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基于适航标准对飞机起降阶段飞行速度的要求,通过建立飞行速度和襟缝翼偏角关系,设计了大型飞机襟缝翼自动保护控制律,并进行了仿真验证。仿真结果表明,该方法能控制襟翼在飞行员误操纵的情况下自动偏转至合理偏角,避免飞机出现失速和超速的危险状态,并随着飞行速度的变化,使襟翼和缝翼的偏转实现最佳组合,保证获得最大升阻比。
Based on the requirements of airworthiness standards for the flight speed of aircraft during the take-off and landing phases, the automatic protection control law of large aircraft wing flaps is designed by establishing the relationship between flight speed and the slat angle, and the simulation is carried out. The simulation results show that this method can control the flap to automatically deflect to a reasonable angle when the pilots mishandle and avoid the dangerous state of stalling and overspeeding. As the flight speed changes, the flap and slat deflection Achieve the best combination to ensure maximum lift-drag ratio.