Clamping device and test method for composite material casing installation edge simulation piece

Abstract

The invention relates to the technical field of engines, and discloses a clamping device and a test method for a composite material casing installation edge simulation piece, the clamping device for the composite material casing installation edge simulation piece comprises a supporting piece, the surface of the supporting piece is used for placing a simulation piece; the first limiting piece is located on the simulation piece, the first limiting piece is connected with the supporting piece through a first fixing piece, a limiting space is formed between the first limiting piece and the supporting piece, and the first side edge of the simulation piece is located in the limiting space; the second limiting piece is located on the supporting piece, one end of the second limiting piece is connected with the supporting piece, the other end of the second limiting piece abuts against the second side edge of the simulation piece, and the length of the second side edge is larger than that of the first side edge. According to the invention, precise fixation of the simulation piece is realized, the operation process is simplified, the simulation piece is protected, the reliability and efficiency of the test are improved, and the problems of poor clamping precision and complex operation of a clamping device in the prior art are solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of engines, in particular to a clamping device for composite material engine case mounting edge simulation and a test method. BACKGROUND

[0002] Composite materials have been widely used in the aviation field due to their excellent specific strength, specific modulus, excellent fatigue resistance and high designability. In the engine structure, the use of composite materials can effectively reduce the structure weight and improve the thrust-to-weight ratio. The examination test of the front mounting edge part of the engine case is the key to verify the rationality of the composite material part design, the structural strength and durability. The structural performance of the engine case, as a load-bearing structure of the engine, is crucial to the overall safety and reliability of the engine. Therefore, research and testing work on the composite material front mounting edge simulation is necessary to ensure the actual quality and performance of the mounting edge.

[0003] The failure process of composite materials under external load is a complex progressive damage process, accompanied by various failure modes. The standard tensile test cannot truly simulate the tensile state of the front mounting edge simulation of the engine case. In addition, the front mounting edge simulation of the composite material often has a complex shape and high installation precision requirements.

[0004] Some existing clamping devices fix the simulation, which is not accurate in positioning and cannot accurately ensure the installation position and angle of the simulation. In addition, some existing clamping devices need to go through multiple complex steps during installation and adjustment, and can only be completed by professional operators, which brings great difficulty to the prediction of the failure behavior of the composite material simulation, and the obtained results have little guiding effect on the optimization design of the mounting edge of the engine case. At the same time, the clamping precision is difficult to meet the requirements, the operation is complex, the universality is poor, and the composite material is easily damaged. SUMMARY

[0005] Therefore, the present application provides a clamping device for composite material engine case mounting edge simulation and a test method to solve the problems of poor clamping precision and complex operation of the clamping device in the prior art.

[0006] In a first aspect, the present application provides a clamping device for composite material engine case mounting edge simulation, comprising: a support, the surface of the support is used to place the simulation; a first limiting piece, the first limiting piece is located on the simulation, the first limiting piece is connected with the support through a first fixing piece, a limiting space is formed between the first limiting piece and the support, and the first side edge of the simulation is located in the limiting space; a second limiting piece, the second limiting piece is located on the support, one end of the second limiting piece is connected with the support, and the other end of the second limiting piece abuts against the second side edge of the simulation, and the length of the second side edge is greater than the length of the first side edge.

[0007] The first limiting piece and the support piece form a limiting space, and the first fixing piece is fastened, so that the short side of the simulation piece is bidirectionally constrained, the lateral displacement and vertical warping of the short side of the simulation piece are limited, the position deviation of the simulation piece due to stress during the test is avoided, the second limiting piece abuts against the long side of the simulation piece, the long side of the simulation piece is constrained, the radial or axial displacement of the long side of the simulation piece is effectively limited through single-point or multi-point abutting, the precise fixing of the simulation piece is realized, the operation process is simplified, the simulation piece is protected, and the reliability and efficiency of the test are improved, and the problems of poor clamping precision and complex operation of the clamping device in the prior art are solved.

[0008] In an optional embodiment, the support piece is a flat plate structure, the first limiting piece is a flat plate structure, the first side edge of the simulation piece is arranged in parallel with the extension direction of the support piece or the extension direction of the first limiting piece, and the extension direction of the second side edge of the simulation piece is arranged at an angle with the extension direction of the support piece or the extension direction of the first limiting piece, so that the support piece and the first limiting piece can be adapted to the shape of the simulation piece and can be arranged to fit the short side of the simulation piece, and the structural stability of the simulation piece during the test is further improved.

