Parameter Estimation of a Space Radiator using Differential Evolution Algorithm

In this article, different combinations of geometrical dimensions of a rectangular space radiator have been estimated using an inverse method. The solution procedure is based on the real-coded differential evolution (DE) optimization algorithm. Electronic equipments and aircraft power plants such as gas turbines need to be consistently cooled for safe operation and due to absence of air medium in space, the heat transfer occurs mainly by surface radiation. The required rate of heat to be dissipated is directly dependent upon the prevailing temperature distribution. Therefore, in this work, the estimation of parameters has been done for satisfying a predefined and simulated surface temperature profile on a space radiator. The temperature distribution used in the present inverse simulation study has been calculated and updated using the fourth order Runge-Kutta method and DE algorithm, respectively. Results have been validated against the existing literature. The present work reveals many possible combinations of the space radiator to attain a given temperature distribution. This offers the opportunity and flexibility to select a space radiator to achieve the required heat transfer rate for cooling various electronic equipments and power generating units typically for space applications.