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.
A two-dimensional heat conduction equation with a time dependent aerodynamic heating condition at one surface and a radiation boundary condition at the other end is solved using finite element method.
Zusammenfassung
Das Ziel der vorliegenden Arbeit ist die Erforschung des Einflusses der normalen und seitlichen Wärmeleitung auf die Temperaturverteilung und den Wärmeübergangskoeffizienten auf der Oberfläche einer typischen Überschallrakete. Dazu wird mit der Methode der Finiten Elemente eine zweidimensionale Wärmeleitungsgleichung mit einer zeitabhängigen Zufuhr von Reibungswärme durch die Luftströmung an einer Wand und Stahlungswärmeaustausch an der anderen Seite als Randbedingung gelöst.
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Abbreviations
- ¯C:
-
capacitance matrix
- ¯F:
-
heat flux vector
- h :
-
heat-transfer coefficient
- ¯K:
-
Thermal conductivity matrix
- k :
-
thermal conductivity
- l :
-
wall thickness
- q:
-
heat flux
- T :
-
temperature
- t :
-
time
- Δt :
-
time increment
- X, Y :
-
Cartesian coordinates
- σ :
-
Stefan Boltzmann constant
- ɛ :
-
emissivity
- α :
-
thermal diffusivity
- a :
-
aeordynamic heating rate
- ar :
-
temperature at which no radiation occurs
- aw :
-
adiabatic wall temperature
- FE :
-
finite element
- in :
-
initial temperature
- r :
-
radiation heat-transfer
- s:
-
skin
References
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Mehta, R.C., Jayachandran, T. & Sastri, V.M.K. Finite element analysis of conductive and radiative heating of a thin skin calorimeter. Wärme- und Stoffübertragung 22, 227–230 (1988). https://doi.org/10.1007/BF01377245
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DOI: https://doi.org/10.1007/BF01377245