1120results about "Aircraft accessories" patented technology

A tail rotor system for a helicopter includes a gear box housing retainer (66) coupled to the tail boom (16) of the helicopter. The tail rotor system also includes a power-limiting device (50) configured to disconnect the tail rotor from a power plant for driving the tail rotor about a rotor axis of rotation.

An inertial separator comprising a tubular body, the tubular body comprises a composition comprising a polymer selected from the group consisting of a cyclic olefin polymer and a cyclic olefin copolymer, and, a polyhedral oligomeric silsesquioxane and/or a flame retardant and/or an anti-static additive, is disclosed.

An air induction system for an engine to remove contaminants from intake air prior to delivery to the engine. The system includes an assembly for filtering air which is mounted in advance of the engine, and a duct for delivering air from the assembly to the engine. A sealing system is provided which prevents entry of unfiltered air while simultaneously permitting movement of the engine relative to adjacent parts of the airframe as engine power setting varies. The seal is protected from high pressures in the duct which can occur in operation of the engine.

A lightweight ballistic resistant rigid structural panel especially for use in aircraft interiors is disclosed. The rigid structural panel is made up of a core layer including a plurality of sheets of flexible, high-tensile strength fabric interleaved with a plurality of sheets of a thermal-fusible film adhesive, and a sheet of cushioning material adhered to the plurality of sheets of flexible, high-tensile strength fabric. Fiber-reinforced face skins are adhered to exterior surfaces of the panel core for structural strength and rigidity. The rigid structural panel is capable of resisting ballistic attack from handguns and like weapons, while maintaining a high degree of strength and rigidity.

An air induction system for an engine to remove contaminants from intake air prior to delivery to the engine. The system includes a filtering unit having barrier filter panels attachable to a mounting frame. The filter panels are interchangeably usable. A juncture between first and second filter panels and the mounting frame is located at a region of relatively lower quantity of intake air flow. The juncture includes lugs on the filter panels which facilitate interchangeability. An opening above the filtering unit permits easy installation and removal of filter panels.

An inertial inlet particle separator system for a vehicle engine includes an inertial inlet particle separator and an adjustment mechanism. The separator includes a fluid inlet coupled to a scavenge channel and to a clean channel such that a first amount of fluid passing through the fluid inlet enters the scavenge channel and a second amount of fluid passing through the fluid inlet enters the clean channel. The scavenge channel is defined by a first wall and a splitter, and the clean channel is defined by a second wall and the splitter. The splitter and the second wall are stationary with respect to each other. The adjustment mechanism is coupled to the inertial inlet particle separator and configured to adjust a size of the scavenge channel. Although not necessarily, the adjustment mechanism may also be coupled to the scavenge fan speed.

A particle separator which broadly comprises: an inner wall, an outer wall and a splitter, wherein the inner and outer walls define an air intake passageway, and wherein the splitter is positioned between the inner and outer walls so as to define a scavenge air flow passageway connected to the intake passageway and a main air flow passageway connected to the intake passageway; the inner wall having a humped-shaped portion between the intake passageway and the main air flow passageway; the humped-shaped portion having a peak and a radius of curvature at any point on the hump-shaped portion of the inner wall after the peak corresponding to a degree of curvature of from about 30 to about 60 degrees; and a boundary layer control mechanism for providing active boundary layer control along the inner wall after the peak and within the main air flow passageway. Also provided is a method for providing active boundary layer flow control along the inner wall after the peak and within the main air flow passageway.

The invention belongs to the cabin door mechanism technology of civil aircraft, and relates to a lifting mechanism of an outward opening cabin door. A mounting seat of the lifting mechanism is fixedly connected with the cabin door, one end of a lifting rocker arm is fixedly connected with a handle rotating shaft, the other end is articulated with the upper end of a lifting rod, a rod end joint of the lower end of the lifting rod is articulated with the middle part of an upper lifting arm, one end of the upper lifting arm is arranged in the mounting seat of the lifting mechanism, the other end is articulated with a stop block on a guiding shaft; an outer end of a main hinge is provided with an upper double ear and a lower double ear, the guiding shaft is arranged in through holes of the upper double ear and the lower double ear of the main hinge, and the guide shaft between the upper double ear and the lower double ear is equipped with the stop block, the main hinge is articulated with the cabin door frame, one end of a lower lifting arm is arranged on the mounting seat of the lifting mechanism, the other end is articulated with the stop block on the guiding shaft. The mechanism is simple, has safe and reliable performance, low production and installation cost, and is applicable to cabin doors of the civil aircrafts.

