- UCAS course code
- H402
- UCAS institution code
- M20
Master of Engineering (MEng)
MEng Aerospace Engineering
- Typical A-level offer: A*AA including specific subjects
- Typical contextual A-level offer: AAA including specific subjects
- Refugee/care-experienced offer: AAB including specific subjects
- Typical International Baccalaureate offer: 37 points overall with 7,6,6 at HL, including specific requirements
Fees and funding
Fees
Tuition fees for home students commencing their studies in September 2025 will be £9,535 per annum (subject to Parliamentary approval). Tuition fees for international students will be £34,000 per annum. For general information please see the undergraduate finance pages.
Policy on additional costs
All students should normally be able to complete their programme of study without incurring additional study costs over and above the tuition fee for that programme. Any unavoidable additional compulsory costs totalling more than 1% of the annual home undergraduate fee per annum, regardless of whether the programme in question is undergraduate or postgraduate taught, will be made clear to you at the point of application. Further information can be found in the University's Policy on additional costs incurred by students on undergraduate and postgraduate taught programmes (PDF document, 91KB).
Scholarships/sponsorships
The University of Manchester is committed to attracting and supporting the very best students. We have a focus on nurturing talent and ability and we want to make sure that you have the opportunity to study here, regardless of your financial circumstances.
For information about scholarships and bursaries please see our undergraduate fees pages and check the Department's funding pages .
Course unit details:
Space Systems
Unit code | AERO21111 |
---|---|
Credit rating | 10 |
Unit level | Level 2 |
Teaching period(s) | Semester 1 |
Available as a free choice unit? | No |
Overview
The design and operation of spacecraft is a multidisciplinary operation covering many aspects of engineering. This course provides an introduction to the physics of orbits and the space environment. The basic physics of spacecraft propulsion, orbit manoeuvres and the key drivers for thermal design, power systems, communication systems and attitude control systems are introduced.
Aims
This course is intended to introduce students to the topic of spacecraft flight and spacecraft subsystems to develop an understanding of the basic analytical techniques and the key concepts in this area. On completion this course students will have a basic understanding of spacecraft applications, mechanics of orbits, basics of spacecraft propulsion, thermal design, power systems, communications systems, attitude control system and the influence of the spacecraft environment on spacecraft design.
Syllabus
1. Space Environment : (1hr)
Students will develop an understanding of the various environmental factors that influence spacecraft design and be able to describe these factors and their effects on design and identify particular orbits where certain factors may dominate.
2. Orbit mechanics: (3hrs)
Students will develop an understanding of the derivation of the velocity equation for the two body problem and will be able to apply these equations to analyse satellite motion. Students will be introduced to the concepts of n-body problems.
3. Orbit transfers and manoeuvres (2hrs)
Students will be able to apply the velocity equations developed from two body motion to derive and determine delta vee requirements and order of required burns for single burn transfers, two burn transfers such as the Hohmann minimum energy transfer, rendezvous manoeuvres and plane change manoeuvres. Students will also be able to assess the relative pros and cons of transfer methods such as the bi-elliptic transfer and the one tangent transfer.
4. Propulsion & Launch vehicles (3hrs)
Students will be introduced to basic propulsion system analysis using the rocket equation and will be introduced to the key types of spacecraft propulsion systems. Students will be able to undertake analysis of launch system designs including multistage systems using the ideal rocket equation and be aware of the limitations of this analysis. Students will develop an understanding of optimum staging for multistage systems. Students will be able to describe the influence of launch site location on the required delta vee to reach Earth orbit.
5. Thermal design(2hrs)
Students will be introduced to the basic physics of spacecraft thermal design, radiative balance, material properties, passive control techniques, active control techniques. Students will be able to undertake basic analysis of equilibrium temperature of a spacecraft as well as basic temporal analysis.
6. Power systems (2hrs)
Students will be introduced to the key technologies employed in spacecraft power systems; Solar arrays, Batteries, Alternative power sources. Students will be able to undertake basic analysis of power systems requirements and sizing.
7. Communications(2hrs)
Students will be introduced to spacecraft communications architecture, Radio frequency digital modulation and encoding and communications Link budget analysis. Students will be able to undertake basic analysis of communication systems using the link budget equation.
8. Attitude control (2hrs)
Students will be introduced to the key technologies employed in spacecraft attitude determination and control. Students will be able to undertake basic analysis of requirements for attitude control systems.
Knowledge and understanding
Practical skills
Assessment methods
Method | Weight |
---|---|
Other | 10% |
Written exam | 50% |
Report | 40% |
Other - online test
Feedback methods
via Blackboard
Study hours
Scheduled activity hours | |
---|---|
Assessment practical exam | 40 |
Assessment written exam | 2 |
Lectures | 22 |
Tutorials | 11 |
Independent study hours | |
---|---|
Independent study | 25 |
Teaching staff
Staff member | Role |
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Katherine Smith | Unit coordinator |