Two computer programs for calculating profiles in a ten-element structure consisting of up to ten materials are presented, along with a third program for calculating the mean temperature for a payload container placed in an orbiting vehicle cargo bay. The three programs are related by the sharing of a common analytical technique; the energy balance is based upon one-dimensional heat transfer. The first program, NQLDW112, assumes a non-ablating surface. NQLDW117 is very similar but allows the outermost element to ablate. NQLDW040 calculates an average temperature profile through an idealized model of the real payload cannister and contents in the cargo bay of an orbiting vehicle
Design and fabrication of sterilization container and model probe assembly for Mars landing capsul
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A preliminary design of a two-stage to orbit vehicle was conducted with the requirements to carry a ...
The results of a thermal-structural test program to verify the performance of a metallic/radiative T...
Among several cellular ceramic structures manufactured by various suppliers for regenerator applicat...
Structural design of spacecraft subjected to thermal sterilization prior to planetary landin
Design concepts are developed and evaluated for a cooled structures assembly for the Scramjet engine...
Fabrication of three flat plate sections for silicon-germanium solar thermoelectric generato
The development and evaluation of a design concept for the cooled structures assembly for the Scramj...
The Energy Systems Optimization Program, which is used to provide analyses of Modular Integrated Uti...
A flight experiment designed to demonstrate current cryogenic heat pipe technology was defined and e...
A design and analysis study was conducted to provide advanced engine descriptions and parametric dat...
The purpose of this calculation is to evaluate the thermal performance of the Naval Long and Naval S...
The program has a finite element library of six elements: two conduction/convection elements to mode...
A user's manual for two computer programs was developed to predict the induced effects of jets exhau...
Design and fabrication of sterilization container and model probe assembly for Mars landing capsul
The feasibility and conceptual design aspects of repair materials and procedures for in orbit repair...
A preliminary design of a two-stage to orbit vehicle was conducted with the requirements to carry a ...
The results of a thermal-structural test program to verify the performance of a metallic/radiative T...
Among several cellular ceramic structures manufactured by various suppliers for regenerator applicat...
Structural design of spacecraft subjected to thermal sterilization prior to planetary landin
Design concepts are developed and evaluated for a cooled structures assembly for the Scramjet engine...
Fabrication of three flat plate sections for silicon-germanium solar thermoelectric generato
The development and evaluation of a design concept for the cooled structures assembly for the Scramj...
The Energy Systems Optimization Program, which is used to provide analyses of Modular Integrated Uti...
A flight experiment designed to demonstrate current cryogenic heat pipe technology was defined and e...
A design and analysis study was conducted to provide advanced engine descriptions and parametric dat...
The purpose of this calculation is to evaluate the thermal performance of the Naval Long and Naval S...
The program has a finite element library of six elements: two conduction/convection elements to mode...
A user's manual for two computer programs was developed to predict the induced effects of jets exhau...
Design and fabrication of sterilization container and model probe assembly for Mars landing capsul
The feasibility and conceptual design aspects of repair materials and procedures for in orbit repair...
A preliminary design of a two-stage to orbit vehicle was conducted with the requirements to carry a ...