A stress-free assembly coordination method for an aircraft hydraulic tubing system

Abstract

The present application relates to a kind of aircraft hydraulic pipeline system stress-free assembly coordination method, belong to the field of aeronautical manufacturing engineering / aircraft assembly.Firstly, the actual position of the body structure component and the pipe installation support is collected and solved by using single camera photogrammetry system, and is uniformly converted to the aircraft coordinate system, then the lofting posture of the pipe installation support is adjusted by using the measuring pen mode of double camera photogrammetry system, to ensure the accuracy of the installation position of the support.During the pipe pre-assembly process, the assembly micro-strain of the pipeline is dynamically monitored by using three-dimensional full-field strain measurement system, and the assembly stress is converted, the installation position of the pipeline support is adjusted in real time, to reduce the assembly stress of the pipeline, so as to achieve the stress-free assembly of the hydraulic pipeline system.By using the present application, the positioning accuracy of the hydraulic pipeline system is improved, the assembly stress of the pipe butt joint section is greatly reduced, and the stress-free installation coordination of the pipeline system is realized.

Description

Technical Field

[0001] This invention relates to a stress-free assembly coordination method for aircraft hydraulic piping systems, belonging to the field of aerospace manufacturing engineering / aircraft assembly. Background Technology

[0002] Among the many stages of aircraft manufacturing, the high-precision assembly of hydraulic conduits is extremely critical. During the assembly process, there are more or less instances of misaligned and forced assembly of aircraft hydraulic conduits. When the assembly pressure exceeds 90% of the aircraft's vibration and ripple, a pressure load will be generated. When the pressure load is too large, it will cause pressure pulsation or even resonance in the aircraft's hydraulic conduits, leading to malfunctions such as deformation, leakage, and cracking of the piping system.

[0003] To minimize forced assembly of pipeline systems and reduce assembly stress, the production site has implemented comprehensive digital forming from the pipeline processing and manufacturing stage, improving pipeline manufacturing precision. During the positioning and assembly of the pipeline system, auxiliary tooling and fixtures are used to improve processes and optimize pipeline assembly and positioning methods. However, the real-time detection and dynamic adjustment of assembly stress on pipeline mounting brackets and ports using digital methods is not yet widely applied.

[0004] Therefore, how to perform real-time detection and deviation analysis of the installation posture of pipeline mounting brackets, and accurately calculate adjustment values ​​for posture correction to ensure the assembly accuracy of pipelines is an urgent problem to be solved. In addition, stress detection of pipeline mating assembly is an important means to ensure stress-free assembly of the pipeline system. Further coupling of force and position detection information and real-time adjustment of the bracket's position are needed to ensure stress-free assembly of the hydraulic pipeline system. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention provides a stress-free assembly coordination method for aircraft hydraulic piping systems.

[0006] The technical solution of the present invention is as follows:

[0007] First, a single-camera photogrammetry system is used to collect and calculate the actual positions of the airframe structural components and duct mounting brackets, and then uniformly transform them into the aircraft coordinate system. Next, a dual-camera photogrammetry system in pen mode is used to lay out and adjust the orientation of the duct mounting brackets, ensuring the accuracy of the bracket installation position. During the duct pre-assembly process, a three-dimensional full-field strain measurement system is used to dynamically monitor the assembly micro-strain of the pipeline, and then the assembly stress is calculated. By fine-tuning the installation position of the pipeline brackets in real time, the assembly stress of the pipeline is reduced, thereby achieving stress-free assembly of the hydraulic pipeline system.

[0008] A stress-free assembly coordination method for an aircraft hydraulic piping system, comprising the following steps:

[0009] Step 1: In CATIA V5 software, import the digital models of assembly tooling, machine body structural components and conduit mounting brackets, extract the part surfaces, create the center coordinates of the reference holes and conduit mounting bracket mounting holes, and save them uniformly in igs format;

[0010] Step 2: Set up the photogrammetric target as required, affix photogrammetric markers and coded points, affix special measurement markers with center point marks on the conduit mounting bracket, and set up the measurement reference ruler at a suitable location;

[0011] Step 3: Use a single-camera photogrammetry system to photograph the airframe structure and calculate the three-dimensional spatial coordinates of the reference holes, reference planes, and guide tube mounting brackets. Import the three-dimensional spatial coordinate values ​​and the IGS model processed in Step 1 into Polyworks software to unify the aircraft coordinate system and equipment coordinate system, and complete the datum transformation and coordinate system fitting accuracy calibration.

