等离子体流动控制的前掠翼静气弹发散主动抑制研究

针对前掠翼静气动弹性发散问题，基于等离子体流动控制与流固双向静力耦合技术，通过求解三维定常可压N-S方程与结构静力平衡方程，在亚声速条件下施加等离子体激励和不施加激励时对其进行对比仿真研究。前掠翼选用NACA0015翼型，等离子体流动控制采用唯象学模型，施加在机翼上表面前缘。研究结果表明：在前掠翼外侧上表面前缘施加等离子体激励后，激励区附近局部来流经激励受到电场力做功，总能量增加，动能与压力势能分别有不同程度的增大，外在表现为上表面局部流速加快，压力增大，升力有一定损失，下表面压力基本不变，在机翼前缘外侧靠近翼尖处产生低头力矩，可控制前掠翼弹性变形，有效抑制其气弹发散，且随着激励强度的增加，抑制作用逐渐增强。研究结果可为变前掠翼飞行器的气动弹性设计和机翼的流动控制等提供参考。

Active Suppression of Static Aero Elastic Divergence of Forward Swept Wing Based on Plasma Flow Control

In view of the problem of the static aero elastic divergence of forward-swept wings, based on plasma flow control and fluid-solid two-way interaction technology, the three-dimensional constant compressible N-S equation and structural static balance equation are solved. Under condition of subsonic velocity, the flow field with and without plasma actuation is calculated. The forward-swept wing being NACA0015 airfoil and the plasma actuation area being a phenomenological model, both of them are applied to the leading edge of the upper surface of the wing. The results show that when the plasma actuation is applied to the upper surface of the outer leading edge of the forward-swept wing the local incoming flow in the actuation region is excited, and the work is done by the electric field force. The total energy, the kinetic energy and the pressure potential energy increase to a different degree, whose external manifestation is that the local flow velocity on the upper surface increases and the pressure increases while the lift partly decreases, and the pressure on the lower surface remains basically unchanged. A bow moment is generated near the wing tip on the outside of the leading edge of the wing, which can control the elastic deformation of the forward swept wing. This effectively suppresses the static aero elastic divergence of the forward-swept wing ,and with the increment of excitation intensity, the suppression effect gradually increases. The results give a reference to the aero elastic design of the variable forward-swept wing aircraft and the flow control of the wing.