The Boeing Company

Eric Anton Howell

Jeffrey Michael Roach

Michael Thomas Fox

Thomas W Omohundro

A hydraulic system for an aircraft. The hydraulic system can include a hydraulic actuator that is operatively coupled to a flight control member. Hydraulic fluid is moved through the hydraulic system by an engine driven pump that delivers hydraulic fluid to the actuator at a first pressure, and a boost pump that delivers hydraulic fluid to the actuator at a second pressure that is higher than the first pressure. The hydraulic system is configured such that the hydraulic fluid returning from the actuator to the engine driven pump can be delivered to the boost pump prior to reaching the engine driven pump.

Hydraulic system for an aircraft

A dual spool valve and methods of controlling hydraulic fluid that is moved to a hydraulic actuator of an aircraft. The dual spool valve may include ports to receive and discharge hydraulic fluid. The dual spool valve may also include first and second valve sections that are selectively positionable to control the flow of hydraulic fluid into and out of the actuator. One position provides for hydraulic fluid to move through closure lines. Method of controlling the dual spool valve may provide for selectively positioning the valve sections to control the flow of hydraulic fluid, and to position the valve sections to move hydraulic fluid through a closure line during certain circumstances.

Aircraft hydraulic system with a dual spool valve and methods of use

A force balance sensor including a mechanical strain amplification system including a sensor torsion member having a first end and a second end spaced from one another along a longitudinal axis of the sensor torsion member, at least one strain sensor coupled to the sensor torsion member between the first and second ends, a first torsional stiffening member coupled to the first end of the sensor torsion member, and a second torsional stiffening member coupled to the second end of the sensor torsion member, wherein the first torsional stiffening member and the second torsional stiffening member are coupled to a torque member.

Force balance sensor and method therefor

There is provided a translational inerter assembly for damping movement of a flight control surface of an aircraft with a support structure. The translational inerter assembly includes a press fit element rotatably disposed within the flight control surface. The translational inerter assembly further includes an inertia element disposed in the press fit element. The translational inerter assembly further includes a torsion bar coupled to the inertia element and to the support structure of the aircraft, such that when the flight control surface rotates, the inertia element translates, and movement of the flight control surface is dampened.

Translational inerter assembly and method for damping movement of a flight control surface

An actuator assembly for an aircraft includes a support strut operatively coupled to a hinge axis of a flight control member of the aircraft, a hydraulic actuator operatively coupled to the flight control member via a pivot element, and an electro-mechanical actuator (EMA) having first and second opposing ends and a biasing member. The first end is operatively coupled to a support structure of the aircraft, and the second end is operatively coupled to both the support strut and the hydraulic actuator. The biasing member moves between a compressed state and an expanded state in response to a varying biasing load exerted on a surface of the flight control member, thereby reducing an amount of current needed to drive the EMA, as well as a number of high-pressure hydraulic cycles of the hydraulic actuator to control the flight control member.

Electro-mechanically biased supercritical flight control surface loading to reduce high pressure actuation cycles

Methods and devices for adjusting a position of a flight control member relative to a base of an aircraft. The devices and methods include a joint that movably connects the flight control surface to the base. An extension member is connected to the flight control surface and extends through the joint. Adjustable linear members of the base are connected to the extension member and configured to adjust the position of the extension member. This adjustment results in re-orienting the flight control member relative to the base to adjust the flight of the aircraft.

Base flight control member orientation mechanism and control

A dual rack and pinion rotational inerter, configured to dampen the flutter of a flight control member of an aircraft, includes an inertial wheel and a brake member disposed on an inertial wheel. The brake member moves between a retracted position and a deployed position based on a rotational velocity of the inertial wheel. The brake member moves to the retracted position when the rotational velocity of the inertial wheel is slower than a predetermined threshold velocity to allow the rotation of the inertial wheel. When the rotational velocity of the inertial wheel is at least as fast as the predetermined threshold velocity, however, the brake member deploys to yieldingly resist the rotation of the inertial wheel. In either position, the inertial wheel causes the inerter to dampen the flutter.