[0012] Step 4: 1) In Polyworks software, extract the measured values ​​of the measurement markers (i.e., pose control points), compare them with the theoretical values, and solve for the pose adjustment values; 2) Import the values ​​after the single-camera photogrammetry system reference conversion into the dual-camera photogrammetry system to complete the orientation of the dual cameras; 3) Import the theoretical coordinate values ​​of the pose control points of the guide tube mounting bracket into the dual-camera system, use the measuring pen mode to lay out the bracket, adjust the pose of the bracket, and monitor the position coordinates of the measurement markers in real time until the installation deviation is within the allowable error range;

[0013] Step 5: Drill initial holes for the conduit mounting bracket and pre-connect using standard process parts;

[0014] Step 6: Spray speckle coating onto the catheter port, and use a digital speckle 3D full-field strain measurement system to dynamically detect micro-strain during the catheter assembly process, thereby calculating the assembly stress.

[0015] Step 7: When the assembly stress exceeds the design allowable value, return to step 4 to adjust the position of the conduit support. Within the range allowed by the technical documents, appropriately widen the installation error range of the conduit support to ensure the coordination and matching between the conduit assembly stress and the support positioning accuracy. Adjust the position of the support in real time to ensure stress-free assembly of the hydraulic pipeline system.

[0016] Step 8: Drill the conduit mounting bracket and the machine body structure to the final hole state, and connect them with standard parts to complete the piping system assembly.

[0017] The precise measurement of the three-dimensional spatial pose of the catheter mounting bracket is performed as follows:

[0018] 1) Determine the transformation datum between the aircraft coordinate system and the measuring equipment coordinate system.

[0019] If the machine body structure is positioned on the assembly fixture, the RP point and ERS point designed and manufactured by the fixture are selected as the reference. If the machine body structure is on the bracket under the frame or in the state of the whole machine, the holes and planar features of the machined parts with good rigidity and stability on the machine body structure are selected as the reference.

[0020] 2) Measurement and conversion of references

[0021] After selecting the reference, photogrammetric targets are laid out on the reference hole and reference plane. Photogrammetric markers and coded points are affixed to the machine body structure. Using a special tool, measurement markers with center point markings are affixed to the guide tube mounting bracket, ensuring that the center of the marker coincides with the center of the hole. Then, the measurement reference ruler is placed in a stable and suitable position. For a single-hole mounting bracket, the measurement marker is affixed to the center point of the single hole; for a double-hole mounting bracket, the measurement marker is affixed to the center points of the two holes respectively.

[0022] A single-camera photogrammetry system was used to photograph the product from multiple angles and directions, and the three-dimensional spatial coordinates of all marker points and measurement targets were calculated. The above three-dimensional spatial coordinate values ​​were imported into Polyworks software, and then the processed IGS digital models of the airframe structural components and duct mounting brackets were imported into the software. Using the transformation datum determined in 1) as the datum, the aircraft coordinate system and the equipment coordinate system were unified, and the datum transformation and coordinate system fitting accuracy calibration were completed.

[0023] 3) Design of a special tool for measuring marker points with center point markings

[0024] To ensure that the center of the measurement marker coincides with the center of the system mounting bracket hole and reduce measurement deviation, a special positioning tool was designed to assist in positioning the measurement marker with the center point mark.

[0025] Structural form: The marker positioning tool is composed of 3 layers. The bottom layer has a diameter of 8mm and a thickness of 3mm. The diameter of the middle layer needs to be matched according to the size and precision of the hole on the bracket. For example, if the size of the bracket hole is Φ5.2H9, then the dimensions of the tool are as follows: the bottom layer diameter is Φ8, the middle layer diameter is Φ5.2f9, and the thickness should be 0.2mm less than the bracket wall thickness. The top layer is a conical structure with a diameter of 1.0mm and a height of 1.5mm, which is the same as the diameter of the center hole of the marker point.

[0026] Instructions for use: Insert the marker positioning tool into the hole of the conduit mounting bracket from below, ensuring that the upper surface of the bottom structure of the tool fits tightly against the bracket parts. Attach the marker from above the conduit mounting bracket, fitting the center hole of the marker into the top conical hole of the positioning tool. After attaching the marker, remove the marker tool from below the conduit mounting bracket.

