Modularized adjustable test device for simulating butt joint of large components of airplane and use method of modularized adjustable test device

Abstract

The embodiment of the invention discloses a modularized adjustable test device for simulating butt joint of large parts of an airplane and a use method thereof, a simulation test module in the device comprises at least one simulation test unit, multiple layers of steel pipes are arranged in an adjustable frame of the simulation test unit in the X and Y directions respectively, and the inner layer of steel pipes are driven to stretch out and draw back, so that the butt joint of the large parts of the airplane is simulated. The sizes of the adjustable frame in the X and Y directions are adjusted; the plurality of simulation test units are sequentially spliced along the spanwise direction or the course of the aircraft to form a spanwise structure or a course structure of the large component of the aircraft; adjusting the size of the size-adjustable frame in each simulation test unit in the X and Y directions to adjust the boundary dimension of the simulation test module in the unfolding direction of the airplane or the course of the airplane; the counterweight modules are placed on the size-adjustable frames of the simulation test units, and the weights and the gravity centers of the large components of the airplane are simulated by applying counterweights; and the center-of-gravity positions of the simulation test module and the single or partial simulation test units are measured through the numerical control positioner.

Description

Technical Field

[0001] The present invention relates to the field of but not limited to the technical field of large aircraft component assembly docking, and in particular to a modular adjustable test device for simulating large aircraft component docking and a use method thereof. Background Art

[0002] During the aircraft assembly process, the docking of large components represented by the fuselage and wings is a key link in aircraft manufacturing. The fuselage is usually divided into three fuselage parts: the front fuselage, the middle fuselage, and the rear fuselage. The wings are usually divided into three wing parts: the left wing, the central wing box, and the right wing. After the manufacture of a single component is completed, each aircraft component needs to be placed on 4 CNC positioners for attitude adjustment and docking to verify the positioning accuracy, repeat positioning accuracy, and assembly process of large aircraft components of the CNC positioner. After the fuselage or wing components are docked, they are fixed to complete the assembly of the entire fuselage or the entire wing. A single CNC positioner has three degrees of freedom in the XYZ direction. The coordinated attitude adjustment of multiple CNC positioners can complete the translation and rotation of aircraft components in the XYZ direction.

[0003] The large aircraft parts themselves are of high value. Before the formal product adjustment and docking of the aircraft, the large aircraft parts simulation test device is usually used to simulate the fuselage or wing for testing to determine whether the CNC positioner can achieve the positioning accuracy and repeat positioning accuracy under the predetermined load. At present, the establishment of each aircraft assembly production line requires two different large aircraft parts simulation test devices for the fuselage and the wing. Moreover, the large aircraft parts simulation test devices for different models of aircraft are very different and cannot be used in a compatible manner. The large parts simulation test device is expensive and has a long manufacturing cycle. The high cost and cycle limit the rapid mass production of aircraft products. Summary of the invention

[0004] Purpose of the present invention: In order to solve the above-mentioned technical problems, the embodiments of the present invention provide a modular adjustable test device for simulating the docking of large aircraft components and a method for using the same, so as to solve the problem that in the existing assembly method of large aircraft components, two different large aircraft component simulation test devices, namely the fuselage and the wing, need to be established separately, and large aircraft component simulation test devices of different models of aircraft cannot be used compatibly, resulting in high costs and cycles that limit the rapid mass production of aircraft products.

[0005] Technical solution of the present invention: In a first aspect, an embodiment of the present invention provides a modular adjustable test device for simulating the docking of large aircraft components, comprising: a large aircraft component simulation test module 1, a plurality of numerically controlled 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, and each aircraft large component simulation test unit is configured as a symmetrical structure along the aircraft heading and span direction, 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, and the double-layer frame is respectively provided with inner and outer nested multi-layer steel pipes in the X direction and Y direction, and a power module a is provided in the middle of the preset multi-layer steel pipe, so that the inner layer steel pipe of the preset multi-layer steel pipe is driven to extend or retract to both sides by the power module a, so that the size of the size-adjustable frame 6 in the X direction and the Y direction is adjusted; the support and hoisting assembly 12 is 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] A plurality of aircraft large component simulation test units are sequentially spliced ​​along the aircraft span direction or the aircraft heading direction, and adjacent steel pipes of adjacent adjustable-size frames 6 are fixedly connected, so as to simulate the span direction structure or heading structure of the aircraft large component through the overall structure formed by splicing; and the dimensions of the adjustable-size frame 6 in each aircraft large component simulation test unit in the X direction and the Y direction are adjusted to adjust the external dimensions of the aircraft large component simulation test module 1 along the aircraft span direction or the aircraft heading direction;

[0008] The counterweight module 4 is placed on the bottom plate of the size-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;

[0009] The aircraft large component simulation test module 1 is placed on multiple CNC positioners 3 through the support and lifting components 12 on both sides of each size-adjustable frame 6, so as to measure the center of gravity position of the aircraft large component simulation test module 1 and a single 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 comprises: at least one set of supplementary simulation test frames 2, and the supplementary simulation test frames 2 are arranged as symmetrical structures along the heading of the aircraft;