[0009] In an optional embodiment, the surface of the support piece is provided with at least two first through holes, the first limiting piece is provided with at least two second through holes, the first through holes and the second through holes are arranged correspondingly, and the first fixing piece is arranged through the second through holes and the first through holes. Through the precise alignment of the two or more through holes, the relative position between the first limiting piece and the support piece can be strictly constrained, and the relative deviation of the first limiting piece and the support piece caused by single through hole connection is avoided, and the clamping effect on the short side of the simulation piece is affected.

[0010] In an optional embodiment, the width of the simulation piece is a, and the distance between the centers of the at least two first through holes or the at least two second through holes is b, wherein a < b-r, and r is the radius of the first through hole or the second through hole. The simulation piece is only constrained by the limiting space formed by the first limiting piece and the support piece, without any additional extrusion stress from the first fixing piece, so that the stress and deformation data measured in the subsequent high-temperature tensile test can accurately map the stress characteristics of the real engine case mounting edge.

[0011] In an optional embodiment, the second limiting piece is an L-shaped structure, the first side edge of the second limiting piece is connected with the side wall of the support piece through the second fixing piece, and the second side edge of the second limiting piece is connected with the simulation piece, so that the lateral displacement of the simulation piece along the surface of the support piece is directly limited.

[0012] In an alternative embodiment, the side wall of the support member is provided with a third through hole, the first side edge of the second limiting member is provided with a fourth through hole, the third through hole and the fourth through hole are correspondingly arranged, and the second fixing member passes through the fourth through hole and the third through hole. The bolt connection rigidly fixes the second limiting member and the support member, and the force transmission is concentrated.

[0013] In an alternative embodiment, the bottom of the support member is connected with a cylindrical connecting rod, and the cylindrical connecting rod is used to connect with the chuck of the fatigue testing machine.

[0014] In a second aspect, the present application further provides a test method for a composite material nacelle mounting edge simulation piece. The test method is based on the clamping device of the composite material nacelle mounting edge simulation piece. The test method comprises the following steps: Step S11: The support member, the first limiting member, and the second limiting member are used to clamp and limit the simulation piece, so as to obtain a unit to be tested. Step S12: The unit to be tested is placed in a heating furnace, wherein the upper and lower ends of the heating furnace are respectively provided with through holes for the second side edge of the simulation piece and the cylindrical connecting rod at the bottom of the unit to be tested. Step S13: The cylindrical connecting rod at the bottom of the unit to be tested is connected with the chuck of the fatigue testing machine, and the simulation piece is connected with another chuck of the fatigue testing machine. Step S14: The simulation piece of the unit to be tested is subjected to a high-temperature tensile test, and a test result is obtained.

[0015] The heating furnace can accurately control the temperature, and the fatigue testing machine can accurately control the tensile load. The effective control of the temperature and the load is realized by the cooperation of the two, the performance data of the simulation piece under different working conditions are obtained, the data dimension is more comprehensive, the test constraints, environment, and load are equivalent to the real service working conditions, and the high-temperature tensile performance of the simulation piece obtained by the test can be directly mapped to the real composite material nacelle mounting edge.

[0016] In an alternative embodiment, step S11 comprises: fixing the first side edge of the simulation piece between the support member and the first limiting member by using the first fixing member; and fixing one end of the second limiting member on the support member by using the second fixing member, so that the other end of the second limiting member abuts against the second side edge of the simulation piece. The short edge of the simulation piece is bidirectionally constrained by the limiting space formed by the first limiting member and the support member and fastened by the first fixing member, the transverse displacement and vertical warping of the short edge of the simulation piece are limited, the position of the simulation piece is prevented from deviating due to stress during the test, the long edge of the simulation piece is abutted by the second limiting member, the long edge of the simulation piece is constrained, the radial or axial displacement of the long edge of the simulation piece is effectively limited by single-point or multi-point abutment, the accurate fixing of the simulation piece is realized, the operation process is simplified, the simulation piece is protected, and the reliability and efficiency of the test are improved. The problems of poor clamping precision and complex operation of the clamping device in the prior art are solved.

