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Sensitivity Coefficient Study
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1.2700 Thrust-To-Weight Ratio allowable analysis angle axial buckling calculated changes configuration considered construction core core thickness corrugation criteria cylinder depth determine direction distribution effect equal equation executive face factor Figure flight force format function GASP given head honeycomb inches included increase input instability Integral Interstage Launch Vehicle length load material matrix maximum minimum modulus Monocoque names needed optimization optimum option output panel parameters percent perform presented pressure printed properties radius range ring routine shear sheet shell skin thickness spacing specified Stage station stiffened stored strength stress stringer Structural Weight subprogram subroutine Table tank tape thickness thrust Thrust-To-Weight Ratio trajectory Ullage values variable versus Waffle Weight Sensitivity Coefficients Wind Yes Yes Yes yield