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

[0012] The supplementary simulation test frame 2 includes: frame 1 21 and frame 2 22 which are overlapped and arranged vertically, and support and lifting components 12 which are symmetrically installed on both sides of the frame; the weight and center of gravity of frame 1 21 and frame 2 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 further comprises: a docking simulation module 7;

[0014] The docking simulation module 7 includes three groups of planar docking plates, each group of planar docking plates includes two symmetrically arranged connecting plates, two L-shaped docking plates symmetrically installed on the connecting plates, one side plate of the two L-shaped docking plates is installed on the connecting plates at corresponding positions through waist-shaped holes and screws, and the other side plates of the two L-shaped docking plates are arranged horizontally opposite to each other;

[0015] The first group of planar docking plates 7-1 further includes: two horizontal docking plates arranged along the horizontal plane; the two horizontal docking plates are respectively installed on the opposite side plates of the corresponding L-shaped docking plates through their bottom plates, so that the two horizontal docking plates overlap and dock in the horizontal plane, and are used for making holes after docking and installation;

[0016] The second group of planar docking plates 7-2 also includes: two vertical docking plates arranged along the vertical surface; the two vertical docking plates are respectively installed on the opposite side plates of the corresponding L-shaped docking plates through their bottom plates, so that the two vertical docking plates overlap and dock on the vertical surface, and are used for docking and installation and then making holes;

[0017] In the third group of planar butt joint plates 7-3, the other side plates of the two L-shaped butt joint plates are fitted and installed as butt joint plates, and holes are made after the fitting and installation;

[0018] The installation positions of the three groups of planar docking plates are used to simulate the docking surface positions of actual large aircraft components; after each group of planar docking plates is installed on the adjacent steel frame of the adjacent adjustable size frame 6 through its connecting plate, holes are made on the docking plates, and the repeated positioning accuracy of the holes is detected after moving the three groups 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 comprises: a drive motor 5, a rack 8 and a gear 9;

[0020] Among them, the inner steel pipe of the multi-layer steel pipe at the preset position in the adjustable size frame 6 includes symmetrically arranged segmented steel pipes on both sides, a rack 8 is fixedly installed on the upper side of the segmented steel pipe on one side, and a rack 8 is fixedly installed on the lower side of the segmented steel pipe on the other side, and the gear 9 is respectively meshed with the two gears 8 above and below, and the driving motor 5 is arranged on the outer steel pipe at the corresponding position, and the end of the driving motor 5 is fixedly connected to the gear 9, which is used to drive the gear 9 to rotate, thereby driving the racks 8 on both sides of the inner steel pipe fixedly installed on the adjustable size frame 6 to move, so as to extend or retract the inner steel pipe, thereby adjusting the external dimensions of a single aircraft large component simulation test unit along the aircraft heading and span directions.

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

[0022] The size-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 of the same structure, and a Z-direction steel tube for connecting the upper steel tube frame and the lower steel tube frame; wherein the upper steel tube frame and the lower steel tube frame respectively include: a rectangular outer frame formed by two X-direction steel tubes and two Y-direction steel tubes, two integral Y-direction steel tubes arranged in the middle of the rectangular outer frame, two rows of segmented X-direction steel tubes arranged between the rectangular outer frame and the two integral Y-direction steel tube brackets, two columns of segmented Y-direction steel tubes arranged between the rectangular outer frame and the two integral Y-direction steel tubes, and the two columns of segmented Y-direction steel tubes form a segmented structure between the two rows of segmented X-direction steel tubes.

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

[0024] The two X-direction steel tubes and the two Y-direction steel tubes in the rectangular outer frame, as well as the adjustable parts of the two integrated Y-direction steel tubes and the two rows of segmented X-direction steel tubes are set as two-stage telescopic steel tubes, which are formed by two layers of steel tubes nested inside and outside; the part of the steel tubes between the segmented X-direction steel tubes and the rectangular outer frame in the two rows of segmented Y-direction steel tubes is set as a three-stage telescopic steel tube, which is formed by three layers of steel tubes nested inside and outside; the upper and lower sides of the inner steel tube are provided with convex guide rails 11, and the upper and lower inner side walls of the outer steel tube are provided with concave grooves matching the guide rails 11, so that the inner steel tube is tightly connected with the outer steel tube;

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

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

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

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

[0029] In each aircraft large component simulation test unit, multiple circular holes are opened on the Y-direction steel pipes on both sides of the rectangular outer frame of the size-adjustable frame 6. The circular holes of adjacent aircraft large component simulation test units are aligned and connected through a U-shaped connection frame 10 and studs.

[0030] In a second aspect, an embodiment of the present invention further provides 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 one of the above items is adjusted, and the method for using the modular adjustable test device for simulating the docking of large aircraft components comprises:

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

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

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

[0034]

[0035] Among them, the coordinates (x0, y0) are the theoretical center of gravity coordinates of the modular adjustable test device, and the 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) meet the following conditions:

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

[0038] Among them, g0 is the actual weight of the large aircraft component, 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 allowable error criterion for the overall weight.