A bird deflector and air replacement system for a jet engine, the bird deflector being conical or arcuate in shape as formed by suitable longitudinal and lateral interconnected bars, and the air replacement apparatus being one of a frustum or a selectively perforated tube or a modified cowl with cooperating external spaced-apart channels or openings formed therearound for directing additional air into the mainstream of the jet engine inlet. The system may be manufactured as an aftermarket add-on, or it may be manufactured as original cowl equipment for respective jet engine models.

A system and method for displaying on a display inside of an aircraft a panoramic view of a view outside the aircraft. The system includes a window plug configured to fit into a window of an aircraft. The window plug includes a camera positioned to capture video outside of the aircraft and a display positioned over the window plug. The camera and display are connected to a processor to display the captured video on the display. The system may include a control panel that controls the operation of the camera and display. A device may be used to control pan and zoom features of the camera. A plurality of cameras may be connected to the processor, which may combine the captured videos from the plurality of cameras to display a single panoramic video on a single display or a plurality of displays. The combined video may be a 3D video.

An adjustable sliding privacy screen for a premium class passenger suite may include a guide rail mounted to a wall partition. The adjustable sliding privacy screen may also include a yaw/roll adjustment bracket slidingly attached to the guide rail and to the screen. The yaw/roll adjustment bracket may include a flanged adjustment screw for adjusting the yaw and roll of the screen and a locking screw for securing the yaw and roll adjustment of the screen. The screen may also include a ball joint adjustment bracket slidingly attached to the guide rail and to the screen. The ball joint adjustment bracket may include a ball joint and adjustment screw for adjusting the pitch of the screen and a locking nut for securing the pitch adjustment of the screen. The device of the present invention thus allows for the adjustment of the yaw, roll, and pitch of the screen.

[Object] To provide a gas turbine engine which is simple in structure but can effectively remove foreign matters from the combustion air.

[Means] The intake passage 21 includes an inlet portion 29, a curved portion 30 and a reduced diameter portion 31. The bypass duct 24 is curved away from the central axial line CL in a region corresponding to the curved portion 30 and reduced diameter portion 31 of the intake passage 29. Between the intake passage 29 and bypass duct 24 is defined an annular space 32. In the reduced diameter portion 31, the outer liner 20 is formed with a large number of foreign matter introduction openings 33 in a circumferential arrangement for communication between the intake passage 21 and annular space 32. The inner casing 4 is formed with a plurality of foreign matter ejection holes 34 in a circumferential arrangement in a part thereof that curves outward for communication between the annular space 32 and bypass duct 24.

An aircraft tail cone comprising a fuselage in which avionic equipment is housed. The tail cone comprises two lateral hatches formed in the fuselage, at least one hatch being formed on each of the two opposite sides of the fuselage. Each hatch is mounted removably with respect to the fuselage so as to take up a closed first position in which the hatch closes a lateral opening in the fuselage, and an open second position in which the open hatch allows access to the inside of the tail cone through the corresponding opening The avionic equipment that requires regular inspection and/or maintenance operations is housed in a part of the tail cone which is accessible through the two lateral openings in the fuselage to a person who remains on the outside of the fuselage.

To attenuate electromagnetic energy, a capacitive bond between a window and a frame is provided by a capacitive coupling. This capacitive coupling includes an elastomeric matrix and a conductive media. The elastomeric matrix provides a seal between the window and the frame. The conductive media is bound to the matrix and conducts electromagnetic energy from the window to the frame.

The invention relates to the field of airliner cabin door linkage structures, and specifically relates to a lifting-opening linkage structure, which is disposed at a half-blocking turn-over airliner cabin door, and is used to control motions such as lifting and opening of the cabin door. The lifting-opening linkage structure specifically comprises: one ends of two upper connection rods are respectively connected with two pedestals; one ends of two arms of a suspension arm are respectively connected with one ends of two bottom connection rods, and the other ends of the two bottom connection rods are hinged to the cabin door; perforated fixing pieces are respectively symmetrically fixedly disposed on the two arms of the suspension arm; the middle parts of two double-arm connection rods are respectively hinged to the perforated fixing pieces, and the two arms of the suspension arm are respectively disposed at the two sides of the perforated fixing pieces; one arms of the two double-arm connection rods are respectively hinged to the other ends of the upper connection rods, and the other arms of the two double-arm connection rods are connected with a square-shaped connection rod, the other side of the square-shaped connection rod is hinged to the cabin door; and a connection rod is connected with the one end of an interior handle and the square-shaped connection rod both in a hinged way. The linkage structure has a compact main mechanism, no spouts and no multiple connection rods, and one set of 'guide groove-guide wheel' mechanism is reduced.