compendium cae march 2008

SELECTION OF BEST STUDENT PROJECT Aerospace Engineering Department

During the final phase of engineering studies, twenty one (21) students of 64th Engineering Course underwent their project phase. A total of thirteen (13) different projects were undertaken, which included six team projects. These project s covered different specialties namely Aerodynamics , Structures, Propulsion s and Materials. The scope of the projects included stress and fatigue analysis of Mirage aircraft, design and fabrication of smoke tunnel for flow visualization, material characterization, development and stress analysis of composite materials, software development for aircraft conc eptual design and centrifugal compressor, design and development of airship, full scale fabrication of UAV and development of MAV. All the students gave their final presentation to defend their project from 17 to 18 March, 2008. The faculty of Aerospace Engineering Department vetted all the presentation s and after considerabl e debate, three projects were nominated for the award of the Best Student Project. In order to finalize the award, a team of five faculty members was formulated which comprised the following: Wg Cdr Abdul Munem Khan (Structures Group) Wg Cdr Ahmad Aizaz (Propulsions Group) Wg Cdr (R) Taimur Qureshi (Structures Group) Sqn Ldr Tauqeer (Aero Group) Sqn Ldr (R) Muhammad Anwar (Aero Group)

The team had a detailed assessment of selected projects and emphasis was given to: Quantum of academic work by the student in terms of design, analysis and application of knowledge to solve a given problem. Ability of the student to write a comprehensiv e report at the end of the project in the required format with sufficient project details. Final presentation made by the student to defend his work, handling of the Q & A session, confidence level and learning from the project itself. Physical output of the project in terms of completion of objectives defined at the start of the project. Importance of the project vis --vis PAF and National interest.

Keeping aforesaid into consideration, the decision of the committee was to award the best student project to the project titled Study of Material Characte rization Methods and Determination of Microstructure of Selected Aviation Materials by using Optical Microscope.

ABSTRAC T OF BEST PROJECT IN AEROSPAC E ENGINEERING

Study of Material Characterizatio n Method And Determinatio n of Microstructur e of Ferrous and Non Ferrous Alloys by Using an Optical Microscope

Plt Off Farrukh Nawaz Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor Gp Capt Fahim Hashmi Date of completion :17 March 2008 Sponsorin g Agency: Aerospac e Department of ferrous and non

Introduction/AbstractThe using aim of the project is to study and analyze with basic the microstructur e of ferrous and non ferrous alloys by proper metallographic techniques for along establishmen t of a well equipped metallographi c facility in CAE which can be utilized metallographi c Objective M ain objective of the characterizatio n . The secondary objectives are to establish specimen preparation laboratory and commissionin g of optical microscope for metallographi c and fractografi c analysis intended to be used for educationa l and research purposes. Methodology LITERATUR E REVIEW project is to learn basic metallographic techniques which are used for material techniques material s science and engineering . teaching and researc h in the field of

Analysis The analysis of microstructur e

Metallographic Results

ferrous alloys including

plain carbon steel, alloy steel,

austenitic stainless steels and aluminum alloys was done by identifying different phases observed in their respective microstructures. Heat treatment s done on each material was validated through the microstructura l results obtained. The expected behavio r of the material was also predicted along wi th effect of different alloy constituent s on the properties of the material. Sensitizatio n effect in austeniti c stainless steel was also studied through AISI 4130 (Annealed) . The structure is ferrite and pearlite at 500 X, 4% picral as etchant. microexaminatio n of welded parts, along with the processes required to control sensitization . More over a comparativ e study to determine the major changes caused in the microstructur e under different service conditions was also carried out. Conclusio ns The project is a successful attempt in preparing a facility which can be utilized for future research projects relating to material sciences and it can also help a lot in investigatin g material failures. Specimen preparation facility is adequatel y established for metallographi c analysis of ferrous and non-ferrous alloys. Optical Microscop e has been fully commi ssioned; its operating manual has also been prepared. Heat treatment s can be verified through metallographic examination. AISI 321 (serviced) Micrograph shows partially recrystallize d austenit e grains, some carbide particles; the whole matrix is austenite at 500 X, 15ml HCl, 10ml HNO3 and 10ml acetic acid used as etchant.

ESTABLISHMEN T OF A METALLOGRAPHI C FACILITY

SPECIME N PREPARATIO N FOR METALLOGRAPHY

METALLOGRAPH Y OF FERROUS AND NONFERROU S ALLOYS

ANALYSI S OF RESULTS

Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur

SELECTION OF BEST STUDENT PROJECT Aerospace Engineering Department

In the final semester of Bachelors of Avionics Engineering, students apply their engineering knowledge of complete an assigned project. A total of eighteen (18) different projects were undertaken by 21 students of 64 Engg Course, which included three projects sponsored by the PAF and the remaining were proposed by the faculty of Avionics Engineering Department. These projects comprised design and fabrication of active and passive circuits in RF / Microwave domain, Robotics and Control, Simulation and Modeling of advanced concepts in Electromagnetic s and Communications , fabrication of Electronics Systems and design of Automated Test Equipment. All the students presented their projects from 17 to 18 March, 2008. The faculty of Avionics Engineering Department validated the quantum and quality of work done and after comprehensiv e deliberations ; three projects were nominated for the award of the Best Student Project. Following tem was constituted to finalize the award: Gp Capt Ahmed Ejaz Nadeem, Head Avionics Engg Department Gp Capt Abdur Rehman, Group Head Communications Wg Cdr Farid Gul, Group Head Navigation and Control Systems Sqn Ldr Atif Bin Mansoor, Group Head Digital & Embedded Systems Sqn Ldr Muhamma d Aamir Khalil, Officer In charge Student Projects and Group Head Circuits and Power Electronics.th

The team adjudged the best project based on the following criteria: Quantum of academic work by the student in terms of design, analysis and application of knowledge to solve a given problem. Ability of the student to write a comprehensiv e report at the end of the project in the required format with sufficient project details. Final presentation made by the student to defend his work, handling of the Q & A session, confidence level and learning from the project itself. Physical output of the project in terms of completion of objectives defined at the start of the project. Importance of the project viz -a-viz PAF and National interest.

Based on above stated criteria the committee awarded the best student project to the project titled Design and Developmen t of a Software for CoLocation of Radars.

1 BE Projects Compendiu m 64 EC

Design and Developmen t of software for CO-LOCATION OF RADARS PHASE III

Pilot Officer Ghazzaal Mazhar Hashmi, Pilot Officer Waqas Mehboob. Avionics Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisory Committee : Wg Cdr Irfan Majid, Sqn Ldr Muhamma d Shahid, Sqn Ldr Abdul Mateen Sponsorin g Agency: ACAS(SE )

installation and efficient use of the software application . Introduction/Abstract Objective Develop a software to predict safe separation distance between two co-located radars. Brief Descriptio n / Abstract Radars are being used for surveillance , air traffic control, maritime applications , weather mapping, high resolution imaging, satellite altimetry, and numerous air defence and weapon control applications . This has resulted in systems that share the same frequenc y spectrum, causing EM interferenc e and susceptibilit y concerns. In PAF, as the air defence environmen t gets denser, similar problems are likely to be faced. The major concern is the co-location of Air Traffic Control Radar (ATCR-33S) and long range high powere d radar (TPS-43G). A multi -phased project was undertaken at CAE to design and develo p a software to predict safe separation distance between two co -located radars. In Phase -I, three teams comprising six students implemente d interferenc e models catering for environmental , propagation , beam shape, and co - existence of another radar in close proximity. Receiver susceptibilit y models and 3-D beam pattern were developed. Additionally , Matlab based code was developed to predict safe separation distance. In Phase -II, a two member team acquired and integrated a highresolution Digital Elevation Model (DEM) with the software application developed earlier. Lin e of sight calculation s were included in the design to enhanc e efficiency of software. Additional l y, virtual radar scope and Google earth utility was also created. In the final stage (Phase-III), receiver susceptibilit y models and interferenc e models pertaining to propagatio n losses were verified, updated and improved using a customize d lab setup by a two member team. Graphical user interfaces (GUIs) and software codes developed in earlier phases were optimized, refined and packaged as a standalone application. Additionally , a User Guide was compiled to facilitate Conclusion Besides reliably predicting the safe separatio n between co located radars, the robust software application developed during this multi -phased project can also be used for line of sight calculations , sector blanking estimations, terrain masking , virtual radar scope showing ground clutter and terrain features, and a convenient and reliable aid for radar deploymen t and coverage estimation.

