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Table 9.2 V-22 ight control actuators
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Left Swash Plate (3) Left Tilt Conversion (1) Left Flaperon (4) Left Rudder (1) Elevators (3) Right Flaperon (4) Right Rudder (1) Right Swash Plate (3) Right Tilt Conversion (1)
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Swash plate actuators (6). Three swash plate actuators in each nacelle perform a function similar to the main rotor actuators on a conventional helicopter. They are located equally distant around the swash plate and allow each rotor to be tilted in the pitch and roll axes. Because there are two tilt rotors that may be tilted fore and aft either in synchronism or differentially the resulting vehicle motion is more complex. For example, demanding the rotors to tilt forward (left rotor) and aft (right rotor) causes the vehicle to yaw in a clockwise direction. These manoeuvring modes will be described later Tilt conversion actuators (2). Each tilt conversion actuator causes the appropriate nacelle to rotate between the VTOL and normal ight conditions Flaperon actuators (8). Four aperon sections (combined aps and ailerons), two on each wing, are powered by two aperon actuators each Rudder actuators (2). The left and right rudder surfaces each have a single actuator Elevator actuators (3). There are three elevator sections, each powered by its own actuator V-22 VTOL Modes of Flight The VTOL modes of ight are illustrated in Figure 9.32 and are described below: Pitch. Forward movement of the cyclic stick causes both proprotor discs to tilt forward. The aircraft assumes a nose-down attitude and the airspeed increases in the same manner as a helicopter. Aft movement of the cyclic stick causes the proprotor discs to tilt aft, increasing nose-up attitude and decreasing speed Roll. Movement of the cyclic stick left and right demands differential application of collective pitch and lateral cyclic cause both proprotors to tilt in the appropriate direction causing the vehicle to roll. If rolling left the right proprotor increases collective pitch while the right proprotor decreases collective pitch. Both proprotor discs tilt to the left and the aircraft rolls left Yaw. Movement of the rudder bars causes differential fore and aft cyclic to be applied to the proprotors. If yawing left the left proprotor disc tilts aft and the right proprotor disc tilts forward causing a couple that yaws the aircraft left
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Thrust. Operation of the Thrust Control Lever (TCL) applies cyclic to both rotors causing the lift to increase and the aircraft to climb therefore increasing or decreasing altitude Lateral translation. Lateral operation of the inching control on top of the cyclic stick applies coordinated cyclic to both rotors causing the aircraft to translate left or right
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V-22 Conventional Modes of Flight The conventional ight modes depicted in Figure 9.33. are controlled as follows: Pitch. Forward movement of the control stick causes the aircraft to pitch nosedown due to the operation of the elevators; altitude decreases and airspeed increases. Aft movement of the control stick causes the aircraft to pitch noseup, altitude increases and airspeed decreases. The Angle of Attack (AoA) is monitored and limited
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Roll. Lateral movement of the control stick causes the aircraft to roll using the aperons as ailerons. If rolling left, the left aperons de ect up while right aperons de ect down and the aircraft rolls left Yaw. Movement of the rudder pedals cause the aircraft to yaw using the twin rudders in a conventional aircraft sense Thrust. Operation of the thrust control lever alters proprotor blade pitch and control engine speed thrust and therefore forward speed
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The ight control system that accomplishes these tasks is shown in Figure 9.34. Flight control algorithms are performed by triple redundant Fight Control Computers (FCCs) that interface with MIL-STD-1553B data buses. These data buses provide the links with the avionics system, air data system, left and right Full Authority Digital Engine Control units (FADECs), and primary and secondary attitude data from the Inertial Navigation System (INS) and Secondary Attitude and Heading Reference System (SAHRS). Angle of Attack (AoA) data is also fed into the FCCs. Hardwired interfaces from the left and right rotor transducer set provide rotor related data to the FCCs. Each FCC has hardwired interfaces to the actuator set to provide commands and receive feedback data. In common with