Abstract: An air turbine starter is provided that includes a check valve assembly. The check valve assembly comprises a valve body, a valve seat and a valve element. The valve body includes an inlet port, an outlet port, and a flow passage extending therebetween. The valve seat is coupled to the valve body, extends at least partially into the flow passage and has an opening therethrough. The valve element is disposed within the flow passage between the valve seat and the valve body outlet port. The valve element is also configured to translate axially between an open position and a closed position in response to a pressure differential between the inlet and outlet ports.

Abstract: A thrust reverser system actuator assembly is provided that includes a torque limiter to limit the number of torque that may be applied to the actuator assembly. The actuator assembly includes an actuator and a torque limiter assembly. The actuator is adapted to receive a drive force and is configured, in response to receipt of the drive force, to move between a stowed position and a deployed position. The torque limiter assembly is coupled to an end of the actuator and is configured to limit torque applied to the actuator assembly upon a torque magnitude being reached in at least the actuator.

Abstract: A fluidic diverter valve for use in flight control systems that includes a non-spherical shuttle element disposed within a cavity formed in the valve housing. In one embodiment, the shuttle element has a disc-shaped main body with first and second sides that are substantially flat and extend substantially parallel to one another, and a substantially symmetrically shaped peripheral section located between the first and second sides.

Abstract: An electro-hydraulic thrust reverser lock actuation system includes a hydraulic fluid source and a lock actuator assembly that is configured to selectively pressurize the hydraulic fluid. The lock actuator assembly is adapted to receive a lock control signal and, in response, pressurize the hydraulic fluid in the hydraulic fluid source. One or more lock assemblies are in fluid communication with the hydraulic fluid source and are configured, in response to the hydraulic fluid pressurization, to move to one of a locked or an unlocked position.

Abstract: A thrust reverser system that includes a pass-through torque activated brake assembly that limits the torque applied in portions of the thrust reverser system drive train. The brake assembly includes two plates that are coupled together with a torsion spring. When a predetermined torque is applied to the torsion spring, the torsion spring displaces the plates from one another. Balls that are positioned in cammed grooves in each of the plates causes the plates to translate away from one another and contact brake surfaces to thereby limit the torque in the drive train.

Abstract: An electro-hydraulic thrust reverser lock actuation system includes a hydraulic fluid source and a lock actuator assembly that is configured to selectively pressurize the hydraulic fluid. The lock actuator assembly is adapted to receive a lock control signal and, in response, pressurize the hydraulic fluid in the hydraulic fluid source. One or more lock assemblies are in fluid communication with the hydraulic fluid source and are configured, in response to the hydraulic fluid pressurization, to move to one of a locked or an unlocked position.

Abstract: An aircraft thrust reverser system that includes a power drive unit operable to supply a drive force. The power drive unit includes a motor and a torque decoupler that sequentially decouples the power drive unit from a plurality of loads. The torque decoupler includes at least two output sections, each of which is coupled to the motor, and are not coupled to one another under normal operating circumstances. The output sections are each operable to decouple the motor from associated thrust reverser moveable components upon a torque magnitude being reached in the output section. The torque decoupler is configured so that the first and second output sections are coupled together a deadband time period after the torque magnitude is reached in on of the output sections.

Abstract: An aircraft thrust reverser system that includes a power drive unit operable to supply a drive force. The power drive unit includes a motor and a torque decoupler that sequentially decouples the power drive unit from a plurality of loads. The torque decoupler includes at least two output sections, each of which is coupled to the motor, and are not coupled to one another under normal operating circumstances. The output sections are each operable to decouple the motor from associated thrust reverser moveable components upon a torque magnitude being reached in the output section. The torque decoupler is configured so that the first and second output sections are coupled together a deadband time period after the torque magnitude is reached in on of the output sections.

Abstract: A thrust reverser system includes one or more actuators each having a locking mechanism that prevents unintended actuator movement, and thus unintended thrust reverser movement. Each of the actuators additionally includes a lock inhibitor assembly that engages the lock and prevents it from moving to its locked position until the actuator is moved into a stow position. Upon movement to the stow position, the lock inhibitor assembly disengages the lock, and the lock automatically moves into its locked position.

