Aerospace Dynamics MSc

The aim of this module is to provide an introduction to the performance, stability and control characteristics of a conventional aircraft.

• Air data systems, Standard atmosphere and pressure error measurement.
• Basic aircraft aerodynamics: lift and drag.
• Cruise and climb performance.
• Static equilibrium and trim.
• Longitudinal static stability, trim, pitching moment equation, static margins and manoeuvre margins.
• Lateral-directional trim and static stability.
• Introduction to dynamic stability and modal analysis

The award of a Masters degree resulting from a taught programme of study requires the student to submit a thesis based on a structured programme of research. This structured programme is typically delivered through collaboration with an industrial sponsor; although it may it may be driven by research interests of the School’s academics. The thesis should satisfactorily set out the results of the structured programme and demonstrate the candidate’s ability to conduct original investigations, to test ideas (whether the candidate’s own or those of others) and to obtain appropriate conclusions from the work. In most cases, the results of the research programme should be set in the context of related work previously published by others. The student is required to communicate their findings in a thesis and through a viva voce, oral presentation and a poster.

The subject matter range will be dependent upon the specific nature of the project.

To provide a knowledge of the physics of compressible flows.

• Thermodynamics and Equations of Motion: Governing equations, introduction to thermodynamics, temperature, energy, entropy. Concept of adiabatic, reversible and isentropic flows, steady flow equations, nozzle choking and convergent/divergent nozzles
• Shock waves: Shock tube problems, Normal shock relations, oblique shock relations, Prandtl-Meyer deflection, shock wave interactions and reflections
• Characteristic relations: Characteristic relations of the governing equations and their physical interpretation, one dimensional results
• Hypersonic Flow: Introduction to the main features of hypersonic flow
• CFD for Compressible Flows : One dimensional linear advection equations, Godunov method, higher order methods

On completion of this module the student will be able to:

• Understand the fundamental phenomena associated with compressible flows
• Competently apply analytical theory to compressible flow problems
• Understand the fundamentals of CFD methods for compressible flows.

• Dr James Whidborne

To provide knowledge of the fundamentals of control engineering for the analysis and design of control systems in aerospace applications.

• Feedback control system characteristics
• Control system performance
• Stability of Linear Feedback Systems
• Root locus method
• Frequency response method
• Nyquist stability
• Classical controller design
• State variable controller design
• Robust control

On successful completion of this module a student should be able to:
1. Analyse and explain the stability, characteristics, behaviour and robustness of single input/ single- output feedback control systems.
2. Design controllers for single-input single-output systems.
3. Use modern PC-based CAD software to solve control engineering problems and design control systems using classical methods.
4. Recognise and explain the advantages and limitations of feedback and recognise the importance of robustness.

• Professor Kevin Garry
• Jenny Holt
• Dr Mudassir Lone

This module aims to give students the skills and understanding to asses commonly encountered wind tunnel test requirements and to design appropriate experiments through knowledge of wind tunnel design, measurement techniques and data analysis.

• Wind tunnel design and layout – subsonic, transonic, supersonic circuit design and test section layouts.
• Measurements Principles for subsonic and supersonic flows: Force and moment measurements.
• Intrusive Flow Measurements – Pressure based systems, hot wire anemometry, skin friction and transition detection.
• Optical Techniques – Particle Image Velocimetry, Laser Doppler Anemometry, Shadowgraph technique, Schlieren, Interferometry.
• Calculation of wind tunnel speed, interference corrections, lift induced errors and blockage corrections.
• Data Acquisition and sensor selection.
• Analysis and post processing of experimental data including considerations and techniques for calculation of experimental errors.
• Software tools for data processing and parameter estimation: Matlab
• XFoil AVL.

This module is a prerequisite for any Aerospace Dynamics MSc candidate planning to undertake experimental work as part of their MSc thesis project.

On successful completion of this module a student should be able to:
1. Safely operate the departments low speed teaching wind tunnels to perform basic wind tunnel testing.
2. Analyse and post process recorded wind tunnel data.
3. Evaluate and select appropriate instrumentation and hardware for common wind tunnel test types.
4. Describe the design principles of wind tunnel layouts and components.
5. Propose an experimental design for common test problems.

To provide a knowledge of the dynamics, stability and control of aircraft and their interpretation in the context of flying qualities.

