Full-aircraft static test multi-working-condition comprehensive load processing and implementation sequencing method

Abstract

The invention belongs to the field of full-aircraft static tests of aircraft structures, and particularly relates to a multi-working-condition comprehensive load processing and implementation sequencing method for a full-aircraft static test, and the method comprises the steps: building wing and fuselage structure auxiliary lever loading nodes; a loading node library is established, and corresponding loading nodes can be quickly called for load processing during load processing of all parts; establishing a full-aircraft static test balancing library, performing comprehensive balancing on all working conditions, forming a set of general balancing points, covering full-aircraft balancing requirements of most working conditions, summarizing loading points of all existing working conditions, preferentially selecting the general balancing points or the existing loading points in new working conditions for full-aircraft balancing, and quickly updating newly added test working conditions to the balancing library; after test load processing and balancing of each working condition of each project are completed, correlation analysis between each working condition of each project is carried out, and sequencing is carried out according to the correlation; the test field installation workload can be reduced, and the test implementation efficiency is improved.

Description

Technical Field

[0001] The present application belongs to the field of aircraft structure full-machine static testing, and in particular to a method for processing and sequencing the multi-condition integrated loads of a full-machine static test. Background Art

[0002] The full-aircraft static test includes full-aircraft test conditions (2.5g, -1g, maximum vertical force landing, etc.) and component test conditions (engine conditions, vertical tail conditions, landing gear conditions, etc.), and the test conditions have multiple cycles and are long. The traditional test load processing method processes and balances each load condition separately, rarely considers the relationship between different conditions, and does not reasonably sort the implementation order of each condition based on the on-site implementation situation. By reasonably processing the comprehensive loads and balancing the full aircraft for each condition, and considering the on-site implementation to sort each project and condition, it can effectively reduce the test site replacement, improve the test efficiency, and reduce the test cost. A method for comprehensive load processing and implementation sorting of multiple conditions for full-aircraft static testing is proposed. Summary of the invention

[0003] The purpose of this application is to provide a method for processing and sequencing comprehensive loads under multiple working conditions in a full-aircraft static test, so as to solve the problem that the traditional test load processing method processes and balances each working condition load separately.

[0004] The technical solution of the present application is: a method for processing and sequencing the comprehensive loads of multiple working conditions in a full-machine static test, including:

[0005] The wings, fuselage and vertical tail are loaded in the form of tape, and the wig, horizontal tail and landing gear joints are loaded: the tape is combined into a large loading node at the intersection of the wing beam and the rib and the fuselage frame station, the upper wing surface is combined into an upward loading node, the lower wing surface is combined into a downward loading node, and the fuselage is respectively combined into vertical, heading and lateral loading nodes;

[0006] Obtain data of all loading nodes on the aircraft, including the front landing gear, main landing gear, suspension, slats, flaps, rear fuselage and vertical tail, and establish a loading node library;

[0007] Obtain the test condition data of all loading nodes on the aircraft and establish a static test balancing library for the entire aircraft; call the loading node library for load processing, classify and filter from the loading node library, and obtain the loading nodes of each part and loading direction; when trimming the entire aircraft, call the static test balancing library for the entire aircraft to obtain the unbalanced values ​​calculated for all conditions of all items, and use the unbalanced values ​​to balance the entire aircraft for all conditions to form a set of universal balancing points;

[0008] Conduct correlation analysis on different projects, calculate the correlation coefficient based on the contribution data of shared loading points and constraint points, and implement sorting according to the correlation coefficient; conduct correlation analysis on different test conditions of the same project, and determine the implementation sorting according to the correlation between different conditions and the previous project and the next project.

[0009] Preferably, the loading node library includes wing loading nodes, fuselage loading nodes, and other parts loading nodes.

[0010] Preferably, a loading node library is established in an Excel workbook using Power Query, slicer, and scatter plot tools.

[0011] Preferably, a full-machine static test balancing library is established in an Excel workbook using Power Query, slicer, and pivot table tools.

[0012] Preferably, when calling the loading node library, the load processing data of the current loading node is uploaded to the loading node library at the same time; when calling the whole-machine static test balancing library, the test data in the whole-machine static test is obtained at the same time and uploaded to the whole-machine static test balancing library.

[0013] Preferably, during load processing, the load is distributed to the loading nodes on the wing and fuselage without affecting the test accuracy; load balancing uses common loading points or existing loading points in previous tests for balancing.

[0014] Preferably, the operating condition sequencing includes implementation sequencing between different projects and implementation sequencing between multiple operating conditions in the same project.

[0015] Preferably, in the contribution data: same constraint point>same tape / tension and compression pad loading node>same joint loading node.

