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Unreliable airspeed symbology based on pitch and power for primary flight display

A technology for aircraft and displays, applied in the field of determining pitch and power settings, can solve problems such as errors, unreliability of key flight instruments, and increased difficulty in space orientation

Active Publication Date: 2016-03-16
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

this exacerbates the difficulty of maintaining spatial orientation when these events occur at night, with no externally visible reference, as flight-critical instruments are unreliable or erroneous

Method used

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  • Unreliable airspeed symbology based on pitch and power for primary flight display
  • Unreliable airspeed symbology based on pitch and power for primary flight display
  • Unreliable airspeed symbology based on pitch and power for primary flight display

Examples

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Embodiment Construction

[0020] Modern aircraft often include an air data system and an inertial reference system. The air data system provides airspeed, angle of attack, temperature and barometric altitude data, while the inertial reference system provides altitude, flight path vector, ground speed and position data. All this data is sent to the input signal management platform of the flight control system. The flight control system includes the primary flight control computer / function and the autopilot computer / function. The main flight control computer and the autopilot computer may have independent input signal management platforms. Modern aircraft further include a display computer which controls the cockpit displays to display the used data to the pilot.

[0021] Air data information in some modern aircraft is provided by eg two ARINC706 air data computers (ADC). These computers are connected to conventional pitot tubes and static ports through airflow ducts running through the aircraft. A n...

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PUM

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Abstract

A system for displaying pitch- and power-based guidance commands and flight path information to the pilot in various display modes (climb, cruise, descent, landing) in response to conditions in which measured airborne data cannot be relied upon. This information is presented on the primary flight display in an intuitive and convenient manner when and where it is needed. The displayed information changes dynamically in response to aircraft parameters.

Description

technical field [0001] The present invention generally relates to systems and methods for determining pitch and power settings during flight when unreliable or failed airborne data systems are detected. Background technique [0002] Modern commercial aircraft place ever-increasing requirements on the availability and integrity of airborne data. The airborne data describe the state of the air mass of the aircraft surrounding the aircraft during flight. Pilots and onboard systems use this airborne data to make operational decisions and control measures regarding the aircraft. The airborne data may include, for example, pitot or total pressure, static pressure, angle of attack, angle of sideslip, and other suitable airborne data. Conventional sensors used to measure such data may be adversely affected by environmental conditions or other conditions or events. For example, ice or other foreign matter may prevent accurate measurement of pressure by a pitot tube used to measure...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C23/00
CPCG01C23/005
Inventor A·M·托热恩
Owner THE BOEING CO
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