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根据驾驶员位置处法向加速度反应近似为零的条件,选择了算例飞机的纵向增稳器返馈系数。按文献[1]的结果,估算了乘座品质的改善情况,且分析了飞机和增稳器组合的动态特性。结果表明,当飞机和增稳器组合的操纵期望参数(CAP)接近9.81/1_x,则可满足乘座品质要求。同时,增稳器的工作范围在平尾总偏角的10%以内。但必须注意返馈系数和舵机、助力器的时间常数之间的匹配关系,以防止对数幅频特性曲线中斜率为-20分贝/+倍频程段的频带过窄。如果平尾的面积相对机翼面积较大,例如(?)≥0.2,则在分析飞机和增稳器组合的动态特性时,必须考虑升降舵偏转引起的升力项。
According to the condition that the normal acceleration response at the driver’s position is approximately zero, the longitudinal stabilizer feedback coefficient of the example aircraft is selected. According to the results of [1], the improvement of ride quality was evaluated and the dynamic characteristics of aircraft and augmentation combiner were analyzed. The results show that the seating quality requirement can be satisfied when the manipulated expected parameter (CAP) of the combined aircraft and augmentation stabilizer approaches 9.81 / 1_x. At the same time, the working range of the stabilizer is within 10% of the total tail angle. However, attention must be paid to the match between the feedback coefficient and the time constant of the servo and booster to prevent the band of the logarithmic amplitude-frequency characteristic curve from being too narrow at a frequency of -20 dB / + octave. If the area of the flat tail is large relative to the wing area, for example (?) ≥0.2, the lift term due to the deflection of the elevator must be taken into account when analyzing the dynamics of the combination of aircraft and augmentation stabilizer.