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基于MIL-STD-1797A飞行品质规范,开展了针对大展弦比飞翼作战飞机滚转轴和偏航轴飞行品质特性的研究.随着控制系统对系统动态特性调节作用的日益增强,由飞机构型所引起的动态响应特性差异已变得越来越小,飞翼飞机的闭环滚转模态、螺旋模态、滚转-螺旋耦合振荡、荷兰滚模态、驾驶员座位处的侧向加速度等均可达到较好的飞行品质,但稳态配平特性主要受构型的影响,不能完全满足飞行品质的要求;分析了大展弦比飞翼作战飞机在快速滚转、侧风起降和非对称推力情形下的对滚转轴和偏航轴操纵效能的要求,由于气动构型和操纵面配置等差异,大展弦比飞翼作战飞机在完成某些飞行任务时对操纵效能的需求与常规构型的飞机存在着较大差异.
Based on MIL-STD-1797A Flight Quality Specification, the flight quality characteristics of roll axis and yaw axis for large aspect ratio flying wing combat aircraft are studied.With the control system's regulation of the dynamic characteristics of the system increasing day by day, Type dynamic response caused by the difference has become smaller and smaller, flying-wing aircraft closed-loop roll mode, spiral mode, roll-screw coupling oscillation, the Dutch roll mode, the lateral acceleration at the driver's seat Can achieve better flight quality, but the steady-state trim characteristics are mainly affected by the configuration and can not fully meet the requirements of flight quality. The analysis of the large aspect ratio flying wing combat aircraft in the rapid roll, crosswind takeoff and landing and Asymmetric thrust on the roll axis and yaw axis maneuverability requirements, due to the aerodynamic configuration and control surface configuration differences, large aspect ratio flying wing combat aircraft in the completion of certain missions on the control performance requirements and The conventional configuration of the aircraft there is a big difference.