B/E Aerospace Patente

A foldable table comprising: a main table plate (1); an ancillary table plate (2); a folding mechanism (10, 11, 12, 13) pivotally connecting the main table plate and the ancillary table plate together, the folding mechanism comprising a pair of side mountings (10), one on each side of the table, and an arrangement of pivot arms (11, 12, 13) configured such that movement of the main table plate in an opening direction (D) relative to the side mountings causes a corresponding and substantially parallel opening of the ancillary table plate (2).

A mounting fitting for removably mounting an object to a surface, the mounting fitting comprising a first portion (11) configured to be attached to the object, in use, and a second portion (12) configured to be attached to the surface, in use, and further comprising a locking and release mechanism (13) configured to releasably lock the first portion relative to the second portion, the locking and release mechanism comprising one or more pins (111) extending radially from the first portion (11), a rotational knob (130) located between the first portion (11) and the second portion (12) via a pre-loaded spring (135) and having defined therein a corresponding one or more L-shaped grooves (133) configured to lockingly receive the one or more pins in the one or more grooves when the knob is in a first rotational position, the rotational knob (130) being rotatable relative to first and second fitting portions (11, 12) to a second rotational position in which the one or more pins can be removed axially from the one or more grooves to remove the first fitting portion (11) from the second fitting portion (12).

An armrest locking mechanism comprising: an axle (20) defining an axis (A) therethrough, an armrest structure (10) mounted relative to the axle to be rotatable relative to the axle about the axis between an open position and a stowed position, a locking mechanism mounted within the armrest structure for releasably locking the armrest relative to the axle in one or both of the open position and the stowed position, the locking mechanism comprising: a lever (32) and a pivot point (P) between the first end and the second end, an actuation member (30) extending out of the armrest structure and in engagement with the first end of the lever, and means for providing locking engagement between the second end of the lever and the axle, and a biasing component (34) arranged to bias the first end of the lever in a second axial direction such that the second end of the lever is biased in an opposite first axial direction into engagement with the axle.

A passenger seat (102) for an aircraft, comprising a seat frame (104), a seatback (106), a seat cushion (108) pivotally connected to the seatback or seat frame, a support leg (110) pivotally connected to the seat cushion and configured, in a first position, to contact the cabin floor and support the seat cushion in a substantially horizontal orientation and an actuation mechanism (214) configured to cause the support leg to pivot with respect to the seat cushion, into a second position, out of contact with the cabin floor such that the support leg no longer supports the seat cushion substantially horizontally and the seat cushion pivots with respect to the seatback and/or seat frame down towards the cabin floor due to gravity.

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A descaling module is disclosed. In one or more embodiments, the descaling module includes a container (201) configured to receive a descaling fluid. The descaling module further includes at least one input port (204) and at least one output port (206). The input port is configured to couple the container to a respective brew head of the beverage maker. The output port is configured to flow the descaling fluid through a fluid path of the beverage maker when pressurized fluid enters the container through the input port and forces the descaling fluid through the output port.

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An integrated seat assembly including a fixed subassembly (108) attachable to a seat backrest (106), a headrest subassembly (110) translatably mounted to a rail (132) of the fixed subassembly, and a neck support subassembly (112) independently translatably mounted to the rail (132). Each of the headrest subassembly (110) and the neck support subassembly (112) includes independently articulating supports configured to enhance support of comfort of the respective subassemblies. Each of the headrest subassembly (110) and the neck support subassembly (112) may include a cushion for further comfort.

An aircraft cabin equipment system (2) is provided. The aircraft cabin equipment system (2) comprises a light fitting (4) for illuminating an aircraft cabin by emitting visible light. The light fitting (4) is configured to broadcast a time signal by modulating an intensity of the emitted visible light. The aircraft cabin equipment system (2) comprises an aircraft cabin device (6, 8, 10) configured to detect visible light emitted by the light fitting (4) and to determine the time signal from the detected visible light.

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A gasper module for use in an aircraft. The gasper module including an inlet (340) configured to receive intake air and a first outlet (95) configured to direct a stream of an airflow from the intake air towards a passenger. Also, a second outlet (92) configured to form an air curtain from the intake air between the passenger receiving the direct stream of airflow and an adjacent passenger.

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There is provided herein an aircraft galley container (2A) including an enclosure housing (4A), a door (6A), an electronically controlled lock (12A) and a control system (16A, 18A). The enclosure housing (4A) defines a cavity within the enclosure housing (4A; 4B; 4C). The door (6A) is moveable between an open position and a closed position. In the closed position, the door (6A) closes and seals the cavity. Control system (16A, 18A) is configured to selectably place the electronically controlled lock (12A) in a locked mode and an unlocked mode, wherein in the locked mode, the door (6A) is prohibited from opening and in the unlocked mode, the door (6A) is able to open. An aircraft galley system is also provided.

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A headrest assembly for a seat, such as an aircraft pilot seat, including a headrest (202) and a headrest tilt mechanism (100). The tilt mechanism includes a headrest support (102), a casing (112) fixed to the headrest support defining a rotation limiter feature (122) determining a full aft headrest position and a full forward headrest position, a driven gear (114) rotatably disposed in the casing, a driver gear (116) rotatably disposed through an axial opening formed though the driven gear, an engaging feature for urging against the headrest, and an actuator for rotating the driver gear. The driven gear and the driver gear have a predetermined gear tooth reduction ratio and a predetermined axial shift distance such that the two gears are arranged in a profile shifted configuration.

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A passenger seat assembly (100) including features for mitigating privacy and use concerns that accompany backrest recline. In embodiments, the assembly (100) includes a seat frame (104), a seat pan (108) coupled to the seat frame, a backrest (110) coupled to the seat frame, a backrest extension (112) movably coupled to the backrest (110) and configured to move between a retracted position within the backrest (110) and an extended position above a top of the backrest (110), and a monitor (114) rotatably mounted to the backrest extension (112) and movable with the backrest extension (112). In use, backrest extension (112) motion and/or monitor (114) rotation may be coordinated with backrest (110) rotation such that motions occurs synchronously.

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A touchless faucet may comprise a faucet housing (112) and an electrically controlled valve assembly located in the faucet housing (112). The electrically controlled valve assembly may be configured to control a flow of fluid to a primary outlet (160) of the faucet housing (112). A manual actuation assembly (190) may be located in the faucet housing (112). The manual actuation assembly (190) may be configured to control the flow of fluid to a secondary outlet of the faucet housing (112).

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A liquid level sensing system (220) for a galley insert appliance (210) in an aircraft galley insert (200) is arranged to alter the angle and/or position of a liquid level sensor (221) in response to an input from a gyroscopic sensor (216). The liquid level sensor (221) is arranged to emit a signal towards the surface (212) of a liquid (211) in the galley insert appliance (210) and to detect the reflection of the signal from the surface (211) for evaluation of the liquid level.