📖Program Curriculum
Course modules
Compulsory modules
All the modules in the following list need to be taken as part of this course.
Design and Analysis of Composite Structures
Aim
To introduce you to the composite materials, manufacturing techniques and analysis methods for the design of aerospace composite structures.
Syllabus
• Introduction; Types of composite materials, especially FRP composites.
• Overview of composites manufacturing techniques.
• Micromechanics and macro mechanics for stiffness and strength analysis of a FRP ply; Macro mechanics, constitutive equation, stiffness and strength analysis of a FRP laminate; Thermal and moisture residual stresses in a FRP laminate.
• Stress analysis of an open section FRP composite structure subjected to various loadings.
• Stress analysis of a closed section FRP composite structure subjected to various loadings.
• Design guidelines and examples for composite structure design and analysis.
• Computer programmes for laminate stress, buckling of laminate and stiffened skin.
The classroom assignment on composite manufacturing techniques will take place towards the end of this module. The date and time will be confirmed by the tutor. The assignment is a one hour written paper that will take place in the classroom under exam conditions. This assignment is formally assessed and is worth 25% of the marks available for this module.
Intended learning outcomes On successful completion of this module you should be able to:
1. Demonstrate an understanding of the key features and particular properties of composite materials, especially fibre reinforced plastics (FRP).
2. Apply analytical methods for the evaluation of moisture and thermal effects on a FRP laminate.
3. Able to evaluate the strength of a FRP laminate based on stress analysis and failure criteria.
4. Able to perform stress analysis of laminated composite structures with open and closed sections subjected to various loadings.
Fatigue, Fracture Mechanics and Damage Tolerance
Aim
To provide you with an understanding of the theories of Fatigue and Fracture Mechanics and show how these structural concepts are applied to the design and testing of aircraft structures and Airworthiness Certification.
Syllabus
• Design awareness: Philosophies of design against fatigue and design for damage tolerance: i.e. safe-life, fail-safe and damage tolerance.
• Fatigue analysis: Traditional S-N curve approach: calculation of crack initiation life; mean stress effect, notch effect; Miner’s cumulative damage rule for variable amplitude loads.
• Aircraft fatigue loads: Typical aircraft load spectra for use in the laboratory and computer simulation.
• Fracture Mechanics: Basic Theory of Linear Elastic Fracture Mechanics (LEFM): Stress Intensity Factor, fracture toughness, strain energy release rate; plane stress and plane strain, crack tip plastic zone; residual strength; prediction of fatigue crack growth. Numerical techniques for crack prediction and analysis.
• Damage Tolerance: Damage tolerant design methods and technologies for composites and metals. Fatigue monitoring in flight/service and structural health monitoring. Inspection methods. CAA and FAA Regulations and their relationship to Airworthiness Certification Material selection.
Intended learning outcomes On successful completion of this module you should be able to:
1. Appraise the importance of design against fatigue, especially for aircraft structures and explain the concept of the damage tolerance design and failsafe design.
2. Command the basic knowledge of Linear Elastic Fracture Mechanics (LEFM) and relate the theory of Linear Elastic Fracture Mechanics to estimate residual strength and crack propagation life of a structure.
3. Solve fatigue analysis problems using both crack initiation and crack propagation approaches.
4. Evaluate and select the most appropriate method; use data sheets for an engineering application.
5. Evaluate the regulatory authority requirements for airworthiness and damage tolerance.
Design for Manufacture and Operation
Aim
To ensure that while you design your structure they are aware of the constraint imposed by manufacturing and operational considerations.
The influence of designing for maintainability will have a considerable effect on the design of both the structure and aircraft systems and a considerable effect on the life cycle cost of the vehicle. The taught material will have immediate practical application to the Group Design Project.
Syllabus
• Metallic and Non-metallic manufacturing processes.
• Material and Manufacturing process selection with CES Edupack.
• Wing configuration and manufacture.
• Assembly and production processes.
• Maintainability and accessibility.
• Design for Assembly and Maintainability methods.
