**Matrix: VDOL/spaceStation_1**

Description: spaceStation optimal control problem (matrix 1 of 14)

(undirected graph drawing) |

Matrix properties | |

number of rows | 99 |

number of columns | 99 |

nonzeros | 927 |

structural full rank? | yes |

structural rank | 99 |

# of blocks from dmperm | 7 |

# strongly connected comp. | 3 |

explicit zero entries | 0 |

nonzero pattern symmetry | symmetric |

numeric value symmetry | symmetric |

type | real |

structure | symmetric |

Cholesky candidate? | no |

positive definite? | no |

author | B. Senses, A. Rao |

editor | T. Davis |

date | 2015 |

kind | optimal control problem |

2D/3D problem? | no |

Additional fields | size and type |

b | full 99-by-1 |

rowname | full 99-by-97 |

mapping | full 99-by-1 |

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, Euler-Rodriguez 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.

Ordering statistics: | result |

nnz(chol(P*(A+A'+s*I)*P')) with AMD | 1,188 |

Cholesky flop count | 2.3e+04 |

nnz(L+U), no partial pivoting, with AMD | 2,277 |

nnz(V) for QR, upper bound nnz(L) for LU, with COLAMD | 1,773 |

nnz(R) for QR, upper bound nnz(U) for LU, with COLAMD | 2,922 |

For a description of the statistics displayed above, click here.

*Maintained by Tim Davis, last updated 04-Jun-2015.Matrix pictures by cspy, a MATLAB function in the CSparse package.
Matrix graphs by Yifan Hu, AT&T Labs Visualization Group.
*