Horizontal measurement method for large-wingspan movable wing aircraft

Abstract

The invention provides a horizontal measurement method of a large-wingspan movable wing aircraft, which comprises the following steps of: establishing a coordinate system by taking a virtual coordinate on a tool as a reference, adjusting a basic platform and a supporting arc to be within an allowable deviation range, positioning a middle section of a product by using the supporting arc, measuring the middle section, judging whether the levelness of a mounting surface of the middle section reaches the standard or not, and adjusting. And sequentially assembling the rear section and the front section by taking the middle section as a standard of complete machine assembly, completing assembly and measurement of the fuselage, and adjusting each section of the fuselage in real time according to a measurement result. And then the wing is assembled, and measurement of the wingtip coordinate and the deflection angle is completed. The tool has the advantages that assembly and measurement are carried out on one tool, alternate station change of products between an assembly table and a measurement table is avoided, a machine body does not need to be rotated during measurement, measurement is completed in the assembly state, the assembly efficiency is guaranteed, and the product safety can be guaranteed.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft assembly measurement, and in particular relates to a level measurement method for a large-wingspan movable-wing aircraft. Background Art

[0002] Large-wingspan active-wing aircraft have the characteristics of large aspect ratio, light weight, and high aerodynamic shape accuracy. During the structural assembly process, it is necessary to perform horizontal measurement of the entire aircraft to ensure the aerodynamic requirements of the aircraft. The traditional measurement method for some missiles is the height gauge measurement method. With the measurement platform as the reference, after the missile body is leveled, the distance from the missile body and the wing measuring points to the platform is measured. Depending on the situation, the missile body needs to be rotated 90°, and the distance from the measuring points on the horizontal and vertical planes to the platform is measured respectively, so as to evaluate the coaxiality of the missile body and the assembly deviation of the wing. For aircraft, which are larger in size, the left and right wings of the middle section of the aircraft are usually used as the positioning reference, the fuselage is leveled, and the horizontal deviation of the measuring points at the front and rear sections of the aircraft is measured. Then, with the front end as the reference, the vertical deviation of the rear section and the vertical tail of the aircraft is measured to evaluate the assembly error of the aircraft.

[0003] For large wingspan movable wing aircraft, it is not convenient to rotate the fuselage to measure the horizontal measuring point, and the movable wing cannot be used as a positioning reference, which will introduce large errors. Therefore, the application of traditional measurement methods must inevitably design complex measurement tools and go through complex measurement steps to measure the product. Summary of the invention

[0004] In view of this, the present invention aims to provide a level measurement method for a large-wingspan movable-wing aircraft to solve at least one problem existing in the above-mentioned prior art.

[0005] To achieve the above object, the technical solution of the present invention is achieved as follows: A horizontal measurement method for a large-wingspan movable-wing aircraft is implemented by a measuring tool, the measuring tool comprises a laser tracker, a basic platform, a front adjustable support arc I, a front adjustable support arc II, a middle fixed support arc I, a middle fixed support arc II, a rear adjustable support arc I, a rear adjustable support arc II, a fuselage calibration point, a wing bracket and a wing calibration point, and the horizontal measurement method comprises the following steps: S1. Establish a common virtual coordinate system for products and measurements; S2. Measure the basic platform, the calibration points of the middle fixed arc support I and the calibration points of the middle fixed arc support II, level the basic platform in the virtual coordinate system, and adjust the middle fixed arc support I and the middle fixed arc support II to within the allowable deviation; S3, laser tracker measures the flatness of the middle section installation surface and locates the middle section; S4, measure multiple measuring points of the rear section, compare with theoretical values, adjust the measuring points of the rear section to within the allowable deviation, and connect the middle section and the rear section; S5. Measure multiple measuring points of the front section, compare with theoretical values, adjust the measuring points of the front section to within the allowable deviation, and connect the middle section and the front section; S6. Use a laser tracker to measure the fuselage measurement points and evaluate the coaxiality index; S7. Install the wing, measure the coordinates of the wing tip measuring points, measure the coordinates of the leading and trailing edge measuring points, and evaluate the wing torsion angle index; S8. Use a laser tracker to measure the physical shape, compare it with the theoretical model, and evaluate the shape deviation of the entire machine.

