Abstract
The paper is devoted to the design and testing of radiative heat flux sensors (RHFSs) for various applications in spacecraft. The paper presents the results of experimental and computational studies using a prototype of attitude determination system, which implements the proposed methods for determination of absorbed radiation heat fluxes for orbital spacecraft. An analysis of different RHFS designs is carried out. The physical model of the process in the experimental system is presented. The requirements for RHFS prototypes, as well as the conditions and parameters of the tests, are formulated. The purpose of the tests is to study the thermal conditions of the RHFS prototypes and to select a sensor that meets the requirements to a certain RHFS. The tests evaluated the dependences of the heat fluxes absorbed by the sensors on the angle of irradiation and the effect of the angular velocity on the determination of radiation. The results of preliminary approbation of the developed approach are presented.
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Nenarokomov, A.V., Budnik, S.A., Nadiradze, A.B. et al. Heat Flux Sensors of Absorbed Radiation for Orbital Spacecraft. Design and Testing. J. Engin. Thermophys. 30, 615–635 (2021). https://doi.org/10.1134/S1810232821040056
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DOI: https://doi.org/10.1134/S1810232821040056