直升机近地飞行时的配平和机动操纵分析  

Trimming and maneuvering control of a helicopter flight near the ground

作　　者：苏媛[1] 曹义华[1] 方振平[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：《航空动力学报》2010年第2期348-353,共6页Journal of Aerospace Power

基　　金：航空科学基金(05A51012)

摘　　要：在单旋翼带涵道尾桨直升机的非线性全量飞行动力学模型的基础上,提出了求解配平和机动操纵问题的一种混合算法,研究了地面效应对配平和机动操纵的影响.以某直升机为算例,在近地飞行和考虑不同速度与高度时,分别进行了直升机稳定飞行时的配平计算,然后以侧向紧急转弯机动为例,对机动操纵规律的问题进行了计算分析,计算结果与地面效应的理论相符合,机动过载和操纵变化规律可以为飞行试验提供借鉴.所建立的理论方法可以为直升机近地飞行时的动力学和控制分析提供参考.Based on a nonlinear flight dynamics model for a single rotor helicopter with ducted tail rotor, a mixed （Newton method/Gradient method） numerical method was proposed to solve helicopter trimming and maneuvering control laws. The effects of ground on trimming and maneuvering control were studied. Taking a typical helicopter as an example, the trims for steady flight with different velocities and altitudes were first solved. Then control laws for lateral jink maneuver were obtained for helicopter NOE （nap of earth） flight. The calculation results conform to the ground effect theory, and load factor and control variation of the maneuver can be used for reference. The theoretical method here can provide the references for the analyses on dynamics and unsteady control in helicopter maneuvering flight near the ground.

关 键 词：直升机 地面效应 非线性 配平 机动操纵 

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]