Intended learning outcomes On successful completion of this module you should be able to:
1. Understand the influence of design for manufacture and maintainability on both structure and aircraft systems.
2. Apply their knowledge and skills to the Group Design Project.
Detail Stressing
Aim
To introduce you to the techniques of detail stressing as practised in the aerospace industry.
Syllabus
The structural function of aircraft components. Definition of Limit, Proof and Ultimate loads and Factors for Civil and Military aircraft
Basic formulas for stress analysis. Stress strain curves for metallic materials. Material equivalents. Concept of Reserve Factors (RF) and Margins of Safety (MS)
Material data. Design guidelines for mechanically fastened joints. Lugs. Strength of bolted/riveted joints. Usage of approved aerospace components
Structures under bending and compression. Euler buckling, flange buckling, inter-rivet buckling. Buckling of struts and plates. Shear buckling of webs
Generalised stress strain curves
Plastic bending and form factors
Rivet and bolt group analysis
Analysis of thin walled structures
Preparation of a detailed Stressing Report and Reserve Factor summary tables for a classroom exercise to be completed during this module.
Intended learning outcomes On successful completion of this module you should be able to:
Apply the principals and techniques in stress analysis and airworthiness requirements to size basic aircraft structural components.
Evaluate the strength of a component and determine its ability to support an applied load.
Compare, propose and select metallic materials suitable for use in aircraft structures.
Acquire transferable skills to allow effective communication with company stress engineers.
Finite Element Analysis
Aim
To provide you with both an introduction to the theory underpinning finite element analysis (FEA) and hands on experience using the well-established FEA package.
Syllabus
• Background to Finite Element Methods (FEM) and its application
• Overview of element discretisation, FEA method, pre-processing, solution and post-processing, basic terminology, range of applications.
• Introduction to concepts of constitutive equations for linear elasticity.
• Introduction to concepts of nodal displacement, element shape functions for 1D and 2D linear-elastic structures.
• Introduction of FEA matrices, equations and critical steps to an FEA solution.
• Presentation of commercial FEA software packages.
• Presentation of FEA for mechanical analysis using various element types: bars, beams, 2D, 3D, shell elements.
• Presentation of FEA for heat transfer analysis, equivalence with other field problems, convergence issue, boundary conditions, model creation and solution.
• Presentation of CAD model, meshing, symmetry, model development, implementation of force boundary conditions, solution, and post processor analysis.
• Advanced FEA analysis: geometric non-linearity, material non-linearity, contact problems, dynamic problems, and explicit solution.
• Applications of FEA to enhanced mechanical designs: Optimisation
• Case studies on metallic and composite structures
Intended learning outcomes On successful completion of this module you should be able to:
Recognise finite element analysis (FEA) methodology and uses by comparing principles, assumptions and case studies to state-of-the-art.
Recognise and examine the limitations associated with the use of FEA in actual applications.
Demonstrate an approach for solving a range of actual problems.
Evaluate considerations for applying FEA to component modelling.
Critically assess the results obtained from FEA by comparing FEA solutions from fundamental matrix operations, constitutive equations and a commercial software.
Initial Aircraft Design
Aim
To introduce you to the process of aircraft conceptual design and support structural layout work, were required, through participation on the Group Design Project.
Syllabus
Aircraft project design process
Drag and weight prediction: Drag sources, polar, estimation, weight prediction methods. Layout aspects: wing; power plant; landing gear; fuselage
Simple tail plane and fin layout
Overall project synthesis and case study of aircraft
Structural requirements, - strength, stiffness and serviceability
Analysis of requirements, sources of load and reference datum lines
Role of structural members - main plane, stabilisers, auxiliary surfaces, fuselage
Analysis and sizing methods - elementary theories
Departures from elementary theories - constraint effects, cut outs, buckling.
Intended learning outcomes On successful completion of this module you should be able to:
1. Demonstrate a systematic understanding of the multidisciplinary nature of aircraft design.
2. Identify the functional role of the structural elements of the entire airframe.
3. Demonstrate an understanding of the top level aircraft design to put the detailed design of one aircraft component into context.
