A modular adjustable test device for simulating the docking of large aircraft components and its use method

Abstract

This invention discloses a modular adjustable testing device and its method for simulating the docking of large aircraft components. The simulation testing module of the device includes at least one simulation testing unit. In the adjustable frame of the simulation testing unit, multiple layers of steel pipes are respectively arranged in the X and Y directions. By driving the inner steel pipes to extend and retract, the dimensions of the adjustable frame in the X and Y directions are adjusted. Multiple simulation testing units are sequentially spliced ​​along the aircraft spanwise or heading to form the spanwise or heading structure of the large aircraft component. By adjusting the dimensions of the adjustable frame in each simulation testing unit in the X and Y directions, the external dimensions of the simulation testing module along the aircraft spanwise or heading are adjusted. A counterweight module is placed on the adjustable frame of each simulation testing unit, and counterweights are applied to simulate the weight and center of gravity of the large aircraft component. The center of gravity position of the simulation testing module and individual or partial simulation testing units is measured using a CNC positioner.

Description

Technical Field

[0001] This invention relates to, but is not limited to, the field of aircraft large component assembly and docking technology, and particularly to a modular adjustable test device for simulating the docking of aircraft large components and its usage method. Background Technology

[0002] In aircraft assembly, the docking of large components, such as the fuselage and wings, is a crucial step in aircraft manufacturing. The fuselage is typically divided into three parts: the forward fuselage, the mid-fuselage, and the aft fuselage. Similarly, the wings are usually divided into three parts: the left wing, the center wing box, and the right wing. After each individual component is manufactured, it needs to be placed on four CNC positioners for attitude adjustment and docking. This verifies the positioning accuracy and repeatability of the CNC positioners, as well as the assembly process for the large aircraft components. Once the fuselage or wing components are docked, they are fixed in place, completing the assembly of the entire fuselage or wing. A single CNC positioner has degrees of freedom in the X, Y, and Z directions; multiple CNC positioners working together can perform translation and rotation of aircraft components in these three directions.

[0003] Large aircraft components are inherently valuable. Before the final attitude adjustment and docking of the aircraft, large aircraft component simulation test devices are typically used to conduct tests on the fuselage or wing to determine whether the CNC positioner achieves the positioning accuracy and repeatability under the predetermined load. Currently, each aircraft assembly line requires two different large aircraft component simulation test devices for the fuselage and wings. Furthermore, the simulation test devices for different aircraft models differ significantly and are incompatible. The large component simulation test devices are expensive and have long manufacturing cycles. These high costs and timelines limit the rapid mass production of aircraft products. Summary of the Invention

[0004] The purpose of this invention is to solve the above-mentioned technical problems. This invention provides a modular adjustable test device for simulating the docking of large aircraft components and its usage method. This addresses the problem that existing assembly methods for large aircraft components require the separate establishment of two different aircraft component simulation test devices for the fuselage and wings, and that aircraft component simulation test devices for different aircraft models are incompatible, resulting in high costs and time constraints that limit the rapid mass production of aircraft products.

[0005] The technical solution of the present invention: In a first aspect, the embodiments of the present invention provide a modular adjustable test device for simulating the docking of large aircraft components, including: a large aircraft component simulation test module 1, multiple CNC positioners 3 and a counterweight module 4;

[0006] The aircraft large component simulation test module 1 includes at least one aircraft large component simulation test unit. Each aircraft large component simulation test unit is configured as a symmetrical structure along the aircraft's heading and span, including: an adjustable frame 6, a power module a, and a support and hoisting assembly 12. The adjustable frame 6 is configured as a double-layer frame formed by steel pipes in three directions. The double-layer frame has multiple nested steel pipes in the X and Y directions, respectively. A power module a is set in the middle of the preset multiple steel pipes to drive the inner steel pipes of the preset multiple steel pipes to extend or retract to both sides, so that the size of the adjustable frame 6 can be adjusted in the X and Y directions. Support and hoisting assemblies 12 are symmetrically installed on both sides of each aircraft large component simulation test unit for hoisting and supporting the aircraft large component simulation test unit.

[0007] Multiple large aircraft component simulation test units are sequentially spliced ​​along the aircraft spanwise or the aircraft heading. Adjacent steel pipes of adjacent adjustable frame 6 are fixedly connected to each other. This is used to simulate the spanwise or heading structure of the large aircraft component through the overall structure formed by splicing. Furthermore, by adjusting the dimensions of the adjustable frame 6 in the X and Y directions in each large aircraft component simulation test unit, the external dimensions of the large aircraft component simulation test module 1 along the aircraft spanwise or the aircraft heading can be adjusted.

[0008] The counterweight module 4 is placed on the base plate of the adjustable frame 6 of each aircraft large component simulation test unit, and is used to simulate the weight and center of gravity of the aircraft large components by applying counterweights.

[0009] The aircraft large component simulation test module 1 is placed on multiple CNC positioners 3 by the support and hoisting components 12 on both sides of the adjustable frame 6 of each size, so as to measure the center of gravity position of the aircraft large component simulation test module 1 and the individual or part of the aircraft large component simulation test units therein through the CNC positioners 3.

[0010] Optionally, the modular adjustable test device for simulating the docking of large aircraft components as described above further includes: at least one set of supplementary simulation test frames 2, and the supplementary simulation test frames 2 are configured as a symmetrical structure along the aircraft heading.

[0011] The supplementary simulation test frame 2 is fixedly installed at the front end and / or rear end of the aircraft large component simulation test module 1. It is used to simulate the heading structure of the aircraft large component and the size, center of gravity, connection form and adjustment process of the heading structure of different types of aircraft large components by cooperating with the aircraft large component simulation test module 1.

[0012] The supplementary simulation test frame 2 includes: a first frame 21 and a second frame 22 arranged vertically overlapping each other, and support and hoisting components 12 symmetrically installed on both sides of the frame; the weight and center of gravity of the first frame 21 and the second frame 22 are adjusted by placing a counterweight module 4.

[0013] Optionally, the modular adjustable test device for simulating the docking of large aircraft components as described above also includes: docking simulation module 7;

[0014] The docking simulation module 7 includes three sets of planar docking plates. Each set of planar docking plates includes two symmetrically arranged connecting plates. Two L-shaped docking plates are symmetrically installed on the connecting plates. One side plate of the two L-shaped docking plates is installed on the corresponding connecting plate through waist-shaped holes and screws. The other side plates of the two L-shaped docking plates are arranged horizontally opposite each other.

