鸭式旋翼/固定翼飞机过渡模式控制律设计  

Control law's design in transitional mode of canard rotor/wing aircraft

作　　者：黄晶[1] 李俨[1] 赵凯瑞[1] 张梦妮[1] 

机构地区：[1]西北工业大学自动化学院,陕西西安710129

出　　处：《飞行力学》2012年第6期523-526,共4页Flight Dynamics

摘　　要：过渡飞行技术是鸭式旋翼/固定翼飞机研制过程中的关键技术之一。针对鸭式旋翼/固定翼飞机过渡模式存在强非线性、控制输入转移的问题,首先建立了飞机纵向非线性方程并进行小扰动线性化;然后针对操纵面冗余提出了配平算法;最后采用指数权重分配方法进行了纵向过渡模式数字仿真。仿真结果表明,该权重分配方法能有效保证过渡模式的平稳过渡。The transitional flight technology is one of the key technologies for the Canard Rotor/Wing aircraft.To solve the problems of the strong nonlinearity and control input change in the transitional mode,we established the longitudinal nonlinear equations and linearized the equations with ＂small perturbation＂.Then,with respect to the inputs redundancy,the trimming algorithm was proposed.Finally,the exponential weighting allocation was given and longitudinal transitional numerical simulation was conducted.The simulation result indicates that the control weighting allocation proposed is able to guarantee the steady transition.

关 键 词：鸭式旋翼 固定翼飞机 过渡模式 指数权重分配 控制律设计 

分 类 号：V275[航空宇航科学与技术—飞行器设计] V249.1