BOMBARDIER INC. Patent applications |
Patent application number | Title | Published |
20160059499 | METHOD FOR PREPARING COMPOSITE STRUCTURES AND CONSUMABLE ASSEMBLY THEREFOR - Methods, a consumable assembly, and a tool for preparing a composite structure from a laminate disposed on a surface of a mold. The method involves preparing consumable materials, such as a breather sheet and a vacuum bag, and preparing an inflatable tool, outside of the mold. These prepared consumable materials and the inflatable tool are then inserted into the mold, and the inflatable tool is inserted into a folded assembly of the breather and vacuum bag. Once inserted into the mold, the inflatable tool is inflated, which deploys the consumable materials against the laminate. A vacuum can be generated, which maintains the deployed consumable materials against the laminate. This can be done for many hours. Finally, the laminate is cured inside the mold so as to form the composite structure. | 03-03-2016 |
20150298816 | CHECKLIST DISPLAY SYSTEM, METHOD AND GRAPHICAL DISPLAY THEREFOR - The present disclosure relates to a check-list display system ( | 10-22-2015 |
20150214709 | CABLE RETAINER DEVICE AND METHOD FOR RETAINING CABLE IN AN AIRCRAFT - A retainer device for a cable used in an aircraft includes a base. A moveable member is movably connected to the base and forms a channel with the base that is adapted to receive a cable. A pad-deforming portion is defined in the moveable member, which is displaceable between an open position in which a portion, of the moveable member is separated from the base to provide access to the channel, and closed positions, in which the moveable member is releasably connected to the base. A resilient pad is located in the pad-deforming portion to contact the cable received in the channel. The resilient pad is sized to deform from a rest state to a deformed state by the pad-deforming portion during insertion thereinto. The resilient pad is held captive after insertion into the pad-deforming portion by reforming toward the rest state. | 07-30-2015 |
20150210373 | DOOR ASSEMBLY FOR AIRCRAFT INTERIOR - Door assemblies for aircraft interiors are described. Such door assemblies may comprise a door for opening and closing an aperture between zones of the aircraft interior and an interface configured to couple the door to the aircraft interior. A pressure-relief element may form at least a portion of the door wherein the pressure-relief element is retained by a magnetic force calibrated to permit release of the pressure-relief element upon presence of a predetermined pressure differential across the pressure-relief element. Components and mechanisms useful in reducing light bleed across doors for aircraft interiors are also disclosed. | 07-30-2015 |
20150151830 | MORPHING WING FOR AN AIRCRAFT - A morphing wing for an aircraft includes a top surface, a bottom surface, a leading edge, a trailing edge, a tip, and a root. A plurality of structural ribs is disposed between the root and tip so that they extend between the top surface and the bottom surface and intersect with a lateral axis thereof. At least one active member connects between two adjacent structural ribs along or at a first angle to the lateral axis. The active member is actively adjustable. At least one passive member connects between the two adjacent structural ribs along or at a second angle to the lateral axis. The passive member is passively adjustable. Adjustment of at least one active member moves the adjacent structural ribs with respect to one another, thereby morphing the wing from a first configuration to a second configuration. | 06-04-2015 |
20150136904 | SEATING ARRANGEMENT CONVERTIBLE TO A BUNK BED - A seating arrangement includes a seat with a seating surface and a top bunk disposed adjacent to the seat. The seat and the top bunk are configurable between a first configuration and a second configuration. In the first configuration, the seat accommodates a user in a seated position and the top bunk is stowed. In the second configuration, the seat and the top bunk form a bunk bed configured to accommodate users in prone positions. In the first configuration, the seating surface is disposed at a first predetermined height. In addition, in the second configuration, the seating surface is disposed at a second predetermined height that is lower than the first predetermined height. | 05-21-2015 |
20150034769 | MECHANISM AND METHOD FOR ARMING/DISARMING THE ACTUATION OF AN EMERGENCY SLIDE - A mechanism for arming and disarming an actuation of an emergency slide retained on a door of an aircraft and selectively configurable between an armed configuration and a disarmed configuration. The mechanism includes at least one transport hook extending radially from the rotating shaft and rotatable therewith about the longitudinal axis of the shaft. The transport hook has interconnected top and bottom portions defining a carrying slot therebetween. In the disarmed configuration, the transport hook receives the girt bar in the carrying slot, such that the transport hook carries the girt bar upon opening of the door. In the armed configuration, the transport hook is pivoted away from the girt bar and oriented such as to move over the girt bar without contact therewith upon opening of the door. | 02-05-2015 |
20150014483 | CONNECTION ASSEMBLY FOR AIRCRAFT DOOR - A connection assembly for an emergency aircraft door. The assembly includes a first pair of non parallel links pivotally attached to the fuselage and a second pair of non parallel links attached to the door. One of the links of the first pair is pivotally connected to both links of the second pair, and one of the links of the second pair is pivotally connected to both links of the first pair. A compact assembly can be achieved. | 01-15-2015 |
20150008707 | AIRCRAFT SEAT - A seat includes a seat pan, having a seat pan front edge and a seat pan rear edge. The seat pan front edge defines a first pivot point and the seat pan rear edge defines a second pivot point. A lumbar cushion, having a lumbar cushion top edge and a lumbar cushion bottom edge, is articulately disposed adjacent to the seat pan rear edge. A backrest, having a backrest top edge and a backrest bottom edge, is articulately disposed adjacent to the lumbar cushion top edge. A headrest, having a headrest top edge and a headrest bottom edge, is articulately disposed adjacent to the backrest top edge. The seat pan, the lumbar cushion, the backrest, and the headrest are positionable with respect to one another such that seat is configurable into at least one of a taxi, takeoff and landing position, a limited recline position, a napping position, and a sleeping position. The first pivot point remains in a substantially fixed position for each of the positions. | 01-08-2015 |
