侧向喷流对导弹方向舵局部气动热特性的影响

To explore the effect law and related mechanism of the lateral jet flow control technology on the local aerodynamic heating characteristics of the hypersonic missile rudder, numerical simulations of a missile with are carried out under different incoming flow and jet conditions. When the jet pressure ratio reaches 75, the surface heating flux in the middle and later section of the rudder leading edge can be greatly reduced, as it can avoid the freestream interfered by the bow shock acting on the rudder. With the increase of the distance between the nozzle position and the leading edge of the rudder, the change of the structure and scope of the recirculation zone after the jet is not obvious, and the change of the wall heat flow at the leading edge of the rudder is not significant. Under different angles of attack, lateral jets can effectively reduce the wall heat flow at the leading edge of the rudder. At an angle of attack above 10°, the thermal protection effect of the jet is reduced. Under a certain angle of attack, the jet in front of the rudder shaft causes the freestream to flow around the jet. The gas density within the boundary layer of the lower wall of the rudder shaft increases, which causes a large pressure difference on both sides of the rudder shaft, and leads to an increase of the surface heating flux of the rudder shaft. Under 0° angle-of-attack incoming flow condition, the lateral force of the rudders on both sides of the nozzle is in the same direction as the jet thrust. This causes increasing of the amplification factor of the missile.