## NASA Technical Report, Issues 357-362 |

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### Contents

SUMMARY | 1 |

PROBLEM DEFINITION | 7 |

CONSTRUCTION OF TRANSFORMED SOLUTION | 14 |

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analysis analytic angular momentum angular velocity APPENDIX associated eigenvalue problem attitude error bare-slab eigenvalues behavior boundary branch cut center of mass computed cone angle constant contour control law corresponding Crack extending equally crack length curve defined by equation definite parity determined differential dual-spin eigenvalue condition equa equations of motion error function expansion coefficients Figure finite follows function given by equation Grenade initial condition initial distribution integral interval Langley Research Center Laplace transformation Liapunov functions linear matrix maximum principle monoenergetic MSL DEG Neutron Transport nominal spin axis nutation obtained optimal control orthogonality relations parameters plane present pseudo-eigenvalues Re(s reflectors region response envelope rivet forces s e S2i s-plane satisfy shown singular slab half-thickness spacecraft damper stability diagram stress-intensity factor stringer spacing symmetric terminal imbedding terminal manifolds theorem Thick-slab time-dependent tion torque trajectory transformed solution Transport Theory values vector wheel damper