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

[0040] In a single measurement of the method of use, the modular adjustable test device includes a single or partial large component simulation test unit, or an entire aircraft large component simulation test module 1, or a combined structure of an entire aircraft large component simulation test module 1 and a supplementary simulation test frame 2; the aircraft large component at the corresponding position is simulated by a single large component simulation test unit, the combined structure of the aircraft large component at the corresponding position is simulated by a partial large component simulation test unit, the aircraft spanwise structure or heading structure is simulated by the aircraft large component simulation test module 1, and the aircraft heading structure is simulated by the combined structure of the aircraft large component simulation test module 1 and the supplementary simulation test frame 2.

[0041] Beneficial effects of the present invention: The embodiment of the present invention provides a modular adjustable test device for simulating the docking of large aircraft components and a method for using the same, wherein a plurality of large aircraft component simulation test units of the same structure and size are spliced ​​to form a large aircraft component simulation test module 1, and the weight and center of gravity of the large aircraft component at the corresponding position are simulated by cooperating with the counterweight module 4, and the center of gravity position of the modular adjustable test device is measured by cooperating with the numerical control positioner 3; wherein the size adjustable frame 6 in a single large aircraft component simulation test unit is set as a double-layer frame formed by steel pipes in three directions, and the double-layer frame is respectively provided with inner and outer nested multi-layer steel pipes in the X direction and Y direction, and a power module a is provided in the middle of the preset multi-layer steel pipe, so that the inner layer steel pipe of the preset multi-layer steel pipe is extended or retracted to both sides through the power module a, so that the size of the adjustable frame 6 in the X direction and the Y direction is adjusted; thereby, the external dimensions of the large aircraft component simulation test module 1 formed by splicing are adjustable along the aircraft span direction or the aircraft heading direction. Compared with the prior art, the technical solution provided by the embodiment 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 simulated docking in the manufacturing process of aircraft of various sizes, replacing the traditional special simulation tooling that is only applicable to a single model. It has a wide range of uses, reduces costs, and improves the efficiency of aircraft assembly docking.

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

[0044] (3) The modular adjustable test device for simulating the docking of large aircraft components and the corresponding method of use provided by the present invention have been verified to meet actual needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0046] Figure 1 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 A schematic structural diagram of a single aircraft large component simulation test unit in a modular adjustable test device for simulating the docking of aircraft large components provided by the illustrated embodiment;

[0048] Figure 3 for Figure 2 The illustrated embodiment provides a schematic diagram of the splicing structure of adjacent large aircraft component simulation test units;

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

[0050] Figure 5 for Figure 2 The illustrated embodiment provides a schematic structural diagram of a power module in a single aircraft major component simulation test unit;

[0051] Figure 6 for Figure 3 The illustrated embodiment provides a schematic structural diagram of a connector in a splicing structure of a simulation test unit of adjacent large aircraft components;

[0052] Figure 7 for Figure 2The illustrated embodiment provides a schematic structural diagram of a multi-layer steel tube in a single aircraft large component simulation test unit.

[0053] Description of reference numerals:

[0054] 1. Aircraft large component simulation test module; 1-1, 1-2, 1-3, 1-4 are all aircraft large component simulation test units; 2. Supplementary simulation test frame; 21. Frame one; 22. Frame two; 3. CNC positioner; 4. Counterweight module; a. Power module; 5. Drive motor; 6. Size-adjustable frame; 7. Docking simulation module; 8. Rack; 9. Gear; 10. Connection frame; 11. Guide rail; 12. Support and lifting assembly 12. DETAILED DESCRIPTION

[0055] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily without conflict.

[0056] The above background technology has already explained the assembly method of large aircraft parts and the requirements of large aircraft parts for positioning accuracy and repeated positioning accuracy during assembly. In the existing assembly method of large aircraft parts, two different large aircraft parts simulation test devices for fuselage and wing need to be established respectively, and large aircraft parts simulation test devices for different models of aircraft cannot be used compatibly, which makes the large parts simulation test device expensive and has a long manufacturing cycle. The high cost and cycle limit the rapid mass production of aircraft products.

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

[0058] In order to solve the problem of assembling large aircraft components, designing an adjustable test device that can adapt to various aircraft models and has low cost can improve the efficiency of simulation tests on large aircraft components and reduce aircraft manufacturing costs. Based on this demand, an embodiment of the present invention provides a modular adjustable test device for simulating the docking of large aircraft components and a method for using the same.

