Method and device for measuring mass distribution uniformity of an aeroengine

Abstract

The present invention provides a device and method for measuring the mass distribution uniformity of an aeroengine. The device includes: a cross beam, one end of which is fixed on a first fixing component, the other end is fixed on a second fixing member, and the middle part of the cross beam is fixed on a third fixing member. A first-direction adjusting mechanism is provided on the cross beam; a front stretching structure and a rear stretching structure, the front stretching structure is fixed below the first fixing component, and the rear stretching structure passes through the cross beam and the first-direction adjusting mechanism; both the front stretching component and the rear stretching structure include a second-direction adjusting mechanism and two groups of stretching components, and each group of stretching components is provided with an electronic hanging scale and a height adjusting component. The device and method designed by the present invention are simple, portable, and quick to operate, and the mass distribution uniformity in the space coordinate system can be obtained with only one adjustment.

Description

Technical Field

[0001] The present invention belongs to the field of aviation technology, relates to aviation engine detection technology, and specifically provides a method and device for measuring the mass distribution uniformity of an aviation engine. Background Art

[0002] The mass distribution uniformity of an aviation engine is an important measurement parameter in the mass characteristics of an aviation engine, and actual measurement must be carried out to determine its precise position. Currently, the commonly used measurement devices generally rely on two principles: one is a measurement device based on the principle of unbalanced moment method, which requires the setting of a relatively precise angle dial and pointer. During measurement, it is not easy to read the angle on the high-altitude dial, and there is an angle between the human eye and the dial, resulting in frequent reading deviations; and during measurement, multiple adjustments are required for alignment, increasing the safety risk; and it can only measure the distribution values in the XZ axis direction. The other is a measurement device based on the principle of multi-point weighing method. Although this device can also obtain the result with only one adjustment, it is often large in volume and mass, requires a dedicated site and is difficult to move, and the engine needs to be transported to the equipment position for detection during actual operation. Summary of the Invention

[0003] The purpose of the present invention is to design a method and device for measuring the mass distribution uniformity of an aviation engine, which has a simple and portable structure, is quick and convenient to operate, and can obtain the mass distribution uniformity of the aviation engine in the space coordinate system with only one adjustment.

[0004] The technical solution for achieving the invention purpose is as follows:

[0005] In a first aspect, the present invention provides a device for measuring the mass distribution uniformity of an aviation engine, including:

[0006] A cross beam, one end of which is fixed on a first fixing component, the other end is fixed on a second fixing member, and the middle part of the cross beam is fixed on a third fixing member. A first direction adjusting mechanism is provided on the cross beam;

[0007] A front stretching structure and a rear stretching structure, the front stretching structure is fixed below the first fixing component, and the rear stretching structure passes through the cross beam and the first direction adjusting mechanism;

[0008] Both the front stretching structure and the rear stretching structure include a second direction adjusting mechanism and 2 sets of stretching components, and each set of stretching components is provided with an electronic hanging scale and a height adjusting component.

[0009] Further, the first direction adjusting mechanism includes:

[0010] A lifting ring adjusting screw, one end of which is arranged on the first fixing component and the other end is arranged on the third fixing component;

[0011] The rear suspension point adjusting screw, one end of the rear suspension point adjusting screw is arranged on the second fixing member, and the other end is arranged on the third fixing member;

[0012] The lifting ring, the lifting ring passes through the cross beam and the lifting ring adjusting screw.

[0013] Furthermore, the front stretching structure includes:

[0014] The front fixing seat, the upper part of the front fixing seat is fixed on the first fixing assembly;

[0015] The front screw, the front screw passes through both ends of the lower part of the front fixing seat, and height adjusting assemblies are fixed at both ends of the front screw, and the stretching assembly is arranged on the height adjusting assemblies.

