VDOL/spaceStation_1
spaceStation optimal control problem (matrix 1 of 14)
Name 
spaceStation_1 
Group 
VDOL 
Matrix ID 
2734 
Num Rows

99 
Num Cols

99 
Nonzeros

927 
Pattern Entries

927 
Kind

Optimal Control Problem 
Symmetric

Yes 
Date

2015 
Author

B. Senses, A. Rao 
Editor

T. Davis 
Structural Rank 
99 
Structural Rank Full 
true 
Num Dmperm Blocks

7 
Strongly Connect Components

3 
Num Explicit Zeros

0 
Pattern Symmetry

100% 
Numeric Symmetry

100% 
Cholesky Candidate

no 
Positive Definite

no 
Type

real 
Download 
MATLAB
Rutherford Boeing
Matrix Market

Notes 
Optimal control problem, Vehicle Dynamics & Optimization Lab, UF
Anil Rao and Begum Senses, University of Florida
http://vdol.mae.ufl.edu
This matrix arises from an optimal control problem described below.
Each optimal control problem gives rise to a sequence of matrices of
different sizes when they are being solved inside GPOPS, an optimal
control solver created by Anil Rao, Begum Senses, and others at in VDOL
lab at the University of Florida. This is one of the matrices in one
of these problems. The matrix is symmetric indefinite.
Rao, Senses, and Davis have created a graph coarsening strategy
that matches pairs of nodes. The mapping is given for this matrix,
where map(i)=k means that node i in the original graph is mapped to
node k in the smaller graph. map(i)=map(j)=k means that both nodes
i and j are mapped to the same node k, and thus nodes i and j have
been merged.
This matrix consists of a set of nodes (rows/columns) and the
names of these rows/cols are given
Anil Rao, Begum Sense, and Tim Davis, 2015.
VDOL/spaceStation
Space station attitude optimal control problem is taken from
Ref.~\cite{betts2010practical}. The goal of the space station
attitude control problem is to determine the state and the control
that minimize the magnitude of the final momentum while the space
statition reaches an orientation at the final time that can be
maintained without utilizing additional control torque. The state of
the system is defined by the angular velocity of the spacecraft with
respect to an inertial reference frame, EulerRodriguez parameters
used to defined the vehicle attitude, and the angular momentum of the
control moment gyroscope and the control of the system is the torque.
The specified accuracy tolerance of $10^{7}$ were satisfied after
thirteen mesh iterations. As the mesh refinement proceeds, the size
of the KKT matrices increases from 99 to 1640.
