CAJ | 학술논문

为防止舰船导弹舱室内固体火箭发动机发生意外点火，避免出现火灾事故，对导弹舱室内固体火箭发动机意外点火的燃气流场进行数值模拟，并基于组分输运和DPM离散相喷雾模型对导弹舱室内的喷雾降温效率进行耦合计算。然后，通过改变喷嘴组合位置、喷嘴数量、喷雾强度、雾锥角和水温研究相关因素对导弹舱室喷雾降温效率的影响。结果显示：在喷雾降温作用下，导弹舱室内的温度快速下降，温度在3 s内可下降至400 K以下。但是，射流冲击区的降温却不理想，且导弹舱室的底板还需要特殊的热防护措施。同时，考虑到火源的随机性，喷嘴应尽可能均匀布置，数量不宜过少且雾锥角应较大，以提高降温效率。然而，当喷雾强度增大至一定程度后，若再继续增大，降温效率的提高却不明显。研究表明，采用所提喷雾降温数值模拟方法对导弹舱室内固体火箭发动机的意外点火情况进行降温和防控均有效可行。
위방지함선도탄창실내고체화전발동궤발생의외점화，피면출현화재사고，대도탄창실내고체화전발동궤의외점화적연기류장진행수치모의，병기우조분수운화DPM리산상분무모형대도탄창실내적분무강온효솔진행우합계산。연후，통과개변분취조합위치、분취수량、분무강도、무추각화수온연구상관인소대도탄창실분무강온효솔적영향。결과현시：재분무강온작용하，도탄창실내적온도쾌속하강，온도재3 s내가하강지400 K이하。단시，사류충격구적강온각불이상，차도탄창실적저판환수요특수적열방호조시。동시，고필도화원적수궤성，분취응진가능균균포치，수량불의과소차무추각응교대，이제고강온효솔。연이，당분무강도증대지일정정도후，약재계속증대，강온효솔적제고각불명현。연구표명，채용소제분무강온수치모의방법대도탄창실내고체화전발동궤적의외점화정황진행강온화방공균유효가행。
In this paper,the exhaust gas flow fields are simulated in the case of accidental ignition of the rocket motor within the magazine. Particularly,the component transport and the DPM are used to simulate the spray cooling process and the exhaust gas physical fields. Numerical simulation is conducted with dif-ferent influential factors such as the number,position,and water intensity of nozzles as well as the cone angle and temperature of the spray,and their respective effects on the cooling process are investigated. Re-sults show that the temperature in the magazine drops significantly after the spray cooling,which drops be-low 400 K within 3 seconds and slowly decreases afterwards. In contrast,the cooling effect in the imping-ing jet zone is not so ideal,so the magazine baseboard requires special thermal insulation. Also,consider-ing the randomness of the fire source,a substantial number of liquid nozzles,with large cone spray an-gles,should be evenly distributed in the magazine so that the cooling efficiency can be maximized. Final-ly,when the spray intensity reaches a certain level,its effect on the overall cooling efficiency becomes less obvious if it continues to enhance.