Advances in the design and development of communication spacecraft are associated with an increase in power consumption and heat dissipation in the spacecraft. As a consequence, advanced thermal control technologies like mechanical pumped fluid loop (MPFL) are increasingly being considered for spacecraft temperature management. These technologies generally use radiative sinks (often deployable) to reject heat. Since mass is a critical parameter in space applications, mass-optimized radiator design is paramount. This paper presents semi-analytical approach to evolve design of a mass-optimized space radiator panel for single-phase MPFL.

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