Abstract: Measuring apparatus for providing a reading representing a magnetic field component or the electric field component of incident radio frequency electromagnetic radiation comprises a set of magnetic field sensors and a set of electric field sensors interchangeably connectable to a measuring device which has an indicator instrument and an optical output to which can be connected a repeater device by means of an optical fibre cable which thus does not exert a perturbing influence on the field being measured. The sensors are omnidirectional balanced devices in which the detector elements are constituted by suitably shaped metallic film deposits on dielectric substrates, and can be interchanged by a simple plug-in connection which also holds the sensor physically in position on the measuring device.

Abstract: A pair of like electrical/electronic equipment racks are uniquely arranged in an avionics bay located in the belly (lower lobe) of a wide-bodied aircraft, with the fronts of the racks facing a central access aisle that extends lengthwise of the fuselage between the racks, and with the rear of each rackfacing one of two outboard aisles that extend parallel to the central aisle along the sides of the bay. At the forward end of the bay, a transversely extending passageway interconnects the central aisle with the two outboard aisles and enables the ground crew to access both the front and rear of each rack by entering the bay through a ground access hatch disposed in the lower most central portion of the fuselage and opening into the bay at the central aisle. Emergency in-flight access to the bay from the upper lobe, by in-flight personnel, is also available through a hatch disposed in a deck lying above and slightly aft of the avionics bay.

Abstract: Core noise, a low frequency noise component believed to be partly caused by the combustion processes within the engine, and turbine noise, a higher frequency noise component caused by the interaction of high velocity gases with the engine's turbine, are attenuated by noise absorbing structures that are disposed within the engine's nozzle and that in part define the physical geometry of the nozzle duct. The nozzle is formed of an outer sleeve and an inner generally bulb-shaped plug which are coaxially arranged to define an annular nozzle duct that channels the flow of gases rearwardly from the outlet of the engine's turbine. The plug has a hollow interior that is partitioned into a plurality of cavities that communicate with the nozzle duct via perforations provided in an outer wall of the plug.

Abstract: An escape slide container is mounted for selective, upward movement with a track-mounted, overhead sliding door in an aircraft fuselage. Slide deployment mechanism for releasing the container from the door and for attaching it to the floor of the aircraft allows the door to move upwardly independently of the container, leaving the container attached to the floor. An over-center linkage supports the container above the floor while upward movement of the door trips the over-center linkage to propel the container outwardly through the door opening to deploy the escape slide under the urging of gravity. Apparatus for arming and disarming the slide for deployment operates in conjunction with door opening and closing apparatus that simultaneously effects movement of a door carrier to unplug the aircraft door from the opening in the fuselage and initiates upward traverse of the door along a plurality of tracks from which the door is supported at three points.

Abstract: An escape slide container is mounted for selective, upward movement with a track-mounted, overhead sliding door in an aircraft fuselage. Slide deployment mechanism for releasing the container from the door and for attaching it to the floor of the aircraft allows the door to move upwardly independently of the container, leaving the container attached to the floor. An over-center linkage supports the container above the floor while upward movement of the door trips the over-center linkage to propel the container outwardly through the door opening to deploy the escape slide under the urging of gravity.

Abstract: A pair of like electrical/electronic equipment racks are uniquely arranged in an avionics bay located in the belly (lower lobe) of a wide-bodied aircraft, with the fronts of the racks facing a central access aisle that extends lengthwise of the fuselage between the racks, and with the rear of each rack facing one of two outboard aisles that extend parallel to the central aisle along the sides of the bay. At the forward end of the bay, a transversely extending passageway interconnects the central aisle with the two outboard aisles and enables the ground crew to access both the front and rear of each rack by entering the bay through a ground access hatch disposed in the lower most central portion of the fuselage and opening into the bay at the central aisle. Emergency in-flight access to the bay from the upper lobe, by in-flight personnel, is also available through a hatch disposed in a deck lying above and slightly aft of the avionics bay.

Abstract: Combination primary and fan air thrust reversal control systems for long duct fan jet engines are disclosed. In one form, the system spoils and expands primary air and, then, allows the spoiled, expanded air to exit from the fan air duct exhaust nozzle while directing fan air in a thrust reversal direction out cascade vanes circumferentially located in the aft portion of the engine nacelle. In other forms, the system directs unequal pressure fan air and primary air through separate thrust reversal ducting and out cascade vanes circumferentially located in the engine nacelle. In equal pressure fan air and primary air systems, the air may be mixed in ducting prior to being emitted from common cascade vanes, or may be maintained separate prior to emission. In still other forms, the primary air is pre-exhausted through separate nozzles located in the primary duct wall, and a portion is then exhausted through the nacelle cascade vanes.

Abstract: An exhaust nozzle for exhausting the effluent of a turbofan gas turbine engine across a portion of the upper surface of an aircraft wing wherein the exhaust nozzle is arranged to establish a temperature profile within the exhausted gases that prevents overheating the wing surface. The nozzle includes a contoured outer housing that longitudinally transists from a circular entrance opening, arranged for interconnection with the rear face of a gas turbine engine, to a semi-elliptical outlet opening located on the upper surface of the aircraft wing. A generally tubular mixer section, of the daisy type, is mounted within the outer housing and coaxially surrounds an engine tail plug.

Abstract: A pod for mounting a turbofan jet propulsion engine on a strut is constructed so that a common cowl and portions of the fan air duct and turbine exhaust duct can accomodate a plurality of different turbofan engines that have substantially the same thrust rating but have variations in structural dimensions. The portions of the pod common to all such engines include an annular cowl, an inlet throat that merges into the forward end of the cowl to form an inlet highlight, a rearward portion of the outer fan duct wall, a rearward portion of the inner fan duct wall and a turbine nozzle. The common portions of the pod structure are designed about a common datum plane orthogonally oriented relative to the pod center line. The rear face of the turbine casing of each of the turbofan jet propulsion engines is positioned in this datum plane when mounted in the pod. An annular inlet adapter forms an inlet wall that couples the rearward edge of the inlet throat to the forward, peripheral portion of the engine fan casing.

Abstract: An aircraft turn coordinator used in an aircraft to sense both yaw and roll rate along the longitudinal flight axis. The coordinator includes a gimbaled rate gyroscope which is connected to a turn indicator arm by a gear train. The rapid rotation or lashing of the gimbaled gyroscope due to air turbulence is reduced by dampening the movement of the gimbal.

Abstract: Detecting and indicating the failure of the primary drive train of a flap actuator system that includes primary and secondary drive trains driven by a common power supply is disclosed. When the primary drive trains fails, a free motion zone formed between the common power supply and the secondary drive train is crossed. Crossing of the free motion zone causes the position of an electro-mechanical sensor (or sensors) to change. The change in position of the electro-mechanical sensor(s) creates or changes the value of an electrical signal or signals to provide an indication of the failure of the primary drive train.