Closed-Loop Stall Control System
Closed-Loop Stall Control System
复制标题
闭环失速控制系统
DOI：
10.2514/1.c000262
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发表时间：
2010
影响因子：
2.2
通讯作者：
A. Mangalam
中科院分区：
文献类型：
--
作者：
J. Poggie;C. Tilmann;P. Flick;J. Silkey;Bradley A. Osbourne;Gregory F Ervin;D. Marić;S. Mangalam;A. Mangalam
在一个变形翼型上演示了闭环失速感测和控制系统。FlexSys，Inc.使命自适应柔性机翼经过修改，在后缘变形襟翼的上游位置安装了波音公司的电介质阻挡放电致动器面板，并在模型表面安装了热膜传感器。由Tao Systems，Inc.开发的信号分析算法，被施加到热膜信号以检测分离并触发介质阻挡放电致动器的激活。该系统在美国空军研究实验室菲利普P. Antonatos亚音速空气动力学研究实验室风洞设施中得到了成功的验证，在闭环控制和湍流边界层状态下，马赫数为0.05（弦雷诺数为9 x 10 5）时，升力提高了约10%。作动器的有效性在马赫数为0.1时得到了验证，但必须扩展到马赫数为0.2-0.3时，才能使大型飞机的起飞和进场的失速控制系统具有实用性。可以通过优化致动器位置和输入波形来获得该性能水平。
A closed-loop, stall sense and control system was demonstrated on a morphing airfoil. The FlexSys, Inc. Mission Adaptive Compliant Wing was modified to accept a Boeing Co. dielectric barrier discharge actuator panel in a location immediately upstream of the trailing-edge morphing flap, and hot-film sensors were installed on the model surface. A signal analysis algorithm, developed by Tao Systems, Inc., was applied to the hot-film signals to detect separation and trigger activation of the dielectric barrier discharge actuators. The system was successfully demonstrated in the U.S. Air Force Research Laboratory Phillip P. Antonatos Subsonic Aerodynamics Research Laboratory wind-tunnel facility, and an improvement in lift of about 10% was observed at Mach 0.05 (chord Reynolds number 9 x 10 5 ) under closed-loop control and a turbulent boundary-layer state. Actuator effectiveness was demonstrated up to Mach 0.1, but must be extended to Mach 0.2-0.3 to enable a practical stall control system for takeoff and approach of large aircraft. It may be possible to obtain that level of performance by optimizing the actuator locations and input waveforms.