A method for adjusting the wing docking posture of an amphibious aircraft

Abstract

The invention relates to a method for adjusting the wing docking posture of an amphibious aircraft, wherein the amphibious aircraft comprises an upper wing with a left wing and a right wing docked. The method comprises: S1. installing process joints at three positions, namely, a front beam of 2 ribs of the wing, a rear beam of 2 ribs and a middle part of a wing rib about 3 / 4 of the wing length away from 0 rib, and propping up the wing with a numerical control positioner; S2. firstly setting measurement points on the wing, and measuring with a laser tracker to obtain the coordinate values ​​of each attitude measurement point of the left wing and the right wing in the aircraft coordinate system; S3. adjusting the numerical control positioner of the wing according to the obtained coordinate values, so that the deviation between the actual measured coordinate value of each measurement point and the theoretical coordinate value meets the set tolerance requirement; S4. measuring the actual measured coordinate value of each measurement point with a laser tracker, and then calculating each value in the wing attitude evaluation index, and when each value meets the wing docking posture adjustment requirement, the adjustment ends; otherwise, the adjustment and measurement are repeated until the requirements are met.

Description

Technical Field

[0001] The invention belongs to the technical field of special aircraft manufacturing, and in particular relates to a method for adjusting the wing docking posture of an amphibious aircraft. Background Art

[0002] At present, in the process of manufacturing aircraft at home and abroad, the docking sequence and method are different according to the different wing segmentation forms. Among them, for high-wing aircraft, the wing currently adopts a three-section form of central wing, left wing, and right wing, or a five-section form of central wing, left middle wing, left outer wing, right middle wing, and right outer wing. In these two forms, the central wing is generally docked with the fuselage first, and then the left wing and the right wing are docked with the central wing. When docking, the wing attitude is adjusted with the fuselage as a reference.

[0003] However, the applicant found that the wings of existing amphibious aircraft all adopt an upper wing form, and the upper wing form is a segmented form of a left wing and a right wing. During assembly, the left wing and the right wing need to be docked first, and then the subsequent wing and fuselage docking are carried out. As a result, there is no fuselage as a reference when the left wing and the right wing are docked, and it is difficult to ensure the accuracy of the docking posture of the left wing and the right wing, and it is impossible to make reasonable adjustments, and it is difficult to ensure that the wing posture meets the requirements when the entire aircraft is finally measured horizontally. Summary of the invention

[0004] In order to overcome the deficiencies of the prior art, the present invention aims to provide a method for adjusting the docking posture of an amphibious aircraft wing.

[0005] To solve the above problems, the technical solution adopted by the present invention is as follows:

[0006] The present invention provides a method for adjusting the docking posture of an amphibious aircraft wing. The amphibious aircraft comprises an upper wing with a left wing and a right wing docked. The method for adjusting the docking posture of the amphibious aircraft wing comprises the following steps:

[0007] S1. Support the wing: Both the left and right wings are supported by three points, and the three support points are respectively set at the front beam of the wing rib 2, the rear beam of the wing rib 2, and the middle of the wing rib about 3 / 4 of the wing length from the rib 0. At the same time, process joints are installed at the three support points of the wing, and the wing is propped up through the process joints using a CNC positioner;

[0008] S2. Measuring the wing attitude: firstly, setting measuring points at the butt joint between the left wing and the fuselage, the joint between the left wing and the pontoon, the horizontal measuring point of the left wing, the butt joint between the right wing and the fuselage, the joint between the right wing and the pontoon, and the horizontal measuring point of the right wing, and installing measuring joints at the measuring points, and using a laser tracker to measure, and obtaining the coordinate values ​​of each attitude measuring point of the left wing and the right wing in the aircraft coordinate system;

[0009] S3. Adjust the wing attitude: adjust the CNC positioners of the three support points of the left wing and the right wing according to the coordinate values ​​obtained in S2, so that the deviation between the measured coordinate value and the theoretical coordinate value of each measuring point meets the set tolerance requirement;

[0010] S4. Evaluate the wing docking posture: after the adjustment in S3 is completed, use a laser tracker to measure each horizontal measurement point of the aircraft to obtain the measured coordinate value; then calculate the Z-direction difference between the corresponding horizontal measurement points according to the corresponding relationship and calculation method between the horizontal measurement points specified in the aircraft design technical documents, and obtain the actual values ​​of the wing installation angle, right wing installation angle, installation angle symmetry, left wing dihedral angle, right wing dihedral angle, and dihedral angle symmetry; then determine whether the deviation between the actual values ​​of the left wing installation angle, right wing installation angle, installation angle symmetry, left wing dihedral angle, right wing dihedral angle, and dihedral angle symmetry and the theoretical values ​​specified in the design documents is within 1 / 5 of the tolerance of the corresponding indicators of the whole aircraft horizontal measurement. If so, the adjustment of the amphibious aircraft wing docking posture is completed; otherwise, repeat S3 and S4.

