Bell Helicopter Textron Inc.

Textron Innovations Inc.

Robert Michael Laramee

Charles L Hollimon

John R Barber

John Herman Sherrer

John Sherrer

Carlos Alexander Fenny

Daniel Bryan Robertson

Michael E Rinehart

Dudley E Smith

William Steyer

Robert A Shepherd

David L Miller

David R Schlichte

Brian P Corbett

One embodiment includes a multistage infrared suppression exhaust system for an aircraft, including: a stage one including a first exhaust conduit to receive a first exhaust air flow at a first temperature-pressure product TP, a second exhaust conduit to receive a second exhaust air flow at a second temperature-pressure product TP, and a flow integrator mechanically configured to mix the first exhaust air flow with the second exhaust air flow in an integration chamber while preventing back flow into the second exhaust conduit; and a stage two including a stage two cooling airflow to cool the mixed first and second exhaust air flows.

Multistage infrared suppression exhaust system

An exhaust system has an engine exhaust plane associated with an entrance to the exhaust system, an exhaust exit plane associated with an exit of the exhaust system, a forward cap movable relative to the engine exhaust plane and configured to selectively intersect the engine exhaust plane, and an aft cap movable relative to the exhaust exit plane and configured to selectively intersect the exhaust exit plane.

Adaptive engine exhaust signature suppressor

A rotorcraft actuator monitoring system to monitor leakage past dynamic rotorcraft actuator seals of a rotorcraft actuator includes a body member and a fluid level indication housing attached to the body member. The body member is mounted to surround a dynamic rotorcraft actuator seal that seals fluid in a rotorcraft actuator, where the body member captures fluid that leaks past the dynamic rotorcraft actuator seal. The fluid level indication housing collects the fluid captured by the body member and indicates that a predetermined volume of fluid that leaked past the dynamic rotorcraft actuator seal has been collected.

Rotorcraft actuator seal leakage monitor

A method of managing aircraft exhaust includes providing hot air at a hot air mass flow rate, providing cold air at a cold air mass flow rate, and mixing the hot air and the cold air at a variable hot air mass flow rate to cold air mass flow rate ratio, wherein the variable hot air mass flow rate to cold air mass flow rate ratio is selectively maintained independent of at least one of (1) a variation in the hot air mass flow rate and (2) a variation in a translational speed of the aircraft.

Infrared suppressing exhaust system

A method for mapping a two-dimensional image data onto a three-dimensional graphic model of an object includes taking a plurality of two-dimensional images of the object. Each two-dimensional image has data, such as temperature data, which is desired to be represented on the three-dimensional graphic model. The three-dimensional model of the object is viewed on a graphic user interface. The three-dimensional model has a plurality of facets, each facet being configured for selectively receiving the data from the two-dimensional images, so that the two-dimensional images are mapped onto the facets of the three-dimensional model. The three-dimensional model can then be analyzed.

System and method for mapping two-dimensional image data to a three-dimensional faceted model

An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The secondary duct has a portion selectively rotatable relative to the remainder of the secondary duct for directing the exhaust gas vector. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.

Engine exhaust system with directional nozzle

An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.

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Fort Worth, TX, United States of America

Robert Michael Laramee