内埋武器投放分离相容性的风洞投放试验预测与评估

采用基于运动动力学相似的风洞投放试验对先进战斗机内埋武器投放分离相容性进行预测与评估，给出载机在不同飞行马赫数、攻角、弹舱长深比及舱内武器剩余数量、不同弹射力、折叠翼是否展开下，内埋导弹从载机弹舱投放分离后的运动轨迹和俯仰姿态角变化规律，研究这些因素对内埋导弹投放分离相容性的影响。结果表明：处于超声速飞行状态下（马赫数为1.5）的载机，攻角处于0°、2°、3°时投放内埋导弹后弹体俯仰角处于低头状态，利于攻击载机前下方敌方目标；在给定的初始分离条件下，对于两种不同的弹舱长深比，内埋导弹均能安全分离，但对内埋导弹俯仰方向运动影响较为显著；弹舱内武器剩余数量对内埋导弹分离特性影响较小，导弹能快速地远离载机干扰流场，投放分离后弹体俯仰角一直处于低头状态；随着内埋导弹初始分离速度增大，可使弹体快速地穿过载机的下洗流场，有利于内埋导弹与载机的安全分离；导弹的不同气动布局对内埋导弹分离相容性有一定的影响。

Prediction and assessment of drop separation compatibility of internal weapons by wind tunnel drop-test

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.