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摘要:
飞翼布局飞行器采用多个气动舵面共同作用来控制飞行，常规气动舵面的结构复杂，在大迎角时由于流动分离，舵面操纵效率显著降低。等离子体激励器具有结构简单、重量轻和响应快等优势，常被用在流动控制上。本文利用激励器抑制单侧翼面流动分离产生不对称的气动力，对飞翼布局飞行器滚转通道的控制进行了试验研究，得出了激励器在飞行器上的最优布置位置和最佳控制参数，并和常规副翼舵面滚转操控效果进行了对比。结果表明：布置于内翼、中翼前缘的等离子体激励器能够获得最佳的滚转控制效果；激励器调制频率对飞行器滚转控制效果的影响较大，而激励电压对滚转控制效果的影响较小；与常规副翼相比，等离子体激励器在大迎角时对滚转通道的操控效果优于副翼。
Abstract:Flying wing aircraft usually uses multiple aerodynamic control surfaces for flight control. The aerodynamic control surface has a complex structure and control efficiency decreases dramatically at large angles of attack due to flow separation. The plasma actuator is usually used in flow control due to the advantages of simple structure, light-weight design and fast time response. In this paper, tests were done using the plasma actuator to produce asymmetrical aerodynamic forces for flying wing aircraft roll control by suppressing the flow separation on unilateral wing. The optimal dispose position and discharge parameter of plasma actuator were obtained and aileron roll control effect was also investigated and compared with plasma actuator. The results indicate that the plasma actuator arranged at the leading edge of inner and middle wing can get the best roll control effect. The modulation frequency of plasma actuator has significant impact on aircraft roll control, while excitation voltage's impact is small. Compared to the aileron, the plasma actuator achieves better roll control effect at large angles of attack.
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Key words:
- plasma actuator /
- flying wing /
- wind tunnel test /
- roll control /
- flow control
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图 3 D布置方式激励器编号
Figure 3. Plasma actuator number corresponding to arrangement position D
图 4 A布置方式滚转力矩系数增量随迎角变化
Figure 4. Variation of rolling moment coefficient increment with angle of attack corresponding to arrangement position A
图 5 B、C布置方式滚转力矩系数增量随迎角变化
Figure 5. Variation of rolling moment coefficient increment with angle of attack corresponding to arrangement position B and C
图 6 AC布置方式滚转力矩系数增量随迎角变化
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Figure 6. Variation of rolling moment coefficient increment with angle of attack corresponding to arrangement position AC
图 7 D布置方式滚转力矩系数增量随迎角变化
Figure 7. Variation of rolling moment coefficient increment with angle of attack corresponding to arrangement position D
图 8 不同调制频率滚转力矩系数增量随迎角变化
Figure 8. Variation of rolling moment coefficient increment with angle of attack corresponding to different modulation frequencies
图 9 不同激励电压滚转力矩系数增量随迎角变化
Figure 9. Variation of rolling moment coefficient increment with angle of attack corresponding to different excitation voltage
图 10 不同占空比滚转力矩系数增量随迎角变化
Figure 10. Variation of rolling moment coefficient increment with angle of attack corresponding to different duty cycles
图 11 激励器与副翼不同舵偏的滚转力矩系数增量随迎角变化
Figure 11. Variation of rolling moment coefficient increment caused by plasma actuator and aileron deflection with angle of attack
图 12 激励器与副翼不同舵偏的升力系数、阻力系数、俯仰力矩系数、侧向力系数及偏航力矩系数增量随迎角变化曲线
Figure 12. Variation of lift coefficient, drag coefficient, pitch moment coefficient, lateral force coefficient and yaw moment coefficient increments caused by plasma actuator and aileron deflection with angle of attack
表 1 天平量程和校准精度
Table 1. Measuring range and calibration accuracy of force balance
参数 X/kg Y/kg Z/kg Mx/
(kg·m)My/
(kg·m)Mz/
(kg·m)天平量程 1.6 6.0 2.2 0.21 0.14 0.38 校准精度/% 0.08 0.03 0.06 0.02 0.01 0.08 注：X—轴向力；Y—法向力；Z—侧向力；Mx—滚转力矩；My—偏航力矩；Mz—俯仰力矩。 
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表 2 不同布置位置对应的等离子激励器编号
Table 2. Plasma actuator number corresponding to different arrangement positions
激励器编号 
A0 0 A1 5 A2 10 A3 15 B0 5 B1 10 B2 20 B3 40 B4 50 C0 0 C1 5 C2 10
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