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Primary flight display pitch- and power-based unreliable airspeed symbology

An aircraft and display technology, applied in the field of determining pitch and power settings, can solve problems such as unreliable flight key instruments, aggravating the difficulty of spatial orientation, and errors

Active Publication Date: 2014-02-05
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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  • Primary flight display pitch- and power-based unreliable airspeed symbology
  • Primary flight display pitch- and power-based unreliable airspeed symbology
  • Primary flight display pitch- and power-based unreliable airspeed symbology

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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Abstract

A system for displaying pitch- and power-based guidance commands and flight path information for a variety of display modes (climb, cruise, descent, landing) to pilots in response to situations wherein the measured air data should not be relied upon. This information is presented in an intuitive and expedient manner exactly when and where it is needed on the primary flight display. The displayed information dynamically changes in response to airplane 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 Applications(China)
IPC IPC(8): G01C23/00
CPCG01C23/005
Inventor A·M·托热恩
Owner THE BOEING CO
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