Aircraft moving part guide pipe shape correcting method based on motion simulation technology

Abstract

The invention belongs to the field of aircraft guide pipe shape correction, and particularly relates to an aircraft moving part guide pipe shape correction method based on a motion simulation technology. Based on the digital virtual motion simulation technology, the shape correction method for the aircraft moving part guide pipe is innovatively provided, the shape correction work of the guide pipe can be accurately and reliably carried out at the fault position of the guide pipe, meanwhile, conformity inspection of guide pipe installation in the static state can be achieved, and movement gap inspection of the guide pipe in the moving state can also be achieved. The invention relates to an airplane moving part conduit shape correction system based on a motion simulation technology. The airplane moving part conduit shape correction system comprises a digital virtual motion simulation module, a digital pipeline design module and a data analysis and processing module. The digital virtual motion simulation module is used for realizing a motion simulation function, the digital pipeline design module is used for correcting the shape of the conduit, and the data analysis processing module ensures the state accuracy of the conduit after shape correction through a built-in calculation principle.

Description

Technical Field

[0001] The invention belongs to the field of aircraft duct correction, and in particular relates to a duct correction method for aircraft moving parts based on motion simulation technology. Background Art

[0002] The aircraft's motion mechanism includes the landing gear motion mechanism, the front wheel turning control mechanism, the flaperon and rudder control mechanism, the aircraft door retraction and extension control mechanism, etc. Some of the motion mechanism components have hydraulic system conduit parts, such as the main landing gear strut from the outer tube to the torque arm and the main starter wheel, which has a brake hydraulic system conduit; the front landing gear strut has a hydraulic system conduit for controlling the front wheel turning; the aircraft door actuator has a hydraulic system conduit for controlling the retraction and extension of the actuator, etc. These conduits play a very important role in realizing the main brake, emergency brake, front wheel turning and retraction and extension functions of the aircraft's moving parts. Therefore, it is very important to ensure the necessary clearance between the moving part conduit and the body structure and system components during the movement of the motion mechanism, so as to avoid the possibility of scratching the conduit, thereby affecting the safety performance of the aircraft.

[0003] At present, in the process of aircraft development, assembly and production, interference or insufficient clearance between the duct of the moving parts and the surrounding structures and system parts often occurs. In the past, the method of bending the duct was generally used to restore the moving parts to the neutral static position, and the duct on the faulty moving parts was corrected by bending tools or manual bending methods. When the moving mechanism was driven to move, the duct shape of the moving part duct after adjustment was checked to see if it met the clearance requirements. If not, the bending work was repeated. The duct bending method has quality effects on the wall thickness, surface depressions, scratches, etc. of the duct, affecting its working performance and service life. Another method is to make a solid sample of the duct, coordinate the duct manufacturing department to check the status of the faulty duct at the assembly site, use soft aluminum tubes to make a tube shape that can ensure the clearance requirements, and the duct manufacturing department manufactures an installed state duct according to the tube shape of the aluminum tube. When the assembly unit drives the moving mechanism to move, check whether the duct shape of the moving part meets the clearance requirements. If not, the duct shape needs to be adjusted repeatedly. The solid sample method has the disadvantages of long coordination cycle between different departments, high time cost, and low work efficiency. Summary of the invention

[0004] In view of the problems existing in the background technology, in order to realize the efficient and rapid adjustment of the shape of the duct of the moving parts of the aircraft, facilitate the production and manufacturing of the duct, and ensure the smooth commissioning of the moving parts in the aircraft assembly production stage, the present invention is based on theoretical digital modeling and provides a method for adjusting the shape of the duct of the moving parts of the aircraft based on motion simulation technology.

[0005] The technical solution of the present invention is as follows:

[0006] The invention includes a duct calibration system for aircraft moving parts based on motion simulation technology, which mainly includes a digital virtual motion simulation module, a digital pipeline design module and a data analysis and processing module. The digital virtual motion simulation module is used to construct a simulation model of aircraft moving parts and system parts on them, and perform simulation analysis, and generate simulation data information such as motion trajectory and envelope of moving parts according to actual needs. The digital pipeline design module is used to calibrate the duct on the moving parts and adjust the tube shape of the duct to ensure the clearance requirements between the duct on it and the aircraft structure and system parts during the operation of the aircraft moving parts. The data analysis and processing module is used to process the data information of the digital pipeline design module and the digital virtual motion simulation module, analyze the compliance of the duct installation parameters after calibration by the digital pipeline design module, and ensure stress-free installation of the duct; analyze and process the model information of the duct after calibration on the moving parts generated by the digital virtual motion simulation module, and analyze whether the matching clearance between the duct after calibration and the aircraft structure and system parts when the moving parts work with the moving parts meets the requirements of the technical documents.

