Rohr, Inc.

Goodrich Lighting Systems Gmbh

Goodrich Corporation

Jai Ganesh Palanisamy

Anil Kumar Jha

Andre Hessling-Von Heimendahl

Abhilash Krishna

Aravind Edupalli

Murugapandian Thangavelu

Boopathy Saravanan

Hessling-Von Heimendahl

A thrust reverser system is provided that includes a sleeve, a fixed cascade structure and a blocker door. The fixed cascade structure is within a cavity of the sleeve when the sleeve is in a sleeve stowed position. The blocker door is within the cavity of the sleeve when the sleeve is in the sleeve stowed position and the blocker door is in a blocker door stowed position. The blocker door projects in a radial inward direction away from the sleeve towards the centerline when the sleeve is in a sleeve deployed position and when the blocker door is in a blocker door deployed position. The blocker door includes a pivot attachment fixed at an end of the blocker door. The pivot attachment is configured to move in a forward direction from a first location to a second location.

Hidden door thrust reverser system for an aircraft propulsion system

A thrust reverser assembly may comprise a sleeve including an inner sleeve portion and an outer sleeve portion. A plurality of guide rails may be coupled to a radially outward surface of the inner sleeve portion. A plurality of blocker doors may be slidably coupled to the plurality of guide rails. The plurality of blocker doors may be located between the inner sleeve portion and the outer sleeve portion.

Translating sleeve thrust reverser assembly

An exterior aircraft light unit according to exemplary embodiments of the invention comprises: a housing including a mounting portion, which is configured for mounting the aircraft light unit to an aircraft; at least one light source; and a heat sink; wherein the heat sink comprises: a first heat sink portion comprising a plurality of cooling ribs being thermally connected with the at least one light source for transferring heat from the at least one light source to the plurality of cooling ribs; and at least one second heat sink portion comprising two heat sink plates and a clamping pin and being configured such that the second heat sink portion is selectively attachable, particularly clampable, to a respective cooling rib of the first heat sink portion.

Exterior aircraft light unit

A floatation device includes a body transformable between a retracted configuration and an extended configuration. A stiffener assembly is movable between a first position and a second position. The stiffener assembly is biased into the second position. The stiffener assembly is operably coupled to the body such that movement of the stiffener assembly between the first position and the second position causes the body to transform between the retracted position and the extended position. During the transformation of the body between the retracted position and the extended position, a partial vacuum is created within the body to inflate the floatation device.

Floatation device without pressurized container

A device for forming a dynamic image on an aircraft sign includes a plurality of light sources, an input power line, a first timer and a second timer both connected to an enable input and a plurality of delay circuits each connected to a different one of the light sources. The system also includes a counter having a plurality of counter outputs, the counter receiving a counting pulse from the first timer in a dynamic mode of operation and disable signal from the second timer after expiration of a preset time, the expiration of the preset time causing the device to transfer from the dynamic mode to a static mode where each of the plurality of light sources are simultaneously illuminated.

Growing community of inventors

Bengaluru, India

Jai Ganesh Palanisamy