Abstract: A quick release panel assembly comprising a panel which is releasably fastened to a structure by a release and locking assembly. The release and locking assembly includes a driver element and four actuating arms that are pivotally connected to the driver element, the cover, and to four respective locking mechanisms located at each edge of the panel. The driver element moves the actuating arms between first and second positions to move the locking mechanisms between a locking position to fasten the cover to the structure and an unlocking position.

Abstract: Apparatus for providing privacy for seated airplane passengers also serves to provide support for passengers walking about the airplane cabin. In a first embodiment, the apparatus is positioned behind and adjacent to the seat. The apparatus includes a side wall that is aligned with the side of the seat along the cabin aisle, and a pedestal that is perpendicular to the aisle and which is mounted to the cabin floor. In a second embodiment, the apparatus includes a rear wall that is mounted to the pedestal in a manner perpendicular to the side wall and that is integrally connected to the side wall.

Abstract: A jet engine has a noise reduction system which reduces the boundary layer located on the outer surface of the nacelle. The noise reduction system includes a plurality of openings located in the outer surface of the nacelle which are in communication with a source of low pressure. The low pressure causes a reduction in the boundary layer at the openings so that resulting ambient air flow velocity near the nacelle surface is increased. This causes a reduction in the shearing between the secondary and ambient airflows thereby reducing the noise.

Abstract: A leading edge flap system for an airplane includes a flap which is rotated about a single hinge point between (i) a retracted position, (ii) an intermediate extended position for high speed maneuvering, and (iii) a fully extended position for low speed maneuvering. In the high speed intermediate position, there is no slot between the flap and the wing leading edge. This position provides additional lift to improve the airplane's turning performance. On the other hand, in the low speed fully extended position, the flap is rotated a greater amount than in the intermediate extended position. In this position there is a slot between the flap and the fixed leading edge to permit air to flow from the bottom of the flap upward and over the upper surface of the leading edge. This improves the lateral stability of the airplane when in a sideslip during stall conditions.

Abstract: A hinge (50) for a panel (26) allows movement of the panel (26) between a closed position inside a framed opening and an open position away from the opening. In an exemplary embodiment, the hinge (50) is used to attach a fan cowl panel (26) to a jet engine (20). To prevent loading the hinge (56) in an axial direction when the panel (26) is in the closed position, the panel (26) is movable axially along the hinge line (66). In the past this has resulted in the fan cowl panel (26) being misaligned during closure between the inlet cowl panel (22) and the thrust reverser cowl panel (24) resulting in damage to the fan cowl panel (26) and surrounding structure. The hinge (50) of the present invention automatically aligns a V-blade (38) of the fan cowl panel (26) with a V-groove (40) of the inlet cowl panel (22) during closure of the fan cowl panel (56) in order to overcome this misalignment problem.

Abstract: A nose landing gear assembly for an airplane which can be launched with catapult assistance. The landing gear assembly includes a nose strut, upper drag link, lower drag link, launch bar and launch bar actuator. When the nose shut is in the extended position, the upper drag link, lower drag link and launch bar form a direct load path between the catapult shuttle and the airplane thereby avoiding subjecting the nose strut to loads reacted from the shuttle. The nose strut, launch bar, launch bar actuator and airplane fuselage form a first four bar linkage. Furthermore, the nose strut, upper drag link, lower drag link and airplane fuselage form a second four bar linkage such that during retraction of the nose strut, the launch bar, launch bar linkage, upper drag link and lower drag link are caused to move up and into the airplane wheel well.

Abstract: Apparatus for assembling fasteners includes a fastening wrench operated by a first operator and having interchangeable sockets of different sizes for engaging nuts of different sizes. The nuts are required to be tightened to different torque values on their respective bolts. When the first operator removes a socket from a socket tray in preparation for attaching the socket to the fastening wrench, a signal is sent to a controller which determines the torque value associated with that socket size. When the fastening wrench reaches the specified torque value during the tightening operation, the controller automatically shuts the fastening wrench off. The apparatus also includes a second wrench, operated by a second operator, for engaging the heads of the bolts to prevent them from turning during the tightening process. During the tightening process the second operator may not be in communication with the first operator.

Abstract: Noise attenuating linings for a turbofan engine inlet are installed around the upper crown area and/or around the lower lip. The acoustical lining at the upper crown area attenuates those fan noise emissions which are normally reflected from the crown area downward toward the ground. The acoustical lining at the lower inlet lip attenuates those fan noise emissions which travel along the inner surface of the lip and are diffracted around the lower lip downward toward the ground.

Abstract: An electrically conductive bridge is formed over a non conductive joint between two or more adjacent electrically conductive panels. The bridge provides a continuous conductive path between the panels. In an exemplary embodiment, the panels form part of a shield against electromagnetic and/or lightning strike energy. The bridge is formed by taping an expanded conductive mesh over exposed conductive portions of the panels and applying an epoxy adhesive. During a following cure cycle, vacuum compression is applied. The expanded mesh of the bridge has an out-of-plane cross sectional configuration which remains in contact with the panel conductive portions during cure so that when the adhesive has cured, the bridge mesh and the panel conductive portions are held in contact with each other.