[0017] In an alternative embodiment, step S14 comprises: closing the fatigue testing machine; setting the heating temperature of the heating furnace to a preset temperature, and starting the heating furnace to heat; waiting for a preset time after the temperature of the heating furnace reaches the preset temperature, and starting the fatigue testing machine to perform the high-temperature tensile test; and using the digital image correlation method to perform real-time monitoring and data collection on the test process to obtain the test result. Starting the heating furnace after closing the fatigue testing machine can prevent early loading when the heating furnace does not reach the preset temperature, and waiting for a preset time after the temperature reaches the standard can allow the whole unit to be tested to reach thermal equilibrium. BRIEF DESCRIPTION OF DRAWINGS

[0018] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following will briefly introduce the drawings needed to be used in the specific embodiments or prior art description. Obviously, the drawings described below are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor.

[0019] Fig. 1 It is a front view of the clamping device of the composite material nacelle mounting edge simulation piece of the embodiment of the present application; Fig. 2 It is an exploded structural schematic view of the clamping device of the composite material nacelle mounting edge simulation piece of the embodiment of the present application; Fig. 3 It is a flow schematic view of the test method of the composite material nacelle mounting edge simulation piece of the embodiment of the present application.

[0020] Explanation of reference signs: 1, simulation piece; 2, first fixing piece; 3, first limiting piece; 31, second through hole; 4, supporting piece; 41, first through hole; 5, second limiting piece; 6, second fixing piece; 7, cylindrical connecting rod. DETAILED DESCRIPTION

[0021] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and in combination with the embodiments.

[0022] It should be noted that the terms used herein are only for describing specific embodiments, and are not intended to limit the exemplary embodiments according to the present application. As used herein, the singular form is intended to include the plural form unless the context clearly indicates otherwise, and it should also be understood that when the terms "comprise" and / or "include" are used in the specification, there is a presence of the features, steps, operations, devices, components and / or combinations thereof.

[0023] It is to be understood that the terms "first", "second", and the like, used in the description and the claims of the present application as well as the above description of the drawings merely refer to structure that is different, and not necessarily to an order or sequence. It is to be understood that the terms so used are interchangeable under appropriate circumstances and embodiments of the application described herein are capable of operating in other sequences than those explicitly described or illustrated herein. Furthermore, the terms "comprise", "include", "contain" and "have" and variations thereof, when used in this description and in the claims of the application, shall be construed as disclosing the presence of the stated element or elements but not excluding the presence of one or more additional elements or steps. The term "comprising" and variations of the term "comprising", such as "comprise" and "comprises", when used in this specification and in the claims of the application, shall not be construed as referring to a closed or limited set of elements or steps.

[0024] Exemplary embodiments according to this application will now be described in more detail with reference to the accompanying drawings. These exemplary embodiments may, however, be implemented in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these exemplary embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the inventive concept of the exemplary embodiments to those skilled in the art, and in the drawings, the thicknesses of layers and regions are exaggerated for clarity, and the same reference numerals are used in different drawings to designate the same elements, and thus the description will not be repeated.

[0025] Embodiments of the present application will be described below with reference to Figs. 1 to 3 .

[0026] According to an embodiment of the present application, in one aspect, a clamping device for a composite nacelle mounting edge mockup is provided. As shown in Fig. 1 , Fig. 2 , the clamping device for the composite nacelle mounting edge mockup comprises a support 4, a surface of the support 4 for placing the mockup 1; a first limiting piece 3, the first limiting piece 3 being located on the mockup 1, the first limiting piece 3 being connected with the support 4 through a first fixing piece 2, a limiting space being formed between the first limiting piece 3 and the support 4, a first side edge of the mockup 1 being located in the limiting space; a second limiting piece 5, the second limiting piece 5 being located on the support 4, one end of the second limiting piece 5 being connected with the support 4, the other end of the second limiting piece 5 abutting against a second side edge of the mockup 1, the length of the second side edge being greater than the length of the first side edge.

[0027] In this embodiment, the first limiting piece 3 and the supporting piece 4 form a limiting space, and the first fixing piece 2 is fastened, so that the short side of the simulation piece 1 can be bidirectionally constrained, the lateral displacement and vertical warping of the short side of the simulation piece 1 are limited, the position deviation of the simulation piece 1 due to stress during the test process is avoided, the second limiting piece 5 abuts against the long side of the simulation piece 1, the long side of the simulation piece 1 is constrained, the radial or axial displacement of the long side of the simulation piece 1 is effectively limited through single-point or multi-point abutting, the precise fixing of the simulation piece 1 is realized, the operation process is simplified, the simulation piece 1 is protected, the reliability and efficiency of the test are improved, and the problems of poor clamping precision and complex operation of the clamping device in the prior art are solved.