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

[0060] Figure 1The overall structural diagram of a modular adjustable test device for simulating the docking of large aircraft components provided by an embodiment of the present invention is as follows: Figure 2 for Figure 1 The illustrated embodiment provides a schematic structural diagram of a single aircraft large component simulation test unit in a modular adjustable test device for simulating the docking of aircraft large components. Figure 3 for Figure 2 The embodiment shown is a schematic diagram of the splicing structure of adjacent large aircraft component simulation test units. 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 by the embodiment of the present invention includes: a plurality of large aircraft component simulation test modules 1, a plurality of 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. Figure 1 As shown in the figure, the aircraft large component simulation test module 1 includes 4 aircraft large component simulation test units, namely 1-1, 1-2, 1-3, and 1-4, and the 4 aircraft large component simulation test units have the same structure, and the overall size can be adjusted according to the actual simulated aircraft size; wherein, the size of each aircraft large component simulation test unit is the same as the aircraft large component at the corresponding position, and is used to simulate the size and connection method of large components such as multiple fuselages and wings in aircraft of different sizes during the assembly process, as well as to simulate the process method and accuracy 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 for the weight and center of gravity of the aircraft large components during the assembly process.

[0062] like Figure 1 and Figure 2 As shown, each aircraft large component simulation test unit is set as a symmetrical structure along the aircraft heading and span direction, including: a size-adjustable frame 6, a power module a, and a support and hoisting assembly 12. Among them, the size-adjustable frame 6 as the main structure of the unit is set as a double-layer frame formed by steel pipes in three directions, and the double-layer frame is respectively provided with inner and outer nested multi-layer steel pipes in the X direction and Y direction, and a power module a is set in the middle of the preset multi-layer steel pipe, so that the inner layer steel pipe of the preset multi-layer steel pipe is driven to extend or retract to both sides through the power module a, so that the size of the size-adjustable frame 6 in the X direction and the Y direction is adjusted; the support and hoisting assembly 12 is symmetrically installed on both sides of each aircraft large component simulation test unit for hoisting and supporting the aircraft large component simulation test unit.

[0063] like Figure 1As shown, a plurality of large aircraft component simulation test units are sequentially spliced ​​along the span direction or heading direction of the aircraft, and adjacent steel pipes of adjacent adjustable-size frames 6 are fixedly connected, so as to simulate the span structure or heading structure of the large aircraft component through the integral structure formed by the splicing; in addition, the dimensions of the adjustable-size frame 6 in the X direction and the Y direction in each large aircraft component simulation test unit can be adjusted to adjust the external dimensions of the large aircraft component simulation test module 1 along the span direction or heading direction of the aircraft.

[0064] In the embodiment of the present invention, multiple aircraft large 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 size of the large aircraft component simulation test module 1 is adjustable along the aircraft heading or span direction.

[0065] like Figure 1 and Figure 2 As shown, the counterweight module 4 is placed on the bottom 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 a plurality of round pancake-shaped iron blocks with a central hole, and the counterweight applied is located at the center. By applying the configuration to each aircraft large component simulation test unit, the weight of the unit is the same as the weight of the aircraft large component at the corresponding position; in addition, the counterweight module 4 is used in conjunction with the use method provided in the embodiment of the present invention to adjust the center of gravity of the unit to be the same as the center of gravity of the aircraft large component at the corresponding position.

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

[0067] It should be noted that in the embodiment of the present invention, not only the weight and center of gravity of the combined aircraft large component simulation test module 1 can be adjusted, but the weight and center of gravity of a single or part of the aircraft large component simulation test units therein can also be adjusted in the same way; in actual operation, the installation work requires the selection of the unit or the entire module to be adjusted.

[0068] In one implementation of the embodiment of the present invention, Figure 1 As shown, the modular adjustable test device is characterized in that it also includes: at least one set of supplementary simulation test frames 2, and the supplementary simulation test frames 2 are set to be a symmetrical structure along the heading of the aircraft.

[0069] In this implementation, the supplementary simulation test frame 2 is fixedly installed at the front end and / or the rear end of the aircraft large component simulation test module 1. Specifically, the supplementary simulation test frame 2 is installed in coordination 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 the tail of the aircraft heading structure, as well as simulate the size, center of gravity, connection form and process flow of adjusting the center of gravity of the heading structures of different types of aircraft large components.

[0070] like Figure 2 As shown, the supplementary simulation test frame 2 includes: a frame 1 21 and a frame 2 22 which are overlapped and arranged vertically, and a support and lifting assembly 12 which is symmetrically installed on both sides of the frame. It should be noted that the supplementary simulation test frame 2 is, for example, configured as a special fixed frame required for simulating aircraft of different sizes and models, and the corresponding supplementary simulation test modules 2 have different sizes when simulating aircraft of different types or sizes. In an optional implementation, the frame 1 21 and the frame 2 22 can also be configured as a frame structure with size adjustment similar to the size-adjustable frame 6, and the weight and center of gravity of the frame 1 21 and the frame 2 22 can also be adjusted by placing a counterweight module 4.

[0071] In a specific implementation, the frame 1 21 and the frame 2 22 are connected in the up-down direction by bolts, and the profile and size of the frame 1 21 and the frame 2 22 match the size of the nose or tail of the aircraft large component. In addition, the size of the supplementary simulation test module 2 corresponding to different real aircraft large components is different, and the supplementary simulation test module 2 can be a variable structure.