Field testing of radar receiver susceptibility

Lab testing of interference models

Software prediction

Figure 2 Software GUIsCompare

Agreed Disagree Refinement

Revised susceptibility models

Revised interference models

Software Integration and code optimization

Software packaging Figure 1 Methodolog y of verification .

Avionics Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur

1

FORMULATIO N OF PROCEDURES , INSTRUCTION S AND DATA SHEETS OF ALL THE EQUIPMENT OF PROP LABSenior Gentlema n Cadet Tayyaab Umer Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor Sqn Ldr Sadiq Amin Date o f completion : 15 March 2008 Sponsorin g Agency: Aerospac e Department Operating procedures , safety precaution s were prepared. In the end, all the relevant data was integrated in to software , made in MATLAB Flow Chart of Work carried out on all the apparatus as wall as in Matlab

Introduction/AbstractLab equipment was never explored to its limits due to limited scope of BE students . During the project capabilitie s of the equipmen t were explored and accuracy of and safety precaution s have been developed for all equipment. Additionall y a GUI using MATLAB to bring the scattered informatio n under one umbrella. Available software of the equipment have also been interlinked and for easy calculations , Excel sheets have also been added to GUI the lab handouts was verified. Working, Maintenanc e instructions

AnalysisExperiment s on selected equipmen t had been performed and problems experimen t observed upon are have and in the some nature, of for of equipment complexit y particular inclusion been of of were the these on rectified. Based recommendation s three equipmen t

curriculum made

subjects,

experiment s in undergraduat e studies. Experiment s already

Objective To perform detailed experimenta l work on every equipment . Preparatio n instructions. Revising lab handouts of the experiments . Preparatio n of data and result sheets for every experiment. Enhancing the skill level of lab staff. of their maintenanc e and working

performed by students of various courses. Efforts are in hand by the lab for problems , which could not be rectified during the project.

Conclusion Lab equipment , though very old can still be used for performing experiment s by BE students Results can still be improved by removing

the discrepancie s observed in the lab equipment.

Methodology Thorough understandin g of the equipmen t and related theory was developed. Lab experiment s were performed on all equipment. A number of readi ngs were taken for each experiment.. Lab handouts were revised for all experiment s and m aintenance , working instructions were prepared

GUI developed can easily be used by students for performing experiment s and data reduction by students.

. Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur

Development of Aircraft Conceptual Design SoftwareNUST CADET K ashan Saleem NUST CADET Faisal Mohammad Aerospace Engineerin g Department , PAF College of Aeronautica l Engineering Advisor Sqn Ldr Messam Abbas Date of completion : 17 March 2008 Sponsorin g Agency: Aerospace Department

Brief DescriptionACDS is a newly design ed software which was developed keeping in mind the limitations of RDS-Student software . This softwar e has been developed in Microsoft Visual Basic 6.0. The software has the capabilit y of automati c iterations and non-repetitive inputs resulting in reduction of design time. It encompasses the whole design process from mission profile selection till optimizatio n unlike RDS. ACDS consists of several aerodynami c modules which separately calculat e componen t parameters ,

Working of ACDSA new project in ACDS demand s selection of a hypothetical mission profile, which is used in computatio n of various modular outputs like take -off gross weight etc. For initial design point selection the software can perform constraint analysis. Next the software requires the user to select airfoils and geometr y of the subject aircraft which are then used to calculate various geometric parameter s providing the built-in CAD tool with various inputs to model the aircraft in 3-D. The user then has to select a propulsion system to meet the mission requirement s of the aircraft. ACDS on the basis of user inputs compute s various parameter s of aerodynamics, propulsion, structure and weights which are then used to analyze the performanc e of the aircraft.

A Snap of Main Screen

weight, propulsio n data, aircraft geometry etc.

All the modules in this software are inter-linked and interrelated. This software can be refined over a period of time to meet the emerging technologie s requirement s.

A Snap of 3D Modeling & Layout Module

ObjectiveThe aim of the project is to develop software for aircraft conceptua l design process which overcome s limitations of RDS, has better user interaction and can be utilized for all aircraft design needs of PAF.

ConclusionACDS covers all the limitations of RDS and BDS. It also facilitates the user in each step of conceptua l design process. A number of airfoils have been added in ACDS to provide a wider range of selection. It has a better graphical user interface and has a very friendly user interface . The CAD tool included in this software is very comprehensiv e and easy to use. Also help is provided by the software for each input require d from user.

Methodology Complet e understandin g of Aircraft Conceptua l Design Process. Understandin g and Working of RDS & BDS. Highlightin g Main Limitation s of RDS & BDS and Improvement s required for new software. Platform Selection (Visu al Basic 6 was selected). Developmen t of Software .

Aerospace Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur

BE Projects Compendium 64 EC

FABRICATIO N OF MAV BY INTEGRATE D PRODUCT AND PROCESS DEVELOPEMENTNUST CADET Afaq Mustafa PIA/OFF Taimur Ellahi Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur AdvisorSqn Ldr Messam Abbas Naqvi Date of completion: 17 March 2008 Sponsoring Agency: Aerospace Department

Introduction/AbstractIn this project, two different design spaces were explored for the fabrication of micro air vehicle and two different configuration s were selected with the help of a morphological matrix. After the exploratio n of the design space a set of all possible variable parameter s were selected and then were reduced to a set of most effective set of input parameter s by doing a sensitivity analysis by identifying the variabilit y of responses through screening test. After selection of final set of input parameter s, ranges were assigned to these variables and optimizatio n was performed on a full factorial design of experiment s array. A final optim ized configuratio n was selected, fabricated by CNC machining and flight tested.

taking their three values, max, min and average. A combinatio n set was made out of these three values with all other parameter s and after that the whole setup

A 3D view MAV configuration 1

was automize d using a software automate and the final results obtaine d out of these combination s were then optimized on the basis of performanc e parameters

Conclusion s Multidisciplinar y design optimizatio n technique is very useful for exploring different design spaces This project helped in understandin g the complete advanced design process. This project also involved understandin g and application of CNC fabrication technique. More work should be done on the avionics of MAV to reduce its weight and drag due to protruded wiring. A single chip avionics integrated solution could help reduce weight significantl y and enhance MAV performance. MAVs are the future of aerospac e industry and must be pursued in order to stay current with the developed world.

ObjectiveThe aim of the project is to design and fabricate a micro air vehicle by developin g a technique which optimizes a selected design space to get an optimal configuratio n.

