反尾旋伞动态仿真计算研究  

Research on simulation of anti-spin parachute system

作　　者：赵涛[1] 王启[1] 王建培[2] 吴菊英[3] 

机构地区：[1]中国飞行试验研究院飞机所,陕西西安710089 [2]西北工业大学365所,陕西西安710072 [3]空军工程大学电讯工程学院,陕西西安710077

出　　处：《飞行力学》2001年第4期19-22,共4页Flight Dynamics

摘　　要：简要介绍了研制与安装应急反尾旋伞系统对现代高机动飞机的大迎角特性试验研究的重要作用 ,特别是对失速 /过失速 /尾旋特性试验鉴定的必要性和重要性。介绍了反尾旋伞系统的工作原理 ,建立了反尾旋伞的数学模型 ,估算确定了反尾旋伞阻力面积 ,并对用反尾旋伞改出尾旋进行了动态仿真计算 ;同时 ,研究了不同尺寸反尾旋伞的尾旋改出效果。In this paper, the importance or necessity for the installation and employment of an anti spin parachute system for the flight test research on modern aircraft high AOA characteristic, especially for the stall/spin and post stall flight test, is described briefly. The mechanism of an anti spin parachute is analyzed, the mathematical model of an anti spin parachute is built, and a numerical simulation of aircraft entering into stall/spin is completed. Furthermore, the dynamic behavior of using the anti spin parachute recovered from the spin is simulated. The spin retrieve effects of using different kinds of parachute sizes are also determined.

关 键 词：反尾旋伞 动态仿真计算 大迎角试验 飞机 数学模型 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]