20140091181 | CONTROLLER - A controller includes a first body portion, adapted to be grasped by a person's middle finger, ring finger, and pinky finger, a second body portion adapted to be grasped by a person's index finger, and a third body portion that defines a first surface adapted to receive a person's thumb. A finger switch is positioned on a front surface of the second body portion. The finger switch is positioned such that it may be actuated by the person's index finger. The second body portion is disposed between the first body portion and the third body portion. The second body portion defines an offset with respect to the first body portion. The third body portion defines a second surface above the finger switch, which may receive the person's index finger. | 04-03-2014 |
20140062102 | LATCH - A latch includes a first locking bolt, where a first extended position of the first locking bolt defines a first locked condition and a first retracted position defines a first unlocked condition. The latch also includes a second locking bolt, where a second extended position of the second locking bolt defines a second locked condition and a second retracted position defines a second unlocked condition. A biasing member operatively connects to the first locking bolt to bias the first locking bolt in the first extended position. A lever pivotally connects to the housing and operatively connects to the first locking bolt such that movement of the lever from a closed position to an opened position causes at least the first locking bolt to move from the first extended position to the first retracted position. A locking indicator is provided in associated with the second locking bolt. | 03-06-2014 |
20140060891 | STANDOFF DEVICE AND METHOD OF INSTALLATION OF HARNESS - A device connects a wire harness to a structure. A fixation portion of the device is secured to the structure. A spacing portion is connected to the fixation portion and to a connector portion. A retaining clip on the connector portion deforms when a wire harness connector component moves axially toward the fixation portion. The clip opposes an abutment edge against the component into engagement position when the component is past the clip to prevent it from moving back onto the clip. An abutment surface contacts another portion of the component in engagement position to prevent further axial movement of the component toward the fixation portion. The component is held captive between the edge and the abutment surface. Also provided are a cable support for connecting the wire harness to the device, a method for connecting and disconnecting the wire harness to a structure with the device, and an aircraft. | 03-06-2014 |
20140000279 | SYSTEM AND METHOD FOR OPERATING A PRECOOLER IN AN AIRCRAFT | 01-02-2014 |
20130256456 | AIRCRAFT INTERIOR CONFIGURATION - An aircraft interior configuration includes a first passageway extending along a longitudinal axis of a fuselage of the aircraft and a second passageway extending along the longitudinal axis. A transitional region is disposed between the first passageway and the second passageway. The transitional region extends perpendicularly to the longitudinal axis, between starboard and port sides of the aircraft. The transitional region is configurable from at least a first configuration to at least a second configuration. | 10-03-2013 |
20130197722 | MULTI-AXIS SERIALLY REDUNDANT, SINGLE CHANNEL, MULTI-PATH FLY-BY-WIRE FLIGHT CONTROL SYSTEM - A multi-axis serially redundant, single channel, multi-path fly-by-wire control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands of the primary flight control computer; and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands to control the aircraft in flight in accordance with the control law algorithms implemented in the flight control computers. | 08-01-2013 |
20120261509 | AIRCRAFT LAVATORY FOR A PERSON WITH REDUCED MOBILITY - An aircraft lavatory includes first and third walls extending inwardly from a second wall and a fourth wall connecting the first wall to the third wall. A countertop extends along a portion of the first wall. A sink is disposed in the countertop. The countertop defines an under-countertop recess free from obstructions. A toilet is disposed adjacent to both the second wall and the third wall and defines a toilet axis bisecting the toilet. A door extends along at least a portion of the third wall. An access axis is defined that is disposed at an access angle with respect to the toilet axis. When a person in a wheelchair enters the lavatory area along the access axis, the countertop recess accommodates at least a portion of the person's body. | 10-18-2012 |
20110258769 | SHOWER SYSTEM FOR AIRCRAFT - A shower unit for an aircraft comprises: a shower head, and controls to manually control the water output. A shower enclosure defines a receiving cavity to receive the user. The shower enclosure supports the shower head and the controls for the user to shower in the receiving cavity. The shower enclosure comprises a first door on a first side of the shower enclosure, and a second door on a second side of the shower enclosure to define a passageway through the shower enclosure. The shower unit is adapted to be positioned in the aircraft such that the passageway communicates between two separate zones of the aircraft. | 10-27-2011 |
20110049305 | IMPROVED SLAT CONFIGURATION FOR FIXED-WING AIRCRAFT - A slat for fixed-wing aircraft that includes a leading edge, a trailing edge, a chord, and an inboard edge that includes particular dimensions to affect airflow over the wing. | 03-03-2011 |
20110040430 | INTEGRITY MONITORING OF INERTIAL REFERENCE UNIT - Systems, methods, and machine-executable programming products adapted for the control of aircraft or other vehicles by receiving from at least one Inertial Reference System (IRS), including a plurality of Inertial Reference Units (IRUs), signals representing vehicle state data; receiving from at least one Augmented Direct Mode Sensor (ADMS) signals representing independently-acquired vehicle state data corresponding to at least a subset of the signals received from the IRS; performing signal selection and fault detection processes on the signals received from the at least one IRS and on the corresponding signals received from the ADMS; based at least partly on the signal and fault detection processes, determining whether at least one component of at least one of the IRS and ADMS is in a fault condition; and based on the fault condition, providing to at least one vehicle control system device one or more vehicle control command signals. | 02-17-2011 |