A 3D view MAV configuration 2

Methodology Studying basics of optimizatio n methodology. Exploratio n of two different design spaces and selecting their input parameters. Optimizatio n of these configuration s on the basis of output performanc e parametrs .

OptimizationThe optimizatio n of these configuration s is done by first selecting the ranges of these input parameter s and then



DESIGN AND FABRICATIO N OF A SCALED DOWN MODEL OF AIRSHIP FOR SURVEILLANCE, RECONNAISSANC E AND ADVERTISEMENTPIA Off Umair Ahmed, PIA Off Zain ul abidin Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor Wing Commande r Azhar Sajjad Date of completion: 17 March 2008 Sponsorin g Agency: Aerospac e Department

Introduction/AbstractAn airship is a lighter than air vehicle. In the present era it is mostly used for advertisemen t and aerial photography . The airship utilization. size Historicall y varies the depending largest upon airship their was DESIGN The conceptua l design was developed and weight was given the utmost importance . Negative buoyancy was considered as to ensure safe recovery and the vertical lift was generated by brushles s motor/propeller combination . Directiona l control an d forward motion was achieved with the help of two DC motors. The structure was developed in solid edge and analyzed in Ansys Software. FABRICATION The fabrication was selected for undertaken with due consideratio n of hull, Styrofoam for to available resources and material. Balsa wood was manufacturin g gondola and stabilizers. Gigs were prepared for bending of frames, and assembly of the hull. used for joining of structure. THEORETICA L STUDY gondola. SCOPE OF THE PROJECT The DETAIL DESIGN scope of the project ability to was plan applicatio n and of Toughlon Epoxy resin was was used as RECOMENDATIONS

approximatel y 1800 ft long. With the advancemen t of technology they can also be employed for surveillanc e and reconnaissance. Objective The objective of this projec t is to design and fabricate a small airship having the following capabilities i) ii) iii) capable of outdoor flight To have the ability to capture images and transmit them to the ground The final product could be used for aerial photography , advertising purpose Methodology surveillanc e and

outer covering to the structure. All avionics was set up in

CONCEPTUA L DESIGN

theoretical knowledge,

execute

developmen t work at the same time explore options and MATERIAL SELCTION possibilitie s for solution of problems experience d at different stages. FABRICATION Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur

BE Projects Compendiu m 64 EC

Study of Material Characterizatio n Method And Determinatio n of Microstructur e of Ferrous and Non Ferrous Alloys by Using an Optical Microscope

Plt Off Farrukh Nawaz Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor Gp Capt Fahim Hashmi Date of completion :17 March 2008 Sponsorin g Agency: Aerospac e Department of ferrous and non

Introduction/AbstractThe using aim of the project is to study and analyze with basic the microstructur e of ferrous and non ferrous alloys by proper metallographic techniques for along establishmen t of a well equipped metallographi c facility in CAE which can be utilized metallographi c Objective M ain objective of the characterizatio n . The secondary objectives are to establish specimen preparation laboratory and commissionin g of optical microscope for metallographi c and fractografi c analysis intended to be used for educationa l and research purposes. Methodology LITERATUR E REVIEW project is to learn basic metallographic techniques which are used for material techniques material s science and engineering . teaching and researc h in the field of

Analysis The analysis of microstructur e

Metallographic Results

ferrous alloys including

plain carbon steel, alloy steel,

austenitic stainless steels and aluminum alloys was done by identifying different phases observed in their respective microstructures. Heat treatment s done on each material was validated through the microstructura l results obtained. The expected behavio r of the material was also predicted along wi th effect of different alloy constituent s on the properties of the material. Sensitizatio n effect in austeniti c stainless steel was also studied through AISI 4130 (Annealed) . The structure is ferrite and pearlite at 500 X, 4% picral as etchant. microexaminatio n of welded parts, along with the processes required to control sensitization . More over a comparativ e study to determine the major changes caused in the microstructur e under different service conditions was also carried out. Conclusio ns The project is a successful attempt in preparing a facility which can be utilized for future research projects relating to material sciences. Important decisions relating to repair and replacemen t of material can be made. AISI 321 (serviced) Micrograph shows partially recrystallize d austenit e grains, some carbide particles; the whole matrix is austenite at 500 X, 15ml HCl, 10ml HNO3 and 10ml acetic acid used as etchant.

ESTABLISHMEN T OF A METALLOGRAPHI C FACILITY

SPECIME N PREPARATIO N FOR METALLOGRAPHY

The service condition of a material for a particular task can be established. Heat treatment s can be verified through metallographic examination.

METALLOGRAPH Y OF FERROUS AND NONFERROUS ALLOYS

This metallographi c facility can contribute significantl y in aircraft accident investigation s relating to material failure .

ANALYSI S OF RESULTS



Stress analysis and Structural Refinement of an AMF Drone COMET using ANSYS softwareP/O MUEED LIQAT Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor Wing Commande r Abdul Munem Khan Date of completion :17 March 2008 Sponsorin g Agency: Aerospac e Department

Introduction/AbstractThis to project is one of the application s Method of that an is DETERMINATIO N OF LIMIT AND ULTIMAT E LOAD Analysis The physical dimensions of the structural members were measured and drawings were created , from which complete FEM model for the drone was created . The load profile was generate d from the aerodynami c anal ysis carried out earlier .Tensile and bending tests were performed to determin e the material strength .The load profile and constraint s were The objective of this project is to benefit PAF by identifying the high stress areas, causes of failure and applying differe nt refinement s to the structure to overcome failure. Methodology PARAMETRIZATIO N OF GEOMETR Y OF THE STRUCTURAL COMPONENTS IDENTIFICATIO N OF MATERIAL S AND THEIR TESTING CREATION OF FINITE ELE MENT MODEL Conclusio ns The material used for the wing is very weak thus applied on the model. Stress concentratio n areas and failure causes were determined , Structural refinement was carried out to overcome failure modes. The limit and ultimate load factors were determined Complete FEM Model of Comet FAILURE MODE AND EFFECT ANALYSIS excellent technique , Finite Element

perform structural analyses of COMET drone. Comet is

the scaled up model of BAZZ and had several occurrence s of failure. The state of art software Ansys was used for this work. After Modeling of the FE model load profile were generated based upon the aero dynamic analysis carried earlier. From stress analyse s results high stress areas and possible causes of failure were to be found . Based on these results structural refinement has also been done. Objective

indicating flaw in manufacturin g method Absence of ribs caused the maximum stress on the skin at the bolts.

