Abstract: A method of protecting an aircraft undercarriage (1) while it is being towed by means of a tow bar (13) hitched to a steerable bottom portion of the undercarriage, the method including the step of generating an alarm when a towing force imposed by the tow bar on the undercarriage reaches or exceeds a predetermined force threshold. The threshold is caused to vary as a function of an orientation of the steerable bottom portion of the undercarriage.

Abstract: The invention relates to a new method and system for health monitoring of aircraft landing gear. The system includes sensors that are attached to the landing gear structure and equipment (e.g., one or more of brakes, tires, hydraulics, electrical systems and switches) and analyzed to report and alert personnel such as pilots, maintenance personnel, airline operators, ground crew and regulatory authorities of the health of the landing gear and the potential need for service, maintenance or replacement. The system monitors and reports critical health issues as real-time information which can be analyzed in conjunction with an extensive database of information and used to alert pilots or other relevant personnel to the condition of the landing gear and actions that may be required as a result.

Abstract: The present invention provides a structural deflection and load measuring device for mounting on an axle. The device includes at least one light beam emitting device connected to the axle and able to emit at least one light beam and at least one light position sensing device connected to the axle. The sensing device is located relative to the light beam emitting device for receiving at least one light beam from the light beam emitting device thereon and is operable to calculate the position of the light beam received on its surface.

Abstract: The invention relates to a new method and system for health monitoring of aircraft landing gear. The system includes sensors that are attached to the landing gear structure and equipment (e.g., one or more of brakes, tires, hydraulics, electrical systems and switches) and analyzed to report and alert personnel such as pilots, maintenance personnel, airline operators, ground crew and regulatory authorities of the health of the landing gear and the potential need for service, maintenance or replacement. The system monitors and reports critical health issues as real-time information which can be analyzed in conjunction with an extensive database of information and used to alert pilots or other relevant personnel to the condition of the landing gear and actions that may be required as a result.

Abstract: The invention provides a multifunction electromechanical device for an aircraft undercarriage, the device comprising at least: a first shaft (10) mounted to rotate on the aircraft about an axis of rotation (R) that is substantially parallel to a hinge axis (X) of the undercarriage relative to the aircraft; a telescopic second shaft (20) mounted to rotate on the undercarriage extending down therealong to the proximity of the wheels carried thereby; transmission means (19) for transmitting rotary motion from the first shaft to the second shaft; transmission means (21) for transmitting rotary motion from the second shaft to at least one wheel carried by the undercarriage; if the wheel is not fitted with a brake, specific brake means (30) for braking one of the shafts relative to the undercarriage; and motor means (11, 15) for causing the first shaft to rotate.

Abstract: The present invention provides a structural deflection and load measuring device for mounting on an axle. The device includes at least one light beam emitting device connected to the axle and able to emit at least one light beam and at least one light position sensing device connected to the axle. The sensing device is located relative to the light beam emitting device for receiving at least one light beam from the light beam emitting device thereon and is operable to calculate the position of the light beam received on its surface.

Abstract: The invention relates to an electrohydraulic actuator comprising a body (1) that defines a cylindrical cavity (2) in which a piston (3) slides in leaktight manner and divides an inside volume of the cavity into two chambers (A, B) of variable volume, the piston being associated with at least one rod (4) passing in leaktight manner through an end wall of the cavity, the actuator including a bidirectional pump (5) having two ports (P1, P2), each connected to one of the chambers, an electric motor (8) for selectively driving the pump in one direction or the other, the pump being placed inside the piston of the actuator so as to move together therewith.

Abstract: An uplock assembly for retaining and releasing landing gear systems, said uplock assembly comprising: a thermal actuator comprising: a chamber configured to contain expansible material therein; a heating mechanism coupled to said chamber for heating said expansible material and causing volumetric expansion thereof; a piston slidably coupled to said chamber and adapted to extend in response to said volumetric expansion; and an uplock release mechanism releasably engaged by said piston when extended such that said engaged uplock release mechanism causes the release of said landing gear.

Abstract: The present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. A charging valve is modified by integrating a small pressure sensing device into the stem of the part such that the active diaphragm is subjected to the pressure within the charged vessel. The wires from the pressure sensing device are connected to a receptacle or connector in the bore of the stem such that a corresponding electrical receptacle may be mated for the purposes of making a measurement. The internal receptacle is designed such that the flow of air or oil is not excessively impeded and normal servicing tools do not interfere with the receptacle.

Abstract: This invention provides a pin assembly that is self-lubricating and includes a pin, a pin insert that is received within the pin and a quantity of lubricating agent. The present invention also provides an insert for a pin that may be used in a pin joint that contains an automatic lubrication dispensing mechanism.

Abstract: This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation.

Abstract: Apparatus for monitoring a parameter associated with a structural component comprises a module (1) which is attachable to the structural component and which is associated with a sensor (2) for making measurements of said parameter. The module incorporates a power supply (7) for powering the apparatus; a memory (4) for storing data from the sensor, and a processor (3) to process measurement signals from the sensor (2) and to store data in said memory (4). A display (5) for displaying measurements made by the sensor (2) may also be provided. The processor may make use of an algorithm such as a rainflow counting algorithm to reduce data stored. For energy saving, the sensor (2) is only powered on as required to take a measurement. The sensor (3) is interfaced to the processor through a signal processing subsystem (6) consisting of an amplifier and A to D converter, and each is turned on and off as required to power the sensor (2) for measuring.

Abstract: The present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. A charging valve is modified by integrating a small pressure sensing device into the stem of the part such that the active diaphragm is subjected to the pressure within the charged vessel. The wires from the pressure sensing device are connected to a receptacle or connector in the bore of the stem such that a corresponding electrical receptacle may be mated for the purposes of making a measurement. The internal receptacle is designed such that the flow of air or oil is not excessively impeded and normal servicing tools do not interfere with the receptacle.

Abstract: This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation.

Abstract: The present invention provides a lock sensor for use in an actuator such as is used in aircraft landing gear systems. The lock sensor comprises at least one field emitting device (46) mounted on a locking actuator pressure vessel where the field emitting device (46) monitors the position of at least one target (48). The field emitting device (46) emits a field that when breached by the target sends a signal to indicate that the actuator is in a locked state.

Abstract: This invention provides a pin assembly that is self-lubricating and includes a pin, a pin insert that is received within the pin and a quantity of lubricating agent. The present invention also provides an insert for a pin that may be used in a pin joint that contains an automatic lubrication dispensing mechanism.

Abstract: A wakeboard binding plate assembly includes a disc and ring. The disc is sized to fit within the opening of the ring, with each of the disc and ring including irregular surfaces, respectively positioned to engage each other. The disc is mounted to a portion of a boot assembly of the wakeboard. The ring is adapted to be fastened to a wakeboard, with the disc held in place between the disc and a boot assembly for the wakeboard, engagement between the irregular surfaces of the disc and the ring preventing rotation of the disc. Loosening the ring allows the disc to rotate so that the boot assembly can be easily moved to a desired alignment.

Abstract: A wakeboard binding plate assembly includes a disc and ring. The disc is sized to fit within the opening of the ring, with each of the disc and ring including irregular surfaces, respectively positioned to engage each other. The disc is mounted to a portion of a boot assembly of the wakeboard. The ring is adapted to be fastened to a wakeboard, with the disc held in place between the disc and a boot assembly for the wakeboard, engagement between the irregular surfaces of the disc and the ring preventing rotation of the disc. Loosening the ring allows the disc to rotate so that the boot assembly can be easily moved to a desired alignment.