超声速半流伞设计与分析

半流伞是一种典型的超声速减速伞，结构设计和气动特性分析是研究其工作性能的基础。文章结合某超声速减速伞设计实践，论述了超声速伞型的选择和半流伞结构设计方法。通过低速风洞试验、高速风洞试验和高速飞行投放试验，对半流伞气动特性、开伞特性及最大开伞动载进行了研究，获得了半流伞的摆角参数和阻力系数变化规律。研究结果表明，半流伞超声速段阻力系数减小是前置体尾流效应、伞形状变化及充气不稳定等综合因素造成的。火工动力开伞与倒拉法程序结合是开伞程序设计的关键。由于颤振和气动热的影响，超声速段开伞动载计算与亚声速段有明显不同。研究结果对超声速伞的稳定减速机理、结构优化设计和性能试验具有参考意义。

Design and Analysis of Supersonic Half-flow Parachute

Half-flow parachute is a typical supersonic decelerator. Structural design and aerodynamic analysis are the basis of researching its working performance. With a practical design of a supersonic decelerator, this paper discusses the selection of supersonic parachutes and design methods for half flow parachute structure. Through low speed wind-tunnel test, high speed wind-tunnel test and high speed air drop test of the half-flow parachute, vibration angle parameters and the changing pattern of persistence coefficient are derived. Results show that the decrease of the persistence coefficient during supersonic period is due to complex factors such as front body wakes effect, deformation of the canopy and inflation instability. The combination of explosive device deployment and pull-down method is key to the design of deployment procedure. In attribute to vibration and aerodynamic heating, dynamic load calculation in supersonic stage is apparently different from that in subsonic stage. The researching results can provide a reference for stabilizing and decelerating mecha- nism, structural optimization and performance test of supersonic parachute.