[0072] In one implementation of the embodiment of the present invention, the modular adjustable test device further includes: a docking simulation module 7; the docking simulation module 7 is used to simulate the docking structure of multiple fuselage sections and wings in large aircraft components, and each set of flat docking plates is provided with holes that are coordinated with the repeat positioning accuracy of the CNC positioner 3. Figure 4 As shown, Figure 1 The illustrated embodiment provides a schematic structural diagram of a docking simulation module in a modular adjustable test device for simulating the docking of large aircraft components. Figure 4 Figure a in the figure is the first set of planar butt joint plates 7-1, Figure 4 Figure b in the figure is the second set of planar butt joint plates 7-2. Figure 4 Figure c in the figure is the third set of planar docking plates 7-3; Figure 3 The docking simulation module 7 is installed between adjacent aircraft large component simulation test units.

[0073] like Figure 3 and Figure 4As shown, the docking simulation module 7 includes three groups of planar docking plates, each group of the planar docking plates includes two symmetrically arranged connecting plates, two L-shaped docking plates symmetrically installed on the connecting plates, one side plate of the two L-shaped docking plates is installed on the connecting plates at corresponding positions through waist-shaped holes and screws, and the other side plates of the two L-shaped docking plates are horizontally arranged relative to each other.

[0074] The first group of planar docking plates 7-1 further includes: two horizontal docking plates arranged along the horizontal plane; the two horizontal docking plates are respectively installed on the opposite side plates of the corresponding L-shaped docking plates through their bottom plates, so that the two horizontal docking plates overlap and dock in the horizontal plane, and are used for making holes after docking and installation;

[0075] The second group of planar docking plates 7-2 also includes: two vertical docking plates arranged along the vertical surface; the two vertical docking plates are respectively installed on the opposite side plates of the corresponding L-shaped docking plates through their bottom plates, so that the two vertical docking plates overlap and dock on the vertical surface, and are used for docking and installation and then making holes;

[0076] In the third group of planar butt joint plates 7-3, the other side plates of the two L-shaped butt joint plates are fitted and installed as butt joint plates, and holes are made after the fitting and installation;

[0077] The installation positions of the three groups of planar docking plates in this implementation are used to simulate the docking surface positions of actual large aircraft components; in addition, after each group of planar docking plates is installed on the adjacent steel frame of the adjacent adjustable size frame 6 through its connecting plate, holes are made on the docking plates, and the repeat positioning accuracy of the holes is detected after moving the three groups of planar docking plates.

[0078] In one implementation of the embodiment of the present invention, a specific implementation of the power module a in the 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 structure of a power module in a single aircraft large 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 steel pipe of the multi-layer steel pipe at a preset position in the size-adjustable frame 6 includes symmetrically arranged segmented steel pipes on both sides, a rack 8 is fixedly installed on the upper side of the segmented steel pipe on one side, and a rack 8 is fixedly installed on the lower side of the segmented steel pipe on the other side, and the gear 9 is meshed with the two gears 8 above and below respectively. The driving motor 5 is arranged on the outer steel pipe at the corresponding position, and the end of the driving motor 5 is fixedly connected to the gear 9, which is used to drive the gear 9 to rotate, thereby driving the racks 8 on both sides of the inner steel pipe fixedly installed on the size-adjustable frame 6 to move, so as to extend or retract the inner steel pipe, thereby adjusting the external dimensions of a single aircraft large component simulation test unit along the aircraft heading and span directions.