4. Perform a simple conceptual design synthesis of an aircraft and evaluate the design.
5. Apply their knowledge and skills to derive the initial structural layout of the Group Design Project aircraft.
Loading Actions
Aim
To provide you with knowledge of all the main loading cases including those encountered on the ground, in the air and those induced by the environment. This is the initial module on the course, its contents are fundamental and the taught material will have immediate practical application to the Group Design Project.(GDP).
Syllabus
• Standard requirements, their application, interpretation and limitations.
• Flight loading cases: symmetric manoeuvres, pitching acceleration, gust effects, asymmetric manoeuvres, roll and yaw.
• Balance equations: rigid airframe response, control movements and forces.
• Ground loading cases: Airload distributions.
• Structural design data: Inertia relief and effect on shear force, bending moment and torque diagrams.
• Factors: load factors, their basis and restrictions.
Intended learning outcomes On successful completion of this module you should be able to:
1. Estimate the design loads that act upon a major aircraft structural component using a simplified approach and evaluate these to isolate design cases.
2. Extend their knowledge and skills to the derivation of structural loads on the Group Design Project aircraft.
3. Demonstrate knowledge of the history and significance of the various airworthiness requirements.
Reliability, Safety Assessment and Certification
Aim
To provide you with an introduction to the aircraft airworthiness as well as knowledge of reliability assessment methods, safety assessment methods, and certification issues associated with the design of Aircraft Systems (including weapon systems and survivability). To familiarise you with current air accidents investigation techniques and processes.
Syllabus
• Airworthiness
• Reliability
• Reliability requirements – JAR25-AC.1309
• Probabilities of failure, MTBF, MTBR, etc.
• Reliability models – series and parallel systems, common mode failures
• Safety Assessment Analysis Methods
• Failure Modes and Effects Analysis (FMEA)
• Fault Tree Analysis (FTA)
• Reliability predictions
• Common Cause Analysis (CCA)
• System Safety Assessment Process
• Functional Hazard Analysis (FHA)
• Preliminary System Safety Assessment (PSSA)
• Air Accidents Investigation
Intended learning outcomes On successful completion of this module you should be able to:
1. Demonstrate an understand of the aircraft certification process and how aircraft design is driven by airworthiness requirements.
2. Identify system safety requirements.
3. Demonstrate a systematic understanding of the procedures and steps for system safety assessment.
4. Develop system reliability models and perform safety assessment at different levels.
5. Simulate and analyse system reliability.
Structural Stability
Aim
To provide you with a fundamental understanding of the buckling of thin walled structures and the ability to calculate the buckling load of a component.
Syllabus
The buckling of thin plates and thin-walled sections using the Rayleigh-Ritz method of analysis. Alternative methods of buckling analysis.
Timoshenko's method for columns.
Exact solution of differential equations.
Approximate solution of differential equations, Finite difference method, Galerkins method, Theoretical post-buckling analysis of plates in compression.
The concept of effective width for thin plates.
The behaviour of imperfect plates, Torsional-Flexural buckling of thin-walled open section columns.
The buckling behaviour and failure of stiffened panels, crippling of thin-walled sections, stiffened shear webs.
This module has additional accompanying tutorials and workshops as required, plus a laboratory demonstration of the compressive buckling failure modes of struts and stiffened panels.
Intended learning outcomes On successful completion of this module you should be able to:
1. Demonstrate a conceptual understanding of the buckling of thin walled structures and structural components.
2. Demonstrate the ability to predict buckling behaviour using hand calculation techniques.
3. Analyse the buckling and post buckling behaviour of simple thin walled stiffened panels.
4. Effectively use data sheets to analyse buckling of real structural components.
Elective modules
A selection of modules from the following list need to be taken as part of this course
Aeroelasticity
Aim
To introduce you to the importance of aeroelastic phenomena, basics of aeroelasticity and analysis methods for the design of aircraft structures.
Syllabus
• Introduction (historical review, aeroelastic phenomena and design requirements);
• Structural and aerodynamic stiffness;
• Static aeroelasticity: torsional divergence, control effectiveness and reversal;
• Structural vibration and modal analysis;
• Aerodynamic loads on an oscillating lifting surface;
• Characteristics of flutter and important design parameters;
• Methods for aeroelastic analysis (divergence and flutter speed prediction);
• Gust response of rigid and flexible airframes;
• This module has additional accompanying tutorials and computer workshops as required.
