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Journal ArticleDOI

Finite element analysis of conductive and radiative heating of a thin skin calorimeter

TL;DR: In this article, the influence of normal and lateral conduction on the temperature distribution and heat transfer coefficient on the surface of a typical sounding rocket was investigated, and the main purpose of the present paper is to investigate the influence that normal conduction has on the performance of a sounding rocket.
Abstract: The main purpose of the present work is to investigate the influence of normal and lateral conduction on the temperature distribution and heat transfer coefficient on the surface of a typical sounding rocket.
Citations
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Journal ArticleDOI
TL;DR: In this article, the authors present a method for a simple and accurate determination of the time-varying heat transfer coefficient (or heat flux) given an accurate temperature history of the body at a selected point beneath the surface.

109 citations

Journal ArticleDOI
TL;DR: In this paper, the tangential matrix of the Newton method is formulated and a method to solve the heat transfer with the non-linear boundary conditions, based on the secant slope of a reference function, is developed.
Abstract: The aim of the paper is to determine the approximation of the tangential matrix for solving the non-linear heat transfer problem. Numerical model of the strongly non-linear heat transfer problem based on the theory of the finite element method is presented. The tangential matrix of the Newton method is formulated. A method to solve the heat transfer with the non-linear boundary conditions, based on the secant slope of a reference function, is developed. The contraction mapping principle is introduced to verify the convergence of this method. The application of the method is shown by two examples. Numerical results of these examples are comparable to the ones solved with the Newton method and the commercial software COMSOL for the heat transfer problem under the radiative boundary conditions.

2 citations


Cites methods from "Finite element analysis of conducti..."

  • ...A onedimensional heat conduction [5, 18] and a two-dimensional one [ 17 ] under radiation boundary conditions is solved with these methods....

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Journal ArticleDOI
TL;DR: In this article, the authors developed a one-dimensional heat conduction model to infer the surface heating rates from the temperature data, which was obtained from a nickel thin film sensor mounted on a quartz substrate during a supersonic flight test.
Abstract: The approach for the present work is to develop a one-dimensional heat conduction model to infer the surface heating rates from the temperature data. The temperature history is obtained from a nickel thin film sensor mounted on a quartz substrate during a supersonic flight test. Polynomial curve fitting with regression analysis and cubic spline methods are used to fit the temperature data. One-dimensional numerical schemes are developed to infer surface heating rates by using Duhamel's superposition integral. Since the temperature data are acquired for 10 s, the one-dimensional behavior of heat penetration might not be applicable for entire time scale. In order to include the lateral conduction of heat along the depth of substrate, finite-element analysis of a more realistic gauge-substrate system is carried out with commercial package ANSYS 11. With the inputs of surface heating rates predicted from Duhamel's superposition integral, the temperature history are then recovered at various depths of the subs...

1 citations


Cites background from "Finite element analysis of conducti..."

  • ...Mehta et al. (1988) investigated the influence of normal and lateral conduction on the temperature distribution and heat transfer co-efficient on the surface of a typical sounding rocket with finite-element technique....

