Aircraft structure state characteristic parameter standard value determination method

Abstract

The invention provides an aircraft structure state characteristic parameter standard value determination method, which belongs to the technical field of aircraft structure health monitoring, and comprises the following steps: hierarchically dividing aircraft structure state characteristic parameters into global structure characteristic parameters and local structure characteristic parameters according to the capability of reflecting the current situation of aircraft health key indexes; determining the global structure feature parameters and specific feature parameters contained in the local structure feature parameters according to whether the global use state of the whole aircraft structure or the failure mode of the local structure of the aircraft can be reflected; classifying specific feature parameters contained in the global structure feature parameters and the local structure feature parameters according to the design states of the global structure feature parameters and the local structure feature parameters; determining a standard extreme value of each specific characteristic parameter according to the variation condition of each specific characteristic parameter after classification; and according to the standard extreme value of the specific characteristic parameter, obtaining a standard value interval of the global structure characteristic parameter and the local structure characteristic parameter of each level of the aircraft.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural health monitoring technology, and specifically relates to a method for determining the standard values ​​of characteristic parameters of aircraft structural conditions. Background Technology

[0002] In aircraft structural health monitoring, due to the complexity and diverse manifestations of the state characteristic parameters of aircraft structures, existing technologies have not established clear distinguishing boundaries and classification criteria, and lack methods for determining standard values ​​of health monitoring characteristic parameters for global and local aircraft structures.

[0003] Therefore, a method is needed to determine the standard values ​​of characteristic parameters for aircraft structural health monitoring, in order to establish evaluation standards for characteristic parameters at different levels of the aircraft and to define the standard values ​​of characteristic parameters for global and local structures. Summary of the Invention

[0004] The purpose of this application is to provide a method for determining standard values ​​of aircraft structural state characteristic parameters to solve or mitigate at least one problem in the prior art.

[0005] The technical solution of this application is: a method for determining the standard values ​​of aircraft structural state characteristic parameters, including:

[0006] Based on their ability to reflect the current status of key aircraft health indicators, aircraft structural state characteristic parameters are classified into global structural characteristic parameters and local structural characteristic parameters according to their hierarchy.

[0007] Based on whether it can reflect the overall operational status of the aircraft structure or the failure mode of a local structure, the specific characteristic parameters contained in the global structural characteristic parameters and the local structural characteristic parameters are determined.

[0008] Based on the design state of the global structural feature parameters and the local structural feature parameters, the specific feature parameters contained in the global structural feature parameters and the local structural feature parameters are classified.

[0009] Based on the variation of each specific feature parameter after classification, determine the standard extreme value of each specific feature parameter;

[0010] Based on the standard extreme values ​​of specific characteristic parameters, the standard value ranges of global and local structural characteristic parameters at each level of the aircraft are obtained.

[0011] Preferably, the global structural feature parameters are parameters that describe the overall operational status of the aircraft corresponding to key indicators of the overall structural health of the aircraft;

[0012] Local structural characteristic parameters are parameters that describe the failure modes corresponding to key health indicators of aircraft components or critical structures.

[0013] Preferably, the information parameter cluster that can reflect the overall operational status of the aircraft structure is as follows: For structural state information parameters Make a judgment if the structural state information parameters Then the structural state information parameter is the global structural feature parameter;

[0014] Information clusters that can reflect the failure modes of local structures of an aircraft are For structural state information parameters Make a judgment if the structural state information parameters If the structural state information parameter is then a local structural feature parameter, then the structural state information parameter is a local structural feature parameter.

[0015] Preferably, the information parameter cluster This includes takeoff and landing information parameters, flight information parameters, flight payload information parameters, flight environment information parameters, and mission information parameters;

[0016] The information cluster N includes load information parameters, strain information parameters, damage monitoring information parameters, vibration information parameters, and local environmental monitoring information parameters.