LOAD PROFILE CREATION DETERMINATIO N OF STRESS CONCENTRATIO N AREAS AND FAILURE CAUSES Change of structural geometry was also required in addition to improvemen t of material strength. Stress concentratio n areas



Redesigning of Fuel System of Super Mushshak AircraftG Cdt Ali Hammad Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor: Wg Cdr Omar Ameen Qazi Sponso ring Agency: AHQ Fuel imbalance between the two wing tanks. Fuel vapourisatio n leading to fuel starvation in various phases of flight. Analysis of fuel system led to identificatio n of following possible causes for these problems. Differenc e in layout of fuel feeding pipes on left and right sides of the aircraft. Vapourisatio n due to change in ambient conditions at altitude leading to vapour lock in certain conditions . Vapourisatio n in wing tanks due to fuel sloshing during manoeuvre s. Non-availabilit y of indication system for pilot to identify fuel feeding problem in the initial stage before fuel imbalanc e goes out of limit. Analytical analysis was carried out wherever possible to quantify the effect of each factor and to study the effect of possible solutions. Vapourisatio n due to change in ambient conditions cannot be controlled without installing a pressurisatio n system. excessive for SMK The requirement s of aircraft and are

IntroductionPAF has experienced some problems with the fuel system of Super Mushshak (SMK) aircraft. The aircraft has a gravityThe reported defects fed fuel system which is supplemente d by a fuel booster pump in critical phases of flight. with fuel indicatio n system. problems. The current project was floated as the initial study to identify the problems , ascertain their causes and to propose feasible solutions. include fuel imbalance , improper feeding and problems CAE was tasked by AHQ to redesign th e fuel system of SMK aircraft to eliminate these

pressurisatio n system were considered to be not recommended. Vapourisatio n in wing tanks due to fuel sloshing can be controlled A through modi fication further has compartmentation .

been proposed that would reduce the effect of this factor but it effect could not be quantified exactly. The recommendation s of a previous project to install digital gauges and individual flow indicators for both tanks were further strengthen ed by this study.

ObjectiveThe aim of the project was to identify problems in the existing fuel system of SMK Aircraft and to propose viable solutions to address these problems.

ConclusionsThis project has laid out the general framework for a detailed analysis can of SMK fuel system for elimination of its existing problems . project carried out The recommendation s of this project at CAE to formulate a viable

MethodologyThe first step in this study was to gather defects data for SMK aircraft fuel system. from the following sources: Discussion s with aircrew. Flight line defects data for the current year. . Defect history and trend analysis from Control squadron. The collected data highlighted three main problems with the fuel system. Fluctuation s in fuel level indicatio n system. This data was collected

AnalysisThe study concluded the following: Differenc e in layout of fuel feeding pipes on left and right sides of the aircraft can generate a fuel imbalanc e of only 1.4 gallons in one hour of flight. Therefor e this factor was not considere d critical. However, an increase in pipe dia on right side is suggested to eliminate the existing differenc e in fuel flow.

be further analysed in conjunctio n with a previous

modificatio n plan for the aircraft.

. Avionics Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur


Determinatio n of Anisotropy in Toughness of Aluminium alloy 2024 T3 plate using the Impact Toughness TestPlt Off Muhamma d Habibullah Siddiqui Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor Gp Cap t Fahim Hashmi Date of completion :17 March 2008 Sponsorin g Agency: Aerospac e Department

Introduction/AbstractThis research was carried out to investigat e the effect of specimen orientatio n on the impact toughnes s values of the Aluminiu m alloy 2024 T3 and compare the values with some know n results to verify the reliability of the work and alloy. Objective The objective of the project is to quantify the existence of anisotrop y in toughnes s of an alumini um alloy 2024 T3 plate using the impact test. There is a further need to establish the direction in which the impact toughnes s of aluminium alloy 2024 T3 plate is maximum and minimum. This is to ascertain the integrity of aircraft structural component s in PAF so that whenever a new componen t is designed the direction of maximum toughnes s is kept in mind to economiz e the weight and the amount of material used on the aircraft. Moreover, the validtaion tester at CAE is required M ethodology THEORETICA L STUDY of the results of the impact to establish the anisotropy in toughnes s of the said Analysis

FRACTOGRAPHY

Table of ResultsSPECIME N NO. ORIENTATION 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 MEAN VALUE ASTM VALUE ABSORBE D ENERGY (JOULES) L-S(A) 15 15.5 15 13 14 15.5 16 15.6 15 17.51 16.1 15.5 14.6 14.4 15.25 13.96 15.65 14.23 15.10 15 L-T(B) 9 10 9.5 11 10 10.5 10.11 9.52 10.7 11.29 10.1 9.02 9.9 10.6 11 11.29 10.7 11.2 10.30 10 T-S (C) 20.5 20 19 20.1 21.46 19.95 18.81 20.79 19.1 19.5 20.79 19.46 19.83 20.13 20.13 20.13 20.13 20.13 20 N/A T-L(D) 16 15 16 16.5 16.87 16 16.23 15.9 16.23 15.6 16.87 16.23 16.23 15.6 16.87 16.87 16.23 16.23 16.20 N/A

The specimen s of four different orientations : L-S, L-T, T-S and T-L which were machined at NCNDT, Islamabad , were analyse d using the Charpy impact toughnes s test. Overall, 72 specimen s orientation, keeping in mind the ASTM E 23 standard specifications . results were astoundingly clear that the The T-S were tested, 18 of each

orientatio n is the toughest orientatio n of the plate absorbing 20 J of energy on impact. There was no similarity in absorbed energy of the four showing that the toughness values of the plate are anisotropic . Furthermore , error analysi s of each orientation with the known ASTM standard values was carried out and the results were within 6% variation which verified the reliability of the experiments. Fractographi c analysis of each specimen orientation was also carried out which showed remarkabl e differences in ductile and brittle regions for different orientations. Conclusions specimen orientation s

Graph of Results

MATERIAL COLLECTION SPECIME N PREPARATION

The T-S orientation is the toughest orientatio n of the plate The error analysis verified the reliability of the experiment s and results The project provides a comprehensiv e data for further work in this aspect of material sciences. Fractographi c analysis provides a microstructural verificatio n of the anisotrop y of this alloy plate.

EXPERIMENTS

COMPARISO N OF RESULTS



Design, Fabrication and Testing of Laminated Honeycomb Specimens used for Lightweight Aircraft Applications and Comparison with FEM Results

ntroduction/Abstractaminated honeycomb structures are efficient lightweight aterials , and consist of two thin and high-strength skins or face anels bonded to a thick and lightweigh t core. The aim of this roject was to select various design and finally panel aircraft parameter s c( ell shape, cell ize, core density core depth, lamination type, bonding agent, dhesive, dimensions) application s , and of fabricate its high because for ghtweigh t strength

Analysis

Sub/Lt Nosher khan, Sub/Lt Junaid Irfan Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor Wing Commande r Abdul Munem Khan Date of completion: 17 March 2008 Sponsorin g Agency: Aerospac e Departmen t , CAE The project provides an understandin g that dimension s C364-94 C365-94 C393-94Type of Test Cell size (in)

Specimens were prepared as per Edgewise Compressiv e Tests Flat wise Compressiv e Tests Three Point Bending Tests

prescribed

honeycomb Sandwic h Panels can be used in smart structures where high stiffnes s along with most important property of structure i.e. weight saving is required

by ASTM Standards for different tests as are given below:

Table of ResultsExperimental Results 3.467 3.12 2.053 1.898 1.237 1.449 ANSYS Results 3.748 3.324 2.142 2.138 1.354 1.596 Percentage Difference 7.49% 6.137% 4.15% 11.2% 8.7% 9.12%

Series of strength tests were carried out on aluminum honeycom b-cored sandwich panel specimens in three point bending , flat wise compressio n and edgewise compressio n loads on Universal Testing Machine, and 10 Ton Testing Machine available in CAE. Effect of the change of the cell size, and core density wasobserved in all the experiments . Also the difference in propertie s between Aluminum Facing Honeycomb Sandwich Panels and of Glass Fiber Facing Honeycom b Sandwic h Panels was investigate d in three point bending tests. Specimen s of the same dimension s as for experiments were modele d in ANSYS software by using bottom up approach. Load was applied in same manner as was applied for three types of conducted experiments, and non linear analysis was done. And required results (displacement s and stresses) were obtained. Test Results0.25(Aluminum Lamination) 1.571 1.726 9.03% Edgewise compressive strength (MPa) 3 Pt Bendin g test for Core shear strength (MPa) Flat wise compressive strength (MPa) 0.125 0.25 0.375 0.25 0.375 0.25 (GFRC Lamination) 0.375 (GFRC Lamination)

to eight ratio.

