Experimental investigations on the separation interference characteristics of supersonic internal weapon releasing from the aircraft

The internal weapon is subject to the complex interference flow field of the aircraft during the separation of supersonic bombs, and its aerodynamic characteristics are significantly different from the freestream conditions, which will have a certain impact on the safety of the bomb separation. Using the new CTS test technology based on the configuration of the parallel mechanism and the schlieren techniques, the interference characteristics of a new aircraft with a typical bomber layout and a typical air-to-air missile model were studied. Under the influence factors such as the separation altitudes and folded/unfolded rudder, the pitching motion characteristics of the missile and the interference of the flow field structures for the aircraft are compared. Results show that at supersonic speed, there exists a complex shock system structure for typical embedded bomber fighter configuration, which will have a strong aerodynamic interference effect on the carrier bomb, inducing the carrier to nose up. With no initial separating angular velocity, unsafe separation is tend to occur. When reducing separation altitude, unsafe separation tendency for the bomb would advance. During the separation process, the rudder surface is not conducive to the attitude control of the loaded bomb. Meanwhile, folded rudder is unfavorable for the attitude control of the bomb during the separation procedure, thus folding the rudder as soon as possible is demanded at the premise of safe separation, in order to guarantee stability control of the bomb attitude.