Abstract: A fluidic diverter valve for use in flight control systems that includes a non-spherical shuttle element disposed within a cavity formed in the valve housing. In one embodiment, the shuttle element has a disc-shaped main body with first and second sides that are substantially flat and extend substantially parallel to one another, and a substantially symmetrically shaped peripheral section located between the first and second sides.

Abstract: A thrust reverser system that includes a pass-through torque activated brake assembly that limits the torque applied in portions of the thrust reverser system drive train. The brake assembly includes two plates that are coupled together with a torsion spring. When a predetermined torque is applied to the torsion spring, the torsion spring displaces the plates from one another. Balls that are positioned in cammed grooves in each of the plates causes the plates to translate away from one another and contact brake surfaces to thereby limit the torque in the drive train.

Abstract: A front wheel of a scooter is pivotally mounted to a frame and includes an upwardly extending shaft supporting a handlebar for steering the scooter. A footpad or peg or pedal, mounted on a spring returned lever, is interconnected with the rear wheel through a gear mechanism supported by the frame. By pumping the footpad, rotation of the rear wheel and forward motion of the scooter occurs. The gear mechanism includes a first gear or sprocket mounted for rotation about the arms of rotation of the rear wheel. A further sprocket coaxially mounted is linked via a drive-chain to a sprocket on an offset shaft. A further sprocket on the offset shaft drives a final, drive sprocket via a further chain. And the final sprocket drives the rear wheel through a one way clutch. Depression of the footpad, peg or pedal moves a rack-like bar longitudinally. The bar is in engagement with and drives the first gear or sprocket. The bar may carry drive-chain cross-members or pins that engage the teeth of the first sprocket.

Abstract: A thrust reverser system that includes a pass-through torque activated brake assembly that limits the torque applied in portions of the thrust reverser system drive train. The brake assembly includes two plates that are coupled together with a torsion spring. When a predetermined torque is applied to the torsion spring, the torsion spring displaces the plates from one another. Balls that are positioned in cammed grooves in each of the plates causes the plates to translate away from one another and contact brake surfaces to thereby limit the torque in the drive train.

Abstract: A multi-stage pilot valve is disclosed for selectively supplying a working fluid to and venting from a reaction jet main stage actuation chamber. In a preferred embodiment of the invention, the pilot valve comprises a solenoid actuated ball and socket flapper valve having a pressure inlet, an exhaust outlet and a service port. The first stage service port is in fluid communication with a second stage actuation chamber. A piston disposed in the second stage actuation chamber operatively engages a ball member of a ball-and-seat type valve comprising the second stage valve. The second stage valve also comprises a pressure inlet, an exhaust outlet and a service port. The piston and ball are sized relative to each other such that when the second stage actuation chamber is pressurized by the first stage, the force is sufficient to seat the ball against the second stage pressure inlet.

Abstract: A front wheel of a scooter is pivotally mounted to a frame and includes an upwardly extending shaft supporting a handlebar for steering the scooter. The fore and aft position of the handlebar may be adjustable for comfort to the rider. A pivotally mounted spring returned lever is interconnected with the rear wheel through a gear mechanism supported by the frame. A gear shift mechanism may be incorporated. By pumping the lever, rotation of the rear wheel and forward motion of the scooter occurs.

Abstract: A thrust reverser system includes one or more actuators each having a locking mechanism that prevents unintended actuator movement, and thus unintended thrust reverser movement. Each of the actuators additionally includes a lock inhibitor assembly that engages the lock and prevents it from moving to its locked position until the actuator is moved into a stow position. Upon movement to the stow position, the lock inhibitor assembly disengages the lock, and the lock automatically moves into its locked position.

Abstract: A front wheel of a scooter is pivotally mounted to a frame and includes an upwardly extending shaft supporting a handlebar for steering the scooter. A footpad or peg, mounted on a spring returned lever, is interconnected with the rear wheel through a gear mechanism supported by the frame. By pumping the footpad or peg, rotation of the rear wheel and forward motion of the scooter occurs.