[0028] The first fixing piece 2 adopts a detachable bolt, a nut and a gasket, the first limiting piece 3 and the supporting piece 4 limit the simulation piece 1, the simulation piece 1 can be quickly taken out or put in by adjusting the nut and the bolt, the mounting and dismounting process of the simulation piece 1 can be simplified, and the simulation piece is suitable for frequent replacement in multiple tests.

[0029] It should be noted that the simulation piece 1 is a substitute for the mounting edge of the case, the simulation piece 1 has a long side and a short side, and usually corresponds to the structural characteristics of the real mounting edge, for example, the long side of the simulation piece 1 is the main bearing edge.

[0030] In one embodiment, the supporting piece 4 is a flat plate structure, the first limiting piece 3 is a flat plate structure, the first side of the simulation piece 1 is arranged in parallel with the extension direction of the supporting piece 4 or the extension direction of the first limiting piece 3, and the extension direction of the second side of the simulation piece 1 is arranged at an angle with the extension direction of the supporting piece 4 or the extension direction of the first limiting piece 3.

[0031] Specifically, since the short side of the simulation piece 1 is a plate structure, the supporting piece 4 and the first limiting piece 3 are arranged as plate structures, and the supporting piece 4 and the first limiting piece 3 are connected to form a limiting space, so that the supporting piece 4 and the first limiting piece 3 can be adapted to the shape of the simulation piece 1 and can be arranged in close contact with the short side of the simulation piece 1, thereby further enhancing the structural stability of the simulation piece 1 during the test.

[0032] In one embodiment, the surface of the supporting piece 4 is provided with at least two first through holes 41, the first limiting piece 3 is provided with at least two second through holes 31, the first through holes 41 and the second through holes 31 are arranged correspondingly, and the first fixing piece 2 passes through the second through holes 31 and the first through holes 41.

[0033] Specifically, by accurate alignment of the two or more through holes, the relative position between the first limiting piece 3 and the support piece 4 can be strictly constrained, avoiding the relative deviation of the first limiting piece 3 and the support piece 4 when a single through hole is connected, which affects the clamping effect of the short side of the simulation piece 1. At the same time, the operator can quickly judge whether the installation of the first limiting piece 3 and the support piece 4 is in place by observing whether the through holes are aligned, which is simple in structure, convenient to operate and cost-saving.

[0034] In one embodiment, the width of the simulation piece 1 is a, and the distance between the centers of the at least two first through holes 41 or the at least two second through holes 31 is b, wherein a < b-2r, r is the radius of the first through hole 41 or the second through hole 31.

[0035] Specifically, from the geometric relationship, "b-2r" represents the shortest distance between the edges of the two first through holes 41. a < b-2r indicates that the width of the simulation piece 1 is completely within the edge range of the two first through holes 41, thereby avoiding physical interference between the simulation piece 1 and the first through hole 41 and the first fixing piece 2. The pre-tightening force of the first fixing piece 2 only acts on the contact surface of the first limiting piece 3 and the support piece 4, and the simulation piece 1 is only constrained by the limiting space formed by the first limiting piece 3 and the support piece 4, without any additional extrusion stress from the first fixing piece 2. The stress and deformation data measured in the subsequent high-temperature tensile test can accurately map the stress characteristics of the real cartridge mounting edge.

[0036] In one embodiment, the second limiting piece 5 is an L-shaped structure, the first side of the second limiting piece 5 is connected with the side wall of the support piece 4 through the second fixing piece 6, and the second side of the second limiting piece 5 is connected with the simulation piece 1.

[0037] Specifically, the second side of the second limiting piece 5 is connected with the second side of the simulation piece 1, which can directly limit the transverse displacement of the simulation piece 1 along the surface of the support piece 4, such as sliding of the simulation piece 1 away from the first limiting piece 3 during test loading.

[0038] In this embodiment, the second limiting piece 5 of the L-shaped structure is provided as one, and in other embodiments, the number of the second limiting piece 5 is not limited to this, but can also be two, three, etc., as long as it is arranged in the width direction of the support piece 4.

[0039] In one embodiment, the side wall of the support piece 4 is provided with a third through hole, the first side of the second limiting piece 5 is provided with a fourth through hole, the third through hole and the fourth through hole are correspondingly arranged, and the second fixing piece 6 is arranged through the fourth through hole and the third through hole.