The Equations of Motion

• Development of the equations of motion for a rigid airframe: the linearised equations for longitudinal symmetric motion and lateral-directional asymmetric motion
• Solution of the equations of motion: the dynamics of a linear second order system, aircraft response transfer functions, state space models
• Aerodynamics modelling: aerodynamic stability and control derivatives, derivative estimation, modelling limitations
• Stability: Routh-Hurwitz criterion, interpretation on the s-plane

Flight Dynamics

• Aircraft dynamics: stability modes, longitudinal dynamics, lateral-directional dynamics, reduced order models, time response, frequency response
• Flying and handling qualities: assessment, requirements, aircraft role, pilot opinion rating, control anticipation parameter, 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

On successful completion of this study the student should be able to:

• Derive and solve the small perturbations equations of motion for an airplane
• Assess the flying qualities of the airplane
• Recommend and design simple stability augmentation system strategies to rectify flying qualities deficiencies
• Plan, manage, execute and report on a stability and control assessment of an airplane.

• Dr Mudassir Lone

The aims of this module are: to describe the essential features of typical command and stability augmentation systems; to introduce contemporary handling qualities criteria and to show how they constrain flight control system design; to demonstrate handling qualities design procedures.

• Flight control system architecture; Multiple redundant systems; Aircraft models; Aircraft state equations; Relaxed longitudinal static stability; Control system properties; Control law design.
• Autostabiliser design using state feedback; Design of a rate command attitude hold command and stability augmentation system; Lateral-directional autostabiliser design.
• Introduction to aircraft handling qualities; Control anticipation parameter; High order systems; The C* criterion; The Neal and Smith criterion; The Gibson criteria; Analysis of the Gibson dropback criterion; Law order equivalent systems; The bandwidth criterion.

On successful completion of this module a student should be able to:
1. Be able to use basic tools for flight control system analysis and design.
2. Understand the conflict between flight control system architecture design for safety with functional design for control.
3. Appreciate the design constraints on command and stability augmentation systems for the provision of acceptable flying qualities.
4. Be able to analyse and design typical command and stability augmentation systems.
5. Be able to interpret flying and handling qualities criteria in order to determine flight control system design constraints.

• Dr Simon Prince

To give candidates with a background in physical science or general engineering an appreciation of the principal aerodynamic factors affecting the design of spacecraft and launch vehicles.

The course describes the thermal and dynamic loads experienced by launch and re-entry vehicles.

The course will cover:
• The fundamentals of flight at high Mach number within the earth atmosphere The design and flow characteristics of hypersonic vehicles.
• Boundary layers, heat transfer and thermal protection, real gas effects Equations of motion for planetary re-entry.
• Ballistic entry and high angles of descent Lifting entry.

• Dr James Whidborne

To provide a knowledge of modern control techniques for the analysis and design of multivariable aerospace control systems.

Multivariable System Analysis

• Multivariable linear systems theory
• System realisations
• Controllability, observability and canonical forms
• Size of signals and systems

Multivariable Control System Design 

• System interconnection and feedback
• Optimal linear quadratic control and estimation
• Uncertainty and conditions for robustness
• H-infinity optimal control

On completion of this module the student will be able to:

• Analyse the stability, robustness and performance of multivariable aerospace control systems
• Design robust and optimal feedback control systems using state variable techniques, using MATLAB
• Recognise the advantages and limitations of optimal feedback control.

The aim of this module is to provide knowledge of the current technology issues in relation to reducing the impact of aviation of the environment.

• General overview of the impact of aviation on the environment, historical trends, current status, aviation profile and technology and cost metrics.
• Current research focus and environmental targets.
• Propulsion systems: engine cycles; fuel burn; internal aerodynamics, open rotors.
• Airframe and aircraft configurations: Range equation; maximising L/D; profile drag; NLFC; HLFC.
• Overview of noise related technology drivers. Local air quality implications.
• Aircraft operations: multi-stage long-haul, ATC. Contrails.
  
  

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

1. Have a basic knowledge of the performance characteristics of commercial aircraft in relation to environmental impact.
2. Understand the relative impact of key engineering design and operational aspects of commercial aircraft on the environment.
3. Assess the relative importance of technological changes in terms of commercial aircraft design.

• Professor Kevin Garry
• Jenny Holt

To provide a detailed understanding of basic equations and mathematical modelling techniques used in fluid flows and a knowledge of boundary layer flows including the methods used for their modelling and prediction.

Basic Concepts:
The Navier-Stokes Equations.
Equation of Continuity: Viscous Stresses - shear and normal.
Navier-Stokes equations.
The viscous flow energy equation.
Similarity parameters.
The 2D boundary layer equations - continuity, x and y momentum and energy.
Incompressible laminar flow on a smooth flat plate.
Blasius solution.
Displacement thickness.
The effective body concept.
Influence of displacement thickness on lift.
Skin friction on a thin flat plate.
Boundary layer separation.

Characteristics of turbulent flow:
Turbulent kinetic energy.
Eddy viscosity.
Mixing length hypothesis.
Structure of the turbulent boundary layer.
Law of the wall.
Approximate formula for zero pressure gradient turbulent boundary layers.
Separation prediction.
Profile drag.