[0027] The specific operation for adjusting the position of the catheter fixing clamp is as follows:

[0028] After completing the aircraft coordinate system and the measurement equipment coordinate system, the coordinates of the measurement mark points on the guide tube mounting bracket are extracted in Polyworks software. The deviation between these coordinates and the theoretical coordinates of the attitude control points is analyzed to solve for the attitude adjustment value.

[0029] For a single-hole support, the pose control point is the measurement marker point; for a double-hole support, the pose control point is the center point of the line connecting the two measurement marker points.

[0030] 1) Method for solving the pose adjustment value of a single-hole support:

[0031] Let the theoretical coordinates of the center O of the measuring mark point of the single-hole mounting bracket be (X, Y, Z), and the measured coordinates be (X', Y', Z').

[0032] The adjustment value of the bracket in the X-axis direction is X'-X, the adjustment value in the Y-axis direction is Y'-Y, and the adjustment value in the Z-axis direction is Z'-Z.

[0033] If the difference is positive, move in the positive direction of the aircraft coordinate system; if the difference is negative, move in the negative direction of the aircraft coordinate system.

[0034] 2) Method for solving the pose adjustment value of the dual-hole bracket:

[0035] Let the measured coordinates of the center P1 of the measurement marker point of the double-hole mounting bracket be (X1', Y1', Z1'), the measured coordinates of the center P2 of the reference point be (X2', Y2', Z2'), and the theoretical coordinates of the pose control point P of the double-hole mounting bracket be (X0, Y0, Z0).

[0036] Measured coordinates of pose control point P:

[0037] X0'=(X1'+X2') / 2; Y0'=(Y1'+Y2') / 2; Z0'=(Z1'+Z2') / 2;

[0038] The adjustment value of the bracket in the X-axis direction is X0'-X0, the adjustment value in the Y-axis direction is Y0'-Y0, and the adjustment value in the Z-axis direction is Z0'-Z0.

[0039] If the difference is positive, move in the positive direction of the aircraft coordinate system; if the difference is negative, move in the negative direction of the aircraft coordinate system.

[0040] A dual-camera industrial photogrammetry system was used to measure the measurement markers of the conduit mounting bracket in real time. The values ​​converted from the single-camera photogrammetry system were imported into the dual-camera system to complete the orientation of the two cameras. The theoretical coordinates of the pose control points of the conduit mounting bracket were then imported into the dual-camera system. Lofting was performed using the measuring pen mode, and the positioning deviation of the bracket was analyzed. The bracket pose was adjusted while the coordinates of the marker points were checked until the installation deviation was within the allowable error range.

[0041] The dynamic detection of the assembly stress at the conduit port is as follows:

[0042] A speckle pattern is sprayed at the conduit port, and a digital speckle three-dimensional full-field strain measurement system is used to dynamically detect the micro-strain during the conduit assembly process, thereby calculating the assembly stress. If the assembly stress is greater than the design allowable value, the conduit support posture is adjusted. The assembly stress and spatial posture detection information are coupled, and the support position is adjusted in real time to ensure stress-free assembly of the hydraulic pipeline system.

[0043] The beneficial effects of this invention are:

[0044] This invention proposes a stress-free assembly coordination method for hydraulic pipeline systems. By applying this invention, the positioning accuracy of hydraulic pipeline systems is improved, the assembly stress of conduit docking sections is greatly reduced, and stress-free installation coordination of pipeline systems is achieved. Attached Figure Description

[0045] Figure 1 Dedicated measurement markers with center point markings;

[0046] Figure 2 Schematic diagram of the reference point location for the conduit mounting bracket;

[0047] Figure 3(a) Side view of a special positioning tool for measurement markers with center point markings;

[0048] Figure 3(b) 3D view of a special positioning tool for measuring marker points with center point marking;

[0049] Figure 4 Flowchart of stress-free assembly of aircraft hydraulic piping system. Detailed Implementation

[0050] Step 1: Measurement Analog Processing

[0051] In CATIA V5 software, create a new Product file and import the digital models of the assembly tooling, machine body structural components, and conduit mounting brackets. Switch to the generative shape design module, extract the part surfaces, and determine the reference holes and reference planes for coordinate system transformation based on the machine body's structural positioning. Create the center coordinates of the reference holes and the mounting holes of the conduit mounting brackets. For single-hole mounting brackets, the measurement marker point is located at the center point of the single hole; for double-hole mounting brackets, the measurement marker point is located at the center point of the line connecting the two holes. Save the data uniformly in igs format as theoretical data for subsequent pose adjustment and inspection.

