Abstract: An actuating system effects rotation of wing slat and flap panels of an aircraft and includes actuators having arms rigidly mounted to the panel and allowing some wing-to-panel rotation during wing/panel bending, and actuators having arms mounted to the panel to allow angular displacement of the arms relative to the rigidly mounted arms, whereby structural deflection of the frame of the aircraft is inhibited from imposing unanticipated destructive loads on either the actuating system components or the aircraft frame itself.

Abstract: A gas turbine engine for aircraft propulsion includes a variable pitch fan, pitch change of which is effected by providing a small D.C. excitation current to a selected one of two non-rotating field coils dependent upon the direction of pitch change desired. The field coils each form the static part of respective polyphase A.C. alternators, and the rotating armatures of the alternators connect to respective separate stator windings of a compound polyphase A.C. reversible induction motor rotating with the fan. An armature of the motor is relatively rotatable and couples with the fan blades to pivotally vary their pitch angle. An A.C. current is available from the non-excited alternator field coil, and may be rectified and controlled for use as the D.C. excitation current. Thus, all energy requirements of the pitch change apparatus may be extracted from the rotor of the fan engine.

Abstract: A variable displacement motor control responsive to the pressure differential across the motor, with provisions for reverse motor operation and for aiding load conditions.