Method for identifying airplane structure load based on flight parameter monitoring

Abstract

The invention relates to a method for identifying an airplane structure load based on flight parameter monitoring. The method comprises the following five steps: (1), recording a flight parameter and load data of an airplane structure dangerous part through a flight test; (2), performing correlation analysis on the flight parameter and the load according to the flight parameter and the load data, and selecting a load identification parameter; (3), establishing a flight parameter and load identification model according to the flight parameter and the load data of an airplane by utilizing a polynomial reconstruction technology; (4), establishing a flight parameter and load identification model according to the flight parameter and the load data of the airplane by utilizing a backward propagation artificial neural network method; and (5), substituting the flight parameter obtained by a flight parameter sensor into a polynomial identification and artificial neural network identification model so as to obtain a load to be identified. The method disclosed by the invention has the characteristics of being high in calculation precision, low in cost, convenient and rapid and capable of obtaining the load data of the airplane structure dangerous part in real time; and thus, requirements of health management and residual life detection can be satisfied.

Description

technical field

[0001] The invention provides an aircraft structure load identification method based on flight parameter monitoring, which belongs to the field of mechanical system state monitoring. Background technique

[0002] The stress spectrum of the dangerous parts of the aircraft structure is one of the prerequisites for its health management and remaining life monitoring. However, in the actual flight of the aircraft, the stress spectrum of the dangerous parts of the structure will change with the change of the flight parameters. Accurate and real-time measurement of the dangerous parts However, the monitoring and recording of flight parameters is very mature and very convenient. If the flight load can be identified according to the flight parameters and its transfer function can be obtained, it can be obtained conveniently and at low cost. Flight load information. For this reason, the present invention proposes a kind of aircraft structural load identification meth...

Examples

Embodiment Construction

[0040] figure 1 It is the block flow chart of method for the present invention, and the present invention is realized in five steps, specifically:

[0041] Step 1. Pass the flight test and record the flight parameters—the load data of the dangerous parts of the aircraft structure.

[0042] Step 2. According to the flight parameter-load data of the aircraft structure, conduct a correlation analysis on the flight parameters and flight loads, select the parameters with significant correlation as the load identification parameters, and make the flight parameters-load data dimensionless.

[0043] The relationship between the load on the dangerous part of the aircraft structure and the flight parameters can be expressed as

[0044] {F}=[C]{V} T (1)

[0045] In the formula, {F} represents the working load of the aircraft structure; {C} represents the transfer function; {V} represents the flight parameters, namely:

[0046] {V}={V,H,n y ,n z ,δ a ,δ r ,δ e ,ω y ,ω x ,ω z ,...

technical field

[0001] The invention provides an aircraft structure load identification method based on flight parameter monitoring, which belongs to the field of mechanical system state monitoring. Background technique

[0002] The stress spectrum of the dangerous parts of the aircraft structure is one of the prerequisites for its health management and remaining life monitoring. However, in the actual flight of the aircraft, the stress spectrum of the dangerous parts of the structure will change with the change of the flight parameters. Accurate and real-time measurement of the dangerous parts However, the monitoring and recording of flight parameters is very mature and very convenient. If the flight load can be identified according to the flight parameters and its transfer function can be obtained, it can be obtained conveniently and at low cost. Flight load information. For this reason, the present invention proposes a kind of aircraft structural load identification meth...

Examples

Embodiment Construction

[0040] figure 1 It is the block flow chart of method for the present invention, and the present invention is realized in five steps, specifically:

[0041] Step 1. Pass the flight test and record the flight parameters—the load data of the dangerous parts of the aircraft structure.

[0042] Step 2. According to the flight parameter-load data of the aircraft structure, conduct a correlation analysis on the flight parameters and flight loads, select the parameters with significant correlation as the load identification parameters, and make the flight parameters-load data dimensionless.

[0043] The relationship between the load on the dangerous part of the aircraft structure and the flight parameters can be expressed as

[0044] {F}=[C]{V} T (1)

[0045] In the formula, {F} represents the working load of the aircraft structure; {C} represents the transfer function; {V} represents the flight parameters, namely:

[0046] {V}={V,H,n y ,n z ,δ a ,δ r ,δ e ,ω y ,ω x ,ω z ,...

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