Abstract
An Inverse Heat Transfer Problem is solved for a sounding rocket module given its geometry and measured temperature profile. The solution is obtained via moving window optimization, a technique for solving inverse dynamics. An analysis is performed to modify the method to avoid oscillatory behavior of the resulting heat flux profile. The method parameters are tuned in relation to characteristic phases of the flight. Results are presented and correlated with measured flight data. Conclusions are drawn for better experiments for measuring heat flux on a sounding rocket skin.
Highlights
We propose to apply this technique to solve the inverse heat transfer problem (IHTP)
The heat inverse problem solution presented in this paper resulted in estimation of heat flux at the surface of a sounding rocket
Methods presented here can be used in future engineering calculations
Summary
This poses a classical inverse problem where effect (here, temperature distribution in space and time) is given, and cause (heat flux distribution) is determined. Perakis and Haidn [15] point to response delays as a difficulty in using thermocouple measurements for determining heat flux. The presented work provides results of inverse heat transfer analysis of a REXUS rocket. This was a sounding rocket with student experiments dedicated to various environmental. The setup rig was not designed to determine heat flux distribution, the data was used to analyze if such calculations are possible
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