Phase transition cooling structure towards the wing antenna of hypersonic vehicle

In order to optimize the heat dissipation efficiency of the wing antenna of a hypersonic vehicle, a comprehensive performance-based investigation of active cooling of the wing antenna unit is proposed, taking into account multiple factors. The volume of fluid (VOF) model is employed to simulate and examine the behavior of bubbles and thermal performance on the model surface with respect to the pipe inlet, pipe outlet, and pipe spacing. Furthermore, the heat dissipation efficiency of the wing antenna structure is validated using a quartz lamp as the heat source. The comprehensive performance factor is able to balance the relationship between pressure drop and heat transfer. The simulated heat dissipation efficiency shows a high level of agreement with experimental testing. These results indicate that an appropriate coolant flow rate and flux can effectively provide the degree of phase change, and vapor can only provide effective heat dissipation within a suitable range. Conversely, in situations with excessive or insufficient bubbles, heat cannot be effectively dissipated, thereby reducing the heat dissipation efficiency.