Airplane aerodynamic parameter partition multi-step identification method adopting acceleration observer

Abstract

The invention discloses an airplane aerodynamic parameter partition multi-step identification method adopting an acceleration observer, and the problem in aerodynamic parameter identification performed according to the flight data in the prior art is partly solved. A aircraft angular acceleration observer, flight data multiple partition and information matrix singular value decomposition are as a core of the method. The characteristics and the advantages of the method comprises: the angular acceleration is accurately estimated by adopting a prediction observer of uniform acceleration model, an accurate aerodynamic moment coefficient is calculated by adopting a kinetic equation of the aircraft, so that the problem of the inaccurate estimation of the angular acceleration is effectively solved; the flight data collinearity question is detected and estimated through the singular value decomposition, so that the identifiable part of the aerodynamic parameter item can be accurately obtained; under the quasi-steady assumption, a linear model of aerodynamic parameter in each section is established through the flight data multiple partition, each aerodynamic parameter can be effectively identified by adopting the least square method, and the method is suitable for the large maneuvering flight data.

Description

technical field [0001] The invention belongs to the field of aircraft parameter identification, in particular to an aerodynamic parameter identification method based on aircraft flight data. Background technique [0002] The aerodynamic parameters of the aircraft are identified based on flight data, which can verify theoretical calculations and wind tunnel test results, and provide a more accurate aerodynamic model for aircraft testing and performance verification. At present, there are mainly three problems in the identification of aerodynamic parameters based on flight data: [0003] First, to solve the aerodynamic moment according to the dynamic equation of the aircraft, it is necessary to know the accurate angular acceleration in advance. Aircraft generally do not install angular acceleration sensors, so it is necessary to calculate the angular velocity measured by the angular velocity sensor, and methods such as numerical differentiation and filtering are often used. ...

AI Technical Summary

Problems solved by technology

At high angles of attack, especially stall angles of attack, the aircraft often does not have a traditional trim state, and this method cannot be used for identification

Images