Numerical simulation and experimental study on lateral gasbag separation of submunition missile
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摘要:
为了研究子母弹侧向气囊分离特性，采用低燃温高燃速固体推进剂作为能量源，建立了燃气囊式分离数学模型，利用4阶龙格库塔法进行求解，获得了燃气发生器内弹道、气囊膨胀以及子弹模拟载荷分离运动等分离参数变化规律，并搭建了子母弹侧向气囊分离模拟试验系统进行分离试验验证。计算结果表明：在分离过程中，气囊内压力呈现先增加后缓慢降低，再缓慢上升的变化趋势，子弹模拟载荷的加速度则呈现出先增加后减小，最大加速度峰值为15.1
g ，分离速度逐渐增加后趋于平缓，分离末速度为6.17 m/s；试验验证了子母侧向气囊分离的可行性，并获得子弹模拟载荷分离的加速、速度等参数的变化特性，计算结果与试验结果趋势基本一致，参数误差均在5.5%以内，表明该分离模型能够较好描述子母弹侧向气囊分离过程，可为子母弹短距离低过载分离技术提供一定基础支撑。Abstract:In order to study the lateral gasbag separation characteristics of the submunition missile, the low burning temperature and high burning rate solid propellant was used as energy source, a mathematical model of gasbag separation was established and solved by fourth-order Runge-Kutta method. The variation laws of separation parameters such as gas generator interior ballistics, gasbag expansion and bullet simulated load separation motion were obtained. A simulation experimental system for lateral gasbag separation of submunition missile was set up for separation test verification simultaneously. The calculation results indicate that during the separation process, the pressure in the gasbag presents a variation trend that it increases first, and then decreases slowly, and then increases slowly. The acceleration of the bullet simulated load increases first and then decreases, with the maximum acceleration peak value of 15.1
g . Its separation speed tends to be flat after gradual increase with the final separation speed at 6.17 m/s. Besides, the feasibility of the lateral gasbag separation of the submunition missile is verified by the experiment, and the variation characteristics of the separation parameters such as acceleration and velocity of the bullet simulated load are obtained. The calculation results are basically consistent with the experimental results, and the parameter errors are within 5.5%, showing that this separation model can better describe the lateral gasbag separation process of the submunition missile, and can provide some basic support for the short-range low-overload separation technology of the submunition missile. -
图 2 分离过程中气囊横截面积变化示意图
Figure 2. Variation of cross-sectional area of gasbag during separation
图 3 燃气发生器燃烧室内压力、质量流量时程曲线
Figure 3. Time history curves of combustion chamber pressure and mass flow rate of gas generator
图 4 分离过程中气囊的压力及其与子弹模拟载荷有效作用面积变化情况
Figure 4. The variation of the pressure of the gasbag and its effective area with bullet simulated load during the separation process
图 5 子弹模拟载荷分离过程中的加速度、速度以及位移随时间变化曲线
Figure 5. Curves of acceleration, velocity and displacement versus time during the separation process of bullet simulated load
图 6 Test#1不同时刻子弹模拟载荷在气囊作用下的分离过程
Figure 6. Separation process of bullet simulated load at different time under the action of gasbag in Test#1
图 7 分离过程燃烧室压力理论与试验时程曲线
Figure 7. The time history curves of theoretical and experimental pressure in combustion chamber during separation process
图 8 子弹模拟载荷分离过程中加速度理论与试验时程曲线
Figure 8. The time history curves of theoretical and experimental acceleration in the separation process of bullet simulated load
图 9 子弹模拟载荷分离过程中速度理论与试验时程曲线
Figure 9. The time history curves of theoretical and experimental velocity in the separation process of bullet simulated load
表 1 子弹模拟载荷及气囊参数
Table 1. Bullet simulated load and airbag parameters
参数 数值 模拟载荷质量/kg 320 载荷圆弧半径/m 0.63 气囊直径/m 0.50 气囊长度/m 0.60 
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表 2 燃气发生器及装药参数
Table 2. Gas generator and charge parameters
参数 数值及说明 密度/（g/cm3） 1.54 燃气温度/K 1375 燃气比热比 1.31 压力指数n 0.395 燃速系数a 1.72×10−5 药型 管状内孔燃烧 根数 1 药柱内径/mm 29 药柱外径/mm 44 药柱长度/mm 42 喷管喉径/mm 7.0 热损失系数 0.9
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