High-speed-deployed, drum-brake, inertia disk for rack and pinion rotational inerter

A dual spool valve and methods of controlling hydraulic fluid that is moved to a hydraulic actuator of an aircraft. The dual spool valve may include first and second manifolds that each includes a movable spool. Multiple ports are positioned in each of the manifolds. The movable spools are positionable within their respective manifolds to control the movement of the hydraulic fluid that is supplied to and removed from the hydraulic actuator.

The hydraulic system can include a control member that is operatively coupled to a member. The control member can include a hydraulic control member and an integrated inerter. Hydraulic fluid at variable pressures is moved through the hydraulic system by pumps. The hydraulic system can be configured for hydraulic fluid returning from the control member to the first pump to be delivered to the second pump prior to reaching the first pump. A dual-spool valve is positioned between the pumps and the control member to control the flow of the hydraulic fluid. The dual-spool valve is movable to move the hydraulic fluid at variable pressures into and out of first and second chambers of the control member. The dual spool valve can also be configured to operate the control member when a spool is not operational.

Hydraulic systems and methods to control a member

A power extraction system and method for a gas turbine engine of a vehicle are provided. The system has an HP spool tower shaft coupled between an HP spool of the gas turbine engine and an accessory gearbox assembly coupled to the gas turbine engine. The HP spool tower shaft extracts mechanical power from the HP spool. The system has an LP spool tower shaft coupled between an LP spool of the gas turbine engine and the accessory gearbox assembly. The LP spool tower shaft extracts mechanical power from the LP spool. The system further has the accessory gearbox assembly having an accessory drive combining the mechanical power from both the HP spool and LP spool, having a planetary gear train coupled to the accessory drive, and having one or more engine-driven accessories coupled to the planetary gear train and driven by a planetary gear train output to generate power.

Power extraction system and method for a gas turbine engine of a vehicle

There is provided a dual rack and pinion rotational inerter system for damping movement of a flight control surface of an aircraft having a support structure. The system has a flexible holding structure disposed between the flight control surface and the support structure. The system has a dual rack and pinion assembly held by the flexible holding structure. The system has a first terminal and a second terminal, coupled to the dual rack and pinion assembly. The first terminal is coupled to the flight control surface. The system has a pair of inertia wheels coupled to the flexible holding structure. The system has an axle element inserted through the inertia wheels, the flexible holding structure, and the dual rack and pinion assembly, such that when the flight control surface rotates, the dual rack and pinion rotational inerter system translates and rotates, and movement of the flight control surface is dampened.

Dual rack and pinion rotational inerter system and method for damping movement of a flight control surface of an aircraft

There is provided a translational inerter assembly for damping movement of a flight control surface of an aircraft. The assembly has a press fit element fixedly disposed within a first end of the flight control surface and rotatably movable with the flight control surface. The assembly further has an inertia element coupled to and installed in the press fit element. The assembly further has a torsion bar having a torsion bar first end coupled to and installed in the inertia element, and having a torsion bar second end fixedly attached to a support structure of the aircraft. Rotation of the flight control surface causes translational movement of the inertia element, via the press fit element, along a hinge axis of the flight control surface and along the torsion bar, resulting in the translational inerter assembly damping movement of the flight control surface.

There is provided a dual rack and pinion rotational inerter system for damping movement of a flight control surface of an aircraft. The system has a flexible holding structure disposed between the flight control surface and a support structure of the aircraft. The system has a dual rack and pinion assembly held by and between the flexible holding structure. The dual rack and pinion assembly has a first rack, a second rack, and a pinion engaged to and between the racks. The system has a first terminal coupled to the first rack and coupled to the flight control surface, via a pivot element, and a second terminal coupled to the second rack, and coupled to the support structure. The system has a pair of inertia wheels adjacent the flexible holding structure. The system has an axle element inserted through the inertial wheels, the flexible holding structure, and the pinion.

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Ballwin, MO, United States of America

Eric Anton Howell