[0080] In one implementation of the present invention, a specific implementation of the size-adjustable frame 6 in the aircraft large component simulation test unit is provided, referring to Figures 1 to 3 As shown, the size-adjustable frame 6 in each of the aircraft large component simulation test units includes: an upper steel tube frame and a lower steel tube frame of the same structure, 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 steel tube frame and the lower steel tube frame respectively include: a rectangular outer frame formed by two X-direction steel tubes and two Y-direction steel tubes, two integrated Y-direction steel tubes arranged in the middle of the rectangular outer frame, two rows of segmented X-direction steel tubes arranged between the rectangular outer frame and the two integrated Y-direction steel tube supports (the portion of the segmented X-direction steel tube located between the two integrated Y-direction steel tubes is a non-adjustable steel tube, and the portion located between the integrated Y-direction steel tube and the rectangular outer frame is an adjustable portion, i.e., a multi-layer steel tube nested inside and outside), two columns of segmented Y-direction steel tubes arranged between the rectangular outer frame and the two integrated Y-direction steel tubes, and the two columns of segmented Y-direction steel tubes form a segmented structure between the two rows of segmented X-direction steel tubes (the portion located between the two rows of segmented X-direction steel tubes is a non-adjustable steel tube, and the portion located between the two rows of segmented X-direction steel tubes and the rectangular outer frame is an adjustable portion, i.e., a multi-layer steel tube nested inside and outside). Figure 2 It can be seen that the rectangular outer frame formed by two X-direction steel pipes and two Y-direction steel pipes, and the two integral Y-direction steel pipes arranged in the middle of the rectangular outer frame are levers of an integrated structure, and the other X-, Y-, and Z-direction steel pipes are welded to the steel pipes on the rectangular outer frame and to the middle steel pipe; in addition, the cross-section of each steel pipe in the size-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 tubes and the two Y-direction steel tubes in the rectangular outer frame, as well as the adjustable parts of the two integrated Y-direction steel tubes and the two rows of segmented X-direction steel tubes are set as two-stage telescopic steel tubes, formed by two layers of steel tubes nested inside and outside; the part of the steel tubes between the segmented X-direction steel tubes and the rectangular outer frame in the two rows of segmented Y-direction steel tubes is set as three-stage telescopic steel tubes, formed by three layers of steel tubes nested inside and outside; the upper and lower sides of the inner steel tube are provided with convex guide rails 11, and the upper and lower inner walls of the outer steel tube are provided with concave grooves matching the guide rails 11, so that the inner steel tube is tightly connected to the outer steel tube. The size-adjustable frame 6 can be telescoped along the X and Y directions through the above-mentioned nested steel tube structure. Figure 7 As shown, Figure 2 The illustrated embodiment provides a schematic diagram of the structure of a multi-layer steel pipe in a single aircraft large component simulation test unit. Figure 7The three-stage telescopic steel pipe is specifically illustrated in the figure, and the structure of the two-stage telescopic steel pipe is similar, except that one layer of steel pipe is missing.

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

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

[0085] In one implementation of the present invention, in each aircraft large component simulation test unit, a plurality of circular holes are opened on the Y-direction steel pipes on both sides of the rectangular outer frame of the size-adjustable frame 6, and the circular holes of adjacent aircraft large component simulation test units are aligned and connected by a U-shaped connection frame 10 and studs, and the connection does not affect the expansion and contraction of the aircraft large component simulation test module 1 along the Y direction. Figure 6 As shown, Figure 3 The illustrated embodiment provides a schematic structural diagram of a connector in a splicing structure of a simulation test unit of adjacent large aircraft components.

[0086] The modular adjustable test device for simulating the docking of large aircraft components provided by the embodiment of the present invention adopts a plurality of large aircraft component simulation test units of the same structure and size to form a large aircraft component simulation test module 1, and simulates the weight and center of gravity of the large aircraft component at the corresponding position by cooperating with the counterweight module 4, and measures the center of gravity position of the modular adjustable test device by cooperating with the numerical control positioner 3; wherein, the size adjustable frame 6 in a single large aircraft component simulation test unit is set as a double-layer frame formed by steel pipes in three directions, and the double-layer frame is respectively provided with inner and outer nested multi-layer steel pipes in the X direction and Y direction, and a power module a is provided in the middle of the preset multi-layer steel pipe, so that the inner layer steel pipe of the preset multi-layer steel pipe is extended or retracted to both sides by the power module a, so that the size of the size adjustable frame 6 in the X direction and the Y direction is adjusted; thereby, the external dimensions of the large aircraft component simulation test module 1 formed by the splicing are adjustable along the aircraft span direction or the aircraft heading direction. Compared with the prior art, the technical solution provided by the embodiment of the present 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 simulated docking in the manufacturing process of aircraft of various sizes, replacing the traditional special simulation tooling that is only applicable to a single model. It has a wide range of uses, reduces costs, and improves the efficiency of aircraft assembly docking.

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

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

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

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

[0092] In this step 1, it is considered that in the aircraft coordinate system, the coordinates of the center of gravity of the aircraft only focus on the X direction and the Y direction; for example, the modular adjustable test device is symmetrically arranged along the X direction, and is used to simulate the heading structure of large aircraft components; the 3 coordinates of the four CNC positioners are symmetrically arranged along the XZ plane; for another example, the modular adjustable test device is symmetrically arranged along the Y direction, and is used to simulate the span structure of large aircraft components; the 3 coordinates of the four CNC positioners are symmetrically arranged along the YZ plane.

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

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

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

[0096]

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

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

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

[0100] Among them, g0 is the actual weight of the large aircraft component, 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 allowable error criterion for the overall weight.

[0101] In one implementation of an embodiment 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 aircraft large component at the corresponding position through a single large component simulation test unit, to simulate the aircraft large component combination structure at the corresponding position through a partial large component simulation test unit, to simulate the aircraft span 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 pressure closing method for narrow and long parts to achieve bearing closing provided by the embodiment of the present invention may also include the following steps:

[0103] Step 6: Check the bearing quality after the bearing closing operation is completed. The quality inspection standards include:

[0104] Appearance inspection of the bearing: wrinkles, cracks and burrs are not allowed at the closing part, extrusion marks are allowed, and the edge clearance at the closing part is less than 0.1mm;

[0105] Check the no-load starting torque of the bearing, and make sure it meets the installation requirements;

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

[0107] In one implementation of the embodiment of the present invention, the setting pressure value in step 4 is determined, for example, as follows:

[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 fixed 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 fixed mold 6 is F2. When the control system 9 detects that the fed-back pressure value F1 is:

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

[0111] Although the embodiments disclosed in the present invention are as above, the contents are only embodiments adopted to facilitate understanding of the present invention and are not intended to limit the present invention. Any technician in the field to which the present invention belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in the present invention, but the patent protection scope of the present invention shall still be subject to the scope defined in the attached claims.

