Structure and method for measuring mass center of aero-engine

Abstract

The invention relates to the technical field of aero-gas turbine engines, and discloses an aero-engine mass center measuring structure and method, and the aero-engine mass center measuring structure comprises two front lifting points, two rear lifting points, lifting ropes, and tensiometers arranged on the lifting ropes. The measuring structure for measuring the weight and the mass center of the aero-engine can be obtained by refitting the four lifting ropes of the aero-engine lifting appliance and adding the tensiometer on each lifting rope, and the measuring structure is simple in refitting and easy to implement. The weight and the mass center of the aero-engine can be measured while the aero-engine is hoisted, and the implementation efficiency is high.

Description

Technical Field

[0001] The invention relates to the technical field of aviation gas turbine engines and discloses an aviation engine mass center measurement structure and method. Background Art

[0002] The weight and center of mass of aircraft engines have a significant impact on the balance and performance of aircraft. The weight and center of mass of each aircraft engine under development must be measured, and a weight and center of mass report must be provided when the aircraft engine is delivered to the aircraft party. Traditionally, the weight and center of mass measurement is performed using a precise center of mass measuring instrument, which requires frequent hoisting and takes a lot of man-hours, affecting the production progress of aircraft engines. Summary of the invention

[0003] The purpose of the present invention is to provide an aircraft engine mass center measurement structure and method, which can measure the weight and mass center of the aircraft engine while hoisting the aircraft engine, and has high implementation efficiency.

[0004] In order to achieve the above technical effects, the technical solution adopted by the present invention is: An aero-engine mass center measurement structure, comprising: Front hanging points, the number of which is two, and the two front hanging points are symmetrically arranged on both sides of the same axial section of the aircraft engine; A rear hanging point, wherein the rear hanging point and the front hanging point are respectively located on both sides of the same axial cross section of the aircraft engine, and the two rear hanging points and the two front hanging points are located on the same plane; A sling rope, wherein the number of the sling ropes is four, the four sling ropes are respectively used to fix one of the sling points, and the four sling ropes are arranged in a vertical direction, and are used to sling the aircraft engine through the front sling point and the rear sling point; A tension meter is provided on each of the suspension ropes for measuring the tension of the corresponding suspension rope when the suspension rope lifts the aircraft engine.

[0005] Furthermore, each of the lifting ropes is installed on a corresponding lifting point via a lifting hook.

[0006] Furthermore, a crossbeam for connecting the lifting mechanism and the two front lifting points is arranged above the two front lifting points, and a crossbeam for connecting the lifting mechanism and the two rear lifting points is arranged above the two rear lifting points.

[0007] In order to achieve the above technical effects, the present invention also provides a method for measuring the center of mass of an aircraft engine. The method is based on the above-mentioned center of mass measurement structure of the aircraft engine and comprises: Lifting the aircraft engine with lifting ropes, adjusting the lengths of the lifting ropes to keep the aircraft engine in a horizontal state, and calculating the weight of the aircraft engine based on the readings of the tension gauges on the lifting ropes when the aircraft engine is in a horizontal state; Take the intersection of the line connecting the two front suspension points and the axis of the aircraft engine as the origin, take the reverse direction of the axis of the aircraft engine as the positive direction of the X axis of the rectangular coordinate system, and the vertical upward direction as the positive direction of the Z axis. After determining the positive direction of the Y axis using the right-hand rule, establish a three-dimensional rectangular coordinate system; According to the readings of the two tension gauges at the rear suspension point when the aircraft engine is in a horizontal state, the weight of the aircraft engine, and the axial distance between the front suspension point and the rear suspension point, the axial distance from the center of mass of the aircraft engine to the line connecting the two front suspension points is analyzed and obtained; According to the readings of the tension gauges at a front hanging point and a rear hanging point distributed on both sides of the aircraft engine when the aircraft engine is in a horizontal state, the displacement of the center of mass along the Y-axis direction is analyzed and obtained; Keep the positions of the two front hanging points unchanged, adjust the lengths of the hanging ropes of the two rear hanging points, so that the axis of the aircraft engine is at a preset angle with the horizontal plane, and analyze and obtain the horizontal distance from the center of mass of the aircraft engine to the line connecting the two front hanging points after the aircraft engine is tilted at the preset angle and stabilized based on the readings of the tension meters of the two rear hanging points after the aircraft engine is tilted at the preset angle and stabilized; The coordinates of the center of mass of the aircraft engine are obtained by analysis based on the axial distance from the center of mass of the aircraft engine to the line connecting the two front hanging points, the offset of the center of mass in the Y direction, and the horizontal distance from the center of mass of the aircraft engine to the line connecting the two front hanging points after the aircraft engine is tilted at a preset angle and stabilized.