[0040] Specifically, the first side edge of the second limiting piece 5 is rigidly connected with the side wall of the support piece 4 through the second fixing piece 6 (screw), and the second side edge of the second limiting piece 5 abuts against the side edge of the simulation piece 1. The screw connection rigidly fixes the second limiting piece 5 with the support piece 4, the force transmission is concentrated, the second limiting piece 5 can bear the reaction force of the simulation piece 1 without being easily bent, and the stability of the limiting is ensured in the long-term test.

[0041] In the embodiment, the second limiting piece 5 is connected with the support piece 4 through the screw, that is, the second fixing piece 6 is a screw; in other embodiments, the connection mode of the second limiting piece 5 and the support piece 4 is not limited to this, and can also be adhesion, clamping and the like.

[0042] In one embodiment, the bottom of the support piece 4 is connected with a cylindrical connecting rod 7, and the cylindrical connecting rod 7 is used to be connected with the chuck of the fatigue testing machine.

[0043] According to the embodiment of the present application, on the other hand, a test method for a composite material nacelle mounting edge simulation piece is also provided, as shown in Fig. 3 The test method is based on the clamping device of the composite material nacelle mounting edge simulation piece, and the test method comprises the following steps. Step S11: The simulation piece 1 is clamped and limited by the support piece 4, the first limiting piece 3 and the second limiting piece 5 to obtain a unit to be tested; In step S11, the simulation piece 1 is placed on the support piece 4, the first limiting piece 3 is placed on the short edge of the simulation piece 1, then the second through hole 31 of the first limiting piece 3 is aligned with the first through hole 41 of the support piece 4, the first fixing piece 2 is passed through the second through hole 31 and the first through hole 41 to realize the clamping and limiting of the short edge of the simulation piece 1 by the first limiting piece 3 and the support piece 4; then the fourth through hole of the short edge of the second limiting piece 5 is aligned with the third through hole of the side edge of the support piece 4, the second fixing piece 6 is passed through the fourth through hole and the third through hole to realize the limiting of the long edge of the simulation piece 1 by the second limiting piece 5.

[0044] Step S12: The unit to be tested is placed in a heating furnace, wherein the upper and lower ends of the heating furnace are respectively provided with through holes for the second side edge of the simulation piece 1 and the cylindrical connecting rod 7 at the bottom of the unit to be tested to extend out; In step S12, the upper circular through hole of the heating furnace facilitates the clamping of the long edge of the simulation piece 1 of the composite material nacelle front mounting edge by the fatigue testing machine, and the lower circular through hole facilitates the connection of the cylindrical connecting rod 7 with the fatigue testing machine. The size of the circular through hole of the heating furnace can meet the requirements of the clamping device for connecting the testing machine.

[0045] The inner wall of the heating furnace is kept at a sufficient distance from the clamping device of the composite material nacelle front mounting edge simulation piece to prevent the simulation piece 1 of the composite material nacelle front mounting edge from colliding with the inner wall of the heating furnace during loading. The upper and lower through holes of the heating furnace are also kept at a certain distance from the simulation piece 1 of the composite material nacelle front mounting edge.

[0046] Step S13: connecting the cylindrical connecting rod at the bottom of the unit to be tested with the chuck of the fatigue testing machine, and connecting the simulation piece 1 with the other chuck of the fatigue testing machine; Step S14: performing a high-temperature tensile test on the simulation piece 1 of the unit to be tested to obtain a test result.

[0047] Through the above steps, the heating furnace can accurately control the temperature, for example, constant temperature, heating rate, and the fatigue testing machine can accurately control the tensile load, for example, load amplitude and loading frequency. The effective control of temperature and load is realized through the cooperation of the two, and the performance data of the simulation piece under different working conditions, such as high-temperature tensile strength, elongation at break, and fatigue life, are obtained. The data dimension is more comprehensive. Since the test constraints, environment, and load are equivalent to the real service working conditions, the high-temperature tensile performance of the simulation piece obtained by the test can be directly mapped to the real composite material case mounting edge.

[0048] For example, if the simulation piece 1 breaks at 800℃ and under a tensile load of 10kN, it can be inferred that the bearing limit of the real case mounting edge under similar working conditions, which provides a basis for the safety factor setting and material selection optimization during design, and avoids safety hazards caused by distorted test data.