[0017] Preferably, based on the design state of the global structural characteristic parameters, the overall structural characteristic parameters are divided into two categories: the first category is the global structural basic flight characteristic parameter M1, which reflects the basic flight state of the aircraft; the second category is the global structural overall load characteristic parameter M2, which reflects the overall load on the aircraft. Further judgment is made on the specific characteristic parameters of the global structural characteristic parameters. If the specific characteristic parameter MK of the global structural characteristic parameters exhibits load characteristics, then... ,otherwise ;

[0018] Based on the design state of local structural characteristic parameters, these parameters are divided into two main categories: the first category, N1, reflects the local structural damage development characteristics, including strain, damage, and environmental factors; the second category, N2, reflects the local structural load characteristics, including the load spectrum. The specific characteristic parameters of each local structural parameter are then evaluated. If the specific characteristic parameter NK exhibits load characteristics, then... ,otherwise .

[0019] Preferably, the design state of each specific characteristic parameter includes two levels of variation, including changes in the structural characteristic parameters that differ from the initial state or predicted state of the aircraft structural design.

[0020] After classification, the standard extreme value λ of each specific feature parameter is the range of values ​​formed by the structural feature parameter T corresponding to the initial state P of the aircraft structural design or the attenuation state predicted by the structural design, and the positive and negative errors Δ introduced during the acquisition of feature parameters, i.e.: .

[0021] Preferably, the standard value ranges of global and local structural characteristic parameters at each level of the aircraft are ranges composed of the standard extreme values ​​of various specific characteristic parameters determined based on the identification of specific characteristic parameter variations, i.e. .

[0022] The method for determining the standard values ​​of characteristic parameters of aircraft structural health status in this application establishes evaluation standards for characteristic parameters of different levels of aircraft structure by defining and classifying characteristic parameters of global or local structures, thereby realizing the definition of standard values ​​of characteristic parameters of global and local structures. Attached Figure Description

[0023] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0024] Figure 1 This is a schematic diagram illustrating the method for determining the standard values ​​of characteristic parameters of aircraft structural health status in this application. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0026] This application proposes a method for determining the standard values ​​of characteristic parameters of aircraft structural health status. For the health monitoring characteristic parameters of different levels of aircraft structure, by defining and classifying the characteristic parameters of global or local structures, the method establishes the evaluation standards of characteristic parameters of different levels of aircraft, and realizes the definition of the standard values ​​of characteristic parameters of global or local structures.

[0027] like Figure 1 As shown, the method for determining the standard values ​​of aircraft structural state characteristic parameters proposed in this application includes the following steps:

[0028] Step S1: Based on the ability to reflect the current status of key aircraft health indicators, the aircraft structural state characteristic parameters are divided into global structural characteristic parameters and local structural characteristic parameters according to their levels.

[0029] In this application, the structural characteristic parameters of the aircraft are divided into two levels. The first level consists of parameters that describe the overall operational status of the aircraft corresponding to the key health indicators of the overall aircraft structure. These parameters are called global structural characteristic parameters. The second level consists of parameters that describe the failure modes corresponding to the key health indicators of aircraft components or key structures (collectively referred to as local structures of the aircraft). These parameters are called local structural characteristic parameters.

[0030] Step S2: Determine the specific characteristic parameters contained in the global structural characteristic parameters and the local structural characteristic parameters based on whether they can reflect the global operational status information of the aircraft structure or the status information of the failure modes of the local structure.

[0031] The information parameter cluster that can reflect the overall operational status of the aircraft structure is This includes takeoff and landing information parameters, flight information parameters, flight load information parameters, flight environment information parameters, and mission information parameters. Structural state information parameters... Make a judgment if the structural state information parameters If the structural state information parameters are such that the pitch angle, yaw angle, roll angle, and sideslip angle are considered flight information parameters, then these four structural state information parameters are global structural characteristic parameters.

[0032] Table 1 shows some of the global structural feature parameters determined according to the above process in this embodiment of the application.