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Book ChapterDOI
10 Jan 2020
TL;DR: In this paper, the effects of input parameters such as time delay, thermocouple cavity, error in the location of thermocalouple position and time and temperature-dependent thermophysical properties are investigated.
Abstract: A one-dimensional transient heat conduction equation is solved using analytical and numerical methods. An iterative technique is employed which estimates unknown boundary conditions from the measured temperature time history. The focus of the present chapter is to investigate effects of input parameters such as time delay, thermocouple cavity, error in the location of thermocouple position and time- and temperature-dependent thermophysical properties. Inverse heat conduction problem IHCP is solved with and without material conduction. A two-time level implicit finite difference numerical method is used to solve nonlinear heat conduction problem. Effects of uniform, nonuniform and deforming computational grids on the estimated convective heat transfer are investigated in a nozzle of solid rocket motor. A unified heat transfer analysis is presented to obtain wall heat flux and convective heat transfer coefficient in a rocket nozzle. A two-node exact solution technique is applied to estimate aerodynamic heating in a free flight of a sounding rocket. The stability of the solution of the inverse heat conduction problem is sensitive to the spatial and temporal discretization.
Journal ArticleDOI
TL;DR: In this article , a thin-film heat flux sensor with antireflective coating based on transparent conductive oxide thermopile was designed and tested by a calibration platform and the experimental results shown that the absorptivity of the membrane structure (for1070nm) improved compared with that before optimization.
Abstract: Purpose The measurement of heat flux is of importance to the development of aerospace engine as basic physical quantities in extreme environment. Heat radiation is one of the basic forms of heat transfer phenomenon. The structure optimizing can improve the performance and infrared absorptivity of the thin film sensor. Design/methodology/approach This paper designed one kind of thin film heat flux sensor (HFS) with antireflective coating based on transparent conductive oxide thermopile. The introduced membrane structure is so thin that it has little impact on sensor performance. Fabrication of thin film sensors were fabricated by physical vapor deposition (PVD) process. Findings The steady-state and dynamic response characteristics of the HFS were investigated by calibration platform. The experimental results shown that the absorptivity of the membrane structure (for1070nm) improved compared with that before optimization. The sensitivity of heat flux gauge was 48.56 µV/ (kW/m2) and its frequency response was determined to be about 1980 Hz. Originality/value The thin film HFS uses thermopile based on Indium Tin Oxid and In2O3. The antireflective coating is introduced to hot endpoint of HFS to improve sensitivity on laser thermal source. The infrared optical properties of membrane layer structure were investigated. The steady-state and the transient response characteristics of the heat flux sensor were also investigated.
References
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Book
01 Jan 1971
TL;DR: In this paper, the authors describe how people search numerous times for their favorite books like this the finite element method in engineering science, but end up in malicious downloads, and instead they cope with some infectious bugs inside their computer.
Abstract: Thank you very much for downloading the finite element method in engineering science. Maybe you have knowledge that, people have search numerous times for their favorite books like this the finite element method in engineering science, but end up in malicious downloads. Rather than enjoying a good book with a cup of tea in the afternoon, instead they cope with some infectious bugs inside their computer.

3,688 citations

Journal ArticleDOI
TL;DR: In this article, the authors present a general approach to transient heat conduction problems with non-linear physical properties and boundary conditions using an unconditionally stable central algorithm which does not require iteration.
Abstract: The paper presents a generally applicable approach to transient heat conduction problems with non-linear physical properties and boundary conditions. An unconditionally stable central algorithm is used which does not require iteration. Several examples involving phase change (where latent heat effects are incorporated as heat capacity variations) and non-linear radiation boundary conditions are given which show very good accuracy. Simple triangular elements are used throughout but the formulation is generally valid and not restricted to any single type of element.

506 citations

22 Jan 1958
TL;DR: In this paper, the authors present measurements of aerodynamic heat transfer at a number of stations along a cone-cylinder-flare model with 15 degree total-angle conical nose and a 10 degree half-angle flare skirt.
Abstract: Report presenting measurements of aerodynamic heat transfer at a number of stations along a cone-cylinder-flare model with 15 degree total-angle conical nose and a 10 degree half-angle flare skirt. Results regarding temperature measurements and heating rates, local flow parameters, heat transfer with theoretical recovery factors, experimental recovery factors, prediction of skin temperatures, and transition are provided.

16 citations

01 May 1961
TL;DR: In this paper, measurements of aerodynamic heat transfer have been made at several stations on the 15 deg total-angle conical nose of a rocket-propelled model in free flight at Mach numbers up to 52.
Abstract: Measurements of aerodynamic heat transfer have been made at several stations on the 15 deg total-angle conical nose of a rocket-propelled model in free flight at Mach numbers up to 52 Data are presented for a range of local Mach number just outside the boundary layer from 140 to 465 and a range of local Reynolds number from 38 x 10(exp 6) to 465 x 10(exp 6), based on length from the nose tip to a measurement station Laminar, transitional, and turbulent heat-transfer coefficients were measured The laminar data were in agreement with laminar theory for cones, and the turbulent data agreed well with turbulent theory for cones using Reynolds number based on length from the nose tip At a nearly constant ratio of wall to local static temperature of 12 the Reynolds number of transition increased from 14 x 10(exp 6) to 30 x 10(exp 6) as Mach number increased from 14 to 29 and then decreased to 17 x 10(exp 6) as Mach number increased to 37 At Mach numbers near 35, transition Reynolds numbers appeared to be independent of skin temperature at skin temperatures very cold with respect to adiabatic wall temperature The transition Reynolds number was 177 x 10(exp 6) at a condition of Mach number and ratio of wall to local static temperature near that for which three-dimensional disturbance theory has been evaluated and has predicted laminar boundary-layer stability to very high Reynolds numbers (approximately 10(exp 12))

15 citations