[0015] The first set of planar mating plates 7-1 also includes: two horizontal mating plates arranged to meet along the horizontal plane; the two horizontal mating plates are respectively installed on the opposite side plates of the corresponding L-shaped mating plates through their base plates, so that the two horizontal mating plates overlap and meet in the horizontal plane, which is used for drilling holes after mating and installation;

[0016] The second set of planar mating plates 7-2 also includes: two vertical mating plates arranged to meet vertically; the two vertical mating plates are respectively installed on the opposite side plates of the corresponding L-shaped mating plates through their base plates, so that the two vertical mating plates overlap and meet vertically, which is used for drilling holes after mating and installation.

[0017] In the third set of planar mating plates 7-3, the other side plate of the two L-shaped mating plates is used as a mating plate for bonding installation, and holes are made after bonding installation.

[0018] The installation positions of the three sets of planar docking plates are used to simulate the docking surface positions of large components of actual aircraft. After each set of planar docking plates is installed on the adjacent steel frame of the adjacent adjustable frame 6 through its connecting plate, the repeatability of the hole positioning is detected by drilling holes in the docking plates and moving the three sets of planar docking plates.

[0019] Optionally, in the modular adjustable test device for simulating the docking of large aircraft components as described above, the power module a in each of the large aircraft component simulation test units includes: a drive motor 5, a rack 8, and a gear 9;

[0020] The inner steel pipe of the multi-layer steel pipe in the adjustable frame 6 includes symmetrically arranged two-sided segmented steel pipes. A rack 8 is fixedly installed on the upper side of one-sided segmented steel pipe and a rack 8 is fixedly installed on the lower side of the other-sided segmented steel pipe. Gears 9 mesh with two gears 8 respectively. The drive motor 5 is set on the outer steel pipe at the corresponding position. The end of the drive motor 5 is fixedly connected to the gear 9 and is used to drive the gear 9 to rotate, thereby moving the racks 8 on both sides of the inner steel pipe fixedly installed in the adjustable frame 6 to extend or retract the inner steel pipe, thereby adjusting the external dimensions of the single aircraft large component simulation test unit in both the flight direction and span direction of the aircraft.

[0021] Optionally, in the modular adjustable test apparatus for simulating the docking of large aircraft components as described above,

[0022] Each of the aforementioned large aircraft component simulation test units includes an adjustable frame 6 comprising: an upper steel pipe frame and a lower steel pipe frame with identical structures, and a Z-direction steel pipe for connecting the upper and lower steel pipe frames; wherein, the upper and lower steel pipe frames each comprise: a rectangular outer frame formed by two X-direction steel pipes and two Y-direction steel pipes, two integral Y-direction steel pipes disposed in the middle of the rectangular outer frame, two rows of segmented X-direction steel pipes disposed between the rectangular outer frame and the two integral Y-direction steel pipes, and two columns of segmented Y-direction steel pipes disposed between the rectangular outer frame and the two integral Y-direction steel pipes, the two columns of segmented Y-direction steel pipes forming a segmented structure between the two rows of segmented X-direction steel pipes.

[0023] Optionally, in the modular adjustable test apparatus for simulating the docking of large aircraft components as described above,

[0024] The two X-direction steel pipes and two Y-direction steel pipes in the rectangular outer frame, as well as the adjustable portions of the two integral Y-direction steel pipes and the two rows of segmented X-direction steel pipes, are configured as secondary telescopic steel pipes, formed by two nested layers of steel pipes; the portion of the steel pipe between the segmented X-direction steel pipes and the rectangular outer frame in the two rows of segmented Y-direction steel pipes is configured as a tertiary telescopic steel pipe, formed by three nested layers of steel pipes; convex guide rails 11 are provided on the upper and lower sides of the inner steel pipe, and concave grooves matching the guide rails 11 are provided on the upper and lower inner walls of the outer steel pipe, so that the inner steel pipe and the outer steel pipe are tightly connected;

[0025] In each of the rectangular outer frames of the adjustable frame 6, the power module a is provided in the middle of the two X-direction steel pipes and the middle of the two integrated Y-direction steel pipes, for adjusting the external dimensions of the adjustable frame 6 in the X and Y directions.

[0026] Optionally, in the modular adjustable test apparatus for simulating the docking of large aircraft components as described above,

[0027] The bottom of the support and hoisting assembly 12 is provided with a ball head, which is locked with the ball socket at the upper end of the CNC positioner 3 at the corresponding position to realize the fixed connection between each large aircraft component simulation test unit and the CNC positioner 3; and the support and hoisting assembly 12 has two pins, which are connected with the hoisting device to realize the hoisting of the large component simulation test module.

[0028] Optionally, in the modular adjustable test apparatus for simulating the docking of large aircraft components as described above,

[0029] In each large aircraft component simulation test unit, multiple round holes are opened on the steel pipes in the Y direction on both sides of the rectangular outer frame of the adjustable frame 6. The round holes of adjacent large aircraft component simulation test units are aligned and connected by U-shaped connecting frame 10 and double-headed studs.

[0030] Secondly, embodiments of the present invention also provide a method for using a modular adjustable test device for simulating the docking of large aircraft components, wherein the center of gravity of the modular adjustable test device for simulating the docking of large aircraft components as described in any of the above claims is adjusted, and the method of use includes:

[0031] Step 1: The modular adjustable test device is placed on four CNC positioners 3 by symmetrically installed support and hoisting components 12; wherein the coordinates of the four CNC positioners 3 are symmetrically arranged along the XZ plane.

[0032] Step 2: Using the Z-axis force sensors at the top of the four CNC positioners 3, the center coordinates of the four CNC positioners 3 are read in the aircraft coordinate system as (x1, y1), (x2, y2), (x3, y3), (x4, y4), and the four force values ​​are read as F1, F2, F3, F4.

[0033] Step 3: Using coordinates (x1, y1) as a reference, calculate the actual center-of-gravity coordinates of the modular adjustable test device. The calculation method for the center-of-gravity coordinates is as follows:

[0034]

[0035] Wherein, coordinates (x0, y0) are the theoretical center of gravity coordinates of the modular adjustable test device, and coordinates (x'0, y'0) are the actual center of gravity coordinates of the overall adjustable test device;

[0036] Step 4: Determine whether the coordinates (x0, y0) and (x'0, y'0) satisfy the following conditions:

[0037] When |x'0-x0|≤a, |y'0-y0|≤b and |g'0-g0|≤c are simultaneously satisfied, the weight and center of gravity of the modular adjustable test device meet the design requirements.

