超机动飞机飞行控制及大迎角飞行品质研究

Research on Flight Control and Flight Qualities at High Angle of Attack for a Super-maneuverable Aircraft

超机动飞机行控制和大迎角飞行品质研究,对于强调超机动能力的第四代战斗机的飞行控制律设计、验证和试飞评定有着直要意义。以鸭式布局飞机为研究对象,应用推力矢量技术,结合奇异摄动原理和逆系统理论,设计了基于非线性动态逆理论的超机动飞行控制律。从过失速状态飞机空气动力的非线性和非定常迟滞效应、大气紊流等方面初步验证了控制律的鲁棒性,并通过目标截获和跟踪任务的模拟,利用库珀—哈珀评定准则,对飞机的大迎角飞行品质进行了简要地分析。研究结果表明:设计的控制作对滞环和大气紊流的影响有较好的鲁棒性;飞机具有良好的大迎角截获和跟踪能力。研究结果可为超机动控制律设计与试飞验证提供一定的理论方法参考。

It is important to study flight control and flight qualities at high angle of attack for flight control law design, verification and flight test assessment of the 4＇h generation aircraft, emphasized on super-maneuverability. Contrary to a canard aircraft, thrust vectoring technology, singular perturbation theory and inversion principle are applied to develop the post-stall control law based on the nonlinear dynamic inversion method. The robustness of the control law was verified in the following two aspects： nonlinear and unsteady hysteresis effect of aerodynamic in post-stall, atmospheric turbulence. The flight quality of this airplane is briefly assessed with the ＂Cooper-Harper＂ rating by ways of simulating target acquisition and tracking mission. The research results show that the robustness of the control law is well verified by the hysteresis of instrument and atmospheric turbulence and the aircraft has favorable ability of acquisition and tracking. This research can be a useful reference theoretically for the super-maneuverable flight control design and flight test.