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本文根据气动助力操纵升降舵系统的特点,推导了飞机纵向静稳定性和纵向阻尼及洗流时差导数的计算公式。导出了飞机由初始定直飞行状态转入到ω_2、ΔV和Δn_y均为常值的稳态机动飞行中升降舵和调整片的偏角。杆位移和杆力以及它们分别对速度和过载的梯度计算公式。利用本文的计算方法,对一架典型的气动助力操纵的大型喷气式飞机(H=8公里,M=0.8)的纵向静态飞行品质进行了验证计算。其结果是可信的,表明计算方法是可行的。
Based on the characteristics of the pneumatic assist control elevator system, this paper deduces the formulas of longitudinal static stability, longitudinal damping and time difference derivative of air flow. The declination angle of the elevator and the adjusting piece in the steady state maneuvering flight from the initial straightening flight state to ω_2 and the constant values of ΔV and Δn_y are derived. Rod displacements and rod forces, and their respective gradient and overload calculations. Using the calculation method in this paper, the longitudinal static flight qualities of a typical large-size air-powered pilot operated airplane (H = 8 km, M = 0.8) are validated. The result is credible, indicating that the calculation method is feasible.