[0008] Furthermore, according to the axial distance from the center of mass of the aircraft engine to the line connecting the two front suspension points, the offset of the center of mass in the Y direction, and the horizontal distance from the center of mass of the aircraft engine to the line connecting the two front suspension points after the aircraft engine is tilted at a preset angle and stabilized, the center of mass coordinates of the aircraft engine are analyzed to be ( , , ),in is the axial distance from the center of mass of the aircraft engine to the line connecting the two front suspension points, is the distance between the two front suspension points, is the displacement of the center of mass of the aircraft engine along the Y axis, It is the horizontal distance from the center of mass of the aircraft engine after it is tilted to a preset angle and stabilized to the line connecting the two front suspension points. is the preset angle.

[0009] Furthermore, the aircraft engine weight ,in is the reading of the tension meter on the suspension rope at one of the front suspension points when the aircraft engine is in a horizontal state. is the reading of the tension meter on the suspension rope at another front suspension point when the aircraft engine is in a horizontal state. is the reading of the tension meter on the suspension rope at one of the rear suspension points when the aircraft engine is in a horizontal state. It is the reading of the tension meter on the suspension rope at another rear suspension point when the aircraft engine is in a horizontal state.

[0010] Furthermore, the axial distance from the center of mass of the aircraft engine to the line connecting the two front suspension points is ,in is the reading of the tension meter on the suspension rope at one of the rear suspension points when the aircraft engine is in a horizontal state. is the reading of the tension meter on the suspension rope at another rear suspension point when the aircraft engine is in a horizontal state. is the axial distance between the front hanging point and the rear hanging point, is the weight of the aircraft engine.

[0011] Furthermore, the displacement of the center of mass along the Y axis ,in is the reading of the tension meter on the suspension rope at one of the front suspension points when the aircraft engine is in a horizontal state. is the reading of the tension meter on the suspension rope at one of the rear suspension points when the aircraft engine is in a horizontal state. is the reading of the tension meter on the suspension rope at another rear suspension point when the aircraft engine is in a horizontal state, and The corresponding front lifting point and The corresponding rear suspension points are located on both sides of the aircraft engine. , is the distance between the two front suspension points, is the distance between the two rear suspension points, is the weight of the aircraft engine.

[0012] Furthermore, the horizontal distance from the center of mass of the aircraft engine after it is tilted at a preset angle and stabilized to the line connecting the two front suspension points , After the aircraft engine is tilted to a preset angle and stabilized, the reading of the tension meter on the suspension rope at one of the rear suspension points is After the aircraft engine is tilted to a preset angle and stabilized, the reading of the tension meter on the suspension rope at another rear suspension point is is the axial distance between the front hanging point and the rear hanging point, is the weight of the aircraft engine.

