头部钝度和尾部形状对空射火箭气动特性的影响  

Effect of Nose Bluntness and Different Afterbody on Aerodynamic Characteristics of Air-launched Rocket Model

作　　者：张艳华[1] 李华星[1] 张登成[2] 屈亮[2] 郑无计 

机构地区：[1]西北工业大学航空学院,西安710072 [2]空军工程大学航空航天工程学院,西安710038

出　　处：《弹道学报》2015年第1期27-32,共6页Journal of Ballistics

基　　金：国家自然科学基金项目(U1333131)

摘　　要：为了研究空中发射运载火箭外形对气动特性的影响规律,通过低速风洞实验,利用六分量天平测量空射火箭模型在迎角0~80°,4个速度（17m/s,25m/s,35m/s,40m/s）下的气动力和气动力矩。结果表明：在零侧滑条件下,模型的背风区出现了非对称涡,产生较大的侧力和偏航力矩,俯仰力矩随迎角的变化存在不稳定区域;相比圆柱形尾部模型,收敛扩张形尾部提高了模型的纵向稳定性,6%头部钝度的圆头模型最大侧力减少至少50%,非对称涡的起始迎角提高了7°。研究结果可为内装式空射火箭的外形设计提供一定的参考。To study the rule of different shape affecting the aerodynamic characteristics of airlaunched rocket,the experiments in low-speed wind tunnel were carried out at the angle of incidence range of 0-80°and the speed of 17m/s,25m/s,35m/s and 40m/s.Forces and moments were measured through six-component balance.The result shows that vortex asymmetry appears under the conditions of zero side slip.Asymmetrical phenomenon leads to larger side force and yaw moment.In addition,variation of the pitching moment with angle of attack shows instability at some incidences.The longitudinal stability of the model with convergent-expanded afterbody is improved compared to cylindrical afterbody.The maximum side force of the blunt nose model with6% bluntness is reduced at least by 50%,and the onset angle for vortex asymmetry is increased by 7°.The results offer some references for designing the cabin air-launched rocket.

关 键 词：空中发射 运载火箭 大迎角 非对称涡 头部钝度 气动特性 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]