Aircraft Engineering MSc

The aim of this module is to introduce students to the major issues faced in product development today, and show them how new technologies can be implemented to help overcome those problems. The module will focus primarily on Computer Aided Design but will also discuss Digital Mockup and Computer Aided Manufacture.

• Module introduction: introduction to integrated product development and the computer based tools used to support IPD
• Product development using integrated computer aided design
• Computer Aided Design principles
• Hands on CAD workshops
• Computer aided engineering tools: computer aided manufacture, rapid prototyping and digital product assembly
• Industrial Case Study 1: Computer Aided Design
• Industrial Case Study 2: digital mockup

On successful completion of this study the student should:

• Have a critical awareness of recent changes in the product development process that have been facilitated by computer based design tools
• Be able to differentiate between and evaluate the functions of different tools used in the product development process including Computer Aided Design, Computer Aided Manufacture, Computer Aided Engineering
• Have an understanding of the issues associated with managing CAD data including integrating and interfacing incompatible systems
• Have acquired the skills required to construct simple CAD models using parametric solid modelling and surface modelling in CATIA v5
• Be able to apply the knowledge they have gained to a novel aircraft design in a collaborative group design project.

The aim of this module is to explain the reasons behind the design choices to be made in the structural layout and manufacture of components such as wings and fuselages.

Component Design

• Wing design and manufacture
• Fuselage design and manufacture
• Undercarriage: shock absorbers and leg geometry, detail considerations
• Flaps and control surfaces: structural configuration and mechanisms

Structural requirements

• Strength, stiffness and serviceability
• Analysis of requirements, sources of load and reference datum lines
• Role of structural members: mainplane, stabilisers, auxiliary surfaces
• Departures from elementary theories: constraint effects, cutouts, buckling

On successful completion of this module a student should be able to:

1. Define the constraints imposed on aircraft design by manufacturing and operational considerations.
2. Review the influence of design for manufacture on the design of both structure and aircraft systems.
3. Evaluate the range of design solutions for aircraft component design.
4. Apply their acquired knowledge to an aircraft design problem

The aim of this module is to introduce students to the process of aircraft conceptual design. Additionally, this module will provide an introduction to the campus academic facilities and develop team working and communication skills.

Team working and communication
In addition to familiarising the students with the design process the module is designed to encourage them to work together effectively as a team and to develop communication skills that will be further utilised throughout the MSc course in the GDP.
Introduction to Aircraft Design
• The design and development process
• Importance of requirements and mass
• Reliability and Maintainability
Aircraft Conceptual Design
• Project design process and parametric techniques
• Flight path performance
• Drag and weight prediction: Drag sources, polar estimation, weight prediction methods
• Layout aspects: wing; powerplant; landing gear; fuselage
• Overview of stability and control: tailplane/elevator, fin/rudder, aileron layout
• Overall project synthesis

• Dr Ioannis Giannopoulos

The course is aimed at giving potential Finite Element USERS basic understanding of the inner workings of the method.

The objective is to introduce users to the terminology, basic numerical and mathematical aspects of the method. This should help students to avoid some of the more common and important user errors, many of which stem from a "black box" approach to this technique. Some basic guidelines are also given on how to approach the modelling of structures using the Finite Element Method.

• Background to Finite Element Methods (FEM) and its application
• Introduction to FE modelling: Idealisation, Discretisation, Meshing and Post Processing
• Tracking and controlling errors in a finite element analysis. ‘Do’s and don’ts’ of modelling.
• Illustration of basics of FEM using the Direct Stiffness method to define both terminology and theoretical approach.
• Problems of large systems of equations for FE, and solution methods.
• FE method for continua illustrated with membrane and shell elements.
• Nonlinear analysis in FEM and examples
• NASTRAN application sessions

• To provide an understanding of the theories of Fatigue and Fracture Mechanics and Damage Tolerance and to show how those concepts are applied to the design and testing of aircraft structures and Airworthiness Certification. 
• To provide basic principles on damage tolerance design philosophies and regulatory rules.