[0016] Furthermore, the rear stretching structure includes:

[0017] The rear fixing seat, the upper part of the rear fixing seat passes through the cross beam and the rear suspension point adjusting screw;

[0018] The rear screw, the rear screw passes through both ends of the lower part of the rear fixing seat, and height adjusting assemblies are fixed at both ends of the rear screw, and the stretching assembly is arranged on the height adjusting assemblies.

[0019] Further, the height adjusting assembly includes:

[0020] The guide rod and the threaded rod, one ends of the guide rod and the threaded rod both pass through the slider assembly, and the other ends are fixed on the side pulling block;

[0021] The pulley assembly, the pulley assembly is fixed at the lower end of the slider assembly, one end of the stretching assembly is fixed on the side pulling block, and the other end passes through the pulley assembly.

[0022] Further, the second direction adjusting mechanism includes a front weight and a rear weight;

[0023] The front weight is sleeved on the positive and negative threads at the end of the front screw of the front stretching structure;

[0024] The rear weight is sleeved on the positive and negative threads at the end of the rear screw of the rear stretching structure.

[0025] In a second aspect, the present invention provides a method for measuring the mass distribution uniformity of an aeroengine, including the following steps:

[0026] Design the positions of two front suspension points and two rear suspension points for detecting the mass distribution uniformity on the aeroengine;

[0027] The mass distribution uniformity measuring device is connected to the aero-engine, lifting the aero-engine and adjusting its position until the aero-engine reaches a horizontal state;

[0028] Adjust the positions of the aero-engine in the X and Y directions to make the stretching assembly in a vertical state;

[0029] Read the data of the electronic hoist scale on the stretching assembly for the first time to obtain the tensile force data N1 of the front suspension point and the rear suspension point;

[0030] Adjust the positions of the 2 rear suspension points to rotate the aero-engine by an angle θ, and read the data of the electronic hoist scale on the stretching assembly for the second time to obtain the tensile force data N2 of the front suspension point and the rear suspension point;

[0031] Calculate the coordinate values [x, y, z] of the center of gravity G of the aero-engine;

[0032] Based on the coordinate values [x, y, z] of the center of gravity of the aero-engine and the theoretical coordinate values [x0, y0, z0], calculate the mass distribution uniformity δ of the aero-engine.

[0033] Furthermore, the calculation method of the coordinate values [x, y, z] of the center of gravity G of the aero-engine is as follows:

[0034] Before the aero-engine is lifted, define the center of gravity of the aero-engine as G, the axial distance between the front suspension point and the center of the main mounting section on the aero-engine as L0, the axial distance between the line connecting the 2 front suspension points and the center of gravity of the aero-engine as L1, the axial distance between the line connecting the 2 rear suspension points and the center of gravity of the aero-engine as L2, the distance L3 in the Y direction between the center of gravity of the aero-engine and one of the front suspension points, and the distance L4 in the Y direction between the center of gravity of the aero-engine and the other front suspension point;

[0035] According to the tensile force data N1, the axial distance L, and the axial distance W1, calculate the coordinate values of the center of gravity of the aero-engine in the X and Y directions;

[0036] After the rotation angle θ of the aero-engine is adjusted, define the axial distance between the center of gravity of the aero-engine and the line connecting the 2 front suspension points as L5, and the axial distance between the center of gravity of the aero-engine and the line connecting the 2 rear suspension points as L6;

[0037] According to the tensile force data N2, the rotation angle θ, and the axial distance L, calculate the coordinate value of the center of gravity of the aero-engine in the Z direction.

[0038] Furthermore, the calculation formula of the mass distribution uniformity δ of the aero-engine is: 。

[0039] Furthermore, the positions of the aero-engine in the X and Y directions are adjusted by the first-direction adjustment mechanism; the rotation angle θ of the aero-engine is adjusted by the height adjustment component with a rear stretching structure.

