冲压翼伞上翼面开缝技术研究进展  

Review on Technology of Parafoil Systems with Spoilers

作　　者：姚晨曦 杨春信[1] 周成龙[1] 程炜 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《航天返回与遥感》2017年第6期19-28,共10页Spacecraft Recovery & Remote Sensing

摘　　要：上翼面扰流缝驱动是一种新颖的控制冲压翼伞横向和纵向飞行性能的方法。文章概括了近年来国外冲压翼伞上翼面开缝技术的研究方向和进展,依次对影响冲压翼伞气动性能的四个扰流缝结构因素——开缝方向、弦向位置、下拉度和开缝气室展向分布的研究情况与结果进行详细阐述与分析总结,得出结论前缘侧扰流缝在纵向控制方面比后缘侧扰流缝更有效。扰流缝的合理弦向位置大约位于0.15~0.3c(c为翼伞的弦长,0.15~0.3c表示开缝位置与翼型左侧之间的弦向距离)。在扰流缝最大下拉度以内,滑翔比随下拉度增大而线性减小,大下拉度还能使翼伞飞行延迟大约4°迎角失速。扰流缝下拉度很小时存在一定范围的死区,之后转率随着下拉度的增加线性增大。开缝气室数量超过最大开缝气室数量时,翼伞系统变得难以控制,且最大转率会饱和。在最大开缝气室数量以内,随着开缝气室数量增加,扰流缝的有效性随之线性增加。开缝气室离伞衣中心线越远越容易产生高的转率,但是会降低滑翔比的控制性能。相比于其他控制方式,下拉扰流缝所需的力远远要小,能有效减小翼伞控制单元的尺寸,对翼伞的操作有重大的意义。该研究可为翼伞精确空投技术研究提供一定的技术参考。The activation of spoilers is a new method of achieving longitudinal and lateral control of ram-air canopies. This paper introduces the concept of upper surface bleed air spoiler, expounds foreign new research work for this technology in these years. The paper discusses 4 important factors flap orientation, chordwise location, deflection and spanwise arrangement of the spoiler, which influences aerodynamic characteristics of parafoils, and gives an analysis and summary of it. The leading edge side spoiler is more effective than the trailing edge side spoiler in longitudinal control. The correct chordwise location of the spoiler is approximately 0.15-0.3c, and 0.15-0.3c represents the chordwise distance between the spoiler position and the left side of the airfoil. Within the maximum deflection of the spoiler, the glide ratio decreases linearly with the increase of the deflection of the spoiler, and the large deflection of the spoiler can cause the stall delay about 4 degrees angle of attack. There is a certain dead zone in the small deflection of the spoiler, and then the turn rate increases linearly with the increment of the deflection of the spoiler. The system becomes difficult to control and the maximum turn rate will be saturated beyond the maximum number of cells with spoilers. Within the maximum number of cells with spoilers, the effectiveness of the spoiler increases linearly with the increment of the number of cells with spoilers. The larger the distance from the centerline of canopy to cells with spoilersis, the higher the turn rate is, but on the contrary for the glide ratio. Compared with other control methods, the force required to actuate spoilers is much less. This can effectively reduce the size and weight of the parafoil system, which has great significance for the parafoil operation. This study can provide the technical reference for the research of PADS system.

关 键 词：扰流缝 滑翔比 转率 冲压翼伞 返回技术 

分 类 号：V244[航空宇航科学与技术—飞行器设计]