Multi-side parallel loading device for aircraft engine casing

Abstract

The present invention provides a multilateral parallel loading device for an aircraft engine casing, comprising: a static platform; a plurality of upper parallel branches, one end of each upper parallel branch is connected to the static platform; a plurality of lower parallel branches, one end of each lower parallel branch is connected to the static platform, and one end of each upper parallel branch is located above one end of each lower parallel branch; an upper moving platform, the other end of each upper parallel branch is connected to the upper moving platform; a lower moving platform, the other end of each lower parallel branch is connected to the lower moving platform, and the upper moving platform is located above the lower moving platform. The embodiment of the present invention forms a moving platform in parallel, replacing the previous loading branch chain that performs multilateral six-degree-of-freedom load loading in a non-standard design distribution manner. The installation and state changes of the casing can be met by the posture control of the moving platform, avoiding the cost and cycle expenditure of manually disassembling and assembling the branches many times, and improving the test efficiency.

Description

Technical Field

[0001] This specification relates to the field of aircraft engine technology, and specifically to a multilateral parallel loading device for an aircraft engine casing. Background Art

[0002] The aircraft engine casing is the primary load-bearing component of the engine. Before the engine is finalized, simulated loads must be applied to each joint edge for static strength testing. These simulated loads are applied in a spatial, six-degree-of-freedom manner, typically requiring concentrated loads to be applied at multiple application points to synthesize the six-degree-of-freedom load. Due to the bulky size of the loading equipment and its low installation precision, structural deformation during testing can lead to loading errors that cannot be compensated, resulting in large loading errors. This necessitates repeated disassembly and assembly of the loading equipment for different test conditions, requiring significant manual effort, low assembly efficiency, and long cycle times.

[0003] Parallel mechanisms have been widely used in the fields of unilateral posture and load control such as mechanical assembly, motion simulation, and forming devices due to their advantages such as compact structure, high rigidity, and large load-bearing capacity. Although the automated assembly equipment for helicopter hubs in the existing technology can realize the positioning and installation of unilateral parallel mechanisms, it cannot realize the load control of the moving platform and the linkage of multiple mounting surfaces. In the existing technology, an automated docking and assembly system for rocket launcher segments based on an orthogonal 3-PRR parallel mechanism has realized the linkage posture control of multiple mounting surfaces, but this technology cannot realize the load linkage control of multiple mounting surfaces. The above-mentioned types of mechanisms all meet the requirements of six-degree-of-freedom loading in the space of multiple mounting surfaces of aircraft engine casings, and their scope of application is limited. Summary of the Invention

[0004] In view of this, an embodiment of the present specification provides a multi-side parallel loading device for an aircraft engine casing to solve the problems of error compensation and long cycle in casing loading.

[0005] The technical solution of the present invention is: a multilateral parallel loading device for an aircraft engine casing, comprising: a static platform; a plurality of upper parallel branches, one end of each upper parallel branch is connected to the static platform; a plurality of lower parallel branches, one end of each lower parallel branch is connected to the static platform, and one end of each upper parallel branch is located above one end of each lower parallel branch; an upper moving platform, the other end of each upper parallel branch is connected to the upper moving platform; a lower moving platform, the other end of each lower parallel branch is connected to the lower moving platform, and the upper moving platform is located above the lower moving platform.

[0006] Furthermore, the static platform includes a constraint base arranged at the bottom, and the multilateral parallel loading device of the aircraft engine casing also includes an image calibrator assembly, which is fixedly connected to the constraint base, and the image calibrator assembly can measure the position and posture of the upper moving platform and the lower moving platform.

[0007] Furthermore, the image calibration instrument assembly includes: a bracket, including a vertical bracket and a horizontal bracket, the lower end of the vertical bracket is fixedly connected to the constraint base, and the middle part of the horizontal bracket is connected to the upper end of the vertical bracket; at least two cameras are respectively arranged at both ends of the horizontal bracket.

[0008] Furthermore, a plurality of coding marking points are provided on both the upper movable platform and the lower movable platform, and the camera can obtain the position coordinates of the coding marking points.

[0009] Furthermore, the upper parallel branch chain and the lower parallel branch chain have the same structure.

[0010] Furthermore, the upper parallel branch chain includes: an upper connecting rod, one end of which is provided with a joint ball joint; a lower connecting rod, which is connected to the other end of the upper connecting rod and can slide along the axial direction of the upper connecting rod; a force sensor, which is fixedly arranged at one end of the lower connecting rod away from the upper connecting rod, and the force sensor is connected to the upper moving platform through a universal ball joint.