[0007] When this method is used to calibrate the shape of the duct of the aircraft moving parts, the core part is the data analysis and processing module, and the processing process of this module is as follows:

[0008] (1) Obtain the model information of the duct and moving parts after calibration, and perform installation compliance check on the duct:

[0009] (1.1) Extract the calibration catheter installation parameter data package:

[0010] S={Δ1,Δ2,Δ3,L,R}

[0011] Δ1, Δ2, Δ3 are the connection error data packets of non-fitting, different axiality and skewness at both ends of the catheter and the middle fixings; L is the data packet of the straight section at both ends of the catheter and the middle fixings; R is the data packet of the bending radius of different curved parts on the catheter;

[0012] Δ1={α1,α2,……α i}

[0013] Δ2={β1,β2,……β i}

[0014] Δ3={γ1,γ2,……γ i}

[0015] L={l1,l2,……l i}

[0016] R={r1,r2,……r j}

[0017] where α i is the degree of non-fit at the i-th position; βi is the different axiality at the i-th position; γ i is the skewness at the i-th position; l i is the straight line segment at the ith position; r j is the bending radius at the jth position;

[0018] (1.2) Compare the compliance of the catheter installation parameters:

[0019] Q=f1(S,P)={Q1,Q2,Q3,Q4,Q5}

[0020] Where P = {α ′ ,β ′ ,γ ′ ,l ′ ,r ′} are the standard values ​​of non-fit, misalignment, skewness, straight line segment and bending radius specified in the technical documents. i The data package after the catheter installation parameter comparison, if Q i All satisfy Q i ≥1 (i=1~5), the calibrated conduit meets the installation compliance requirements, and the moving part conduit movement clearance inspection can be carried out. i If any of the following items do not meet the requirements, the conduit should be re-calibrated and the conduit installation compliance check should be performed.

[0021] (2) Obtain model information of the catheter working with the moving parts after calibration and check the clearance of the catheter movement:

[0022] (2.1) The spatial geometric model of the catheter motion envelope after correction is:

[0023] F(x,y,z)=0

[0024] (2.2) The overall spatial geometric model of the surrounding aircraft structure and system components is:

[0025] H(x,y,z)=0

[0026] (2.3) The clearance between the calibrated duct and the overall model of the aircraft structure and system components:

[0027] δ=f2(F(x,y,z)=0,H(x,y,z)=0)

[0028] (2.4) Compare the fit clearance δ with the requirements of the technical documents to determine whether the calibrated conduit meets the requirements:

[0029] k=f3(δ,m)

[0030] Where m is the clearance requirement for moving parts specified in the technical documents; k ≥ 1 indicates that the calibrated catheter meets the clearance requirement; 0 ≤ k < 1 indicates that the calibrated catheter does not meet the clearance requirement and needs to be recalibrated.

[0031] Beneficial effects of the present invention:

[0032] (1) Based on digital virtual motion simulation technology, the present invention innovatively proposes a method for calibrating the duct of an aircraft moving component, which can accurately and reliably calibrate the duct at the duct fault location, and can also realize both the compliance check of the duct installation under static conditions and the motion clearance check of the duct under motion conditions.

[0033] (2) The present invention relates to a duct calibration system for aircraft moving parts based on motion simulation technology, which mainly includes a digital virtual motion simulation module, a digital pipeline design module and a data analysis and processing module. The digital virtual motion simulation module is used to realize the motion simulation function, the digital pipeline design module is used for duct calibration, and the data analysis and processing module ensures the accuracy of the duct state after calibration through built-in calculation principles.

