Method for testing mechanical bearing and medium transport performance of aircraft structure

Abstract

The application relates to a mechanical bearing and medium transport performance test method of an aircraft structure, and belongs to the technical field of aircraft structure performance testing. The method solves the problem that the prior art lacks a method for simultaneously testing mechanical bearing and medium transport performance, cannot simultaneously perform coupling tests between fluid and mechanics, and the test result is inaccurate. The method couples the mechanical bearing and medium transport functions of the aircraft structure for test, can simultaneously test the mechanical bearing and medium transport performance of the aircraft structure, can consider the coupling effect between fluid and mechanics, simulates a real use scene, and the test result is more accurate; the test steps are simple, the test cost is low; and the mechanical bearing and medium transport performance of the aircraft structure obtained through the test is excellent.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of performance test of aviation structural parts, and particularly relates to a mechanical bearing and medium transport performance test method of an aircraft structural part. BACKGROUND

[0002] Good bearing performance of an aircraft structural part is of great significance to ensure the durability and safety of equipment. At the same time, with the rapid development of aerospace, electronics and electrical fields, various industries urgently need to solve the heat dissipation problem of equipment. Arranging a flow channel to dissipate heat by cooling water is a common heat dissipation means at present. With the demand for material saving and weight reduction and the significant improvement of equipment compactness, the available space is gradually reduced, and integrated bearing and transport structural parts have attracted widespread attention. The test of the bearing and medium transport performance of the integrated structure is a necessary way for the structural part to meet the functional and performance requirements of the aircraft.

[0003] It is very important for an equipment to have good mechanical bearing performance and medium transport performance at the same time. The mechanical bearing and medium transport performance tests are usually carried out independently, and independent tests cannot fully simulate the real working conditions, so the test results are not accurate.

[0004] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. SUMMARY

[0005] The purpose of the present application is to provide a mechanical bearing and medium transport performance test method of an aircraft structural part to solve the problem that there is no method for simultaneously testing the mechanical bearing and medium transport performance in the prior art, the coupling test between fluid and mechanics cannot be carried out at the same time, and the test results are not accurate.

[0006] The technical solution of the present application is:

[0007] A mechanical bearing and medium transport performance test method of an aircraft structural part, comprising:

[0008] Step 1, determining a to-be-tested aircraft structural part;

[0009] Step 2, splitting the to-be-tested aircraft structural part into at least one test piece, determining the loading position of the load loading point of the test piece, and setting strain gauges on the test piece;

[0010] Step 3, determining the passage of the cooling medium flowing in the test piece;

[0011] Step 4, respectively performing internal pipe flow resistance test, internal pressure bearing capacity test, mechanical bearing performance test and internal pressure and mechanical bearing coupling test on the test piece to obtain test data;

[0012] Step 5, obtaining a load-strain curve of the to-be-tested aircraft structure and a cooling medium flow variation curve under the coupling of internal pressure and mechanical load according to the test data.

[0013] In at least one embodiment of the present application, in step 1, the to-be-tested aircraft structure is determined, including:

[0014] Step 11, determining the structure of the preset aircraft structure;

[0015] Step 12, obtaining the to-be-tested aircraft structure based on the preset aircraft structure and the aircraft structure topology optimization model.

[0016] In at least one embodiment of the present application, the preset aircraft structure includes a load-bearing structure and a transport pipeline, and the transport pipeline includes a supply flow passage and a collection flow passage.

[0017] In at least one embodiment of the present application, in step 12, the to-be-tested aircraft structure is obtained based on the preset aircraft structure and the aircraft structure topology optimization model, including:

[0018] Step 121, extracting the load borne by the aircraft load-bearing frame from the overall load of the aircraft;

[0019] Step 122, obtaining the cooling medium flow requirement;

[0020] Step 123, optimizing the preset aircraft structure to obtain the to-be-tested aircraft structure using the aircraft structure topology optimization model based on the load borne by the aircraft load-bearing frame and the cooling medium flow requirement.