• Design awareness: philosophies of design against fatigue: i.e. safe-life, fail-safe and damage tolerance.
• Fatigue analysis: the traditional S-N curve approach: calculation of crack initiation life; mean stress effect, notch effect, and other influential factors; Palmgren-Miner's cumulative damage rule and fatigue analysis under variable amplitude loadings.
• Aircraft fatigue loads: atmospheric turbulence, manoeuvre, landing and ground loads; determination of cumulative frequency load distribution; typical aircraft load spectra which have been developed for use in the laboratory and computer simulation.
• Fracture Mechanics: basic theory of Linear Elastic Fracture Mechanics (LEFM): concepts of Stress Intensity Factor, fracture toughness, energy release rate; plane stress and plane strain, plastic zone at the crack tip; calculation of residual strength for a component containing cracks; prediction of fatigue crack growth using the Paris law and Forman's formula. Effect of variable amplitude loads.
• Damage Tolerance: damage tolerant design methods. Fatigue monitoring in flight/service. Inspection methods CAA and FAA Regulations and their relationship to Airworthiness Certification. Composites vs. metallic.

On successful completion of this study the student should:

• Understand the importance of design against fatigue, especially for the aircraft structures; understand the concept of the damage tolerance design and fail-safe design
• Command the basic knowledge of Linear Elastic Fracture Mechanics; know how to use the theory of LEFM to estimate residual strength and crack propagation life of a structure
• Understand why metals break; demonstrate understanding of the various forms of material deformation and failure in metallic and composite structural components and composites to form a sound base for the skills required for fatigue analysis using both crack initiation and crack propagation approaches
• Be able to select the most appropriate method and use fatigue data sheets for an engineering application
• Have knowledge of regulatory authority requirements for airworthiness and damage tolerance.

• Professor Shijun Guo

This module is separated into two ten hour blocks. The aim of the first ten hours is to describe all the main loading cases, including those encountered on the ground, in the air and those induced by the environment. In addition, the student is introduced to the history and significance of the various airworthiness requirements. The aim of the second ten hour block is to introduce students to the concept of aeroelasticity, develop the importance of aeroelastic phenomena as applied to aircraft design and to provide students with methods of analysis and criteria.

Standard requirements, their application, interpretation and limitations

Flight loading cases

• Symmetric manoeuvres, pitching acceleration, gust effects, asymmetric manoeuvres, roll and yaw

Structural design data

• The effect of inertia on relief shear force, bending moment and torque diagrams

Factors

• Load factors, their basis and restrictions, repeated and random loads

Aeroelasticity

• Importance of aeroelastic phenomena
• Aeroelastic requirements in aircraft design
• Basics of static aeroelasticity: divergence, control efficiency and reversal
• Unsteady aerodynamic loads on oscillating airfoils
• Characteristics of flutter and important design parameters and criteria
• Aeroelastic analysis and optimisation techniques
• Gust response of rigid and flexible airframes and analysis techniques

On successful completion of this study the student should:

• Have an understanding of the origin of the design loads acting on a structural component
• Have a critical understanding of the salient terminology, mathematics and methodologies employed in aeroelasticity
• Have an understanding of the aeroelastic phenomena and criteria in aircraft design
• Have an understanding of the fundamental theory and analytical methods and be able to apply them to analysing basic.

• Dr Ioannis Giannopoulos

To introduce students to the techniques of detail stressing as practised in the aerospace industry.

• 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
• Generalized 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.

• 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.

To expand the students’ knowledge of airframe systems, their role, design and integration. In particular, to provide students with an appreciation of the considerations necessary when selecting aircraft power systems and the effect of systems on the aircraft as a whole.

• 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
• Aircraft Emergency 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
• Ageing of Aircraft Systems
• Advanced and Possible Future Airframe Systems.

The aim of this module is to provide students with an understanding of the design of crashworthy aircraft structures and the considerations necessary when designing safe and crashworthy aircraft. The main purpose of crashworthy design is to eliminate injuries and fatalities in mild impacts and minimise them in severe but survivable impacts.

Overview of Aircraft Crashworthiness

• Objectives and Approach
• Regulations
• Human Tolerance
Crash Energy Management

• Structural Collapse
• Collapse of metallic and composite structural components
• Component collapse vs. structural collapse
Introduction to methods for crash analysis

• Hand calculations
• Hybrid analysis methods
• Detailed analysis methods
Role and capability of testing and simulation in the crashworthiness field

• Outline the main priorities and fundamentals of crashworthiness in aircraft in the context of protection in crash events
• Define the requirements for structural components used for impact energy absorption and structural collapse in aircraft
• Describe crashworthiness requirements on major equipment and systems
• Identify relevant regulations for aircraft crashworthy design
• Discuss human tolerance in the context of crashworthiness
• Identify the main experimental and analytical techniques used in design for crashworthiness
• Apply the systems approach in impact energy management to aircraft design
• Use simple approximate calculations on the performance of energy absorption components and structures to assess the crashworthiness of an aircraft structure.