[0006] Furthermore, the laser tracker and the basic platform are both installed on the ground; a movable support arc and a fixed support arc are installed above the basic platform, and a fuselage and wings are installed above the movable support arc and the fixed support arc, and the fuselage includes a front section, a middle section and a rear section arranged in sequence.

[0007] Furthermore, the movable supporting arc includes a front adjustable supporting arc I, a front adjustable supporting arc II, a rear adjustable supporting arc I and a rear adjustable supporting arc II. The front adjustable supporting arc I and the front adjustable supporting arc II are both used to support the front section, and the rear adjustable supporting arc I and the rear adjustable supporting arc II are both used to support the rear section.

[0008] Furthermore, the fixed supporting arc includes a middle section fixed supporting arc I and a middle section fixed supporting arc II, and the middle section fixed supporting arc I and the middle section fixed supporting arc II are both used to support the middle section.

[0009] Furthermore, a number of fuselage calibration points are arranged on the basic platform, and the fuselage calibration points are distributed on the basic platform, the middle fixed support arc I and the middle fixed support arc II, and the fuselage calibration points are used to adjust the basic platform.

[0010] Furthermore, a wing bracket is provided at the bottom of the wing, and the wing is connected to the middle section; a wing calibration point is provided on one side of the wing bracket, and the wing calibration point is distributed on the extension seat of the basic platform, and the wingtip coordinates and the leading and trailing edge coordinates of the wing are measured through the wing calibration point.

[0011] Furthermore, the basic platform can be adjusted in three directions, XYZ.

[0012] Compared with the prior art, the level measurement method of a large-wingspan movable-wing aircraft described in the present invention has the following advantages: (1) The present invention discloses a method for measuring the level of a large-span movable-wing aircraft. The present invention proposes that assembly and measurement are performed on a set of tooling, thereby avoiding the product from having to be replaced between the assembly table and the measurement table. The fuselage does not need to be rotated during measurement, and the measurement can be completed in the assembled state, thereby ensuring both assembly efficiency and product safety.

[0013] (2) The horizontal measurement method of a large-wingspan movable-wing aircraft described in the present invention can measure the coordinates of the feature points on the real object through equivalent conversion, and at the same time, compare the theoretical features of the product with the real object to obtain the deviation between the theoretical contour of the product and the real object, and finally complete the coordinate measurement of the feature points of the product and the shape error analysis in the inertial coordinate system. The dual measurement of coordinate values ​​and shape errors is achieved by replacing the three-dimensional scanner with a laser tracker. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings: Figure 1 This is a flow chart of the measurement method according to an embodiment of the present invention; Figure 2 This is a schematic diagram of fuselage measurement according to an embodiment of the present invention; Figure 3 This is a schematic diagram of wing measurement according to an embodiment of the present invention.

[0015] Description of reference numerals: 1. Laser tracker; 2. Basic platform; 3. Front section adjustable support arc I; 4. Front section; 5. Front section adjustable support arc II; 6. Middle section fixed support arc I; 7. Middle section; 8. Middle section fixed support arc II; 9. Rear section adjustable support arc I; 10. Rear section; 11. Rear section adjustable support arc II; 12. Fuselage calibration point; 13. Wing; 14. Wing bracket; 15. Wing calibration point. DETAILED DESCRIPTION

[0016] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0017] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying 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 cannot be understood as limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0018] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0019] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0020] like Figures 1 to 3 As shown, a method for horizontal measurement of a large-wingspan movable-wing aircraft is implemented by a measuring tool, which includes a laser tracker 1, a basic platform 2, a front adjustable support arc I3, a front section 4, a front adjustable support arc II5, a middle fixed support arc I6, a middle section 7, a middle fixed support arc II8, a rear adjustable support arc I9, a rear section 10, a rear adjustable support arc II11, a fuselage calibration point 12, a wing 13, a wing bracket 14 and a wing calibration point 15. The measurement and assembly process is as follows: (1) Establish a common virtual coordinate system for products and measurements.

