Astronautics and Space Engineering MSc

To demonstrate how to develop the design of a space system, from the initial mission objective, through requirements definition, concept development and trade-off, and through to a baseline design.

• Brief history & context: Background to the development of space, agencies, funding, future missions.

• Introduction to space system design methodology: requirements, trade-off analysis, design specifications, system budgets.

• Spacecraft sub-systems design: Structure & configuration; Power, the power budget and solar array and battery sizing; Communications and the link budget; Attitude determination and control; Orbit determination and control; Thermal control.

• Mission and payload types Spacecraft configuration: examples of configuration of spacecraft designed for various mission types; case study.

• Introduction to cost engineering.

• Space and Spacecraft Environment: Radiation, vacuum, debris, spacecraft charging, material behaviour and outgassing.

• Assembly, Integration and Test processes; Launch campaign; Space mission operations.

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

1. Establish quantitative mission requirements.

2. Characterise the mission design drivers and identify solution options at system and subsystem level.

3. Evaluate the performance of options by means of a trade-off analysis.

4. Produce a baseline system definition, with appropriate engineering budgets.

5. Outline a programme plan to verify the system performance.

To provide an understanding of the physics fundamentals and thermofluid dynamic concepts underlying space propulsion and their implications for launch vehicle and spacecraft system performance and design.

Introduction: The interactions between propulsion system, mission & spacecraft design.

Spacecraft Performance: Mission requirements, Vehicle dynamics, Tsiolkovski rocket equation, Launch vehicle sizing and multi-staging. Illustrative launcher performance (Ariane, Shuttle programmes, Falcon...). Launch site/range safety constraints, Geostationary orbit acquisition.

Launch Vehicles: Current Options: Vehicle design summaries, Orbital transfer vehicles, Comparative launch costs, and Reusable launchers.

Propulsion Fundamentals: Systems classification, Nozzle flows, Off-design considerations (under/over-expanded flows), Thermochemistry.

Space Propulsion Systems and Performance: Propellants and combustion, Solid and liquid propellant systems, Engine cycles: Spacecraft propulsion—orbit raising, station-keeping and attitude control, Propellant management at low-g—alternative storage and delivery systems: Electric propulsion, Separately Powered rocket performance, Low thrust manoeuvres, Thruster concepts and configurations.

Alternative propulsion concepts and future developments: Overview of potential alternatives to current (or common) propulsion systems and their advantages, problems, or feasibility. This includes Sails, Nuclear propulsion, Air-Breathing, Space Elevators.

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

1. Evaluate the constraints imposed by launch vehicle performance & operation on mission analysis.

2. Assess the impact of molecular mass, toxicity, and storability of the propellant on thruster performance and cost.

3. Design system points, off-design calculations, and mission analysis using fundamental physics relationships.

4. Critically assess the relative strengths of the principal options for propulsion systems in relation to both boosters and secondary spacecraft propulsion for a range of mission applications.

5. Estimate thruster performance using fundamental methods while appraising the limitations of the techniques.

To provide a critical understanding of the basic principles of Astrodynamics and Mission Analysis and of their application to typical mission analysis problems.

Astrodynamics - Keplerian orbital motion

• Newton’s Law of Gravitation.
• Equations of Motion for a two body system.
• Motion in a Central Field. Conic Sections.
• The Geometry of the Ellipse. Kepler's Laws.
• The Position-Time Problem.
• The Energy Integral.
• The Satellite Orbit in Space.

Astrodynamics - Orbit Perturbations. 

• Variation of Parameters.
• Perturbations Caused by Earth Oblateness.
• Perturbations Caused by a Third Body.
• Triaxiality Perturbations.

Mission analysis

• Orbit Selection for Mission Design.
• Hohmann Transfer and Inclinations Changes.
• Hyperbolic Passage.
• Patched Conics Interplanetary trajectories.

On completion of this module you should be able to:

1. Apply appropriate techniques to solve a range of practical astrodynamics and mission analysis problems.

2. Describe widely used orbit types and their applications, and evaluate the perturbations on these orbits.

3. Plan impulsive orbital manoeuvres to achieve mission design requirements.

The aim of this module is to provide an introduction to the principles and architectures of aerospace position, navigation and timing (PNT) systems, review and discuss sources of information and technologies aiming to enhance the performance, resilience and trust of such systems.

