CAJ | 학술논문

由于航空器的弹性性质,飞行过程中飞行参数的不断变化会引发运动稳定性和阵风响应特性的改变. 在设计颤振主动抑制或阵风减缓控制器的过程中,以某一飞行状态为基础设计出的控制律往往不能保证在一定飞行参数范围内的性能. 针对此问题,首先通过非定常气动力有理拟合方法建立时域连续阵风响应状态空间方程,再考虑模型随马赫数和动压的变化特性建立线性参数变化(LPV)模型. 最后以线性参数变化模型为基础构造了包含动压和马赫数参数不确定性的线性分式变换模型,并设计了机翼颤振主动抑制与阵风减缓鲁棒控制器. 结果表明,对于算例机翼,其在马赫数05~07范围内的颤振动压平均增大10%,且在飞行参数不断变化的时域仿真中,翼尖过载的均方根值降低514%.
유우항공기적탄성성질,비행과정중비행삼수적불단변화회인발운동은정성화진풍향응특성적개변. 재설계전진주동억제혹진풍감완공제기적과정중,이모일비행상태위기출설계출적공제률왕왕불능보증재일정비행삼수범위내적성능. 침대차문제,수선통과비정상기동력유리의합방법건립시역련속진풍향응상태공간방정,재고필모형수마혁수화동압적변화특성건립선성삼수변화(LPV)모형. 최후이선성삼수변화모형위기출구조료포함동압화마혁수삼수불학정성적선성분식변환모형,병설계료궤익전진주동억제여진풍감완로봉공제기. 결과표명,대우산례궤익,기재마혁수05~07범위내적전진동압평균증대10%,차재비행삼수불단변화적시역방진중,익첨과재적균방근치강저514%.
The stability characteristics and dynamic responses of a flexible wing vary with flight conditions. During the design process of a controller for active flutter suppression or gust alleviation, the controller' s performance can?not be sustained when flight conditions change if it is designed on the basis of a single flight condition. To solve this problem, the time domain state?space model is firstly built up with rational function approximation of the unsteady aerodynamics, then the model' s dependence on Mach number and dynamic pressure is taken into account by con?structing a linear parameter?varying ( LPV) model. A linear fractional transformation model is finally built up on the basis of the LPV model;after which a robust controller is designed for active flutter suppression and gust allevia?tion. The results on a test wing show that the flutter dynamic pressure increases about 10% when the Mach number varies between 05 and 07. As can be seen from the simulation results, when the flight parameters keep varying, the root?mean?square of the wing tip overloads decreases by 514%.