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为了有效降低飞机机翼根部弯矩和减轻结构重量,针对我国大型飞机中的机动载荷减缓控制系统进行了设计与仿真分析验证,根据实际飞机结构特点提出了一种传感器布局方案,建立了升降舵、副翼、扰流片等独立偏转的仿真分析模型,在常规控制律的基础上,基于控制分配方法进行直接升力控制,仿真结果表明:所设计的系统能够实现机动载荷的减缓,并使得飞机法向过载降低21.7%。
In order to effectively reduce the root bending moment of aircraft wings and reduce the weight of the structure, aiming at the maneuvering load reduction control system of large aircraft in our country, the design and simulation analysis are carried out. According to the characteristics of actual aircraft structure, a sensor layout scheme is proposed, Aileron, spoiler and other independent deflection of the simulation analysis model, based on the conventional control law, based on the control of the distribution method for direct lift control, the simulation results show that: the system designed to achieve the reduction of maneuvering load, and makes the aircraft method Reduce overload to 21.7%.