[0052] Step 2: Measurement Preparation

[0053] Photogrammetric targets are laid out on the selected reference holes and planes. Photogrammetric markers and coded points are affixed to the machine body structure. Dedicated measurement markers with center point markings are affixed to the conduit mounting bracket. The measurement reference ruler is placed in a stable and suitable position. For single-hole mounting brackets, the markers are affixed to the center point of the single hole; for double-hole mounting brackets, the markers are affixed to the center point of the line connecting the two holes.

[0054] Step 3: Precise measurement of the three-dimensional spatial pose of the catheter mounting bracket

[0055] A single-camera photogrammetry system was used to capture images of the airframe structure from multiple angles and directions, ensuring that all measurement targets and markers on the reference holes, reference planes, and duct mounting brackets were acquired. The three-dimensional spatial coordinates of all markers and measurement targets were calculated using the single-camera photogrammetry system. These three-dimensional spatial coordinate values ​​were then imported into Polyworks software. Next, the processed IGS models of the airframe structural components and duct mounting brackets were imported into the software. Using the transformation datum determined in Step 1 as the reference, the aircraft coordinate system and equipment coordinate system were unified, completing the datum transformation and calibration of the coordinate system fitting accuracy.

[0056] Step 4: Adjusting the position of the catheter placement support

[0057] 1) Single-hole mounting bracket

[0058] In Polyworks software, the measured values ​​of the extracted measurement marker points (i.e., pose control points) are (13646.302, -1194.986, -1373.985). The theoretical coordinates (X, Y, Z) of the pose control point O of the single-hole mounting bracket, measured in the igs format measurement model, are (13645.999, -1195.586, -1373.284).

[0059] The adjustment value of the bracket in the X-axis direction is +0.303, the adjustment value in the Y-axis direction is +0.6, and the adjustment value in the Z-axis direction is -0.701.

[0060] Conclusion: The support was adjusted by 0.303mm in the positive X direction, 0.6mm in the positive Y direction, and 0.701mm in the negative Z direction.

[0061] 2) Double-hole mounting bracket

[0062] In Polyworks software, the measured values ​​of measurement marker point P1 are (14068.316, -266.582, -1779.532), and the measured values ​​of measurement marker point P2 are (14030.913, -267.002, -1777.188). Therefore, the measured coordinates of the support posture control points are:

[0063] X0'=(14068.316+14030.913) / 2=14050.115

[0064] Y0'=(-266.582+-267.002) / 2=-266.792

[0065] Z0'=(-1779.532+-1777.188) / 2=-1778.36

[0066] The theoretical coordinates (X0, Y0, Z0) of the pose control point P of the double-hole mounting bracket, measured in the IGS format measurement model, are (14049.279, -266.502, -1778.81).

[0067] The bracket's adjustment value is +0.836 in the X-axis direction, -0.29 in the Y-axis direction, and +0.45 in the Z-axis direction.

[0068] Conclusion: The support was adjusted by 0.836mm in the positive X direction, 0.29mm in the negative Y direction, and 0.45mm in the positive Z direction.

[0069] 3) Import the values ​​after datum transformation of the single-camera photogrammetry system into the dual-camera photogrammetry system to complete the orientation of the dual cameras and unify the measurement coordinate system of the dual cameras with the aircraft coordinate system.

[0070] 4) Then import the theoretical coordinates of the position control points of the catheter installation bracket into the dual-camera system, use the measuring pen mode to lay out the bracket, adjust the position of the bracket, and monitor the position coordinates of the measuring mark points in real time until the installation deviation is within the allowable error range.

[0071] Step 5: Pre-assembly of the piping system

[0072] Initial positioning holes are drilled together on the conduit mounting bracket and the machine body structure, and pre-connected using standard process parts.

[0073] Step 6: Dynamic detection of assembly stress at the conduit port

[0074] A speckle pattern is sprayed onto the catheter port, and a digital speckle three-dimensional full-field strain measurement system is used to dynamically detect the micro-strain during the catheter assembly process, thereby calculating the assembly stress.

