Abstract:
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.