[0021] In at least one embodiment of the present application, in step 4, the internal pipeline flow resistance test of the test piece includes:

[0022] Dividing the passage of the test piece into multiple loops;

[0023] Passing the cooling medium into the multiple loops respectively, and keeping the flow stable during measurement;

[0024] Recording the flow, pressure, temperature and flow rate in the multiple loops.

[0025] In at least one embodiment of the present application, in step 4, the internal pressure capacity examination test of the test piece includes:

[0026] Dividing the passage of the test piece into multiple loops;

[0027] Connecting the multiple loops accurately and sealing them perfectly;

[0028] Gradually pressurizing the multiple loops by the cooling medium;

[0029] Record the strain data of the strain gauges on the test piece.

[0030] In at least one embodiment of the present application, in step 4, the test piece is subjected to a mechanical bearing performance test, comprising:

[0031] Step-by-step loading of horizontal thrust at the loading position of the load loading point of the test piece;

[0032] Record the strain data of the strain gauges on the test piece.

[0033] In at least one embodiment of the present application, in step 4, the test piece is subjected to an internal pressure bearing and mechanical bearing coupling test, comprising:

[0034] Divide the passages of the test piece into multiple loops, introduce cooling medium into the multiple loops, and step-by-step pressurize the multiple loops by the cooling medium;

[0035] Step-by-step loading of horizontal thrust at the loading position of the load loading point of the test piece;

[0036] Record the strain data of the strain gauges on the test piece.

[0037] The present application has at least the following beneficial technical effects:

[0038] The mechanical bearing and medium transport performance test method of the aircraft structure piece of the present application can realize the simultaneous test of the mechanical bearing and medium transport performance of the aircraft structure piece, can take into account the coupling effect between fluid and mechanics, can simulate the real use scene, and the test result is more accurate; the test steps are simple, and the test cost is low; the mechanical bearing and medium transport performance of the aircraft structure piece obtained by test is excellent. BRIEF DESCRIPTION OF DRAWINGS

[0039] Figure 1 is a schematic view of the front side frame of the aircraft structure piece to be tested of the present application;

[0040] Figure 2 is a schematic view of the back side frame of the aircraft structure piece to be tested of the present application;

[0041] Figure 3 is a schematic view of the front side of the test piece of the aircraft structure piece to be tested of the present application;

[0042] Figure 4 is a schematic view of the back side of the test piece of the aircraft structure piece to be tested of the present application;

[0043] Figure 5 is a schematic view of the multiple passages of the test piece of the aircraft structure piece to be tested of the present application;

[0044] Figure 6 Schematic diagram of multiple loops of a test piece of a test aircraft structure of the present application;

[0045] Figure 7 Coordinate schematic diagram of the front side of a test piece of a test aircraft structure of the present application.

[0046] Wherein:

[0047] 1. Front side frame, 2. Second supply flow channel, 3. First supply flow channel, 4. Front side web, 5. First supply flow channel inlet, 6. Second supply flow channel inlet, 7. First supply flow channel outlet, 8. First collection flow channel inlet, 9. Back side frame, 10. First collection flow channel, 11. Second collection flow channel, 12. Back side web, 13. Second collection flow channel outlet, 14. First collection flow channel outlet, 15. Second collection flow channel inlet, 16. Second supply flow channel outlet, 17. First load loading point, 18. Second load loading point, 701. First supply flow channel outlet I, 702. First supply flow channel outlet II, 703. First supply flow channel outlet III, 704. First supply flow channel outlet IV, 1501. Second collection flow channel inlet I, 1502. Second collection flow channel inlet II, 1503 Second collection flow channel inlet III, 1504. Second collection flow channel inlet IV. DETAILED DESCRIPTION

[0048] In order to make the objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, identical or similar labels represent identical or similar elements or elements with identical or similar functions throughout. The described embodiments are part of the embodiments of the present application, rather than all the embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as a limitation on the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below with reference to the drawings.

[0049] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the scope of protection of the present application.

