控制舵面：副翼，升降，方向。
用数值优化方法取得自适应翼型最优的舵面偏角，并计算其气动特性。
An optimization method is used to obtain deflection Angle of control surface and the aerodynamic efficiency of airfoil is calculated.
使用在线参数辨识方法，对飞机的气动特性进行估计并用于舵面分配。
The aerodynamic parameters wear estimated through online parameter identification method and were used for actuator deflect allocation.
针对多操纵面飞翼构型飞机，提出了一种在线诊断其舵面故障的方法。
This article provides a method to diagnose on-line the fault of multi-control effector flying wing control surfaces.
本文提出了一种基于模糊观测器的飞机舵面故障检测与重构控制策略。
A fault accommodation approach based on fuzzy observer for nonlinear systems is presented in this paper.
以某型飞机为例，详细描述了如何利用该方法测量舵面铰链力矩的过程。
To a certain type of aircraft, for example, describes the process in detail how to use the methods to measure hinge moment of control surface.
根据舵面悬挂点与摇臂操纵形式的不同，提出了四种连接方式的局部模型。
Based on different forms of hinge points and rocker - arms, four local models of control surface linkage forms were proposed.
今天的飞机，使用硬件余度方法无法恢复关键舵面缺损所造成的严重故障。
In today's aircraft, the hardware redundancy is driven by the critical surfaces resulting in single point-failures.
应用特征方程反问题的直接方法对舵面-液压伺服机构连接刚度参数进行了辨识。
The parameter identification of joining stiffness of rudder hydraulic servo mechanism can be done by using the direct method of characteristic equation anti problem.
研究了当飞机常规操纵舵面失效时，通过调节飞机发动机推力大小来操纵飞机的飞行问题。
In this paper, the concept of emergency flight control system which USES the engine throttle to manipulate the aircraft in case of control surface failure is discussed.
以分枝模态法为基础，将全弹分成弹身、弹翼和舵面三个分枝，建立全弹结构动力学模型。
The branch Mode Method is used to reckon missile's structural dynamic characteristic, and the whole missile is regarded to be composed of three branches-the fuselage, the wings and the rudders.
研究表明：使用非线性试验气动力和线性理论气动力所分析得到的舵面效率具有较大的差别；
The analytical results indicate that the control surface efficiency analyzed based on nonlinear experimental aerodynamic forces and linear theoretical aerodynamic forces are different.
该系统以无刷直流电机作为伺服电机，采用三闭环的控制策略，实现舵面位置的高性能跟踪。
This system with brushless DC motor (BLDCM for short) as its drive adopts three-loop control strategy to achieve the aim at high accuracy position trail of rudder.
针对此翼面上有升降舵的多舵面布局，建立了俯仰运动下不同于翼面上只有副翼的动力学模型。
About multi - control surface configuration with elevators, its dynamic model was established under pitch movement, differing from wing with ailerons alone.
结果表明，该方法简便且精度高，为舵面-液压伺服机构的动力学建模和分析提供了有效方法。
The results show that the method is simple and precise, and it provides an effective way to model and analyze dynamics of rudder hydraulic servo mechanism.
指出了舵面间接正向挤压铸造工艺特点，分析了压力的变化和液流的充填性对舵面成形性的影响。
Technology characteristics have been pointed out. Effects of pressure variety and flow fillability on rudder formation have been analysed.
飞机的基本控制律采用非线性动态逆方法设计，对于模型不准确和舵面故障等因素导致的逆误差采用神经网络进行在线补偿。
The base control law is designed in nonlinear dynamic inversion, and neural networks are used to cancel the inversion error induced by many reasons, especially by actuator failures.
随动补偿片，铰接在操纵面后缘(副翼，方向舵，升降舵)的可动部。
BALANCE TAB, a small hinged moveable part on the trailing edge of a control surface (aileron, elevator, rudder).
鸭式飞机的水平安定面和升降舵从一架飞行器伸出的一个短的翼状控制平面，如航天飞船的机身，被安在飞机翼前方，作为水平稳定器。
A short, winglike control surface projecting from the fuselage of an aircraft, such as a space shuttle, mounted forward of the main wing and serving as a horizontal stabilizer.
升降舵，铰连在水平安定面后缘上的可动部件。用以操纵飞机的俯仰运动(机头朝上及朝下)。
ELEVATOR, a hinged moveable part on the trailing edge of the horizontal stabilizer for airplane pitch (nose up and nose down) control.
俯仰轴—又称水平轴或横轴。由飞机的一侧通向另一侧。飞机绕此轴转动即造成机首的俯与仰。俯仰控制是由升降舵来达成的，水平安定面则为配平之用。
Pitch axis - Horizontal or lateral axis, passes through the airplane from one side to the other - nose up and nose down control is by elevators (and stabilizer for trim).
大展弦比飞翼布局飞机取消了垂尾和常规方向舵，通常采用大偏角的开裂式方向舵作为偏航操纵面。
The high-aspect-ratio flying wing eliminates vertical tail and conventional rudder, and uses instead a split drag rudder with large deflection as its directional control surface.
对螺旋桨与舵附推力鳍分别采用升力面法和非线性涡格法计算。
Lifting surface method and non-linear vortex lattice method were used for the calculation of propeller and rudder with additional thrust fins respectively.
鲁德尔敏感性，或从一个极端总运动，另一方面是受舵角上的漏洞，并在一定程度上，由“皮卡”洞角上了电梯。
Rudder sensitivity, or total movement from one extreme to the other, is controlled by the holes on the rudder horn and, to a degree, by the "pickup" hole on the elevator horn.
从飞机一侧通向另一侧的水平轴或横轴。升降舵控制机头绕此轴作上下的运动。(水平安定面则用以配平。)
Horizontal or lateral axis, passes through the airplane from one side to the other - nose up and nose down control is by elevators (and stabilizer for trim).
水平和垂直安定面、驾驶舱门、方向舵以及升降舵组件目前正在组装和安装。
The assembly and installation of the vertical and horizontal stabilizers, cabin door, rudder and elevator assemblies are being concluded.
水平和垂直安定面、驾驶舱门、方向舵以及升降舵组件目前正在组装和安装。
The assembly and installation of the vertical and horizontal stabilizers, cabin door, rudder and elevator assemblies are being concluded.
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