Abstract: In a method for advanced identification of a customer, a customer may remotely place an order, intending to later go to a store to pick up the ordered item. The store may have a pick-up area (e.g., at the back of the store) where the customer can go to pick up the ordered item. To save the customer time, the customer may be identified when she enters the store so that an employee can obtain her ordered item and have it ready to pick up by the time the customer walks through the store and arrives at the pick-up area.

Abstract: A differential assembly provided with a power distribution unit includes a first housing, an output shaft, a shaft, and a torque limiter. The first housing defines a biasing member bore and a brake bore. The output shaft extends at least partially through the first housing. The shaft is disposed about the output shaft and extends between a first shaft end that is connected to a differential unit and a second shaft end. The torque limiter is disposed within the first housing and is arranged to selectively inhibit rotation of at least one of the output shaft and the shaft.

Abstract: A differential assembly provided with a power distribution unit includes a first housing, an output shaft, a shaft, and a torque limiter. The first housing defines a biasing member bore and a brake bore. The output shaft extends at least partially through the first housing. The shaft is disposed about the output shaft and extends between a first shaft end that is connected to a differential unit and a second shaft end. The torque limiter is disposed within the first housing and is arranged to selectively inhibit rotation of at least one of the output shaft and the shaft.

Abstract: A differential assembly provided with a power distribution unit includes a first housing, an output shaft, a shaft, and a torque limiter. The first housing defines a biasing member bore and a brake bore. The output shaft extends at least partially through the first housing. The shaft is disposed about the output shaft and extends between a first shaft end that is connected to a differential unit and a second shaft end. The torque limiter is disposed within the first housing and is arranged to selectively inhibit rotation of at least one of the output shaft and the shaft.

Abstract: An actuator system for controlling a flight surface of an aircraft includes a first actuator having a first actuator input and a first linear translation element that moves based on rotational motion received at the first actuator input and a first laser distance sensor disposed inside the first actuator that generates a first output based on a displacement of the first linear translation element. The system also includes a second actuator having a second actuator input and a second linear translation element that moves based on rotational motion received at the second actuator input and a second laser distance sensor disposed inside the second actuator that generates a second output based on a displacement of the second linear translation element. The system also includes a control unit that receives the first and second outputs and determines if an error condition exists for the system based on first and second output.

Abstract: A predictive system is provided and include a torque-limiter, a sensor disposed to sense a condition of the torque-limiter and a processing system. The processing system is coupled to the sensor and configured to process readings of the sensor, to calculate whether the condition of the torque-limiter is indicative of degradation or failure incidents based on the readings being processed and to determine whether an action should be taken based on a calculation result.

Abstract: A differential assembly provided with a power distribution unit includes a first housing, an output shaft, a shaft, and a torque limiter. The first housing defines a biasing member bore and a brake bore. The output shaft extends at least partially through the first housing. The shaft is disposed about the output shaft and extends between a first shaft end that is connected to a differential unit and a second shaft end. The torque limiter is disposed within the first housing and is arranged to selectively inhibit rotation of at least one of the output shaft and the shaft.

Abstract: A retention member monitoring system for a slat-flap control lever assembly including a control lever movable over a range of discrete angular positions. Also included is a retention member engageable with the control lever to retain the control lever in each of the discrete angular positions. Further included is at least one electric device in communication with the retention member to determine the structural integrity of the retention member.

Abstract: A method and apparatus for lubricating a gear of a differential gear system is disclosed. A member or shaft rotates within a housing of the differential gear system. The shaft includes a chamber for receiving a lubricant from the exterior of the housing. A gear rotates relative to the shaft, and a hole in the shaft disperses the lubricant from the chamber to a selected gear location of the gear to lubricate the gear.

Abstract: A retention member monitoring system for a slat-flap control lever assembly including a control lever movable over a range of discrete angular positions. Also included is a retention member engageable with the control lever to retain the control lever in each of the discrete angular positions. Further included is at least one electric device in communication with the retention member to determine the structural integrity of the retention member.

Abstract: A predictive system is provided and include a torque-limiter, a sensor disposed to sense a condition of the torque-limiter and a processing system. The processing system is coupled to the sensor and configured to process readings of the sensor, to calculate whether the condition of the torque-limiter is indicative of degradation or failure incidents based on the readings being processed and to determine whether an action should be taken based on a calculation result.

