Aerothermodynamics of Launchers and Re-Entry Vehicles S3 (SPACE)
Module aims
This course explores the unique flow physics experienced by vehicles travelling at hypersonic speeds in an atmosphere. Compressible flow relations introduced in previous years are modified for hypersonic conditions and the role of viscosity is considered in the form of compressible boundary layers and shock/boundary-layer interactions. These building blocks are applied to predict the aero-thermodynamic performance of past and current spacecraft designed for atmospheric entry missions and evaluate new and emerging technologies that meet future mission requirements. The equations of motion to describe an entry mission and the entry environment itself are also defined.
Learning outcomes
On successfully completing this module, you should be able to:
1. Appraise the extreme environments experienced by spacecraft during atmospheric entry and apply this knowledge to analyse the aero-thermodynamic performance of aerospace vehicles at hypersonic conditions, including the role of compressible boundary layers and shock/boundary-layer interactions;
2. Evaluate existing state-of-the-art designs and technologies for entry-descent-landing missions, based on an appreciation of the advantages and limitations of the various tools and methodologies available for doing so;
3. Evaluate the contrasting demands of re-entry missions on Earth and Mars, based on the parameters which affect the trajectories (spacecraft dynamics and atmospheric conditions);
4. Analyse the performance of current entry vehicles (including heat-shield technologies) and make appropriate design choices based on defined mission parameters;
5. Evaluate new and emerging technologies for future entry-descent-landing missions, including deployable ad inflatable aero-decelerators for high payloads missions to Mars.
Module syllabus
• Motivation for access to space incl. historical context;
• Mission requirements for launch and re-entry vehicles;
• Overview of the composition and characteristics of the Earth’s upper atmosphere;
• Basic principles of 3DOF and 6DOF re-entry trajectory modelling;
• Approximate methods for estimating lift and drag at high speed;
• Lifting high speed vehicles: Space-planes, wave-riders incl. ramjets, scramjets, etc.;
• Non-lifting high speed vehicles: Rockets – aerothermodynamics & propulsion;
• Re-entry vehicle design overview: challenges of Entry, Descent, and Landing;
• E: Entry vehicle heat shield design: conventional and advanced concepts;
• D: Descent stage aerodynamic (parachute) and retropropulsive (thrusters) decelerators;
• L: Landing technologies: airbags, thrusters, legs, etc.;
• Viscous compressible flow including shock-wave/boundary-layer interactions;
• Introduction to hypersonic aerothermodynamics;
• Hypersonic boundary layer theory incl. transition;
• High temperature gas dynamics: real gas effects incl. basic chemistry;
• Aerodynamic heating: incl. Reynolds analogy, empirical methods, ablation;
• Numerical and experimental approaches to hypersonic research;
• Case study: Mars EDL for future human missions;
• Economics/ethics/legislation of access to space.
Teaching methods
The module will be delivered primarily through large-class lectures introducing the key concepts and methods, supported by a variety of delivery methods combining the traditional and the technological. The content is presented via a combination of slides, whiteboard and visualizer.
Learning will be reinforced through tutorial question sheets.
Assessments
This module presents opportunities for both formative and summative assessment.
You will be formatively assessed through progress tests and tutorial sessions.
You will have additional opportunities to self-assess your learning via tutorial problem sheets.
You will be summatively assessed by a written closed-book examination at the end of the module.
| Assessment type
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Assessment description
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Weighting
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Pass mark
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| Examination
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Closed-book written examination
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100%
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50%
|
You will receive feedback on examinations in the form of an examination feedback report on the performance of the entire cohort.
You will receive feedback on your performance whilst undertaking tutorial exercises, during which you will also receive instruction on the correct solution to tutorial problems.
Further individual feedback will be available to you on request via this module’s online feedback forum, through staff office hours and discussions with tutors.
Reading list
Reading
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Anderson, John D.,
Third edition., American Institute of Aeronautics and Astronautics Inc
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Cambridge University Press
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Cambridge University Press; Cambridge University Press
Module leaders
Professor Paul Bruce