• Professor Philip Irving

The course seeks to provide engineers with knowledge of polymer composite properties and behaviour relevant to their in-service performance durability and maintenance in aircraft structures

Basic principles
Introduction to composite materials comparison of relevant mechanical and service properties to those of metals; manufacturing process and relation of process and constituents to service performance.

Regulatory background
Requirements for fatigue and damage tolerant design in civil and military aircraft as implemented for polymer composite structures. Requirements for rotorcraft and for large fixed wing aircraft.

Structural analysis
Brief summary of methods and techniques for stress analysis and aircraft design using polymer composite materials.

Fatigue analysis
In-plane fatigue and failure processes; stiffness and strength changes under fatigue loading; fatigue notch effects in polymer composite laminates; cycle counting techniques and variable amplitude loading in metallic and polymer composite materials; life assessment and calculation procedures for design against in-plane fatigue.

Delamination crack growth and fracture mechanics
Basic theory of linear elastic fracture mechanics; strain energy release rate; applications to delamination crack growth in polymer composite laminates; delamination crack growth testing under static and fatigue loading; laboratory testing to measure Mode I and Mode II interlaminar fracture toughness (GIC and GIIC); comparison with stress intensity approaches in metallic materials; calculation of delamination behaviour of small samples and of aircraft structures. Damage tolerance issues in composites.

Service degradation processes
Impact damage in polymer composite laminates
Response of polymer composites to out-of-plane impact loading; laboratory testing, effects of velocity, mass and impacting body shape on damage produced; damage morphologies, barely visible impact damage (BVID) concepts; effects of laminate constituents on damage resistance; effects of in-plane loading on impact damage growth and laminate strength; compression and fatigue after impact; design against impact damage.

Service environment issues
Including response to temperature and humidity; bird strike; in- service damage detection in composite structures; repairs; operator experience with polymer composite aircraft structures. Structural test requirements to prove airworthiness.

On successful completion of this module a student should be able to:
1. Describe the properties and manufacture techniques of polymer composite materials, and of the basic approaches to design with them.
2. Categorise the aircraft service degradation processes of polymer composite laminates involving fatigue, impact loading, temperature and humidity fluctuations.
3. Evaluate the effect aircraft service degradation processes have on strength and durability of the composite.
4. Undertake simple calculations of damage tolerance based on laboratory test data.
5. Formulate structural and coupon sample test requirements to demonstrate the adequacy of the static and fatigue strength and damage tolerance of a composite aircraft structure.
6. Critically appraise the design principles and relate them to structural safety considerations in the appropriate regulatory context, for both new designs and in- service aircraft.

The aim of this module is to provide an introduction to the performance and stability characteristics of a conventional aircraft by means of flight test.

Please note that this is a 2 week module.

Assessed elements:
• Air data systems, Standard Atmosphere and pressure error measurement
• Lift, drag and cruise performance

Non-assessed elements:
• Static equilibrium and trim
• Longitudinal static stability, trim, pitching moment equation, static margins
• Manoeuvrability: and manoeuvre margins
• Lateral-directional trim and static stability
• Introduction to dynamic stability

On successful completion of this module a student should be able to:

1. Critically evaluate the lift, drag and cruise performance characteristics of a conventional aircraft.
2. Critically assess the pressure measurement system in the context of industry standard specifications.
3. Apply the principles of flight test to aircraft performance evaluation.

To describe and demonstrate methods for the analysis of the linear dynamics, stability and control of aircraft and their interpretation in the context of flying qualities.

