纵列式直升机配平计算及稳定性、操纵性分析  

Analysis for determining trim,stability and controllability of tandem helicopter

作　　者：李国知[1] 曹义华[1] 杨倩[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《北京航空航天大学学报》2009年第1期74-77,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：为了进行纵列式直升机定直平飞状态的配平计算,建立了两种非线性飞行动力学模型(涡流理论模型和动量理论模型).提出了基于线性小扰动理论和五点中心差分算法的稳定性、操纵性导数计算方法;采用状态空间表达式形式的动力学方程,计算了纵列式直升机非耦合运动状态下的稳定根;以动量理论模型为基础,以MATLAB软件为计算平台,进行了纵列式直升机稳定性与操纵性的分析.最终计算结果与参考数据吻合较好,为纵列式直升机飞行品质研究奠定了基础.Two nonlinear tandem helicopter dynamic models （i. e. the vortex theory model and the momentum theory model） were built separately to trim the helicopter at the hover in the forward and backward /light. A computational method for the stability and controllability derivatives was proposed based on the linear perturbation theory and five-point central difference algorithm. The stability roots of the tandem helicopter in the uncoupled mode were computed using the dynamic equations in the state-space form. Based on the momentum theory model, the stability and controllability of the tandem helicopter were analyzed through using the MATLAB software as the computational platform. The agreement between the computational results and the referenced data indicates that the models are feasible and effective, and they can lay the foundation of the research about the tandem helicopter＇s flying qualities.

关 键 词：纵列式直升机 配平计算 稳定性 操纵性 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]