retracted. Lock mechanisms and sensors assure that the main gear is down and locked or up and locked.
主起落架支撑机身和部。通过一个减震支柱来减弱与地面的撞击，及滑行时的冲撞和振动。各主起落架都是通过液压作动向内侧收起到机身内部。可通过舱门及轮舱密封性来判断起落架收起是否失效。上锁机构和传感器确保主起落架放下锁好或收起锁好。
(6) The nose gear, located below the aft bulkhead of the control cabin, provides the support for the forward section of the fuselage. The nose gear includes a drag brace, shock strut, torsion links, a hydrauic nose gear actuator and a hydraulic lock actuator. The shock strut consists of inner and outer cylinders. The upper part of the outer cylinderis “Y” shaped with arms extended to the sidewalls of the wheel well. Trunnion pins connect the gear to airplane structure. The “Y” arms and pins provide lateral stability. The gear rotates about the trunnion pins during extension and retraction. A tow lug and crossbolt are installed for attaching a tow bar to the nose gear.
前起落架，位于驾驶舱后压力隔板的下方，为机身前段提供支撑。前起落架包括一个阻力杆、减震支柱、扭力臂、一个液压前起作动筒和一个液压锁作动筒。减震支柱包括内、外作动筒。外部作动筒的上部是一个“Y”形的有一伸向轮舱侧壁的杆。轴向销钉连接着机轮与机身。“Y”形杆和销钉可提供稳定性。轮子在收放时以轴向销钉为轴旋转。牵引环和横向螺栓安装在前起落架上用来连接牵引杆。 (7) Shocks and bumps during taxi, take off and landing are absorbed by the shock strut which contains oil and is charged with compressed air or nitrogen. Longitudinal stability is provided by a hinged drag brace which folds upward and aft during gear retraction。for steering, the shock strut inner cylinder turns within the outer cylinder. Torsion links connected at the upper end to a steering collar and at the lower end to the shock strut inner cylinder transmit a turning moment supplied by hydraulically
actuated steering cylinders. The steering is controlled by the handwheel on the pilots sidewall or by the rudder pedals. The handwheel can turn the nose wheel 78 from center and the rudder pedals at full deflection can turn the nose wheel 7 from center.
飞机在滑行、起飞及降落时的震动和撞击可通过包含滑油和注入压缩空气或氮气的减震支柱减弱消除。纵向稳定性可通过铰接的阻力杆在起练架收起时折合在上方及后方。作动时，减震支柱里面的圆柱体在外圆柱体里面转动。扭力臂。 LESSON 15 FLIGHT CONTROLS 一、单词 飞行 水平的 轴 起飞 地面 主要的 驾驶盘 导致 角度 建立 Flight Lateral Axes Takeoff Ground Primary Control wheel Cause Angular Establish 操纵 纵向的 增加 着陆 被分成 次要的 配平 转 动 量； 值 大小、尺寸 全部的 保持 角度 驾驶舱 反馈 转动鼓轮 Control longitudinal Increase Landing into Secondary Trim Rotate Amount Magnitude Total remain Angle Flight deck Feedback bus Drum 方法、手段 位置 姿.态 操纵面 达到 对?起作用 稳定的 降低 操纵台 信号 驾驶盘操纵 考虑 反向力 驾驶杆 扇形盘 Means Position Attitude Control surface Reach Act on Stable Lose Control stand Signal Control steering 换能器 升力中心 横滚 扭力管 transducer Center lift Roll Torque tube 副翼操纵力限制 Aileron force limiter 重心 俯仰（率） 调整片 Center gravity Pitch rate Tab Control column quadrant Counter force Consider wheel 机动动作 垂直的 升力 阻力 maneuver Vertical Lift Drag Group Are divided 集团 再成流线型 Refair 平衡 坡度 命令 传感器 Balance bank Command Sensor 自动驾驶仪 Autopilot 操纵杆 Control rod 曲柄 Crank 供给、容许 admit 二、TEXT
(1) the flight controls provide maneuvering control about the lateral, longitudinal, and vertical axes. They also provide increased lift for take off and landing as well as increased aerodynamic drag both in flight and on ground. Flight controls are divided into two major groups: primary and secondary. The primary flight controls consist of the ailerons, elevators, and rudder. The secondary flight controls consist of the spoilers, trailing edge flaps, leading edge devices, and the stabilizer. We will introduce the primary flight controls in this lesson.
