带伞空降风洞试验中稳定伞的模拟研究  

Simulation Study of Stable Parachute in Wind Tunnel Tests with Airborne Parachutes

作　　者：惠增宏[1] 侯金玉 熊超[1] 张彬乾[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空工程进展》2014年第2期154-158,164,共6页Advances in Aeronautical Science and Engineering

基　　金：西北工业大学科技创新基金(2010KJ0101)

摘　　要：为了更加真实地模拟空降初期过程,在国内率先对带伞空降风洞试验中稳定伞的模拟方法进行研究,包括稳定伞相似参数的确定、阻力系数的模拟。主要讨论一种在伞模型末端系配重并进行自由落体试验的方法来测量伞阻力系数,并通过在伞顶开孔来调整伞阻力系数,最后采用调整后的伞模型进行风洞试验验证。结果表明:该方法可精确测量伞阻力系数,改变伞顶孔大小能有效调整伞阻力系数,且伞顶开孔可使稳定伞的下落过程更稳定;试验结果符合真实空降时近机身复杂绕流运动流场特性,与空降视频中空降轨迹发展规律相一致,表明所论述的稳定伞模拟技术是可行的。In order to simulale the initial process of airborne parachute more truly, the simulation method of sta ble parachutes in airborne parachute wind tunnel tests is presented, which is the first presentation in China, in eluding figuring out the similar parameters and simulating the drag coefficiem. It mainly discusses a method to measure drag coefficient by fastening counterweights onto the end of parachute and doing the free fall tests. Which adjusts the drag eoefficient by opening holes on the top of the stable parachute model, and finally uses the adjusted model to make experimental verification in wind tunnel tests. The method can accurately measure the drag coefficient, and opening holes on the top of the stable parachute can effectively adjust the drag coeffieient and make the falling of parachutes more stable. The results of wind tunnel tesls results agree with the complex flow field characteristics near the fuselage, and are in line with the airborne trajectories law on video, h shows that the simulation technology of stable parachutes is feasible.

关 键 词：带伞空降 风洞试验 稳定伞模拟 阻力系数 视觉测量 流场 

分 类 号：V211.753[航空宇航科学与技术—航空宇航推进理论与工程]