[0040] Compared with the prior art, the beneficial effects of the present invention are as follows: The mass distribution uniformity measuring device and method for the aero-engine designed by the present invention have a simple and portable structure, quick operation, and can obtain the mass distribution uniformity in the space coordinate system with only one adjustment. Description of the Drawings

[0041] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only for the present invention to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0042] Figure 1 It is a schematic diagram of the mass distribution uniformity measuring device for the aero-engine in the specific implementation manner;

[0043] Figure 2 It is a schematic diagram of the front stretching structure in the specific implementation manner;

[0044] Figure 3 It is a schematic diagram of the rear stretching structure in the specific implementation manner;

[0045] Figure 4 It is a schematic diagram of the height adjustment component in the specific implementation manner;

[0046] Figure 5 It is a semi-sectional outer contour top view of the aero-engine before hoisting in the specific implementation manner;

[0047] Figure 6 It is a semi-sectional outer contour top view of the aero-engine after hoisting and with the angle adjusted in the specific implementation manner;

[0048] Among them, 1. Hoisting ring adjusting screw; 3. Cross beam; 4. Hoisting ring; 2-1. First fixing component; 2-2. Second fixing piece; 5. Third fixing piece; 6. Rear hoisting point adjusting screw; 7. Rear stretching structure; 8. Electronic hoisting scale; 9. First pin shaft; 10. Adapter plate; 11. Pin; 12. Front auxiliary mounting seat; 14. Front stretching structure; 15. Height adjustment component; 14-1. Front fixing seat; 14-2. Front screw; 15-1. Guide rod; 15-2. Threaded rod; 15-3. Slide block assembly; 15-4. Side pulling block; 15-5. Pulley assembly; 15-6. Second pin shaft; 16-1. Front weight; 16-2. Rear weight; 7-1. Rear fixing seat; 7-2. Rear screw. Detailed implementation manners

[0049] The present invention will be further described below in conjunction with specific embodiments, and the advantages and features of the present invention will become clearer as the description progresses. However, these embodiments are merely exemplary and do not constitute any limitation to the scope of the present invention. Those skilled in the art should understand that without departing from the spirit and scope of the present invention, modifications or substitutions can be made to the details and forms of the technical solutions of the present invention, but such modifications and substitutions all fall within the protection scope of the present invention.

[0050] In the description of this embodiment, it should be understood that the orientation or positional relationships indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are based on the orientation or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0051] In addition, the terms "first", "second", "third", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first", "second", etc. may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, the meaning of "a plurality" is two or more.

[0052] Embodiment 1:

[0053] This embodiment provides a device for measuring the mass distribution uniformity of an aeroengine, as Figure 1 shown. The device for measuring the mass distribution uniformity includes: a cross beam 3, a front stretching structure 14, and a rear stretching structure 7

[0054] As Figure 1 shown, one end of the cross beam 3 is fixed on the first fixing component 2-1, the other end is fixed on the second fixing member 2-2, and the middle part of the cross beam 3 is fixed on the third fixing member 5. A first-direction adjusting mechanism is provided on the cross beam 3.

[0055] As Figure 1 shown, the front stretching structure 14 is fixed below the first fixing component 2-1. The rear stretching structure 7 passes through the cross beam 3 and the first-direction adjusting mechanism, and the first-direction adjusting mechanism can adjust the positions of the front stretching structure 14 and the rear stretching structure 7 relative to the cross beam 3 in the first direction (i.e., the X direction).

[0056] The front stretching structure 14 and the rear stretching structure 7 both include a second-direction adjusting mechanism and two sets of stretching components. Each set of stretching components is provided with an electronic hanging scale 8 and a height adjusting component 15. The second-direction adjusting mechanism can adjust the positions of the front stretching structure 14 and the rear stretching structure 7 relative to the cross beam 3 in the second direction (i.e., the Z direction), and the height adjusting component 15 can adjust the positions of the stretching components in the vertical direction (i.e., the Y direction). The electronic hanging scale 8 can read the pulling force after the stretching components lift the workpiece to be measured.

