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Inertia and ADS height fusion method based on air pressure reference adaptive correction

A technology of barometric altitude and fusion method, which is applied in altitude/horizontal measurement, character and pattern recognition, and navigation through speed/acceleration measurement, etc. It can solve the problems of inconsistency of altitude measurement information reference, difficulty in ensuring flight safety, and barometric reference switching Jump and other problems, to improve navigation accuracy, ensure safe interval and stable flight, and enhance robustness

Active Publication Date: 2022-03-25
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS +1
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Problems solved by technology

[0005] The technical problem to be solved by the present invention is: aiming at the problems that the altitude measurement information output by the inertial navigation system and the atmospheric data system are not uniform, the barometric reference switching jumps, and the flight safety in the vertical direction is difficult to be guaranteed within the scope of the entire aviation field. A fusion method of inertial and ADS altitude based on adaptive correction of barometric reference is proposed
Solve the altitude jump problem when the barometric reference is switched by designing a suitable barometric reference adaptive correction strategy

Method used

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  • Inertia and ADS height fusion method based on air pressure reference adaptive correction
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  • Inertia and ADS height fusion method based on air pressure reference adaptive correction

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Embodiment

[0227] In this simulated track use case, the results of the vertical altitude error before and after correction when the barometric reference is switched during the whole flight segment are shown in Table 1.

[0228] Table 1 Altitude error results in the vertical direction before and after correction when the barometric reference is switched for the whole flight segment

[0229]

[0230] It can be seen that the inertial and ADS height fusion method based on the self-adaptive correction of the air pressure reference in the present invention keeps the vertical height error of the aircraft in the entire voyage at the meter level, improves the navigation accuracy in the vertical direction of the entire voyage of the aircraft, and solves the problem of air pressure at the same time. The jump problem of height error at the reference switching point ensures the stability of the navigation system.

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Abstract

The invention discloses an inertia and ADS height fusion method based on air pressure reference self-adaptive correction, and the method comprises the steps: designing a self-adaptive correction strategy for solving the problem that the air pressure height outputted by an air data system ADS is suddenly changed due to air pressure reference switching in a full leg range, and guaranteeing the smooth transition during the air pressure reference switching; the height reference in the vertical direction is unified, it is ensured that height measurement information of an inertial navigation system (INS) and height measurement information of an atmosphere data system are both based on a WGS-84 reference ellipsoid, and a foundation is laid for multi-source navigation information fusion; through combined navigation, effective fusion of multi-source height information in the vertical direction is realized. The method improves the navigation precision of the navigation system in the aviation field in the vertical direction of the full flight segment, and can guarantee the safe flight of an aircraft.

Description

technical field [0001] The invention relates to an inertial and ADS height fusion method based on self-adaptive correction of air pressure reference, which belongs to the technical field of integrated navigation. Background technique [0002] With the continuous increase of civil aviation airspace traffic, it is very important to make reasonable use of the vertical safety distance between aircraft and ensure the high safety and high reliability of aircraft in the vertical direction. The operational requirements such as "Reduced Vertical Separation (RVSM)" implemented by civil aviation aircraft have more stringent requirements for improving the navigation accuracy of the aircraft in the vertical direction. [0003] Most of the navigation systems used by modern civil aviation aircraft are integrated navigation systems based on inertial navigation systems (INS). The inertial navigation system can estimate the ellipsoid altitude of the aircraft relative to the WGS-84 ellipsoid,...

Claims

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Application Information

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IPC IPC(8): G01C5/00G01C5/06G01C21/16G06K9/62
CPCG01C5/00G01C5/005G01C5/06G01C21/165G06F18/25
Inventor 瞿潇炜赖际舟李志敏吕品
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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