[0011] Furthermore, the upper moving platform and the lower moving platform are both provided with multiple connecting seats, the multiple upper parallel branches are connected one-to-one with the multiple connecting seats provided on the upper moving platform, and the multiple lower parallel branches are connected one-to-one with the multiple connecting seats provided on the lower moving platform.

[0012] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above-mentioned technical solutions adopted in the embodiments of this specification include at least the following: the embodiments of the present invention form a dynamic platform in a parallel manner, replacing the previous loading branches that are distributed in a non-standard design to perform multilateral six-degree-of-freedom load loading. The installation and state changes of the casing can be met by the posture control of the dynamic platform, avoiding the cost and periodic expenditure of multiple manual disassembly and assembly of the branches, and improving the test efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0014] Figure 1 This is a schematic structural diagram of a multilateral parallel loading device for an aircraft engine casing according to the present invention;

[0015] Figure 2 This is a top view of the internal structure of a multilateral parallel loading device for an aircraft engine casing;

[0016] Figure 3 Schematic diagram of the upper parallel branched chain composition in the present invention;

[0017] Figure 4It is a schematic diagram of the composition of the moving platform in the present invention.

[0018] Reference numerals in the figure: 1. static platform; 2. upper parallel branch chain; 3. lower parallel branch chain; 4. upper moving platform; 5. lower moving platform; 6. image calibration instrument assembly; 8. constraint base; 11. column frame; 12. adjustment assembly; 41. connecting seat; 42. loading plate; 43. coding mark point; 71. upper connecting rod; 72. lower connecting rod; 73. joint ball hitch; 74. universal ball hitch; 75. force sensor. DETAILED DESCRIPTION

[0019] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0020] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features in the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0021] like Figures 1 to 4 As shown, an embodiment of the present invention provides a multilateral parallel loading device for an aircraft engine casing, comprising a static platform 1, a plurality of upper parallel branches 2, a plurality of lower parallel branches 3, an upper movable platform 4, and a lower movable platform 5. One end of each upper parallel branch 2 is connected to the static platform 1; one end of each lower parallel branch 3 is connected to the static platform 1, and one end of each upper parallel branch 2 is located above one end of each lower parallel branch 3; the other end of each upper parallel branch 2 is connected to the upper movable platform 4; the other end of each lower parallel branch 3 is connected to the lower movable platform 5, and the upper movable platform 4 is located above the lower movable platform 5.

[0022] The embodiment of the present invention forms a dynamic platform in a parallel manner, replacing the previous loading branches that are distributed according to non-standard designs to perform multilateral six-degree-of-freedom load loading. The installation and state changes of the casing can be met through the posture control of the dynamic platform, avoiding the cost and periodic expenditure of multiple manual disassembly and assembly of the branches, and improving the test efficiency.

[0023] The static platform 1 includes a column frame 11 and an adjustment component 12. The column frame 11 is fixed to the ground. The adjustment component 12 is arranged inside the column of the column frame 11 and is fixedly connected to the column. The constraint base 8 is arranged at the bottom center of the column frame 11 and is constrained and connected to the casing to be tested; the upper parallel branch chain 2 is arranged inside the column frame 11 and is connected to the adjustment component 12 and the upper moving platform 4; the lower parallel branch chain 3 is similar in structure to the lower parallel branch chain 3, and is connected to the adjustment component 12 and the lower moving platform 5; the upper moving platform 4 and the lower moving platform 5 are distributed parallel to each other and are separated by a certain distance. The loading mounting surface of the casing to be tested is installed on the upper moving platform 4 and the lower moving platform 5.

[0024] Preferably, the column frame 11 is a hexagonal prism structure, and the prism surface is provided with equally spaced adjustment holes. The upper parallel branch chain 2 and the lower parallel branch chain 3 are connected to the short sides through the adjustment component 12.

[0025] The hole spacing on the surface of the column frame is 150 mm. The upper parallel branch chain 2 and the lower parallel branch chain 3 can be adapted to the height dimensions of different models of casings by changing the installation hole positions and adjusting the distance between the upper moving platform 4 and the lower moving platform 5.

[0026] In this embodiment, the three short sides of the column frame are equal in length, and the three long sides are equal in length. After the two end points of the short sides are connected to the center of plane symmetry, the angle between the two sides is 30 degrees, which can meet the six-degree-of-freedom load range of the test to the greatest extent and avoid the singularity of the Jacobian matrix of the six-degree-of-freedom loading.

