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以UH-60A直升机为例,建立了适合于飞行品质评价的直升机非线性飞行动力学模型,对算例机模型进行配平验证,并计算了稳定性、操纵性导数.计算结果与参考数据吻合较好,证明模型可用.根据军用直升机飞行品质规范(GJB902—90),选取的典型气动布局参数,计算了不同参数下的直升机的动态响应特性和操纵特性,分析了飞行品质对设计参数的敏感性.结果表明,旋翼高度对各项飞行品质指标都有明显的影响,降低尾桨高度能显著提升滚转操纵功效的品质等级,尾桨纵向位置是影响偏航操纵功效和偏航操纵灵敏度的主要因素.
Taking UH-60A helicopter as an example, a helicopter nonlinear flight dynamics model suitable for flight quality evaluation was established, and the model of the example machine was verified by the formula and the stability and maneuvering derivative were calculated. The calculated results are in good agreement with the reference data It is proved that the model is available.According to the typical helicopter flight quality specifications (GJB902-90), the typical aerodynamic layout parameters are selected to calculate the helicopter’s dynamic response and maneuvering characteristics under different parameters, and the sensitivity of the flight quality to the design parameters The results show that the rotor height has a significant effect on the flight quality indexes, and the reduction of the tail rotor height can significantly improve the quality grade of the roll steering function. The longitudinal position of the tail rotor is the main factor affecting the yaw steering efficiency and yaw steering sensitivity factor.