飞行控制系统提供水平、纵向及垂直方向上的机动控制。它们同时也为飞机在地面起飞时提供升力及从空中降落时提供空气阻力。飞控系统分为两个主要部分：主飞控系统及次飞控系统。主飞行控制系统包含副翼、升降舵及方向舵。次飞控系统包含扰流板、后缘襟翼、前缘襟翼及水平安定面。本课主要讲述主飞控系统。
(2) The aileron control system provides the means of rotating the airplane about the longitudinal axis. The aileron control system is actuated by rotation of either the captain’s or first officer’s aileron control wheel. The autopilot system also provides a control input. These inputs control a hydraulic powered system which drives the ailerons. Moving the ailerons out of their trimmed position causes the airplane to ratote and change attitude. The angular amount of control surface moved establishes the “rate-of –change”. When the desired magnitude of attitude change has been reached, the control surfaces are refaired, total forces acting on the airplane are balanced and the airplane remains stable in a bank angle. Since the airplane is in a bank, the wing loses some of its lift, so up elevator command is used by the pilot or by the autopilot.
副翼控制系统提供飞机纵向转动的方式。副翼控制系统通过转动机长或副驾位的副翼控制轮作动。自动驾驶系统也可提供控制输入。这些
输入控制驱动副翼的液压动力系统。转动副翼离开配平位置，致使飞机转动并改变姿态。控制面角度的移动形成“变化率”。当姿态变化达到希望的量值时，控制面再成流线型，作用在飞机上的合力达到平衡，同时飞机在一个角度上保持稳定。因飞机有一定的角度，机翼升力降低，所以驾驶员或自动驾驶系统会给出升降舵上升的命令。 (3) The ailerons are located on the outboard trailing edge of each wing. Other aileron components are located in 3 main areas: ? Flight deck
The control wheels are located in the forward portion of the flight deck. The aileron trim switch is located on the control stand. ? Wheel well area
The aileron power control units(PCU, convert a pilot or autopilot mechanical driven input to a hydraulic power driven mechanical output to drive the aileron) are located on the forward wall of the main wheel well. The autopilot aileron actuators are located on the forward wall of the main wheel well. The aileron position sensor provides two feedback postion signal from the aileron system to the A/P system. ? Lower nose compartment
The control drum and bus drum are connected to the control wheel, located in the lower nose compartment. The roll CWS force transducer is connected between the bus drum and the control drum, the output of the force transducer provides signals to the autopilot. The aileron force limiter limits control wheel movement during A/P operation, the control wheel rotation is limited to 17°with flaps up and 25°with flaps down. 副翼位于每个机翼前缘外侧，其它副翼组件位于3个主要区域： ? 驾驶舱
控制轮位于驾驶舱前部。副翼配平开关位于控制台上。 ? 轮舱区域
副翼动力控制组件（PCU，转变驾驶员或自动驾驶系统机械驱动的输
入为液压驱动机械输出，用以驱动副翼）位于主轮舱前壁。自动驾驶副翼作动筒主轮舱前壁。副翼位置传感器从副翼系统提供两个位置反馈信号给自动驾驶系统。 ? 机头下方
控制鼓及转动鼓轮连接到控制轮上，位于机头下方。横滚驾驶盘操纵反向换能器连接在转 动鼓轮与控制鼓之间，力量转换器的输出为自动驾驶提供信号。副翼操纵力限制器限制控制轮在自动驾驶仪操作时移动。控制轮的转动被限制在襟翼上升17°及襟翼下降25°之间。 (4) To understand elevator poeration consider the airplane balanced about the center of lift (CL). The center of gravity (CG) is shown forward of the center of lift. The stabilizer provides a counter force to the CG. The stabilizer may be trimmed to changer the force as required to maintain balance.
The elevators are used to change the pitch attitude. Moving the elevators out of their faired position causes the airplane to change the pitch attitude about the lateral axis. The amount of elevator movement establishes the airplane pitch rate. When the desired attitude is reached, the elevators are faired and the air-plane maintains the new pitch attitude.
升降舵操作要考虑飞机相对于升力中心的平衡。重力中心一般在升力中心的前面。安定面提供一个反向力给重力中心。安定面也可以在需要时通过配平改变力量以保持平衡。
升降舵用来改变飞机俯仰姿态。移动升降舵离开它们的流线型位置，使得飞机改变水平轴上的俯仰姿态。升降舵的移动量形成俯仰率。当达到希望的姿态时，升降舵再成流线型，飞机保持新的俯仰姿态。 (5) Two control columns provide pitch control of the airplane . each control column extends through the floor into the lower nose compartment. A torque tube connects the control columns together. The control columns allow the pilots to control the airplane about the lateral axis.
两个驾驶杆提供飞机俯仰控制。每个控制杆通过地板沿伸到前舱。一