基于翼面压力的飞行器气动力感知技术与自由飞验证

Aerodynamic perception from distributed pressure and free flight test

飞行器在大迎角飞行状态下其复杂绕流流动会导致非指令运动出现,严重影响了飞行器的操纵性与飞行安全。现有以惯性元件为核心的机载设备无法直接提供非定常气动力参数,而如何实时感知飞行器大迎角状态的非定常气动力/力矩,是抑制非指令运动现象的核心所在,将是未来战机设计中亟待解决的空气动力学和飞行控制的关键问题之一。针对上述问题,提出基于翼面压力信息获取特征截面滚转力矩系数Clsec,估算飞行器全机在大迎角状态下的非定常气动力矩,进而判断飞行器的滚转运动的设想。风洞和飞行试验研究结果表明:对于80°/48°双三角翼,0.8c特征截面滚转力矩系数Clsec与模型滚转力矩存在相关性;在飞行器进行大迎角平飞动作时,非指令滚转运动下的滚转力矩系数Clsec大幅增加;Clsec能够比惯性传感器提前预测模型的滚转运动趋势,可为飞行器大迎角状态的非指令运动抑制提供一定数据依据。

The complex flow around the aircraft at high Angle of Attack(AOA)will lead to uncommanded motions,seriously damaging the maneuverability and flight safety of the aircraft.Since the existing airborne equipment with inertial core components is unable to provide unsteady aerodynamic parameters,real-time perception of the unsteady aerodynamic force/moment of aircraft at high AOA,which is the core of restraining uncommanded motions,will be one of the key problems in aerodynamics and flight control in the future advanced aircraft design.To solve these problems,this paper proposes a new method to estimate the unsteady aerodynamic moment of the whole aircraft at high AOA based on the distributed pressure to obtain the rolling moment coefficient Clsecof the characteristic section,and then to judge the rolling motion of the aircraft.The results of wind tunnel and flight experiments show that for the 80°/48° double delta wing,the 0.8c characteristic cross section Clsechas a correlation with the rolling moment of the model;when the aircraft is flying at high AOA,the rolling moment coefficient Clsecincreases considerably;Clseccan predict the rolling motion trend of the model ahead of time compared with the inertial sensor,thus providing valuable data foundation for the suppression of uncommanded motions at high AOA.