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Method for monitoring integrity of aircraft heading data source

A technology for aircraft heading and integrity, which is applied in the field of aircraft cockpit display systems and can solve problems such as increasing aircraft development costs.

Pending Publication Date: 2019-01-01
CHINESE AERONAUTICAL RADIO ELECTRONICS RES INST
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  • Abstract
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Problems solved by technology

In order to improve the integrity of the heading display, the usual method is to increase the hardware redundancy, improve the design of the inertial navigation system, and improve the integrity of the data source, but this method will increase the cost of aircraft development

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  • Method for monitoring integrity of aircraft heading data source
  • Method for monitoring integrity of aircraft heading data source
  • Method for monitoring integrity of aircraft heading data source

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Embodiment Construction

[0016] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0017] In order to reduce the cost of aircraft development, the integrity monitoring method of the aircraft heading data source shown in this embodiment is to use the heading output by the aircraft backup instrument to monitor the integrity of the heading output by the inertial navigation system, but the heading output by the aircraft backup instrument is susceptible to External magnetic field interference needs to be checked to eliminate the influence of the interfering magnetic field. The World Geomagnetic Model WMM can be used to verify the correctness of the backup instrument magnetic heading. The World Geomagnetic Model (WMM) is a mathematical model of the Earth's main magnetic field, which can be used to calculate the characteristic quantities of the geomagnetic field at any point around the world. Since the long-term changes of the Ear...

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Abstract

The invention discloses a method for monitoring integrity of an aircraft heading data source. The method comprises the following steps: 1. calculating a three-dimensional geomagnetic field strength and a magnetic difference of a current position of an aircraft; 2. using the magnetic difference to convert magnetic heading outputted by an backup instrument into a true heading; 3. using the backup instrument to measure the three-dimensional geomagnetic field strength; 4. detecting whether the aircraft has maneuver. If the maneuver not exists, proceeds to step 5; 5. if the calculated three-dimensional geomagnetic field strength and the three-dimensional geomagnetic field strength measured by the backup instrument are less than a set threshold, the magnetic heading output of the backup instrument is correct, and proceeds to step 6; 6. using the true heading output of an inertial navigation system and the true heading obtained in step 2 to generate a heading residual, and testing the residual to determine whether the heading of the inertial navigation system meets integrity requirements. The method for monitoring the integrity of the aircraft heading data source improves the integrity ofthe aircraft heading data source without increasing hardware cost, thereby improving the safety of the aircraft.

Description

technical field [0001] The invention relates to an aircraft cockpit display system, in particular to the integrity monitoring of heading data sources in the cockpit display system. Background technique [0002] The heading of the aircraft is generally displayed on the main flight display and navigation display, which is the key information for the pilot to control the aircraft and navigate. Wrong heading display may lead to serious accidents. For transport aircraft, the probability of simultaneous wrong headings of the pilot and co-pilot is required to be less than 10 -7 / Hour. [0003] Heading data typically comes from an inertial navigation system. In order to improve the integrity of the heading display, the usual method is to increase the hardware redundancy, improve the design of the inertial navigation system, and improve the integrity of the data source, but this method will increase the cost of aircraft development. Contents of the invention [0004] The purpose...

Claims

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 谷青范吴狄李文辉周元辉
Owner CHINESE AERONAUTICAL RADIO ELECTRONICS RES INST
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