[0013] Compared with the prior art, the present invention has the following beneficial effects: by modifying the four suspension ropes of the aircraft engine hoist, and adding a tension meter to each suspension rope, a measurement structure for measuring the weight and center of mass of the aircraft engine can be obtained, and the modification of the measurement structure is simple and easy to implement. The weight and center of mass of the aircraft engine can be measured while the aircraft engine is hoisted, and the implementation efficiency is high. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1It is a structural schematic diagram of the aircraft engine in Embodiment 1 or 2 being hoisted in a horizontal state; Figure 2 A schematic diagram of the structure in which the aircraft engine is hoisted in an inclined state in Embodiment 1 or 2; Among them, 1. aircraft engine; 2. suspension rope; 3. tension meter; 4. beam. DETAILED DESCRIPTION

[0015] The present invention is further described in detail below in conjunction with the embodiments and drawings. However, it should not be understood that the scope of the above subject matter of the present invention is limited to the following embodiments, and all technologies realized based on the content of the present invention belong to the scope of the present invention.

[0016] Example 1 See also Figure 1 and Figure 2 , an aero-engine mass center measurement structure, comprising: Front suspension points, the number of which is two, and the two front suspension points are symmetrically arranged on both sides of the same axial cross section of the aircraft engine 1; A rear hanging point, wherein the rear hanging point and the front hanging point are respectively located on both sides of the same axial cross section of the aircraft engine 1, and the two rear hanging points and the two front hanging points are located on the same plane; A sling 2, wherein the number of the slings 2 is four, and the four slings 2 are respectively used to fix one of the sling points, and the four slings 2 are arranged in a vertical direction, and are used to sling the aircraft engine 1 through the front sling point and the rear sling point; A tension meter 3 is provided on each of the suspension ropes 2 , and is used to measure the tension of the corresponding suspension rope 2 when the suspension rope 2 lifts the aircraft engine 1 .

[0017] In this embodiment, the method steps of measuring the mass center of the aircraft engine 1 using the mass center measurement structure of the aircraft engine 1 include: Step 1: Use the lifting ropes 2 to lift the aircraft engine 1, adjust the length of each lifting rope 2, so that the aircraft engine 1 is in a horizontal state, and calculate the weight of the aircraft engine 1 according to the readings of the tension meters 3 on each lifting rope 2 when the aircraft engine 1 is in a horizontal state; Step 2: Take the intersection of the line connecting the two front suspension points and the axis of the aircraft engine 1 as the origin, take the reverse direction of the axis of the aircraft engine 1 as the positive direction of the X axis of the rectangular coordinate system, and the vertically upward direction as the positive direction of the Z axis. After determining the positive direction of the Y axis using the right-hand rule, establish a three-dimensional rectangular coordinate system; Step 3: Analyze and obtain the axial distance from the center of mass of the aircraft engine 1 to the line connecting the two front suspension points based on the readings of the two tension meters 3 at the rear suspension point when the aircraft engine 1 is in a horizontal state, the weight of the aircraft engine 1, and the axial distance between the front suspension point and the rear suspension point; Step 4: Analyze and obtain the displacement of the center of mass along the Y-axis direction according to the readings of the tension meters 3 at a front suspension point and a rear suspension point distributed on both sides of the aircraft engine 1 when the aircraft engine 1 is in a horizontal state; Step 5: Keep the positions of the two front suspension points unchanged, adjust the lengths of the suspension ropes 2 of the two rear suspension points, so that the axis of the aircraft engine 1 is at a preset angle with the horizontal plane, and analyze the readings of the tension meters 3 of the two rear suspension points after the aircraft engine 1 is tilted at the preset angle and stabilized to obtain the horizontal distance from the center of mass of the aircraft engine 1 to the line connecting the two front suspension points; Step 6: Analyze and obtain the coordinates of the center of mass of the aircraft engine 1 based on the axial distance from the center of mass of the aircraft engine 1 to the line connecting the two front suspension points, the offset of the center of mass in the Y direction, and the horizontal distance from the center of mass of the aircraft engine 1 to the line connecting the two front suspension points.

[0018] In this embodiment, by modifying the four lifting ropes 2 of the aircraft engine 1 hoist, and adding a tension meter 3 to each lifting rope 2, a measurement structure for measuring the weight and center of mass of the aircraft engine 1 can be obtained. The measurement structure is simple to modify and easy to implement. The weight and center of mass of the aircraft engine 1 can be measured while the aircraft engine 1 is being hoisted, and the implementation efficiency is high.

