SPACE AVIONICS - 2018/9
Module code: EEEM059
Expected prior learning: Module EEE3XXX Space Systems Design, or equivalent learning.
Previous Module: EEE3020 Spacecraft Bus Subsystems
Module purpose: Through a series of lectures and a design assignment, the module aims to give an introduction to the engineering design principles, requirements and solutions for satellite bus subsystems.
Electrical and Electronic Engineering
BRIDGES Christopher (Elec Elec En)
Number of Credits: 15
ECTS Credits: 7.5
Framework: FHEQ Level 7
JACs code: H430
Module cap (Maximum number of students): N/A
Prerequisites / Co-requisites
Given satellite avionics is primarily electronics based, an undergraduate level understanding of embedded computers and programming languages, such as C, will be highly useful.
Indicative content includes the following.
TELECOMMAND, TELEMETRY & CONTROL (TT&C)
1. Design function of TT&C system: launch and early operation phase (LEOP), end-of-life operations.
2. Communications Link: TT&C frequencies, Doppler curve - AOS, LOS TCA; link design: carrier-to-noise ratio, Eb/No, signal quality.
3. Tracking and ranging methods, worked examples.
4. Telemetry systems, formatting and synchronization, validation and authorization.
5. Packet Radio: HDLC and AX.25 packet formats, existing alternatives in packet radio.
6. Software Defined Radios: gnuradio introduction, common equipment and design philosophy to single chip solutions, the FUNcube Dongle and DVB tuners.
7. Ground-station design, Mission Operations Control Centre (MOCC), ground-support equipment, use during AIT and LEOP, orbit determination.
8. Tour of Surrey’s MOCC and Groundstation.
9. Common design practices: OBCs, OBDH, mission and risk tradeoffs
10. Processors: key design considerations, heritage controllers, SSTL and SSC examples.
11. Configurable Systems: FPGAs and logic cells, radiation tolerant design, IP cores, LEON3 processor and worked examples, on-chip triple modular redundancy.
12. Bus systems and performance: Topologies, ESA Bus, control area network (CAN-SU), I2C, FlexRay.
13. Radiation effects and mitigation - SEEs and total dose damage, example systems.
14. Sensor interfacing, ADC/DAC conversion.
15. Payload requirements: solid-state memories and buffering in store-and-forward operations.
16. Harnessing: key interfacing considerations, materials, existing specifications.
17. OSI Layer Stack: reduced design layers, common open-source tools.
18. Software standards: CCSDS, SOIS, PlugNPlay (PnP).
19. Real time aspects and Runtime Kernels: RTEMS, embedded Linux, FreeRTOS.
20. Software security and integrity: design rules, scrubbing, error detection and control.
21. Autonomous software: bootloader, non-volatile to volatile operations.
22. Common AOCS, sensors, propulsion control loop.
23. Methods and Tools: Requirements, design, coding, integration and test, revision control.
24. Simulation, in-circuit testing and debugging.
|Assessment type||Unit of assessment||Weighting|
|Examination||2 HOUR CLOSED BOOK EXAM||70|
|Coursework||COURSEWORK - 1 X DESIGN STUDY 1 X TECHNICAL REPORT||30|
Not applicable: students failing a unit of assessment resit the assessment in its original format.
The assessment strategy for this module is designed to provide students with the opportunity to demonstrate an understanding of principles, technologies and operation of a spacecraft’s core avionics and how they are driven by both the space environment and the mission requirements.
Thus, the summative assessment for this module consists of the following.
· Closed book examination [70%]
· Assignment 1 [15%]
· Assignment 2 [15%]
These are appropriate in marks and length to give the opportunity to demonstrate knowledge at an examination level and also in ‘hands-on’ experiences.
Any deadline given here is indicative. For confirmation of exact dates and times, please check the Departmental assessment calendar issued to you.
Formative assessment and feedback
For the module, students will receive formative assessment/feedback in the following ways.
