增速发动机斜置喷管燃气对导弹气动性能的影响  

Effects of exhausting gases from oblique nozzles of a missile's speeding engine on its aerodynamic performances

作　　者：王恒宇 孙中文 肖赟 李畅 彭士 张弛 周小淞 曹白玉 WANG Hengyu, SUN Zhongwen, XIAO Yun, LI Chang, PENG Shi, ZHANG Chi, ZHOU Xiaosong,CAO Baiyu(Jiangnan Industries Group Go., Ltd, Xiangtan 411207, China)

机构地区：[1]江南工业集团有限公司,湘潭411207

出　　处：《固体火箭技术》2018年第5期658-663,670,共7页Journal of Solid Rocket Technology

摘　　要：为了得出增速发动机斜置喷管燃气对导弹气动性能的影响,应用CFD软件先计算得出了无燃气影响下导弹的气动参数特性,再对导弹在飞行过程中增速发动机斜置喷管燃气影响下导弹的外流场进行了数值模拟,对比分析得出了燃气流对导弹气动性能影响的大小。计算结果表明,燃气改变了导弹在飞行过程中的外流场结构,导致导弹的升力系数减小,阻力系数和滚转力矩系数增大,特别是引起导弹气动压心系数发生了变化,使导弹在增速段的压心前移,静稳定度降低,研究结果对导弹在增速段的弹道设计和控制具有重要意义。In order to investigate the effects of exhausting gases from the oblique nozzles of a missile＇s speeding engine on its aerodynamic performances, a CFD code has been used to calculate the aerodynamic parameters of the missile without nozzle gases first, and then the flow field of the missile was simulated numerically under the effects of the speed engine oblique nozzle gases dur- ing the missile flight. By comparative analyses, the influence of nozzle gas on aerodynamic performance of the missile has been ob- tained.The calculated results show that the nozzle gases would change the flow field structure of the missile during flight, which in- duces the decrease of the lift coefficient, and the increase of the drag coefficient and roll torque coefficient. In particular, it causes the change of the aerodynamic pressure coefficient in the action center.As a result,the pressure center of the missile is moved for- ward and the static stability was reduced.The results are of great significance to the ballistic design and the control of the missile in the acceleration period.

关 键 词：导弹 斜置喷管燃气 气动参数 CFD 静稳定度 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]