Register for webinar: Explore our Aerospace Vehicle Design MSc on 22 April 2021.
Overview
- Start dateOctober
- DurationOne Year
- DeliveryTaught modules 20%, individual research project 80%
- QualificationMSc
- Study typeFull-time
- CampusCranfield campus
Who is it for?
Manufacturers of modern aircraft are demanding more lightweight and more durable structures. Structural integrity is a major consideration of today’s aircraft fleet. For an aircraft to economically achieve its design specification and satisfy airworthiness regulations, a number of structural challenges must be overcome. This course trains engineers to meet these challenges, and prepares them for careers in civil and military aviation. It is suitable if you have a background in aeronautical or mechanical engineering, or relevant industrial experience.
Why this course?
We have been at the forefront of postgraduate education in aerospace engineering since 1946. Aerospace Vehicle Design at Cranfield University was one of the original foundation courses of the College of Aeronautics. Graduates of this course are eligible to join the Cranfield College of Aeronautics Alumni Association (CCAAA), an active community which hold a number of networking and social events throughout the year.
Cranfield University is well located for students from all over the world, and offers a range of library and support facilities to support your studies. This enables students from all over the world to complete this qualification whilst balancing work/life commitments.
Informed by industry
The course has an Industrial Advisory Committee with senior members from major UK aerospace companies, government bodies and the military services. The committee meets twice a year to review and advise on course content, acquisition skills and other attributes are desirable from graduates of the course. Panel members include:
• Airbus,
• BAE Systems,
• Boeing,
• Department of National Defence and the Canadian Armed Forces,
• GKN Aerospace,
• Messier-Dowty,
• Royal Air Force,
• Royal Australian Air Force,
• Thales UK.
We also arrange visits to sites such as BAE Systems, Marshall Aerospace, GKN and RAF bases which specialise in the maintenance of military aircraft. This allows you to get up close to the aircraft components and help with your understanding.
Course details
This option comprises four compulsory modules and a minimum of 120 hours of optional modules, selected from a list of 18 options. You will also complete an individual research project. Delivered via a combination of structured lectures, industry guest lectures, computer based workshops and private study.
A unique feature of the course is that we have four external examiners: two from industry who assess the group design project and two from academia who assess the individual research project.
Course delivery
Taught modules 20%, individual research project 80%
Individual project
The individual research project aims to provide the training necessary for you to apply knowledge from the taught element to research, and takes place from January to September. It is sometimes associated with a real-world problem that one of our industry partners are looking to resolve.
Examples in aircraft structural design and analysis topics:
Investigation in the numerical representation of damage on CFRP stiffened panels and behaviour under combined loading;
Delamination growth of carbon fibre composites under fatigue loads;
Experimental testing and numerical analysis of aircraft bolt jointed sandwich composites;
Strength prediction via testing and/or numerical simulation of bolted joints on fibre reinforced laminates;
Composite design considerations for trailing arm landing gears;
Fatigue behaviour of bolted joints on CFRP laminates following pull through failure;
Simulation of thermal residual stresses of CFRP wing;
Fatigue of buckled composite stiffened panel;
Dynamic Indentation of composite laminates;
Numerical modelling of through-thickness reinforced composite laminates;
Direct measurement of traction-separation law in fatigue damage of adhesive bonding;
Composite joints reinforced by composite fasteners.
Modules
Keeping our courses up-to-date and current requires constant innovation and change. The modules we offer reflect the needs of business and industry and the research interests of our staff and, as a result, may change or be withdrawn due to research developments, legislation changes or for a variety of other reasons. Changes may also be designed to improve the student learning experience or to respond to feedback from students, external examiners, accreditation bodies and industrial advisory panels.
To give you a taster, we have listed the compulsory and elective (where applicable) modules which are currently affiliated with this course. All modules are indicative only, and may be subject to change for your year of entry.
