Abstract: A gravity descending and motorized ascending load carrying platform provides easy loading and installation underneath a ceiling. All mechanical and electrical components needed for operation of the platform travel with the platform. The mechanical components enable the platform to descend/ascend parallel to the floor, to hover parallel and over the floor when the platform supporting legs remain stored within its structure, to tilt when the cables on one side of the platform are under zero gravity force while the cables on the other side are still subjected to gravity force, to hover in a tilted position over the floor if the short supporting legs are not in contact with the floor while its long supporting legs are, to rest on its supporting legs whether in a position parallel to the floor or in a position forming a slope with the floor.

Abstract: A thrust reverser nozzle for a gas turbine engine nacelle includes opposite and asymmetrically pivoting first and second doors defining a nacelle aft section, first and second trailing edges of the first and second doors adjacent to a propulsive jet nozzle outlet of the nacelle, the doors being pivotable simultaneously between a stowed position and a deployed position such that the first trailing edge is positioned behind the second trailing edge when the doors are in the deployed position, and the first and second fairings attached to the first and second doors in relative fixed positions to the first and second doors respectively. Male contour middle portions of the first fairings may complementarily match female contour middle portions of the second fairings and are received within the female contour middle portion when the doors are in the stowed position. The fairings may be removably attached to the doors.

Abstract: A pivot arrangement for a thrust reverser door of a gas turbine engine, the pivot fitting having a base and a shaft projecting from a main side of the base. The shaft receives a preferably curved pivot arm of the door to provide a low profile arrangement which improves performance when the doors are stowed.

Abstract: The thrust reverser comprises sections, such as arms and skins, which may be connected along joints to provide a thrust reverser body. A plurality of fittings may be integrally formed on a surface of each arm.

Abstract: A thrust reverser door provides in one aspect a separation of structural and aerodynamic functions through the provision of individual structures. In some embodiments, an aerodynamic element is adjustable in position, while in other embodiments, the relative positions are fixed. An exemplary aerodynamic element extends radially into the reverser flow to redirect the flow away from the door surface.

Abstract: The thrust reverser is used with an aircraft gas turbine engine and includes upper and lower doors pivotable between a stowed position and a deployed position. When deployed, the doors redirect a portion of the efflux to generate a nose-down pitching moment on an aircraft to improve handling during thrust reversing on a runway.

Abstract: A thrust reverser door is provided, in one configuration, with a plurality of peripherally-disposed frames circumferentially spaced apart from one another and projecting radially inwardly on an interior side of the door to thereby provide a channel for redirecting thrust.

Abstract: The thrust reverser includes, in one aspect, an interior flow deflector which defines a portion of a substantially continuous and uninterrupted nozzle interior surface with the interior of a jet pipe when the door is in a stowed position, thereby reducing aerodynamic losses and improving efficiency. In another aspect, improved sealing arrangement between the jet pipe and the door provides increased performance when the doors are stowed.

Abstract: An access panel is shown in the present invention to provide easy and safe access to an attic space or elevated structure. The access panel is fully automatic. During opening, the access panel uses an energizing motor to control the gravitational forces for opening a cover and deploying ladder sections. During closing, the access panel is energized to retract the ladder sections and close the access panel. The motor is energized to close the access panel until a stow latch engages to stow the access panel during non-use. A safety switch is mounted inside the attic space to allow a user to open the panel and extend the ladder should the user be trapped in the attic space.

Abstract: The thrust reverser comprises a first reverser door and a second reverser door asymmetrically pivotable between a stowed position and a deployed position, one having a pivot axis closer to the central axis than the other.

Abstract: A thrust reverser nozzle for a gas turbine engine nacelle includes opposite and asymmetrically pivoting first and second doors defining a nacelle aft section, first and second trailing edges of the first and second doors adjacent to a propulsive jet nozzle outlet of the nacelle, the doors being pivotable simultaneously between a stowed position and a deployed position such that the first trailing edge is positioned behind the second trailing edge when the doors are in the deployed position, and the first and second fairings attached to the first and second doors in relative fixed positions to the first and second doors respectively. Male contour middle portions of the first fairings may complementarily match female contour middle portions of the second fairings and are received within the female contour middle portion when the doors are in the stowed position. The fairings may be removably attached to the doors.

Abstract: An access panel is shown in the present invention to provide easy and safe access to an attic space or elevated structure. The access panel is fully automatic. During opening, the access panel only uses gravitational forces for opening a cover. Only during closing is the access panel motorized. The gravitational forces are used to both open the cover and extend the ladder sections, while the motor is only used to retract the latter sections and close the cover. A stow latch keeps the cover closed during non-use. A safety switch keeps the access panel from accidentally opening and the ladder sections from lowering if the stow latch is released. A mechanical lock keeps the cover open when the ladder sections have been lowered.

Abstract: The thrust reverser is used with a gas turbine engine and includes first and second doors pivotable between a stowed position and a deployed position. When deployed, pivoting fairings on the first door are moved so as to give room to the second door as its trailing edge moves within the first door. When stowed, the second door preferably provides the locking mechanism to the pivoting fairings of the first door.

Abstract: The thrust reverser comprises sections, such as arms and skins, which may be connected along joints to provide a thrust reverser body. A plurality of fittings may be integrally formed on a surface of each arm.

Abstract: The thrust reverser includes, in one aspect, an interior flow deflector which defines a portion of a substantially continuous and uninterrupted nozzle interior surface with the interior of a jet pipe when the door is in a stowed position, thereby reducing aerodynamic losses and improving efficiency. In another aspect, improved sealing arrangement between the jet pipe and the door provides increased performance when the doors are stowed.

Abstract: A thrust reverser door provides in one aspect a separation of structural and aerodynamic functions through the provision of individual structures. In some embodiments, an aerodynamic element is adjustable in position, while in other embodiments, the relative positions are fixed. An exemplary aerodynamic element extends radially into the reverser flow to redirect the flow away from the door surface.

Abstract: The thrust reverser is used with an aircraft gas turbine engine and includes upper and lower doors pivotable between a stowed position and a deployed position. When deployed, the doors redirect a portion of the efflux to generate a nose-down pitching moment on an aircraft to improve handling during thrust reversing on a runway.

Abstract: A pivot arrangement for a thrust reverser door of a gas turbine engine, the pivot fitting having a base and a shaft projecting from a main side of the base. The shaft receives a preferably curved pivot arm of the door to provide a low profile arrangement which improves performance when the doors are stowed.

Abstract: The thrust reverser is used with a gas turbine engine and includes first and second doors pivotable between a stowed position and a deployed position. When deployed, pivoting fairings on the first door are moved so as to give room to the second door as its trailing edge moves within the first door. When stowed, the second door preferably provides the locking mechanism to the pivoting fairings of the first door.

Abstract: A thrust reverser door is provided, in one configuration, with a plurality of peripherally-disposed frames circumferentially spaced apart from one another and projecting radially inwardly on an interior side of the door to thereby provide a channel for redirecting thrust.