[0038] Where g0 is the actual weight of the major components of the aircraft, g'0 is the actual weight of the adjustable test device in this test; a is the error criterion for the allowable center of gravity position in the X direction, b is the error criterion for the allowable center of gravity position in the Y direction, and c is the error criterion for the overall weight.

[0039] Optionally, the method of using the modular adjustable test apparatus for simulating the docking of large aircraft components as described above further includes:

[0040] In a single measurement using the method, the modular adjustable test device includes a single or partial large component simulation test unit, or an overall aircraft large component simulation test module 1, or a combination structure of the overall aircraft large component simulation test module 1 and the supplementary simulation test frame 2; to simulate the corresponding position of the aircraft large component through a single large component simulation test unit, to simulate the combination structure of the corresponding position of the aircraft large component through partial large component simulation test units, to simulate the aircraft spanwise structure or heading structure through the aircraft large component simulation test module 1, and to simulate the aircraft heading structure through the combination structure of the aircraft large component simulation test module 1 and the supplementary simulation test frame 2.

[0041] The beneficial effects of the present invention: The embodiments of the present invention provide a modular adjustable test device and its method for simulating the docking of large aircraft components. Multiple aircraft component simulation test units with identical structures and dimensions are spliced ​​together to form an aircraft component simulation test module 1. A counterweight module 4 is used to simulate the weight and center of gravity of the corresponding aircraft component, and a CNC positioner 3 is used to measure the center of gravity position of the modular adjustable test device. The adjustable frame 6 in a single aircraft component simulation test unit is a double-layer frame formed by steel pipes in three directions. Multiple nested steel pipes are arranged in the X and Y directions of the double-layer frame. A power module a is set in the middle of a preset multi-layer steel pipe, which drives the inner layer of the preset multi-layer steel pipe to extend or retract to both sides, thereby adjusting the dimensions of the adjustable frame 6 in the X and Y directions. This allows the external dimensions of the assembled aircraft component simulation test module 1 to be adjustable along the aircraft spanwise or yaw direction. Compared with the prior art, the technical solution provided by the embodiments of the present invention has the following beneficial effects:

[0042] (1) The modular adjustable test device for simulating the docking of large aircraft components provided by the present invention can be applied to the simulation docking process of various aircraft of different sizes. It replaces the traditional special simulation tooling that is only applicable to a single aircraft type. It has a wide range of applications, reduces costs, and improves the efficiency of aircraft assembly docking.

[0043] (2) The modular adjustable test device provided by the present invention can calculate and display the weight and center of gravity of a single or part of the aircraft large component simulation test unit, as well as the overall aircraft large component simulation test module 1 and its superimposed configuration module 4 and supplementary simulation test frame 2 in real time, and the method of adjusting the weight and center of gravity is convenient and quick.

[0044] (3) The modular adjustable test device and corresponding usage method for simulating the docking of large aircraft components provided by the present invention have been verified and can meet actual needs. Attached Figure Description

[0045] The accompanying drawings are provided to further understand the technical solutions of the present invention and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of the present invention and do not constitute a limitation on the technical solutions of the present invention.

[0046] Figure 1 This is a schematic diagram of the overall structure of a modular adjustable test device for simulating the docking of large aircraft components, provided by an embodiment of the present invention.

[0047] Figure 2 for Figure 1 The illustrated embodiment provides a structural schematic diagram of a single aircraft large component simulation test unit in a modular adjustable test device for simulating the docking of large aircraft components.

[0048] Figure 3 for Figure 2 A schematic diagram of the splicing structure of the adjacent large aircraft component simulation test unit provided in the embodiment shown;

[0049] Figure 4 As shown, Figure 1 A schematic diagram of the docking simulation module in the modular adjustable test device for simulating the docking of large aircraft components provided in the embodiment shown; Figure 4 Figure a shows the first set of planar mating plates 7-1. Figure 4 Figure b in the diagram shows the second set of planar mating plates 7-2. Figure 4 Figure c in the diagram represents the third group of planar mating plates 7-3;

[0050] Figure 5 for Figure 2 The illustrated embodiment provides a schematic diagram of the power module structure in a single large aircraft component simulation test unit.

[0051] Figure 6 for Figure 3 A schematic diagram of the connecting parts in the splicing structure of the adjacent large aircraft component simulation test unit provided in the embodiment shown;

[0052] Figure 7 for Figure 2The illustrated embodiment provides a schematic diagram of the structure of multiple steel pipes in a single aircraft large component simulation test unit.

[0053] Explanation of reference numerals in the attached figures:

[0054] 1. Aircraft large component simulation test module; 1-1, 1-2, 1-3, and 1-4 are all aircraft large component simulation test units; 2. Supplementary simulation test framework; 21. Frame 1; 22. Frame 2; 3. CNC positioner; 4. Counterweight module; a. Power module; 5. Drive motor; 6. Adjustable size frame; 7. Docking simulation module; 8. Rack; 9. Gear; 10. Connecting frame; 11. Guide rail; 12. Support and hoisting components. Detailed Implementation

[0055] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

[0056] As explained in the background section, this paper discusses the assembly methods for large aircraft components and the requirements for positioning accuracy and repeatability during assembly. Existing assembly methods for large aircraft components require the separate establishment of two different simulation test devices for the fuselage and wings. Furthermore, these simulation test devices are incompatible with different aircraft models, resulting in high costs and long manufacturing cycles. These high costs and timelines limit the rapid mass production of aircraft products.

[0057] In the Chinese patent with publication number CN207607664U, the test piece simulates some structural components of the fuselage. The designed test loading and support dummy is used to conduct static tests under balanced loads. The stiffness and strength meet the test requirements, and the machining and operation are relatively convenient. Its shortcomings are that it only simulates some parts of the aircraft structure, and the test piece has a fixed size, simple structure, and poor adjustability.

[0058] To address the assembly issues of large aircraft components, designing an adjustable testing device that can adapt to various aircraft models and is cost-effective can improve the efficiency of simulation testing of large aircraft components and reduce aircraft manufacturing costs. Based on this requirement, this invention provides a modular adjustable testing device for simulating the docking of large aircraft components and its usage method.

[0059] The present invention provides the following specific embodiments, which can be combined with each other. For the same or similar concepts or processes, they may not be described again in some embodiments.