Abstract: A mechanical lock for an airplane engine thrust reverser is connected to an actuator for the thrust reverser sleeve. The mechnical lock includes an electrically operated solenoid which moves a locking pin between an unlocked position and a locked position. When the pin is in the locked position, it engages a toothed wheel which is mounted about a shaft which engages a drive gear for the thrust reverser actuator. In this manner, movement of the thrust reverser sleeve is prevented until commanded operation of the thrust reverser whereby the locking pin is moved to the unlocked position.

Abstract: A method of modifying human behavior using automatically generated active signals to elicit post-hypnotic suggestions. When a patient is in a hypnotic state, a post-hypnotic suggestion is linked to the active signal. After the hypnotic state has been terminated, the active signal is automatically generated by an appropriate active device in the patient's environ. In this manner, the suggested behavior is reliably elicited without the need for patient intervention.

Abstract: A device for changing the direction of airflow inside a duct includes a curved panel portion with a leading edge and a trailing edge. The leading edge includes a spanwise extending rounded element which eliminates turbulent separation resulting from the change in airflow direction.

Abstract: A device for supporting wire bundles which pass through an opening of a structural element such as the tracks of an airplane slat. The device includes an inside spacer element which both supports and spaces apart the individual wire bundles. The spacer is supported within a hollow split bolt which is formed by two half cylinders which are held together by detachable connectors as well as by a split locking nut which is screwed onto a threaded end of the split bolt. The nut is also formed by the joining of two half nuts which are held together by detachable connectors. In this manner, the supporter can be installed around wire bundles which are already in place through the structure opening.

Abstract: An emergency escape slide for a commercial passenger airplane includes a girt bar which connects the slide to the airplane. The girt bar includes a middle portion having a rectangular cross section to which the slide is connected, and cylindrical end fittings which are attached to opposite ends of the middle portion. When the escape slide is armed, the cylindrical end fittings are positioned within floor mounted receptacles which permit the end fittings to rotate. Thus, when the escape slide is deployed, the girt bar is permitted to rotate so that the wide axis of the girt bar remains aligned with the loads generated by the slide deployment. In this manner, the strongest portion of the girt bar is in position to react the loads.

Abstract: A controller for reducing unwanted sideways motion of an aircraft by reducing lateral side loads, resulting from air mass, turbulence and gusts. The controller functions in a manner that in the presence of higher frequency side loads, the rudder is caused to move in a relieving direction so that the net force across the vertical stabilizer is reduced. A pressure differential across opposite sides of the vertical stabilizer is measured and used to generate a first rudder deflection signal. To maintain stability of the aircraft, a beta-dot signal from the yaw damper module is gain adjusted and filtered to generate a second rudder deflection signal which is added to the first rudder deflection signal. The resulting combined signal reduces lateral side loads at higher frequencies without comprising aircraft directional stability.

Abstract: An airplane, such as a supersonic airplane, includes at least one viewing tunnel located behind the cockpit instrument panel for allowing the pilot to see in front of and to the side of the airplane during low speed flight. The viewing tunnel is especially useful during landing approaches and touchdown when the airplane's high angle of attack and long nose prevents the pilot from seeing the landing environment through the conventional forward cockpit windows. The viewing tunnel allows the pilot to see through a large opening in the bottom and sides of the airplane. This opening is covered by canards during high speed flight and uncovered during low speed flight when the canards are moved to the extended position to provide additional control authority for the airplane.

Abstract: Water Repellent compositions including a silico-titanium polymer, a cationic, surface-active quaternary ammonium compound, and a spreading agent which provides odor detection properties.

Abstract: A sensor which is installed in a waste tank to determine when the tank is full includes a shroud having a body with a curved surface and a leading edge which is mounted flushly to the inner surface of the tank wall and a trailing edge which is spaced apart from the sensor face. As waste material is swirled about the inside surface of the tank wall, the shroud causes the waste material to be transported above the sensor face without disrupting the flow of the waste material along the tank wall. The cover is sized and configured appropriately to allow convenient rinsing when the waste tank is emptied.

Abstract: A throttle controller includes a manual mode where engine output is a function of throttle lever angle, and an alternatively selectable Speed Hold/Thrust Hold mode which is initiated when the throttle is placed in a center Hold position. Throttle operation during the Speed Hold mode is governed by (i) a selected speed entered at a mode control panel, or (ii) a speed existing when the lever was placed in the Hold detent, given that no speed is entered and selected at that mode control panel or (iii) a selected speed/thrust designated in a flight plan entered into the aircraft's flight management computer. During the Thrust Hold mode, the throttle controller maintains the level of thrust which existed when the throttle lever was placed in the Hold detent. When out of the Hold detent, the controller operates to control output thrust as a function of Throttle Lever Angle (TLA).

Abstract: A tester simulates high energy pulses typically present at the inputs to an avionics device after an aircraft carrying the avionics device has been struck by lightning. The tester is used to assist in determining whether the avionics device is sufficiently protected against the effects of a lightning strike on the aircraft. The tester includes a trigger circuit for generating trigger signals at fixed or random intervals so that the pulses which make up each burst as well as the bursts themselves are generated at fixed or random intervals. A number of individual pulse generating circuits are provided to generate high energy pulses which are output to the avionics device under test. A sequencing circuit feeds the trigger signals to the pulse generating circuits so as to generate the high energy pulses and bursts at the selected fixed or random intervals.