MESSIER-DOWTY INC. Patent applications |
Patent application number | Title | Published |
20150377262 | MODULAR ACTUATOR WITH SNUBBING ARRANGEMENT - Described is a modular linear actuator for use in an aerospace application, comprising: a piston housing having a closed end and an open end; a piston rod slideable within an interior of the piston housing between an extended position and a compressed position, the piston rod having a first end proximal to the closed end of the piston housing and a second end distal to the closed end of the piston housing; an attachment mechanism for removably attaching a lug end to the closed end of the piston housing, the lug end for attaching the actuator to a first component; an attachment mechanism for removably attaching a rod end to the second end of the piston rod, the rod end for attaching the piston rod to a second component; and, a piston head removably attached to the first end of the piston rod, the piston head for providing a snubbing engagement with the closed end of the piston housing. | 12-31-2015 |
20140252210 | PROXIMITY SENSOR - A proximity sensor for detecting non-contact detection of a target using a fibre optic strain sensor and a system for operating multiple such proximity sensors is disclosed. The proximity sensor includes an optic fibre that has an optic fibre strain sensor that is coupled to a mass that moves in response to the target. The mass can be a magnet that moves when a ferrous target is within the magnetic field of the magnet causing the magnet to move and apply strain to the optic fibre strain sensor. The optic strain sensor can include periodic variation in the refractive index of the optic fibre, such as a fibre Bragg grating. The proximity sensor can include a second fibre optic sensor that is sensitive to temperature or a second fibre optic strain sensor coupled to a second magnet that operates in opposition to the first magnet. A system coupling multiple proximity sensors can include an interrogator that has an optical power source and a detector, each coupled to a processor. The processor compares frequency information from the proximity sensor to a threshold to determine whether a target is in proximity to its corresponding proximity sensor. | 09-11-2014 |
20140210647 | SWITCH ASSEMBLY AND OVER-STEER DETECTION SYSTEM - A switch assembly is disclosed having a switch with an actuator moveable from an armed position to a disarmed position. A housing is attached to the switch and contains a cam that holds the switch actuator in the armed position. A trigger makes contact with the cam causing it to rotate within the housing and allowing the actuator to extend to move to a disarmed position. In some variants the cam can be shaped to prevent manually rotation against the bias force of the actuator in the disarmed position. The switch assembly can be positioned on an aircraft landing gear to detect an over-steer occurrence where the landing gear may become damaged. The state of the switch can be visibly or audibly indicated by an indicator in the aircraft cockpit or other location visible/audible to the ground operators. | 07-31-2014 |
20140208935 | LOCKING MECHANISM FOR LOCKING AN ACTUATOR - A locking mechanism for locking an actuator piston within an actuator cylinder housing is disclosed. The locking mechanism comprises a locking pin that is moveable between extended and retracted positions. The locking pin can be moved using a controller, such as a hydraulic controller, for example. In the extended position the locking pin engages the actuator piston thereby locking the actuator piston in a specific position. The locking mechanism includes a mechanical bias (such as a spring or other mechanical system) that biases the locking pin towards an extended position to lock the actuator piston when counter-pressure on the locking pin is lower than the pressure provided by the mechanical bias. The locking pin can be hydraulically operated so that hydraulic pressure that forces the actuator piston to retract also exerts force on the locking pin to move it from a locked position to an unlocked position. | 07-31-2014 |
20130207327 | HYDRAULIC SHIMMY DAMPER FOR AIRCRAFT LANDING GEAR - A hydraulic shimmy damper that resolves drawbacks in several known shimmy dampers, such as damping characteristics that are dependent on oil temperature variations. The disclosed shimmy damper includes a hydraulic compensator ( | 08-15-2013 |
20130134000 | LANDING GEAR SHOCK ABSORBER METERING USING PIVOTING JOINT - A metering pin assembly, for use in an aircraft landing gear shock absorber, that is operable to move within the shock absorber, independently of the shock absorber, to respond to movement of the landing gear under subjected load. | 05-30-2013 |
20120292443 | DOUBLE HOOK DOOR MECHANISM - The present invention provides a double hook door mechanism for use in opening and closing aircraft landing gear bay doors. | 11-22-2012 |
20120280564 | ELECTRIC ACCUMULATOR UTILIZING AN ULTRA-CAPACITOR ARRAY - Disclosed is an electric accumulator for selectively operating at least one aircraft device. The electric accumulator includes an ultra-capacitor array for storing electrical energy, which can later be used to power an aircraft device. The stored electrical energy can also be used as a source of emergency backup power. The distribution of the electrical energy is controlled by a power distribution controller. The electric accumulator may be charged by a power source on an aircraft, or it may be pre-charged by an external power source. | 11-08-2012 |
20110154907 | Structural Deflection and Load Measuring Device - 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. | 06-30-2011 |
20110140513 | ELECTRIC ACCUMULATOR UTILIZING AN ULTRA-CAPACITOR ARRAY - Disclosed is an electric accumulator for selectively operating at least one aircraft device. The electric accumulator includes an ultra-capacitor array for storing electrical energy, which can later be used to power an aircraft device. The stored electrical energy can also be used as a source of emergency backup power. The distribution of the electrical energy is controlled by a power distribution controller. The electric accumulator may be charged by a power source on an aircraft, or it may be pre-charged by an external power source. | 06-16-2011 |
20110056197 | LANDING GEAR UPLOCK MECHANISM EMPLOYING THERMAL PHASE-CHANGE ACTUATION - 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. | 03-10-2011 |
20100140395 | DOUBLE HOOK DOOR MECHANISM - The present invention provides a double hook door mechanism for use in opening and closing aircraft landing gear bay doors. | 06-10-2010 |
20100140394 | ROLLER SLOT DOOR MECHANISM - The present invention provides an aircraft landing bay door mechanism that includes the use of a roller slot mechanism for opening and closing the landing bay door. | 06-10-2010 |
20100114411 | SYSTEM AND METHOD FOR DETERMINING AIRCRAFT HARD LANDING EVENTS FROM INERTIAL AND AIRCRAFT REFERENCE FRAME DATA - 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. | 05-06-2010 |
20090293624 | HYDRAULIC/PNEUMATIC CHARGING VALVE WITH INTEGRATED PRESSURE TRANSDUCER - 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. | 12-03-2009 |
20090091476 | LOCK SENSOR FOR AN INTERNALLY LOCKING ACTUATOR - 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 ( | 04-09-2009 |
20080217107 | SELF LUBRICATING PIN ASSEMBLY - 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. | 09-11-2008 |