Thermal Protection Systems. Application Research Of Materials Properties And Structural Concepts

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Report Number: ML TDR 64-82
Author(s): Hurwicz, Henryk, Mascola, Robert
Corporate Author(s): Avco Corp Wilmington Mass Research And Advanced Development Div
Laboratory: AF Materials Laboratory
Date of Publication: 1965-01
Pages: 690
Contract: AF 33(616)-7483
DoD Project: 7381
DoD Task: 738101
Identifier: AD0611772

Pertinent factors affecting the function of thermal protection systems are reviewed with emphasis on glide re-entry applications. Review is made and new information is generated in the areas of: (1) system, material, and design performance criteria needed for evaluation, (2) methods and techniques necessary for experimental and theoretical acquisition of the necessary parameters, (3) correlation of data to present information for the material selection and development effort, and protection system design use, (4) design and development techniques for built-up shield - structure components (vehicle sizing), and (5) basic mechanisms of heat and mass transfer associated with the mode of heat absorption or dissipation and of load carrying and transmission capacity.Selection of significant parameters for materials and overall thermal protection systems is made. Parametric studies are conducted to provide information for the designer and materials developer for several systems of interest, while correlation methods and techniques are developed. Effort is devoted to the examination of Q* concept for radiation ablation systems. Experimental techniques and facilities are improved and modified and experiments are conducted to permit meaningful determination of performance criteria needed for materials ranking, and to extend the knowledge of material behavior. A rapid, inexpensive and accurate thermal design method is developed for sizing and parametric studies. Environmental factors and structural effects in the aero-thermo-structural interface are studied. Design and development techniques are established or clarified for initial sizing of the vehicle and methods provided for final design. The dependence of the thermal protection system design on aerodynamic environment for a flight corridor and a range of load carrying substructures is shown, while desirable material characteristics to strive for in material development effort may be deduced from the parametric studies.Systematic means for material and system selection are provided for radiative system, radiative systems with subsidiary mass transfer (ablation), and for combinations of above systems with forced backface cooling. Forced transpiration system (mass injection) and plastic impregnated matrix are investigated.

Provenance: Lockheed Martin Missiles & Fire Control

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