[0050] The above description is only a specific implementation of the present application. It should be understood by those skilled in the art that the application can be implemented in other specific forms without departing from the spirit and essential characteristics of the application. The embodiments described above are therefore illustrative, but not restrictive. The scope of the application is determined not by the description of the embodiments, but by the claims. Any variations or modifications that fall within the equivalent scope of the claims should be covered by the scope of the present application. Figures 1 to 7The application is further described in detail.

[0051] The application provides a method for testing mechanical bearing and medium transport performance of an aircraft structure, and the specific steps are as follows:

[0052] Step 1, determining the aircraft structure to be tested;

[0053] Step 2, splitting the aircraft structure to be tested into at least one test piece, determining the loading position of the load loading point of the test piece, and setting strain gauges on the test piece;

[0054] Step 3, determining the passage of the cooling medium flowing in the test piece;

[0055] Step 4, respectively performing internal pipeline flow resistance test, internal pressure bearing capacity test, mechanical bearing performance test and internal pressure and mechanical bearing coupling test on the test piece, and obtaining test data;

[0056] Step 5, obtaining the load-strain curve of the aircraft structure to be tested and the cooling medium flow variation curve under the coupling action of internal pressure and mechanical bearing according to the test data.

[0057] In the preferred embodiment of the application, the aircraft structure to be tested is determined in step 1, and the specific steps are as follows:

[0058] Step 11, determining the structure of the preset aircraft structure, the preset aircraft structure including a bearing structure and a transport pipeline, the transport pipeline including a supply flow channel and a collection flow channel.

[0059] Further, the bearing structure includes a front side frame 1 and a back side frame 9; the transport pipeline includes a supply flow channel and a collection flow channel; the supply flow channel is arranged in the front side frame 1 and used for supplying cooling medium, and the collection flow channel is arranged in the back side frame 9 and used for collecting cooling medium.

[0060] Further, referring to Figure 1 and Figure 3 , the front side frame 1 includes a first web frame, a first front side and a second front side with the same shape; the first front side and the second front side have the same shape and include a front side bottom surface, a front side upper curved surface and a front side lower curved surface; the front side bottom edges of the two front sides are butted to form the front side frame 1; the outer surface of the front side frame 1 is provided with a second supply flow channel 2, a first supply flow channel 3, a front side muscle strip 4, a first supply flow channel inlet 5, a second supply flow channel inlet 6, a first supply flow channel outlet 7 and a first collection flow channel inlet 8;

[0061] Further, referring to Figure 2 and Figure 4The back side frame 9 comprises a second abdominal frame, a first back side and a second back side which have the same shape. The first back side and the second back side have the same shape, comprising a back side bottom, an upper back side curve and a lower back side curve. The back side bottom edges of the two back sides are butted to form the back side frame 9. The outer surface of the back side frame 9 is provided with a first collection flow channel 10, a second collection flow channel 11, a back side muscle strip 12, a second collection flow channel outlet 13, a first collection flow channel outlet 14, a second collection flow channel inlet 15 and a second supply flow channel outlet 16.

[0062] It can be understood that the front side is the same direction as the aircraft heading, and the back side is the opposite direction of the aircraft heading.

[0063] Further, referring to Figure 1 and Figure 2 , the front side frame 1 and the back side frame 9 have the same shape, which is composed of curves with different upper and lower curvatures and is left-right symmetrical. The front side frame 1 and the back side frame 9 are symmetrically attached to form a preset aircraft structural member.

[0064] Further, referring to Figure 1 and Figure 2 , the first supply flow channel 3 and the second collection flow channel 11 are respectively arranged at the upper positions of the front side frame 1 and the back side frame 9. The first supply flow channel 3 and the second collection flow channel 11 have the same shape, and the arrangement positions of the first supply flow channel 3 and the second collection flow channel 11 on the front side frame 1 and the back side frame 9 correspond to the same position area on the bearing structure.

