The Boeing Company

Richard A Cote

Ty Aaby Larsen

Mark Stephen Shander

Farhad Nozari

John T Paterson

Michael L Drake

Casey Y K Ng

Michael B McAvoy

Howard Carter, Iii

Eric Joseph Harvey

John T Peters

Michael S Hoag

David F King

A method and apparatus comprising a projector system and a structure connected to the projector system. The projector system is configured to project an image on an exterior surface of an aircraft. The structure is configured to be connected to the aircraft and has a shape configured to reduce an undesired airflow caused by the projector system when the aircraft is in flight.

Aircraft projector system and movement detection system responsive to aircraft structure movement

Systems and methods for providing AC power from multiple turbine engine spools are disclosed. An aircraft system in a particular embodiment includes an engine having a first shaft connected and a second shaft. The aircraft system can further include a bus system and a first energy converter including a starter/generator, coupled between the first shaft and the bus system to convert a first variable frequency energy transmitted by the first shaft to a first generally constant frequency energy. A second energy converter can be coupled between the second shaft and the bus system, with the second energy converter including a generator to convert a second variable frequency energy transmitted by the second shaft to a second generally constant frequency energy.

Systems and methods for providing AC power from multiple turbine engine spools

A method for improving the conspicuity of aircraft is described that includes determining onto which exposed portions of an aircraft surface a retro-reflective material is to be placed, and attaching the retro-reflective material to the exposed portions such that an observer of the retro-reflective material is provided with an indication of a size, location, and orientation of the aircraft.

Methods and systems for improving aircraft visibility

Systems and methods for providing AC power from multiple turbine engine spools are disclosed. A system in a particular embodiment includes a turbofan engine having a compressor, a first turbine and a first shaft connected between the compressor and the first turbine, and a fan, a second turbine and a second shaft connected between the fan and the second turbine. The system can further include a state power bus and a first energy converter coupled between the first shaft and the power bus, with the first energy converter including a starter/generator, and being positioned to convert a first variable frequency energy transmitted by the first shaft to a first generally constant frequency energy. A second energy converter can be coupled between the second shaft and the power bus, with the second energy converter including a generator and being positioned to convert a second variable frequency energy transmitted by the second shaft to a second generally constant frequency energy, with the second generally constant frequency energy in phase with and at generally the same frequency as the first generally constant frequency energy. A controller can be operatively coupled to the starter/generator and the generator, e.g., to control the functions of these devices.

An electrical architecture for an aircraft is provided. The electrical architecture is particularly suitable for relatively small, compact, and lightweight aircraft. In one embodiment, the electrical architecture includes an electrical generator component coupled to the aircraft engine, and an air compression system coupled to the electrical generator component. The electrical generator component is configured to receive mechanical power from the engine and to generate a constant frequency AC electrical power from the engine mechanical power, and the air compression system is configured to receive the constant frequency AC power as an input and, in response thereto, produce a pressurized air output having variable characteristics (for example, a variable flow rate or a variable air pressure).

Electrical systems architecture for an aircraft, and related operating methods

A hybrid fluorescent-LED lighting system comprising a controller, LED elements, fluorescent lamp, and a color/brightness sensor, wherein the color/brightness sensor measures a combined light output of both the fluorescent lamp and the LED elements. A method for controlling the hybrid fluorescent LED lighting system includes receiving a request for brightness/color, setting a fluorescent lamp output to a particular brightness level, setting output of LEDs to a particular brightness level, measuring a combined output of the fluorescent lamp and LEDs; and adjusting the output of LEDs until the total output of the fluorescent lamp and LEDs matches the request for brightness/color. Adjusting the output of LEDs may include the step of driving a specific spectrum range of the LEDs as necessary in order to fill-in variances in a spectrum range of the fluorescent lamp. The method further allows modifying the color of light output. The method also provides a smooth transition from a current state of the lighting system to the received request for brightness/color by over-driving the LEDs beyond a steady state design rating of the LEDs.

Color-compensating Fluorescent-LED hybrid lighting

A light emitting diode (LED) assembly is provided for use as an airplane position light which meets Federal Aviation Regulation lighting requirements and lasts longer than conventional incandescent and halogen position lights, while being relatively lightweight, cheap, and requiring relatively little power for operation. The LED assembly includes a first plurality of circuit boards in electrical communication with a base circuit board, wherein each circuit board of the first plurality of circuit boards is parallel to every other one of the first plurality of circuit boards, but is disposed at an acute angle to the base circuit board. The LED assembly also includes a second plurality of circuit boards in electrical communication with the base circuit board, wherein each circuit board of the second plurality of circuit boards is disposed at a different angle to the base circuit board such that the second plurality of circuit boards form a fan-shaped structure. In addition, the LED assembly includes a plurality of light emitting diodes electrically mounted to said first plurality of circuit boards and to said second plurality of circuit boards. The circuit boards and LEDs may be identical to facilitate construction and maintenance of the aircraft position light, and to decrease the cost of manufacturing the aircraft position light. Furthermore, LEDs may be chosen to comply with Federal Aviation Regulations lighting color requirements, obviating the need for a position light cover.

Growing community of inventors

Mill Creek, WA, United States of America

Richard A Cote