[0075] Step 7: Flexible positioning adjustment of the catheter installation support

[0076] If the assembly stress is detected to be greater than the design allowable value, return to Step 4 to adjust the position of the conduit support. At this time, the allowable error range for the installation of the conduit support can be appropriately relaxed to ensure the coordination and matching between the conduit assembly stress and the support positioning accuracy. By adjusting the position of the support in real time, stress-free assembly of the hydraulic pipeline system can be ensured.

[0077] Step 8: Piping system assembly completed.

[0078] Drill the connection holes between the conduit mounting bracket and the machine body structure to the final hole state, and complete the assembly of the piping system by connecting standard parts.

Claims

1. A stress-free assembly coordination method for an aircraft hydraulic piping system, characterized in that, The steps are as follows: Step 1: In CATIA V5 software, import the digital models of assembly tooling, machine body structural components and conduit mounting brackets, extract the part surfaces, create the center coordinates of the reference holes and conduit mounting bracket mounting holes, and save them uniformly in igs format; Step 2: Set up the photogrammetric target as required, affix photogrammetric markers and coded points, affix special measurement markers with center point marks on the conduit mounting bracket, and set up the measurement reference ruler at a suitable location; Step 3: Use a single-camera photogrammetry system to photograph the airframe structure and calculate the three-dimensional spatial coordinates of the reference holes, reference planes, and guide tube mounting brackets; import the three-dimensional spatial coordinate values ​​and the IGS model processed in Step 1 into Polyworks software to unify the aircraft coordinate system and the equipment coordinate system, and complete the reference transformation and coordinate system fitting accuracy calibration. Step 4: 1) In Polyworks software, extract the measured values ​​of the measurement markers, compare them with the theoretical values, and solve for the pose adjustment values; 2) Import the values ​​converted from the single-camera photogrammetry system into the dual-camera photogrammetry system to complete the orientation of the dual cameras; 3) Import the theoretical coordinates of the pose control points of the catheter installation bracket into the dual-camera system, use the measuring pen mode to lay out the bracket, adjust the pose of the bracket, and monitor the position coordinates of the measuring mark points in real time until the installation deviation is within the allowable error range. Step 5: Drill initial holes for the conduit mounting bracket and pre-connect using standard process parts; Step 6: Spray speckle coating onto the catheter port, and use a digital speckle 3D full-field strain measurement system to dynamically detect micro-strain during catheter assembly, thereby calculating the assembly stress; Step 7: When the assembly stress exceeds the design allowable value, it is necessary to return to step 4 to adjust the position of the conduit support to ensure the coordination and matching between the conduit assembly stress and the support positioning accuracy. The position of the support is adjusted in real time to ensure stress-free assembly of the hydraulic pipeline system. Step 8: Drill the conduit mounting bracket and the machine body structure to the final hole state, and connect them with standard parts to complete the piping system assembly.

2. The stress-free assembly and coordination method for an aircraft hydraulic piping system as described in claim 1, characterized in that, The precise measurement of the three-dimensional spatial pose of the catheter mounting bracket is performed as follows: 2.1 Determine the transformation datum between the aircraft coordinate system and the measuring equipment coordinate system If the machine body structure is located on the assembly tooling, the RP point and ERS point designed and manufactured by the tooling are selected as the reference. If the machine body structure is on the bracket under the frame or in the state of the whole machine, the holes and planar features of the machined parts with good rigidity and stability on the machine body structure are selected as the reference. 2.2 Measurement and Conversion of Reference Standards After selecting the reference, photogrammetric targets are set up on the reference hole and reference plane. Photogrammetric markers and coded points are affixed to the machine body structure. Using a special tool for measuring markers with center point markings, the measuring markers with center point markings are affixed to the guide tube mounting bracket, ensuring that the center of the marker coincides with the center of the hole. Then, the measuring reference ruler is placed in a stable position. For a single-hole mounting bracket, the measuring marker is affixed to the center point of the single hole; for a double-hole mounting bracket, the measuring marker is affixed to the center points of the two holes respectively. A single-camera photogrammetry system was used to take pictures of the product from multiple angles and directions to calculate the three-dimensional spatial coordinates of all marker points and measurement targets. The three-dimensional spatial coordinate values ​​were then imported into Polyworks software. The processed IGS models of the airframe structural components and duct mounting brackets were then imported into the software. Using the transformation datum determined in section 2.1 as the datum, the aircraft coordinate system and the equipment coordinate system were unified to complete the datum transformation and coordinate system fitting accuracy calibration.