[0027] The aircraft engine casing multilateral parallel loading device also includes an image calibration instrument assembly 6, fixedly connected to the constraint base 8. This assembly is mounted on the lower end of the column frame 11, providing an image field of view that covers the upper and lower platforms 4 and 5, as well as the surface of the constraint base 8. The image calibration instrument assembly 6 measures the position and posture of the upper and lower platforms 4 and 5. This allows for regular calibration of the platform loading, improving the loading accuracy and maturity of the test.

[0028] Specifically, the image calibration instrument component 6 is a digital image device that can identify coded marking points. After the digital image device is unified through global coordinates, it can measure the relative conversion relationship between its own coordinate system and the coordinate systems of the static platform 1, the upper moving platform 4, and the lower moving platform 5, and then measure the posture of the upper moving platform 4 and the lower moving platform 5, provide calculation parameters for the loading of the parallel mechanism, and perform posture control and load control.

[0029] There are three sets of image calibration instrument components 6, which are symmetrical about the center of the column frame 11 and are arranged on the symmetry center line of the connecting seat 41; the field of view of each set of image calibration instrument components 6 can cover the coded marking points in the corresponding directions of the upper moving platform 4, the lower moving platform 5, and the constraint base 8, and can identify the coded marking points 43 as unique numbers, and solve the global coordinates of the numbers, thereby calculating the posture of the upper moving platform 4 and the lower moving platform 5.

[0030] The image calibration instrument assembly 6 includes a bracket and at least two cameras. The bracket includes a vertical bracket and a horizontal bracket. The lower end of the vertical bracket is fixedly connected to the constraint base 8, and the middle of the horizontal bracket is connected to the upper end of the vertical bracket. The at least two cameras are respectively set at both ends of the horizontal bracket.

[0031] The upper movable platform 4 includes a connecting seat 41, a loading plate 42, and coding marking points 43. The three connecting seats 41 are distributed at 120 degrees and connected to the upper parallel branch chain 2 and the loading plate 42. The mounting holes on the loading plate 42 are connected to the mounting surface of the receiver to be tested, and the six-degree-of-freedom load loading of the receiver mounting surface is achieved through posture control; the coding marking points 43 are located on the symmetrical centerline of the connecting seat 41. The three coding marking points 43 are centrally symmetrical, and the connecting lines form an equilateral triangle. The coding can be recognized by the image calibration instrument assembly 6. The lower movable platform 5 has the same structure as the upper movable platform 4, and the specific structure of the upper movable platform 4 will not be repeated here.

[0032] Preferably, a constraint mounting hole and a coding marking point 43 are provided on the constraint base 8. The constraint mounting hole is used for the constraint installation of the casing to be tested. The coding marking point 43 is consistent with the plane coordinates of the coding marking point 43 of the upper moving platform 4. The coding marking point 43 can be recognized by the image calibration instrument component 6.

[0033] The upper parallel branch chain 2 and the lower parallel branch chain 3 have the same structure. The upper parallel branch chain 2 comprises an upper connecting rod 71, a lower connecting rod 72, and a load cell 75. One end of the upper connecting rod 71 is provided with a ball joint 73; the lower connecting rod 72 is connected to the other end of the upper connecting rod 71 and can slide along the axial direction of the upper connecting rod 71. The load cell 75 is fixed to the end of the lower connecting rod 72 away from the upper connecting rod 71 and is connected to the upper movable platform 4 via a universal ball joint 74.

[0034] It should be noted that the structure of each branch of the upper parallel branch 2 and the lower parallel branch 3 is similar, but the load levels can be different. It is a typical SPS parallel mechanism. The six loads fed back by the force sensor 75 of each branch are converted into six-degree-of-freedom loads through the force-Jacobian matrix. The loads applied to the mounting surface of the casing by the upper moving platform 4 and the lower moving platform 5 should be balanced with the constraint surface.

[0035] Specifically, in an embodiment of the present invention, the top of the upper connecting rod 71 is connected to the adjustment assembly 12 through a joint ball joint 73, the lower connecting rod 72 is connected to a force sensor 75, the force sensor 75 in the upper parallel branch chain 2 is connected to the upper moving platform 4 through a universal ball joint 74, and the force sensor 75 in the lower parallel branch chain 3 is connected to the lower moving platform 5 through a universal ball joint 74.

[0036] In this embodiment, there are six upper parallel branches 2 and six lower parallel branches 3. The six upper parallel branches 2 are symmetrical about the center of the static platform 1, the upper moving platform 4, and the lower moving platform 5. The top projection line of the upper and lower connection points is a hexagon, with three short sides of equal length and three long sides of equal length. The driving method can be pneumatic, hydraulic or electric, and the movement is controlled by a closed-loop system composed of a force sensor 75, an image calibration instrument component 6, and a motion controller.

