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Method for installing an inertial reference unit in an aircraft, and aircraft equipped in this way

An inertial navigation system, navigation system technology, applied in the field of inertial navigation system installation, can solve problems such as difficult accuracy, and achieve the effect of simplifying the installation method

Active Publication Date: 2011-10-05
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Furthermore it can be observed that it is ultimately very difficult to obtain the necessary accuracy in roll and pitch industrially (as determined by the EIRD - "Equipement Installation Requirement Document")

Method used

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  • Method for installing an inertial reference unit in an aircraft, and aircraft equipped in this way
  • Method for installing an inertial reference unit in an aircraft, and aircraft equipped in this way
  • Method for installing an inertial reference unit in an aircraft, and aircraft equipped in this way

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Embodiment Construction

[0051] figure 1 and 2 A navigation system mount 1 that can be used within the scope of the mounting method of an inertial navigation system according to the invention is shown. Typically, the navigation system support 1 comprises a pallet 2 on which the inertial navigation system is intended to be carried, and a rear wall 3 extending from a rear edge 15 of the pallet, orthogonally to the pallet 2 .

[0052] The pallet 2 is perforated to have a finite mass. The rear wall 3 has an aperture 12 intended to receive a connector (not shown) for the connection of the inertial navigation system to the aircraft's power supply and data transmission network.

[0053] The navigation system support 1 is intended to be fastened to structural elements of the aircraft by means of screws, not shown here, which pass through the pallet 2 . As an example of installation in an aircraft, such a navigation system mount has an axial direction 20 parallel to the pallet 2, which coincides with the th...

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Abstract

The invention relates to a method for installing an inertial reference unit in an aircraft, in which: a reference unit support (1) is fixed to a structural element of the aircraft; support installation angles-in heading, roll and pitch-representative of angular errors of positioning of the reference unit support relative to an aircraft coordinate system are determined, this determination being based on the measurement of coordinates of points of a previously defined reference coordinate system and of characteristic points of the reference unit support; the said support installation angles are recorded in memory means, for the purposes of subsequent correction of data measured by the inertial reference unit. Preferably the reference coordinate system used is defined by means of targets formed on the structure of a segment of the aircraft for the purposes of joining this segment with an adjacent segment.

Description

technical field [0001] The invention relates to a method for installing an inertial navigation system (centrale à inertia) in an aircraft. Background technique [0002] The attitude and heading of the aircraft are usually controlled by one or more inertial navigation systems, known by the acronym ADIRU ("Air Data Inertial Reference Unit"). The positioning of such inertial navigation systems within the aircraft needs to be particularly precise in order to provide the correct attitude and heading values ​​which are indispensable for the complete safe operation of the aircraft. [0003] Inertial navigation systems are usually attached to supports called nav system mounts, which themselves are attached to structural elements of the aircraft. Precise positioning of the inertial navigation system on its navigation system mount is readily available. Therefore, the positioning error between the inertial navigation system and its support is negligible. From this point forward, the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D45/00
CPCG01C25/005G01B11/27G01B21/24Y10T29/4978
Inventor V·布里韦T·卡尔特罗J-D·佩里
Owner AIRBUS OPERATIONS GMBH
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