[0016] The multi-condition comprehensive load processing and implementation sequencing method for the full-machine static test of the present application has the following beneficial effects:

[0017] Combine the wing and fuselage tape points into large loading nodes to improve load handling efficiency and reduce the workload of lever processing and replacement between different working conditions;

[0018] Establish various loading node libraries, quickly classify and screen loading nodes, and significantly improve load processing efficiency;

[0019] Establish a full-aircraft static test trim library to perform comprehensive trimming for all working conditions, forming a set of universal trim points that cover the full-aircraft trimming requirements for most working conditions; the full-aircraft trim library summarizes all existing working condition loading points, and in new working conditions, universal trim points or existing loading points are given priority for full-aircraft trimming. New test working conditions are quickly updated to the trim library, which significantly improves the full-aircraft trimming efficiency and reduces test costs;

[0020] For all items and working conditions of the whole aircraft static test, they are comprehensively sorted according to the degree of relevance, and the implementation sequence is determined. The common loading points / universal balancing points are installed at one time, which reduces the installation workload on the test site and improves the efficiency of test implementation. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0022] Figure 1 This is a schematic diagram of the overall process of this application. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0024] A method for comprehensive load processing and implementation sequencing of multiple conditions in a full-aircraft static test. The full-aircraft static test plan for a certain large passenger aircraft includes full-aircraft test conditions such as 2.5g, -1g, and maximum vertical force landing, as well as section test conditions such as the front landing gear, main landing gear, pylon, slats, flaps, rear fuselage, and vertical tail.

[0025] like Figure 1 As shown, the following steps are included:

[0026] Step S100, the wings, fuselage, vertical tail and other parts are loaded in the form of tape, and the wig, horizontal tail, landing gear and other parts are loaded in the form of joints: the tape is auxiliaryly combined into a large loading node at the intersection of the wing beam and the rib and the fuselage frame station, the upper wing surface is combined into an upward loading node, the lower wing surface is combined into a downward loading node, and the fuselage is respectively combined into vertical, heading, and lateral loading nodes.

[0027] The wings, fuselage and other structures are loaded by a tape-lever system. The tape has many nodes. The tape points in an area of ​​the wing and fuselage (the intersection of the wing beam and the rib, and the fuselage frame) are combined into a large loading node, and auxiliary lever loading nodes in different loading directions of the wing and fuselage are established. In subsequent wing and fuselage load processing, it is only necessary to process the original load to the loading nodes in various directions of the corresponding parts, which can greatly simplify the workload of test load processing and reduce the replacement of levers between different working conditions.

[0028] Step S200, obtaining data of all loading nodes on the aircraft, including the front landing gear, main landing gear, pylon, slats, flaps, rear fuselage, vertical tail, etc., and establishing a loading node library.

[0029] Preferably, the loading node library is classified, and the loading node library includes wing loading nodes, fuselage loading nodes, and other parts loading nodes (wig joints, horizontal tail joints, landing gear joints, etc.). When processing the load of each part, the corresponding loading node can be quickly called for load processing.

[0030] Preferably, a loading node library is established in an Excel workbook using Power Query, slicer, and scatter plot tools.

[0031] Step S300, obtain the test condition data of all loading nodes on the aircraft, establish a full-aircraft static test balancing library, and the full-aircraft balancing library summarizes all existing loading nodes. In subsequent test conditions, general balancing points or existing loading points are preferentially selected for full-aircraft balancing.

[0032] Preferably, a full-machine static test balancing library is established in an Excel workbook using Power Query, slicer, and pivot table tools.

[0033] Step S400, calling the loading node library for load processing. During load processing, the loading node library can be quickly classified and screened to obtain the loading nodes of each part and each loading direction. When balancing the whole machine, the whole machine static test balancing library is called to obtain the unbalanced amount calculated for all items and all working conditions. The whole machine is balanced for all working conditions through the unbalanced amount to form a set of universal balancing points, which covers the whole machine balancing requirements for most working conditions. It can be installed on site at one time to reduce the replacement between different working conditions.

[0034] Preferably, when calling the loading node library, the load processing data of the current loading node is uploaded to the loading node library at the same time to achieve synchronous update of the data; when calling the full-aircraft static test balancing library, the test data in the full-aircraft static test is obtained at the same time and uploaded to the full-aircraft static test balancing library to achieve synchronous update of the data.

[0035] Preferably, during load processing, the load is distributed to large loading nodes on the wing and fuselage without affecting the test accuracy; load balancing is performed using a set of common loading points or existing loading points in previous tests as much as possible.

[0036] Step S500, test implementation, sorting different test conditions by correlation coefficients; specifically: performing correlation analysis on different projects, calculating correlation coefficients based on contribution data of shared loading points and constraint points, and sorting the projects in order of high to low or low to high correlation coefficients; performing correlation analysis on different test conditions of the same project, and determining the sorting based on the correlation between different conditions and the previous project and the next project.