3. The stress-free assembly and coordination method for an aircraft hydraulic piping system as described in claim 2, characterized in that, The aforementioned special tool for measuring marker points with center point markings: The structure consists of three layers: the bottom layer has a diameter of 8mm and a thickness of 3mm; the diameter of the middle layer needs to be matched according to the size and precision of the holes on the bracket; and the top layer is a conical structure with the same diameter as the center hole of the marking point.

4. The stress-free assembly and coordination method for an aircraft hydraulic piping system as described in claim 2, characterized in that, The method of using the special tool for measuring marker points with center point marking is as follows: Insert the special positioning tool for marker points into the hole of the guide tube mounting bracket from below, ensuring that the upper surface of the bottom structure of the tool is in close contact with the bracket parts. Attach the marker point from above the guide tube mounting bracket, with the center hole of the marker point fitting into the top conical hole of the special positioning tool. After attaching the marker point, remove the special tool for marker points from below the guide tube mounting bracket.

5. The stress-free assembly and coordination method for an aircraft hydraulic piping system as described in claim 1, characterized in that, The specific operation for adjusting the position of the catheter fixing clamp is as follows: After completing the aircraft coordinate system and the measuring equipment coordinate system, the coordinates of the measuring mark points on the guide tube mounting bracket are extracted in Polyworks software. The deviation between these coordinates and the theoretical coordinates of the attitude control points is analyzed to solve for the attitude adjustment value. For a single-hole support, the pose control point is the measurement marker point; for a double-hole support, the pose control point is the center point of the line connecting the two measurement marker points. Method for solving the pose adjustment value of a single-hole support: Let the theoretical coordinates of the center O of the measuring mark point of the single-hole mounting bracket be (X, Y, Z), and the measured coordinates be (X', Y', Z'). The adjustment value of the bracket in the X-axis direction is X'-X, the adjustment value in the Y-axis direction is Y'-Y, and the adjustment value in the Z-axis direction is Z'-Z. If the difference is +, it moves in the positive direction of the aircraft coordinate system; if the difference is -, it moves in the negative direction of the aircraft coordinate system.

6. The stress-free assembly and coordination method for an aircraft hydraulic piping system as described in claim 5, characterized in that, The position adjustment of the aforementioned catheter fixing clamp is achieved using a method for determining the position adjustment value of a dual-hole support: Let the measured coordinates of the center P1 of the measurement marker point of the double-hole mounting bracket be (X1', Y1', Z1'), the measured coordinates of the center P2 of the reference point be (X2', Y2', Z2'), and the theoretical coordinates of the pose control point P of the double-hole mounting bracket be (X0, Y0, Z0). Measured coordinates of pose control point P: X0'=(X1'+X2') / 2; Y0'=(Y1'+Y2') / 2; Z0'=(Z1'+Z2') / 2; The adjustment value of the bracket in the X-axis direction is X0'-X0, the adjustment value in the Y-axis direction is Y0'-Y0, and the adjustment value in the Z-axis direction is Z0'-Z0. If the difference is positive, move in the positive direction of the aircraft coordinate system; if the difference is negative, move in the negative direction of the aircraft coordinate system.

7. The stress-free assembly and coordination method for an aircraft hydraulic piping system as described in claim 5, characterized in that, The orientation adjustment of the aforementioned conduit fixing clamp is achieved by using a dual-camera industrial photogrammetry system to measure the measurement markers of the conduit mounting bracket in real time. The values ​​converted from the single-camera photogrammetry system are imported into the dual-camera photogrammetry system to complete the orientation of the dual cameras. The theoretical coordinate values ​​of the orientation control points of the conduit mounting bracket are imported into the dual-camera system, and the layout is performed using the measuring pen mode. The positioning deviation of the bracket is analyzed, and the coordinates of the marker points are detected while adjusting the bracket orientation until the installation deviation is within the allowable error range.

8. The stress-free assembly and coordination method for an aircraft hydraulic piping system as described in claim 1, characterized in that, The dynamic detection of assembly stress at the conduit port is performed as follows: A speckle pattern is sprayed at the conduit port, and a digital speckle three-dimensional full-field strain measurement system is used to dynamically detect the micro-strain during the conduit assembly process, thereby calculating the assembly stress. If the assembly stress is greater than the design allowable value, the conduit support posture is adjusted. The assembly stress and spatial posture detection information are coupled, and the support position is adjusted in real time to ensure stress-free assembly of the hydraulic pipeline system.

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