[0065] Further, the second supply flow channel 2 is arranged on the first front side of the front side frame 1, and the first collection flow channel 10 is arranged on the first back side. The arrangement positions of the second supply flow channel 2 and the first collection flow channel 10 on the front side frame 1 and the back side frame 9 correspond to the same position area on the bearing structure, and the second supply flow channel 2 and the first collection flow channel 10 have the same shape.

[0066] Further, referring to Figures 1-2 , the first supply flow channel 3 and the second collection flow channel 11 are each provided with two primary flow channels, each of which is provided with two secondary flow channels, which have the characteristics of “one into four” and “four into eight” and have good medium uniform transport and bearing performance.

[0067] Further, the second supply flow channel 2 and the first supply flow channel 3 respectively transport two area cooling media. The first supply flow channel inlet 5 and the second supply flow channel inlet 6 are used to realize uniform distribution of the two area cooling media. The first collection flow channel inlet 8 is located on the front side of the aircraft structural member, and the second supply flow channel outlet 16 is located on the back side of the aircraft structural member.

[0068] In use, the cooling medium flows in from the first supply channel inlet 5 and the second supply channel inlet 6, respectively flows through the first supply channel 3 and the second supply channel 2, and then flows out from the first supply channel outlet 7 and the second supply channel outlet 16 to the radiators arranged on both sides;

[0069] Then the cooling medium flows in from the second collection channel inlet 15 and the first collection channel inlet 8, respectively flows through the second collection channel 11 and the first collection channel 10, and then flows out from the second collection channel outlet 13 and the first collection channel outlet 14.

[0070] That is, the cooling medium supply process is: the first path is: the first supply channel inlet 5 to the first supply channel 3 to the first supply channel outlet 7; and the second path is: the second supply channel inlet 6 to the second supply channel 2 to the second supply channel outlet 16.

[0071] The cooling medium recovery process is: the third path is: the first collection channel inlet 8 to the first collection channel 10 to the first collection channel outlet 14; and the fourth path is: the second collection channel inlet 15 to the second collection channel 11 to the second collection channel outlet 13 and the first collection channel outlet 14.

[0072] Further, the aircraft structure is an aircraft load-bearing frame.

[0073] Step 12, obtaining the to-be-tested aircraft structure based on the preset aircraft structure and the aircraft structure topology optimization model, and the specific steps are as follows:

[0074] Step 121, extracting the load borne by the aircraft load-bearing frame from the full-aircraft load as the mechanical load input;

[0075] Step 122, obtaining the cooling medium flow demand.

[0076] In this embodiment, the cooling medium flow demand is 14 L / min.

[0077] Further, according to the medium transportation function demand and the bearing capacity demand, the fuselage main bearing frame is adopted as the aircraft structure.

[0078] Step 123, based on the load borne by the aircraft load-bearing frame and the cooling medium flow demand, using the aircraft structure topology optimization model to optimize the preset aircraft structure to obtain the to-be-tested aircraft structure.

[0079] Further, the aircraft structure topology optimization model includes a rib topology optimization model and a flow channel topology optimization model.

[0080] Further, the front and side ribs 4 and the back and side ribs 12 are determined according to the rib topology optimization model, and the expression is:

[0081]

[0082] Minimize C = ∫ D H(φ S (x))f·udV

[0083] s.t.

[0084]

[0085] where D represents the total set of design variables of the struts; Dj represents the set of design variable vector of the jth strut; Dn represents the set of design variable vector of the nth strut; n is the total number of struts; T represents the matrix transpose; x represents the coordinate vector at the element node x in the design domain; C represents the objective function of the strut optimization; H(.) represents the Heaviside function; φ S (.) represents the topological description function of the strut; f represents the body force acting on the Neumann boundary Γ t ; u represents the displacement field matrix; V represents the volume of the design domain; q represents the penalty index value required by the topological description function; Cijkl represents the fourth-order isotropic elastic tensor of the pre-set aircraft structural material; ε(.) represents the second-order linear strain tensor; v represents the trial function defined in the design domain; S' represents the trial function domain; V represents the upper threshold value of the volume constraint; D represents the set of all design variables; u0 represents the prescribed displacement on the Dirichlet boundary, which is a zero matrix here; Γ u represents the Dirichlet boundary; D represents the lower limit of all design variables; represents the upper limit of all design variables.

