Able to develop mathematical models of control sys

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Able to develop mathematical models of control systems containing mechanical, electrical and electronic components: able to form simulation models of control systems and assess their validity:

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Module Title:	Control Engineering I
Module Code:	6ET006
Component Number:		1	Element Number:
Component Titles		AIRCRAFT ROLL STABILISATION SYSTEM
Weighting:		30%
Learning Outcomes to be assessed:
US - Underpinning Science and Mathematics - able to develop mathematical models of control systems containing mechanical, electrical and electronic components: able to form simulation models of control systems and assess their validity: able to analyse hybrid control systems and identify parameters that influence prominent aspect of the transient response
Marking Criteria:
Written reports produced using IT skills. In order to achieve 40% (minimum pass grade) students are expected to produce reports that show a basic understanding of the subject area using standard available material. The reports are to be produced electronically using relevant illustrations, where applicable. In order to achieve above 70% students must produce reports that demonstrates extensive, well researched knowledge of the subject area, expressing competent personal opinions and arguments. The reports must be electronically produced, well-illustrated and adequately referenced.
The minimum pass mark is 40%.
Assignment Issued:
Latest dates for submission:
Assignments submitted after the deadline, and without an authorised extension, will be graded F0.
Please mark your assignment for the attention of:
You should make it very clear what sources of information have been used; where material/information from these sources is quoted, it must be clearly referenced using the Harvard Referencing System. (Details can be obtained from Learning Centre pages on the University website).

 

 

 

RESIT ASSIGNMENT – AIRCRAFT ROLL STABILISATION SYSTEM

The transfer function of an aircraft roll stabilisation system is measured by perturbing the aircraft about the roll axis and recording the resultant angular displacement. The open-loop transfer function is found to be:

Motion about this axis must be controlled. The outline control structure shown below has been suggested.

 

As the engineer responsible for designing the control system, your tasks are listed below.

Part 1: Phase Lead Controller Design (40%)

1. Obtain the open-loop Bode diagram (without controller).
2. Hence find the gain margin (GM) and phase margin (PM).
3. Using the design rules in the Control Engineering Data Sheets, obtain the TF of the “equivalent” 2nd order TF.
4. Compare the unit step responses of the equivalent 2^nd order TF and the actual closed loop system (without controller), and comment on the accuracy of the equivalent.
5.             Design a prototype phase lead controller,, to give a phase margin, .
6. Using the design rules in the Control Engineering Data Sheets, obtain the TF of the “equivalent” 2nd order TF (including controller).
7. Compare the unit step responses of the equivalent 2^nd order TF and the actual closed loop system, and comment on the accuracy of the equivalent.

Part 2: Digital Controller Implementation (60%)

1. Using the phase lead controller transfer function obtained above as a prototype, design a digital controller using the Bilinear Transform
2. Select a suitable sampling increment, T, given the following constraints:
   1. the minimum value for T is, T= 1mS
   2. the value of T should be as large as possible, but must provide a unit step response that is within a 5% error band around the unit step response obtained from the ‘ideal’ closed loop system designed in Part 1.