[0060] Figure 1This is a schematic diagram of the overall structure of a modular adjustable test device for simulating the docking of large aircraft components, provided by an embodiment of the present invention. Figure 2 for Figure 1 The illustrated embodiment provides a schematic diagram of the structure of a single aircraft large component simulation test unit in a modular adjustable test apparatus for simulating the docking of large aircraft components. Figure 3 for Figure 2 The illustrated embodiment provides a schematic diagram of the splicing structure of an adjacent large aircraft component simulation test unit. (Refer to...) Figure 1 and Figure 2 As shown, the overall structure of the modular adjustable test device for simulating the docking of large aircraft components provided in this embodiment of the invention includes: multiple large aircraft component simulation test modules 1, multiple CNC positioners 3, and a counterweight module 4.

[0061] like Figure 1 and Figure 2 In the structure of the modular adjustable test device shown, the aircraft large component simulation test module 1 includes at least one aircraft large component simulation test unit. For example... Figure 1 As illustrated, the aircraft large component simulation test module 1 includes four aircraft large component simulation test units, namely 1-1, 1-2, 1-3, and 1-4. These four aircraft large component simulation test units have the same structure, and their overall size can be adjusted according to the actual size of the aircraft being simulated. The size of each aircraft large component simulation test unit is the same as that of the corresponding aircraft large component. It is used to simulate the size and connection method of multiple fuselage sections and wings in aircraft of different sizes during the assembly process, as well as to simulate the process and precision of adjusting the center of gravity of the aircraft. In addition, the weight and center of gravity of each of the above-mentioned aircraft large component simulation test units combined with the counterweight module 4 are used to control the weight and center of gravity of the aircraft large component during the assembly process.

[0062] like Figure 1 and Figure 2 As shown, each aircraft major component simulation test unit is configured as a symmetrical structure along the aircraft's heading and span, including: an adjustable frame 6, a power module a, and support and hoisting components 12. The adjustable frame 6, as the main structure of the unit, is a double-layered frame formed by steel pipes in three directions. Multiple nested steel pipes are arranged in the X and Y directions of the double-layered frame. A power module a is pre-installed in the middle of the pre-installed multiple steel pipes, driving the inner layer of the pre-installed multiple steel pipes to extend or retract to both sides, thereby adjusting the dimensions of the adjustable frame 6 in the X and Y directions. Support and hoisting components 12 are symmetrically installed on both sides of each aircraft major component simulation test unit for hoisting and supporting the aircraft major component simulation test unit.

[0063] like Figure 1As shown, multiple large aircraft component simulation test units are sequentially spliced ​​along the aircraft spanwise or the aircraft heading. Adjacent steel pipes of adjacent adjustable frames 6 are fixedly connected to each other, and the overall structure formed by splicing is used to simulate the spanwise or heading structure of the large aircraft component. In addition, by adjusting the dimensions of the adjustable frames 6 in the X and Y directions in each large aircraft component simulation test unit, the external dimensions of the large aircraft component simulation test module 1 along the aircraft spanwise or the aircraft heading can be adjusted.

[0064] In this embodiment of the invention, multiple large aircraft component simulation test units are combined (i.e.) Figure 1 The combination of 1-1 to 1-4 constitutes the main structure for simulating the assembly process of large aircraft components. The overall dimensions of the large aircraft component simulation test module 1 are adjustable along the heading or span of the aircraft.

[0065] like Figure 1 and Figure 2 As shown, the counterweight module 4 is placed on the base plate of the adjustable frame 6 of each aircraft large component simulation test unit, and is used to simulate the weight and center of gravity of the aircraft large component by applying counterweight. In a specific implementation, for example, the counterweight module 4 includes multiple disc-shaped iron blocks with central holes, and the applied counterweight is located at the center. By applying the counterweight to each aircraft large component simulation test unit, the weight of this unit is made the same as the weight of the corresponding aircraft large component. In addition, by using the counterweight module 4 in conjunction with the usage method provided in the embodiment of the present invention, the center of gravity of this unit is adjusted to be the same as the center of gravity of the corresponding aircraft large component.

[0066] like Figure 1 and Figure 2 As shown, the large aircraft component simulation test module 1 is placed on multiple CNC positioners 3 by the support and hoisting components 12 on both sides of the adjustable frame 6 of each size, so as to measure the center of gravity position of the large aircraft component simulation test module 1 and the individual or part of the large aircraft component simulation test units therein through the CNC positioners 3.

[0067] It should be noted that, in this embodiment of the invention, not only can the weight and center of gravity of the combined aircraft large component simulation test module 1 be adjusted, but the weight and center of gravity of a single or part of the aircraft large component simulation test unit can also be adjusted in the same way; in actual operation, the unit or the whole module to be adjusted is selected according to the installation work requirements.

[0068] In one implementation of this invention, such as Figure 1 As shown, the modular adjustable test device is characterized by further comprising: at least one set of supplementary simulation test frames 2, wherein the supplementary simulation test frames 2 are configured as a symmetrical structure along the flight path of the aircraft.

[0069] In this implementation, the supplementary simulation test frame 2 is fixedly installed at the front end and / or rear end of the aircraft large component simulation test module 1. Specifically, the supplementary simulation test frame 2 is installed in conjunction with the aircraft large component simulation test module 1 to simulate the heading structure of the aircraft large component. For example, the supplementary simulation test frame 2 can simulate the nose and / or tail of the aircraft heading structure, as well as simulate the size, center of gravity, connection form and adjustment process of the heading structure of different types of aircraft large components.

[0070] like Figure 2 As shown, the supplementary simulation test frame 2 includes: a first frame 21 and a second frame 22 stacked vertically, and support and hoisting components 12 symmetrically installed on both sides of the frame. It should be noted that the supplementary simulation test frame 2 can be configured as a dedicated fixed frame for simulating aircraft of different sizes and models; the size of the supplementary simulation test module 2 will differ depending on the type or size of the aircraft being simulated. Alternatively, the first frame 21 and the second frame 22 can also be configured as a frame structure with adjustable dimensions, similar to the adjustable frame 6, and the weight and center of gravity of the first frame 21 and the second frame 22 can be adjusted by placing a counterweight module 4.

[0071] In practice, frame 1 (21) and frame 2 (22) are connected vertically using bolts. The outlines and dimensions of frame 1 (21) and frame 2 (22) match the dimensions of the nose or tail of the aircraft's major components. Furthermore, the dimensions of the supplementary simulation test module 2 differ for different real aircraft major components; the supplementary simulation test module 2 can be a variable structure.