[0019] Example 2 See also Figure 1 and Figure 2 This embodiment takes the hoisting of a certain type of aircraft engine 1 as an example to explain in detail the method for measuring the center of mass of the aircraft engine 1 of the present invention. A and B are the two front hoisting points of the aircraft engine 1, and the line connecting A and B passes vertically through the axis of the aircraft engine 1; C and D are the two rear hoisting points of the aircraft engine 1, and the line connecting C and D passes vertically through the axis of the aircraft engine 1. A and C are located on the same side of the aircraft engine 1, and B and D are located on the other side of the aircraft engine 1; the four hoisting points must all be located in a horizontal plane passing through the axis of the aircraft engine 1. The axial distance between the two front hoisting points and the two rear hoisting points is , the distance between the A and B hanging points is , the distance between the C and D hanging points is The specific steps for measuring the centroid position are as follows: Step 1: Use the lifting ropes 2 to lift the aircraft engine 1, adjust the length of each lifting rope 2, so that the aircraft engine 1 is in a horizontal state, and calculate the weight of the aircraft engine 1 according to the readings of the tension meters 3 on each lifting rope 2 when the aircraft engine 1 is in a horizontal state; In this embodiment, the weight of the aircraft engine 1 is ,in is the reading of the tension meter 3 on the suspension rope 2 at the suspension point A when the aircraft engine 1 is in a horizontal state, is the reading of the tension meter 3 on the suspension rope 2 at the suspension point B when the aircraft engine 1 is in a horizontal state, is the reading of the tension meter 3 on the suspension rope 2 at the suspension point C when the aircraft engine 1 is in a horizontal state, It is the reading of the tension meter 3 on the suspension rope 2 at the suspension point D when the aircraft engine 1 is in a horizontal state.

[0020] Step 2: Take the intersection of the line connecting the two front suspension points and the axis of the aircraft engine 1 as the origin, take the reverse direction of the axis of the aircraft engine 1 as the positive direction of the X axis of the rectangular coordinate system, and the vertically upward direction as the positive direction of the Z axis. After determining the positive direction of the Y axis using the right-hand rule, establish a three-dimensional rectangular coordinate system; Step 3: Analyze and obtain the axial distance from the center of mass of the aircraft engine 1 to the line connecting the two front suspension points based on the readings of the two tension meters 3 at the rear suspension point when the aircraft engine 1 is in a horizontal state, the weight of the aircraft engine 1, and the axial distance between the front suspension point and the rear suspension point; In this embodiment, the axial distance from the center of mass of the aircraft engine 1 to the line connecting the two front suspension points is according to Obtained by analysis.

[0021] Step 4: Analyze and obtain the displacement of the center of mass along the Y-axis direction according to the readings of the tension meters 3 at a front suspension point and a rear suspension point distributed on both sides of the aircraft engine 1 when the aircraft engine 1 is in a horizontal state; In this embodiment, the displacement of the center of mass along the Y axis is according to , analysis obtained, .

[0022] Step 5: Keep the positions of the two front suspension points unchanged, and adjust the lengths of the suspension ropes 2 of the two rear suspension points so that the axis of the aircraft engine 1 is at a preset angle to the horizontal plane. , according to the readings of the two rear suspension point tension meters 3 after the aircraft engine 1 is tilted at a preset angle and stabilized, the horizontal distance from the center of mass of the aircraft engine 1 to the line connecting the two front suspension points is obtained; In this embodiment, after the aircraft engine 1 is tilted at a preset angle and stabilized, the horizontal distance from the center of mass of the aircraft engine 1 to the line connecting the two front suspension points is according to The analysis obtained The reading of the tension meter 3 on the suspension rope 2 at the suspension point C after the aircraft engine 1 is tilted to a preset angle and stabilized, The reading of the tension meter 3 on the suspension rope 2 at the suspension point D after the aircraft engine 1 is tilted to a preset angle and stabilized, is the axial distance between the front hanging point and the rear hanging point, The weight of one aircraft engine.

