路基同心筒发射导弹热环境与载荷特性对比研究

Comparative study on thermal environment and load characteristics of missile for land-based concentric canister launch scheme

针对路基同心筒自力发射过程载荷与热环境的评估问题,研究了两型路基中段导流同心筒的发射流场特性。以火箭发动机的纯气相燃气流场试验证实了本文采用的基于压力基耦合格式计算燃气流的可靠性;依托域动分层结构化动网格技术,对2种结构的中段导流同心筒自力发射三维流场进行了非定常数值仿真计算,分析了各同心筒方案发射过程流动机理及导弹载荷特性。三维计算表明:2种方案受“引射效应”和“倒吸效应”的影响都较小,导弹只在发射初期受到高温燃气流扰动;相同条件下,“内圆外方”方案的热环境、载荷特性稍逊于“内圆外圆”方案。

Aiming at the evaluation of the load and thermal environment during the self-launching process of the roadbed concentric canister launch,this paper studied the launch flow field characteristics of the two types of roadbed CCL system.The pure gas jet flow field of the rocket engine was solved by the pressure-based coupling scheme,the numerical calculation flow field structures were in good agreement with the experimental results.Based on the pure gas flow field test of the rocket engine,the reliability of the calculation method based on the pressure-based coupling scheme adopted in this paper was verified from the comparison of the flow field structure calculation and test.Relying on the layered structured dynamic grid technology,the non-constant simulation calculations of the three-dimensional flow field of the middle diversion CCL self-launching process were performed.Both the flow field mechanism and missile load characteristics of different structure forms were analyzed.The three-dimensional calculations showed thatthe two schemes were less affected by the“ejection effect”and the“reverse absorption effect”,and the missile was only disturbed by the high-temperature gas flow at the initial stage of launch process;the thermal environment and load characteristics of the“inner circle and outer circle”scheme were slightly inferior to those of the“inner circle and outer circle”scheme at the same conditions;after structural optimization,the“inner circle and outer side”scheme could only have the characteristics of convenient transportation and excellent thermal environment.