[0072] In one implementation of this invention, the modular adjustable testing device further includes a docking simulation module 7; this docking simulation module 7 is used to simulate the docking structure of multiple fuselage and wing sections in a large aircraft component, and each set of planar docking plates has holes that are coordinated with the repeatability accuracy of the CNC positioner 3. Figure 4 As shown, Figure 1 The diagram shown is a structural schematic of the docking simulation module in the modular adjustable test apparatus for simulating the docking of large aircraft components provided in the embodiment. Figure 4 Figure a shows the first set of planar mating plates 7-1. Figure 4 Figure b in the diagram shows the second set of planar mating plates 7-2. Figure 4 Figure c in the diagram represents the third group of planar mating plates 7-3; Figure 3 The docking simulation module 7 is installed between adjacent large aircraft component simulation test units shown.

[0073] like Figure 3 and Figure 4As shown, the docking simulation module 7 includes three sets of planar docking plates. Each set of planar docking plates includes two symmetrically arranged connecting plates. Two L-shaped docking plates are symmetrically installed on the connecting plates. One side plate of the two L-shaped docking plates is installed on the corresponding connecting plate through waist-shaped holes and screws. The other side plates of the two L-shaped docking plates are horizontally opposite each other.

[0074] The first set of planar mating plates 7-1 also includes: two horizontal mating plates arranged to meet along the horizontal plane; the two horizontal mating plates are respectively installed on the opposite side plates of the corresponding L-shaped mating plates through their base plates, so that the two horizontal mating plates overlap and meet in the horizontal plane, which is used for drilling holes after mating and installation;

[0075] The second set of planar mating plates 7-2 also includes: two vertical mating plates arranged to meet vertically; the two vertical mating plates are respectively installed on the opposite side plates of the corresponding L-shaped mating plates through their base plates, so that the two vertical mating plates overlap and meet vertically, which is used for drilling holes after mating and installation.

[0076] In the third set of planar mating plates 7-3, the other side plate of the two L-shaped mating plates is used as a mating plate for bonding installation, and holes are made after bonding installation.

[0077] In this implementation, the installation positions of the three sets of planar docking plates are used to simulate the docking surface positions of large components of actual aircraft. In addition, after each set of planar docking plates is installed on the adjacent steel frame of the adjacent adjustable frame 6 through its connecting plate, the repeatability of the hole positioning is detected by drilling holes in the docking plates and moving the three sets of planar docking plates.

[0078] In one implementation of this invention, a specific implementation of the power module a in an aircraft large component simulation test unit is provided, such as... Figure 5 As shown, Figure 2 The illustrated embodiment provides a schematic diagram of the power module in a single aircraft major component simulation test unit. The power module a in this implementation includes: a drive motor 5, a rack 8, and a gear 9.

[0079] In this implementation, the inner layer of the multi-layer steel pipe in the adjustable frame 6 includes symmetrically arranged two-sided segmented steel pipes. A rack 8 is fixedly installed on the upper side of one-sided segmented steel pipe, and a rack 8 is fixedly installed on the lower side of the other-sided segmented steel pipe. Gears 9 mesh with the two gears 8 respectively. The drive motor 5 is set on the outer steel pipe at the corresponding position. The end of the drive motor 5 is fixedly connected to the gear 9 and is used to drive the gear 9 to rotate, thereby moving the racks 8 on both sides of the inner layer steel pipe fixedly installed in the adjustable frame 6 to extend or retract the inner layer steel pipe, thereby adjusting the external dimensions of the single aircraft large component simulation test unit in both the flight direction and span direction of the aircraft.

[0080] In one implementation of this invention, a specific implementation of the adjustable frame 6 in an aircraft large component simulation test unit is provided, referring to... Figures 1 to 3 As shown, the adjustable frame 6 in each of the aircraft major component simulation test units includes: an upper steel tube frame and a lower steel tube frame with identical structures, and a Z-direction steel tube for connecting the upper steel tube frame and the lower steel tube frame.

[0081] In this implementation, the upper and lower steel pipe frames each include: a rectangular outer frame formed by two X-direction steel pipes and two Y-direction steel pipes; two integral Y-direction steel pipes set in the middle of the rectangular outer frame; two rows of segmented X-direction steel pipes supported by the rectangular outer frame and the two integral Y-direction steel pipes (the portion of the segmented X-direction steel pipe between the two integral Y-direction steel pipes is non-adjustable, and the portion between the integral Y-direction steel pipe and the rectangular outer frame is adjustable, i.e., a multi-layered structure of nested steel pipes); and two columns of segmented Y-direction steel pipes set between the rectangular outer frame and the two integral Y-direction steel pipes respectively. These two columns of segmented Y-direction steel pipes form a segmented structure between the two rows of segmented X-direction steel pipes (the portion between the two rows of segmented X-direction steel pipes is non-adjustable, and the portion between the two rows of segmented X-direction steel pipes and the rectangular outer frame is adjustable, i.e., a multi-layered structure of nested steel pipes). Figure 2 It can be seen that the rectangular outer frame formed by the two X-direction steel pipes and the two Y-direction steel pipes, as well as the two integral Y-direction steel pipes set in the middle of the rectangular outer frame, are levers of an integral structure. Other X, Y, and Z-direction steel pipes are welded to the steel pipes on the rectangular outer frame and to the steel pipe in the middle. In addition, the cross-section of each steel pipe in the adjustable frame 6 is rectangular. The length direction of the cross-section of the X-direction steel pipe is perpendicular to the X-direction, and the length direction of the cross-section of the Y-direction steel pipe is perpendicular to the Y-direction.

[0082] In this implementation, the two X-direction steel pipes and two Y-direction steel pipes within the rectangular outer frame, as well as the adjustable portions of the two integral Y-direction steel pipes and the two rows of segmented X-direction steel pipes, are configured as secondary telescopic steel pipes, formed by two nested layers of steel pipes. The portion of the segmented Y-direction steel pipes located between the segmented X-direction steel pipes and the rectangular outer frame is configured as a tertiary telescopic steel pipe, formed by three nested layers of steel pipes. The inner steel pipe has convex guide rails 11 on its upper and lower sides, and the outer steel pipe has concave grooves matching the guide rails 11 on its upper and lower inner walls, ensuring a tight connection between the inner and outer steel pipes. The adjustable frame 6 can achieve telescopic movement along the X and Y directions through the aforementioned nested steel pipe structure. Figure 7 As shown, Figure 2 The illustrated embodiment provides a schematic diagram of the multi-layer steel pipe structure in a single large aircraft component simulation test unit. Figure 7The diagram illustrates a three-stage telescopic steel pipe. The structure of a two-stage telescopic steel pipe is similar, except that it has one less layer of steel pipe.