The Atmospheric Boundary Layer:
The nature of the wind.
Mean hourly wind speed profiles.
Diffusion of pollutants.
Typical treatment of strong wind profiles.
Wind tunnel simulation of wind engineering problems.

Laminar boundary layer in compressible flow:
Similarity parameters in compressible flow.
General properties of thermal boundary layers.
Prandtl number.
Heat transfer and skin friction.
Reynolds analogy.
Compressible laminar flow over a flat plate.
Effect of freestream pressure gradient.
Shock boundary layer interaction.

Boundary layer transition:
The transition process. Factors effecting transition. Laminar flow aerofoils.
Boundary layer control.

On successful completion of this module a student should be able to:
1. Apply knowledge of the structure within a boundary layer to flow related problems.
2. Explain current turbulence models and how they may be applied.
3. Interpret and calculate characteristics of the atmospheric boundary layer and apply the data to wind engineering problems.
4. Identify boundary layer control techniques and assess their use for future aeronautical applications.

• Dr James Whidborne
• Dr Mudassir Lone

Mathematical modelling and simulation of modern air-vehicles is a complex activity which requires a wide range of technical skills to be applied using a multi-disciplinary approach. The aims of this course are to provide the student with the skills and knowledge necessary to model, simulate and then critically analyse the resultant non-linear motion of modern air vehicles using advanced design and analysis software tools.

• Introduction to mathematical modelling and simulation; systems of non-linear ODEs; equilibrium, linearisation and stability; numerical & computational tools (10 hours).
• Model building; model testing, validation and management; trimming and numerical linearisation (10 hours).

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

1. Describe the requirements for large amplitude non-linear mathematical modelling and simulation of aerospace vehicles.
2. Describe air-vehicle dynamics as a set of ordinary differential equations.
3. Recognise, implement and apply selected numerical integration routines for model simulation using modern software tools.
4. Define and implement example air-vehicles in terms of their aerodynamic, control, mass and inertia characteristics.  Evaluate and critically compare the resultant motion.
5. Identify the requirements for model testing, verification and validation, and demonstrate their application to an air-vehicle model.
6. Define mathematical trim conditions, how they relate specifically to air-vehicles and validate an air vehicle using trim data generated for a range of flight conditions and vehicle configurations.
7. Define mathematical linearisation, how it relates specifically to air-vehicles and validate a non-linear air-vehicle model using the linear model equivalents generated at a range of flight conditions.

To provide an elementary insight into rotorcraft performance estimation and provide knowledge of the stability and control characteristics of helicopters.

• Forces and moments acting on a rotorcraft
• Performance estimation in the hover and forward flight
• Flight test methods for performance evaluation
• Conventional rotorcraft control and stability

On completion of this module the student will be able to:

• Describe the forces acting on a helicopter
• Estimate the power required by a rotorcraft in the hover or forward flight
• Assess the viability of a typical flight profile
• Describe the key stability and control attributes of a typical rotorcraft

• Dr Stephen Hobbs

The aim of this module is to provide an introduction to the principles of aerospace navigation systems based on inertial sensors and satellite navigation as well as to provide an introduction to the principles of sensor fusion, system integration and error analysis and prediction.

GNSS and INS

• Introduction (1 hour)
Overview of navigation principles, typical applications; axis systems and projections (1 hour)
• Inertial Navigation Systems (3 hours)
Principles of inertial navigation; accelerometers, gyroscopes, specific technologies such as Ring Laser Gyros; Axis transformations and mechanisation of IN equations; Errors in inertial navigation, Schuler loop tuning, INS modelling & aiding
• GNSS (6 hours)
Development history: GNSS, GPS, GLONASS, EGNOS, Galileo; GPS system architecture (ground, space, user segments); Code (CDMA) and carrier techniques; signal processing (correlation), integer ambiguities; Error sources (natural, other); Augmentation: differential GPS (local, wide area), other sensors (e.g. INS); Applications / issues: user groups (aviation, space), integrity (RAIM), accuracy, reliability

Sensors and Data Fusion

• Error Characteristics of Aircraft Sensors, INS, GPS, VOR, DME (2 lectures)
• Random Signals And Random Processes (1 lecture)
• Measurement In Noise (1 lecture)
• Error Analysis (2 lectures)
• Discrete Kalman Filter (2 lectures)
• Case Study: Barometric Aiding For INS (1 lecture)
• Case Study: GPS models (1 lecture)

• Dr James Whidborne

To provide an understanding of the mathematical techniques that underpin both classical and modern control law design.