[0037] Preferably, the operating condition sequencing includes implementation sequencing between different projects and implementation sequencing between multiple operating conditions in the same project.

[0038] Preferably, in the contribution data: same constraint point>same tape / tension and compression pad loading node>same joint loading node, so that the replacement amount in the whole implementation process is minimized and the implementation efficiency is maximized.

[0039] In summary, the beneficial effects of this application are:

[0040] Combine the wing and fuselage tape points into large loading nodes to improve load handling efficiency.

[0041] Reduce the workload of lever processing and replacement between different working conditions;

[0042] Establish various loading node libraries, quickly classify and screen loading nodes, and significantly improve load processing efficiency;

[0043] Establish a full-aircraft static test trim library to perform comprehensive trimming for all working conditions, forming a set of universal trim points that cover the full-aircraft trimming requirements for most working conditions; the full-aircraft trim library summarizes all existing working condition loading points, and in new working conditions, universal trim points or existing loading points are given priority for full-aircraft trimming. New test working conditions are quickly updated to the trim library, which significantly improves the full-aircraft trimming efficiency and reduces test costs;

[0044] For all items and working conditions of the whole aircraft static test, they are comprehensively sorted according to the degree of relevance, and the implementation sequence is determined. The common loading points / universal balancing points are installed at one time, which reduces the installation workload on the test site and improves the efficiency of test implementation.

[0045] Finally, it should be noted that: the drawings of the embodiments disclosed in the present invention only involve structures related to the embodiments disclosed in the present invention, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0046] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for processing and sequencing the comprehensive loads of multiple working conditions in a full-machine static test, characterized in that: include: The wings, fuselage and vertical tail are loaded in the form of tape, and the wig, horizontal tail and landing gear joints are loaded: the tape is combined into a large loading node at the intersection of the wing beam and the rib and the fuselage frame station, the upper wing surface is combined into an upward loading node, the lower wing surface is combined into a downward loading node, and the fuselage is respectively combined into vertical, heading and lateral loading nodes; Obtain data of all loading nodes on the aircraft, including the front landing gear, main landing gear, suspension, slats, flaps, rear fuselage and vertical tail, and establish a loading node library; Obtain the test condition data of all loading nodes on the aircraft and establish a static test balance library for the entire aircraft; Call the loading node library for load processing, classify and filter the loading node library, and obtain the loading nodes of each part and loading direction; when trimming the whole machine, call the whole machine static test balancing library to obtain the unbalanced amount calculated for all items and all working conditions, and use the unbalanced amount to balance the whole machine for all working conditions to form a set of universal balancing points; Conduct correlation analysis on different projects, calculate the correlation coefficient based on the contribution data of shared loading points and constraint points, and implement sorting according to the correlation coefficient; conduct correlation analysis on different test conditions of the same project, and determine the implementation sorting according to the correlation between different conditions and the previous project and the next project.

2. The method for processing and sequencing the multi-condition comprehensive loads of the full-machine static test according to claim 1 is characterized in that: The loading node library includes wing loading nodes, fuselage loading nodes, and other parts loading nodes.

3. The method for processing and sequencing the multi-condition comprehensive loads of the full-machine static test according to claim 1 is characterized in that: Use Power Query, Slicer, and Scatter Chart tools in Excel workbooks to create a loading node library.

4. The method for processing and sequencing the multi-condition comprehensive loads of the full-machine static test according to claim 1 is characterized in that: Use Power Query, Slicer, and PivotTable tools in Excel workbooks to create a full-aircraft static test balancing library.

5. The method for processing and sequencing the multi-condition comprehensive loads of the full-machine static test according to claim 1 is characterized in that: When calling the loading node library, the load processing data of the current loading node is uploaded to the loading node library at the same time; when calling the whole aircraft static test balancing library, the test data in the whole aircraft static test is obtained at the same time and uploaded to the whole aircraft static test balancing library.

6. The method for processing and sequencing the multi-condition comprehensive loads of the full-machine static test according to claim 1 is characterized in that: During load processing, the load is distributed to the loading nodes on the wing and fuselage without affecting the test accuracy; load balancing uses common loading points or existing loading points in previous tests for balancing.

7. The method for processing and sequencing the multi-condition comprehensive loads of the full-machine static test according to claim 1 is characterized in that: The working condition sequencing includes implementation sequencing between different projects and implementation sequencing between multiple working conditions in the same project.

8. The method for processing and sequencing the multi-condition comprehensive loads of the full-machine static test according to claim 1 is characterized in that: In the contribution data: same constraint point > same tape / tension and compression pad loading node > same joint loading node.

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