lowThrust optimal control problem (matrix 3 of 13)
Name lowThrust_3
Group VDOL
Matrix ID 2707
Num Rows 7,064
Num Cols 7,064
Nonzeros 80,645
Pattern Entries 80,645
Kind Optimal Control Problem
Symmetric Yes
Date 2015
Author B. Senses, A. Rao
Editor T. Davis
Structural Rank 7,064
Structural Rank Full true
Num Dmperm Blocks 1
Strongly Connect Components 1
Num Explicit Zeros 0
Pattern Symmetry 100%
Numeric Symmetry 100%
Cholesky Candidate no
Positive Definite no
Type real
Download MATLAB Rutherford Boeing Matrix Market
Optimal control problem, Vehicle Dynamics & Optimization Lab, UF       
Anil Rao and Begum Senses, University of Florida                       
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.                            
Low-thrust orbit transfer optimal control problem is taken from        
Ref.~\cite{betts2010practical}. The goal of the low-thrust orbit       
transfer problem is to determine the state and the control that        
minimize the fuel consumption during the orbit transfer of a           
spacecraft that starts from a low-earth orbit and terminates at the    
geostationary orbit via low-thrust propulsion systems.  The highly     
nonlinear dynamics of the low-thrust orbit transfer problem is given   
in modified equinoctial elements (state of the system) and the thrust  
direction (control of the system).  Furthermore, the low-thrust        
optimal control problem is a badly scaled problem because of the       
small thrust-to-initial-mass ratio, that is typically on the order of  
$O(10^{-4})$, and the long orbit transfer duration. Badly scaling of   
the problem leads to a lot of delayed pivots. The specified accuracy   
tolerance of $10^{-8}$ were satisfied after thirteen mesh iterations.  
As the mesh refinement proceeds, the size of the KKT matrices          
increases from 584 to 18476.                                           
  title={Practical Methods for Optimal Control and Estimation Using    
     Nonlinear Programming},                                           
  author={Betts, John T},                                              
  publisher={SIAM Press},                                              
  address = {Philadelphia, Pennsylvania},