[0011] Further, the left wing installation angle in S4 is divided into a left wing root section installation angle, a left wing middle section installation angle, and a left wing tip section installation angle; the right wing installation angle is divided into a right wing root section installation angle, a right wing middle section installation angle, and a right wing tip section installation angle; the left wing dihedral angle is divided into a left wing inner section dihedral angle and a left wing outer section dihedral angle; and the right wing dihedral angle is divided into a right wing inner section dihedral angle and a right wing outer section dihedral angle.

[0012] Furthermore, the tolerance requirements of the measured coordinate values ​​and the theoretical coordinate values ​​of each measuring point in S3 are as follows: the X, Y, and Z tolerances of the measuring points at the butt joint between the left wing and the fuselage and the measuring points at the butt joint between the right wing and the fuselage are ±1.0, ±0.5, and ±0.5, respectively; the X, Y, and Z tolerances of the measuring points at the right wing and the pontoon connection joint and the measuring points at the right wing and the pontoon connection joint are ±1.0, ±3.0, and ±1.0, respectively; the X, Y, and Z tolerances of the right wing horizontal measuring point and the left wing horizontal measuring point are ±1.0, ±3.0, and ±1.5, respectively.

[0013] Furthermore, the CNC positioner in S1 can translate along the three directions of X, Y, and Z, and its accuracy meets the X, Y, and Z three-axis positioning accuracy of 0.1mm and the repeat positioning accuracy of 0.05mm.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] Through the above technical solution, the present invention can effectively adjust the docking posture of the wing of an amphibious aircraft, ensure that the wing posture meets the requirements when the whole aircraft is finally measured horizontally, and improve the quality of the amphibious aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic flow chart of the method for adjusting the wing docking posture of an amphibious aircraft according to the present invention;

[0017] Figure 2 It is a schematic diagram of a structure supporting a right wing in an embodiment of the method for adjusting the wing docking posture of an amphibious aircraft according to the present invention;

[0018] Figure 3 It is a schematic diagram of setting measurement points on the right wing in an embodiment of the amphibious aircraft wing docking posture adjustment method described in the present invention.

[0019] Explanation of the accompanying reference numerals: 1. measurement point of the first right wing and fuselage docking joint, 2. measurement point of the second right wing and fuselage docking joint, 3. measurement point of the first right wing and pontoon connection joint, 4. measurement point of the second right wing and pontoon connection joint, 5. horizontal measurement point of the first right wing root section, 6. horizontal measurement point of the second right wing root section, 7. horizontal measurement point of the first right wing middle section, 8. horizontal measurement point of the second right wing middle section, 9. horizontal measurement point of the first right wing tip section, 10. horizontal measurement point of the second right wing tip section. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0021] The method for adjusting the wing docking posture of an amphibious aircraft according to an embodiment of the present invention comprises an upper wing with a left wing and a right wing docked, that is, the upper wing is formed by a left wing and a right wing in two sections. Figure 1 As shown, the method for adjusting the wing docking posture of an amphibious aircraft comprises the following steps:

[0022] Step S1. Supporting the wing: Both the left wing and the right wing are supported at three points, and the three supporting points are respectively arranged at the front beam of the wing rib 2, the rear beam of the wing rib 2, and the middle of the wing rib about 3 / 4 of the wing length from the rib 0. At the same time, process joints are installed at the three supporting points of the wing, and the wing is propped up through the process joints using a CNC positioner; the CNC positioner can translate in the three directions of X, Y, and Z, and its accuracy meets the X, Y, and Z three-axis positioning accuracy of 0.1mm and the repeat positioning accuracy of 0.05mm.

[0023] For example Figure 2As shown, process joints are installed at A at the 2nd rib front beam, B at the 2nd rib rear beam, and C at the middle of the wing rib about 3 / 4 of the wing length from rib 0 on the lower surface of the right wing, and a CNC positioner D is set on the ground corresponding to the three locations, and the driving end of the CNC positioner D is connected to the corresponding process joints. Similarly, process joints are installed at A at the 2nd rib front beam, B at the 2nd rib rear beam, and the middle of the wing rib about 3 / 4 of the wing length from rib 0 on the lower surface of the left wing, and three CNC positioners are set on the ground and connected to the three process joints of the left wing respectively, and are symmetrically arranged with the supporting structure of the right wing.