[0057] As Figure 1 shown, the stretching components of the front stretching structure 14 include a first pin shaft 9, an adapter plate 10, a pin 11, and a front auxiliary mounting seat 12; the stretching components of the rear stretching structure 7 include a first pin shaft 9, an adapter plate 10, and a pin 11.

[0058] In one embodiment, as Figure 1 shown, the first-direction adjusting mechanism includes:

[0059] A lifting ring adjusting screw 1, one end of the lifting ring adjusting screw 1 is arranged on the first fixing component 2-1, and the other end is arranged on the third fixing piece 5;

[0060] A rear hanging point adjusting screw 6, one end of the rear hanging point adjusting screw 6 is arranged on the second fixing piece 2-2, and the other end is arranged on the third fixing piece 5;

[0061] A lifting ring 4, the lifting ring 4 passes through the cross beam 3 and the lifting ring adjusting screw 1.

[0062] The adjusting method of the first-direction adjusting mechanism is: rotate the lifting ring adjusting screw 1, and the lifting ring adjusting screw 1 drives the lifting ring 4 to move on the cross beam 3; rotate the rear hanging point adjusting screw 6, and the rear hanging point adjusting screw 6 drives the rear stretching structure to move on the cross beam 3.

[0063] In one embodiment, as Figure 2 shown, the front stretching structure 14 includes:

[0064] A front fixing seat 14-1, the upper part of the front fixing seat 14-1 is fixed on the first fixing component 2-1;

[0065] A front screw 14-2, the front screw 14-2 passes through both ends of the lower part of the front fixing seat 14-1, and height adjusting components 15 are fixed at both ends of the front screw 14-2, and the stretching components are arranged on the height adjusting components 15.

[0066] In one embodiment, as Figure 3 shown, the rear stretching structure 7 includes:

[0067] Rear fixing seat 7-1, the upper part of the rear fixing seat 7-1 passes through the cross beam 3 and the rear suspension point adjusting screw 6;

[0068] Rear screw 7-2, the rear screw 7-2 passes through both ends of the lower part of the rear fixing seat 7-1, and height adjusting components 15 are fixed at both ends of the rear screw 7-2, and a stretching component is provided on the height adjusting component 15.

[0069] In one embodiment, as Figure 4 shown, the height adjusting component 15 includes:

[0070] Guide rod 15-1, threaded rod 15-2, one ends of the guide rod 15-1 and the threaded rod 15-2 both pass through the slider assembly 15-3, and the other ends are fixed to the side pulling block 15-4 through the second pin shaft 15-6;

[0071] Pulley assembly 15-5, the pulley assembly 15-5 is fixed to the lower end of the slider assembly 15-3, one end of the stretching component is fixed to the side pulling block 15-4, and the other end passes through the pulley assembly 15-5.

[0072] The process of the height adjusting component 15 adjusting the height is: rotating the threaded rod 15-2, the threaded rod 15-2 drives the side pulling block 15-4 to slide on the guide rod 15-1, and the pulley assembly 15-5 rotates to make the stretching component rise or fall in the vertical direction (i.e., the Y direction).

[0073] In one embodiment, as Figure 2 and Figure 3 shown, the second direction adjusting mechanism includes a front weight (16-1), a rear weight 16-2;

[0074] The front weight 16-1 is sleeved on the positive and negative threads at the end of the front screw 14-2 of the front stretching structure 14; the rear weight 16-2 is sleeved on the positive and negative threads at the end of the rear screw 7-2 of the rear stretching structure 7.

[0075] The process of the second direction adjusting mechanism adjusting the position in the Z direction is: rotating the front weight 16-1, the front screw 14-2 undergoes a displacement change in the Z direction relative to the first fixing component 2-1, driving the stretching component of the front stretching structure 14 to undergo a displacement change in the Z direction relative to the first fixing component 2-1; or rotating the rear weight 16-2, the rear screw 7-2 undergoes a displacement change in the Z direction relative to the second fixing component 2-2, driving the stretching component of the rear stretching structure 7 to undergo a displacement change in the Z direction relative to the second fixing component 2-2.