[0034] (3) The present invention provides a method for calibrating the shape of an aircraft moving component duct based on motion simulation technology, which realizes efficient and rapid calibration of the duct type when a matching failure occurs in the moving component duct, avoids damage to the duct caused by bending repair and the cycle of communication and coordination for actual samples, improves the calibration efficiency of the moving component duct, and can realize digital manufacturing of the duct after calibration. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 The figure is a schematic flow chart of the method for calibrating the shape of a duct of an aircraft moving component according to the present invention. DETAILED DESCRIPTION

[0036] See attached Figure 1 The specific implementation method of the aircraft moving parts duct correction method based on motion simulation technology is as follows:

[0037] S01: Condition analysis of aircraft moving parts

[0038] First, analyze the components of the motion mechanism where the moving parts are located, determine the driving components, transmission components and execution components, and analyze their driving methods, motion trajectories and motion targets. Secondly, analyze the connection methods between the components inside the motion mechanism to transmit motion, that is, determine the types of motion pairs between the components.

[0039] S02: Building a motion simulation model

[0040] According to the state analysis of the aircraft moving parts in step S01, a simulation model of the faulty motion mechanism is constructed through the digital virtual motion simulation module, and through the mechanism degree of freedom analysis function in the simulation module, it is determined that the constructed model has motion simulation capabilities (that is, the degree of freedom must satisfy DOF=0).

[0041] S03: Movement simulation to catheter fault location

[0042] According to the motion simulation model constructed in step S02, the model is simulated to a position where the duct of the moving component interferes with the aircraft structure and system components or the clearance is insufficient, and the model state of the moving component and the duct thereon is maintained at this position.

[0043] S04: Catheter shaping

[0044] S04.1: Switch the system to the digital pipeline design module, and adjust the faulty conduit in step S03 to a suitable pipe shape based on the theoretical digital model. Send the adjusted moving parts and their conduits to the data analysis and processing module.

[0045] S04.2: Switch the system to the data analysis and processing module to perform installation compliance check on the catheter.

[0046] S04.2.1: The data analysis and processing module automatically extracts the installation parameter data package of the shaped duct according to the shaped duct status imported from the digital pipeline design module:

[0047] S={Δ1,Δ2,Δ3,L,R}

[0048] Δ1, Δ2, Δ3 are the connection error data packets of non-fitting, different axiality and skewness at both ends of the catheter and the middle fixings; L is the data packet of the straight section at both ends of the catheter and the middle fixings; R is the data packet of the bending radius of different curved parts on the catheter;

[0049] Δ1={α1,α2,……α i}

[0050] Δ2={β1,β2,……β i}

[0051] Δ3={γ1,γ2,……γ i}

[0052] L={l1,l2,……l i}

[0053] R={r1,r2,……r j}

[0054] where α i is the degree of non-fit at the i-th position; βi is the different axiality at the i-th position; γ i is the skewness at the i-th position; l i is the straight line segment at the ith position; r j is the bending radius at the jth position;

[0055] S04.2.2: Compare the installation parameters of the conduit after the correction in step S04.2.1 with the installation parameter requirements in the technical documents to confirm the compliance of the installation status of the conduit after the correction.

[0056] Q=f1(S,P)={Q1,Q2,Q3,Q4,Q5}

[0057] Where P = {α ′ ,β ′ ,γ ′ ,l ′ ,r ′} are the standard values ​​of non-fit, misalignment, skewness, straight line segment and bending radius specified in the technical documents.

[0058] Q i The data package after the catheter installation parameter comparison, if Q i All satisfy Q i ≥1 (i=1~5), the calibrated conduit meets the installation compliance requirements, and the moving part conduit movement clearance inspection can be carried out. i If any of the items does not meet the requirements, switch to the digital piping design module to re-calibrate the conduit and then perform a conduit installation compliance check.

[0059] S05: Confirmation of the movement status of the catheter after calibration

[0060] S05.1: After the calibrated duct meets the duct installation compliance check in step S04, the system is switched to the digital virtual motion simulation module to perform motion simulation analysis of the duct of the moving component after calibration. The motion envelope space model of the calibrated duct is generated by the simulation result analysis function in the module.

[0061] S05.2: Send the motion envelope space model of the catheter after correction generated in step S05.1 to the data analysis and processing module for analytical processing to generate its geometric model.

[0062] F(x,y,z)=0

[0063] S05.3: Send the spatial model of the surrounding aircraft structure and system components to the data analysis and processing module for analytical processing to generate its geometric model.

[0064] H(x,y,z)=0

[0065] S05.4: Execute the data analysis function in the data analysis processing module to calculate the fitting clearance value between the two geometric models in steps S05.2 and S05.3.