• The Laplace transform.
• Transfer-function approach to modelling dynamic systems.
• State-space approach to modelling dynamic systems.
• Time-domain analysis of simple dynamic systems.
• Frequency response of simple dynamic systems.
• Sampled-data and discrete time systems.

• Professor Nicholas Lawson

The aim of this module is to provide the student with an understanding of transonic flow development and how this affects aerodynamic performance.

The main emphasis within the course content is on well-ordered flows at subsonic and sonic speeds about smooth bodies such as aerofoils or wings which is particularly relevant to aerodynamic analysis and design.


Basic concepts in the formation of shock waves and their interaction with viscous flows on aerofoils: 

• Compressible flow properties of air leading to shock wave formation
• Supercritical flow development on an aerofoil
• Shock wave interaction with aerofoil boundary layer and how this changes with Mach number and Reynolds number, including differences between laminar and turbulent boundary layers
• Development of shock-induced flow separation


Overall characteristics of swept wings and their flow development: 

• Simple sweep concepts and how wing sweep helps high speed performance
• Geometric layout of the wings of civil transport aircraft and subsonic military combat aircraft and how these relate to performance requirements
• Finite-wing effects on pressure distribution and corresponding shock wave patterns, and the importance of appropriate design treatment


The performance of aerofoils and wings:

• Influence by the flow development, general performance characteristics of an aerofoil, including methods for drag breakdown
• Effects of pressure distribution and shock waves on the boundary layer development over the aerofoil surface
• Differences between Model A and Model B separation characteristics
• Simple methods for analysing wing drag, including vortex drag, and how flow separation characteristics differ from 2-D


Wind tunnel testing : 

• Various types of transonic tunnel, examples of test results on aerofoils and wings to illustrate what had been studied earlier

On completion of this module the student will be able to:

• Apply their understanding of transonic flows to current aeronautical problems.

To understand the key features of CFD methods used for simulating external flows for engineering applications.

• CFD methods used in industry.
• The hierarchy of governing equations
• Mesh generation techniques
• Solution strategies

• To introduce the foundations of computational fluid dynamics and the mathematical properties of the governing equations.
• To introduce the basics of numerical analysis and numerical methods for partial differential and algebraic equations.
• To introduce the concepts of grid generation.
• To understand the CFD methods used for computing incompressible and compressible flows.
• To introduce the concepts of High Performance Computing.

• Introduction to computational fluid dynamics and turbulence modelling.
• Introduction to numerical analysis.
• Numerical Integration, Numerical derivation, Discretization using finite difference methods and stability, Error Analysis.
• Geometry modelling and surface grids.
• Algebraic mesh generation.
• Overview of various numerical methods for compressible and incompressible flows.
• Validation and Verification for CFD
• Mathematical properties of hyperbolic systems.

• Dr Mudassir Lone

To provide fundamental insight into analytical methods and flight test techniques used for the derivation of mathematical models of an aircraft.

• Basic Systems and Estimation Theory
• Regression Methods
• Maximum Likelihood Methods
• Frequency Domain Methods
• Flight Test Design and Flight Data Analysis.

On the completion of this module the diligent student will be able to:

• Apply available mathematical tools to derive flight dynamic models from flight test data
• Plan a flight test sortie to obtain flight test data most suited for system identification
• Describe and categorise methods of system and parameter identification based on the desired mathematical model.

The aim of this module is to give the student an appreciation of the factors influencing supercritical flow development and the interaction with other aerofoil / wing design features. The aim is also to provide students with knowledge of industrial aircraft design practice / process and project management along with some practical experience.

Aerofoil design aims and methodology, highlighting the influence of such factors as Mach number, lift coefficient, thickness/chord and thickness form, and the limits provided by viscous effects and Reynolds number.

3D wing design, covering the role of sweep, taper, wing twist and dihedral, and the impact on wing aerodynamics of propulsion integration, fuselage interference and high lift (take-off and landing) requirements.

Main features of the subcritical and supercritical CFD methods and how they are used as graphical interactive design tools. Particular importance is attached to interpretation of the results of the CFD calculation and how closely these relate to what would occur in the true aerofoil flow.

The conceptual aircraft design process and project management practice.

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

1. Describe the influence of factors effecting super critical aerofoil performance and apply this to knowledge to determine a design methodology.
2. Understand the factors involved in the design of efficient transonic wings in the context of overall aircraft design and the other allied disciplines
3. Use CFD methods to carry out supercritical wing design and evaluate results against performance criteria, including an appreciation of aircraft certification rules.
4. Assess the limitations of CFD methods for prediction of aerofoil flow characteristics.
5. Appreciate the process and management of conceptual aircraft design in industry, including the role of periodic design reviews and “gateway” decision points.