Honeywell International Inc.

Alliedsignal Inc.

The Garrett Corporation

Paul S Evans

Louie Timothy Gaines

Paul T Wingett

Calvin C Potter

James I Kern

James Neil Quitmeyer

Casey Hanlon

Kellan P Geck

David M Eschborn

Glenn H Lane

David M Mathis

Gary A Farnsworth

Terry L Keller

Howard W Ripy

Jimmy D Wiggins

James N Quitmeyer

A relatively small, lightweight actuator includes a plurality of motors, an actuation element, a translation member, and a plurality of position sensors. The motors each supply a drive force to the actuation member, causing it to rotate. The translation member is configured, upon rotation of the actuator, to translate to a position. The position sensors sense the translational position of the translation member and the rotational position of each motor. The actuator is relatively small, lightweight, and can withstand the relatively severe environmental conditions and relatively significant levels of vibration and shock associated with many aerospace applications.

Electromechanical actuator including redundant, dissimilar position feedback

An aircraft brake actuation system implements an anti-hysteresis feature that compensates for various hysteresis effects exhibited in an aircraft brake actuation system due to one or more sources of mechanical inefficiency within the system. The anti-hysteresis feature adjusts the command signal up or down, depending on the direction of the command, a predetermined amount based on the amount of hysteresis in the system. By doing so, the actual brake force supplied to the aircraft brake elements more accurately represents the brake force being commanded.

Aircraft brake actuation system and method including anti-hysteresis control

Methods and apparatus are provided for monitoring an aircraft accessory. The apparatus comprises a processor associated with said aircraft accessory, a transducer coupled to said processor and operable to produce parametric data relating to said aircraft accessory and a memory coupled to said processor having baseline parametric data residing therein, wherein said baseline parametric data comprises the parametric data obtained during an acceptance test procedure. The method comprises installing a transducer configured to produce parametric data relating to said aircraft accessory, coupling said transducer to a processor associated with said aircraft accessory, coupling said processor to a memory associated with said aircraft accessory, recording baseline parametric data relating to said aircraft accessory in said memory during an acceptance test procedure for said aircraft accessory.

Aircraft accessory monitor

A thrust vector actuation control system and method is configured to allow self-testing of the entire actuation system and/or its individual system components. The control system also provides real-time, continuous monitoring of actuation system status, and allows system gain and compensation parameters to be changed during vehicle operation remote from its launch site.

Thrust vector actuation control system and method

A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.

Flight control actuation system

In a closed loop control system that governs the movement of an actuator a filter is provided that attenuates the oscillations generated by the actuator when the actuator is at a resonant frequency. The filter is preferably coded into the control system and includes the following steps. Sensing the position of the actuator with an LVDT and sensing the motor position where motor drives the actuator through a gear train. When the actuator is at a resonant frequency, a lag is applied to the LVDT signal and then combined with the motor position signal to form a combined signal in which the oscillation generated by the actuator are attenuated. The control system then controls ion this combined signal. This arrangement prevents the amplified resonance present on the LVDT signal, from causing control instability, while retaining the steady state accuracy associated with the LVDT signal. It is also a characteristic of this arrangement that the signal attenuation will always coincide with the load resonance frequency of the system so that variations in the resonance frequency will not effectuate the effectiveness of the filter.

Anti-resonance mixing filter

A launching device with a work-controlled gas generator employs a dampening piston in combination with an accumulator volume to provide substantially uniform acceleration of a launching piston.

Work-controlled launching device with accumulator

A fluidic analog temperature sensor which compensates for variations in the supply pressure to the temperature sensor.

Growing community of inventors

Mesa, AZ, United States of America

Paul S Evans