Optimizing a parametric model of aircraft performance

A parametric, aircraft technology, applied in the field of avionics, to achieve the effect of ensuring convergence

Pending Publication Date: 2020-06-30
THALES SA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In fact, these methods are often not robust to variations in the actual behavior of a given aircraft compared to the behavior of the "average" (modeled) aircraft

Method used

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  • Optimizing a parametric model of aircraft performance
  • Optimizing a parametric model of aircraft performance
  • Optimizing a parametric model of aircraft performance

Examples

Experimental program
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Effect test

Embodiment Construction

[0019] [ figure 1 ] shows the effect of thrust mode and vertical guidance on parameters SEP, FF and N1.

[0020] The acronym SEP 111 for "Specific Excess Power" refers to the energy available for the aircraft to climb, which is the aircraft's ability to climb divided by its weight (this parameter is not constant).

[0021] The acronym FF for "Fuel Flow" refers to the change in fuel weight.

[0022] The acronym N1 refers to the rpm of the engine's first stage, which is the rpm that has the greatest impact on fuel consumption. The available power is strongly related to this rotational speed N1.

[0023] The parameters SEP, FF and N1 are closely related.

[0024] One approach to quantify or define the relationship between SEP, FF and N1 involves formulating a model (equation) that models these relationships.

[0025] There are multiple relationships between the parameters FF, N1 and SEP, but they mostly depend on the flight mode of the aircraft, which on the one hand breaks d...

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PUM

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Abstract

Methods and systems for optimizing the flight of an aircraft are disclosed. The trajectory is divided into segments, each of the segments being governed by distinct sets of equations, depending on engine thrust mode and on vertical guidance (climb, cruise or descent). By assuming two, aerodynamic and engine-speed, models, data from flight recordings are received and a number of parameters from a parameter-optimization engine is iteratively determined by applying a least-squares calculation until a predefined minimality criterion is satisfied. The parameter optimization engine is next used to predict the trajectory point following a given point. Software aspects and system (e.g. FMS and / or EFB) aspects are described.

Description

technical field [0001] In general terms, the present invention relates to the field of avionics. In particular, the present invention relates to methods and systems for optimizing all or some operations of an aircraft. Background technique [0002] Methods known from the prior art (eg WO 2017042166 or US9290262) are generally based on datasets modeling the performance of the aircraft. Although these performance data are known to aircraft manufacturers, they are generally not published, which presents a significant obstacle to the development of methods for optimizing aircraft operation. [0003] Furthermore, when the data are disclosed, the data (generally) describe the behavior of the aircraft type, not the behavior of a specific aircraft (ie, the data is not specific). Finally, model airplanes may not be royalty-free. [0004] Producers of systems for optimizing aircraft operation must use, where appropriate, performance data provided by the aircraft manufacturer, and m...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F30/15G06F119/14
CPCB64D45/00B64D47/00B64D2045/0075B64F5/00G01C21/20G01C21/34G05D1/0005G05D1/101G08G5/0021G08G5/0047G08G5/0052Y02T90/00G06F17/17
Inventor G·梅勒C·皮埃尔D·马丁内斯
Owner THALES SA
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