Aerodynamic Control of High Performance Aircraft Using Pulsed Plasma Actuators
Aerodynamic Control of High Performance Aircraft Using Pulsed Plasma Actuators
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DOI：
10.2514/6.2009-697
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发表时间：
2009-01
期刊：
影响因子：
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通讯作者：
T. Matsuno;H. Kawazoe;R. Nelson
中科院分区：
文献类型：
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作者：
T. Matsuno;H. Kawazoe;R. Nelson
目前正在发展一种操纵细长切向卵形头部体前体涡的主动流动控制技术。等离子体作动器被用来利用非对称前体涡尾流的非线性特性，在低速和大迎角范围内进行侧向/方向控制。实验证实了等离子体激励器可以利用附壁效应来驱动前体模型上的旋涡。力和力矩的测量结果表明，这种位移可以成功地产生显着的变化，他们的侧力，这可以用来扩大机动飞行包线为未来的战斗机设计。高速可视化数据表明，涡运动的响应存在很强的时滞，并建议多参数耦合来确定驱动的效果。
The active flow control technology to manipulate forebody vortices on a slender tangent ogive nose body is being developed. The plasma actuators are being used to exploit the bistable nature of the asymmetric forebody vortex wake for lateral/directional control in lowspeed and high-angle-of attack regimes. The experiments have confirmed that the plasma actuator can be used to displace the vortex on the forebody model by the Coanda effect. The results of the force and moment measurement indicate that this displacement could successfully generate significant change in their side force, which could be utilized to extend maneuvering flight envelop for future fighter designs. High speed visualization data show that there is strong time lag in the response of the vortex motion, and multi-parameter coupling to determine the effect of the actuation is suggested.