Goodrich Patente

A method (200) for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying, via a gas, a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and measuring a pressure of the gas. This process may be performed over time to determine a lifespan of the propellant grain.

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The present disclosure provides for pneumatic deicer boot assemblies (10), and related methods of fabrication and use. More particularly, the present disclosure provides for bartack stitched pneumatic deicer boot assemblies for aircraft or the like, with the bartack stitched pneumatic deicer boot assemblies having an inflatable carcass formed by two layers (e.g., a stretchable layer (12) and a non-stretchable layer (14)) stitched together using bartack stitches (16).

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The disclosure relates to a valve assembly (2) comprising a valve body (4) comprising a first port (6), a second port (8) and a fluid passageway (10) extending therebetween. A valve member (12), comprising a through port (14), is arranged in the fluid passageway (10) and is moveable between an open position and a closed position. A sealing arrangement (15A) is arranged between the first port (6) and the valve member (12) and comprises a sealing member (16) arranged to seal against the valve member (12) such that fluid cannot flow around an outer surface (34) of the valve member (12). The sealing arrangement further comprises a sleeve (18) arranged in the fluid passageway (10) between the first port (6) and the valve member (12); and a deformable, incompressible, medium (20) contained around the sleeve (18) and arranged such that, in use, a fluid within the sleeve (18) exerts an outward pressure on the sleeve (18) causing the sleeve (18) to deform and act on the medium (20) which applies a force to push the sealing member (16) against the valve member (12).

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A method includes receiving a plurality of laser pulses as a pulse train on a plurality of imaging sensor pixels in an array of pixels. For each pixel in the array of pixels, the method includes receiving a respective one of the laser pulse trains, and scanning the pixels response across a range of frequencies with a bandpass filter to determine pulse shape characteristics of the respective one of the laser pulse trains. The method includes filtering out all of the laser pulse trains that do not fit a predetermined pulse shape characteristic for a true target designation pulse train, and physically adjusting trajectory of a physical resource toward a target based on location on the imaging sensor of one or more pixels receiving a laser pulse train that fits the predetermined pulse shape characteristic for the true target designation pulse train.

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An attachment bracket for fastening a heat shield panel of a wheel assembly to a radially inner surface of a wheel, the bracket having an essentially Z-shaped structure comprising an attachment part (30) defining two inner contact surfaces (301, 302) in a first plane each shaped to form, in use, a surface contact with the radially outer surface of the heat shield panel, and a wheel connector part (10) defining an outer contact surface in a second plane arranged to form, in use, a surface contact with the wheel when the heat shield panel is located in position relative to the wheel, where the first and second planes are essentially parallel but spaced apart in the axial direction of the wheel, and a sloping connector part (20) extending from the first plane to the second plane connecting a first end of the attachment part to a first end (102) of the wheel connector part.

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A lighting and monitoring module is disclosed herein. The lighting and monitoring module includes a module body (340, 440) including a front surface (350, 450) and a back surface (352, 452), the module body (340, 440) defining a space between the front surface (350, 450) and the back surface (352, 452), a connector (348, 448) disposed within the space defined by the module body (340, 440), a light disposed within the space defined by the module body (340, 440), the light coupled to the connector (348, 448), a first component (344, 444) disposed within the space defined by the module body (340, 440), the first component (344, 444) coupled to the connector (348, 448), and a second component (346, 446) disposed within the space defined by the module body (340, 440), the second component (346, 446) coupled to the connector (348, 448).

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A composite structure (300) may comprise a composite core (310) comprising a composite material, and a heat resistant system (320) coupled to the composite core comprising a binder and/or at least one of a heat dissipation material or a thermal barrier material. The heat dissipation material may comprise boron nitride, graphene, graphite, carbon fiber, carbon nanotubes, aluminum foil, and/or copper foil, and the thermal barrier material may comprise montmorillonite, aluminum hydroxide, magnesium hydroxide, silicate glass, mica powder or flake, aluminum oxide powder, titanium dioxide powder, and/or zirconium oxide powder. The binder may comprise at least one of polyvinyl alcohol, polyvinyl alcohol copolyacetate, polyacrylamide, polyethylene glycol, polyethylenimine, polyurethane, polyester, or latex.

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An evacuation system health monitoring system (200) for use on an aircraft (10) is disclosed herein. The system comprises a digital pressure sensor (206), an evacuation system readiness device (218), and a memory. The digital pressure sensor is in electronic communication with a controller (204). The system may further comprise a customer system (218) in communication with the controller. The customer system may communicate a pressure data from the digital pressure sensor to a customer device in real-time during an aircraft flight. The evacuation system readiness device may be in electronic communication with the controller. The evacuation system readiness device may be configured to display a visual indication of system readiness based on operations of the controller.

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