Abstract: A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, an actuator, and a hydraulic assist mechanism. The actuator is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The hydraulic assist mechanism is coupled to the transcowl and is configured to react reverse thrust loads on the transcowl at least when the transcowl is translating between the stowed position and the deployed position.

Abstract: A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, and an actuator. The transcowl is mounted on the support structure and is axially translatable between a stowed position and a deployed position. The actuator is coupled to the transcowl and the support structure, and is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The actuator includes an actuator housing, a screw, a nut, a rod end, and a tension rod. The tension rod is engaged by the nut when the transcowl is in the deployed position and is engaged by the rod end when the transcowl is in the stowed position, whereby actuator loads, in both the deployed and stowed positions, are transmitted through the tension rod to the support structure.

Abstract: A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, a door, a main actuator, and an assist actuator. The transcowl is mounted on the support structure and is axially translatable between a stowed position and a deployed position. The door is pivotally coupled to the support structure and is rotatable between at least a first position and a second position when the transcowl translates between the stowed position and the deployed position, respectively. The main actuator is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The assist actuator is coupled to the door, and is configured to supply an actuation assist force to the door and, upon rotation of the door to an intermediate position between the first position and the second position, to commence load sharing with the main actuator.

Abstract: A thrust reverser control system includes a plurality of actuators, an electric motor, an electric brake, and a control. Each actuator is responsive to an actuator input torque to move between a stowed position and a deployed position. The electric motor is coupled to each of the actuators and is configured, upon being energized from a voltage source having a supply voltage magnitude, to supply the actuator input torque to the actuators and further configured to selectively generate regenerative current. The electric brake is coupled to be selectively supplied with the regenerative current and is configured, upon being supplied with the regenerative current, to supply a braking torque that slows movement of the actuators. The control is coupled to the electric brake and is configured, upon the supply voltage magnitude exceeding a predetermined value, to cause the regenerative current to be supplied to the electric brake.

Abstract: A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, and an actuator. The transcowl is mounted on the support structure and is axially translatable between a stowed position and a deployed position. The actuator is coupled to the transcowl and the support structure, and is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The actuator includes an actuator housing, a screw, a nut, a rod end, and a tension rod. The tension rod is engaged by the nut when the transcowl is in the deployed position and is engaged by the rod end when the transcowl is in the stowed position, whereby actuator loads, in both the deployed and stowed positions, are transmitted through the tension rod to the support structure.

Abstract: A thrust reverser control system includes a plurality of actuators, an electric motor, an electric brake, and a control. Each actuator is responsive to an actuator input torque to move between a stowed position and a deployed position. The electric motor is coupled to each of the actuators and is configured, upon being energized from a voltage source having a supply voltage magnitude, to supply the actuator input torque to the actuators and further configured to selectively generate regenerative current. The electric brake is coupled to be selectively supplied with the regenerative current and is configured, upon being supplied with the regenerative current, to supply a braking torque that slows movement of the actuators. The control is coupled to the electric brake and is configured, upon the supply voltage magnitude exceeding a predetermined value, to cause the regenerative current to be supplied to the electric brake.

Abstract: A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, an actuator, and a retractable cable. The support structure is configured to be mounted to the turbine engine. The transcowl is mounted on the support structure and is axially translatable, relative to the support structure, between a stowed position and a deployed position. The actuator is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The retractable cable is coupled to the transcowl and the support structure, and is configured to react reverse thrust loads on the transcowl at least when the transcowl is in the deployed position, to thereby at least reduce thrust loading on the actuator.

Abstract: A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, an actuator, and a hydraulic assist mechanism. The actuator is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The hydraulic assist mechanism is coupled to the transcowl and is configured to react reverse thrust loads on the transcowl at least when the transcowl is translating between the stowed position and the deployed position.

Abstract: A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, a door, a main actuator, and an assist actuator. The transcowl is mounted on the support structure and is axially translatable between a stowed position and a deployed position. The door is pivotally coupled to the support structure and is rotatable between at least a first position and a second position when the transcowl translates between the stowed position and the deployed position, respectively. The main actuator is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The assist actuator is coupled to the door, and is configured to supply an actuation assist force to the door and, upon rotation of the door to an intermediate position between the first position and the second position, to commence load sharing with the main actuator.

Abstract: A system and method are provided for controlling the movement of an aircraft engine cowl door between an open position and a closed position. The system includes an electric motor, at least one actuator, and an electrically operated brake. The actuator is coupled to the motor and is operable to move the cowl door between the closed and the open position. The electrically operated brake is coupled to the electric motor and the at least one actuator and is configured, upon being energized, to supply a unidirectional resisting torque load to the electric motor that does not prevent motor rotation.

Abstract: A fluid-powered thrust reverser actuation system includes electromechanical speed control to implement multiple mid-stroke speeds. The system may also be configured to implement two different operational modes—a normal operational mode and a rejected take-off operational mode.

Abstract: A system and method are provided for controlling the movement of an aircraft engine cowl door between an open position and a closed position. The system includes an electric motor, at least one actuator, and an electrically operated brake. The actuator is coupled to the motor and is operable to move the cowl door between the closed and the open position. The electrically operated brake is coupled to the electric motor and the at least one actuator and is configured, upon being energized, to supply a unidirectional resisting torque load to the electric motor that does not prevent motor rotation.