一种飞机侧向增稳系统设计方案及仿真验证

Design Scheme and Simulation Validation for Aero Lateral Stability Augmentation System

摘要:

具有三角翼、大后掠角等气动布局特点的现代超音速飞机虽然解决了飞行速度问题,但同时极易出现高空飞行的荷兰滚阻尼、航/横侧向静稳定性减小、滚摆比变大等问题。为改善飞机航/横侧运动的飞行品质,基于飞机滚转和偏航两通道的相互交联,将滚转通道舵偏信号引入偏航通道,以增强偏航角速度反馈信号,增加飞机转弯的协调性,进而设计了一种高速飞机航/横侧向增稳控制系统。通过进行大量仿真,验证了所设计的飞机航/横侧向增稳控制系统结构简单合理,在其控制规律传动比等参数选择合理时,飞机航/横侧向飞行品质良好。

Abstract:

Though speed of the modern supersonic airplane in the pneumatic layout with delta-wing and big sweepbacketc. characteristics was increased, the problems were contemporary appearance in high altitude and velocity which aero lat.eral movtion damp and yaw/roll lateral static stability would get smaller and the roll versus swing ratio would get bigger. Inorder to improve aero lateral fly stability in high altitude and velocity, basis on coupling relation of the aero roll and yawtwo channels, the high speed aero Lateral Stability Augmentation System (LSAS) were designed that roll rudder departureangle signal was imported to the yaw channel, so that yaw angle speed feedback signal was got enhanced and aero turn ma.neuverability was got improved. A great deal of contrastive simulation was done under the Matlab platform. The simulationresult showed that the aero lateral LSAS structure was simple and reasonable, and easy to realization. At it control law ratiowas chosed reasonable, the designed aero LSAS can improve aero fly quality.