Preliminary Experimental Study on Aerodynamic Characteristics Control of Slender Body Using DBD Plasma Actuator
Preliminary Experimental Study on Aerodynamic Characteristics Control of Slender Body Using DBD Plasma Actuator
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DOI：
10.2322/tastj.10.pe_97
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发表时间：
2012
期刊：
影响因子：
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通讯作者：
H. Nishida;Sakae Mizuki;Isao Miyazaki;S. Nonaka;T. Nonomura;Y. Inatani
中科院分区：
文献类型：
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作者：
H. Nishida;Sakae Mizuki;Isao Miyazaki;S. Nonaka;T. Nonomura;Y. Inatani
细长体大迎角非对称分离涡对细长体产生很强的侧向力，导致细长体姿态失稳。本文研究了细长体分离流动的主动控制问题，提出了侧向力和俯仰力矩的比例控制方法。采用介质阻挡放电（DBD）等离子体激励器作为流动控制装置，在风洞中进行了锥柱试验体的流动控制实验。自由流速度为9 m/s，雷诺数约为42000。利用后体作动器将侧力系数按比例控制在±1.0左右，通过控制重心位于距机身顶点55%位置时的俯仰力矩，将静稳定性迎角控制在25 ° ~ 40 °和65 ° ~ 85 °。我们估计，在真实的飞行中，为了有效地控制空气动力学，需要更高的致动器输出功率。此外，我们证实，致动器的突发操作模式可以降低所需的输出功率。
Asymmetric separation vortices over a slender body at a high angle of attack exert a strong side force on the body and lead to the loss of attitude stability. We investigated the active control of the separation flow over a slender body and addressed the proportional control of the side force and the pitching moment. A flow control experiment was conducted in a wind tunnel using a cone-cylinder test body and a Dielectric Barrier Discharge (DBD) plasma actuator as a flow control device. The free-stream velocity was 9 m/s and the Reynolds number was approximately 42000. The side force coefficient was proportionally controlled within approximately ±1.0 using the actuator at the aft body, and the static stability angle of attack was controlled from 25 to 40 degrees and 65 to 85 degrees by controlling the pitching moment when the center of gravity was at the 55% position from the body apex. We estimated that a higher actuator output power is required for the effective control of the aerodynamics in a real flight. In addition, we confirmed that the actuator burst operation mode could reduce the required output power.