• Overview of navigation principles and applications.

• Measurement principles and introduction to metrology.

• Inertial Navigation Systems: sensors, performance and integration.

• Space-based PNT sources: GNSS, LEO, star/sun trackers, opportunistic sources.

• Other sources: legacy, visual, magnetic, terrestrial opportunistic.

• Time information sources.

• Processing techniques and technologies: Pre-processing Acquisition, tracking and discrimination Sensor fusion Machine learning and AI.

• Integrity, trust and cybersecurity for PNT. 

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

1. Categorise sources of position and timing information according to main performance characteristics and suitability to practical scenarios.
2. Propose and evaluate the design of position, navigation and timing (PNT) system considering real-life scenarios and requirements.
3. Set up commonly used algorithms for PNT systems.
4. Evaluate the performance of PNT systems navigation systems using domain and application-related metrics.
5. Assess performance limitations of PNT systems due to the typical error sources of individual sensors and of the complete system.

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

•  Background to Finite Element Methods (FEM) and its application.

•  Introduction to FE modelling: Idealisation, Discretisation, Meshing and Post Processing.

•  Tracking and controlling errors in a finite element analysis. ‘Do’s and don’ts’ of modelling.

•  Illustration of basics of FEM using the Direct Stiffness method to define both terminology and theoretical approach.

•  Problems of large systems of equations for FE, and solution methods.

•  FE method for continua illustrated with membrane and shell elements.

•  Nonlinear analysis in FEM and examples.

•  A series of NASTRAN application sessions targeted at knowledge based practical approach to implementing FEM models

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

1. Distinguish, analyse, and evaluate the underlying principles and key aspects of practical application of FEA to structural problems.

2. Distinguish, analyse, and evaluate the main mathematical and numerical aspects of the element formulations for 1D, 2D and 3D elements.

3. Build and analyse finite element models based on structural and continuum elements with proper understanding of limitations of the FEM.

4. Interpret results of the analyses and assess error levels.

5. Critically evaluate the constraints and implications imposed by the finite element method

To provide fundamental knowledge on control and estimation theories and their application in guidance navigation and control schemes in space systems.

Control and Estimation Theory: 

• State Space Representation of Dynamic Systems.

• Stability and Controllability of Linear and Non-Linear Systems.

• Design of Feedback Control Laws (PID, LQR).

• Observability and Estimation of Dynamic Systems.

• Kalman Filters (Linear, Extended).

• Definition and Solution of Optimisation Problems.

• Space-Based Applications.

• GNC applications for Spacecraft Rendezvous and/or Planetary Rovers.

• Optimal Manoeuvres in Space 

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

1. Model and characterise the dynamics of space systems operations in their orbital operations.

2. Analyse the stability, controllability and observability of dynamic systems, with a particular focus on space applications.

3. Design, implement and assess performance of appropriate control and estimation techniques to solve a range of space-based GNC problems using MATLAB.

4. Describe, analyse, and evaluate numerical and simulation results in technical reports.

To provide you with an introduction to the state-of-the-art in applied mathematics and techniques in astrodynamics and trajectory design.

1. Refresher of Matlab Programming:

• • The Matlab Environment.
• • Matrices and Operators.
• • Scripts and Functions.
• • Loops.
• • Programmer’s toolbox.

2. Lambert Arc:

• • Two-body orbital boundary-value problem.
• • Minimum energy transfer.
• • F & G Solutions for elliptic orbits.
• • Differential Correctors and Continuation methods.

3. Pork-chop plots:

• • Hohmann transfer and Patched Conics.
• • Lambert arc grid search and visualisation.
• • Earth Escape and C3.
• • Synodic Period.

4. Low thrust trajectory design:

• • Gravity losses.
• • Method of variation of parameters and sub-optimal control laws.
• • Edelbaum Solution.
• • Shape-base methods.

5. Circular Restricted Three Body Problem:

• • Synodic reference frame.
• • Equations of motion.
• • Jacobi Integral.
• • Equilibrium Points.
• • Zero Velocity Curves.

6. Libration Point Orbits:

• • Stability of the equilibrium points.
• • Classification of Fixed Points.
• • Periodic Orbits near L1 and L2.
  
