development of new processes. In this research, bubble rising behavior to the water surface is studied in rectangular water column using Particle Image Velocimetry (PIV). Bubbles are being studied in velocity and rising pathline behavior in three different location camera views. Simulation of bubble rising behavior also carried out using Gambit and Fluent software replicate the experiment dimension. From the result obtain, bubble velocity initially increase until the middle part then reduce when approaching the water surface. Observation gives the result of pathline bubble rising in zigzag mode. Simulation was being carried out for 5 seconds; give zigzag for the pathline result. Study of bubble can be expended for future development in different liquid medium with different density properties.
Modeling and analysis of aero-composite materials in aircraft structure applications
(2009-04-01)
Mustaffa , Mohd Syahiran
This final year project focuses on the conceptual three-dimensional modelling of a composite honeycomb sandwich structure for use as skin panels to common commercial aircraft airframe structures. The honeycomb sandwich structure was modelled using CATIA V5R16 Composites Design workbench. It is then analysed via finite element analysis using CATIA Generative Structural Analysis workbench. Airframe structures of nose radome, inboard trailing edge mid flap, elevator and rudder was then modelled using CATIA design workbenches, based on the real airframe structures of the Boeing 747, and are assembled with composite skin panels based on the modelled composite honeycomb sandwich structure. The airframe structures are then analysed by finite element analysis using CATIA Generative Structural Analysis workbench and the effects and outcome of Von Misses stress, stress principal tensors, deformation and translational displacements due to static loading on the structures is observed. Conclusion on the suitability of the modelled composite honeycomb sandwich structure as airframe structure skin panels was then made.
Aeros - conceptual design of uav composite airframe
(2009-04-01)
Mohd Shaharanee, Mohd Izmir
This project presents AEROS, a new conceptual design of Unmanned Aerial Vehicles. This UAV will have a mission to scout the weather in Malaysia. Although this projects is about the conceptual design, but the main part that is focused is the structural configuration. All of the layout that can be considered suitable for the requirement will be analyze. The selection of the material also will be analyzed first before the final designs begin. An assembly of part finally is done in the final stage of this project and a new UAV is born. There are some limitation occurs during this project, such as the limited resources of the previous related project, lack of knowledge on the designing method and also time consuming when design using CAD software stage. This project actually can become quite helpful to a lot of people. Weather is one of the elements that if we know it, we can gain a great profit after it. At the end of this project, the things that should be understand on designing an aircraft is that weather our step in design will lead to the fulfillment of the objective or vice versa.
Active magnetic control of gravity gradient satellite using 3 magnetic torquers
(2009-04-01)
Mohd Sabri, Mohd Naim
This thesis deals with design of controller for gravity gradient satellites. One of the control techniques that have been used on this type of satellite is magnetic control technique. Thus, in this project the magnetic attitude control of the gravity gradient satellite will be analyzed. Three magnetic torquers will be used and placed along the satellite primary axes. Then, the comparison of the Euler Angle between original properties of satellite and after added with the torquers can be made after the simulation is done. In this, the results of the research are obtaining from the simulation models that designed from MATLAB SIMULINK software. On the other hand, the development is taking the first Malaysia microsatellite, TiungSAT-1 as the references model of it characteristic and initial conditions. At the end of this project, should understand the role of the three magnetic torquers to the gravity gradient satellite due to the satellite missions. The findings of this project also prove that Euler angles of the satellite can be control with more accurate with the existence of the controller.

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