Claims

1. A modular adjustable test device for simulating the docking of large aircraft components, characterized in that: include: An aircraft large component simulation test module (1), a plurality of numerically controlled positioners (3) and a 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 heading and span directions of the aircraft, including: a size-adjustable frame (6), a power module (a), and a support and lifting 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 inner and outer nested multi-layer steel pipes in the X direction and the Y direction, respectively, and a power module (a) is provided in the middle of the preset multi-layer steel pipe, so that the inner layer steel pipe of the preset multi-layer steel pipe is driven to extend or retract to both sides by the power module (a), so that the size of the size-adjustable frame (6) in the X direction and the Y direction is adjusted; the support and lifting assembly (12) is symmetrically installed on both sides of each large aircraft component simulation test unit, which is used for lifting and supporting the large aircraft component simulation test unit; A plurality of large aircraft component simulation test units are sequentially spliced ​​along the aircraft span direction or the aircraft heading direction, and adjacent steel pipes of adjacent size-adjustable frames (6) are fixedly connected, so as to simulate the span direction structure or heading structure of the large aircraft component through the overall structure formed by the splicing; and the dimensions of the size-adjustable frames (6) in each large aircraft component simulation test unit in the X direction and the Y direction are adjusted to adjust the external dimensions of the large aircraft component simulation test module (1) along the aircraft span direction or the aircraft heading direction; The counterweight module (4) is placed on the bottom plate of the size-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; The large aircraft component simulation test module (1) is placed on a plurality of numerical control positioners (3) via support and lifting assemblies (12) on both sides of each size-adjustable frame (6), so that the center of gravity position of the large aircraft component simulation test module (1) and a single or partial large aircraft component simulation test unit therein can be measured via the numerical control positioners (3).

2. The modular adjustable test device for simulating the docking of large aircraft components according to claim 1, characterized in that: Also includes: At least one set of supplementary simulation test frames (2), wherein the supplementary simulation test frames (2) are arranged to be symmetrical structures along the heading of the aircraft; The supplementary simulation test frame (2) is fixedly mounted on the front end or / and the rear end of the aircraft large component simulation test module (1), and is used to simulate the heading structure of the aircraft large component by cooperating with the aircraft large component simulation test module (1) to simulate the size, center of gravity, connection form and process flow of adjusting the center of gravity of the heading structure of different types of aircraft large components; The supplementary simulation test frame (2) comprises: a frame 1 (21) and a frame 2 (22) which are arranged to overlap each other, and a support and lifting assembly (12) symmetrically installed on both sides of the frame; the weight and center of gravity of the frame 1 (21) and the frame 2 (22) are adjusted by placing a counterweight module (4).

3. 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) comprises three groups of planar docking plates, each group of the planar docking plates comprises two symmetrically arranged connecting plates, two L-shaped docking plates symmetrically mounted on the connecting plates, one side plate of the two L-shaped docking plates being mounted on the connecting plates at corresponding positions via waist-shaped holes and screws, and the other side plates of the two L-shaped docking plates being arranged horizontally opposite to each other; The first group of planar butt joint plates (7-1) further comprises: two horizontal butt joint plates arranged butt joint along a horizontal surface; the two horizontal butt joint plates are respectively mounted on opposite side plates of the corresponding L-shaped butt joint plates through their bottom plates, so that the two horizontal butt joint plates overlap and butt joint in a horizontal plane, and are used for butt joint installation and post-hole making; The second group of planar butt joint plates (7-2) also includes: two vertical butt joint plates arranged butt joint along the vertical surface; the two vertical butt joint plates are respectively installed on the opposite side plates of the corresponding L-shaped butt joint plates through their bottom plates, so that the two vertical butt joint plates overlap and butt joint on the vertical surface, and are used for butt joint installation and post-hole making; In the third group of plane butt joint plates (7-3), the other side plates of the two L-shaped butt joint plates are fitted and installed as butt joint plates, and are used for making holes after the fitting and installation; The installation positions of the three groups of planar docking plates are used to simulate the positions of the docking surfaces of actual large aircraft components; after each group of planar docking plates is installed on the adjacent steel frame of the adjacent size-adjustable frame (6) through its connecting plate, holes are made on the docking plates, and the three groups of planar docking plates are moved to detect the repeat positioning accuracy of the holes.