[0066] δ=f2(F(x,y,z)=0,H(x,y,z)=0)

[0067] S05.5: Execute the data analysis function in the data analysis processing module, compare the fitting clearance δ in step S05.4 with the requirements of the technical documents, and determine whether the calibrated catheter meets the movement clearance requirements during the movement process.

[0068] k=f3(δ,m)

[0069] Where m is the clearance requirement for moving parts specified in the technical documents; k ≥ 1 indicates that the calibrated catheter meets the clearance requirement; 0 ≤ k < 1 indicates that the calibrated catheter does not meet the clearance requirement and it is necessary to switch to the digital pipeline design module to re-calibrate the catheter.

[0070] S06: Complete the calibration of the moving parts duct

[0071] When the calibrated moving part conduit meets the installation compliance check in step S04 and the movement clearance check in step S05, the calibrated moving part conduit is completed. The calibrated conduit is saved in the form of a digital model and sent to the conduit manufacturing department, and the manufacturing of the calibrated conduit can be completed by the CNC bending equipment.

Claims

1. A method for calibrating the shape of a duct of an aircraft moving part based on motion simulation technology, characterized in that: Here are the steps: S01: Condition analysis of aircraft moving parts First, analyze the components of the motion mechanism where the moving parts are located, determine the driving components, transmission components and execution components, and analyze their driving methods, motion trajectories and motion targets; secondly, analyze the connection methods between the components inside the motion mechanism to transmit motion, that is, determine the types of motion pairs between the components; S02: Building a motion simulation model According to the state analysis of the aircraft moving parts in step S01, a simulation model of the faulty moving mechanism is constructed through a digital virtual motion simulation module, and through the mechanism degree of freedom analysis function in the simulation module, it is determined that the constructed model has motion simulation capabilities; S03: Movement simulation to catheter fault location According to the motion simulation model constructed in step S02, the model is simulated to a position where the duct of the moving component interferes with the aircraft structure and system components or the clearance is insufficient, and the model state of the moving component and the duct thereon is maintained at this position; S04: Catheter shaping S04.1: Switch the system to the digital pipeline design module, and adjust the faulty conduit in step S03 to a suitable pipe shape based on the theoretical digital model; send the adjusted moving parts and their conduits to the data analysis and processing module; S04.2: Switch the system to the data analysis and processing module to perform installation compliance check on the catheter; S05: Confirmation of the movement status of the catheter after calibration; S06: Complete the calibration of the moving parts catheter.

2. The method for duct correction of aircraft moving parts based on motion simulation technology as claimed in claim 1, characterized in that: The degree of freedom in S02 must satisfy DOF=0.

3. The method for duct correction of aircraft moving parts based on motion simulation technology as claimed in claim 1 or 2, characterized in that: The specific operation of step S04.2 is as follows: S04.2.1: The data analysis and processing module automatically extracts the installation parameter data package of the shaped duct according to the shaped duct status imported from the digital pipeline design module: S={Δ1,Δ2,Δ3,L,R} Δ1, Δ2, Δ3 are the connection error data packets of non-fitting, different axiality and skewness at both ends of the catheter and the middle fixings; L is the data packet of the straight section at both ends of the catheter and the middle fixings; R is the data packet of the bending radius of different curved parts on the catheter; Δ1={α1,α2,……α i } Δ2={β1,β2,……β i } Δ3={γ1,γ2,……γ i } L＝{l1,l2,……l i} R＝{r1,r2,……r j} where α i is the degree of non-fit at the i-th position; β i is the different axiality at the i-th position; γ i is the skewness at the i-th position; l i is the straight line segment at the ith position; r j is the bending radius at the jth position; S04.2.2: Compare the installation parameters of the conduit after the calibration in step S04.2.1 with the installation parameter requirements in the technical documents to confirm the compliance of the installation status of the conduit after the calibration; Q=f1(S,P)={Q1,Q2,Q3,Q4,Q5} Where P = {α ′ ,β ′ ,γ ′ ,l ′ ,r ′ } are the standard values ​​of non-fit, misalignment, skewness, straight line segment and bending radius specified in the technical documents; Q i The data package after the catheter installation parameter comparison, if Q i All satisfy Q i ≥1 (i=1~5), the calibrated conduit meets the installation compliance requirements, and the moving part conduit movement clearance inspection can be carried out; if Q i If any of the items does not meet the requirements, switch to the digital piping design module to re-calibrate the conduit and then perform a conduit installation compliance check.

