The multi-scale flow coupling effects induced by Shock Wave/Boundary Layer Interaction (SWBLI) in hypersonic flows significantly exacerbate the challenges of thermal load management for flight vehicles. A transverse-opposing dual-jet active control scheme for air rudder is proposed, and its impact characteristics on SWBLI and aerothermal environments under complex inflow conditions is revealed. The numerical methods employed are validated against experimental data from open literature, and a grid independence analysis is conducted. Results indicate that the transverse-opposing dual-jet scheme achieves global heat reduction superior to single-jet configurations through spatially coupled configurations. Under the condition of an 11° rudder deflection, positioning the transverse jet further upstream and the opposing jet at a higher elevation constructs a large-scale separation zone that isolates the hight-emperature mainstream. Consequently, the peak heat fluxes on the leading edge and the plate are controlled below 3 200 kW·m^-2 and 300 kW·m^-2, respectively. At an angle of attack of 11°, all dual-jet configurations significantly reduce the gap heat flux to below 300 kW·m^-2. However, the leading-edge heat flux is sensitive to jet positioning; it is crucial to ensure the opposing jet remains within the low-pressure wake of the transverse jet to prevent severe flow re-attachment and a subsequent surge in heat flux.

Aiming at the thermal control problem of high temperature components in special cabin of advanced aircraft, a new semi-active temperature control principle was proposed. Based on this principle, a new semi-active cooling device was designed and its experimental study was conducted. The heat transfer performance and temperature control mechanism of the new semi-active cooling device under different working conditions were analyzed and compared. The results indicate that the thermal control performance of the new semi-active cooling device is significantly better, especially for the semi-active cooling device filled with 100% infiltrated aerogel, the hot end temperature is 272 ℃ at 3000 s, which is 102 ℃ lower than that under the passive heat transfer condition, and the peak efficiency is up to 68%. With increasing of the outlet pressure of the cooling device, the time for the coolant to reach the boiling point is longer. Filling infiltration aerogel can effectively extend the duration from heat absorption to evaporation of the coolant, and it is also lighter in weight compared to other filling methods.