[0021] (2) Measure the basic platform 2, the middle fixed support arc I6 calibration point, and the middle fixed support arc II8 calibration point, level the basic platform 2 in the virtual coordinate system, and adjust the middle fixed support arc I6 and the middle fixed support arc II8 to within the allowable deviation.

[0022] (3) The laser tracker 1 measures the flatness of the mounting surface of the middle section 7 and positions the middle section 7.

[0023] (4) Measure the measuring points 3U, 4U, 3R (3L), and 4R (4L) of the rear section 10, compare them with the theoretical values, adjust the measuring points of the rear section 10 to within the allowable deviation, and connect the middle section 7 and the rear section 10.

[0024] (5) Measure the measuring points 1U, 2U, 1R (1L), and 2R (2L) of the front section 4, compare them with the theoretical values, adjust the measuring points of the front section 4 to within the allowable deviation, and connect the middle section 7 and the front section 4.

[0025] (6) Use laser tracker 1 to measure the fuselage measurement points and evaluate the coaxiality index.

[0026] (7) Install the wing 13, measure the coordinates of the wing tip measuring points 5L and 5R of the wing 13, measure the coordinates of the leading and trailing edge measuring points 6LF (6LB) and 6RF (6RB), and evaluate the torsion angle index of the wing 13.

[0027] (8) Use the laser tracker 1 to measure the physical shape, compare it with the theoretical model, and evaluate the shape deviation of the whole machine.

[0028] like Figure 2 As shown, the laser tracker 1 is supported on the ground, and the height of the laser emitter and the distance from the product are adjusted to ensure that the field of view of the laser tracker 1 can cover the entire machine range; the basic platform 2 is fixed on the ground, which can be adjusted in three directions, XYZ, and is equipped with movable support arcs (front adjustable support arc I3, front adjustable support arc II5, rear adjustable support arc I9, rear adjustable support arc II11) and fixed support arcs (middle fixed support arc I6, middle fixed support arc II8). The fuselage calibration points 12 are distributed on the basic platform 2, the middle fixed support arc I6 and the middle fixed support arc II8 to adjust the basic platform 2; after the middle section 7 is leveled, it is fixed on the middle fixed support arc I6 and the middle fixed support arc II8; the rear section 10 is placed on the rear adjustable support arc I9 and the rear adjustable support arc II11, and the measuring points are measured. After the rear section 10 is adjusted to meet the requirements, it is fixed to the middle section 7. Similarly, the front section 4 is placed on the front section adjustable support arc I3 and the front section adjustable support arc II5, the measuring points are measured, and the front section 4 is fixed to the middle section 7 after being adjusted to meet the requirements.

[0029] like Figure 3 As shown, the wing 13 is placed on the wing bracket 14 to connect the wing 13 and the middle section 7; the wing calibration points 15 are distributed on the extension seat of the basic platform 2, and the wing tip coordinates and the leading and trailing edge coordinates of the wing 13 are measured through the wing calibration points 15.

[0030] This method establishes a virtual reference, takes the cross section (middle section) of the fuselage and wing as the positioning reference to perform leveling in the X and Y directions, and uses a laser tracker to measure the fuselage and wing measurement points and the overall shape of the aircraft, and can obtain evaluation indicators such as coaxiality, torsion angle, wingtip deviation, and shape deviation. At the same time, assembly and measurement are carried out on a set of tooling, avoiding the alternating station of the product on the assembly table and the measuring table. The fuselage does not need to be rotated during measurement, and the measurement is completed in the assembly state, which ensures both assembly efficiency and product safety.

