Hunter Douglas,inc.

The Boeing Company

Federal Express Corporation

Other

Robert E Fisher

Richard N Anderson

Donald E Fraser

Suresh Rangan

James L Bowman

Steven R Haarer

Eugene W Thompson

James Patrick Irwin

Kevin Scott Callahan

Steve G Mackin

Kevin M Dann

James M Anthony

Joseph E Kovach

Stephen R Haarer

John T Paterson

Daniel M Fogarty

Eddie Kwon

Kelly Thomas Jones

Michael Scott Goldberg

Clark D Brace

Nickolas C Buccola, Jr

Paul Griffin Vahey

Michael E Rorabaugh

Mark John Gardner

Benjamin A Johnson

Kevin O Gaw

Todd Michael Nelson

Paul A Brayford

Daniel A Huber

Jan Pruegner

Timothy K Sheehan

Robert M Murphy

Max Oelschlager

Santiago Alvarado, Jr

Joseph A Pantelleria

Shannon Coleman

Mark J Gardner

Example methods and apparatus can be used to reduce noise in motor assemblies, such as those used in architectural coverings. An example apparatus includes a first driver configured to be coupled to and rotated by an output shaft of a motor, a second driver, and a plurality of vibration-absorbers disposed between the first driver and the second driver. The second driver is configured to be coupled to a rotating member to transfer rotational motion from the first driver to the rotating member via the vibration-absorbers.

Methods and apparatus to reduce noise in motor assemblies

Methods, systems, and apparatus, including computer programs encoded on a computer storage medium, for receiving data related to a first flight risk factor and a second flight risk factor where the first and second risk factors include one of: a proficiency risk factor, an equipment risk factor, an environmental risk factor, or a performance risk factor. Applying a first weighting to the first flight risk factor to generate a first weighted flight risk factor, and applying a second weighting to the second flight risk factor to generate a second weighted flight risk factor. Assessing a flight risk level for a flight based on the first weighted flight risk factor and the second weighted flight risk factor. Providing data indicating the assessed flight risk level for the flight for display to a user.

Risk assessment framework

A handle is releasably secured to a rail wall by means of fasteners extending from inside the rail. An actuator shaft pushes against a contact plate to move a movable braking member to stop the rotation of a rod inside the rail.

Handle and brake arrangement for a covering for architectural openings

Methods, systems, and apparatus, including computer programs encoded on a computer storage medium, for receiving data related to a first flight risk factor and a second flight risk factor where the first and second risk factors include one of: a proficiency risk factor, an equipment risk factor, an environmental risk factor, or a performance risk factor. Applying a first weighting to the first flight risk factor to generate a first weighted flight risk factor, and applying a second weighting to the second flight risk factor to generate a second weighted flight risk factor. Assessing a flight risk level for a flight based on the first weighted flight risk factor and the second weighted flight risk factor, Providing data indicating the assessed flight risk level for the flight for display to a user.

Methods and apparatus to control movement of a component are disclosed herein. An example apparatus includes a housing defining a bore and a piston disposed inside the bore. The piston is to be coupled to a movable component disposed outside of the bore. The example apparatus further includes a fluid flowline in fluid communication with a first chamber of the bore and a second chamber of the bore. The first chamber is on a first side of the piston, and the second chamber on a second side of the piston. The example apparatus also includes a valve to control fluid flow through the fluid flowline. The valve is to be in a first state to enable the piston to dampen movement of the component, and the valve is to be in a second state to enable the piston to hold the component substantially stationary.

Methods and apparatus to control movement of a component

An ice prevention system is configured to prevent ice from forming and/or melt ice with respect to one or more portions of an aircraft. The ice prevention system includes a combustor having an air inlet and a gas outlet. A supply air conduit is coupled to the air inlet of the combustor. The supply air conduit is configured to channel low pressure air to the combustor. One or more delivery conduits are coupled to the gas outlet of the combustor. The delivery conduit(s) are configured to be coupled to the one or more portions of the aircraft. The combustor is configured to exhaust heated gas to the delivery conduit(s) through the gas outlet to prevent ice from forming with respect to the portion(s) of the aircraft.

Systems and methods for preventing ice formation on portions of an aircraft

A deresonated fluid system may include a pressurizable fluid line having distal, opposite line ends with the fluid line extending between the line ends. A source may be configured to apply variations in pressure of fluid in the fluid line having a frequency appropriate for producing a standing wave in the fluid line between the line ends. A fluid coupler having opposite first and second coupler ends may be attached to the fluid line in a medial portion of the fluid line between the line ends. A flow acceleration ramp may be formed about an inside of the first coupler end. An artificial acoustic shoulder may be formed about an inside of the second coupler end. The artificial acoustic shoulder may define a substantially central orifice in fluid communication with the flow acceleration ramp.

Pressurized fluid line deresonator

An apparatus, system, and method for reducing the warpage of a rotor of an aircraft engine. When the aircraft engine is placed in standby mode, a solenoid-operated bypass valve may receive a control signal to open. When open, the solenoid-operated bypass valve places an electric hydraulic pump in fluidic communication with an engine driven hydraulic pump. The engine driven hydraulic pump rotates because of the pressured provided by the electrical hydraulic pump. The mechanical linkage between the engine driven hydraulic pump and the rotor causes the rotor of the aircraft engine to rotate.

Apparatus, controller and method for controlling the cool down of an aircraft engine rotor

A cord wrapping mechanism converts linear motion to circular motion for use in coverings for architectural openings. The cord is guided onto a spool.

Cover for architectural openings

An arrangement for mounting an actuator button to a rail wherein the fastener for securing the button housing to the rail is hidden from view of the user.

Arrangement for mounting an actuator button onto a rail of a window covering

Growing community of inventors

Owensboro, KY, United States of America

Robert E Fisher