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通过风洞实验方法研究了非零侧滑角状态下,大迎角细长体模型的侧向力和偏航力矩变化规律。并且应用主动流动控制技术,对非零侧滑角模型的侧向力和偏航力矩加以控制,研究其有效控制的侧滑角范围和控制规律。研究结果表明:在迎角α=55°、侧滑角β=-24°~+24°范围内,改变细长体模型头部微扰动摆振片的平衡周向角位置(有效周向角位置在±16°之间变化),模型侧向力和偏航力矩呈线性变化规律。此项力和力矩线性控制技术为飞行器在大迎角高机动飞行发生侧滑时,实现恢复及保持安全姿态飞行,提供一种有效飞行控制新方法。
The variation of lateral force and yaw moment of slender body model at high angle of attack under non-zero side slip angle was studied by wind tunnel test. And the active flow control technology is applied to control the lateral force and yaw moment of the non-zero slip angle model to study the effective control of the slip angle range and control law. The results show that in the range of α = 55 ° angle of attack and β = -24 ° ~ + 24 ° of side slip angle, the position of the equilibrium circumferential angle of the perturbed pendulum vibration element in the slender body model is changed (effective circumferential angle position is ± 16 °), the model lateral force and yaw moment change linearly. The force and moment linear control technology provides a new effective flight control method for the aircraft to achieve the recovery and maintain a safe attitude flight when the aircraft maneuvers in a high maneuvering flight at a high angle of attack.