Rosemount Aerospace Limited

Jonathan L Boer

Eric L Lovaasen

Joseph T Pesik

Kevin J Benning

Richard Alan Schwartz

Kaleb Anderson

Wallace Johnson

Kenneth Freeman

Curtis Wicks

A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that an evacuation slide deployment path is within the field of view of the camera. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera to identify a region within the captured image data that corresponds to the evacuation slide deployment path, determine whether the evacuation slide deployment path will generate a failed deployment outcome, and produce a warning associated with the evacuation slide deployment path in response to determining that the evacuation slide deployment path will generate the failed deployment outcome.

Aircraft door camera system for evacuation slide deployment monitoring

A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that an engine inlet of an engine of the aircraft is within the field of view of the camera. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera to determine whether persons or foreign objects are present near the engine inlet, or detect damage or deformation of the engine inlet.

Aircraft door camera system for engine inlet monitoring

A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that a leading edge of a wing of the aircraft is within the field of view of the camera. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera to predict a likelihood of foreign object collision with the leading edge of the wing, or detect damage or deformation to the leading edge.

Aircraft door camera system for wing monitoring

A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that a wheel of a main landing gear of the aircraft is within the field of view of the camera. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera to monitor the landing gear.

Aircraft door camera system for landing gear monitoring

Camera housing

A heat exchanger system may have a base, a mounting apparatus for attaching the base to a device, a gasket shelf for placing a gasket, a dissipation member for dissipating heat, and heat generator attachment sites for absorbing heat. A mounting apparatus may have finger-like extensions which flex and draw the base into contact with an underlying electronic device from which the system conducts heat. A base may also have an integrated heat pipe clamp attachment forming an aperture in the base into which a heat pipe may extend and may be clamped in thermal communication. The dissipation device may be a series of fins and troughs and a fan may direct air over the dissipation device to cool the apparatus.

Integrated pipe heat exchanger

A mount includes a keyed insert and a key receiver. The keyed insert includes a key base and a keyed plate mounted to the key base and having one or more key features extending from a periphery of the keyed plate. The key receiver accepts the keyed insert and includes a receiver base, a retaining ring, a key set ring, a key entrance ring, and a spring plate. The retaining ring is connected to the receiver base. The key set ring is disposed between the retaining ring and the receiver base and includes one or more receiving notches and one or more locking notches. The one or more receiving notches is configured to receive the one or more key features the one or more locking notch is spaced away from the one or more receiving notch and is configured to lockingly engage the one or more key features.

Tool-less low profile rotation mount

An assembly is disclosed for mounting an electronic display device to a supporting structure within the cockpit of an aircraft which includes a circular adapter plate configured for attachment to a rear surface of an electronic display device, the adapter plate having a central alignment aperture with an axially extending annular wall that faces away from the rear surface of the display device, and a receiver plate configured for attachment to a supporting structure within the cockpit of an aircraft, the receiver plate having a recessed port for blindly receiving the annular wall of the central alignment aperture of the adapter plate.

Rotating electronic display mount

A compression mounted window assembly is disclosed that includes a circular window having opposed front and rear planar surfaces and an outer periphery having forward and rearward chamfered edge surfaces, a compressible gasket circumscribing the outer periphery of the window, a housing with a portal having an annular seat for accommodating the window circumscribed by the gasket, wherein the annular seat has a first chamfered abutment surface corresponding to the forward chamfered edge surface of the window, an annular bezel operatively associated with the housing for compressively retaining the window assembly within the annular seat of the portal, and structure for securing the bezel to the housing, wherein the bezel has a second chamfered abutment surface corresponding to the rearward chamfered edge surface of the window.

Growing community of inventors

Lakeville, MN, United States of America

Jonathan L Boer