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Method for determining inertial navigation element performances based on flight test and theoretical calculation

A flight test and theoretical calculation technology, applied to measuring devices, instruments, etc., can solve the problems that frequency domain data cannot be measured, attitude can only measure time domain values, etc., and achieve the effect of strong versatility

Active Publication Date: 2015-04-22
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

[0004] The technical solution problem of the present invention is: the present invention proposes a kind of method based on flight test and theoretical calculation to judge the performance of inertial navigation element, the present invention measures the frequency characteristic of data frequency characteristic and theoretical flight motion mode by comparative test, thereby Analyzing the performance of the inertial navigation components and evaluating the measurement performance of the inertial navigation components can effectively solve the problem that the attitude of the UAV flight test can only measure the time domain value, but the frequency domain data cannot be measured. Performance evaluation provides a reliable means of measurement

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  • Method for determining inertial navigation element performances based on flight test and theoretical calculation
  • Method for determining inertial navigation element performances based on flight test and theoretical calculation
  • Method for determining inertial navigation element performances based on flight test and theoretical calculation

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[0032] The working principle and working process of the present invention will be further explained and illustrated below in conjunction with the accompanying drawings.

[0033] In the UAV air flight test, inertial navigation components are used to measure the flight attitude angle such as pitch angle and roll angle, but the accuracy of the measurement signal needs to be further assessed. The UAV body is equipped with an inertial navigation system that can measure the attitude angle. Components: The vertical gyroscope can measure the UAV pitch angle θ and roll angle γ. The time-domain attitude angle value measured by it is not available in the whole process. In order to stimulate the flight mode of the UAV, it is necessary to investigate the large jitter response of the UAV attitude under the condition of wind interference or flight mode change. This signal can be processed.

[0034] The frequency-domain theoretical analysis tool used is Fast Fourier Transform FFT, which can ...

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Abstract

The invention relates to a method for determining inertial navigation element performances based on a flight test and theoretical calculation. The method comprises the following steps of acquiring actual measurement frequency of an unmanned plane inertial navigation element, acquiring theoretical measurement frequency of the unmanned plane inertial navigation element, and comparing the actual measurement frequency and theoretical measurement frequency of the unmanned plane inertial navigation element, wherein if the absolute value of the difference of the two frequency values is less than or equal to a certain threshold value, the inertial navigation element can satisfy unmanned plane flight frequency measurement requirements or not, otherwise. The method solves the problem that at present, an unmanned plane with flight test attitude can only measure a time domain value and cannot measure frequency domain data, and provides a trusted measurement means for inertial navigation element performance assessment.

Description

technical field [0001] The invention relates to a method for judging the performance of inertial navigation components based on flight tests and theoretical calculations, which can effectively solve the defect that the attitude of UAV flight tests can only be measured in the time domain, but the frequency domain data cannot be measured. It provides a credible measurement method for evaluating and measuring performance status, and belongs to the technical field of unmanned aerial vehicle flight test measurement. Background technique [0002] In the UAV flight test, the assembled inertial navigation components can only measure the time domain signal of the attitude angle, but it is unknown whether the measurement meets the frequency domain requirements of the UAV flight performance. The frequency domain data processing method can be used to analyze the attitude measurement data, and Compared with the flight quality attributes of the controlled UAV, it meets the inspection requ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 苏浩秦包晓翔陈迪李平坤刘凯曾立科
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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