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To introduce you to the composite materials, manufacturing techniques and analysis methods for the design of aerospace composite structures.

• 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.
 

On successful completion of this module you should be able to:

1. 1. Demonstrate an understanding of the key features and particular properties of composite materials, especially fibre reinforced plastics (FRP).
2. 2. Apply analytical methods for the evaluation of moisture and thermal effects on a FRP laminate.
3. 3. Able to evaluate the strength of a FRP laminate based on stress analysis and failure criteria.
4. 4. Able to perform stress analysis of laminated composite structures with open and closed sections subjected to various loadings.

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.

• 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.

On successful completion of this module you should be able to:

1. 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. 2. Formulate the requirements that drive the design of the main airframe systems.
3. 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. 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. 5. Examine the reasons for, and propose possible types of changes, that may occur in airframe systems in the near future.

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.

• 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.

On successful completion of this module you should be able to:

1. 1. Have knowledge of the performance of characteristic of conventional fixed wing aircraft.
2. 2. Understand and be able to apply methods of estimation of flight path performance.
3. 3. Be able to assess and evaluate the performance characteristics of a conventional aircraft.
4. 4. Appreciate the importance of airworthiness requirements in conventional aircraft.

To provide an introduction to the fundamentals of aircraft stability and control.

• 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.

On successful completion of this module you will be able to:

1. 1. Describe the concepts of: trim, stability and control.
2. 2. Describe methods of providing static stability for a conventional aircraft.
3. 3. Describe the modes of motion of a conventional aircraft.

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.

• - 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.
• - Various classroom exercises will be completed during this module, with solutions provided during and at the end of the sessions.

On successful completion of this module you should be able to:

1. 1. Understand the influence of design for manufacture and maintainability on both structure and aircraft systems.
2. 2. Apply their knowledge and skills to the Group Design Project.

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.

• 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).

1. 1. Describe the flight test techniques used to measure simple aerodynamic parameters and assess navigation systems.
2. 2. Describe the dynamic stability modes of a conventional aircraft.

To introduce you to the process of aircraft conceptual design and support structural layout work, were required, through participation on the Group Design Project.

• 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.

On successful completion of this module you should be able to:

1. 1. Demonstrate a systematic understanding of the multidisciplinary nature of aircraft design.
2. 2. Identify the functional role of the structural elements of the entire airframe.
3. 3. Demonstrate an understanding of the top level aircraft design to put the detailed design of one aircraft component into context.
4. 4. Perform a simple conceptual design synthesis of an aircraft and evaluate the design.
5. 5. Apply their knowledge and skills to derive the initial structural layout of the Group Design Project aircraft.

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.

• 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. 

On successful completion of this module you should be able to:

1. 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. 2. Extend their knowledge and skills to the derivation of structural loads on the Group Design Project aircraft.
3. 3. Demonstrate knowledge of the history and significance of the various airworthiness requirements.

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.

• 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

On successful completion of this module you should be able to:

1. 1. Demonstrate an understand of the aircraft certification process and how aircraft design is driven by airworthiness requirements.
2. 2. Identify system safety requirements.
3. 3. Demonstrate a systematic understanding of the procedures and steps for system safety assessment.
4. 4. Develop system reliability models and perform safety assessment at different levels.
5. 5. Simulate and analyse system reliability.

To introduce you to the importance of aeroelastic phenomena, basics of aeroelasticity and analysis methods for the design of aircraft structures.

• 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.

On successful completion of this module you should be able to:

1. 1. Recognise the importance of aeroelastic phenomena and design requirements.
2. 2. Explain the theory of aeroelasticity including static and dynamic aeroelastic problems.
3. 3. Illustrate the approach for evaluating divergence and flutter speed of aircraft structures.
4. 4. Demonstrate the application of knowledge to the practical design aspects of aerospace structures using available PC based computer programs.
5. 5. Apply their knowledge and skills to estimate the flutter speed of the Group Design Project aircraft.

To introduce you to system engineering concepts, system lifecycle models and system design processes and methods.

• Introduction to Systems.
• Life Cycle Models.
• System Requirements.
• Systems Design.
• System Integration, Verification and Validation.

On successful completion of this module you should be able to:

1. 1. Demonstrate a understanding of the basic concepts of the main life-cycle models.
2. 2. Discuss the advantages and disadvantages of these models.
3. 3. Define and analyse system requirements and specifications.
4. 4. Determine system development process and define the work to be performed at different development phases.
5. 5. Apply development life-cycle models to the AVD Group project.

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.

• 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).

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

1. 1. Demonstrate knowledge of the characteristics of the international standard atmosphere and design atmospheres.
2. 2. Identify aircraft air data systems and air data measurement.
3. 3. Identify the basic force system of a conventional aircraft.
4. 4. Demonstrate an ability to calculate the principle aerodynamic forces of lift and drag.
5. 5. Perform a simple initial aerodynamic design of an aircraft.

To introduce you to the engine and aircraft-related aspects of the propulsion system, with the primary emphasis being placed on gas turbine engines.

• 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.