[0033] Table 1. Global structural characteristic parameters (partial)

[0034] Serial Number Feature parameters 1 Overload G-force of the maneuver limit 2 Cruise speed V 3 Flight altitude H 4 Pitch angle 5 Yaw angle 6 Incline angle 7 Sideslip angle 8 Center of gravity normal overload 9 Lateral overload at the center of gravity 10 Heading overload at center of gravity

[0035] Information clusters that can reflect the failure modes of local structures of an aircraft are This includes load information parameters, strain information parameters, damage monitoring information parameters, vibration information parameters, and local environmental monitoring information parameters. (The text also mentions structural state information parameters.) Make a judgment if the structural state information parameters If the structural state information parameter is a local structural characteristic parameter, then the crack length is a damage monitoring information parameter.

[0036] Table 2 shows some of the aircraft local structural feature parameters determined according to the above process in this embodiment of the application.

[0037] Table 2. Local structural characteristic parameters (partial)

[0038] Serial Number Feature parameters 1 Vertical overload at the center of gravity of the right outer wing 2 Vertical overload at the center of gravity of the left outer wing 3 Crack length L

[0039] Step S3: Based on the design status of the global structural feature parameters and the local structural feature parameters, classify the specific feature parameters contained in the global structural feature parameters and the local structural feature parameters.

[0040] Based on the design state of the global structural characteristic parameters, this application divides the overall aircraft structural characteristic parameters into two main categories: the first category consists of parameters M1 reflecting the basic flight state of the aircraft (i.e., the basic flight characteristic parameters of the global structure), such as flight altitude, speed, time, and aircraft attitude angles; the second category consists of parameters M2 reflecting the overall load on the aircraft (i.e., the overall load characteristic parameters of the global structure), such as three-dimensional overload at the center of gravity, cabin pressurization value, and landing center of gravity sinking speed. Further evaluation of the specific characteristic parameters of the global structural characteristic parameters is then conducted. If the specific characteristic parameter MK exhibits load characteristics, then... ,otherwise .

[0041] Tables 3 and 4 show the first type of parameter M1 and the second type of parameter M2 after further classification of the global structural feature parameters in this embodiment of the application.

[0042] Table 3. Basic Flight Characteristic Parameters of Global Structure M1

[0043] Serial Number Feature parameters 1 Overload limiting maneuver 2 cruising speed 3 Flight altitude 4 Pitch angle 5 Yaw angle 6 Incline angle 7 Sideslip angle

[0044] Table 4 Global structural load characteristic parameter M2

[0045] Serial Number Feature parameters 1 Center of gravity normal overload 2 Lateral overload at the center of gravity 3 Heading overload at center of gravity

[0046] Based on the design state of local structural characteristic parameters, this application also divides the local structural characteristic parameters into two main categories: the first category is parameter N1 (i.e., local structural damage development characteristic parameters) that reflects the strain, damage, and environment of the local structure, including crack length, corrosion depth, etc.; the second category is parameter N2 (i.e., local structural load characteristic parameters) that reflects the load spectrum of the local structure, mainly the load parameters of parts such as the fuselage, wing, tail, moving wing surface, engine mounts, landing gear, and control system. The specific characteristic parameters of the local structural characteristic parameters are judged; if its specific characteristic parameter NK exhibits load characteristics, then... ,otherwise .

[0047] Tables 5 and 6 show the first type of parameter N1 and the second type of parameter N2 after further classification of the local structural feature parameters in this embodiment of the application.

[0048] Table 5 Local structural load characteristic parameters N2

[0049] Serial Number Feature parameters 1 Vertical overload at the center of gravity of the right outer wing 2 Vertical overload at the center of gravity of the left outer wing

[0050] Table 6 Characteristic parameters of local structural damage development N1

[0051] Serial Number Feature parameters 1 Crack length L

[0052] Step S4: Determine the standard extreme values ​​of each specific feature parameter based on the variation of each specific feature parameter after classification.

[0053] In this application, the design state of each specific characteristic parameter includes two levels of variation, including changes in the structural characteristic parameters that differ from the initial state or predicted state of the aircraft structural design.

[0054] After classification, the standard extreme value λ of each specific feature parameter is the range of values ​​formed by the structural feature parameter T corresponding to the initial state P of the aircraft structural design or the attenuation state predicted by the structural design, and the positive and negative errors Δ introduced during the acquisition of feature parameters, i.e.: .

