CAJ | 학술논문

为了研究导弹箱式热发射中导弹发动机建压速率对发射箱易碎盖开盖的影响，通过对动力源进行假设，建立了发动机建压速率与易碎盖开盖能量之间的关系，分析了发动机建压速率对易碎盖开盖的影响；利用数值仿真得到不同速率下的箱内压力曲线，仿真结果表明，建压速率越高前盖开盖风险越大。对比分析了不同导弹飞行试验中发射箱内压力数据，试验验证了仿真结果的正确性。该研究为前、后易碎盖开盖压力指标的优化提供了参考。
위료연구도탄상식열발사중도탄발동궤건압속솔대발사상역쇄개개개적영향，통과대동력원진행가설，건립료발동궤건압속솔여역쇄개개개능량지간적관계，분석료발동궤건압속솔대역쇄개개개적영향；이용수치방진득도불동속솔하적상내압력곡선，방진결과표명，건압속솔월고전개개개풍험월대。대비분석료불동도탄비행시험중발사상내압력수거，시험험증료방진결과적정학성。해연구위전、후역쇄개개개압력지표적우화제공료삼고。
In order to research the influence of rising rate of rocket motor’s pressure on opening gas-opening fragile cover in box-launching process,the assumption about power source was carried out,and the relationship between power source and the rising rate of motor’s pressure was also established.The effect of the rising rate of rocket motor’s pressure on opening fragile cover was analyzed.The box-launching pressure curve was achieved by numerical simulation.The result shows that the perils of pre-cover’s opening are augmented with the increase of the rising rate of motor’s pressure.Comparing with the box-launching pressure curve in different flight test,the simulation result was validated.The study results offer reference for the optimizing pre-and-post fragile cover opening-pressure.