操縱桿  Control rod 曲柄  Crank 供給、容許  admit

(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.
飛行控制系統(tǒng)提供水平、縱向及垂直方向上的機(jī)動(dòng)控制。它們同時(shí)也為飛機(jī)在地面起飛時(shí)提供升力及從空中降落時(shí)提供空氣阻力。飛控系統(tǒng)分為兩個(gè)主要部分：主飛控系統(tǒng)及次飛控系統(tǒng)。主飛行控制系統(tǒng)包含副翼、升降舵及方向舵。次飛控系統(tǒng)包含擾流板、后緣襟翼、前緣襟翼及水平安定面。本課主要講述主飛控系統(tǒng)。
(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.