Intended learning outcomes
On successful completion of this module you should be able to:
1. Recognise the importance of aeroelastic phenomena and design requirements.
2. Explain the theory of aeroelasticity including static and dynamic aeroelastic problems.
3. Illustrate the approach for evaluating divergence and flutter speed of aircraft structures.
4. Demonstrate the application of knowledge to the practical design aspects of aerospace structures using available PC based computer programs.
5. Apply your knowledge and skills to estimate the flutter speed of the Group Design Project aircraft.
Aerospace System Development and Life Cycle Model
Aim
To introduce you to system engineering concepts, system lifecycle models and system design processes and methods.
Syllabus
• Introduction to Systems.
• Life Cycle Models.
• System Requirements.
• Systems Design.
• System Integration, Verification and Validation.
Intended learning outcomes On successful completion of this module you should be able to:
1. Demonstrate a understanding of the basic concepts of the main life-cycle models.
2. Discuss the advantages and disadvantages of these models.
3. Define and analyse system requirements and specifications.
4. Determine system development process and define the work to be performed at different development phases.
5. Apply development life-cycle models to the AVD Group project.
Aircraft Aerodynamics
Aim
The aim of this module is to provide you with the knowledge of the Atmosphere and of the basic aerodynamic characteristics of a conventional aircraft in the context of its mechanics of flight.
Syllabus
Atmosphere Mechanics: structure of the atmosphere, international standard atmosphere model, design atmospheres.
Air Data Systems: Pitot-static systems. Altitude, airspeed and Mach number. Air temperature and airflow direction detectors.
Basic flight mechanics: forces acting on the aircraft, balance and trim. The forces of lift and drag and their characteristic dependencies.
Powerplant thrust characteristics: effects of weight, altitude, temperature and Mach number.
Aircraft axis systems.
The aerodynamic aspects of the outline design process of a transport aircraft.
This module has additional accompanying flying laboratory tutorials in the Jetstream Aircraft. See Flight Experimental Methods (FXM).
Intended learning outcomes On successful completion of this module a you should be able to:
1. Demonstrate knowledge of the characteristics of the international standard atmosphere and design atmospheres.
2. Identify aircraft air data systems and air data measurement.
3. Identify the basic force system of a conventional aircraft.
4. Demonstrate an ability to calculate the principle aerodynamic forces of lift and drag.
5. Perform a simple initial aerodynamic design of an aircraft.
Aircraft Performance
Aim
To facilitate you in gaining fundamental knowledge of the theory of conventional fixed wing aircraft performance to a level suitable for an aerospace vehicle designer. In particular, to provide you with the ability to apply aircraft performance theory, practically in the context of aerospace vehicle design.
Syllabus
• Introduction to Aircraft Performance
• Aircraft Cruising Performance
• Aircraft Climb and Descent Performance
• Aircraft Take-off and Landing Performance
• Aircraft Manoeuvre Performance
• Flight Path Performance Estimation
• Aircraft Performance Measurement
A classroom exercise will be completed during this module. Solutions will be collected in by the tutor at the end of the module.
Intended learning outcomes On successful completion of this module you should be able to:
1. Have knowledge of the performance of characteristic of conventional fixed wing aircraft.
2. Understand and be able to apply methods of estimation of flight path performance.
3. Be able to assess and evaluate the performance characteristics of a conventional aircraft.
4. Appreciate the importance of airworthiness requirements in conventional aircraft.
Aircraft Power Plant Installation
Aim
To introduce you to the engine and aircraft-related aspects of the propulsion system, with the primary emphasis being placed on gas turbine engines.
Syllabus
• Simple gas turbine theory illustrating the effect of gas turbine cycle parameters.
• Relations between specific fuel consumption, specific range and thermal and overall efficiencies for various engine types including turbo-props.
• Choice of cycle for various applications.
• Brief assessment of engine size required and engine / airframe matching including the importance of the airworthiness performance requirements.
• Impact of engine rating on engine / airframe matching.
• Impact on engine installation of various systems required by the aircraft.
