Honeywell International Inc.

Alliedsignal Inc.

Stephen G Abel

Donald Jeffrey Christensen

Calvin C Potter

George T Woessner

George J Klupar

Mark H Baker

Casey Hanlon

Grant A Gordon

Joseph J Nutaro

Sharon K Brault

William F Ryan

Raymond R Tseng

Ronald A Peck

Terry J Ahrendt

Dennis M Alexander

Douglas T Hopper

Joseph P Silk

Michael A Pepe

An aircraft electric taxi system diagnostics and prognostics evaluation method, including receiving, with a computer, an electronically recorded first performance parameter of a first electric taxi system of a first aircraft during a taxi operational event at an airport; and comparing the first performance parameter with a first performance factor statistical model generated in response to the first performance parameter and first comparative performance parameters; and calculating a first performance parameter difference based on the comparison.

Aircraft electric taxi system diagnostic and prognostic evaluation system and method

Systems and methods of controlling solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and propellant gas flow rate, rely on pulse width modulation of a control valve duty cycle. A control valve that is movable between a closed position and a full-open position is disposed downstream of, and in fluid communication with, a solid propellant gas generator. The solid propellant in the solid propellant gas generator is ignited, to thereby generate propellant gas. The control valve is moved between the closed position and the full-open position at an operating frequency and with a valve duty cycle. The valve duty cycle is the ratio of a time the control valve is in the full-open position to a time it takes the valve to complete one movement cycle at the operating frequency. The valve duty cycle is controlled to attain a desired solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and/or propellant gas flow rate.

Solid propellant burn rate, propellant gas flow rate, and propellant gas pressure pulse generation control system and method

A pilot flight control stick haptic feedback system includes a pilot user interface, a position sensor, a pilot motor, and a control circuit. The pilot user interface is movable to a position at a movement rate. The position sensor senses the position of the pilot user interface and supplies a pilot user interface position signal. The pilot motor is coupled to the pilot user interface, and receives pilot motor feedback signals. The pilot motor, in response to the pilot motor feedback signals, supplies feedback force to the pilot user interface. The control circuit determines one or more of the pilot user interface position, movement rate, aircraft control surface slew rate capacity, aircraft control surface load rate capacity, and aerodynamic stall risk and, based on at least a subset of these determinations, supplies pilot motor feedback signals to the pilot motor.

Pilot flight control stick haptic feedback system and method

A system for regulating the voltage in an electrical distribution system includes a plurality of flywheels, motor/generators, and controllers. Each of the motor/generators is coupled to one of the energy storage flywheels and to the electrical supply system. The motor/generators each supply one or more signals representative of motor/generator operational parameters, and each motor/generator controllers receive one or more of the motor/generator operational parameter signals from each of the motor/generators. In response to the operational parameter signals, the motor/generator controllers each control the operation of one of the motor/generators in either a motor mode or a generate mode, to thereby regulate the electrical supply system voltage and equally share the electrical load between the motor/generators.

Energy storage flywheel voltage regulation and load sharing system and method

A fluidic diverter valve includes valve element freely disposed within a valve bore. The valve bore has a cross sectional area that varies. As a result, the clearance between the valve element and an inner surface of the valve bore also varies. This variation in cross sectional area, and thus clearance, is such that a force of sufficient magnitude to move the valve element from a seated position is initially applied to the valve element, but the force on the valve element is reduced once it is moved from the seated position. Thus, the impact force upon attaining another seated position is reduced.

Fluidic diverter valve with a variable valve-bore clearance

A vehicle, such as a missile, with a pilot valve system controls the vehicle's thrust valves despite a hostile propellant gas environment. The pilot valve system can have one or more pilot valves. Using refractory elements, the pilot valve ball reciprocates between a supply seat and a vent seat which is subject to the filtered inflow of propellant thrust gases. When open, the pilot valve allows the stray thrust gas to communicate to a control chamber which closes a poppet against a valve seat in the nozzle. When an associated solenoid closes the pilot valve by pushing the pilot valve ball against the supply seat, the control chamber is vented to ambient. The poppet may then travel into the cylinder bore and the nozzle is opened to exhaust propellant gases and exert lateral thrust on the vehicle. Certain nozzle thrust geometries provide useful vehicle guidance.

