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Heat flux transducers for control of heat load on the aerodynamic paylod fairing of a lounch-vehicle

Work number - M 20 AWARDED

Authors: Dekusha O.L., Kovtun S.I.

This work presented by Institute of Engineering Thermophysics, National Academy of Sciences of Ukraine.

The work describes task of determining the thermal load on the main part of the space launch vehicle for the control of its flight safety by measuring the heat flow on the outer and inner surfaces using heat flux transducers.

The authors performed a set of analytical and experimental studies of  properties thermoelectric materials and electrical potting compounds and their temperature dependencies which allowed to predict metrological parameters of the heat flux transducers.Created specifications for the heat flux transducers which can be used in a wide temperature range with stable characteristics over time.

By using the method of mathematical modeling investigated the distribution of temperature and heat flux in transducers for different boundary conditions simulating thermal processes, including dynamic. Obtained relationship between relative density of heat flow from the Fourier criterion. It is proved that the design of transducer with additional corrective battery of thermocouples allow decrease respond time to rapid input heat load.

As part of the research was created a unique stand for the experimental studies, calibration and configuration of heat flow transducers.

One of important tasks of the work was creating recommendations for metrological certification and periodic calibration of heat flow transducers in a temperature range 300 ÷ 500 K.

The results of the work are two versions of the heat flux transducers that were used in the measurement system of rockets "Dnepr" during 18 starts which allowed for the first time in aeronautics research to get a unique measuring about the reliability of spacecraft thermal protection during the start.

The economic effect of the implementation of the work is the possibility to optimize the choice of the main thermal insulation of  space rocket, opening the way to increase the mass of the payload.

The results obtainedin the presented research work supported by 13 implementation acts that obtained from leading aerospace companies.

Main results reflected in 24 scientific publications and discussed at the 11International Conferences.