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
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Aim |
To introduce the composite materials, manufacturing techniques and analysis methods for the design of aerospace composite structures. |
Syllabus |
• 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 and • sandwich panels with FRP composite facing skins. 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 a student should be able to: 1. Demonstrate an understanding of the key features and particular properties of composite materials, especially fibre reinforced plastics (FRP). 2. Understand modern manufacturing techniques for aerospace composite structures. 3. Apply analytical methods for the evaluation of moisture and thermal effects on a FRP laminate. 4. Demonstrate an ability to predict the buckling behaviour of laminate plates and sandwich panels through the application of analytical techniques and data sheets. 5. Evaluate a FRP laminate based on stiffness and stress analysis failure criteria techniques using PC-Based software. 6. Perform stress analysis of laminated composite structures with open and closed sections subjected to various loadings. 7. Extend their knowledge and skills to the design and analysis of more complex composite structures on the Group Design Project. |
Fatigue, Fracture Mechanics and Damage Tolerance
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Aim |
To provide 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 |
• 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. • Damage Tolerance: Damage tolerant design methods. Fatigue monitoring in flight/service. Inspection methods. CAA and FAA Regulations and their relationship to Airworthiness Certification Material selection. • Classroom exercise will be assigned during this module to further enhance the learning objectives. Completed work will be collected in by the tutors at the end of the module. |
Intended learning outcomes |
On successful completion of this module a student should be able to: 1. Recognise the importance of design against fatigue, especially for aircraft structures. 2. Explain the concept of the damage tolerance design and failsafe design. 3. Command the basic knowledge of Linear Elastic Fracture Mechanics (LEFM). 4. Apply the theory of LEFM to estimate residual strength and crack propagation life of a structure. 5. Solve fatigue analysis problems using both crack initiation and crack propagation approaches. 6. Evaluate and select the most appropriate method; use data sheets for an engineering application. 7. Interpret the regulatory authority requirements for airworthiness and damage tolerance. 8. Extend their knowledge and skills to the calculation of crack propagation rates, structural life and inspection intervals on the Group Design Project. |
Finite Element Analysis
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Aim |
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. |
Syllabus |
• 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 |
Intended learning outcomes |
On successful completion of this module a student should be able to:
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Structural Stability
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Aim |
Provide a fundamental understanding of the buckling of thin walled structures and the ability to calculate the buckling load of a component. |
Syllabus |
• 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 a student 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
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Aim |
To introduce 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 a student should be able to: |
Aircraft Aerodynamics
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Aim |
The aim of this module is to provide knowledge of the Atmosphere and of the aerodynamic characteristics of a conventional aircraft in the context of its mechanics of flight. |
Syllabus |
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Intended learning outcomes |
On successful completion of this module a student 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. 6. Apply their knowledge and skills to the aerodynamic aspects of the Group Design Project aircraft. |
Aircraft Performance
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Aim |
To facilitate students’ 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 students with the ability to apply aircraft performance theory, practically in the context of aerospace vehicle design. |
Syllabus |
• 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 a student 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 students to the engine and aircraft-related aspects of the propulsion system, with the primary emphasis being placed on gas turbine engines. |
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Syllabus |
• 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 a student 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
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Aim |
To provide an introduction to the fundamentals of aircraft stability and control. |
Syllabus |
• 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 the students will be able to:
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Computer Aided Design (CAD)
Aim |
The aim of this module is to introduce students 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. |
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Syllabus |
• 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 a student 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 their knowledge and skills to design aircraft components as part of the Group Design Project. |
Design for Manufacture and Operation
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Aim |
To ensure that while the student designs his/her structure he/she is 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 |
• Flaps and control surfaces: Structural configuration and mechanisms. • Assembly and production processes. • Maintainability and accessibility. • Design for Assembly. • Design for Maintainability. 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 a student 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. |
