论文部分内容阅读
根据复合式共轴直升机的构型特点,建立了上/下旋翼、机翼、机身、全动平尾、垂尾(含方向舵)和螺旋桨的气动力模型,并在此基础上建立了过渡过程的配平方程.针对过渡飞行过程的操纵冗余问题,分别采用线性过渡和功率最小优化过渡两种过渡飞行方案,对复合式共轴直升机的过渡飞行过程的操纵策略进行了研究.以样例复合式共轴直升机为例,进行了过渡飞行模式下两种操纵策略的配平计算,并对两种过渡操纵策略下的需用功率、操纵量和姿态进行了对比.结果表明:所述两种过渡方案均能解决操纵冗余问题,并能合理给出过渡模式的操纵量和姿态.在操纵量变化的平稳度、飞行控制的难易程度和飞行品质方面,线性过渡方案更优.
According to the configuration characteristics of the compound coaxial helicopter, the aerodynamic model of the upper / lower rotor, the wing, the fuselage, the fully movable tail, the vertical tail (including the rudder) and the propeller is established and the transition process is established .To solve the problem of maneuvering redundant during the transitional flight process, two transitional flight schemes of linear transition and minimum power optimization transition are respectively used to study the maneuvering tactics of the transitional flight process of composite co-axial helicopters. Composite coaxial helicopter as an example, the calculation of two kinds of maneuvering tactics in the transitional flight mode is carried out, and the required power, the manipulated variable and the attitude under the two transitional maneuvering strategies are compared.The results show that the two kinds The transition scheme can solve the problem of maneuvering redundancy and can rationally give the manipulative amount and attitude of the transitional mode.The linear transition scheme is superior in the smoothness of the manipulated variable, the flight control ease and the flight quality.