Method for estimating identification error intervals of flight vehicle pneumatic parameters

Abstract

The invention discloses a method for estimating identification error intervals of flight vehicle pneumatic parameters, and is used for estimating the error intervals of the pneumatic parameters identified from flight test measuring data. On the basis of the common method for estimating a standard C-R (Cramer - Rao) bound of the parameter identification error intervals, aiming at solving the problem of too small estimating value of the error intervals when the standard C-R bound is applied to the flight test measuring data, a C-R bound correction method is derived by a principle, and the correction method can be used for accurately estimating the identification error intervals of the flight vehicle pneumatic parameters. The method for estimating the identification error intervals has the advantages that the convenience and the practicality are realized, and the error interval of each pneumatic parameter identification result is given by only needing the samples of the single flight test measuring data; and compared with the prior art, more accuracy and more reliability are realized, and a foundation is laid for applying the pneumatic parameters identified from the flight test measuring data into the design and improvement of the flight vehicle.

Description

technical field [0001] The invention belongs to the field of aircraft system identification and relates to a method for estimating the error interval of an aircraft aerodynamic parameter identification result. Background technique [0002] For the maximum likelihood identification of aircraft aerodynamic parameters, the C-R circle gives the best theoretical prediction of the parameter identification error interval, which is widely used to determine the aircraft aerodynamic parameter identification error interval, the prerequisite is that the observation noise is Gaussian White Noise. However, the practice of aerodynamic parameter identification of flight test measurement data shows that the statistical value of the sample standard deviation of the aerodynamic parameter identification results of multiple flight tests is several times higher than that of the C-R boundary. "Determination of Stability and Control Parameter of a Light Airplane from Flight Data Using Two Estimati...

AI Technical Summary

Problems solved by technology

[0003] The technical problem to be solved by the present invention is: on the basis of the commonly used parameter identification error interval estimation standard C-R boundary, aiming at the problem that the value of the estimated result is too small when it is applied to the flight test measurement data, a C-R boundary is obtained through theoretical derivation Correction method, using this correction method can more accurately estimate the aircraft aerodynamic parameter identification error interval

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