Messier-bugatti-dowty

Safran Landing Systems Canada, Inc.

Messier-dowty Inc.

Gary Ataman

A fuse pin valve includes a housing, a piston, and a mechanical fuse, such as a fuse pin. As assembled, the piston is movably disposed in the housing and is retained in a static position by the fuse pin. Upon a certain pressure (e.g., an abnormal pressure) acting on the piston, the fuse pin fails, thereby releasing the piston to move from a first or start position to second or end position. In the start position of the piston, the valve is in a first operational state (e.g., a closed state). In the end position of the piston, the valve is in a second operational state (e.g., an open state, fully open states, etc.). In other embodiments, in the start position of the piston the valve is in an open state, and in the end position of the piston the valve is in a closed state.

Fuse pin valve

Control system () comprising a control rod () extending between a first zone () situated in a hydraulic chamber delimited by a chamber wall () and a second zone () situated outside the hydraulic chamber. The control system () further comprising a seal () arranged around and against this control rod () to oppose the passage of fluid between the first and second zones (). The system further comprises a guide piece () assembled removably with respect to the chamber wall (), the seal () is assembled inside the guide piece () so as to allow relative movement of the rod () with respect to the guide piece () while at the same time achieving sealing between the first and second zones ().

Control system comprising a control rod

A sensor () having a housing () defining an internal volume (), a movable part (), a detector () for detecting movement of the movable part (), a transfer mechanism () passing through a first opening () of the housing () to control movement of the movable part () from a first external zone (), and a first sealing structure () for opposing the passage of fluid coming from the first external zone () towards said internal volume (). The housing () includes a second opening () extending between the internal volume () and a second external zone (); and a second sealing structure () between the internal volume () and the second external zone (), the second sealing structure being adapted to break so as to allow fluid to pass as soon as a first predetermined pressure difference is exceeded.

Proximity sensor for aircraft and having a hydraulic fuse

A linear telescopic actuator () that comprises a cylinder (), a sliding part (), a spring seat () and a first compression spring () capable of resiliently opposing the sliding part () approaching the spring seat (). The spring seat () presents an outer annular groove () and the cylinder () includes an inner annular groove (). The actuator () also presents a blocking part (), the actuator () being adapted to adopt selectively an assembled configuration and a disassembled configuration. The blocking part () in the assembled configuration is engaged inside the inner and outer annular grooves (). The blocking part () in the disassembled configuration being disengaged from one of the grooves so as to allow spring seat () to slide in the cylinder ().

Linear telescopic actuator

A sensor () comprising a casing () delimiting an internal volume () and having a passage () between the internal volume and a first external zone (Z) external to the casing; a moving part () moveable inside the internal volume (); detector () for detecting a movement of the moving part () comprising a detection portion () extending in the passage () and having a groove () open to the outside of the detection portion (), the groove () extending between the first external zone (Z) external to the casing and the internal volume () internal to the casing. The sensor () comprises first sealing structure () positioned around the detection portion () inside the passage (), the first sealing structure () being arranged in such a way as to prevent fluid from passing between the internal volume () and the first external zone (Z) via the groove ().

Proximity sensor for aircraft, provided with a special sealed assembly

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 manual 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.

Growing community of inventors

Whitby, Canada

Gary Ataman