适应火工装置冲击环境的铝蜂窝缓冲特性研究

Aluminum honeycomb buffering characteristics adapted to impact environment of pyrotechnic device

针对火工装置发射过程中对卫星平台产生的冲击,设计了一种基于铝蜂窝的新型空间发射缓冲结构,通过火药密爆试验和铝蜂窝准静态压溃试验分别建立了空间火工发射装置内弹道模型和铝蜂窝压溃模型,在此基础上建立了发射后坐动力学模型,并重点研究了火药药量和铝蜂窝内径对发射后坐特性的影响。研究结果表明:当火药药量增大0.3 g,后坐力平均值增大了1.95%,牵引体发射速度增大了5.10%,后坐位移增大了7.64%,后坐力持续时间减小10.3%。当铝蜂窝内径从148 mm分别减小1 mm和2 mm时,后坐力平均值增大了4.06%和9.08%,牵引体发射速度增大了0.22%和0.54%,后坐位移增大了3.38%和15.24%。同时以上参数的合理选择可以有效降低发射后坐力并保证牵引体的发射性能。

Here,aiming at impact on satellite platform in launch process of pyrotechnic device,a new launch buffer structure based on aluminum honeycomb was designed.Then,the internal ballistic model of pyrotechnic device and aluminum honeycomb crushing model were established using closed blast tests of gunpowder and quasi-static tests of aluminum honeycomb.Afterwards,the launch recoil dynamic model was built.Effects of gunpowder dosage and inner diameter of aluminum honeycomb on launch recoil characteristics were studied.The study results showed that when gunpowder dosage increases by 0.3 g,average recoil force increases by 1.95%,launch speed of traction body increases by 5.10%,recoil displacement increases by 7.64%,and duration of recoil decreases by 10.3%;when inner diameter of aluminum honeycomb decreases by 1 mm and 2 mm,respectively from 148 mm,average recoil force increases by 4.06%and 9.08%,launch speed of traction body increases by 0.22%and 0.54%,recoil displacement increases by 3.38%and 15.24%;the reasonable selection of above parameters can effectively reduce recoil force after launch and ensure launch performance of traction body.