Analysis of an Autopilot using MATLAB and Simulink - Engineering Assignment Help

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Assignment Task :

Assignment Briefing Sheet (2020/21 Academic Year) 
This Assignment assesses the following module Learning Outcomes (from Definitive Module  Document): 
LO1 -
Explore advanced methods of control for engineering systems using advanced  mathematical modelling 
LO2 - Evaluate appropriate equipment and software to implement digital controllers for  engineering systems; 
LO3 - Simulate the dynamic performance of a control system
 

Assignment Brief: 
The motion of an aircraft can be defined by a set of complex equations. The basic coordinate axes and  forces acting on an aircraft are shown in the figure below: 

Axes

 

Figure 1: Basic Co-Ordinate Axes and forces on an aircraft 
The following assumptions can be made: 
? The aircraft is in a steady cruise at a constant altitude and velocity. As such, thrust, drag, weight  and lift balance each other out. 
? A change in pitch angle will not change the speed of the aircraft under any circumstance 
As such, the state space model can be defined as follows: 
 
Equation 2: State Space Model of Aircraft motion 
By using the methods shown in the Lectures for state space, show the process of calculating the  transfer function of this system. In addition, show the final transfer function obtained from MATLAB to  validate this answer. 
You will then be required to identify and comment on the behavior of the closed loop pitch response of  the aircraft. This will be achieved by conducting the Closed Loop Step Response and Open Loop Nyquist Plot and, based on your understanding of control systems, comment on the stability of the  system. 
Following this, the aircraft will be required to achieve the following characteristics: 
? Overshoot less than 10% 
? Settling time less than 10 seconds 
? Steady-state error less than 2%
 

 

 

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