4. The method for duct correction of aircraft moving parts based on motion simulation technology as claimed in claim 1 or 2, characterized in that: The specific operations of step 5 are as follows: S05.1: After the calibrated duct meets the duct installation compliance check in step S04, the system is switched to the digital virtual motion simulation module to perform motion simulation analysis of the duct of the moving part after calibration. The motion envelope space model of the calibrated duct is generated by the simulation result analysis function in the module; S05.2: sending the motion envelope space model of the catheter after correction generated in step S05.1 to the data analysis and processing module for analytical processing to generate its geometric model; F(x,y,z)=0 S05.3: Send the spatial model of the surrounding aircraft structure and system components to the data analysis and processing module for analytical processing to generate its geometric model; H(x,y,z)=0 S05.4: Execute the data analysis function in the data analysis processing module to calculate the fitting clearance value between the two geometric models in steps S05.2 and S05.3; δ=f2(F(x,y,z)=0,H(x,y,z)=0) S05.5: Execute the data analysis function in the data analysis processing module, compare the fit clearance δ in step S05.4 with the requirements of the technical documents, and determine whether the calibrated catheter meets the requirements of the movement clearance during the movement process; k=f3(δ,m) Where m is the clearance requirement for moving parts specified in the technical documents; k ≥ 1 indicates that the calibrated catheter meets the clearance requirement; 0 ≤ k < 1 indicates that the calibrated catheter does not meet the clearance requirement and it is necessary to switch to the digital pipeline design module to re-calibrate the catheter.

5. The method for calibrating the shape of a duct of an aircraft moving component based on motion simulation technology as claimed in claim 3, characterized in that: The specific operations of step 5 are as follows: S05.1: After the calibrated duct meets the duct installation compliance check in step S04, the system is switched to the digital virtual motion simulation module to perform motion simulation analysis of the duct of the moving part after calibration. The motion envelope space model of the calibrated duct is generated by the simulation result analysis function in the module; S05.2: sending the motion envelope space model of the catheter after correction generated in step S05.1 to the data analysis and processing module for analytical processing to generate its geometric model; F(x,y,z)=0 S05.3: Send the spatial model of the surrounding aircraft structure and system components to the data analysis and processing module for analytical processing to generate its geometric model; H(x,y,z)=0 S05.4: Execute the data analysis function in the data analysis processing module to calculate the fitting clearance value between the two geometric models in steps S05.2 and S05.3; δ=f2(F(x,y,z)=0,H(x,y,z)=0) S05.5: Execute the data analysis function in the data analysis processing module, compare the fit clearance δ in step S05.4 with the requirements of the technical documents, and determine whether the calibrated catheter meets the requirements of the movement clearance during the movement process; k=f3(δ,m) Where m is the clearance requirement for moving parts specified in the technical documents; k ≥ 1 indicates that the calibrated catheter meets the clearance requirement; 0 ≤ k < 1 indicates that the calibrated catheter does not meet the clearance requirement and it is necessary to switch to the digital pipeline design module to re-calibrate the catheter.

6. The method for calibrating the shape of a duct of an aircraft moving component based on motion simulation technology as claimed in claim 1, 2 or 5, characterized in that: The specific operations of step 5 are as follows: When the calibrated moving component conduit meets the installation compliance check in step S04 and the movement clearance check in step S05, the calibrated moving component conduit is completed; the calibrated conduit is saved in the form of a digital model and sent to the conduit manufacturing department, and the manufacturing of the calibrated conduit can be completed by CNC bending equipment.

7. The method for calibrating the shape of a duct of an aircraft moving part based on motion simulation technology as claimed in claim 3, characterized in that: The specific operations of step 5 are as follows: When the calibrated moving component conduit meets the installation compliance check in step S04 and the movement clearance check in step S05, the calibrated moving component conduit is completed; the calibrated conduit is saved in the form of a digital model and sent to the conduit manufacturing department, and the manufacturing of the calibrated conduit can be completed by CNC bending equipment.

8. The method for calibrating the shape of a duct of an aircraft moving part based on motion simulation technology as claimed in claim 4, characterized in that: The specific operations of step 5 are as follows: When the calibrated moving component conduit meets the installation compliance check in step S04 and the movement clearance check in step S05, the calibrated moving component conduit is completed; the calibrated conduit is saved in the form of a digital model and sent to the conduit manufacturing department, and the manufacturing of the calibrated conduit can be completed by CNC bending equipment.

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