Experimental investigations on the separation interference characteristics of supersonic internal weapon releasing from the aircraft
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摘要: 在超声速条件下的机弹分离过程中，内埋武器受到载机复杂干扰流场作用，其气动特性与自由流情况有很大差异，对机弹分离安全有一定影响。采用基于并联机构构型的CTS（Captive Trajectory Simulation）试验技术以及纹影显示技术，研究了内埋弹舱布局新型战斗机与典型空空导弹模型的机弹干扰特性，在有/无载机干扰、不同分离角速度和分离高度、载弹尾舵折叠/展开等条件下，对比分析了载弹俯仰力矩/运动特性以及载机干扰流场结构。研究结果表明：在超声速条件下，典型内埋弹舱布局战斗机存在复杂的激波系结构，会对载弹产生较强的气动干扰效应，诱导载弹出现"抬头"俯仰运动趋势；无初始分离角速度时，出现不安全分离的趋势；分离高度降低，会使载弹不安全分离趋势提前；在分离过程中，尾舵折叠不利于载弹姿态控制，在保证分离安全的前提下，应尽早展开尾舵，进行姿态增稳控制。Abstract: 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.
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Key words:
- aircraft-missile interference /
- separation drop /
- CTS test /
- complex flow /
- internal weapons
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图 7 载弹俯仰力矩系数随下落位移的变化曲线
Figure 7. Variation of the pitching moment characteristics along with the falling displacement of the missile model
图 8 有/无载机干扰的载弹俯仰力矩/运动特性(ω0=-30°/s, v0=7 m/s)
Figure 8. Comparisons of pitching motion characteristics of the missile with or without the aircraft interference(ω0=-30°/s, v0=7 m/s)
图 9 有/无分离角速度的载弹俯仰力矩/运动特性(v0=7 m/s)
Figure 9. Comparisons of pitching motion characteristics of the missile with/without separation angular velocity(v0=7 m/s)
图 10 不同分离高度下的载弹俯仰运动特性(ω0=0°/s, v0=7 m/s)
Figure 10. Comparisons of pitching motion characteristics of missiles with different separating altitudes(ω0=0°/s, v0=7 m/s)
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