[0055] Tables 7 to 10 show the standard extreme values ​​of the specific feature parameters determined in this embodiment of the application.

[0056] Table 7 Standard extreme values ​​of basic flight characteristic parameters of global structure

[0057] Serial Number Standard extreme values ​​of characteristic parameters 1 Maximum maneuvering limit overload Gmax 2 Maximum cruising speed Vmax 3 Maximum flight altitude Hmax 4 Maximum pitch angle Apmax 5 Maximum yaw angle (Aymax) 6 Maximum tilt angle Atmax 7 Maximum sideslip angle Asmax 8 Minimum pitch angle Apmin 9 Minimum yaw angle Aymin 10 Minimum tilt angle Atmin 11 Minimum sideslip angle Asmin

[0058] Table 8 Standard extreme values ​​of global structural load characteristic parameters

[0059] Serial Number Standard extreme values ​​of characteristic parameters 1 Maximum center of gravity normal overload Gzmax 2 Lateral overload at maximum center of gravity (Gymax) 3 maximum center of gravity yaw overload Gxmax 4 Normal overload at minimum center of gravity Gzmin 5 Lateral overload at minimum center of gravity (Gymin) 6 Heading overload at minimum center of gravity Gxmin

[0060] Table 9 Standard extreme values ​​of characteristic parameters of local structural loads

[0061] Serial Number Standard extreme values ​​of characteristic parameters 1 Maximum vertical overload at the center of gravity of the right outer wing (Grjymax) 2 Maximum vertical overload at the center of gravity of the left outer wing (Gljymax) 3 Minimum vertical overload at the center of gravity of the right outer wing (Grjymin) 4 Minimum vertical overload at the center of gravity of the left outer wing (Gljymin)

[0062] Table 10 Standard values ​​of characteristic parameters for the development pattern of local structural damage

[0063] Serial Number Standard extreme values ​​of site damage 1 Crack length L

[0064] Step S5: Based on the standard values ​​of each specific feature parameter, obtain the standard value ranges of global structural feature parameters and local structural feature parameters at each level of the aircraft.

[0065] The standard value range of global or local structural characteristic parameters at each level of the aircraft is an interval composed of the standard extreme values ​​of various specific characteristic parameters determined based on the identification of anomalies in specific characteristic parameters, i.e. .

[0066] Table 11 shows the overall structural feature parameters and their standard values ​​obtained in this embodiment of the application.

[0067] Table 11 Global structural characteristic parameters and their standard values

[0068] Serial Number Parameter Name Standard Value Range 1 Overload limit range for maneuverability (Gmin, Gmax) 2 Standard range of flight speed (Vmin, Vmax) 3 Flight altitude standard range (Hmin, Hmax) 4 Standard range of sideslip angle (Asmin, Asmax) 5 Standard range of tilt angle (Atmin, Atmax) 6 Standard range of pitch angles (Apmin, Apmax) 7 Standard range of yaw angle (Aymin, Aymax) 8 Standard range of normal overload at the center of gravity (Gzmin, Gzmax) 9 Standard range of lateral overload at the center of gravity (Gymin, Gymax) 10 Standard range of heading overload at the center of gravity (Gxmin, Gxmax)

[0069] Table 12 shows the local structural feature parameters and their standard values ​​obtained in this embodiment of the application.

[0070] Table 12 Local structural characteristic parameters and their standard values

[0071] Serial Number Parameter Name Standard Value Range 1 Vertical overload standard value range at the center of gravity of the right outer wing (Grjymin, Grjymax) 2 Standard range of vertical overload at the center of gravity of the left outer wing (Gljymin, Gljymax) 3 Standard range of crack length (Lmin, Lmax)

[0072] The method for determining the standard values ​​of characteristic parameters of aircraft structural health status in this application establishes evaluation standards for characteristic parameters of different levels of aircraft structure by defining and classifying characteristic parameters of global or local structures, thereby realizing the definition of standard values ​​of characteristic parameters of global and local structures.

