摘要
由卷弧翼火箭圆锥运动稳定性分析需要,对卷弧翼火箭稳态流场作数值模拟,并将计算结果与试验结果进行对比,验证了数值模拟的精度,且计算中得到试验中不易获得的侧向力矩系数。根据翼面压力分布,分析了卷弧翼火箭自诱导滚转力矩和侧向力矩产生的原因。利用强迫滚转法和气动辨识技术计算了火箭的滚转阻尼力矩系数,计算结果和试验结果差别不大。经数值模拟圆锥运动时卷弧翼火箭的非稳态流场认为,圆锥运动对阻力的影响主要是由攻角产生的静态效应。
Aiming at stability analysis for cone motion of rocket with wraparound fins, the flow field was numerically simulated. The accuracy of numerical simulation was verified by comparing computational and experimental results, and the side moment coefficient was obtained. The pressure contours on fin surface obtained during the experiment was used for analyzing the formation reasons of roll moment and side moment of rocket with wraparound fins. The roll damping moment coefficient was calculated by means of forced roll method and aerodynamic parameter identification technique, and the calculated results agree well with the experiment data. Finally unsteady flow filed of rocket with wraparound fins during the cone motion was numerically simulated, and it was found that the main effect of the cone motion on drag is the static effect caused by attack angle.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2007年第3期181-183,218,共4页
Journal of Solid Rocket Technology
关键词
卷弧翼
滚转阻尼力矩
圆锥运动
wraparound fin
roll damping moment
cone motion