Perform ing FEM Analysis was an important part for omparison of the experimenta l results.

bjectivehe main aim of this project was to design, fabri cate, and vestigate sandwich anels of investigatio n was o determine the structural failure characteris t ics of aluminum andwich panels because due to their design they exhibit very pecial failure modes such as buckling, shear crimping, face heet wrinkling, face sheet dimpling, and face/core yielding. ethodology THEORETICAL STUDY EXPERIMENTAL TESTING& ANALYSIS MATERIAL SELECTION FABRICATION& FEM MODELING IN ANSYS the strength with characteristic s of aluminum core aluminum honeycom b

experimentall y and omputationally using FEM. The major area

1.250

1.358

7.95%

Conclusio ns Flat wise compressiv e stress, edgewise compressiv e stress, and core shear stress has been determine d from experiment s and FEM Analysis. There is some differenc e between experimenta l and analytical results because of Geometri c and Material Nonlinearities , and also because of human errors.


Flat wise compressiv e stress

3 Pt. bending specimen

erospace Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur


FABRICATION OF A FULL SCALE WEAPON CAPABLE UAV (KILLER DRONE)Plt/Off Aamir Dawood Plt/Off Waqas Nazar Nust/Cdt Salman Ahmed Nust/Cdt Umair Sufyan Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor Sqn Ldr Messam Abbas Naqvi Date of completion :17 March 2008 Sponsoring Agency: Aerospac e Department

Introduction/AbstractThe emerging need for sophisticated , intelligent unmanned aerial vehicles has been the center stage of aviation for the last decade . Pakistan Air Force is a hitech air force with a vision to empl oy UAVs as a major componen t of their air- defense network. Air dominanc e with computer controlled highl y maneuverabl e lethal aerial vehicles minus the human stress endurance limitations , is the vision worth pursuing. Former efforts include target drones and small size emissary UAVs . Recently , the task of developing a weapon capable UAV was undertake n at CAE to fulfill the operational requirement s of PAF . In the initial phases a conceptual design of a diamondwing-configuratio n UAV was presented an d verified by a successfu l flying half scale model. Based on this designs success, detailed design of a full scale UAV was carried out including the CFD analysis to validate the basic design parameter s. Th e current project aimed at the full scale fabrication of this unique UAV design . Th e challengin g task was successfull y accomplishe d in a short span of 20 weeks. The UAV is completely made of composit e materials and is capable of carryi ng explosive payload up to 50 Kg and cruise at a speed of 1 45 knots at an altitude of 7000 ft.

ObjectiveThe aim of the project is to fabricate a full scale remotely controlled, GPS navigated and weapon capable unmanned aerial vehicle (UAV ).

Conclusions Refining of design features helped us to relate theoretical knowledge with practical experience. This project was helpful in comprehensio n and implementa tion of the complete aircraft fabrication process.

Methodology Studying the conceptua l and detailed design of the UAV. Refinemen t of the final design configuratio n and systems identification. Exploratio n and selection of the fabrication processes in composit e constructio n. Full scale fabricatio n and systems installati on .

UAV under fabrication

FabricationThe fabricatio n was started by generating manufacturing drawings for templates , foam to which exact were shape used and to wire cut polystyren e foam modules (i.e. fuselage, wing s, vertical tail etc). Hi -stress bearing areas were frame further strengthened . making proper Engine seating mounting for them. Surface was installed in the fuselage. Wings were joined to contours.

Fiberglass layu p was performed on these exact shaped

the fuselage after removal and

Access hatch was made on the fuselage for fuel tank access to electrical system. finishing and painting was done afte r this. Lastly landing gears were attached along with engine installation.

Fully fabricated killer drone





Finite Element analyses of M irage aircraft using commerciall y available Finite E lement software, ANSYSSG/C Muhamma d Ali, PIA Off Muhamma d Ayaz Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor Wing Commande r Abdul Munem Khan ate of completion : 17 March 2008 Sponsoring Agency: Mirage Rebuild Factory, PAC, Kamra

Introduction/AbstractThis project is an applicatio n of Finite Element Method on a fighter aircraft for determinin g high stress areas and to do necessary fatigue calculation s. This project is a continuation project; was profile was prepared using available data and statistical techniques . Project was broken down in two part s; stress and fatigue analyses . From stress analyses results obtained Kamra. Objective The objective of the project is to estimate high stress areas and calculate fatigue life of Mirage aircraft. These results would be helpful for MRF in conducting third overhaul of Mirages and different inspections. MethodologyVERIFICATION OF THE MODEL

stress no.26

areas

were

obtained

from

the

results

of

stress analyses which mainly are main spar, bulkhead and wing-fuselage main attachment. The results analyses for of mission were performed flight namely thus obtained were compared with the results obtained from MRF Kamra. Fatigue using data conditions . Three types from stress analyses different profiles

Stress Analyses Results : Von-Mises Stresses

in

the

last

semester

FE

model

prepared. ANSYS was used for this work. Load

cruise (Navigation) , ge neral and severe combat mission were prepared for fatigue analyses to simulate the behavior of Mirage completely . Predicted life of Mirage is obtained by fatigue analyse s and the results are shown in the table. Conclusions The correctnes s and completenes s of the model is verified and it is ready for further analyses. Stress results are in complete accordanc e with results prescribed in manual s by the manufacturer. There is not much stress on the skin except the skin in the vicinity of main spar and bulkhead no.26. Since main wing fuselage attachmen t and main spar are the principal structural elements, therefore, their fatigue life is basically the structural life of the aircraft. Displacemen t Vector Sum

high

stress

areas

were

obtained to venture into fatigue analyses . All the results from anal yses were duly verified from MRF

STRESS ANALYSES FOR 1- g AND 6- g LOAD CONDITIONS

FATIGUE ANALYSES

Table of ResultsFatigue Calculation Results: Main Spar Life Type of Mission (hours) Severe Combat 2433 Mission 9133.62 General Mission Simple Cruise 45021.28 Mission Attachment Life (hours) 3248 12069 55695

COMPARISON OF RESULTS

Analysis Load profile for delta wings of Mirage aircraft was constructed . Stress analyses were done by applying loads and suitable constraint s on the FE model of Mirage. High

Aerospac e Engineering Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur


Developmen t of software to design and optimize performanc e of a centrifugal compressor for different design features considered for variety of fluidsNUST CADET Awais Iqbal Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor: Sqn Ldr Abdul Naeem Khan(Retd) Date of completion :17 March 2008 Sponsoring Agency: CAE

Introduction/AbstractCentrifuga l compresso r was first developed during the Second World War by the Bri tish. Since then it has been widely used in aerospac e application s as well as in industry. Although, compresso r application s use in small but the developmen t its use in of find axial its

Met hodology Studying basics of flow in turbo machinery. Derivation of equations for each componen t of centrifugal compresso r from governing equations. Equations for each componen t are solved iteratively to reach design. Software and GUI developed in MATLAB

