复合式共轴直升机过渡模式的操纵策略

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.

Control strategy for compound coaxial helicopter under conversion mode

According to the characteristics of the compound coaxial helicopter,the general aerodynamic forces and moments of rotors,wing,fuselage,stabilator,vertical stabilizers (containing the rudder) and propeller were modeled and a trimming equation set was established accordingly.In view of the controlling redundancy problem,a control strategy was studied for the compound coaxial helicopter under conversion mode,using the linear transition method and minimal power optimization transition method.A sample compound coaxial helicopter was taken as an example to demonstrate the effectiveness of the method.Then the trimming values,the attitude angles and the power of these two methods were compared.The result shows that both the two methods can solve the controlling redundancy problem,while the trimming values and the attitude angles are reasonable and the linear transition method is better in the smooth change of the control values,the difficulty level of the controlling system and the flight quality.