[0073] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for determining standard values ​​of aircraft structural state characteristic parameters, characterized in that, include: Based on their ability to reflect the current status of key aircraft health indicators, aircraft structural state characteristic parameters are classified into global structural characteristic parameters and local structural characteristic parameters according to their hierarchy. Based on whether it can reflect the overall operational status of the aircraft structure or the failure mode of a local structure, the specific characteristic parameters contained in the global structural characteristic parameters and the local structural characteristic parameters are determined. Based on the design state of the global structural feature parameters and the local structural feature parameters, the specific feature parameters contained in the global structural feature parameters and the local structural feature parameters are classified. Based on the variation of each specific feature parameter after classification, determine the standard extreme value of each specific feature parameter; Based on the standard extreme values ​​of specific characteristic parameters, the standard value ranges of global and local structural characteristic parameters at each level of the aircraft are obtained.

2. The method for determining standard values ​​of aircraft structural state characteristic parameters as described in claim 1, characterized in that, The global structural feature parameters are parameters that describe the overall operational status of the aircraft corresponding to the key indicators of the overall structural health of the aircraft. Local structural characteristic parameters are parameters that describe the failure modes corresponding to key health indicators of aircraft components or critical structures.

3. The method for determining the standard values ​​of aircraft structural state characteristic parameters as described in claim 2, characterized in that, The information parameter cluster that can reflect the overall operational status of the aircraft structure is For structural state information parameters Make a judgment if the structural state information parameters Then the structural state information parameter is the global structural feature parameter; Information clusters that can reflect the failure modes of local structures of an aircraft are For structural state information parameters Make a judgment if the structural state information parameters If the structural state information parameter is then a local structural feature parameter, then the structural state information parameter is a local structural feature parameter.

4. The method for determining standard values ​​of aircraft structural state characteristic parameters as described in claim 3, characterized in that, The information parameter cluster This includes takeoff and landing information parameters, flight information parameters, flight payload information parameters, flight environment information parameters, and mission information parameters; The information cluster N includes load information parameters, strain information parameters, damage monitoring information parameters, vibration information parameters, and local environmental monitoring information parameters.

5. The method for determining standard values ​​of aircraft structural state characteristic parameters as described in claim 4, characterized in that, Based on the design state of the global structural characteristic parameters, the overall structural characteristic parameters are divided into two categories: the first category is the basic flight characteristic parameter M1, which reflects the basic flight state of the aircraft; the second category is the overall load characteristic parameter M2, which reflects the overall load on the aircraft. Further evaluation is performed on the specific characteristic parameters of the global structural characteristic parameters. If the specific characteristic parameter MK of the global structural characteristic parameters exhibits load characteristics, then... ,otherwise ; Based on the design state of local structural characteristic parameters, these parameters are divided into two main categories: the first category, N1, reflects the local structural damage development characteristics, including strain, damage, and environmental factors; the second category, N2, reflects the local structural load characteristics, including the load spectrum. The specific characteristic parameters of each local structural parameter are then evaluated. If the specific characteristic parameter NK exhibits load characteristics, then... ,otherwise .

6. The method for determining standard values ​​of aircraft structural state characteristic parameters as described in claim 5, characterized in that, The design state of each specific characteristic parameter includes two levels of variation, including changes in the structural characteristic parameters that differ from the initial state or predicted state of the aircraft structural design. After classification, the standard extreme value λ of each specific characteristic parameter is the range of values ​​formed by the structural characteristic parameter T corresponding to the initial state P of the aircraft structural design or the attenuation state predicted by the structural design, and the positive and negative errors Δ introduced during the acquisition of characteristic parameters, i.e.: .

7. The method for determining standard values ​​of aircraft structural state characteristic parameters as described in claim 6, characterized in that, The standard value ranges of global and local structural characteristic parameters at each level of the aircraft are composed of the standard extreme values ​​of various specific characteristic parameters determined based on the identification of anomalies in specific characteristic parameters. .

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