[0023] Step 6: Analyze and obtain the coordinates of the center of mass of the aircraft engine 1 based on the axial distance from the center of mass of the aircraft engine 1 to the line connecting the two front suspension points, the offset of the center of mass in the Y direction, and the horizontal distance from the center of mass of the aircraft engine 1 to the line connecting the two front suspension points.

[0024] In this embodiment, the coordinates of the center of mass of the aircraft engine 1 are obtained by analysis as follows: , , ),in is the axial distance from the center of mass of the aircraft engine 1 to the line connecting the two front suspension points, is the distance between the two front suspension points, is the displacement of the mass center of the aircraft engine 1 along the Y axis, It is the axial distance from the center of mass of the aircraft engine 1 after it is tilted at a preset angle and stabilized to the line connecting the two front suspension points.

[0025] In this embodiment, in order to facilitate lifting and keep the lifting rope 2 at each lifting point in the vertical direction, a crossbeam 4 for connecting the lifting mechanism and the two front lifting points can be set above the two front lifting points, and a crossbeam 4 for connecting the lifting mechanism and the two rear lifting points can also be set above the two rear lifting points.

[0026] In this embodiment, in order to facilitate the installation of the hanging point, a hook can be set on the hanging rope 2, and each of the hanging ropes 2 is installed on the corresponding hanging point through the hook. It should be noted that when the hook is set, the reading of the tension meter 3 should be subtracted from the weight of the hook at the corresponding hanging point, or the weight of the sling under the tension meter 3. However, when the hook is not used or the weight of the sling under the tension meter 3 is small, its influence on the reading of the tension meter 3 can be ignored.

[0027] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aero-engine mass center measurement structure, characterized in that: include: Front hanging points, the number of which is two, and the two front hanging points are symmetrically arranged on both sides of the same axial section of the aircraft engine; A rear hanging point, wherein the rear hanging point and the front hanging point are respectively located on both sides of the same axial cross section of the aircraft engine, and the two rear hanging points and the two front hanging points are located on the same plane; A sling rope, wherein the number of the sling ropes is four, the four sling ropes are respectively used to fix one of the sling points, and the four sling ropes are arranged in a vertical direction, and are used to sling the aircraft engine through the front sling point and the rear sling point; A tension meter is provided on each of the suspension ropes for measuring the tension of the corresponding suspension rope when the suspension rope lifts the aircraft engine.

2. The aero-engine mass center measurement structure according to claim 1, characterized in that: Each of the lifting ropes is installed on a corresponding lifting point through a lifting hook.

3. The aero-engine mass center measurement structure according to claim 1, characterized in that: A crossbeam for connecting the lifting mechanism and the two front lifting points is arranged above the two front lifting points, and a crossbeam for connecting the lifting mechanism and the two rear lifting points is arranged above the two rear lifting points.

4. A method for measuring the center of mass of an aircraft engine, the method being based on the structure for measuring the center of mass of an aircraft engine according to claim 1, characterized in that: include: Lifting the aircraft engine with lifting ropes, adjusting the lengths of the lifting ropes to keep the aircraft engine in a horizontal state, and calculating the weight of the aircraft engine based on the readings of the tension gauges on the lifting ropes when the aircraft engine is in a horizontal state; Take the intersection of the line connecting the two front suspension points and the axis of the aircraft engine as the origin, take the reverse direction of the axis of the aircraft engine as the positive direction of the X axis of the rectangular coordinate system, and the vertical upward direction as the positive direction of the Z axis. After determining the positive direction of the Y axis using the right-hand rule, establish a three-dimensional rectangular coordinate system; According to the readings of the two tension gauges at the rear suspension point when the aircraft engine is in a horizontal state, the weight of the aircraft engine, and the axial distance between the front suspension point and the rear suspension point, the axial distance from the center of mass of the aircraft engine to the line connecting the two front suspension points is analyzed and obtained; According to the readings of the tension gauges at a front hanging point and a rear hanging point distributed on both sides of the aircraft engine when the aircraft engine is in a horizontal state, the displacement of the center of mass along the Y-axis direction is analyzed and obtained; Keep the positions of the two front hanging points unchanged, adjust the lengths of the hanging ropes of the two rear hanging points, so that the axis of the aircraft engine is at a preset angle with the horizontal plane, and analyze and obtain the horizontal distance from the center of mass of the aircraft engine to the line connecting the two front hanging points after the aircraft engine is tilted at the preset angle and stabilized based on the readings of the tension meters of the two rear hanging points after the aircraft engine is tilted at the preset angle and stabilized; The coordinates of the center of mass of the aircraft engine are obtained by analysis based on the axial distance from the center of mass of the aircraft engine to the line connecting the two front hanging points, the offset of the center of mass in the Y direction, and the horizontal distance from the center of mass of the aircraft engine to the line connecting the two front hanging points after the aircraft engine is tilted at a preset angle and stabilized.

