CAJ | 학술논문

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。
통과풍동실험방법연구료비령측활각상태하，대영각세장체모형적측향력화편항력구변화규률。병차응용주동류동공제기술，대비령측활각모형적측향력화편항력구가이공제，연구기유효공제적측활각범위화공제규률。연구결과표명：재영각α＝55°、측활각β＝-24°～＋24°범위내，개변세장체모형두부미우동파진편적평형주향각위치（유효주향각위치재±16°지간변화），모형측향력화편항력구정선성변화규률。차항력화력구선성공제기술위비행기재대영각고궤동비행발생측활시，실현회복급보지안전자태비행，제공일충유효비행공제신방법。
With non-zero sideslip angle condition,the changing laws of side force and yawing moment of a slender body at high angles of attack were investigated through wind tunnel testing.An active flow control technique was used to control the slender body's side forces and yawing moments at non-zero sideslip angle, so as to study the controlling law and the range of effective controlling sideslip angles as well.The results showed that at the condition ofα=55°and the range of sideslip angleβ=-24°~+24°,the side forces and ya-wing moments showed linear changing laws at the effective azimuthally angle ranges (±16°)through changing the equilibrium position of a fast swing micro tip-strake installed on the slender model.When the phantom yaw movement of high agility combat aircraft occurs,this active linear flow control technique could be a new possible flight controlling method for aircraft recovering and safety.