There are a number of actuation units, besides the primary and secondary fight control, there are 3 The secondary controls available to give the pilot finer control over flight or to ease the workload. They include wing flaps, slats, spoilers, air brakes and variable-sweep wings. pitch, roll and yaw control, basically obtained by deflection of elevators, ailerons and rudder (and combinations of them) The secondary fight control (blue, for color print) indicated in blue for the secondary flight control: high-lift and lift-dump devices, airbrakes, tail trimming, etc 2.2 Aircraft has a number of different control surfaces: The primary flight control (Red, for colour print), i.e.
3 and 4 show the classic layout for a conventional airliner. The number and type of aerodynamic surfaces to be controlled changes with aircraft category. Roll – Ailerons Yaw – Rudder Pitch – ElevatorsĪ further evolution of the servo-assisted control is the fly-by-wire technique, based on signal processing of the pilot’s demand before conversion into actuator control. The primary fight control is the ailerons, elevators, and rudder.įig 4 – A simplified diagram for Flight control surfaces on airliner Secondary Flight Control refers to control of aircraft flight other than Primary Flight Control.įig 3: The primary and secondary fight control surface 2 The above are called Primary Flight Control. Roll(along Y axis) pitch (along X axis) yaw (along z axis). If the aircraft wishes to head into a new direction, it must make a turn (or a roll) on one of the X, Y, aor Z axis. The various control related to the fight systemįig 2: The X-Y-Z 3D view of aircraft flight xĪircraft flies on a 3D terrain (X, Y, and Z) The following will x x xįlight Control Linkage Hydraulic Components Environmental Controlįig 1. Without these parts, the airplane will not be able to leave the ground.īesides the electric system to provide the electrical energy discussed before, there are fight control system. In this topic, we will concentrate on the fight related control electrical unit. Due to the complexity, each of its function can be classified as a “system”.īasically, The electrical system based on electrical power or electronic control and with mechanical and other control units, we will focus more on the electrical and control parts. This section will introduce some of its functions. Modern aircraft is a complex machine with a lot of electrical, electronic, mechanical, hydraulic or a combination of them. The electro-hydraulic servo valves control the movement of the actuators.Introduction to Aircraft Design and Aviation Systems (ENG3005) The actuators convert hydraulic pressure into control surface movements. The actuators are powered by the hydraulic pressure generated by the pumps in the hydraulic circuit.
With hydraulic flight control systems, the aircraft's size and performance are limited by economics rather than a pilot's muscular strength.Ī hydro-mechanical flight control system has two parts: Hydraulically powered control surfaces help to overcome these limitations. The complexity and weight of mechanical flight control systems increase considerably with the size and performance of the aircraft. A hydraulic system uses a fluid under pressure to drive machinery or move mechanical components.
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