• 基本释义

  • 常见搭配

1.Install aileron triangular rocker position.
副翼三角摇臂的安装位置。收藏指正
2.F/A-18 Aileron Composite Actuaror
飞行控制舵机新发展——F/A-18副翼复合材料舵机收藏指正
3.Aileron servo pull rod should be vertical to the shaft of aileron basically.
副翼舵机拉杆应基本上垂直于副翼转动轴线。收藏指正
4.A control surface on an airplane that combines the functions of an elevator and an aileron.
升降副翼兼有升降舵和副翼两种功能的飞机控制平面收藏指正
5.Usually only a small amount of rudder is needed, especially if a large amount of differential(more up aileron motion than down motion) is present.
通常只需要少量的方向舵,尤其是出现大量差速时(上副翼动作多于下副翼动作).收藏指正
6.In mode 2, the right control stick operates the aileron and elevator and the left stick operates the rudder and throttle.
在模式2中,右边的操纵杆控制副翼和升降舵,左边的操纵杆控制方向舵和油门。收藏指正
7.This calculation procedure is programmed in Algol-60 Language. Aerodynamic data of two models with aileron down are then determined and compared with the experimental results.
计算方案已编成Algol—60语言源程序,计算了2个型号偏副翼时气动特性并和实验结果进行比较。收藏指正
8.As a result of applying this method, simple and optimal control laws have successfully been developed for the active suppression of wing bending-torsion flutter and under-ballanced aileron flutter using a single trailing-edge active control tab.
运用这种方法获得用单独后缘主控调整片抑颤的优化控制律,实现了对质量不平衡舵面颤振和翼面弯扭颤振的有效抑制。收藏指正
9.The wing is devided into 12 functional parts,such as structure for bending momen t, for shear force, for air load distribution, for landing gear mounts, for exte rnal hanging, for fuel tank mounts,for leading edge , for trailing edge, for fla p, for aileron, for wing-body joints and for the other parts of the wing.First, established is the wing mass estimation model.Then,the correct factors in the mo del are based on present data of fighter wings determined.
首先建立了飞机总体设计阶段机翼结构质量分配的分析模型;然后根据现有飞机机翼的质量和飞机总体几何参数,用参数优化方法确定了该分析模型中的结构修正系数;从而得到一个机翼结构质量分配模型。收藏指正
10.Several icing parameters were imported to calculate the change of drag coefficient and typical derivatives between clean aircraft and iced aircraft, and the aircraft flight envelope change of iced and un-iced situation was computed, and the small disturbance flight dynamics model was modified to study the effect of the ice accretion on the aircraft dynamics by importing the ice parameter to it, and the longitudinal and lateral stability and the elevator, aileron and rudder step response were also studied and simulated.
根据这些参数计算了飞机结冰后阻力系数以及典型气动导数的变化,并计算了结冰前后飞机的飞行包线;同时对结冰前后飞机的纵向、横侧动稳定性以及升降舵、副翼和方向舵阶跃操纵响应进行仿真计算。收藏指正
尝试查询