[0083] It should be noted that the guide rail 11 protruding from the inner steel tube in the adjustable frame 6 has a smooth contact surface with the groove on the inner wall of the next outer steel tube, and the telescopic distance meets the requirements of various large aircraft components.

[0084] In one embodiment of the present invention, the bottom of the support and hoisting assembly 12 is provided with a ball head, which is locked with the ball socket at the upper end of the CNC positioner 3 at the corresponding position to realize the fixed connection between each large aircraft component simulation test unit and the CNC positioner 3; in addition, the support and hoisting assembly 12 has two pins, which are connected with the hoisting device to realize the hoisting of the large component simulation test module.

[0085] In one implementation of this invention, in each aircraft large component simulation test unit, multiple circular holes are provided on the steel pipes in the Y direction on both sides of the rectangular outer frame of the adjustable frame 6. The circular holes of adjacent aircraft large component simulation test units are aligned and connected by a U-shaped connecting frame 10 and double-headed studs. The connection does not affect the extension and retraction of the aircraft large component simulation test module 1 along the Y direction. Figure 6 As shown, Figure 3 The schematic diagram shows the structure of the connecting parts in the splicing structure of the adjacent large aircraft component simulation test unit provided in the embodiment shown.

[0086] The modular adjustable test device for simulating the docking of large aircraft components provided in this invention uses multiple aircraft large component simulation test units with identical structure and size to form an aircraft large component simulation test module 1. A counterweight module 4 is used to simulate the weight and center of gravity of the corresponding aircraft large component, and a CNC positioner 3 is used to measure the center of gravity position of the modular adjustable test device. The adjustable frame 6 in a single aircraft large component simulation test unit is a double-layer frame formed by steel pipes in three directions. Multiple nested steel pipes are arranged in the X and Y directions of the double-layer frame. A power module a is set in the middle of the preset multi-layer steel pipes to drive the inner layer of the preset multi-layer steel pipes to extend or retract to both sides, thereby adjusting the dimensions of the adjustable frame 6 in the X and Y directions. This allows the external dimensions of the assembled aircraft large component simulation test module 1 to be adjustable along the aircraft spanwise or yaw direction. Compared with the prior art, the technical solution provided in this invention has the following beneficial effects:

[0087] (1) The modular adjustable test device for simulating the docking of large aircraft components provided by the present invention can be applied to the simulation docking process of various aircraft of different sizes. It replaces the traditional special simulation tooling that is only applicable to a single aircraft type. It has a wide range of applications, reduces costs, and improves the efficiency of aircraft assembly docking.

[0088] (2) The modular adjustable test device provided by the present invention can calculate and display the weight and center of gravity of a single or part of the aircraft large component simulation test unit, as well as the overall aircraft large component simulation test module 1 and its superimposed configuration module 4 and supplementary simulation test frame 2 in real time, and the method of adjusting the weight and center of gravity is convenient and quick.

[0089] (3) The modular adjustable test device and corresponding usage method for simulating the docking of large aircraft components provided by the present invention have been verified and can meet actual needs.

[0090] Based on the modular adjustable test device for simulating the docking of large aircraft components provided in the above embodiments of the present invention, the present invention also provides a method for using the modular adjustable test device. The center of gravity of the modular adjustable test device for simulating the docking of large aircraft components provided in any of the above embodiments can be adjusted. The method of use provided by the present invention may include the following steps:

[0091] Step 1: The modular adjustable test device is placed on four CNC positioners 3 by symmetrically installed support and hoisting components 12; wherein the coordinates of the four CNC positioners 3 are symmetrically arranged along the XZ plane.

[0092] In step 1, considering that in the aircraft coordinate system, the coordinates of the aircraft's center of gravity only focus on the X and Y directions; for example, the modular adjustable test device is symmetrically set along the X direction, which is used to simulate the heading structure of large aircraft components; the four CNC positioners are symmetrically set along the XZ plane; as another example, the modular adjustable test device is symmetrically set along the Y direction, which is used to simulate the spanwise structure of large aircraft components; the four CNC positioners are symmetrically set along the YZ plane.

[0093] It should be noted that, as Figure 1 As shown, the modular adjustable test device in this embodiment of the invention can be placed on multiple CNC positioners 3 as a whole, and the positioning measurement is performed by four CNC positioners 3 at the bottom of the single or partial or all large component simulation test unit that requires weight and center of gravity measurement.

[0094] Step 2: Using the Z-axis force sensors at the top of the four CNC positioners 3, the center coordinates of the four CNC positioners 3 are read in the aircraft coordinate system as (x1, y1), (x2, y2), (x3, y3), (x4, y4), and the four force values ​​are read as F1, F2, F3, F4.

[0095] Step 3: Using coordinates (x1, y1) as a reference, calculate the actual center-of-gravity coordinates of the modular adjustable test device. The calculation method for the center-of-gravity coordinates is as follows:

[0096]

[0097] Wherein, coordinates (x0, y0) are the theoretical center of gravity coordinates (known quantities) of the modular adjustable test device, and coordinates (x'0, y'0) are the actual center of gravity coordinates of the overall adjustable test device.

[0098] Step 4: Determine whether the coordinates (x0, y0) and (x'0, y'0) satisfy the following conditions:

[0099] When |x'0-x0|≤a, |y'0-y0|≤b and |g'0-g0|≤c are simultaneously satisfied, the weight and center of gravity of the modular adjustable test device meet the design requirements.

[0100] Where g0 is the actual weight of the major components of the aircraft, g'0 is the actual weight of the adjustable test device in this test; a is the error criterion for the allowable center of gravity position in the X direction, b is the error criterion for the allowable center of gravity position in the Y direction, and c is the error criterion for the overall weight.