• The Equations of Motion (10 lectures)
• Development of the linearised equations for longitudinal symmetric motion and lateral directional asymmetric motion. Solution of the equations of motion:- aircraft response transfer functions and state space models. Aerodynamic modelling:- Aerodynamic stability and control derivatives, derivative estimation, modelling limitations. Stability: interpretation on the s-plane
• Flight Dynamics (10 lectures)
• Aircraft dynamics:- Stability modes, longitudinal dynamics, lateral-directional dynamics, reduced order models, time response. Flying and handling qualities:- Assessment, requirements, aircraft role, pilot opinion rating, flying qualities requirements on the s-plane
• Flight control:- Introduction to stability augmentation, closed loop system analysis, the root locus plot, longitudinal stability augmentation, lateral-directional stability augmentation

This module aims to introduce several major topics associated with Engineering Integration in the context of what has been known in recent years as Integrated Product Development (IPD) in the Extended/Virtual Enterprise. The objective is to follow the process from the early stages of the product development lifecycle when the Prime has to deal with vague or difficult to quantify customer needs and to convert those to sound (functional) requirements and subsequently to design embodiments. The emphasis is on the architectural design enabling methods, but tools and technologies are also discussed.

Introduction 
Overview of the topics covered in the module. Included also are brief introductions to Quality Function Deployment (QFD) and Design Space Exploration, Optimisation and Trade-off Analysis.

Object Oriented Approach to Systems Modelling  
This lecture covers the fundamental concepts, including also a very brief introduction to the Unified Modelling Language (UML) and the Systems Modelling Language (SysML). The lecture is essential since software and systems engineering play an increasing role in aerospace product development.

Engineering Integration and Architectural Design
Covered are the principles of the semi-formal Axiomatic Design approach. Useful for both engineering architecture and software design. Included also is an exercise.

System Life Cycle Processes
Covers established standards for the engineering of systems such as ANSI/EIA 632 and ISO/IEC 15288.

Information and Knowledge Sharing
Covers the principles of information sharing and standards such as STEP (Standard for the exchange of product model data) and its modelling language EXPRESS.

Systems Modelling 
Covers the basics of the Systems Modeling Language (SysML) – a de facto standard, general-purpose modelling language for systems engineering applications. A hands on exercise is included.

BAE Systems Case Studies
Customer and Market Needs Definition- Mapping to Requirements, integrated design, modelling and simulation (Synthetic Environments), engineering integration, managing by maturity, integrated product teams and organisation.

Product Lifecycle Management (PLM)
This lecture covers state of the art in PLM including also the need for information management in integrated product development, key elements of Product Data Management (PDM), standards, integration and implementation issues.

On successful completion of this module a student should be able to:
1. Apply axiomatic design principles to a simple architectural design problem.
2. Use the object oriented approach to model a simple design or system and draw an object model diagram to describe the system.
3. Demonstrate a critical understanding of the concepts of systems information processes and information and knowledge sharing in engineering design.
4. Describe the key elements of a PLM system and understand PLM implementation challenges.

• Dr Konstantinos Salonitis

The aim of the Manufacturing module is to provide students with a basic understanding of a broad range of issues associated with aircraft manufacture. The module will cover technical and management topics ranging from strategy and factory planning to composite manufacture.

• Key manufacturing concepts and processes
• Lean and cellular manufacturing principles
• Modelling and simulation of manufacturing systems and use of factory physics
• Manufacturing planning and control systems
• Supply chain strategy
• Through-life capability
• Manufacturing cost engineering
• Quality management
• Composite Manufacture

To provide a comprehensive overview of avionics systems and infrastructures.

• Introduction to avionics systems.
• Airborne sensor systems.
• Navigation and communications systems – terrestrial and satellite-based systems, autonomous navigation systems, digital data links.
• Radar – principle of operation, operational modes, radar cross section.
• Displays – head down, head up and helmet mounted displays.
• Avionics systems architectures and integration, databases.
• Flight management and situational awareness systems, air traffic management.
• Military applications – electronic warfare and countermeasures.
• Product design considerations – design standards, fault tolerance and product life cycle.
• Case study – a complete avionics installation.

This module has an additional tutorial inside the cockpit of the large aircraft flight simulator. Students will be able to appreciate the cockpit layout design, understand information displayed to the pilot, and have the opportunity of flying the simulator. This tutorial is intended to enhance the learning process and the knowledge gained.

On successful completion of this module a student should be able to:
1. Demonstrate an understanding of the principles of operation, basic functions and properties of avionics systems.
2. Identify the design and development strategies of avionics systems.
3. Be capable of developing avionics installation requirements in aircraft.