Intended learning outcomes On successful completion of this module you should be able to:
1. Understand how a propulsion system is defined.
2. Assess the performance interface between the engine and the airframe.
Aircraft Stability and Control
Aim
To provide an introduction to the fundamentals of aircraft stability and control.
Syllabus
• Stability, control and handling qualities relationships.
• Aircraft aerodynamic controls.
• Static equilibrium and trim.
• Longitudinal static stability, trim, pitching moment equation, static margins.
• Lateral-directional static stability.
• Introduction to dynamic stability, first and second order responses.
• Equations of motion and modal characteristics.
Intended learning outcomes
On successful completion of this module you will be able to:
Describe the concepts of: trim, stability and control.
Describe methods of providing static stability for a conventional aircraft.
Describe the modes of motion of a conventional aircraft.
Computer Aided Design
Aim
The aim of this module is to introduce you to the role of Computer Aided Design technologies in a modern Integrated Product Development process and provide hands-on experience of CAD using the CATIA v5 software.
Syllabus
• Introduction to Integrated Product Development (IPD) for aircraft design
• Overview of Computer Aided Design, Manufacture and Engineering tools and their role in IPD
• Introduction to CAD modelling techniques:
o Solid Modelling
o Assembly Modelling
o Parametric Design
o Surface Modelling
o Drafting
• Hands on CATIA exercises using CATIA v5 including fuselage and wing design exercises
• Using CATIA for the Group Design Project.
Intended learning outcomes On successful completion of this module you should be able to:
1. Explain the role of Computer Aided technologies in the aircraft development process.
2. Differentiate between Computer Aided Design, Computer Aided Manufacture and Computer Aided Engineering and understand the information flows between these tools.
3. Select appropriate CAD modelling techniques for a variety of design applications.
4. Use Computer Aided Design software to create simple 3D models using solid, assembly and surface modelling techniques.
5. Apply your knowledge and skills to design aircraft components as part of the Group Design Project.
Design of Airframe Systems
Aim
To expand the your knowledge of airframe systems, their role, design and integration. In particular, to provide you with an appreciation of the considerations necessary and methods used when selecting aircraft power systems and the effect of systems on the aircraft as a whole.
Syllabus
Introduction to airframe systems
Systems design philosophy and safety
Aircraft secondary power systems
Aircraft pneumatics power systems
Aircraft hydraulics power systems
Aircraft electrical power systems
Flight control power systems
Aircraft environmental control
Aircraft icing and ice protection systems
Aviation fuels and aircraft fuel systems
Engine off-take effects
Fuel penalties of systems
Advanced and possible future airframe systems
Intended learning outcomes On successful completion of this module you should be able to:
1. Identify the main airframe systems and explain their purposes and principles of operation; including Secondary Power Systems (Pneumatic, Hydraulic and Electric), Environmental Control Systems, Ice Protection Systems, Flight Control Power Systems and Fuel Systems.
2. Formulate the requirements that drive the design of the main airframe systems.
3. For each of the main airframe systems: differentiate the various architectures and reasons behind the differences; identify types of equipment and major components used and assess their principles of operation; and perform basic sizing analysis for systems and major components.
4. Appraise the effects of airframe systems power provision on aircraft power plants and analyse fuel penalties resulting from a given system’s presence on an aircraft by carrying out basic calculations.
5. Examine the reasons for, and propose possible types of changes, that may occur in airframe systems in the near future.
Flight Experience
Aim
To provide you with flights in the Flying Laboratory in support of the lecture course in Aircraft Aerodynamics, Aircraft Performance, and Aircraft Stability and Control. These flights are key for students who are from a non-aeronautical background, and will also serve as a refresher for the remaining students.
Syllabus
Measurement of aircraft drag and effect of flap (AD, SD & ASD).
Aircraft longitudinal static stability (AD & SD)
Avionic demonstration and inertial system accuracy (ASD)
Dynamic stability modes (AD, SD & ASD)
Intended learning outcomes On successful completion of this module a student should be able to:
Describe the flight test techniques used to measure simple aerodynamic parameters and assess navigation systems.
Describe the dynamic stability modes of a conventional aircraft.
Landing Gear Design