[0101] In one implementation of the present invention, in a single measurement using the method, the modular adjustable test device is, for example, a single or partial large component simulation test unit, or an aircraft large component simulation test module 1, or a combination structure of an aircraft large component simulation test module 1 and a supplementary simulation test frame 2; to simulate the corresponding position of the aircraft large component through a single large component simulation test unit, to simulate the combination structure of the corresponding position of the aircraft large component through partial large component simulation test units, to simulate the aircraft spanwise structure or heading structure through the aircraft large component simulation test module 1, and to simulate the aircraft heading structure through the combination structure of the aircraft large component simulation test module 1 and the supplementary simulation test frame 2.

[0102] Furthermore, the constant-force compression method for achieving bearing narrowing of elongated parts provided in this embodiment of the invention may further include the following steps:

[0103] Step 6: Perform a quality inspection on the bearings after the bearing end-closing operation. The quality inspection standards include:

[0104] Bearing visual inspection: There should be no wrinkles, cracks and burrs at the end of the bearing. Extrusion marks are allowed. The edge gap at the end of the bearing should be less than 0.1mm.

[0105] Check the no-load starting torque of the bearing; the no-load starting torque meets the installation requirements.

[0106] Check the axial thrust of the bearing. Under the specified axial thrust, there should be no relative displacement between the bearing and the housing bore, or the relative displacement should not exceed 0.1 mm.

[0107] In one implementation of this invention, the method for determining the pressure value in step 4 is, for example:

[0108] Considering that the baffle 72 in the baffle force measuring assembly 7 undergoes a small-angle deformation under pressure, the angle between the axis of the bearing fixing mold 6 and the normal of the baffle 72 is α.

[0109] In this implementation, the pressure value fed back by the pressure sensor 71 is F1, and the axial pressure of the bearing fixing mold 6 is F2. When the control system 9 detects the fed-back pressure value F1, it is:

[0110] When F1 = F2cosα, it indicates that the axial pressure applied to the bearing fixing mold 6 has reached the set pressure value. In this embodiment of the invention, the value of α can be obtained by strength simulation using finite element software.

[0111] While the embodiments disclosed in this invention are as described above, they are merely illustrative of the embodiments to facilitate understanding of the invention and are not intended to limit the invention. Any person skilled in the art to which this invention pertains may make any modifications and variations in the form and details of the implementation without departing from the spirit and scope disclosed herein; however, the scope of patent protection for this invention shall still be determined by the scope defined in the appended claims.

Claims

1. A modular adjustable test device for simulating the docking of large aircraft components, characterized in that, include: Aircraft large component simulation test module (1), multiple CNC positioners (3) and counterweight module (4); The large aircraft component simulation test module (1) includes at least one large aircraft component simulation test unit. Each large aircraft component simulation test unit is configured as a symmetrical structure along the flight direction and span direction of the aircraft, including: a size-adjustable frame (6), a power module (a), and a support and hoisting assembly (12). The size-adjustable frame (6) is configured as a double-layer frame formed by steel pipes in three directions. The double-layer frame is provided with nested multi-layer steel pipes in the X and Y directions respectively. A power module (a) is set in the middle of the preset multi-layer steel pipes so that the inner layer steel pipes of the preset multi-layer steel pipes can be extended or retracted to both sides by the power module (a), so that the size of the size-adjustable frame (6) can be adjusted in the X and Y directions. Support and hoisting assemblies (12) are symmetrically installed on both sides of each large aircraft component simulation test unit for hoisting and supporting the large aircraft component simulation test unit. Multiple large aircraft component simulation test units are spliced ​​together sequentially along the aircraft span or the aircraft heading. The adjacent steel pipes of the adjacent adjustable frame (6) are fixedly connected to simulate the span or heading structure of the large aircraft component through the overall structure formed by splicing. Furthermore, by adjusting the size of the adjustable frame (6) in the X and Y directions in each large aircraft component simulation test unit, the external dimensions of the large aircraft component simulation test module (1) along the aircraft span or heading are adjusted. The counterweight module (4) is placed on the base plate of the adjustable frame (6) of each aircraft large component simulation test unit, and is used to simulate the weight and center of gravity of the aircraft large components by applying counterweight. The large aircraft component simulation test module (1) is placed on multiple CNC positioners (3) by the support and hoisting components (12) on both sides of the adjustable frame (6) of each size, so as to measure the center of gravity position of the large aircraft component simulation test module (1) and the individual or part of the large aircraft component simulation test units therein through the CNC positioners (3). The modular adjustable test device for simulating the docking of large aircraft components further includes: at least one supplementary simulation test frame (2), and the supplementary simulation test frame (2) is configured as a symmetrical structure along the flight path of the aircraft. The supplementary simulation test frame (2) is fixedly installed at the front end and / or rear end of the aircraft large component simulation test module (1) and is used to simulate the heading structure of the aircraft large component and the size, center of gravity, connection form and adjustment process of the heading structure of different types of aircraft large components by cooperating with the aircraft large component simulation test module (1). The supplementary simulation test frame (2) includes: frame one (21) and frame two (22) stacked vertically, and support and hoisting components (12) symmetrically installed on both sides of the frame; the weight and center of gravity of frame one (21) and frame two (22) are adjusted by placing counterweight modules (4).

2. The modular adjustable test device for simulating the docking of large aircraft components according to claim 1, characterized in that, Also includes: Docking simulation module (7); The docking simulation module (7) includes three sets of planar docking plates. Each set of planar docking plates includes two symmetrically arranged connecting plates. Two L-shaped docking plates are symmetrically installed on the connecting plates. One side plate of the two L-shaped docking plates is installed on the corresponding connecting plate through waist-shaped holes and screws. The other side plate of the two L-shaped docking plates is horizontally opposite to each other. The first set of planar mating plates (7-1) also includes: two horizontal mating plates arranged to meet along the horizontal plane; the two horizontal mating plates are respectively installed on the opposite side plates of the corresponding L-shaped mating plates through their base plates, so that the two horizontal mating plates overlap and meet in the horizontal plane, and are used for drilling holes after mating and installation; The second set of planar mating plates (7-2) also includes: two vertical mating plates arranged to meet vertically; the two vertical mating plates are respectively installed on the opposite side plates of the corresponding L-shaped mating plates through their base plates, so that the two vertical mating plates overlap and meet vertically, for drilling holes after mating and installation; In the third set of planar mating plates (7-3), the other side plate of the two L-shaped mating plates is used as mating plates for bonding installation, and holes are made after bonding installation; The installation positions of the three sets of planar docking plates are used to simulate the docking surface positions of actual large aircraft components. After each set of planar docking plates is installed on the adjacent steel frame of the adjacent adjustable frame (6) through its connecting plate, the repeatability of the hole is detected by making holes in the docking plates and moving the three sets of planar docking plates.