Design of Airframe Systems
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Intended learning outcomes |
On successful completion of this module a student should be able to: 1. Identify the main airframe systems in civil and military aircraft and explain their purposes and principles of operation. 2. Cite the sources of systems power and explain their architecture, generation and distribution methods. 3. Discuss the requirements for; identify types of equipment and systems used for; and perform basic analysis of environmental control and oxygen systems in aircraft. 4. Cite and explain the problems resulting from icing on aircraft and systems available to provide protection. 5. Identify and explain the major considerations to be made in the design of aircraft fuel systems and the major components and sub-systems, including aviation fuels. 6. Appraise the effects of airframe systems power provision on aircraft power plants. 7. Analyse fuel penalties resulting from a given system’s presence on an aircraft by carrying out basic calculations. 8. Recognise and interpret the reasons for, and possible types of changes, that may occur in airframe systems in the near future. |
Detail Stressing
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Syllabus |
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Intended learning outcomes |
On successful completion of this module a student should be able to:
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Flight Experience
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Syllabus |
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Intended learning outcomes |
On successful completion of this module a student should be able to:
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Initial Aircraft Design
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Syllabus |
This module has additional accompanying tutorials and workshops as required. A miniature group PBL conceptual design project 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 a student 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 of an aircraft. 5. Apply their knowledge and skills to derive the initial structural layout of the Group Design Project aircraft. |
Landing Gear Design
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Syllabus |
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Intended learning outcomes |
On successful completion of this module a student should be able to:
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Loading Actions
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Aim |
To provide students 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 MSc 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. This module has additional accompanying support sessions to assist application of the material to the GDP. A classroom exercise will be completed during this module. Solutions will be collected at the end of the module and archived for future inspection. |
Intended learning outcomes |
On successful completion of this module a student should be able to: 1. Estimate the design loads that act upon a major aircraft structural component using a simplified approach. 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
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Syllabus |
• 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 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 a student 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 Dynamics
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Aim |
To provide student with the basic knowledge and understanding of structural vibration modes and dynamic response through theory and experiment, and a good understanding of finite element analysis and application. |
Syllabus |
• Introduction to a mechanical system vibration and structural dynamics
• Free, forced and damped vibration theory and experiment • Eigenvalue problem solution methods • Direct time integration methods • Lumped and consistent mass matrices in finite element modelling • Structural dynamic response analysis • Application of FEM to aerospace structures |
Intended learning outcomes |
On successful completion of this module a student should be able to: |
Teaching team
You will be taught by staff with many years of both academic and industrial experience. Key members of teaching staff on this option include: The teaching on some taught modules is also supported by lectures from visiting speakers from both industry and the military. Former speakers have included senior representatives from: Airbus, BAE Systems, Boeing and Eurocopter. The Course Director for the October intake for this programme is Dr Ioannis Giannopoulos. The March intake Course Director is Dr Shijun Guo.
Accreditation
Re-accreditation for the MSc in Aerospace Vehicle Design is currently being sought with the Institution of Mechanical Engineers (IMechE) and the Royal Aeronautical Society (RAeS) on behalf of the Engineering Council as meeting the requirements for Further Learning for registration as a Chartered Engineer. Candidates must hold a CEng accredited BEng/BSc (Hons) undergraduate first degree to comply with full CEng registration requirements.
Your career
This Aerospace Vehicle Design option in Structural Design is valued and respected by employers worldwide. The applied nature of this course ensures that our graduates are ready to be of immediate use to their future employer and has provided sufficient breadth of understanding of multi-discipline design to position them for accelerated career progression.
Graduates from this option have gone onto pursue engineering careers in disciplines such as structural design, stress analysis or systems design. Many of our graduates occupy very senior positions in their organisations, making valuable contributions to the international aerospace industry. Student destinations have included BAE Systems, Airbus, Dassault and Rolls-Royce.
How to apply
Online application form. UK students are normally expected to attend an interview and financial support is best discussed at this time. Overseas and EU students may be interviewed by telephone.