Abstract: A fluid device system includes a fluid pump, an electric motor in engagement with the fluid pump, and a controller. The electric motor is adapted for rotation in response to an electric signal. The controller is adapted to communicate the electric signal to the electric motor. The controller includes a lookup table having a plurality of performance data related to the fluid pump and the electric motor. The performance data from the lookup table is used by the controller to set aspects of the electrical signal communicated to the electric motor in order to achieve a desired attribute of the fluid pump.

Abstract: A fluid device system includes a fluid pump, an electric motor in engagement with the fluid pump, and a controller. The electric motor is adapted for rotation in response to an electric signal. The controller is adapted to communicate the electric signal to the electric motor. The controller includes a lookup table having a plurality of performance data related to the fluid pump and the electric motor. The performance data from the lookup table is used by the controller to set aspects of the electrical signal communicated to the electric motor in order to achieve a desired attribute of the fluid pump.

Abstract: A drive apparatus is provided to transmit force from a source of power to a driven assembly, such as a pump, in an aircraft. The drive apparatus can be operated from a disengaged condition back to an engaged condition when the aircraft is on the ground. The drive apparatus includes a first annular array of teeth which is connected with an input member and a second annular array of teeth which is connected with an output member. A plurality of disengagement levers extend outward from the output member. A retaining member is connected with outer end portions of the disengagement levers. An actuator member or yoke is movable to move the retaining member and the outer ends of the engagement levers to disengage the drive apparatus.

Abstract: A drive apparatus is provided to transmit force from a source of power to a driven assembly, such as a pump, in an aircraft. The drive apparatus can be operated from a disengaged condition back to an engaged condition when the aircraft is on the ground. The drive apparatus includes a first annular array of teeth which is connected with an input member and a second annular array of teeth which is connected with an output member. A plurality of disengagement levers extend outward from the output member. A retaining member is connected with outer end portions of the disengagement levers. An actuator member or yoke is movable to move the retaining member and the outer ends of the engagement levers to disengage the drive apparatus.