A reliable control of current orientation of a spacecraft is a very important task in aerospace engineering. This makes important to elaborate a backup or replacement system which can be used for the verification or correction of the orientation. It seems natural to use various conditions of radiative heating of the design elements of different orientations with respect of the Sun and strongly radiating or reflecting planets of the Solar system. In the case of an ordinary slow variation of the vehicle orientation in space, the temperature measurements can be used to distinguish different integral (over the spectrum) radiative flux to various surfaces of a specially designed thermal sensor with several facets. An analysis of a possibility of such an engineering solution is a subject of the present study. The mathematical problem to be solved is one of the so-called inverse heat transfer problems, and its solution is not a simple task. Therefore, the main efforts of the authors are focused on solution of this ill-posed problem. The known methods of the inverse problem regularization are modified to take into account special features of the heat transfer problem under consideration. The resulting algorithm is verified using the typical case problems. It was shown that one can obtain sufficiently accurate results on the bases of a limiting set of relatively simple temperature measurements. The latter enables us to consider the method suggested as a promising way to elaborate a series simple backup/replacement system of an approximate retrieval of a spacecraft current orientation. This statement is confirmed by calculation for one of the typical trajectory of a vehicle in the Solar system.

航天器当前方位的可靠控制是航空航天工程中非常重要的任务。这对于拟定可用于方向验证或校正的备用或替换系统非常重要。相对于太阳和强烈辐射或反射太阳系行星的方向不同的设计元素，采用辐射加热的各种条件似乎很自然。在车辆空间方向通常缓慢变化的情况下，温度测量值可用于区分不同积分（在整个光谱范围内）到具有多个小平面的特殊设计热传感器各个表面的辐射通量。对这种工程解决方案的可能性的分析是本研究的主题。要解决的数学问题是所谓的逆传热问题之一，并且其解决不是简单的任务。因此，作者的主要精力集中在解决这个不适的问题上。修改反问题正则化的已知方法，以考虑到所考虑的传热问题的特殊特征。使用典型案例问题验证了所得算法。结果表明，在有限的一组相对简单的温度测量的基础上，可以获得足够准确的结果。后者使我们能够将所建议的方法视为拟定一系列简单的备用/置换系统的有前途的方法，该系统是对航天器当前方向的近似检索。