Review for Exam 1 Fall 2008 Modern Control Potential Topics on Exam 1: 1. State-space representation (SSR): state vector, control vector, output vector, and matrices
A, B, C, and D. 2. Linearization: 1) select reference pt (equilibrium or operating point)
Syllabus MAE 4720/7720 Modern Control Fall 2008 Dr. Craig Kluever KlueverC@missouri.edu
Reference texts: Modern Control Engineering (4th ed), K. Ogata, 2002 (not required) Optimal Control, F.L. Lewis, 1986 (not required)
Course Description: Modern Control
Syllabus MAE 4720/7720 Modern Control Fall 2008 Dr. Craig Kluever KlueverC@missouri.edu
Reference texts: Modern Control Engineering (4th ed), K. Ogata, 2002 (not required) Optimal Control, F.L. Lewis, 1986 (not required)
Course Description: Modern Control
Homework Set #1: MAE 4720/7720 Modern Control Fall 2008 Due September 11, 2008 Problem 1. A simple RLC circuit has the following voltage equation (obtained by applying Kirchhoffs law):
di 1 ea = L + Ri + idt dt C0
t
where ea is the applied voltage (input)
Homework Set #2: MAE 4720/7720 Modern Control, Fall 2008 Due Sept 18, 2008 Problem 1: The governing equation for a simple mass-spring system is
+ 4 z = 0 z
where z is the position of the mass, measured from equilibrium. There is no forcing function (no i
Homework Set #2: MAE 4720/7720 Modern Control, Fall 2008 Solution The governing equation for a simple mass-spring system is
+ 4 z = 0 z
a) the SSR is shown below:
x = [z
T z]
0 1 A= 4 0
1 2 = +4=0 4
Eigenvalues: det ( I A) = det
Therefore, the eigenv
Homework Set #3: MAE 4720/7720 Modern Control Fall 2008 Due October 7, 2008
Problem 1: Consider again the motion of an unpowered (gliding) reusable launch vehicle (RLV) first introduced in HW#1. The vehicle parameters are Vehicle mass m = 4000 slugs Wing
Homework Set #4: MAE 4720/7720 Modern Control Fall 2008 Due October 28, 2008
Problem 1: Given the quadratic scalar function F to be minimized:
2 2 2 Minimize F (u) = 2u1 + 6u 2 + 0.3u 3
subject to the two linear equality constraints h1 (u) = u1 4u 2 = 0 h
Project I, MAE 4720/7720 Modern Control, Fall 2008 Due date: Oct 30
The below diagram is from the 1971 MIT report on the Apollo lunar descent guidance design. The spacecraft (LM) fires a short de-orbit burn to descend from a circular lunar parking orbit,
Ascent Trajectory Optimization
Powered Explicit Guidance (PEG)
Powered Explicit Guidance (PEG) is the iterative guidance algorithm that solves an optimal control problem in order to determine the thrust-steering vector profile for 2nd stage (after SRB se