Conclusion The software developed calculates all the values of the geometric parameter s of a centrifuga l compressor . The algorithm is developed in such a way that it involves the design optimizatio n of all component s as well as their interaction with each other. Complete theoretical analysisof the centrifugal compresso r has been done following the onedimensiona l approach. Because of simplifying assumption s made to make theoretical analysis possible actual flow in a compressor will be somewhat different but the values obtained from the software developed , can serve as the initial step of a complete design process. Besides the complete design of centrifuga l compressor, the effects of change in various geometric parameters on performanc e of a centrifuga l compressor are also shown in the form of plots. A user friendly GUI makes the design process easy.

has minimize d

aerospac e

still centrifuga l

compresso r

turboprop engines. They are still widely

Ana lysisThe requiremen t to develop software to design and test the performanc e of a centrifuga l compresso r to optimize pressure ratio for different design features considere d for variety of fluids called for an Inverse Design Approach . Inverse Design Approach parameter s given that of of is determinin g of geometri c from based the on a centrifuga l compresso r parameter s

used in industry where they hav e many advantage s over axial and piston compressors. The flow pattern in threedimensiona l flow passage of the impeller of a centrifuga l compresso r is very complex . For simplificatio n the flow in centrifugal compresso r is considered in the radial -axial (meridional ) by plane. it Further to be simplificatio n inviscid. An in theoretica l for analysis of flow through centrifuga l compresso r is obtaine d assuming approach determinin g geometric parameter s of centrifugal compressor from the specified performanc e requirement s is discussed in this project and a computer code along with graphical user interface is developed to calculate these geometric parameters.

performance requirements . The opposite process calculating performanc e inputs is usually called analysis or direct

geometri c

calculation . An algorithm and compute r code implementin g the Inverse Design Approach is developed . The geometri c parameter s separatel y for from each component are calculated required performance parameter s and

ObjectiveThe aim of this project is to develop soft ware which is capable of calculating all the geometri c parameter s required to obtain specific performance . A Graphical User Interface is also to be developed to interact with the user during design process and to make design process easy to understand.

then are integrated to check that the required performanc e of the whole machine is achieved. If the desired performanc e parameter s are not achievabl e the software displays error message and also guides the user in this regard. Similarly for unrealisti c inputs or outputs the software displays appropriat e error messages.

ge of Aeronautica l Engineering , PAF Academy Risalpur

Aerospac e Engineerin g Department , PAF Colle


Design and Fabrication of a Smoke-Tunnel for Visualisatio n of Dynamic Flow BehaviourPlt Off Zakria Ghazanfar Toor Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor: Wg Cdr Omar Ameen Qazi Sponso ring Agency: CAE with computerise d control of pitch and rate of pitch.

IntroductionSmoke-tunnels are used as training aids for visualisatio n of flow behaviour around aerodynami c objects. problems . They can also be used for experimenta l investigatio n into flow At CAE, a smoke tunnel is used for flow to students as a part of the curriculum. demonstratio n

Methodology Literature survey and study of the existing design. oil droplet Preliminar y design and m arket survey for component s. Detail design and production of manufacturing drawings . Design and programmin g of computer interface Fabricatio n of the final design. Operationa l testing of the smoke tunnel. Developmen t of users manual. Completio n of project report. The

However, the following improvemen t were desired in the design of the existing smoke -tunnel: In has this Increase in operation time Enhancemen t of stream density at mid-section Computerise d control of pitch and rate of pitch Possibilit y of using Laser Doppler Anemometry project, design the and fabrication of a smoke above Fan and was

AnalysisThe final design of the smoke -tunnel fulfils all projected design requirements . of operation for an extended period of time. used for -tunnel tunnel. to conduct measurement s through LDA technique. demonstratio n in the The models smoke In existing The new wind tunnel is capable

(LDA)equipmen t for experimenta l investigations -tunnel incorporatin g features highlighted

been undertaken .

Conceptua l design, detail design

and fabrication of the equipment was completed. Computerised control

smoke generation modules were developed indigenously . interface developed using LabView software. Conceptua l design for installation of LDA equipment has also been carried out. Compatibilit y of design with the existing smok e tunnel was ensured to facilitate the use of existing model s with the new smoke tunnel.

in Aerodynamic s Lab can be used with the new

addition, the tunnel ca n be fitted with seeding equipment

ConclusionsThe design caters for requirement s of fluid flow demonstration to supplemen t BE curriculum at Aerospac e Departmen t and also provides a tool for experimenta l i nvestigation s of Boundary layer flows. . .

ObjectiveThe aim of the project was to design and fabricate a smoke tunnel with the desired stream density and operation time and

Avioni cs Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur


Tensile and Fatigue testing of adhesively bonded metal structures in the constructio n of light weight aircraftPlt O ff Muhamma d Sohaib Aerospac e Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor Sqn Ldr Ahmad Junaid Date of completion :17 March 2008 Sponsorin g Agency: Aerospac e Department

Introduction/AbstractThe aim of this research is to investigat e the effect of replacing riveting in aircraft structures by adhesive bonding bonding. Amongst the three generally acce pted methods for joining structural accomplishe s reactions. Objective The aim of the project was to analyze the adhesivel y bonded structures through tensile and fatigue testing. The objective was to develop the pragmati c approache s used in aircraft industry related to adhesive bonding by carrying out structural fatigue tests in butt joint configurations , single lap shear tests to determine lap shear strength in single lap joint and tensile tests to evaluate tensile strength in butt joint configuration. Methodology THEORETICA L STUDY OF ADHESIO N THEORY members , adhesive the strength of structures through chemical

Analysis Three different engineering metals were selected for

Table of Results

Adhesive

analyzing adhesive bonding and they were Aluminum, Stainless Steel and Nickel. One alloy for each metal was selected : K500, etching AA 2024-T3, Each SS alloy cleaning, 400 was and MONEL to chemical respectivel y. with subjected

pretreatment s like solvent mechanica l etching with

priming,

acids, chemical etching with alkali and

sand blasting for surface preparation . Each prepared plate was bonded using five different adhesives in different combination s of constituent s, by weight. Shear tests were conducted as per Japan Industrial Standard JIS K6850. Fatigue butt and tensile tests were to conducted in Industrial joint configuration according Japan

EPOWELD 13230 REDUX FILM 775 ARALDITE 2014 CYTEC FM 47 BETAMATE XD 4600

Chemical Chemical Chemical weightage weightage weightage 60/40 70/30 80/20 7.76 7.88 8.20 8.12 8.44 6.88 9.66 8.24 8.55 6.96 9.81 8.34 8.91 7.20 10.06

Standar d JIS K6849. for all materials

Failure strengths in all three cases,

Fractograph y of SS 400

were compared for different adhesives , surface treatments and weight compositio n of adhesive. Fractograph y of study SEM fracture (courtesy the failed surfaces was done to

MATERIA L SELECTION SPECIME N PREPARATION EXPERIMENTS

characteristic s of bonded

joint,

using

Mech Engg Dept GIKI Topi). Conclusio ns Adhesive Betamate XD 4600 provided the best shear strength for all weight combination s of resin and hardener. Adhesive Redux Film 7 75 gave best tensile strength characteristic s. Araldite 2014 gave the best fatigue strength characteristic s.


(Courtesy Mechanical Engineering Department, GIKI Topi)

Intergranula r features on SS 400

FRACTOGRAPHY



Display and Enhancemen t of the Output of Thermal Imaging SystemPlt/Off Akhunzada Ilyas Said PIA/Off Nizamuddin Avionics Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur AdvisorGp Cpt Abdul Rehman Sponsorin g Agency: Avionics Department

Study of completed student projects on thermal imaging systems.

