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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 Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781725628502 Category : Languages : en Pages : 32
Book Description
A reduction method which combines classical Rayleigh-Ritz modal superposition techniques with contemporary finite-element methods is applied to transient nonlinear thermal analysis of aerospace structures. The essence of the method is the use of a few thermal modes from eigenvalue analyses as basis vectors to represent the temperature response in the structure. The method is used to obtain approximate temperature histories for a portion of the Shuttle orbiter wing subject to reentry heating and for a large space antenna reflector subject to heating associated with a low Earth orbit. The reduction method has excellent potential for significant size reduction for radiation-dominated problems such as the antenna reflector. However, for conduction-dominated problems such as the Shuttle wing, especially those with complex spatial and temporal variations in the applied heating, additional work appears necessary to find alternate sources of basis vectors which will permit significant problem size reductions. Shore, C. P. Langley Research Center NASA-TP-2373, L-15777, NAS 1.60:2373 RTOP 506-53-53...
Author: Earl Arthur Thornton Publisher: AIAA (American Institute of Aeronautics & Astronautics) ISBN: Category : Science Languages : en Pages : 576
Book Description
This text presents recent research and development in aerothermodynamics, advanced light metals and composites, thermal structures, materials performance and failure criteria, and intelligent processing of materials, as they relate to high-speed flight. Researchers and designers of aerospace vehicles for high-speed flight, as well as materials scientists, should find this text valuable.
Author: National Aeronaut Administration (Nasa)
Author: National Aeronaut Administration (Nasa)
Author: Max L. Blosser
Author: Max L. Blosser
Author: Thomas N. Bernstein
Author: William L. Ko
Author: National Aeronautics and Space Administration (NASA)
Author: Earl Arthur Thornton
Author: Howard M. Adelman
Author: William L. Ko
Author: Earl A. Thornton