The Boeing Company

Other

Charles E Kaul

James Louis Tylee

Elham Boozarjomehri

Robert Edwin Root

Michael E Irrgang

Andrew E Hall

Andrea De Klerk

A device for tail-specific parameter computation includes a memory, a network interface, and a processor. The memory is configured to store a tail-specific aircraft performance model for a first aircraft of an aircraft type. The tail-specific aircraft performance model is based on historical flight data of the first aircraft and a nominal aircraft performance model associated with a second aircraft of the aircraft type. The network interface is configured to receive flight data from a databus of the first aircraft. The processor is configured to generate, based at least in part on the flight data and the tail-specific aircraft performance model, a recommended cost index and a recommended cruise altitude. The processor is also configured to provide the recommended cost index and the recommended cruise altitude to a display device.

Systems and methods for tail-specific parameter computation

Techniques to increase accuracy of estimating fuel for an aircraft. A statistical analysis is performed on data for multiple past instances of flights between a departure airport and an arrival airport for multiple aircraft to determine one or more predicted real-world limitations more stringent than what is imposed by a set of regulations. A calibration flight plan is generated based on an operator flight plan and the one or more predicted real-world limitations. The calibration flight plan includes an airborne operating parameter that conforms to the one or more predicted real-world limitations. Based on the calibration flight plan, a first fuel load is calculated for the aircraft travelling from the departure airport to the arrival airport.

Aircraft fuel optimization analytics

Method and system for providing optimal, achievable flight plans for a flight of an aircraft and for providing accurate fuel load calculations. The method and system can check for and correct inaccurate assumptions in a flight plan. The method and system can also perform statistical analysis to recognize and account for real-world limitations on flight plans. The method and system can also perform statistical analysis to determine actual aircraft wear that can affect aircraft performance and account for such wear when calculating fuel load.

An active, electro-optical display system for use on fixed-wing, land-based airport runways, is disclosed for remotely guiding a pilot during visual approach and landing of an aircraft. Conventional Microwave Landing System (MLS) ground-transmitted data is air-derived on board the aircraft and data-linked to a ground receiver to produce a continuous digital data signal indicative of aircraft slant range, elevation and azimuth relative to the desired landing position. The resulting data signal is electrically coupled to a signal processor governed in accordance with control guidance laws to produce three discrete signals indicative of the magnitude and direction of the descent rate error, the flight path acceleration, and the lateral drift rate of the aircraft relative to the intended landing area. The three control signals are respectively coupled to display drivers which produce a plurality of drive signals for energizing individual light cells in horizontally oriented linear arrays located adjacent to the runway. The resulting light signals provide a continuous visual indication of the flight path acceleration and flight path angular error, in the elevation and azimuth planes, for appropriate corrective action by the pilot.

Active visual display system for remote three-axis flight path guidance

An electro-optical display system, particularly useful aboard aircraft carriers, is disclosed for remotely aiding a pilot in the landing of an aircraft. A conventional radar receiver continuously tracks the aircraft and produces a digital data signal indicative of aircraft slant range and elevation angle. The digital data signal is provided to a signal processor governed in accordance with either of a pair of control guidance algorithms to produce a control signal indicative of the magnitude and direction of an error in the appropriate descent rate of the aircraft. Based upon the control signal, a display driver produces a plurality of drive signals for energizing discrete light cells in vertically-oriented arrays as a visual indication of the descent rate error for appropriate corrective action by the pilot.

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Prescott, AZ, United States of America

Charles E Kaul