A study of thermo-structural design concepts for lifting entry vehicles, Volume 240
NASA, 1965 - Technology & Engineering - 165 pages
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12 g undershoot ablation temperature ablator and insulation Ablator Thickness ablator weight ablator's abort aluminum honeycomb aluminum single shell analyses angle of attack approach to touchdown ascent axial load bending Body Location bond line temperature bottom surface Buckling Cold Soak composite cone upper convective cost cracking cross section deflections design condition design criteria double wall concepts elevons fabrication face sheet fiberglass honeycomb fiberglass outer shell Fiberglass Shell filled H/C ablator filled honeycomb ablator fps reentry frame spacing H/C ablator design heat of vaporization heat shield honeycomb core depth Honeycomb Core Height inches inner shell insulation thicknesses internal pressure laminated ablator design Leeward longeron max q nose cap Overshoot percent pressure vessel refurbishing REQUIRED HONEYCOMB CORE shell structure shown in figure single aluminum shell space flight Stagnation Point steel outer shell stiffness Structural Sizes Structure Weight substructure thermal conductivity Thermal Strain versus Total Ablator trajectory Unit Weights upper surface