[0031] Example 1 This measuring tooling includes a laser tracker 1, a basic platform 2, an adjustable front arc I3, an adjustable front arc II5, a fixed middle arc I6, a fixed middle arc II8, an adjustable rear arc I9, an adjustable rear arc II11, a fuselage calibration point 12, a wing bracket 14, and a wing calibration point 15. In this embodiment, a coordinate system is established based on the virtual coordinates on the tooling, the basic platform 2 and the arc are adjusted to within the allowable deviation, the middle section 7 of the product is positioned with the arc, the middle section 7 is measured, and the horizontality of its installation surface is judged to be up to standard, and adjustments are made. With the middle section 7 as the reference for the assembly of the whole machine, the rear section 10 and the front section 4 are assembled in sequence, the assembly of the fuselage is completed and measured, and the various sections of the fuselage are adjusted in real time according to the measurement results. Then the wing 13 is assembled to complete the measurement of the wingtip coordinates and the deflection angle.

[0032] In this embodiment, the laser tracker 1 and the basic platform 2 are both installed on the ground; a movable support arc and a fixed support arc are installed above the basic platform 2, and a fuselage and wings 13 are installed above the movable support arc and the fixed support arc. The fuselage includes a front section 4, a middle section 7 and a rear section 10 which are arranged in sequence.

[0033] In this embodiment, the movable support arc includes a front adjustable support arc I3, a front adjustable support arc II5, a rear adjustable support arc I9 and a rear adjustable support arc II11. The front adjustable support arc I3 and the front adjustable support arc II5 are both used to support the front section 4, and the rear adjustable support arc I9 and the rear adjustable support arc II11 are both used to support the rear section 10.

[0034] In this embodiment, the fixed supporting arc includes a middle section fixed supporting arc I6 and a middle section fixed supporting arc II8, and the middle section fixed supporting arc I6 and the middle section fixed supporting arc II8 are both used to support the middle section 7.

[0035] In this embodiment, a plurality of fuselage calibration points 12 are also provided on the basic platform 2 . The fuselage calibration points 12 are distributed on the basic platform 2 , the middle fixed support arc I6 and the middle fixed support arc II8 . The fuselage calibration points 12 are used to adjust the basic platform 2 .

[0036] In this embodiment, a wing bracket 14 is further provided at the bottom of the wing 13, and the wing 13 is connected to the middle section 7; a wing calibration point 15 is further provided on one side of the wing bracket 14, and the wing calibration point 15 is distributed on the extension seat of the basic platform 2, and the wingtip coordinates and the leading and trailing edge coordinates of the wing 13 are measured through the wing calibration point 15.

[0037] The principle of this measurement method is: with the product coordinate system as a reference, a set of marking points is established on the assembly measurement tooling, a virtual coordinate system is constructed as the inertial coordinate system for measurement, and the origin of the virtual coordinate system on the tooling is coincident with the theoretical coordinate origin of the aircraft. Through equivalent transformation, the coordinates of the characteristic points on the physical object can be measured, and at the same time, the theoretical characteristics of the product can be compared with the physical object to obtain the deviation between the theoretical contour of the product and the physical object, and finally the coordinate measurement of the characteristic points of the product and the shape error analysis can be completed in the inertial coordinate system.

[0038] Advantages of the present invention: The present invention proposes that assembly and measurement are performed on a set of tooling, thereby avoiding the product from having to be replaced alternately between the assembly table and the measurement table. The body does not need to be rotated during measurement, and measurement can be completed in the assembly state, thereby ensuring both assembly efficiency and product safety.

[0039] The present invention can measure the coordinates of the feature points on the real object through equivalent conversion, and at the same time compare the theoretical features of the product with the real object to obtain the deviation between the theoretical contour of the product and the real object, and finally complete the coordinate measurement of the feature points of the product and the shape error analysis in the inertial coordinate system. The laser tracker is used to replace the three-dimensional scanner to achieve dual measurement of coordinate values ​​and shape errors.