[0024] Step S2. Measuring the wing attitude: firstly, setting measuring points at the butt joint between the left wing and the fuselage, the connection joint between the left wing and the pontoon, the horizontal measuring point of the left wing, the butt joint between the right wing and the fuselage, the connection joint between the right wing and the pontoon, and the horizontal measuring point of the right wing, and installing measuring joints at the measuring points, and using a laser tracker to measure, and obtaining the coordinate values ​​of each attitude measuring point of the left wing and the right wing in the aircraft coordinate system.

[0025] For example Figure 3 As shown, the lower surface of the right wing is provided with a first right wing and fuselage docking joint measurement point 1, a second right wing and fuselage docking joint measurement point 2, a first right wing and pontoon connection joint measurement point 3, a second right wing and pontoon connection joint measurement point 4, a first right wing root section horizontal measurement point 5, a second right wing root section horizontal measurement point 6, a first right wing middle section horizontal measurement point 7, a second right wing middle section horizontal measurement point 8, a first right wing tip section horizontal measurement point 9, and a second right wing tip section horizontal measurement point 10, for a total of 10 measurement points. Similarly, 10 test points are set on the lower surface of the left wing, including the first left wing and fuselage docking joint measurement point, the second left wing and fuselage docking joint measurement point, the first left wing and pontoon connection joint measurement point, the second left wing and pontoon connection joint measurement point, the first left wing root section horizontal measurement point, the second left wing root section horizontal measurement point, the first left wing middle section horizontal measurement point, the second left wing middle section horizontal measurement point, the first left wing tip section horizontal measurement point, and the second left wing tip section horizontal measurement point, which are symmetrically arranged with the 10 measurement points of the right wing.

[0026] Step S3. Adjust the wing attitude: According to the coordinate values ​​obtained in step S2, the numerical control positioners of the three supporting points of the left wing and the right wing are adjusted so that the deviation between the measured coordinate values ​​of each measuring point and the theoretical coordinate values ​​meets the set tolerance requirements. The tolerance requirements of the measured coordinate values ​​of each measuring point and the theoretical coordinate values ​​are as follows: the X, Y, and Z tolerances of the measuring points at the butt joint between the left wing and the fuselage and the measuring points at the butt joint between the right wing and the fuselage are ±1.0, ±0.5, and ±0.5, respectively; the X, Y, and Z tolerances of the measuring points at the right wing and the buoy connection joint and the measuring points at the right wing and the buoy connection joint are ±1.0, ±3.0, and ±1.0, respectively; the X, Y, and Z tolerances of the horizontal measuring points of the right wing and the horizontal measuring points of the left wing are ±1.0, ±3.0, and ±1.5, respectively. The tolerance requirements are used to confirm whether the wing attitude adjustment in step S3 is in place, and then determine whether to execute step S4.

[0027] Of course, the above tolerances of the present application can also be adaptively adjusted according to the specific positions of the measuring points and the deformation of the wings, so as to be suitable for the adjustment of the docking postures of wings of different specifications.

[0028] Step S4. Evaluate the wing docking posture: After the adjustment in S3 is completed, use a laser tracker to measure each horizontal measurement point of the aircraft to obtain the measured coordinate value; then according to the corresponding relationship and calculation method between the horizontal measurement points specified in the aircraft design technical document (that is, the difference between a certain point and a certain point specified in the design technical document, for example: the design technical document specifies that the wing installation angle is the Z-direction difference between point A and point B. This calculation method belongs to the prior art and will not be described in detail here.), calculate the Z-direction difference between the corresponding horizontal measurement points to obtain the wing attitude evaluation index, which includes the wing installation angle, the right wing installation angle, the installation angle symmetry, the left wing dihedral angle, the right wing dihedral angle, Then, it is determined whether the deviations of the left wing installation angle, the right wing installation angle, the installation angle symmetry, the left wing dihedral angle, the right wing dihedral angle, and the dihedral angle symmetry from the theoretical values ​​specified in the design documents are within 1 / 5 of the tolerance of the corresponding indicators of the whole aircraft horizontal measurement. If so, the adjustment of the wing docking posture of the amphibious aircraft is completed. Otherwise, steps S3 and S4 are repeated, that is, the wing attitude measurement points are repeatedly measured to calculate the various values ​​in the wing attitude evaluation index. When the various values ​​in the wing attitude evaluation index meet the requirements for the wing docking posture adjustment, the wing docking posture adjustment is completed; if not, the wing attitude adjustment and measurement process are repeated until it is met.

