ADVANCED GUIDANCE, NAVIGATION AND CONTROL - 2017/8

Module code: EEEM009

Module provider

Electrical and Electronic Engineering

Module Leader

LUCCA FABRIS A Dr (Elec Elec En)

Number of Credits

15

ECT Credits

7.5

Framework

FHEQ Level 7

JACs code

H643

Module cap (Maximum number of students)

N/A

Module Availability

Semester 2

Overall student workload

Independent Study Hours: 120

Lecture Hours: 33

Assessment pattern

Assessment type Unit of assessment Weighting
Coursework COURSEWORK 20%
Examination EXAMINATION 2 HRS 80%

Alternative Assessment

Not applicable: students failing a unit of assessment resit the assessment in its original format.

Prerequisites / Co-requisites

None.  

Module overview





Expected prior learning:  EEE3010 – Dynamics and Control of Spacecraft (6-dyc) and EEEM040 – Spacecraft Systems Design (7-ssd), or equivalent learning, which should include a knowledge of basic control theory.




Module purpose:  This module provides advanced understanding of the dynamics of satellites and of methods for controlling satellite motion.





 

Module aims

To develop an understanding of the complexities of real satellite dynamics, and of practical methods to determine and control spacecraft motions.

Learning outcomes

Attributes Developed
Describe real satellite orbits and how to model them.   K
Apply these models to representative cases such as rendezvous in space and the use of GPS in satellite navigation. P
Evaluate real world algorithms used for attitude and orbit control. C
Explain the limitations of sensors and actuators used on modern satellites.   K

Attributes Developed

C - Cognitive/analytical

K - Subject knowledge

T - Transferable skills

P - Professional/Practical skills

Module content





Indicative content includes the following.


Essential elements of control theory.
Overview of Satellite orbits. Review of Keplerian orbits and the most useful orbits for Earth orbiting satellites. Brief introduction to time and coordinate frames and the complexities of their definition.
Perturbation effects in real orbits. Mean and osculating elements, the disturbing function and Lagrange’s equations. Long and short periodic variations and secular evolution. Atmospheric drag modelling. Effects of Solar radiation pressure.
Orbit determination and Estimation. Data for orbit estimation and determination, GPS, Radar tracking, Least Squares method, Weighted Least Squares Methods, Batch Least Squares method, The Extended Kalman filter.
Rendezvous in space: Continuous thrust manoeuvres, Hill’s formulation and relative motion control, Epicycle description – inclusion of perturbing influences. Orbit control.
Attitude dynamics. Euler and kinematic equations. Quaternions and the evolution equations. Control moment gyroscopes.
Attitude determination and estimation: attitude sensors. Estimation methods: triad method and Quest algorithms, the Extended Kalman Filter.
Attitude control. Attitude actuators: momentum/reaction wheels, control moment gyroscopes, thrusters, magnetotorques. Design of control loops. Lead-lag compensators. Multivariable design.






 

Methods of Teaching / Learning





The learning and teaching strategy is designed to achieve the aims that students should


Develop an understanding of real satellite orbits and the factors that influence (perturb) these orbits.
Develop an understanding of real satellite attitude dynamics.
Apply and evaluate practical methods in order to control satellite orbits.
Apply and evaluate practical methods in order to control satellite attitude dynamics.


Learning and teaching methods include the following.


3-hour lecture per week x 10 weeks
Practical problem based assignment – 60 hours
Independent study and preparation for final exam – 60 hours


 





 

Assessment Strategy

The assessment strategy for this module is designed to provide students with the opportunity to demonstrate the following.  The written examination will assess the knowledge and assimilation of real satellite orbits and how to model them, evaluation of real world algorithms used for attitude and orbit control, and the limitations of sensors and actuators used on modern satellites.  The practical software-tool-based theoretical assignment will assess how the student can apply these models to representative cases such as rendezvous in space and the use of GPS in satellite navigation.

 

Thus, the summative assessment for this module consists of the following.

·         2-hour, closed-book written examination

·         Software-tool-based theoretical assignment (15 to 20 pages) due Tuesday Week 10.

 

Any deadline given here is indicative. For confirmation of exact date and time, 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.

·         Via the marking of written reports.

Reading list

Reading list for ADVANCED GUIDANCE, NAVIGATION AND CONTROL : http://aspire.surrey.ac.uk/modules/eeem009

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 2017/8 academic year.