[0049] In one embodiment, step S11 includes: fixing the first side edge of the simulation piece 1 between the support piece 4 and the first limiting piece 3 by using the first fixing piece 2; and fixing one end of the second limiting piece 5 on the support piece 4 by using the second fixing piece 6, so that the other end of the second limiting piece 5 abuts against the second side edge of the simulation piece 1.

[0050] The first limiting piece 3 and the support piece 4 form a limiting space, and the short edge of the simulation piece 1 is constrained in two directions through the first fixing piece 2, which limits the transverse displacement and vertical warping of the short edge of the simulation piece 1, avoids the position deviation of the simulation piece 1 due to stress during the test, and the second limiting piece 5 abuts against the long edge of the simulation piece 1 to constrain the long edge of the simulation piece 1. Through single-point or multi-point abutting, the radial or axial displacement of the long edge of the simulation piece 1 can be effectively limited, the precise fixing of the simulation piece 1 is realized, the operation process is simplified, the simulation piece 1 is protected, and the reliability and efficiency of the test are improved. The problems of poor clamping precision and complex operation of the clamping device in the prior art are solved.

[0051] In one embodiment, step S14 includes: turning off the fatigue testing machine; setting the heating temperature of the heating furnace to a preset temperature and starting the heating furnace to heat; waiting for a preset time after the temperature of the heating furnace reaches the preset temperature, and then turning on the fatigue testing machine to perform a high-temperature tensile test; and using the digital image correlation method to monitor and collect data in real time during the test to obtain a test result.

[0052] After the fatigue testing machine is turned off, the heating furnace is started, so that the heating furnace can be prevented from being loaded in advance when the temperature of the heating furnace does not reach the preset temperature, if the tensile load is applied at low temperature, the simulation piece will first generate low-temperature deformation, after the temperature rises, the composite material may appear secondary deformation superposition due to high-temperature softening, so that the test data cannot reflect the pure tensile properties at high temperature.

[0053] After the temperature reaches the standard, a preset time is waited, so that the whole to-be-tested unit can reach thermal equilibrium, because the temperature in the heating furnace reaches the standard, but the internal temperature of the simulation piece 1 is different due to the multilayer structure of the composite material, for example, the temperature of the surface layer is high, and the temperature of the inner layer is low, if loading is immediately performed, the mechanical property difference of different regions of the simulation piece will cause uneven stress distribution, and the test result is distorted, and the waiting for heat preservation can eliminate the temperature gradient, so that the whole simulation piece 1 is ensured to be in a uniform preset high-temperature environment, and the stress state is consistent with the actual service when loading.

[0054] The technical scheme of the present application has the following technical effects: The present application fixes the short side of the composite material nacelle front mounting edge simulation piece between the support piece 4 and the first limiting piece 3 through the fastening bolt, realizes the clamping of the composite material nacelle front mounting edge simulation piece, fixes one end of the second limiting piece 5 to the side edge of the support piece 4 through the bolt, ensures the stable connection, provides a reliable positioning reference, the other end of the second limiting piece 5 is in close contact with the composite material nacelle front mounting edge simulation piece, plays the role of accurate displacement limitation and positioning, at the same time, the heating furnace device with a smaller volume is adopted, so that the temperature in the loading process is more stable, effectively solves the problems that the clamping effect of the existing clamping device on the composite material nacelle front mounting edge simulation piece is poor, the workpiece is easily damaged, and the operation is inconvenient, and has the effects of stable and reliable clamping and fastening, easy high-temperature loading, and true simulation of the tensile state of the nacelle front mounting edge simulation piece.

[0055] For the convenience of description, spatial relative terms such as "above", "upper", "on", "top", etc. can be used herein to describe the spatial positional relationship of one device or feature with other devices or features as shown in the drawings. It should be understood that the spatial relative terms are intended to include different orientations in use or operation in addition to the orientation of the device described in the drawings. For example, if the device in the drawing is inverted, the device described as "above" or "on" other devices or structures will be positioned "below" or "under" other devices or structures. Therefore, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated by 90 degrees or in other orientations), and the spatial relative description used herein is interpreted accordingly.

[0056] In addition to the above, it should be noted that the terms "one embodiment," "another embodiment," and "embodiment" used in this specification refer to specific features, structures, or characteristics described in connection with that embodiment, which are included in at least one embodiment described in the general description of this application. The appearance of the same expression in multiple places in the specification does not necessarily refer to the same embodiment. Furthermore, when a specific feature, structure, or characteristic is described in connection with any embodiment, the intention is to suggest that implementing such a feature, structure, or characteristic in conjunction with other embodiments also falls within the scope of this invention.

