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.
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.
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.
Computational fluid dynamic (cfd) simulation of 3-dimensional pitching wing
(2014-04-01)
Laili Anuar, Mohammad Adzlan Shah
A study of the dynamic behavior of the delta wing undergoing oscillatory 3D pitching motion has been studied using computational fluid dynamic (CFD) code Fluent 6 TM. A flat delta-shaped half wing with sharp leading edge and sweep angle of 70 degree was chosen in this CFD simulation. A hybrid mesh was generated in the surrounding region. A simple harmonic motion equation used to prescribe the motion of the 3D pitching wing. The wing was sinusoidally pitched about its one half chord at reduced frequencies ranging from 0.05 to 0.30 at root chord Reynolds numbers between 9 × 104 and 3.5 × 105, for angle of attack ranges of 29 ° to 39 ° and 0° to 45°. The steady case of α= 0°, 29°, 39°, 45° were also investigated. The solver used was implicit segregated and the turbulence modeling was Spallart-Almarast with standard wall function. The preliminary results show that the Computational Fluid Dynamics (CFD) results have fairly agreement with the available experimental data.
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.

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