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1. 发明授权

US06796532B2 Surface plasma discharge for controlling forebody vortex asymmetry 失效
标题翻译：用于控制前体涡流不对称的表面等离子体放电
公开(公告)号：US06796532B2
公开(公告)日：2004-09-28
申请号：US10326751
申请日：2002-12-20
申请人： Norman D. Malmuth , Alexander Fedorov , Vladimir Shalaev , Vladimir Zharov , Ivan Shalaev , Anatoly Maslov , Victor Soloviev
发明人： Norman D. Malmuth , Alexander Fedorov , Vladimir Shalaev , Vladimir Zharov , Ivan Shalaev , Anatoly Maslov , Victor Soloviev
IPC分类号： B64C2100
CPC分类号： B64C23/005 , B64C5/12 , B64C2230/12 , Y02T50/166
摘要： The present invention provides a system and method for rapidly and precisely controlling vortex symmetry or asymmetry on aircraft forebodies to avoid yaw departure or provide supplemental lateral control beyond that available from the vertical tail surfaces with much less power, obtrusion, weight and mechanical complexity than current techniques. This is accomplished with a plasma discharge to manipulate the boundary layer and the angular locations of its separation points in cross flow planes to control the symmetry or asymmetry of the vortex pattern. Pressure data is fed to a PID controller to calculate and drive voltage inputs to the plasma discharge elements, which provide the volumetric heating of the boundary layer on a time scale necessary to adapt to changing flight conditions and control the symmetry or asymmetry of the pressures and vortices. In the case of yaw departure avoidance, the PID controller controls the plasma to adjust the separation points to angular locations around the forebody that provide a robustly stable symmetric vortex pattern on a time scale that the asymmetries develop. In the case of lateral control, the PID controller controls the plasma to adjust the separation points to angular locations around the forebody that provide an asymmetric vortex pattern that produces the desired supplementary lateral force and rolling moment.
摘要翻译：本发明提供了一种用于快速且精确地控制飞行器前体的涡流对称性或不对称性的系统和方法，以避免偏航偏离或提供超过从垂直尾部表面获得的辅助侧向控制，其功率，重量，重量和机械复杂度低于当前技术这是通过等离子体放电来实现的，以操纵边界层及其分离点在横流平面中的角位置以控制涡流图案的对称性或不对称性。压力数据被馈送到PID控制器以计算和驱动对等离子体放电元件的电压输入，这些等离子体放电元件在适应不断变化的飞行条件和控制压力的对称性或不对称性的时间尺度上提供边界层的体积加热，旋涡在偏航偏离避免的情况下，PID控制器控制等离子体以将分离点调整到围绕前体的角位置，从而在非对称性发展的时间尺度上提供鲁棒稳定的对称涡流模式。在横向控制的情况下，PID控制器控制等离子体以将分离点调整到围绕前体的角位置，从而提供产生期望的辅助横向力和滚动力矩的不对称涡流模式。

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