The Boeing Company

Ian M Gunter

Fred Norman Krueger

Dean Walters

Dan John Clingman

James Henry Mabe

Robert T Ruggeri

Ordie Dean Butterfield

Darin J Arbogast

Cris Kevin Bosetti

Bryan David McGranahan

Mathew Lee Rueger

Stefan P Hovik

Thomas R Kenow

Bernard J Sklanka

Chris Jorgens

Chris Bosetti

Remy M Gutierrez

Daniel Morgenroth

An apparatus and a method for measuring one or more acoustic parameters in a duct are described. The method includes arranging at least one pair of microphones in an array on a microphone support device, disposing the microphone support device including the array of microphones in the duct, generating an acoustic signal in the duct such that the acoustic signal propagates toward the array of microphones, and receiving by the array of microphones, the acoustic signal to provide a microphone output signal. The microphone support device is configured to fit within an inner diameter of the duct.

In-duct acoustic measuring apparatus and method

Systems and methods for the manufacture and use of artificial ice shapes for aircraft certification, including methods of manufacturing artificial ice shapes, artificial ice component systems for attachment to aircraft, methods of flight testing aircraft having artificial ice sections attached thereto, and artificial ice testing systems.

Systems and methods for icing flight tests

Methods and apparatus to control pitch and twist of blades are disclosed. An example apparatus includes a twist input assembly driven by a drive shaft that drives a rotation of blades of a rotorcraft, the twist input assembly comprising a twist shaft, a first gear set driven by the drive shaft, and a first frequency controller to create a first rotational speed difference between a first gear of the first gear set and the drive shaft, the first rotational speed difference to cause the twist shaft to oscillate. The examples apparatus includes a pitch input assembly driven by the drive shaft, the pitch input assembly comprising a pitch link in communication with a first one of the blades of the rotorcraft, a second gear set driven by the drive shaft, and a second frequency controller to create a second rotational speed difference between a second gear of the second gear set and the drive shaft, the second rotational speed difference to cause the pitch link to oscillate.

Methods and apparatus to control pitch and twist of blades

A tunable mass-damping apparatus may include a housing having an interior surface, an interior volume containing a fluid, and an axis. The housing may be configured to be coupled to a wind tunnel model. The apparatus may further include a mass configured to move back and forth in the interior volume along the axis. The mass may be configured to make an airtight seal with the interior surface of the housing, thereby dividing the interior volume into an upper chamber and a lower chamber. The apparatus may include a passage fluidly connecting the upper chamber and the lower chamber and a spring configured to exert a position-dependent force upon the mass. The spring may be characterized by a variable spring constant chosen based on a variable natural frequency of a support structure of the wind tunnel model. The variable spring constant may be established with a nickel-titanium alloy spring heated to at least one calibrated temperature that corresponds to a predetermined spring constant.

Variable spring-constant tuned mass damper

A method and apparatus for locking an externally threaded member in place. An apparatus comprises a number of internally threaded members and a shape memory element associated with the number of internally threaded members. The number of internally threaded members is configured to engage the externally threaded member. Changing a baseline shape of the shape memory element to a modified shape either prevents or allows movement of the number of internally threaded members relative to the externally threaded member.

Lead screw locking mechanism

A rotational actuator assembly employs a first torsion actuator having a shape memory alloy (SMA) tube with a first trained twist direction and a second torsion actuator having a SMA tube with an opposite trained twist direction collinear with the first torsion actuator with abutting proximal ends. A central fitting joins the proximal ends. A control system for temperature control of the first torsion actuator and second torsion actuator about an average temperature provides combined antagonistic rotation of the central fitting.

Remotely actuated wind tunnel model rudder using shape memory alloy

A rotational actuator assembly employs a drive torque actuator having a shape memory alloy (SMA) tube with a first trained twist direction and a return actuator having a SMA tube with an opposite trained twist direction collinear with the drive torque actuator with abutting proximal ends. A central fitting joins the proximal ends. A control system employs a position sensor for the drive torque actuator and the torque sensor for the return actuator for combined antagonistic rotation of the central fitting.

Torque controlled antagonistic shape memory alloy actuator

A torsion lock may include a clutch, a spring, and a shape memory alloy (SMA) member. The spring may cause the application of pressure on the clutch for engagement thereof. The SMA member may linearly contract when heated in a manner to relieve the pressure on the clutch for disengagement thereof.

Shape memory alloy actuated torsion lock

An actuator assembly may comprise a housing, a shaft, a shape memory alloy (SMA) torque tube, and first and second unidirectional bearings. The SMA torque tube may rotate the shaft. The first unidirectional bearing may limit rotation of the shaft relative to the SMA torque tube to a first direction. The second unidirectional bearing may prevent rotation of the shaft relative to the housing along a second direction opposite the first direction.

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Burien, WA, United States of America

Ian M Gunter