## Optimum re-entry into the earth's atmosphere by use of a variable control forceWright Air Development Center, Air Research and Development Command, U. S. Air Force, 1960 - Science - 127 pages |

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### Contents

Section Page | 1 |

Appendix VDensityAltitude Function | 106 |

Appendix VIDeceleration Tolerance | 108 |

8 other sections not shown

### Common terms and phrases

aerodynamic control aerodynamic drag aerodynamically-controlled body Analysis Angle of incidence Appendix assumed axial Behavior of v(r Bounded deceleration considered constant constraint control force program coolant system Cooling Schematic defined Descent integration differential equations discussion earth earth's atmosphere end conditions equation 36 equations 146 equations of motion Euler equation Euler-Lagrange equations feasibility Figure 26 Figure 34 Figure 42 final conditions flight Flight Dynamics function given hard landing Heating rate implies initial conditions lift force magnitude maximum non-dimensional non-radiating body non-radiating cooling numerical integration orbit ordinary differential equations parameters particular problem proposed vehicle radiating body Range versus altitude re-entry satisfying Section set which minimizes sin2 singularities stagnation point Stefan-Boltzmann law surface Taylor series temperature thrust control thrust versus altitude thrust-controlled body tion total heat absorbed trajectory transverse Velocity versus veq(r WADC yield zero