[0040] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for measuring the level of a large-wingspan movable-wing aircraft, characterized in that: The horizontal measurement method is implemented by a measuring tool, which includes a laser tracker (1), a basic platform (2), a front adjustable support arc I (3), a front adjustable support arc II (5), a middle fixed support arc I (6), a middle fixed support arc II (8), a rear adjustable support arc I (9), a rear adjustable support arc II (11), a fuselage calibration point (12), a wing bracket (14) and a wing calibration point (15). The horizontal measurement method includes the following steps: S1. Establish a common virtual coordinate system for products and measurements; S2, measuring the basic platform (2), the middle fixed arc I (6) calibration point, and the middle fixed arc II (8) calibration point, leveling the basic platform (2) in the virtual coordinate system, and adjusting the middle fixed arc I (6) and the middle fixed arc II (8) to within the set deviation; S3, a laser tracker (1) measures the flatness of the mounting surface of the middle section (7) and positions the middle section (7); S4, measuring multiple measuring points of the rear section (10), comparing with theoretical values, adjusting the measuring points of the rear section (10) to within the allowable deviation, and connecting the middle section (7) and the rear section (10); S5, measuring multiple measuring points of the front section (4), comparing with theoretical values, adjusting the measuring points of the front section (4) to within the allowable deviation, and connecting the middle section (7) and the front section (4); S6. Use a laser tracker (1) to measure the measuring points on the fuselage and evaluate the coaxiality index; S7, installing the wing (13), measuring the coordinates of the wing tip measuring points of the wing (13), measuring the coordinates of the leading and trailing edge measuring points, and evaluating the torsion angle index of the wing (13); S8. Use a laser tracker (1) to measure the physical shape, compare it with the theoretical model, and evaluate the shape deviation of the whole machine.

2. The method for measuring the level of a large-wingspan movable-wing aircraft according to claim 1, characterized in that: The laser tracker (1) and the base platform (2) are both installed on the ground; a movable support arc and a fixed support arc are installed above the base platform (2); a fuselage and wings (13) are installed above the movable support arc and the fixed support arc; the fuselage comprises a front section (4), a middle section (7) and a rear section (10) which are arranged in sequence.

3. The method for measuring the level of a large-wingspan movable-wing aircraft according to claim 2, characterized in that: The movable supporting arc comprises a front adjustable supporting arc I (3), a front adjustable supporting arc II (5), a rear adjustable supporting arc I (9) and a rear adjustable supporting arc II (11); the front adjustable supporting arc I (3) and the front adjustable supporting arc II (5) are both used to support the front section (4); the rear adjustable supporting arc I (9) and the rear adjustable supporting arc II (11) are both used to support the rear section (10).

4. The method for measuring the level of a large-wingspan movable-wing aircraft according to claim 2, characterized in that: The fixed supporting arc comprises a middle section fixed supporting arc I (6) and a middle section fixed supporting arc II (8), and the middle section fixed supporting arc I (6) and the middle section fixed supporting arc II (8) are both used to support the middle section (7).

5. The method for measuring the level of a large-wingspan movable-wing aircraft according to claim 4, characterized in that: The basic platform (2) is also provided with a plurality of fuselage calibration points (12), which are distributed on the basic platform (2), the middle section fixed support arc I (6) and the middle section fixed support arc II (8), and the fuselage calibration points (12) are used to adjust the basic platform (2).

6. The method for measuring the level of a large-wingspan movable-wing aircraft according to claim 1, characterized in that: A wing bracket (14) is also provided at the bottom of the wing (13), and the wing (13) is connected to the middle section (7); a wing calibration point (15) is also provided on one side of the wing bracket (14), and the wing calibration point (15) is distributed on the extension seat of the basic platform (2), and the wing tip coordinates and the leading and trailing edge coordinates of the wing (13) are measured through the wing calibration point (15).

7. The method for measuring the level of a large-wingspan movable-wing aircraft according to claim 1, characterized in that: The basic platform (2) can be adjusted in three directions, XYZ.

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