Lab 1a
Overview of MATLAB and SIMULINK
Introduction
The purpose of this lab is to increase the users abilities in MABLAB and SIMULINK
aimed specifically at Control System Dynamics. These tools will increase the speed at which
controls problems can be solv

EXPERIMENT 3
Gyroscope Stabilized Platform
Objective
The purpose of this experiment is to design a controller that maintains the
direction of a gyroscope under base excitation. The controller can also be used to rotate
the gyro platform to a desired locat

EXPERIMENT 6
Lateral-Directional Stability and Control Augmentation
System Design
Objective
The objective of this experiment is to design a lateral-directional stability and
control augmentation system for an airplane.
Equipment Required
1. PC
2. MATLAB a

EXPERIMENT 8
Inverted Pendulum Stabilization
Proportional (/Derivative) Control Determined through LQR Analysis
This experiment will demonstrate the control of a system using full state feedback, where
the control system is designed using the principles o

EXPERIMENT 5
Longitudinal Stability and Control Augmentation System
Design
Objective
The objective of this experiment is to design a longitudinal stability and control
augmentation system for an airplane.
Equipment Required
1. PC
2. MATLAB and SIMULINK
Pa

EXPERIMENT 4
3-D Helicopter Control
Objective
The purpose of this experiment is to design an attitude controller for the 3-D
helicopter mechanism and to test the controller using the real time experimental set up.
Equipment Required
1.
2.
3.
4.
3-D helico

AE 4525
LAB 4 3D HELICOPTER CONTROLLER
IMPLEMENTATION AND EVALUATION
LAB 5A AIRCRAFT LONGITUDINAL SAS
DESIGN
OCTOBER 5, 2015
Announcements
Sign attendance sheet before leaving lecture.
This week: show up at the controls lab at the scheduled time for you

AE 4525
LAB 4
SEPTEMBER 28, 2015
Announcements
Sign attendance sheet before leaving lecture
This week: show up at Computer Lab at 3pm
Read Lab 4 before you start the lab (10 min read)
This week lab assumes you know Lab 3.
Lab 3 report (Group) is due

AE 4525
LAB 5C Longitudinal CAS Design
October 19, 2015
Announcements
Sign lecture attendance sheet before leaving lecture.
Come to the Computer Lab this week for 3 hours.
Lab 4 Report due at the START of Lab this week.
Mid-semester peer evaluation
D

AE 4525
LAB 6A LATERAL STABILITY
AUGMENTATION SYSTEM DESIGN
OCTOBER 26, 2015
Announcements
Sign lecture attendance sheet before leaving lecture
Come to the Computer Lab this week for 3 hours
Mid-semester peer evaluation
If you havent turned one in, pl

The first thing to note is that upon release in the experiment, the position of the helicopter
drops as a result of gravity. This was not modeled in our block diagrams. As a result, the
helicopter drops initially until the integrator corrects the error. T

In this problem we were asked to design a compensator for a gain margin of at least 10dB
and a phase margin of at least 50. We got a Kc=41.5, =4.5, and =18.5. Figure 21 shows
this design. The open loop poles are 0 and -2, and the closed loop poles are:
-6

Pre-Lab: Lab 8
By substituting in the following values, we are able to find the value of matrix A and B
(which are as follows).
mp = 0.21
mc = .815
lp = .305
g = 9.81
0
1 0
0
0
0
0 1
A
0 1.781 0 0
0 28.503 0 0
0
0
B
1.153
.742
Q is found by choos

#2
Pole Value
Damping
-3.57
1
-1.89
1
-.011
1
-4.067.32i
.485
Kay = -1
Roll Mode Time Constant
Tc=.280112
Tc=.529101
Spiral Mode, Minimum Doubling Time
T2 = 63
Dutch Roll Mode
=.485
=8.37
=4.05945
Frequency
3.57
1.89
.011
8.37
#3
Pole Value
-5.86
-1.681.7

EXPERIMENT 6
Longitudinal Stability and Control
Augmentation System Design
Objective
The objective of this experiment is to design a longitudinal stability and control
augmentation system for an airplane.
Equipment Required
1. PC
2. MATLAB and SIMULINK
De

AE 4525
Experiment #3
3-D Helicopter Control
Synopsis of Part A: Controller Design
This portion of the lab began by using provided systems for pitch, roll, and yaw of
a 3-D Helicopter mechanism in order to determine appropriate PID controller gains. The
p

A compensator with a 45 phase margin, a gain margin of at least 8dB, and a static velocity
error of 4s-1 was asked to be designed. Equation 4 shows the given transfer function, while
Equation 5 shows the given lead compensator equation. The compensator wa

We designed a block diagram using a trigonometric block in this problem. We then
compared it with the same block diagram minus the trigonometric block. Figures 29 and
30 show the block diagrams. Then, using each we ran tests at input steps of /10, /5,
/2,

Equation 7 was modeled in SIMULINK for this problem. Figure 17 shows the block
diagram, while 18 shows the response when the function is open loop. Figure 19 and 20
describe the response when the function is closed loop.
G(s)=1/(s2+s+4)
(7)
The open loop

Figure 8 shows the SIMULINK model of the given differential equation. Four given
conditions were tested with this model. The first had no initial conditions, and is shown in
Figure 9 (position) and 10 (velocity). The second set of conditions set original

AE 4525
LAB 6 PART B
NOVEMBER 2, 2015
Announcements
Sign lecture attendance sheet before leaving lecture
Come to the Computer Lab this week for 3 hours
Nothing is due this week!
Lab 6 individual report is due next week
Banked Turn
Truly banked
Vehicl