Stabilised estimation of the pitch angles of an aircraft

一种飞行器、姿态角的技术，应用在飞行器的驾驶辅助领域，能够解决偏差大、无法包括姿态单元等问题

Active Publication Date: 2011-09-21
EUROCOPTER
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] The disadvantage of this application is that it no longer compensates for any changes in the gyro measurement bias after the bias has consolidated
With current technology, such MEMS gyros have biases that are too large for them to be included in the attitude unit

Method used

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  • Stabilised estimation of the pitch angles of an aircraft
  • Stabilised estimation of the pitch angles of an aircraft
  • Stabilised estimation of the pitch angles of an aircraft

Examples

Experimental program
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Embodiment Construction

[0079] exist Figures 1 to 6 In , the general reference numeral 1 designates the aircraft. exist Figure 2 to Figure 5 Among them, the aircraft 1 is a helicopter but is not limited to a helicopter.

[0080] exist figure 1 In it, various parts of the pilot assistance device on board the aircraft 1 according to the invention can be seen. Specifically, the aircraft 1 includes an attitude unit 2 . By way of example, reference numeral 2 designates the “AHRS” system of the aircraft 1 and / or emergency instruments such as Integrated Electronic Backup Instruments (IESI). In general, in the aircraft 1 , systems and emergency instruments of the AHRS type are found to be present.

[0081] The unit 2 specifically includes a computing virtual platform 3 .

[0082] The platform 3 performs calculations to maintain an estimate of the direction of the navigation axis, this estimate is subject to three angular errors: the two angles of inclination with respect to the actual horizontal pla...

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PUM

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Abstract

The present invention relates to estimating the attitude angles of an aircraft (1). The estimated attitude angles are generated by a device (9) that performs algorithmic integration on inertial measurements indicative of an angular velocity and of a linear acceleration. Horizontal components (34-39) of desired corrections are obtained by a linear combination of two horizontal components (32-33), with cross coefficients between said horizontal axes being continuous variable over time and dependent on the estimated rate of turn. As a result, the estimated attitude angles are stable, and the biases of the gyros continue to be estimated, including during stages during which the aircraft (1) is turning.

Description

technical field [0001] The general field of the invention is that of pilot assistance for aircraft. [0002] In particular, the invention relates to measuring the attitude of such aircraft. In general, the invention applies to gesture units. These measurements are primarily used by the pilot of the aircraft (by piloting the flight display (PFD)) or the display used by the flight display system (FDS), and by the autopilot system or automatic flight control system (AFCS). Background technique [0003] Among the attitude units considered, the invention is applicable, for example, to so-called Attitude and Heading Reference Systems (AHRS) or indeed to emergency instruments known as Integrated Electronic Standby Instruments (IESE). [0004] An example of an attitude and heading measurement system is described in document FR2614694. [0005] Document FR2614694 describes a unit with three detection assemblies that deliver respectively the gyroscopic, acceleration and magnetomete...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24B64C13/18
CPCG01C21/16G01C21/185G01C21/188
Inventor J·P·佩蒂珑
Owner EUROCOPTER
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