3. The modular adjustable test device for simulating the docking of large aircraft components according to claim 1, characterized in that, The power module (a) in each of the aircraft major component simulation test units includes: a drive motor (5), a rack (8), and a gear (9); The inner steel pipe of the multi-layer steel pipe in the adjustable frame (6) includes symmetrically arranged two-sided segmented steel pipes. A rack (8) is fixedly installed on the upper side of one-sided segmented steel pipe and a rack (8) is fixedly installed on the lower side of the other-sided segmented steel pipe. The gear (9) meshes with the two racks (8) respectively. The drive motor (5) is set on the outer steel pipe at the corresponding position. The end of the drive motor (5) is fixedly connected to the gear (9) to drive the gear (9) to rotate, thereby driving the racks (8) on both sides of the inner steel pipe fixedly installed in the adjustable frame (6) to move, so as to extend or retract the inner steel pipe, thereby adjusting the external dimensions of the single aircraft large component simulation test unit along the two directions of the aircraft heading and span.

4. The modular adjustable test device for simulating the docking of large aircraft components according to any one of claims 1 to 3, characterized in that, Each of the aircraft major component simulation test units has an adjustable frame (6) including: an upper steel pipe frame and a lower steel pipe frame with the same structure, and a Z-direction steel pipe for connecting the upper steel pipe frame and the lower steel pipe frame; wherein, the upper steel pipe frame and the lower steel pipe frame respectively include: a rectangular outer frame formed by two X-direction steel pipes and two Y-direction steel pipes, two integral Y-direction steel pipes set in the middle of the rectangular outer frame, two rows of segmented X-direction steel pipes set between the rectangular outer frame and the two integral Y-direction steel pipes, and two columns of segmented Y-direction steel pipes set between the rectangular outer frame and the two integral Y-direction steel pipes respectively, and the two columns of segmented Y-direction steel pipes form a segmented structure between the two rows of segmented X-direction steel pipes.

5. The modular adjustable test device for simulating the docking of large aircraft components according to claim 4, characterized in that, The two X-direction steel pipes and two Y-direction steel pipes in the rectangular outer frame, as well as the adjustable parts of the two integral Y-direction steel pipes and the two rows of segmented X-direction steel pipes, are set as secondary telescopic steel pipes, which are formed by two layers of steel pipes nested inside and outside; the part of the steel pipe between the segmented X-direction steel pipe and the rectangular outer frame in the two columns of segmented Y-direction steel pipes is set as a tertiary telescopic steel pipe, which is formed by three layers of steel pipes nested inside and outside; the upper and lower sides of the inner steel pipe are provided with convex guide rails (11), and the upper and lower inner walls of the outer steel pipe are provided with concave grooves that match the guide rails (11), so that the inner steel pipe and the outer steel pipe are tightly connected; In each of the rectangular outer frames of the adjustable frame (6), the power module (a) is provided in the middle of the two X-direction steel pipes and the middle of the two integrated Y-direction steel pipes, for adjusting the external dimensions of the adjustable frame (6) in the X and Y directions.

6. The modular adjustable test apparatus for simulating the docking of large aircraft components according to any one of claims 1 to 3, characterized in that, The bottom of the support and hoisting assembly (12) is provided with a ball head, which is locked to the ball socket at the upper end of the corresponding CNC positioner (3) to realize the fixed connection between each aircraft large component simulation test unit and the CNC positioner (3); and the support and hoisting assembly (12) has two pins, which are connected to the hoisting device to realize the hoisting of the large component simulation test module.

7. The modular adjustable test apparatus for simulating the docking of large aircraft components according to any one of claims 1 to 3, characterized in that, In each large aircraft component simulation test unit, multiple round holes are provided on the steel pipes in the Y direction on both sides of the rectangular outer frame of the adjustable frame (6). The round holes of adjacent large aircraft component simulation test units are aligned and connected by a U-shaped connecting frame (10) and a double-headed stud.

8. A method of using a modular adjustable test device for simulating the docking of large aircraft components, characterized in that, The center of gravity of the modular adjustable test device for simulating the docking of large aircraft components, as described in any one of claims 1 to 7, is adjusted by means of: Step 1: The modular adjustable test device is placed on four CNC positioners (3) by symmetrically installed support and hoisting components (12); wherein the coordinates of the four CNC positioners (3) are symmetrically set along the XZ plane; Step 2: Using the Z-axis force sensors at the top of the four CNC positioners (3), the center coordinates of the four CNC positioners (3) in the aircraft coordinate system are (x1, y1), (x2, y2), (x3, y3), (x4, y4), and the four force values ​​are F1, F2, F3, F4. Step 3: Using coordinates (x1, y1) as a reference, calculate the actual center-of-gravity coordinates of the modular adjustable test device. The calculation method for the center-of-gravity coordinates is as follows: ； Wherein, coordinates (x0, y0) are the theoretical center of gravity coordinates of the modular adjustable test device, and coordinates (x'0, y'0) are the actual center of gravity coordinates of the overall adjustable test device; Step 4: Determine whether the coordinates (x0, y0) and (x'0, y'0) satisfy the following conditions: When |x'0-x0|≤a, |y'0-y0|≤b and |g'0-g0|≤c are satisfied simultaneously, the weight and center of gravity of the modular adjustable test device meet the design requirements; Where g0 is the actual weight of the major components of the aircraft, g'0 is the actual weight of the adjustable test device in this test; a is the error criterion for the allowable center of gravity position in the X direction, b is the error criterion for the allowable center of gravity position in the Y direction, and c is the error criterion for the overall weight.

9. The method of using the modular adjustable test device for simulating the docking of large aircraft components according to claim 8, characterized in that, Also includes: In a single measurement using the method, the modular adjustable test device includes a partial large component simulation test unit, or an overall aircraft large component simulation test module (1), or a combination structure of the overall aircraft large component simulation test module (1) and a supplementary simulation test frame (2); to simulate the corresponding position of the aircraft large component through a single large component simulation test unit, to simulate the combination structure of the corresponding position of the aircraft large component through a partial large component simulation test unit, to simulate the aircraft spanwise structure or heading structure through the aircraft large component simulation test module (1), and to simulate the aircraft heading structure through the combination structure of the aircraft large component simulation test module (1) and the supplementary simulation test frame (2).

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