内埋武器投放分离相容性的风洞投放试验预测与评估

The compatibility of aircraft-missile separation from an internal weapons bay in advanced fighter aircraft is predicted and evaluated by using the wind tunnel drop-test that is similar to kinematics dynamics. The trajectory and attitude angle variation law of internal missile are obtained under different initial conditions of Mach number, angle of attack, length-to-depth ratio, residual number of missile in the bay, ejection forces and deployment of folding wings. The influence of these factors on the compatibility for drop separation of internal missiles is studied. The results show that the pitching angle of the missile body is in a bow state when the angle of attack is 0°, 2°, or 3° in the supersonic flight state(Mach number 1.5), which is conducive to attack the enemy target in the lower front of the aircraft. Under the given initial separation conditions, the internal missile can be safely separated in two different compartment length-depth ratios, but the pitching direction motion of the internal missile is more prominent. The residual number of weapons in the missile compartment has little influence on the separation characteristics of the internal missile and the missile can quickly stay away from the interference flow field of the carrier aircraft and the pitch angle of the missile body is always in low-head state after separation. With the increase of the initial launching speed of the internal missile, the missile body can rapidly pass through the downwash flow field of the carrier aircraft, which is beneficial to the safe separation of the internal missile and the carrier aircraft. The aerodynamic layout of the missile has influence on the separation compatibility for the internal missile.