[0037] The arrangement of the lower parallel branch chain 3 is the same as that of the upper parallel branch chain 2. Detailed description thereof will not be given here.

[0038] In an embodiment of the present invention, the upper parallel branch 2 and the lower parallel branch 3 control the six-degree-of-freedom load and posture of the upper moving platform 4 and the lower moving platform 5 according to the posture feedback of the image calibration instrument assembly 6. The load feedback obtains the six-degree-of-freedom load of the upper moving platform 4 and the lower moving platform 5 through the force sensor 75, thereby realizing six-degree-of-freedom loading of multiple mounting surfaces of the casing to be tested.

[0039] The embodiments of the present invention have the following technical effects:

[0040] By acquiring measurement parameters through a visual measurement system, and using a controller to drive a parallel device for load control, a standard six-degree-of-freedom (DOF) load-loading device for the receiver is formed. This device eliminates the need for disassembly when replacing test pieces, and can accommodate the size requirements of different test pieces by adjusting the spacing between the moving platforms and the mounting hole positions. This invention implements six-DOF load loading for a multilateral parallel mechanism, achieving unified position measurement of multiple moving platforms through image calibration and coded marker point recognition measurement. This innovative posture measurement method offers significant engineering value for six-DOF loading of test pieces with multiple loading surfaces.

[0041] Compared to existing casing static strength loading testers, this invention utilizes parallel loading platforms to form a dynamic platform, replacing the conventional non-standard design of loading branches. This allows the dynamic platform's position control to accommodate casing installation and state changes, eliminating the cost and cycle time of multiple manual disassembly and assembly of branches and improving test efficiency. Utilizing a sophisticated six-degree-of-freedom calibration sensor, the dynamic platform's loading can be regularly calibrated, improving the loading accuracy and maturity of the test.

[0042] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A multilateral parallel loading device for an aircraft engine casing, characterized in that: include: static platform (1); A plurality of upper parallel branches (2), one end of each upper parallel branch (2) is connected to the static platform (1); A plurality of lower parallel branches (3), one end of each lower parallel branch (3) is connected to the static platform (1), and one end of each upper parallel branch (2) is located above one end of each lower parallel branch (3); An upper movable platform (4), wherein the other end of each upper parallel branch chain (2) is connected to the upper movable platform (4); A lower moving platform (5), the other end of each lower parallel branch chain (3) is connected to the lower moving platform (5), and the upper moving platform (4) is located above the lower moving platform (5); The upper parallel branch chain (2) and the lower parallel branch chain (3) have the same structure; The upper parallel branch chain (2) includes an upper connecting rod (71), a lower connecting rod (72) and a force sensor (75), wherein one end of the upper connecting rod (71) is provided with a joint ball joint (73); the lower connecting rod (72) is connected to the other end of the upper connecting rod (71) and can slide along the axial direction of the upper connecting rod (71); the force sensor (75) is fixedly arranged at one end of the lower connecting rod (72) away from the upper connecting rod (71), and the force sensor (75) is connected to the upper movable platform (4) via a universal ball joint (74); The upper movable platform (4) and the lower movable platform (5) are both provided with a plurality of connecting seats (41), the plurality of upper parallel branches (2) are connected one-to-one with the plurality of connecting seats (41) provided on the upper movable platform (4), and the plurality of lower parallel branches (3) are connected one-to-one with the plurality of connecting seats (41) provided on the lower movable platform (5).

2. The aircraft engine casing multilateral parallel loading device according to claim 1, characterized in that: The static platform (1) includes a constraint base (8) arranged at the bottom, and the aircraft engine casing multilateral parallel loading device also includes an image calibration instrument component (6) fixedly connected to the constraint base (8), and the image calibration instrument component (6) is capable of measuring the position and posture of the upper moving platform (4) and the lower moving platform (5).

3. The aircraft engine casing multilateral parallel loading device according to claim 2, characterized in that: The image calibration instrument component (6) includes: The bracket comprises a vertical bracket and a horizontal bracket, wherein the lower end of the vertical bracket is fixedly connected to the constraint base (8), and the middle part of the horizontal bracket is connected to the upper end of the vertical bracket; At least two cameras are respectively arranged at two ends of the horizontal support.

4. The aircraft engine casing multilateral parallel loading device according to claim 3, characterized in that: A plurality of coding marking points (43) are provided on both the upper movable platform (4) and the lower movable platform (5), and the camera can obtain the position coordinates of the coding marking points (43).

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