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.

中文翻译：

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轨道航天器吸收辐射的热通量传感器。设计和测试

摘要

本文致力于设计和测试用于航天器各种应用的辐射热通量传感器 (RHFS)。本文介绍了使用姿态确定系统原型的实验和计算研究结果，该系统实现了所提出的确定轨道航天器吸收辐射热通量的方法。对不同的 RHFS 设计进行了分析。给出了实验系统中过程的物理模型。制定了 RHFS 原型的要求，以及测试的条件和参数。测试的目的是研究 RHFS 原型的热条件并选择满足特定 RHFS 要求的传感器。测试评估了传感器吸收的热通量对辐射角度的依赖性以及角速度对辐射测定的影响。介绍了所开发方法的初步认可结果。