[0086] Further, the second supply flow channel 2, the first supply flow channel 3, the first collection flow channel 10 and the second collection flow channel 11 are expressed according to a flow channel topology optimization model, and the expression is:

[0087]

[0088] s.t.

[0089]

[0090] where D' represents the total set of design variables of the flow channel and the strut; D'i represents the set of variable vector of the ith flow channel; denotes the set of variable vectors of the n-mth flow channel, where the total number of flow channels and the number of ribs are m and n, respectively; T denotes the matrix transpose; denotes the design variable vector of the jth rib assembly; denotes the set of design variable vectors of the mth rib; x denotes the coordinate vector at the element node in the design domain; C mix denotes the mixed objective function, which is obtained by weighting the total elastic strain energy of the structure and the standard deviation of the flow rate at several flow channel outlets; H(.) denotes the Heaviside function; φ S (.) denotes the topological description function of the rib; f denotes the body force acting on the Neumann boundary Γ t denotes the displacement field matrix; V denotes the volume of the design domain; q denotes the penalty index value required by the topological description function; denotes the fourth-order isotropic elastic tensor of the preset aircraft structural component material; ε(.) denotes the second-order linear strain tensor; v denotes the trial function defined in the design domain; S' denotes the trial function domain; denotes the set of values that the trial function can take; denotes the upper threshold value of the volume constraint; denotes the set of all design variables; denotes the prescribed displacement on the Dirichlet boundary, which is a zero matrix here; Γ u denotes the Dirichlet boundary; D denotes the lower limit of all design variables; denotes the upper limit of all design variables; a denotes the weight coefficient of the total elastic strain energy of the structure; b denotes the weight coefficient of the standard deviation of the flow rate at several flow channel outlets; v i denotes the outlet flow rate of the ith flow channel; vave denotes the average outlet flow rate of all flow channels.

[0091] Further, the design constraints include the load borne by the preset aircraft structural component and the flow rate requirement of the cooling medium.

[0092] In step 2, referring to Figure 7 , the aircraft structural component to be tested is divided into two test pieces along the respective side and bottom surfaces, and the test is performed on the test piece provided with the second supply flow channel 5 and the first collection flow channel 10; the loading position of the load loading point of the test piece is determined, and strain gauges are attached to the test piece;

[0093] Further, two load loading points are provided; strain gauges are attached to the ribs and webs of the test piece.

[0094] Further, referring to Figure 7With the positive side frame 1 as an example, the intersection of the positive side surface bottom surface and the positive side surface lower curved surface is taken as the origin, and the positive side surface bottom surface is taken as the y axis; the intersection of the positive side surface upper curved surface and the positive side surface lower curved surface is taken as the x axis, which is perpendicular to the direction of the positive side surface bottom surface; the coordinates of the first load loading point 17 are (x1, y1), and the coordinates of the second load loading point 18 are (x2, y2).

[0095] Further, the loading positions of the two load loading points are determined according to the actual engineering structure loading positions.

[0096] Step 3, four passages of the cooling medium flowing in the test piece are determined.

[0097] Specifically, referring to Figure 3 and Figure 4 , the first supply flow channel outlet 7 includes the first supply flow channel outlet I 701, the first supply flow channel outlet II 702, the first supply flow channel outlet III 703 and the first supply flow channel outlet IV 704; and the second collection flow channel inlet 15 includes the second collection flow channel inlet I 1501, the second collection flow channel inlet II 1502, the second collection flow channel inlet III 1503 and the second collection flow channel inlet IV 1504.