[0076] Embodiment 2:

[0077] This embodiment provides a method for measuring the mass distribution uniformity of an aeroengine, including the following steps:

[0078] S1. Design the positions of two front suspension points and two rear suspension points for detecting the mass distribution uniformity on the aeroengine.

[0079] As Figure 5 shown, it is a half-sectional external contour top view before the aeroengine is lifted. Its overall shape is approximately axisymmetric. Taking the intersection point of the axis of the main mounting section of the intermediate casing and the axis of the engine as the origin, taking the reverse course direction of the engine axis as the positive direction of the X-axis of the rectangular coordinate system, and taking the direction from the origin of the engine to the right in the forward course direction (i.e., one end of suspension A) as the positive direction of the Y-axis, the positive direction of the Z-axis is determined by the right-hand rule.

[0080] The four suspension points of the engine should be arranged on the X-Y plane through the suspensions. Among them, suspensions A and B are the front suspension points, and suspensions C and D are the rear suspension points.

[0081] Define the center of gravity of the aeroengine as G, the axial distance between the front suspension point and the center of the main mounting section on the aeroengine as L0, the axial distance between the line connecting the two front suspension points and the center of gravity of the aeroengine as L1, the axial distance between the line connecting the two rear suspension points and the center of gravity of the aeroengine as L2, the distance between the center of gravity of the aeroengine and one of the front suspension points (such as suspension A) in the Y direction as L3, and the distance between the center of gravity of the aeroengine and the other front suspension point (such as suspension B) in the Y direction as L4.

[0082] S2. Connect the mass distribution uniformity measuring device to the aeroengine, lift the aeroengine and adjust the position of the aeroengine until the aeroengine reaches a horizontal state.

[0083] Specifically, connect the two front suspension points of the engine to two sets of stretching components on the front stretching structure 14 of the mass distribution uniformity measuring device respectively, connect the two rear suspension points of the engine to two sets of stretching components on the rear stretching structure 7 of the mass distribution uniformity measuring device respectively, connect a lifting device (such as a crane) to the lifting ring 4 of the mass distribution uniformity measuring device, and lift the mass distribution uniformity measuring device and the aeroengine.

[0084] S3. Adjust the positions of the aeroengine in the X direction and the Y direction to make the stretching components reach a vertical state.

[0085] In this step, a first-direction adjustment mechanism is used to adjust the positions of the aeroengine in the X direction and the Y direction; specifically, by rotating the lifting ring adjustment screw 1, the lifting ring 4 is moved on the cross beam 3 to move the lifting ring 4 to a position near the center of gravity of the aeroengine to make the engine approximately horizontal; by rotating the rear suspension point adjustment screw 6, adjust to make the four stretching components reach a vertical state.

[0086] S4. Read the data of the electronic hoist scale on the stretching component for the first time, and obtain the tensile force data N1 of the front suspension point and the rear suspension point.

[0087] Among them, the tensile force data N1 includes N A , N B , N C , N D .

[0088] S5. Adjust the positions of the 2 rear suspension points to make the rotation angle θ of the aeroengine. Read the data of the electronic hoist scale on the stretching component for the second time, and obtain the tensile force data N2 of the front suspension point and the rear suspension point.

[0089] In this step, the height adjustment component 15 of the rear stretching structure 7 is used to adjust the rotation angle θ of the aeroengine. As Figure 6 shown is the half-sectional external contour top view of the aeroengine after hoisting and adjusting the angle. At this time, the axial distance between the center of gravity of the aeroengine and the connection line between the 2 front suspension points is defined as L5, and the axial distance between the connection line between the 2 rear suspension points is defined as L6;

[0090] When the engine is stable, read the tensile force data N2. The tensile force data N2 includes N a , N b , N c , N d .

