摘要
在高速风洞中对旋转导弹振荡鸭舵与尾翼远距耦合的旋涡干扰特性进行了实验研究。模型由模拟弹身、鸭舵和尾翼组成,其中尾翼有矩形、梯形和三角形三种基本舵面外形。用粒子图像测速(PIV)技术测量了鸭舵尾涡随时间和空间的变化,用快响应压敏涂料(PSP)技术测量尾翼表面的非定常压力分布,用微型六分量气动天平测量尾翼所受的非定常气动力。研究发现:振荡鸭舵尾涡强度沿流向逐渐减弱且旋涡向弹体方向发展;尾翼表面的非定压力分布和气动力与舵面外形和展长相关;展长越长,旋涡影响区越远离翼根,且展长相同时三角舵对尾翼影响最显著。为降低旋涡的干扰,需综合考虑改变旋涡对尾翼的影响区位置和降低旋涡影响强度以进行合理选择。研究结果对降低旋转导弹鸭舵旋涡对尾翼的干扰有重要的参考意义。
Vortex interaction of a long-coupled oscillating-canard and tail of rolling airframe missile was studied by wind tunnel test in this paper.The test model was composed of body,canard and tail.The tail included three type forms of rectangle,trapezoid and triangle.The particle image velocimetry(PIV)technology was applied to measure the vortex under various time and space.The fast-response pressure sensitive paint(PSP)was applied to measure surface unsteady pressure of tail.A micro six component balance was applied to get the unsteady aerodynamics of tail.The study shows that strength of vortex of the oscillating-canard decays along stream-wise and the vortex location goes closer to the body.The unsteady pressure and aerodynamics on tail are related to different span and shape of the canard.The vortex interaction zone goes far away from tail root with longer canard aspect and interference of triangle canard is more obvious.To reduce the disturbance of vortex,it needs to consider both changing the influence area of vortex on the tail and reducing the vortex strength for proper choice.The study results are useful to the model design to reduce the interference between canard vortex and tail of rolling airframe missiles.
出处
《上海航天》
CSCD
2017年第S1期36-43,共8页
Aerospace Shanghai
关键词
旋转导弹
旋涡干扰
振荡鸭舵
尾翼
远距耦合
粒子图像测速
压敏涂料
动态压力测量
rolling airframe missile
vortex interaction
oscillating canard
tail
long-coupled
particle image velocimetry(PIP)
pressure sensitive paint(PSP)
dynamic pressure measurement
