Aerospace Dynamics MSc

To give you a basic knowledge of aerodynamic principles and familiarity with the fundamental characteristics of fluid flow around aircraft.

• Fluid Properties and Basic Flow Equations.
• Dimensional Analysis and Aerodynamic force
• Viscosity the Boundary Layer and Skin Friction.
• Vortex Flow and Aerofoil Circulation
• Finite Low Speed Wings.
• Aerofoil and Wing High Lift Devices.
• The aerodynamic characteristics of flying controls.
• Supersonic Flow Characteristics. 
• Supersonic aerofoil sections.
• Finite Supersonic Wings.
• Transonic Flow Characteristics.
• Preliminary training in MATLAB.

• Summarise the principles of incompressible flows including vortices and viscous effects, boundary layers and basic wing and aerofoil section characteristics.
• Describe the implications of compressibility effects; shock waves, supersonic and transonic flow.
• Understand the use of basic low speed and high speed wind tunnel facilities.
• Relate the flow science to its application to aircraft design.

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.
• Certification specification requirements and compliance assessment.

To provide a knowledge of the physics of compressible flows, and the theoretical methods for your calculation.

• 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 you 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.

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

Basic Concepts:

• Viscous Stresses - shear and normal. Navier-Stokes equations.
• 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.
• 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.
• Approximate formula for zero pressure gradient turbulent boundary layers.
• Separation prediction.
• Profile drag.

Boundary layer transition:

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

Environmental Impact:

• General overview of the impact of aviation on the environment, historical trends, current status, aviation profile and technology and cost metrics.
• Overview of noise related technology drivers. Local air quality implications.
• Overview of aerodynamics of propulsion systems: fuel burn; key internal aerodynamic characteristics.
• Aircraft operations: multi-stage long-haul, ATC. Contrails.
• Airframe and aircraft configurations: Range equation; maximising L/D; profile drag; current aerodynamic flow control priorities including NLFC; HLFC.

On successful completion of this module you should be able to:
1. Apply knowledge of the structure within a boundary layer to flow related problems.
2. Demonstrate knowledge of the performance characteristics of commercial aircraft in relation to environmental impact.
3. Evaluate the environmental impact of commercial aviation relative to that of other sectors.
4. Appraise the relative impact of key engineering design and operational aspects of commercial aircraft on the environment.
5. Assess the relative importance of technological changes in terms of commercial aircraft design. 

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 you 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.

To provide an elementary insight into aerodynamics of hovering flight, vertical flight and forward flight, rotorcraft performance estimation and provide knowledge of trim stability and control characteristics of helicopters.

• Momentum Theory and Blade Element Theory.
• Aerodynamics of Hovering Flight, Vertical Flight and forward flight.
• Vortex Ring State.
• Performance estimation in the hover and forward flight.
• Flight test methods for performance evaluation.
• Conventional rotorcraft control and stability.
• Aerodynamics of autorotation.
• Flow control methods for the blades.

On completion of this module you will be able to:

• ​Describe the generic aerodynamics of a helicopter rotor system.
• 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.
• How to apply flow control methods for the blades.

The aims of this module are to:

• Describe the essential features of typical command and stability augmentation systems.
• Introduce contemporary handling qualities criteria and to show how they constrain flight control system design.
• 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 you should be able to:
1. 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. Analyse and design typical command and stability augmentation systems.
5. Interpret flying and handling qualities criteria in order to determine flight control system design constraints.

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

• 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 realizations
• 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

​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 you 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 you should be able to:

1. Recognise, implement and apply selected numerical integration routines for model simulation using modern software tools.
2. Describe air-vehicle dynamics as a set of ordinary differential equations and define and implement example air-vehicles in terms of their aerodynamic, control, mass and inertia characteristics. Evaluate and critically compare the resultant motion.
3. Identify the requirements for model testing, verification and validation, and demonstrate their application to an air-vehicle model.
4. 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.
5. 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 give you 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.
• Equations of motion for planetary re-entry.
• Ballistic entry and high angles of descent lifting entry.
• Introduction to shock-wave boundary layer interactions and shock-shock interaction.
• Real gas effects.
• Higher order computational methods for hypersonic flows.

To introduce you to the:

• Foundations of computational fluid dynamics and the mathematical properties of the governing equations.
• Basics of numerical analysis and numerical methods for partial differential and algebraic equations.
• Concepts of grid generation.
• CFD methods used for computing incompressible and compressible flows.
• 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.

​This module aims to give you the skills and understanding to assess 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.

On successful completion of this module you 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.

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)

​The aim of this module is to give you an appreciation of the factors influencing supercritical flow development and the interaction with other aerofoil / wing design features. The aim is also to provide you 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.

​The aim of this module is to provide fundamental insight into analytical methodologies and flight test techniques used for the derivation of linear and nonlinear mathematical models of an aircraft (fixed-wing, rotary-wing and UAVs).

​
• Mathematical Background
• Basic Systems and Estimation Theory,
• Regression Methods,
• Maximum Likelihood Methods,
• Frequency Domain Methods,
• Flight Test Design and Kinematic Consistency Check.
• Case Study

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

• Apply various classical and state-of-art- system identification tools to derive qualified flight dynamic models from flight test data.
• Plan a flight test sortie to obtain flight test data and conduct data compatibility analysis to create a reliable dataset most suited for system identification.
• Determine the appropriate structure model and estimate the model parameters validated by suitable approaches.
• Describe and categorise methods of system and parameter identification based on the desired mathematical model.
• Apply system identification tool to explore and understand better the nonlinear aerodynamic phenomenon.

​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.

• ​Demonstrate the ability to build a suitable CFD model for external flow simulation.
• Critically evaluate the limitations of these methods.

• 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.

• ​Use Laplace transform techniques to derive transfer functions of typical mechanical, electrical and fluid systems.
• Calculate and plot the step and frequency responses of linear systems.
• Derive the state equations for typical systems.
• Obtain discrete time representations of linear systems.
• Use MATLAB for matrix and systems algebra and to plot system responses.