[0098] In use, referring to Figure 5 and Figure 6 , the cooling medium flows in from the first supply flow channel inlet 5, flows through the first supply flow channel 3 respectively, and then flows out from the first supply flow channel outlet I 701, the first supply flow channel outlet II 702, the first supply flow channel outlet III 703 and the first supply flow channel outlet IV 704 to the flow divider, and then flows in from the flow divider to the first collection flow channel inlet 8, and then flows through the first collection flow channel 10, flows into the first collection flow channel outlet 14, and finally enters the cooling medium tank;

[0099] The cooling medium flows in from the second supply flow channel inlet 6, flows through the second supply flow channel 2, flows into the second supply flow channel outlet 16 to the flow divider, and then flows in from the flow divider to the second collection flow channel inlet I 1501, the second collection flow channel inlet II 1502, the second collection flow channel inlet III 1503 and the second collection flow channel inlet IV 1504, and then flows through the second collection flow channel 11, flows into the second collection flow channel outlet 13, and finally enters the cooling medium tank;

[0100] Referring to the accompanying Figure 5 , the four passages are passage one, passage two, passage three and passage four;

[0101] Among them, the passage one is that the first supply flow channel inlet 5 flows in respectively to the first supply flow channel outlet I 701, the first supply flow channel outlet II 702, the first supply flow channel outlet III 703 and the first supply flow channel outlet IV 704 to flow out;

[0102] Passage two is from the second supply channel inlet 6 to the second supply channel outlet 16;

[0103] Passage three is from the second collection channel inlet I 1501, the second collection channel inlet II 1502, the second collection channel inlet III 1503 and the second collection channel inlet IV 1504 to the second collection channel outlet 13.

[0104] Passage four is from the first collection channel inlet 8 to the first collection channel outlet 14.

[0105] Step 4, the test piece is respectively subjected to internal pipeline flow resistance test, internal pressure capacity test, mechanical bearing performance test and internal pressure and mechanical bearing coupling test, and test data is obtained.

[0106] Specifically, referring to Figures 3-5 The specific steps of the internal pipeline flow resistance test of the test piece are as follows:

[0107] (1) Passage one and passage four constitute loop one, and passage two and passage three constitute loop two, ensure that the transport pipeline is connected accurately and sealed perfectly, and the pump body is supplied with pressure twice to supply pressure to loop one and loop two, and the cooling medium enters loop one and loop two from passage one and passage two respectively;

[0108] (2) Close the passage two ball valve or the passage one ball valve through the pump body control cabinet, ensure that the first supply channel inlet 5 and the second supply channel inlet 6 respectively measure the flow rate of the cooling medium to be stable at half of the flow rate required, preferably 7L / min, and keep the cooling medium circulating in the transport pipeline; record the flow rate, pressure, temperature and flow rate of the first supply channel outlet I 701, the first supply channel outlet II 702, the first supply channel outlet III 703 and the first supply channel outlet IV 704, and the second supply channel outlet 16.

[0109] Specifically, referring to Figures 3-5 The specific steps of the internal pressure capacity test of the test piece are as follows:

[0110] (1) Passage one and passage four constitute loop one, and passage two and passage three constitute loop two;

[0111] (2) Ensure that the transport pipeline is connected accurately and sealed perfectly;

[0112] (3) The pump body gives the closed transport pipeline cooling medium pressure boost.

[0113] Pre-experiment stage: according to 5% of the test pressure load, gradually increase the pressure load to 40% of the pressure load, and measure the strain of the strain gauge gradually; repeat the pre-experiment stage twice, and obtain the test data of the two pre-experiment stages.

[0114] Check the repeatability and validity of the test data of the above two pre-test stages, and the error of the strain value of the strain gauge measured each time is less than 5%. If the repeatability is unqualified, check the test process until the requirements are met.

[0115] The formal test stage:

[0116] The first formal test stage: load step by step according to 5% test pressure load, load to 67% test pressure load, hold for 30 seconds, measure strain step by step, and then unload to 0. After unloading, check the test piece. If there is damage, return to step 1 to re-determine the aircraft structure to be tested. After the test, check the repeatability and validity of the test data. If unqualified, check the test process until the requirements are met.