[0091] S6. Calculate the coordinate values [x, y, z] of the center of gravity G of the aeroengine;

[0092] In this step, the calculation method of the coordinate values [x, y, z] of the center of gravity G of the aeroengine is as follows:

[0093] S601. Calculate the coordinate values of the center of gravity of the aeroengine in the X direction and the Y direction according to the tensile force data N1, the axial distance L, and the axial distance W1;

[0094] Specifically, according to the moment balance, we can get: , where , ;

[0095] From this, the axial distance between the center of gravity of the engine and the connection line of the front suspension points (A suspension, B suspension) can be obtained as: ;

[0096] Similarly: , where , ;

[0097] From this, the Y-direction distance between the center of gravity of the engine and the A suspension can be obtained as:

[0098] ;

[0099] S602. Calculate the coordinate value of the center of gravity of the aero-engine in the Z direction based on the tensile force data N2, the rotation angle θ, and the axial distance L.

[0100] Specifically, according to the moment balance equation, we can obtain: , where , .

[0101] Thus, the horizontal distance between the center of gravity of the engine and the front suspension A is: .

[0102] S603. According to the data in S1, S5, S601, and S602, obtain that the X coordinate value of the center of gravity of the engine is x = , the Y coordinate value is y = , and the Z coordinate value is z = , that is, the coordinate value [x, y, z] of the center of gravity of the engine is: , , .

[0103] S7. Based on the coordinate value [x, y, z] of the center of gravity of the aero-engine and the theoretical coordinate value [x0, y0, z0], calculate the mass distribution uniformity δ of the aero-engine.

[0104] In this step, the calculation formula for the mass distribution uniformity δ of the aero-engine is: .

[0105] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

[0106] In addition, it should be understood that although this specification is described according to the embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A device for measuring the mass distribution uniformity of an aero-engine, characterized in that, Comprising: A crossbeam (3), one end of the crossbeam (3) is fixed on the first fixing component (2-1), the other end is fixed on the second fixing member (2-2), and the middle part of the crossbeam (3) is fixed on the third fixing member (5). A first direction adjusting mechanism is provided on the crossbeam. The first direction adjusting mechanism includes a sling adjusting screw (1), a rear sling point adjusting screw (6) and a sling (4). One end of the sling adjusting screw (1) is arranged on the first fixing component (2-1), the other end is arranged on the third fixing member (5). One end of the rear sling point adjusting screw (6) is arranged on the second fixing member (2-2), the other end is arranged on the third fixing member (5). The sling (4) passes through the crossbeam (3) and the sling adjusting screw (1); A front stretching structure (14) and a rear stretching structure (7). The front stretching structure (14) is fixed below the first fixing component (2-1), and the rear stretching structure (7) passes through the crossbeam (3) and the first direction adjusting mechanism; Both the front stretching structure (14) and the rear stretching structure (7) include a second direction adjusting mechanism and 2 sets of stretching components. Each set of stretching components is provided with an electronic hanging scale (8) and a height adjusting component (15). The second direction adjusting mechanism includes a front weight (16-1) and a rear weight (16-2). The front weight (16-1) is sleeved on the positive and negative threads at the end of the front screw (14-2) of the front stretching structure (14). The rear weight (16-2) is sleeved on the positive and negative threads at the end of the rear screw (7-2) of the rear stretching structure (7). The height adjusting component (15) includes a guide rod (15-1), a threaded rod (15-2) and a pulley assembly (15-5). One end of the guide rod (15-1) and the threaded rod (15-2) both pass through the slider assembly (15-3), and the other end is fixed on the side pulling block (15-4). The pulley assembly (15-5) is fixed at the lower end of the slider assembly (15-3). One end of the stretching component is fixed on the side pulling block (15-4), and the other end passes through the pulley assembly (15-5).