[0057] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0058] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A clamping device for a composite material nacelle mounting edge mockup, characterized in that, include: Support (4), the surface of which is used to place the simulation component (1); The first limiting member (3) is located on the simulation member (1). The first limiting member (3) is connected to the support member (4) through the first fixing member (2). A limiting space is formed between the first limiting member (3) and the support member (4). The first side of the simulation member (1) is located in the limiting space. The second limiting member (5) is located on the support member (4). One end of the second limiting member (5) is connected to the support member (4), and the other end of the second limiting member (5) abuts against the second side of the simulation member (1). The length of the second side is greater than the length of the first side.

2. The clamping device of a composite material case mounting edge mockup according to claim 1, characterized in that, The support member (4) is a flat plate structure, the first limiting member (3) is a flat plate structure, the first side of the simulation member (1) is arranged parallel to the extension direction of the support member (4) or the extension direction of the first limiting member (3), and the extension direction of the second side of the simulation member (1) is arranged at an angle to the extension direction of the support member (4) or the extension direction of the first limiting member (3).

3. A clamping device for a composite material fairing mockup of a nacelle mounting edge according to claim 1 or 2, characterized in that, The surface of the support member (4) is provided with at least two first through holes (41), and the first limiting member (3) is provided with at least two second through holes (31). The first through holes (41) and the second through holes (31) are provided in a corresponding manner, and the first fixing member (2) is provided through the second through holes (31) and the first through holes (41).

4. The clamping device of a composite material case mounting edge mockup according to claim 3, characterized in that, The width of the simulation component (1) is a, and the distance between the centers of at least two first through holes (41) or at least two second through holes (31) is b, where a < b - 2r, and r is the radius of the first through hole (41) or the second through hole (31).

5. The clamping device of a composite material case mounting edge mockup according to claim 1, characterized in that, The second limiting member (5) has an L-shaped structure. The first side of the second limiting member (5) is connected to the side wall of the support member (4) through the second fixing member (6). The second side of the second limiting member (5) is connected to the simulation member (1).

6. A clamping device for a composite material nacelle mounting edge mockup according to claim 5, characterized in that The support member (4) has a third through hole on its side wall, and the second limiting member (5) has a fourth through hole on its first side. The third through hole and the fourth through hole are provided correspondingly, and the second fixing member (6) is provided through the fourth through hole and the third through hole.

7. The clamping device of a composite material case mounting edge mockup according to claim 1, characterized in that, The bottom of the support member (4) is connected to a cylindrical connecting rod (7), which is used to connect with the clamp of the fatigue testing machine.

8. A method of testing a composite fairing mounting edge mockup, characterized in that, The test method is based on the clamping device of the composite material casing mounting edge simulator according to any one of claims 1-7, and the test method includes: Step S11: The simulation component (1) is clamped and limited by the support component (4), the first limiting component (3), and the second limiting component (5) to obtain the test unit; Step S12: Place the unit to be tested in a heating furnace, wherein the upper and lower ends of the heating furnace are respectively provided with through holes for the second side of the simulation component (1) and the cylindrical connecting rod (7) at the bottom of the unit to be tested to extend out; Step S13: connecting the cylindrical connecting rod at the bottom of the unit to be tested with a chuck of the fatigue testing machine, connecting the simulation piece (1) with another chuck of the fatigue testing machine; Step S14: performing high-temperature tensile test on the simulation piece (1) of the unit to be tested to obtain a test result.

9. The test method of claim 8, wherein, The step S11 comprises: adopting a first fixing piece (2) to fix a first side edge of the simulation piece (1) between the support piece (4) and the first limiting piece (3); adopting a second fixing piece (6) to fix one end of the second limiting piece (5) on the support piece (4) so as to abut the other end of the second limiting piece (5) with a second side edge of the simulation piece (1).

10. The test method of claim 8, wherein, The step S14 comprises: closing the fatigue testing machine; setting the heating temperature of the heating furnace as a preset temperature, and starting the heating furnace to heat; waiting for a preset time after the temperature of the heating furnace reaches the preset temperature, and starting the fatigue testing machine to perform high-temperature tensile test; adopting digital image correlation method to monitor and collect data in real time during the test to obtain the test result.

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