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Inverse heat transfer problem solution of sounding rocket using moving window optimization.

Adam Dąbrowski¹, Leszek Dąbrowski²

¹Department of Mechanics and Mechatronics, Faculty of Mechanical Engineering, Gdansk University of Technology, Gdańsk, Poland.

|June 25, 2019

Summary

This summary is machine-generated.

This study solves an inverse heat transfer problem for sounding rockets using moving window optimization. The method was refined to accurately measure heat flux on rocket skin during flight.

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Area of Science:

Aerospace Engineering
Thermodynamics
Heat Transfer

Background:

Accurate heat flux measurement is crucial for sounding rocket thermal protection system design.
Existing methods for inverse heat transfer problems can exhibit oscillatory behavior.

Purpose of the Study:

To solve an inverse heat transfer problem for a sounding rocket module.
To modify and optimize the moving window method for improved heat flux profile accuracy.
To correlate results with flight data for validation.

Main Methods:

Utilized moving window optimization for solving the inverse heat transfer problem.
Analyzed and modified the method to mitigate oscillatory behavior in heat flux.
Tuned method parameters based on characteristic flight phases.

Main Results:

Successfully obtained a stable heat flux profile for the sounding rocket module.
Demonstrated correlation between model predictions and measured flight temperature data.
Identified key parameters for successful application of the method.

Conclusions:

The modified moving window optimization effectively solves inverse heat transfer problems for sounding rockets.
Parameter tuning is essential for accurate heat flux estimation during different flight phases.
Recommendations for improved experimental design for future heat flux measurements on rocket skins.