Vehicle, lightweight pneumatic pilot valve and related systems therefor

A digital filter and filtering method uses a rate of change limit and an acceleration limit to significantly attenuate high bandwidth noise signals with minimal phase lag, while simultaneously passing low bandwidth signals substantially uncorrupted. The filter uses two memory states making it computationally efficient.

Rate and acceleration limiting filter and method for processing digital signals

A prognostic health and fault management system and method that accurately determines the health and rate of degradation of one or more flywheel systems, by comparing actual and simulated responses of flywheel systems to supplied command signals. Based on the determined health status and degradation rate of the flywheel systems, one or more unhealthy, active flywheel systems are deactivated, and one or more healthy, deactivated flywheel systems are activated. The system can be used in terrestrial applications, or in vehicles such as satellites, spacecraft, or ships.

Flywheel prognostic health and fault management system and method

An integrated power and attitude control system that includes a plurality of flywheels and a controller. The controller receives power commands and attitude commands and determines the optimum set of flywheel acceleration and gimbal velocity commands to supply to each flywheel, to meet the commanded power and attitude. Flywheel rotational acceleration is controlled to provide the commanded power, and both flywheel acceleration and flywheel gimbal angular velocity are controlled to provide the commanded attitude.

Integrated power and attitude control system and method

A system and method for controlling an active magnetic bearing assembly by varying the system control laws in a continuous non-linear fashion as a function of rotor rotational speed. The system control law variation is carried out in a continuous and optimal manner over the operating speed range of the rotor, and is not computationally intensive.

System and method for controlling an active magnetic bearing using continuous variable compensation

An active magnetic bearing assembly includes at least two rotors and two stator assemblies each having two pole faces. The pole faces of the stator assemblies are axially offset from the pole faces of their associated rotors. Thus, axial control of a shaft that is rotationally mounted using the active magnetic bearing assembly is provided by a reluctance centering force.

Active magnetic bearing assembly using permanent magnet biased homopolar and reluctance centering effects

A multi-stage pilot valve is disclosed for selectively supplying a working fluid to and venting from a reaction jet main stage actuation chamber. In a preferred embodiment of the invention, the pilot valve comprises a solenoid actuated ball and socket flapper valve having a pressure inlet, an exhaust outlet and a service port. The first stage service port is in fluid communication with a second stage actuation chamber. A piston disposed in the second stage actuation chamber operatively engages a ball member of a ball-and-seat type valve comprising the second stage valve. The second stage valve also comprises a pressure inlet, an exhaust outlet and a service port. The piston and ball are sized relative to each other such that when the second stage actuation chamber is pressurized by the first stage, the force is sufficient to seat the ball against the second stage pressure inlet. This shuts off the flow of high pressure gases to the second stage service port and permits the second stage service port to vent through the exhaust port. When the second stage actuation chamber is vented by the first stage valve, the pressure acting on the ball is sufficient to seat the ball against the second stage exhaust outlet. This opens the second stage pressure inlet to permit high pressure gases to enter the second stage service port. The bi-directional movement of the ball member of the second stage valve is accomplished entirely by fluid pressure, thus enabling a fast responding, high flow rate regulation of the hot gases using low electrical power and eliminating the use of springs or other resilient members that would be of dubious reliability operating in a hot gas environment.

Two stage gas pilot valve controlling gas flow to a reaction jet nozzle

A thruster valve has a continuously positionable piston between a closed position and a maximum open position. The piston moves in response to the difference in pressure between the pressure of the valve's inlet and thruster nozzle and the pressure behind the piston. A pivotable flapper valve regulates this pressure difference. When a change in thrust is required a force is applied to the flapper causing a change in this pressure difference which causes the piston to move until the desired thrust level is obtained.

Force driven hot gas proportional thruster valve

A thruster valve has a continuously positionable piston between a closed position and a maximum open position. The piston moves in response to the difference in pressure between the pressure in the intermediate annulus and the pressure behind the piston. A pivotable flapper valve regulates this pressure difference. When a change in thrust is required, the position of the flapper is changed causing a change in this pressure difference which causes the piston to move until the desired thrust level is obtained.

Position driven hot gas proportional thruster valve

A circuit arrangement is described which detects when the moving member of an electromagnetic device is in motion by detecting coincidence of energization of the device coil and a negative first differential of the current/time waveform and a positive first differential of the voltage/time waveform through said coil.

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Chandler, AZ, United States of America

Stephen G Abel