[0029] In one possible implementation, the left wing installation angle in S4 is divided into the left wing root section installation angle, the left wing middle section installation angle, and the left wing tip section installation angle; the right wing installation angle is divided into the right wing root section installation angle, the right wing middle section installation angle, and the right wing tip section installation angle; the left wing dihedral angle is divided into the left wing inner section dihedral angle and the left wing outer section dihedral angle; the right wing dihedral angle is divided into the right wing inner section dihedral angle and the right wing outer section dihedral angle, thereby further improving the accuracy of wing attitude adjustment.

[0030] The above-mentioned embodiments are only preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. A method for adjusting the wing docking posture of an amphibious aircraft, characterized in that: The amphibious aircraft comprises an upper wing with a left wing and a right wing docked; the method for adjusting the docking posture of the amphibious aircraft wings comprises the following steps: S1. Support the wing: Both the left and right wings are supported by three points, and the three support points are respectively set at the front beam of the wing rib 2, the rear beam of the wing rib 2, and the middle of the wing rib about 3 / 4 of the wing length from the rib 0. At the same time, process joints are installed at the three support points of the wing, and the wing is propped up through the process joints using a CNC positioner; S2. Measuring the wing attitude: firstly, setting measuring points at the butt joint between the left wing and the fuselage, the joint between the left wing and the pontoon, the horizontal measuring point of the left wing, the butt joint between the right wing and the fuselage, the joint between the right wing and the pontoon, and the horizontal measuring point of the right wing, and installing measuring joints at the measuring points, and using a laser tracker to measure, and obtaining the coordinate values ​​of each attitude measuring point of the left wing and the right wing in the aircraft coordinate system; S3. Adjust the wing attitude: adjust the CNC positioners of the three support points of the left wing and the right wing according to the coordinate values ​​obtained in S2, so that the deviation between the measured coordinate value and the theoretical coordinate value of each measuring point meets the set tolerance requirement; S4. Evaluate the wing docking posture: after the adjustment in S3 is completed, use a laser tracker to measure each horizontal measurement point of the aircraft to obtain the measured coordinate value; then calculate the Z-direction difference between the corresponding horizontal measurement points according to the corresponding relationship and calculation method between the horizontal measurement points specified in the aircraft design technical documents, and obtain the actual values ​​of the wing installation angle, right wing installation angle, installation angle symmetry, left wing dihedral angle, right wing dihedral angle, and dihedral angle symmetry; then determine whether the deviation between the actual values ​​of the left wing installation angle, right wing installation angle, installation angle symmetry, left wing dihedral angle, right wing dihedral angle, and dihedral angle symmetry and the theoretical values ​​specified in the design documents is within 1 / 5 of the tolerance of the corresponding indicators of the whole aircraft horizontal measurement. If so, the adjustment of the amphibious aircraft wing docking posture is completed; otherwise, repeat S3 and S4.

2. The method for adjusting the wing docking posture of an amphibious aircraft according to claim 1, characterized in that: The left wing installation angle in S4 is divided into the left wing root section installation angle, the left wing middle section installation angle, and the left wing tip section installation angle; the right wing installation angle is divided into the right wing root section installation angle, the right wing middle section installation angle, and the right wing tip section installation angle; the left wing dihedral angle is divided into the left wing inner section dihedral angle and the left wing outer section dihedral angle; the right wing dihedral angle is divided into the right wing inner section dihedral angle and the right wing outer section dihedral angle.

3. The method for adjusting the wing docking posture of an amphibious aircraft according to claim 1, characterized in that: The tolerance requirements between the measured coordinate values ​​and the theoretical coordinate values ​​of each measuring point in S3 are as follows: the X, Y, and Z tolerances of the measuring points at the butt joint between the left wing and the fuselage and the measuring points at the butt joint between the right wing and the fuselage are ±1.0mm, ±0.5mm, and ±0.5mm, respectively; the X, Y, and Z tolerances of the measuring points at the right wing and the pontoon connection joint and the measuring points at the right wing and the pontoon connection joint are ±1.0mm, ±3.0mm, and ±1.0mm, respectively; the X, Y, and Z tolerances of the right wing horizontal measuring point and the left wing horizontal measuring point are ±1.0mm, ±3.0mm, and ±1.5mm, respectively.

4. The method for adjusting the wing docking posture of an amphibious aircraft according to any one of claims 1 to 3, characterized in that: The CNC positioner in S1 can move in translation along the X, Y, and Z directions, and its accuracy meets the X, Y, and Z three-axis positioning accuracy of 0.1mm and the repeat positioning accuracy of 0.05mm.

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