· During lectures, by question and answer sessions
· By means of unassessed problem sheets (with answers/model solutions)
· During supervised laboratory sessions
· During meetings with his/her project supervisor
· Via the marking of written reports
· Via assessed coursework
- This module aims to introduce the student to the operating principles, design and operation of spacecraft avionics systems able to support a wide variety of spacecraft missions – primarily in Earth orbit.
|1||By the end of the module, the student should have a good understanding of the principles, technology and operation of a spacecraft's key ‘avionics’ or ‘platform’ systems and how the space and mission environments constrain these.|
|2||The student should be capable of applying this knowledge the produce a preliminary design of a spacecraft on-board computer to interface to particular subsystems in a robust manner. He/she should be able to analyse and evaluate the performance of key systems of the spacecraft.|
|3||The assignments will allow the student to emulate data, utilising existing databases or simulated sources, in order to understand the data requirements and design to evaluate its performance. The student will then produce a succinct and clear report describing this analysis.|
C - Cognitive/analytical
K - Subject knowledge
T - Transferable skills
P - Professional/Practical skills
Overall student workload
Methods of Teaching / Learning
The learning and teaching strategy is to facilitate learning through direct application of knowledge with real software and hardware tools in a laboratory environment using and expanding on worked examples.
In this class, avionics tools and associated modelling programs will be used to provide a ‘hands-on’ learning approach which will allow students to understand and appreciate the key blocks in spacecraft avionics through detailed examples. The programme’s aim to clearly define communications channels from the ground-station to the spacecraft. During the labs, supervision is on hand to guide the students through the tools and help during common problems.
Learning and teaching methods include the following.
- Lectures: 22 Contact Hours.
- Discuss & Demo Lectures: 11 Contact Hours
- Assignment 1 [15%]: Design of a Low-Cost On-Board Computer (OBC). Together given mission and data requirements, the students are to research processor technologies on how to build and interface an OBC to various sensors and buses. A paper study is required into justifying robust decisions in solving space avionics problems as hardware or software functions the following requirements: fault-tolerant memory storage, ADC/DAC, EDAC, and any radiation mitigation techniques. This is designed to allow students to fully appreciate spacecraft requirements and their importance.
- Assignment 2 [15%]: Implementation of Low-Cost On-Board Computer (OBC) Functions: Using existing software and hardware tools, the student is to programme, test and verify common space avionics design features in a lab environment. Additional flight computers will be made available as alternatives. This assignment is designed to allow students to explore their own expertise in avionics and in handling representative flight hardware.
Indicated Lecture Hours (which may also include seminars, tutorials, workshops and other contact time) are approximate and may include in-class tests where one or more of these are an assessment on the module. In-class tests are scheduled/organised separately to taught content and will be published on to student personal timetables, where they apply to taken modules, as soon as they are finalised by central administration. This will usually be after the initial publication of the teaching timetable for the relevant semester.
Reading list for SPACE AVIONICS : http://aspire.surrey.ac.uk/modules/eeem059
Programmes this module appears in
|Space Engineering MSc||1||Optional||A weighted aggregate mark of 50% is required to pass the module|
|Electronic Engineering with Space Systems MEng||1||Optional||A weighted aggregate mark of 50% is required to pass the module|
|Electrical and Electronic Engineering MEng||1||Optional||A weighted aggregate mark of 50% is required to pass the module|
|Electronic Engineering MEng||1||Optional||A weighted aggregate mark of 50% is required to pass the module|
|Electronic Engineering (EuroMasters) MSc||1||Optional||A weighted aggregate mark of 50% is required to pass the module|
|Electronic Engineering MSc||1||Optional||A weighted aggregate mark of 50% is required to pass the module|
Please note that the information detailed within this record is accurate at the time of publishing and may be subject to change. This record contains information for the most up to date version of the programme / module for the 2018/9 academic year.