Conclusion Thermal images have been successfull y acquired and displayed on PC monitor and flat panel display. More work on image enhancemen t needs to be done on the acquired IR images.

Introduction/AbstractCAE is conducting R&D in the field of thermal imaging. So far, more than 20 student projects have been completed in different areas related to thermal imaging. The objective of this project is to acquire the IR thermal image of an existing system for image enhancemen t applications. A detailed study of the completed techniques project were reports to flat

Evaluatio n of different techniques for acquiring IR image. Study of the data acquisitio n schemes to acquire the IR image. Study of the video display of the PC and flat panel display.

was undertaken . Various

studied

Study of microcontrolle r for acquiring and displaying IR image on flat panel display. Study of parallel port and image acquisitio n card for acquiring and display ing image on computer monitor.

interface the existing thermal imaging system with display and image acquisitio n card for PC has been used. After acquiring the thermal image, different

panel display and PC. Finally, microcontrolle r for flat panel

image

Application

and

evaluation

of

different

image

Fig1: T he IR search system

enhancemen t techniques were

applied, evaluate d and

enhancemen t schemes. Development of a GUI to compare the effects of image enhancemen t techniques

the comparison of results is displayed in the form of a GUI.

ObjectiveThis project aims to acquire and display the IR image of an existing thermal imaging system on flat panel display and PC monitor, apply different image enhanceme nt techniques and evaluate their performanc e .

Analysis After acquiring and displaying the thermal images on flat panel monitor, display and PC monitor, technique various performs image On PC better Fig2: Enhanced thermal image shown on a GUI enhancement techniques have been applied.

Gamma correctio n

Methodology Study of the existing thermal imaging system.

than others. On flat panel display, only alternate raster scan is displayed due to faster scan information update rate.



Developmen t of a Palm-print Based Authenticatio n SystemSG/C Hassan Masood Avionics Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor, Sqn Ldr Atif Bin Mansoor Sponsorin g Agency: Avionics Department individuals.

Introduction/AbstractBiometric s-based personal identification an effective pattern method for hand, automaticall y including a is regarded as recognizing number a of

Implementatio n of classifiers for template matching. Evaluatio n of results on the developed database of images and the database of Polytechni c universit y of Hong Kong.

persons identity. Palm -print is the unique inner surface of human discriminatin g features, suc h as principal lines, wrinkles , etc. In this project a new and is images. The proposed for the personal identificatio n palm -print

Analysis The results obtained on the databases using different mathematica l transforms employing Euclidean distance base d classificatio n are.

singular points, texture reliable approach presented using

system consists of two parts. An indigenousl y made image acquisitio n system and an efficient algorithm for palm - print verification . The image dataset is acquired using a digital camera with a resolution of 200 dpi. The acquired images are pre-processed in order to remove translationa l and rotational invarianc e and then the palm -print is extracted. The obtained regio n of interest is analyzed for its texture using the DCT (Discrete Contourlet Transform) , the Contourlet tran sform and the FFT. Distinct features were extracted and were stored in templates . The both at the feature level employing the Euclidean Distance and the dot product classifier. The algorithm has been tested on the world largest database of 5400 images acquired from the Polytechni c University of Hong Kong Hand Image Databas e and also it has been verified on palm-print images from 120 users collected using the indigenousl y made imag e acquisition system. . Avionics Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur feature and vectors at the or templates level extracted from texture have been combined and tested decision Objective Reliability in the personal authen tication is key to the security i n the networked society. This project attempts to develop a reliable palm-print-based verification system by analyzing and extracting distinctive features from palm -print texture using different transforms of image processing. Methodology Study of image processing. Literature survey of existing biometric s and on going search in palm -print authenticatio n systems. Development of Image acquisitio n platform. User training and image acquisition. Image registration. Extracting features from the registered images and making a gallery containing the templates of registered It was analyzed that the results on the acquired database can be improved by removing the problem caused by motion blur and illuminatio n invariance . degraded Conclusion The successful demonstrated the completion effectivenes s of of the project has images was found authentication. The enhancemen t of effective in reliable

palm -print based

authenticatio n system. A novel Contourlet based feature extraction and classification encouragin g results. is investigate d that gave


Computer Vision Based Automatic Scoring of Air to Ground RangesPlt/Off Faizan Ali Avionics Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor Sqn Ldr Atif Bin Mansoor Sponsoring Agency: Directorat e Of Plans Image database development. Applicatio n of contrast stretching based on Power Law Transform to enhance the image in the spatial domain. Applicatio n of Morphologica l operations based on Erosion to facilitate implementat i on of the algorithm. Applicatio n of Hysteresi s Thresholdin g to segment the target from the backgroun d and the bullet hits from the target. Applicatio n of Distance Transform to locate the centre of the bulls eye and cropping the bulls eye out of the target. Labeling of bullet hits and scoring based on eight pixels connectivity.IMAG E SEGMENTATIO N BY HYSTERESIS THRESHOLDING THICKENIN G THE BOUNDARIE S OF FOREGROUN D PIXEL S BY EROSION

implementatio n of the system.

Introduction/AbstractScoring at PAF Air to Ground ranges is presently done manually where a scorer is detailed to count the number of bullet hits after the aircrafts firing mission. The pre sent scorin g system is time consuming and also raises safety issue s for the scorers present on the firing range. This project attempt s to replace the present manual scoring system with a compute r vision based automati c scoring system. It will considerabl y reduce the scoring time and is also safe and secure . A detailed literature survey was carried out which provide d the basic platform for the developmen t of the algorithm. Images of Air to Ground range targets were collecte d and then processed with the help of the algorithm developed based on digital image consists of image and image segmentatio n techniques which processing techniques . The algorithm enhancemen t separates the target area from the backgroun d and then distinguishe s the bullet hits from the target area.

BASIC STEPS IN ALGORITHMIMAGE ACQUI SITION

IMAGE ENHANCEMEN T BY POWE R LAW TRANSFORMATION

AnalysisAfter the developmen t phase of the algorithm, PAF Indus firing range was visited for testing and validation of the developed algorithm . The algorithm has an accuracy of 92.96% for real Air to Ground range targets. Scaled down version of strafing targets were made for simulated testing in the Lab environment . The results are: SAMPLES ACCURACY 98.3 %

LABELIN G AND SCORING

ObjectiveThe project aims to develop a computer vision LAB EXPS based automatic scoring system with the processing application s to automaticall y label and score the bullet hits on the strafing targets. help of Image

100

ConclusionThe developed system is able to automaticall y score the bullet hits on the strafing targets. It is much more efficient as compared to the present manual scoring system. A windows compatibl e the . Graphical User Interface is designed for

Methodology Literature survey. Development of the algorithm.

System Graphical User Interface

Avionics Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur


Design and Developmen t of Mobile EOD RobotP/O Altaf Omer Khan Avionics Engineerin g Department , PAF College of Aeronautica l Engineering , PAF Academy Risalpur Advisor, Sqn Ldr Sarfraz Khan Sponsorin g Agency: Avionics Department microcontroller.

ConclusionThe Mobile EOD robot now has an improved motor circuitry. RF receiver has been interfaced integration with of motor driving circuitry throug h Successfu l microcontroller .