4. 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 comprises: a drive motor (5), a rack (8) and a gear (9); The inner steel pipe of the multi-layer steel pipe at a preset position in the size-adjustable frame (6) comprises two symmetrically arranged segmented steel pipes, a rack (8) is fixedly mounted on the upper side of the segmented steel pipe on one side, and a rack (8) is fixedly mounted on the lower side of the segmented steel pipe on the other side, and a gear (9) is meshed with the two gears 8 at the upper and lower sides, respectively. A driving motor (5) is arranged on the outer steel pipe at a corresponding position, and the end of the driving motor (5) is fixedly connected to the gear (9) for driving the gear (9) to rotate, thereby driving the two side racks (8) of the inner steel pipe fixedly mounted on the size-adjustable frame (6) to move, so as to extend or retract the inner steel pipe, thereby adjusting the external dimensions of a single aircraft large component simulation test unit along the aircraft heading and span directions.

5. The modular adjustable test device for simulating the docking of large aircraft components according to any one of claims 1 to 4, characterized in that: The size-adjustable frame (6) in each of the aircraft major component simulation test units comprises: an upper steel tube frame and a lower steel tube frame of the same structure, and a Z-direction steel tube for connecting the upper steel tube frame and the lower steel tube frame; wherein the upper steel tube frame and the lower steel tube frame respectively comprise: a rectangular outer frame formed by two X-direction steel tubes and two Y-direction steel tubes, two integral Y-direction steel tubes arranged in the middle of the rectangular outer frame, two rows of segmented X-direction steel tubes arranged between the rectangular outer frame and the two integral Y-direction steel tube brackets, two columns of segmented Y-direction steel tubes arranged between the rectangular outer frame and the two integral Y-direction steel tubes, and the two columns of segmented Y-direction steel tubes forming a segmented structure between the two rows of segmented X-direction steel tubes.

6. The modular adjustable test device for simulating the docking of large aircraft components according to claim 5, characterized in that: The two X-direction steel tubes and the two Y-direction steel tubes in the rectangular outer frame, as well as the adjustable parts of the two integrated Y-direction steel tubes and the two rows of segmented X-direction steel tubes are configured as two-stage telescopic steel tubes, formed by two layers of steel tubes nested inside and outside; the part of the steel tubes between the segmented X-direction steel tubes and the rectangular outer frame in the two rows of segmented Y-direction steel tubes is configured as a three-stage telescopic steel tube, formed by three layers of steel tubes nested inside and outside; the upper and lower sides of the inner steel tube are provided with convex guide rails (11), and the upper and lower inner side walls of the outer steel tube are provided with concave grooves matching the guide rails (11), so that the inner steel tube is tightly connected with the outer steel tube; The power module (a) is arranged in the middle of two X-direction steel pipes and two integrated Y-direction steel pipes in the rectangular outer frame of each size-adjustable frame (6), and is used to adjust the external dimensions of the size-adjustable frame (6) in the X-direction and the Y-direction.

7. The modular adjustable test device for simulating the docking of large aircraft components according to any one of claims 1 to 4, characterized in that: The support and lifting assembly (12) is provided with a ball head at the bottom, and the ball head is locked with the ball socket at the upper end of the CNC positioner (3) at the corresponding position to achieve fixed connection between each aircraft large component simulation test unit and the CNC positioner (3); and the support and lifting assembly (12) is provided with two pins, which are connected with the lifting device to achieve the lifting of the large component simulation test module.

8. The modular adjustable test device for simulating the docking of large aircraft components according to any one of claims 1 to 4, characterized in that: In each aircraft large component simulation test unit, a plurality of circular holes are opened on the Y-direction steel pipes on both sides of the rectangular outer frame of the size-adjustable frame (6), and the circular holes of adjacent aircraft large component simulation test units are aligned and connected via a U-shaped connection frame (10) and studs.

9. A method for using a modular adjustable test device for simulating the docking of large aircraft components, characterized in that: The center of gravity of a modular adjustable test device for simulating the docking of large aircraft components according to any one of claims 1 to 7 is adjusted, and the method of using the device comprises: Step 1, the modular adjustable test device is placed on four CNC positioners (3) through symmetrically installed support and lifting components (12); wherein the coordinates of the four CNC positioners (3) are symmetrically arranged along the XZ plane; Step 2, through the Z-direction force sensors at the top of the four CNC positioners (3), the coordinates of the sphere centers of the four CNC positioners (3) read in the aircraft coordinate system are (x1, y1), (x2, y2), (x3, y3), (x4, y4), and the four force values ​​read are F1, F2, F3, F4 respectively; Step 3, taking the coordinates (x1, y1) as the reference, calculate the actual center of gravity coordinates of the modular adjustable test device. The calculation method of the center of gravity coordinates is: Among them, the coordinates (x0, y0) are the theoretical center of gravity coordinates of the modular adjustable test device, and the 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) meet the following conditions: When |x'0-x0|≤a, |y'0-y0|≤b and |g'0-g0|≤c are satisfied at the same time, the weight and center of gravity indicators of the modular adjustable test device meet the design requirements; Among them, g0 is the actual weight of the large aircraft component, 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 allowable error criterion for the overall weight.

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

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