气动布局参数对直升机飞行品质的影响

Influences of aerodynamic configuration parameters on helicopter flying qualities

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.

The UH-60A helicopter nonlinear flight dynamic model suited to evaluate the flying qualities was built. Trim calculation of the model was conducted, stability and controllability derivatives were calculat ed, and the agreement between the computational results and the referenced data indicated that the model is feasible and effective. The openloop flying qualities of the UH-60A helicopter were studied by using flying qualities specification of military helicopter （ GJB902-90）. According to the requirements, the change of the UH60A dynamic response characteristics and the control characteristics were computed and compared when the selected aerodynamic configuration parameters were adjusted, the flying qualities sensitivities with respect to the parameters were analyzed. The results show that, changing the rotor height has a significant impact on each quality, the decrement of tail rotor height can improve roll attitude change level, and the tail rotor longi tudinal position is a major factor affecting yaw attitude change and yaw attitude response.