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Method for preprocessing temperature measurement data of aircraft surface heat flow identification device

A technology of data preprocessing and temperature measurement, which is applied to thermometers, measuring devices, and thermometers using electric/magnetic elements that are directly sensitive to heat, can solve the problems that it is difficult to identify effective input conditions for heat flow identification, and the quality of measurement data is not high. Achieve improved impact, increased accuracy and reliability

Active Publication Date: 2018-04-24
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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Problems solved by technology

[0006] The technical solution of the present invention is to provide a preprocessing method for the temperature measurement data of the aircraft surface heat flow identification device, which can provide reasonable heat flow identification for the current problem that the measurement data of the heat flow identification component is not high in quality and difficult to be used as an effective input condition for heat flow identification. The temperature data input can effectively improve the influence of temperature steps and local jump points on the heat flow identification results, and improve the accuracy and reliability of the heat flow identification results

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  • Method for preprocessing temperature measurement data of aircraft surface heat flow identification device
  • Method for preprocessing temperature measurement data of aircraft surface heat flow identification device
  • Method for preprocessing temperature measurement data of aircraft surface heat flow identification device

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[0050] Figure 4(a) and Figure 4(b) show the overall and local curves of the original data, polynomial fitting data and smoothed data of a typical flight test heat flow identification device, respectively. The processing results of these methods are in good agreement with the original data curves, but from a local point of view, the preprocessing results of the present invention are more consistent with the original data, and can more accurately reflect the changes of the original data.

[0051] Figures 5(a) and 5(b) show the overall and partial enlarged views of the original temperature measurement data and the smoothed data of different point data of a typical flight test heat flow identification device, respectively. Among them, the temperature results of smoothing with N=200, 400, and 800 adjacent data points are given. From a macroscopic point of view, the smoothing results of different points are almost the same. It can be seen from the partial enlarged image that there ar...

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Abstract

The present invention provides a method for preprocessing temperature measurement data of an aircraft surface heat flow identification device, and belongs to the technical field of aerospace flight test thermal parameter measurement and processing. The method comprises: carrying out local distortion point (local hop point) removal processing on the temperature rise measurement data of the heat flow identification device, using the average smooth processing method of N adjacent data points to carry out smooth processing on the measurement data, and finally obtaining temperature measurement datasatisfying the requirement of heat flow identification, wherein the N value is determined according to temperature sensor related parameters and temperature profile characteristics. By virtue of themethod provided by the present invention, heat flow identification can be carried out on the preprocessed temperature measurement data, the influence of the temperature hop and the local hop point onthe heat flow identification result can be effectively improved, and the accuracy and reliability of the identification result of the heat flow can be improved.

Description

technical field [0001] The invention relates to a method for preprocessing temperature measurement data of an aircraft surface heat flow identification device, which is suitable for preprocessing measurement data of current hypersonic aircraft flight tests, and belongs to the technical field of thermal parameter measurement and processing for aerospace flight tests. Background technique [0002] The aerodynamic heating environment on the surface of hypersonic aircraft is harsh, and the aircraft thermal insulation system is faced with severe challenges, which puts forward strict requirements on the design accuracy and conservative quantities of the aircraft thermal insulation system. The accurate prediction of the aerodynamic heating environment and distribution is the premise and foundation of the refined design of the thermal insulation system. At present, subject to the status quo of aerodynamic thermal environment prediction technology, the thermal environment prediction ...

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Application Information

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IPC IPC(8): G06K9/00G01K7/02
CPCG01K7/02G06F2218/02
Inventor 李宇聂亮黄建栋檀妹静聂春生刘宇飞王迅袁野蒋云淞曹占伟王振峰周禹陈敏
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
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