  

On successful completion of this module you should be able to:
1. Write reliable code to solve realistic mission analysis scenarios.
2. Apply a range of applied mathematical techniques to solve trajectory design problems and be able to independently expand on appropriate tools and know-how when necessary.
3. Reflect on current challenges for trajectory design, and their synergy with space system engineering, for both Earth observation and interplanetary missions.
4. Identify most common non-Keplerian orbit types and explain their applications.

This module aims at provide you with a thorough understanding of satellite commutations system design and overview current approaches of communications data link between spacecraft and ground station.

• Overview of Satellite Communications.
• Satellite Terminals, Space and Ground Segment.
• Satellite Communications for Air Mobility.
• Multiplexing and Transmission Techniques.
• Analogue and Digital Modulation Schemes.
• Communications System Design (Uplink/Downlink Model, Noise, SNR, Bit Error Rate).
• Link Budget Design.
• Antenna System and Ground Terminal Design.
• Channel Capacity Techniques.

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

1. Distinguish the fundamental principles of satellite communications.

2. Assess different types of modulation and multiplexing techniques.

3. Analysis link budget & communications system design and air mobility.

4. Estimate different antenna types, characteristics and applications.

5. Evaluate channel capacity and coding techniques.

To provide an introduction to spacecraft kinematics and dynamics, focussing on rigid body dynamics and control of Earth orbiting satellites.

Overview:
• How does spacecraft dynamics relate to satellite control problem?
• AOCS (Attitude & Orbit Control Sub-system) design process.
• Interactions with other sub-systems.
• Control loop representation.

Kinematics:
• Attitude representation: Euler angles, Euler parameters (quaternions).
• Common reference frames (inertial, orbit referenced).
• Transformation between reference frames.
• Small angle linearisation (reduction of 3dof control problem to 1dof).

Rigid body dynamics:
• Euler's equations for rigid bodies.
• Axisymetric spacecraft & free-body dynamics.
• Disturbance torques.

Application to spacecraft control:
• Simulating spacecraft free-body kinematics & dynamics in MATLAB.
• Sensor basics (sun sensors, star trackers, rate sensors).
• Actuator basics (thrusters, reaction wheels).
• Rate control of rigid body spacecraft.
• Attitude control of 3-axis stabilised spacecraft.

To demonstrate how to develop the design of a space system, from the initial mission objective, through requirements definition, concept development and trade-off, and through to a baseline design.

• Systems Engineering Principles and Standards.

• Product Lifecycle Management.

• Stakeholder Analysis and Requirements Definition.

• Architecting Complex Systems.

• System Modelling and Analysis.

• Tradespace Exploration and Decision Making in Engineering Systems Design.

• Human and Programmatic Factors in Systems Design.

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

1. Describe and implement established systems engineering standards and methodologies, as well as newly emerging approaches.

2. Structure and manage the lifecycle of complex engineering systems.

3. Apply systems engineering methods and tools to design and develop complex systems.

4. Formulate and analyse complex system architectures using quantitative tools.

5. Incorporate human and programmatic factors, including endogenous and exogenous influences, in the design and management of complex engineering systems.

Payloads are the reason for the mission and pay for it: their design is central to mission system design. This module links user requirements to payload system design with particular relevance to imaging payloads (cameras, radar) and their application in Earth observation – especially climate science. On completion of this module a system engineer should be able to relate (science) user requirements to payload system design, to integrate the payload effectively into the mission system design.

• The payload as part of a system; the flow-down of requirements.

• Payload principles, especially for imaging payloads.

• Quantifying payload performance (e.g. resolution, signal-to-noise ratio) from payload system parameters (size, power, data-rates, etc.).

• Imaging payload case studies.

• Earth system introduction (components – atmosphere, oceans, land, cryosphere – and their interactions) – as a prime justification for future Earth Observation (EO) missions.

• EO measurement techniques (relating signal to target properties).

• Quantifying user requirements and relating these to imager requirements.

• Climate change science and derived observation requirements.

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

1. Relate user requirements to payload requirements.

2. Develop the system design for an imaging payload.

3. Quantify payload performance, e.g. resolution and SNR.

4. Relate Earth system science, especially climate science and its related observation requirements, to space mission design.