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Author: National Aeronaut Administration (Nasa) Publisher: ISBN: Category : Languages : en Pages : 56
Book Description
An analytical solution was derived for the transient response of an insulated structure subjected to a simplified heat pulse. The solution is solely a function of two nondimensional parameters. Simpler functions of these two parameters were developed to approximate the maximum structural temperature over a wide range of parameter values. Techniques were developed to choose constant, effective thermal properties to represent the relevant temperature and pressure-dependent properties for the insulator and structure. A technique was also developed to map a time-varying surface temperature history to an equivalent square heat pulse. Equations were also developed for the minimum mass required to maintain the inner, unheated surface below a specified temperature. In the course of the derivation, two figures of merit were identified. Required insulation masses calculated using the approximate equation were shown to typically agree with finite element results within 10%-20% over the relevant range of parameters studied. Blosser, Max L. Langley Research Center NASA/TP-2012-217595, L-20165, NF1676L-15092 AEROSPACE VEHICLES; INSULATION; TRANSIENT HEATING; AIRCRAFT STRUCTURES; TRANSIENT RESPONSE; MATHEMATICAL MODELS; HYPERSONIC VEHICLES; SIZE (DIMENSIONS); FINITE ELEMENT METHOD; TEMPERATURE DEPENDENCE; THERMAL PROTECTION; SURFACE TEMPERATURE
Author: National Aeronaut Administration (Nasa) Publisher: ISBN: Category : Languages : en Pages : 56
Book Description
An analytical solution was derived for the transient response of an insulated structure subjected to a simplified heat pulse. The solution is solely a function of two nondimensional parameters. Simpler functions of these two parameters were developed to approximate the maximum structural temperature over a wide range of parameter values. Techniques were developed to choose constant, effective thermal properties to represent the relevant temperature and pressure-dependent properties for the insulator and structure. A technique was also developed to map a time-varying surface temperature history to an equivalent square heat pulse. Equations were also developed for the minimum mass required to maintain the inner, unheated surface below a specified temperature. In the course of the derivation, two figures of merit were identified. Required insulation masses calculated using the approximate equation were shown to typically agree with finite element results within 10%-20% over the relevant range of parameters studied. Blosser, Max L. Langley Research Center NASA/TP-2012-217595, L-20165, NF1676L-15092 AEROSPACE VEHICLES; INSULATION; TRANSIENT HEATING; AIRCRAFT STRUCTURES; TRANSIENT RESPONSE; MATHEMATICAL MODELS; HYPERSONIC VEHICLES; SIZE (DIMENSIONS); FINITE ELEMENT METHOD; TEMPERATURE DEPENDENCE; THERMAL PROTECTION; SURFACE TEMPERATURE
Author: Max L. Blosser Publisher: BiblioGov ISBN: 9781289152826 Category : Languages : en Pages : 58
Book Description
An analytical solution was derived for the transient response of an insulated structure subjected to a simplified heat pulse. The solution is solely a function of two nondimensional parameters. Simpler functions of these two parameters were developed to approximate the maximum structural temperature over a wide range of parameter values. Techniques were developed to choose constant, effective thermal properties to represent the relevant temperature and pressure-dependent properties for the insulator and structure. A technique was also developed to map a time-varying surface temperature history to an equivalent square heat pulse. Equations were also developed for the minimum mass required to maintain the inner, unheated surface below a specified temperature. In the course of the derivation, two figures of merit were identified. Required insulation masses calculated using the approximate equation were shown to typically agree with finite element results within 10%-20% over the relevant range of parameters studied.
Author: Thomas N. Bernstein Publisher: ISBN: Category : Aerodynamic heating Languages : en Pages : 68
Book Description
The thermal analysis is presented of a portion of the external surface thermal protection system and load bearing structure of a hypersonic vehicle, whose mission consists of a climb-out to 100,000 feet, cruise at Mach 6, descent, and a final phase, termed turn around, which includes landing rollout, refueling and maintenance. Temperature-dependent thermo-physical properties are utilized and compared to results obtained for constant thermo-physical properties.
Author: National Aeronaut Administration (Nasa)
Author: National Aeronaut Administration (Nasa)
Author: Max L. Blosser
Author: Max L. Blosser
Author: Thomas N. Bernstein
Author: Howard M. Adelman
Author: Earl Arthur Thornton
Author: Earl A. Thornton
Author: 
Author: 
Author: Howard M. Adelman