Abstract: An actuator system for controlling a flight surface of an aircraft includes a first actuator having a first actuator input and a first linear translation element that moves based on rotational motion received at the first actuator input and a first laser distance sensor disposed inside the first actuator that generates a first output based on a displacement of the first linear translation element. The system also includes a second actuator having a second actuator input and a second linear translation element that moves based on rotational motion received at the second actuator input and a second laser distance sensor disposed inside the second actuator that generates a second output based on a displacement of the second linear translation element. The system also includes a control unit that receives the first and second outputs and determines if an error condition exists for the system based on first and second output.

Abstract: An airfoil surface control system includes a movable surface. An actuator is coupled to the surface. The airfoil surface control system includes a motor. A torque tube assembly operatively couples the motor and actuator and includes first and second shafts coupled by a universal joint. The universal joint is configured to provide a first maximum angle between the first and second shafts. A stop is configured to provide a second maximum angle between the first and second shafts that is less than the first maximum angle.

Abstract: A method and apparatus for lubricating a gear of a differential gear system is disclosed. A member or shaft rotates within a housing of the differential gear system. The shaft includes a chamber for receiving a lubricant from the exterior of the housing. A gear rotates relative to the shaft, and a hole in the shaft disperses the lubricant from the chamber to a selected gear location of the gear to lubricate the gear.

Abstract: An electromechanical actuation system (10) for a space vehicle includes a propellant source (18) and at least one turbine (14) operably connected to the propellant source (18) and rotatable by a flow of propellant (16) therefrom. At least one electrical generator (20) is operably connected to the at least one turbine (14) and is configured to convert rotation of the turbine (14) into electrical energy. At least one electromechanical actuator (12) is operably connected to the at least one electrical generator (20) such that electrical energy from the at least one electrical generator (20) drives operation of the at least one electromechanical actuator (12). A method of operating a turbine powered electromechanical actuator (12) for a space vehicle includes rotating the at least one turbine (14) via a flow of propellant (16) therethrough.

Abstract: An airfoil surface control system includes a movable surface. An actuator is coupled to the surface. The airfoil surface control system includes a motor. A torque tube assembly operatively couples the motor and actuator and includes first and second shafts coupled by a universal joint. The universal joint is configured to provide a first maximum angle between the first and second shafts. A stop is configured to provide a second maximum angle between the first and second shafts that is less than the first maximum angle.

Abstract: An electromechanical actuation system (10) for a space vehicle includes a propellant source (18) and at least one turbine (14) operably connected to the propellant source (18) and rotatable by a flow of propellant (16) therefrom. At least one electrical generator (20) is operably connected to the at least one turbine (14) and is configured to convert rotation of the turbine (14) into electrical energy. At least one electromechanical actuator (12) is operably connected to the at least one electrical generator (20) such that electrical energy from the at least one electrical generator (20) drives operation of the at least one electromechanical actuator (12). A method of operating a turbine powered electromechanical actuator (12) for a space vehicle includes rotating the at least one turbine (14) via a flow of propellant (16) therethrough.

Abstract: A method for determining a load on a driven component of a rotating or stationary electromechanical system includes locating a rotationally flexible shaft portion in operable communication with a driving component having a drive rotor rotable about an axis and the driven component. The shaft portion is operably connected thereto. Angular positions of the drive rotor and the driven component are determined. A magnitude of a load on the driven component is calculated based on a difference in angular position of the drive rotor and the driven component and a known torsional rigidity of the shaft portion.

Abstract: A method for determining a load on a driven component of a rotating or stationary electromechanical system includes locating a rotationally flexible shaft portion in operable communication with a driving component having a drive rotor rotable about an axis and the driven component. The shaft portion is operably connected thereto. Angular positions of the drive rotor and the driven component are determined. A magnitude of a load on the driven component is calculated based on a difference in angular position of the drive rotor and the driven component and a known torsional rigidity of the shaft portion.

Abstract: A rotary holding unit attached to a body including a plurality of clamping legs which move relative to each other. The unit allows simultaneous operation of either mounting the assembly to a vertical or horizontal edge or securing an object within the fully rotating holding housing. By moving the legs against the biasing force, the unit is prepared for mounting to an edge such as a ladder leg or table. Upon release the unit is automatically secured to the edge by means of the biasing force. Inadvertent movement of the unit once positioned is further limited by grip improving materials. The holding housing—in this case a female dovetail socket capable of receiving and securing a mating male dovetail fitted to or part of an accessory or component—may be rotated to the desired position.