NEAR SYNCHRONOUS CONTROLLED INDUCTION MOTOR DRIVE ACTUATION SYSTEM
First Claim
1. A control system for controlling a plurality of actuators, the system comprising:
- a plurality of actuators for actuating movement of one or more adjustable components of an aircraft, wherein each actuator has a first end coupled to a structure of the aircraft and a second end coupled to one of the one or more adjustable components and each actuator additionally includes a motion control assembly that includes a drive path from a motion provider to the one adjustable component, wherein the one or more components is configured to move along a respective drive path; and
a controller operable to output motor drive power through a common bus to a plurality of the motion providers in a synchronous manner to actuate movement of the one or more adjustable components.
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Accused Products
Abstract
A distributed electromechanical actuation system including multiple electromechanical actuators intended to operate together in a synchronous (or near synchronous) manner. Each individual actuator is powered by one or more induction motors or other appropriate motor such as a stepper motor. The induction motors are designed to have a very high pullout torque with very low slippage to the pull out point. The group of actuators is controlled from a single controller (e.g., an induction motor controller) that utilizes a Volts per Hertz type of open loop control where the bus voltage and frequency are controlled to assure that the motors always operate on the low slip side of the pull out point performance curve.
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Citations
25 Claims
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1. A control system for controlling a plurality of actuators, the system comprising:
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a plurality of actuators for actuating movement of one or more adjustable components of an aircraft, wherein each actuator has a first end coupled to a structure of the aircraft and a second end coupled to one of the one or more adjustable components and each actuator additionally includes a motion control assembly that includes a drive path from a motion provider to the one adjustable component, wherein the one or more components is configured to move along a respective drive path; and a controller operable to output motor drive power through a common bus to a plurality of the motion providers in a synchronous manner to actuate movement of the one or more adjustable components. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20)
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21. A method for controlling a plurality of actuators for actuating movement of one or more adjustable components of an aircraft, the system comprising:
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receiving a command for adjusting the one or more adjustable components; controlling a plurality of actuators for actuating movement of the one or more adjustable components of the aircraft by a controller that outputs controlled motor drive power over a common bus in a synchronous manner to the plurality of actuators; adjusting the one more adjustable components based on the command information. - View Dependent Claims (22, 23, 24, 25)
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Specification