5. The method for measuring the center of mass of an aircraft engine according to claim 4, characterized in that: According to the axial distance from the center of mass of the aircraft engine to the line connecting the two front hanging points, the offset of the center of mass in the Y direction, and the horizontal distance from the center of mass of the aircraft engine to the line connecting the two front hanging points after the aircraft engine is tilted at a preset angle and stabilized, the coordinates of the center of mass of the aircraft engine are analyzed as follows: , , ),in is the axial distance from the center of mass of the aircraft engine to the line connecting the two front suspension points, is the distance between the two front suspension points, is the displacement of the center of mass of the aircraft engine along the Y axis, It is the horizontal distance from the center of mass of the aircraft engine after it is tilted to a preset angle and stabilized to the line connecting the two front suspension points. is the preset angle.

6. The method for measuring the center of mass of an aircraft engine according to claim 5, characterized in that: The aircraft engine weight ,in is the reading of the tension meter on the suspension rope at one of the front suspension points when the aircraft engine is in a horizontal state. is the reading of the tension meter on the suspension rope at another front suspension point when the aircraft engine is in a horizontal state. is the reading of the tension meter on the suspension rope at one of the rear suspension points when the aircraft engine is in a horizontal state. It is the reading of the tension meter on the suspension rope at another rear suspension point when the aircraft engine is in a horizontal state.

7. The method for measuring the center of mass of an aircraft engine according to claim 5, characterized in that: The axial distance from the center of mass of the aircraft engine to the line connecting the two front suspension points ,in is the reading of the tension meter on the suspension rope at one of the rear suspension points when the aircraft engine is in a horizontal state. is the reading of the tension meter on the suspension rope at another rear suspension point when the aircraft engine is in a horizontal state. is the axial distance between the front hanging point and the rear hanging point, is the weight of the aircraft engine.

8. The method for measuring the center of mass of an aircraft engine according to claim 5, characterized in that: The offset of the center of mass along the Y axis ,in is the reading of the tension meter on the suspension rope at one of the front suspension points when the aircraft engine is in a horizontal state. is the reading of the tension meter on the suspension rope at one of the rear suspension points when the aircraft engine is in a horizontal state. is the reading of the tension meter on the suspension rope at another rear suspension point when the aircraft engine is in a horizontal state, and The corresponding front lifting point and The corresponding rear suspension points are located on both sides of the aircraft engine. , is the distance between the two front suspension points, is the distance between the two rear suspension points, is the weight of the aircraft engine.

9. The method for measuring the center of mass of an aircraft engine according to claim 5, characterized in that: The horizontal distance from the center of mass of the aircraft engine to the line connecting the two front suspension points after the aircraft engine is tilted to a preset angle and stabilized , The reading of the tension gauge on the suspension rope at one of the rear suspension points after the aircraft engine is tilted to a preset angle and stabilized. After the aircraft engine is tilted to a preset angle and stabilized, the reading of the tension meter on the suspension rope at another rear suspension point is is the axial distance between the front hanging point and the rear hanging point, is the weight of the aircraft engine.

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