阻力伞高原气动力增大机理与控制方法研究及验证  

Research and verification on mechanism and control method of drag parachute aerodynamic force increase on the plateau

作　　者：徐宏 余凤华 XU Hong;YU Fenghua(AVIC Aerospace Life-support Industries Ltd.,Xiangyang 441003,China)

机构地区：[1]航空工业航宇救生装备有限公司,湖北襄阳441003

出　　处：《飞行力学》2022年第6期77-82,共6页Flight Dynamics

摘　　要：针对飞机高原着陆释放阻力伞气动力增大机理与控制方法开展了研究与验证。首先,分析了阻力伞高/平原开伞动载情况。然后,对阻力伞高/平原拉直力进行了研究,理论推导出开伞过程中拉直力随海拔高度增加而增大;通过试验现象研究指出采用先拉伞衣法,拉直过程中主伞衣不加约束控制的随机充气,在提前充气阻力特征达到一定条件下,拉直力的数值会超过开伞动载,并分别在平原地区进行了调研取证和高原地区专项试验验证。最后,针对高原试验中阻力伞轴颈断裂问题,提出了加装伞衣套约束主伞衣提前充气控制拉直力增大的方法,并进行了试验验证。研究成果表明,对阻力伞高原开伞过程气动力增大机理与控制方法的研究及验证的结果是一致的,措施是有效的。The aerodynamic force increase mechanism and control method of the release drag parachute for aircraft landing on plateau were studied and verified. Firstly, the dynamic load of plateau/plain parachute opening was analyzed. Then, the drag parachute plateau/plain snatch force was studied. It was deduced theoretically that the snatch force in the opening process increases with the increase of the altitude. It was pointed out through experimental phenomenon research that if the method of pulling the parachute first was adopted and the main parachute was randomly inflated without constraint control during the straightening process, the value of the snatch force would exceed the opening-shock force when the resistance characteristic of inflating in advance reaches to a certain condition. The research and evidence collection in the plain area and the special test in the plateau area were carried out respectively. Finally, aiming at the problem of the shaft neck fracture of the resistance parachute in the altitude test, the method of controlling the increase of snatch force by adding a parachute sleeve to restrain the main parachute to inflate in advance was put forward, and carried out test verification. The research results show that the mechanism of parachute aerodynamic force increase is consistent with the results of control method research and verification, and the measures are effective.

关 键 词：高原 阻力伞 气动力 拉直力 控制与验证 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]