[0117] The second formal test stage: load step by step according to 5% test pressure load, load to 67% test pressure load, and then load step by step according to 3% test pressure load, load to 100% test pressure load, hold for 30 seconds, measure strain step by step, and then unload to 0. After unloading, check the test piece. If there is damage, return to step 1 to re-determine the aircraft structure to be tested. After the test, check the repeatability and validity of the test data. If unqualified, check the test process until the requirements are met.

[0118] Specifically, refer to Figure 7 The specific steps of the mechanical bearing performance test of the test piece are as follows:

[0119] (1) Ensure that the test piece and the loading position of the load loading point are correctly centered and well centered, and the connecting rod is pushed by the hydraulic cylinder to apply horizontal thrust to the two loading points of the test piece through the single ear double ear pin connection.

[0120] (2) Pre-test stage: load step by step according to 5% test load, add to 40% load and measure strain of strain gauge step by step; complete recording and unload to check the stress of the test piece and the loading equipment, repeat the test twice.

[0121] (3) Check the repeatability and validity of the test data of the above two pre-test stages, and the error of the strain value of the strain gauge measured each time is less than 5%. If the repeatability is unqualified, check the test process until the requirements are met.

[0122] (4) Formal test stage:

[0123] The first formal test phase: the horizontal thrust loading is increased step by step according to 5% test pressure load, and is loaded to 67% test pressure load, and is kept for 30 seconds, and the strain is measured step by step, and after completion, is unloaded to 0; after unloading, the test piece is checked, if there is damage, return to step 1 to re-determine the aircraft structure to be tested; after the test, the repeatability and effectiveness of the test data are checked, if unqualified, the test process is checked until the requirements are met.

[0124] The second formal test phase: the horizontal thrust loading is increased step by step according to 5% test pressure load, and is loaded to 67% test pressure load, and then is increased step by step according to 3% test pressure load, and is loaded to 100% test pressure load, and is kept for 30 seconds, and the strain is measured step by step, and then is unloaded to 0; after unloading, the test piece is checked, if there is damage, return to step 1 to re-determine the aircraft structure to be tested; after the test, the repeatability and effectiveness of the test data are checked, if unqualified, the test process is checked until the requirements are met.

[0125] Specifically, referring to Figure 6 The specific steps of the internal pressure and mechanical load coupling test of the test piece are as follows:

[0126] The first formal test phase: the pump body flow system (the body) and the mechanical loading system (the hydraulic cylinder pushes the connecting rod to apply horizontal thrust to the two loading points of the test piece through the pin connection of the single ear and the double ear) are loaded simultaneously according to 5% test load, and are loaded to 67% test load, and are kept for 30 seconds, and the strain is measured and recorded step by step, and after completion, are unloaded to 0; after unloading, the test piece is checked, if there is damage, return to step 1 to re-determine the aircraft structure to be tested; after the test, the repeatability and effectiveness of the test data are checked, if unqualified, the test process is checked until the requirements are met.

[0127] The second formal test phase: the horizontal thrust loading is increased step by step according to 5% test pressure load, and is loaded to 67% test pressure load, and then is increased step by step according to 3% test pressure load, and is loaded to 100% test pressure load, and is kept for 30 seconds, and the strain is measured step by step, and then is unloaded to 0; after unloading, the test piece is checked, if there is damage, return to step 1 to re-determine the aircraft structure to be tested; after the test, the repeatability and effectiveness of the test data are checked, if unqualified, the test process is checked until the requirements are met.

[0128] Finally, in step 5, the load-strain curve of the cooling medium aircraft structure obtained in step 4, and the cooling medium flow variation curve under the coupling effect of internal pressure and mechanical load.

[0129] The method for testing the mechanical bearing and medium transport performance of the aircraft structure of the application can couple the mechanical bearing and medium transport functions of the aircraft structure for testing, can realize the simultaneous testing of the mechanical bearing and medium transport performance of the aircraft structure, can consider the coupling effect between fluid and mechanics, can simulate the real use scene, and the testing result is more accurate; the test steps are simple, and the test cost is low; the mechanical bearing and medium transport performance of the aircraft structure obtained through testing is excellent.

