Aerodynamic mechanism and aeroacoustic analysis of rocket sled with winged payload

The rocket sled system is not only a high-speed dynamic ground test system, but also one of the future aerospace horizontal launch schemes. The winged load, as a common type of payload, has greater vibration and noise intensity than the wingless load. Due to the severe aerodynamic instability prior to separation, the head-up or head-down phenomena are more evident and the test accuracy significantly decreases. The high-precision computer fluid dynamics and aeroacoustic analysis are employed to explore the multifield coupling mechanism of a rocket sled with the winged payload in the wide speed range ( Ma = 0.5–2). The results show that as the incoming velocity increases, the cone angle of the shock wave of the rocket sled decreases, the shock pressure increases quickly, and the vortex between the slippers splits and gradually shrinks in size. The velocity of the rocket sled exerts little influence on the modal resonance frequency. The wing has a significant impact on aerodynamic noise, and as the sound pressure level rises, the propagation direction gradually shifts towards the rear and upper regions of the wing.