On successful completion of this module you should be able to:

1. 1. Understand how a propulsion system is defined.
2. 2. Assess the performance interface between the engine and the airframe.

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.

• • 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.

On successful completion of this module you should be able to:

1. 1. Explain the role of Computer Aided technologies in the aircraft development process.
2. 2. Differentiate between Computer Aided Design, Computer Aided Manufacture and Computer Aided Engineering and understand the information flows between these tools.
3. 3. Select appropriate CAD modelling techniques for a variety of design applications.
4. 4. Use Computer Aided Design software to create simple 3D models using solid, assembly and surface modelling techniques.
5. 5. Apply your knowledge and skills to design aircraft components as part of the Group Design Project.

To introduce you 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.

• 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.

On successful completion of this module you should be able to:

1. 1. Apply the principals and techniques in stress analysis and airworthiness requirements to size basic aircraft structural components.
2. 2. Evaluate the strength of a component and determine its ability to support an applied load.
3. 3. Compare, propose and select metallic materials suitable for use in aircraft structures.
4. 4. Acquire transferable skills to allow effective communication with company stress engineers.

To provide you with an understanding of the theories of Fatigue and Fracture Mechanics, and to demonstrate how these methods and the damage tolerance design concepts are applied to the design and testing of aircraft structures and Airworthiness Certification

• 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.

On successful completion of this module you should be able to:

1. 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. 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. 3. Solve fatigue analysis problems using both crack initiation and crack propagation approaches.
4. 4. Evaluate and select the most appropriate method; use data sheets for an engineering application.
5. 5. Evaluate the regulatory authority requirements for airworthiness and damage tolerance.

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.

• - 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.

On successful completion of this module you should be able to:

1. 1. Understand the underlying principles and key aspects of practical application of FEA to structural problems.
2. 2. Understand the main mathematical and numerical aspects of the element formulations for 1D, 2D and 3D elements.
3. 3. Build and analyse finite element models based on structural and continuum elements with proper understanding of limitations of the FEM.
4. 4. Interpret results of the analyses and assess error levels.
5. 5. Critically evaluate the constraints and implications imposed by the finite element method.

To provide you with an introduction to the leading IVHM technologies and concepts being implemented in various health monitoring systems, and their application to aircraft design.

IVHM has become an integral part of Aerospace Vehicle Design. You will be able to comprehend IVHM techniques and be able to use them in AVD Group Design Project.

• Failure Modes, Effects and Criticality Analysis (FMECA) and different tools available.
• Sensors and Instrumentation for different aircraft sub-systems (aircraft structures, aero-propulsion systems, electric power and power distribution systems, avionics, etc.).
• Fault detection and isolation techniques.
• Reasoning methods (model-based, case-based, etc.) and their use in aircraft health management.
• Prognosis approaches for aircraft health management.
• Physics of failure approaches.
• IVHM Design for aircraft health management.
• Structural health monitoring.
• Cost benefit analysis of IVHM implementation.

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

1. 1. Communicate unambiguously IVHM terminology and apply it correctly, given that the IVHM is a developing field.
2. 2. Demonstrate an understanding of the key IVHM Concepts; failure modes, failure effects, failure symptoms, sensors, detection, diagnostics, prognostics, etc.
3. 3. Select appropriate sensors and instrumentation for different sub-systems of the aircraft.
4. 4. Build a diagnostics/prognostics algorithm(s) for different sub-systems of the aircraft.
5. 5. Design IVHM systems for different sub-systems of the aircraft in the Group Design Project.

To provide you with a general understanding of the design of landing gear and the associated systems and the associated challenges of integrating them into an airframe. The module also aims to highlight the implications that the design of the landing gear has on the aircraft layout and structure.

• Landing gear layout (Skids, flying boats, tricycle, bicycle, multi-wheel etc.).
• Ground flotation (Aircraft Classification Number [ACN] & Pavement Classification Number [PCN]).
• Tyres (Failure modes and causes and wear. Radial vs. Cross-ply).
• Wheels (Bowl type vs. ‘A’ type).
• Brakes.
• Struts (Cantilever vs. Trailing arm).
• Loads (Ground loads and airframe attachment loads).
• Shock Absorbers (Single acting and double acting. Compression curves).
• Retraction.
• Ground manoeuvring (Steering).

On successful completion of this module you should be able to:

1. 1. Evaluate the various landing gear layout schemes and assess which is best for any particular aircraft layout.
2. 2. Demonstrate a systematic understanding of the procedures and steps for positioning the landing gear on the aircraft (longitudinally and laterally).
3. 3. Critique historic landing gear designs and understand why various design decisions have been made and analyse their impacts on the aircraft.

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.

• 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.

On successful completion of this module you should be able to:

1. 1. Demonstrate a conceptual understanding of the buckling of thin walled structures and structural components.
2. 2. Demonstrate the ability to predict buckling behaviour using hand calculation techniques.
3. 3. Analyse the buckling and post buckling behaviour of simple thin walled stiffened panels.
4. 4. Effectively use data sheets to analyse buckling of real structural components.