[0130] The above is only a specific embodiment of the application, but the protection scope of the application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the application, which should be covered within the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. A method for testing the mechanical load-bearing and media transport performance of an aircraft structural component, characterized in that, include: Step 1: Identify the structural components of the aircraft to be tested; Step 2: Disassemble the aircraft structure under test into at least one test piece, determine the loading position of the load loading point of the test piece, and install strain gauges on the test piece; Step 3: Determine the flow path of the cooling medium in the test specimen; Step 4: Conduct internal pipeline flow resistance test, internal pressure bearing capacity assessment test, mechanical bearing performance assessment test, and internal pressure bearing and mechanical bearing coupling test on the test specimen to obtain test data; Step 5: Based on the test data, obtain the load-strain curve of the test aircraft structural component, and the cooling medium flow rate change curve under the coupled action of internal pressure and mechanical bearing. In step 1, the structural components of the aircraft to be tested are identified, including: Step 11: Determine the structure of the preset aircraft structural component. The preset aircraft structural component includes a load-bearing structure and a transport pipeline. The load-bearing structure includes a front side frame and a back side frame. The transport pipeline includes a supply channel and a collection channel. The supply channel is disposed in the front side frame, and the collection channel is disposed in the back side frame. The front side frame and the back side frame are symmetrically fitted together to form the preset aircraft structural component. Step 12: Obtain the aircraft structure to be tested based on the preset aircraft structure and the aircraft structure topology optimization model.

2. The method for testing the mechanical load-bearing and media transport performance of aircraft structural components according to claim 1, characterized in that, In step 12, the aircraft structural component to be tested is obtained based on the preset aircraft structural component and the aircraft structural component topology optimization model, including: Step 121: Extract the load borne by the load-bearing frame of the aircraft from the total load of the aircraft; Step 122: Obtain the required cooling medium flow rate; Step 123: Based on the load borne by the aircraft load-bearing frame and the cooling medium flow requirements, the preset aircraft structural component is optimized using the aircraft structural component topology optimization model to obtain the aircraft structural component to be tested.

3. The method for testing the mechanical load-bearing and media transport performance of aircraft structural components according to any one of claims 1-2, characterized in that, Step 4 involves conducting an internal piping flow resistance test on the test piece, including: The pathway of the test piece is divided into multiple loops; The cooling medium is introduced into multiple circuits to maintain a stable flow rate during measurement; Record the flow rate, pressure, temperature, and velocity in multiple loops.

4. The method for testing the mechanical load-bearing and media transport performance of aircraft structural components according to any one of claims 1-2, characterized in that, Step 4 involves conducting an internal pressure-bearing capacity assessment test on the test specimen, including: The pathway of the test piece is divided into multiple loops; Connect multiple circuits accurately and seal them properly; Multiple circuits are pressurized in stages using a cooling medium; Record the strain data of the strain gauges on the test specimen.

5. The method for testing the mechanical load-bearing and media transport performance of aircraft structural components according to any one of claims 1-2, characterized in that, Step 4 involves conducting a mechanical load-bearing capacity assessment test on the test specimen, including: A horizontal thrust is applied in stages at the loading positions of the load loading points on the test specimen; Record the strain data of the strain gauges on the test specimen.

6. The method for testing the mechanical load-bearing and media transport performance of aircraft structural components according to any one of claims 1-2, characterized in that, In step 4, the test specimen undergoes a coupled test of internal pressure bearing and mechanical load bearing, including: The passage of the test piece is divided into multiple loops, and a cooling medium is introduced into the multiple loops to gradually increase the pressure of the multiple loops through the cooling medium. A horizontal thrust is applied in stages at the loading positions of the load loading points on the test specimen; Record the strain data of the strain gauges on the test specimen.

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