Introduction/AbstractInspired by the advancement in the field of Robotics, the project Mobile EOD Robot (Phase -III) was undertaken for making a prototype vehicle that can be used as an alternative to human beings for Explosive Ordinanc e Disposal (EOD) tasks. The project is an extension of the phase -II Mobile EOD robot. The phase II robot was driven through mechanica l switching. The mechanica l switches were actuated by

Finding the parameter s of the servomotor s used in the arm. Modeling and simulatio n of the joint of the arm in Simulink. Stability analysis of the joint. Addition of solar panel. View enhancemen t by using additional cameras.

microcontrolle r makes this robot more flexible. Availabilit y of backup solar power enhances the mission endurance . One additional camera has been installed at the front end to enhance the view.

AnalysisIn many application s motors are driven by motor driving circuitry normally known as h-bridge circuit. The circuit is used to drive the motor in both directions . The RF receiver gives out pulse modulated signals of variable duty cycle of 1 ms, 1.5 ms and 2 ms used for servo control. The task was to convert these pulse modulated signals into 0s and 1s required by the h-bridge circuit. Programmin g of 89c52 microcontrol ler was done to convert these PWM signals into logic inputs. Two channels of the receiver were utilized for this purpose with a motor being controlled by both of them. Joint wise stability analysis of the robotic arm has Figure 1: Motor Driving circuitry been carried out where each joint is a combinatio n of gears and servomotors . This involved th e calculatio n of unknown parameter s of a servomoto r and modelin g the joint in Simulink to simulate the response. The missio n enduranc e was increased by adding solar power capability vehicle which charges the battery with sunlight. to the

servomotor s to give bidirectiona l movement to DC motors in order to move the vehicl e in forward, reverse, right and left direction. Various up-gradation measures to the previous work have been undertake n in phase -III. It includes interfacing of RF receiver with motor driving circuitry, joint-wise stability analysis of additional endurance. robotic arm, view enhancemen t using cameras and solar power capability for more

ObjectiveThe project aims at improving the previously developed robot. The robotic vehicle is remotely controlled . A command and control station is required to be interfaced with the robot to control the movemen t of robot and make decisions.

Methodology a Study the previous system. Understandin g and implementatio n of driving circuitry. Interfacing of driving circuitry with RF receiver using

. Avionics Engineerin g Department , PAF College of Aeronautica l Engineering, PAF Academy Risalpur


Computer Aided Visual Inspection of Aircraft SurfacePlt/Off Mustafa Mumtaz Avionics Engineerin g Department , PAF College of Aeronautica l Engineering, PAF Academy Risalpur Advisor Sqn Ldr Atif Bin Mansoor Sponsorin g Agency: Avionics Department computationall y efficient computer aided visual inspection of through different methods like thresholdin g technique s of Otsu and Entropy, Gabor Filter for texture analysis, Nonsubsample d Network. Adaptiv e address Contourlet models Transform were and optimized Neural to

Introduction/AbstractVisual Inspection is, by far most widely used methods in aircraft surface inspection . This inspection is used to ensure structu ral integrity of aircraft surfaces. This project attempts to replac e have visual inspection Various by computer vision and machine intelligence . enhancemen t technique s

aircraft surfaces which would be beneficia l for PAF by reducing cost and repair time of maintenance.

Methodology Studying basics of Digital Image Processing (DIP). Real data collection by identifying and photographing different crack susceptibl e areas of aircrafts. Formulatio n of suggestion s for ni clusion of surface imaging in existing periodic inspections. Study of various enhancemen t techniques for their applicabilit y to the project. Optimizatio n of parameter s for automati c crack marking system. Testing and evaluating various methods to differentiate between crack and scratch. Optimizatio n of algorithms to decrease FAR (False Alarm Rate).

random illuminatio n variations . Differentiatio n of

crack and scratch was performed through various methods like Neural Network Classifier, Discrete Cosine Transform in collaboratio n with Dot Product Classifier and energy calculation s via Wavelet Transform in order to minimize critical aircraft FAR. A set of 400 images of differen t

been applied to get better analysis of surface like texture analysis,

cracks. Automatic marking of surface cracks has been performed by various techniques thresholding , various transfor m based and classifier based

surfaces were taken under various illuminatio n condition s over a span of five months. This data set was divided into training and validation set of 100 images each for surface scratch and crack. FAR of 3% was achieved for scratch and 10% for crack.

methods. This led to a set of generalize d techniques . A new visual method is devised to differentiat e between crack and scratch to supplemen t existing NDI techniques. In PAF, periodic inspection s are carried out according to work card and pre -defined manuals. Surface imaging is suggested i n existing periodic inspection s which assist in better record keeping identified and and trend prone analysis to of aircrafts. were Various areas of aircraft cracks

ConclusionThe project depicts intelligent utilization of DIP for specific applications . The project is capable of automati cally marking the cracks present in aircraft surfaces and for

AnalysisSurface imaging is suggested in existing periodic inspection for better record keeping and trend analysis of aircraft. The surfaces prone to cracks were photograph for 10 T-37 and 4 Mushshak aircraft weekly. Standard scale and angle were defined and maintaine d while photographing . Image enhancemen t technique s were implemente d for analysis of surface cracks to smoothen out light intensity variation, adjust contrast variations reduce blurriness, and increase sharpnes s. Automati c marking of cracks was investigated

differentiation of crack and scratch with an accuracy of 97% for scratch and 90% for crack. Suggestion s for surface imaging in existing periodic inspection s have also been formulated .

were photographe d weekly. Suggestion s

for conducting surface imaging at certain scale and angle were also defined. The propose d computer aided visual inspection techniques will reduce cost and repair time for maintenance , thus ensuring maximum utilization of aircraft for flying.

ObjectiveThis and project aims to develop cost effective



DESIGN & FABRICATION OF AN RF/MICROWAVE MEASUREMENT SYSTEM CONSISTING OF AN ANTENNA AND AN AMPLIFIER TO SETUP A RECEIVER IN THE 0.8- 1.3 GHz BAND

Paying Cadet Ahmed Hafeez Avionics Engineerin g Department , College of Aeronautica l Engineering , PAF Academy Risalpur Coordinato r : W//CDR IRFAN MAJEED S/L ABDUL MATEEN Sponsoring Agency: CAE

Literature review Theoretical and analytical design Modeling and simulation using IE3D and ADS Design optimization Fabrication Measurements

Introduction/AbstractThe aim of the project is to design and fabricate a measurement system to detect radiations in the frequency range of 0.8 1.3 GHz. The setup consists of an antenna connected to a Low Noise Amplifier. The output of the system is displayed on a spectrum analyzer. The system is a receiver system, therefore, it is required to have low noise and high gain characteristics. Th e antenna is log periodic type wi th printed dipoles on a thin sheet of copper clad silica -fiber (FR4). A 3V driven Low Noise Amplifier is connected to the receiving antenna. The amplifier in design has been simulated by modeling the ADS (Advanced Design Systems) antenna in IE3D and the Momentum. Fabricatio n of the antenna and LNA pad has

AnalysisThe log periodic printed dipole array antenna was designed using IE3D, a Method of Moments based simulation software. The amplifier circuitry was modeled in ADS. The whole system was 50 ohm matched. The results of the two are shown in table 1. Table 1

been done using LPKF PCB prototypin g machine.

Antenna Gain Antenna efficiency

8.5 dBi Average 69% average 800 MHz -20 dB average 28 dB at 1.3 GHz

compendium cae march 2008

Documents

project vis

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sufficient project details

optical microscop e

comparativ e study

abstrac t of best project

material characterization

material sciences