2. The device for measuring the mass distribution uniformity of an aero-engine according to claim 1, characterized in that, The front stretching structure (14) includes: A front fixing seat (14-1), the upper part of the front fixing seat (14-1) is fixed on the first fixing component (2-1); A front screw (14-2), the front screw (14-2) passes through both ends of the lower part of the front fixing seat (14-1), and both ends of the front screw (14-2) are fixed with the height adjusting component (15), and the stretching component is provided on the height adjusting component (15).

3. The device for measuring the mass distribution uniformity of an aero-engine according to claim 1, characterized in that, The rear stretching structure (7) includes: A rear fixing seat (7-1), the upper part of the rear fixing seat (7-1) passes through the crossbeam (3) and the rear sling point adjusting screw (6); A rear screw (7-2), the rear screw (7-2) passes through both ends of the lower part of the rear fixing seat (7-1), and both ends of the rear screw (7-2) are fixed with the height adjusting component (15), and the stretching component is provided on the height adjusting component (15).

4. A method for measuring the mass distribution uniformity of an aero-engine, characterized in that, Using the measuring device for the mass distribution uniformity of an aeroengine according to any one of claims 1 to 3 to measure the mass distribution uniformity, the method comprising the following steps: Designing the positions of two front suspension points and two rear suspension points for detecting the mass distribution uniformity on the aeroengine; Connecting the measuring device for the mass distribution uniformity to the aeroengine, lifting the aeroengine and adjusting the position of the aeroengine until the aeroengine reaches a horizontal state; Adjusting the positions of the aeroengine in the X direction and the Y direction to make the stretching assembly in a vertical state; Reading the data of the electronic hanging scale on the stretching assembly for the first time to obtain the tensile force data N1 of the front suspension point and the rear suspension point; Adjusting the positions of the two rear suspension points to rotate the aeroengine by an angle θ, reading the data of the electronic hanging scale on the stretching assembly for the second time to obtain the tensile force data N2 of the front suspension point and the rear suspension point; Calculating the coordinate values [x, y, z] of the center of gravity G of the aeroengine; Based on the coordinate values [x, y, z] of the center of gravity of the aeroengine and the theoretical coordinate values [x0, y0, z0], calculating the mass distribution uniformity δ of the aeroengine.

5. The method for measuring the mass distribution uniformity of an aero-engine according to claim 4, characterized in that: The calculation method for the coordinate values [x, y, z] of the center of gravity G of the aeroengine is as follows: Before the aeroengine is lifted, defining the center of gravity of the aeroengine as G, the axial distance between the front suspension point and the center of the main mounting section on the aeroengine as L0, the axial distance between the line connecting the two front suspension points and the center of gravity of the aeroengine as L1, the axial distance between the line connecting the two rear suspension points and the center of gravity of the aeroengine as L2, the distance L3 in the Y direction between the center of gravity of the aeroengine and one of the front suspension points, and the distance L4 in the Y direction between the center of gravity of the aeroengine and the other front suspension point; Calculating the coordinate values of the center of gravity of the aeroengine in the X direction and the Y direction according to the tensile force data N1, the axial distance L, and the axial distance W1; After the rotation angle θ of the aeroengine is adjusted, defining the axial distance between the center of gravity of the aeroengine and the line connecting the two front suspension points as L5, and the axial distance between the center of gravity of the aeroengine and the line connecting the two rear suspension points as L6; Calculating the coordinate value of the center of gravity of the aeroengine in the Z direction according to the tensile force data N2, the rotation angle θ, and the axial distance L.

6. The method for measuring the mass distribution uniformity of an aero-engine according to claim 4, characterized in that: The calculation formula for the mass distribution uniformity δ of the aeroengine is as follows: 。 7. The method for measuring the mass distribution uniformity of an aero-engine according to claim 4, characterized in that: The positions of the aeroengine in the X direction and the Y direction are adjusted by the first direction adjusting mechanism; the rotation angle θ of the aeroengine is adjusted by the height adjusting assembly (15) of the rear stretching structure (7).

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