Helicopter complex damaged component residual life high-fidelity prediction method
By combining fatigue performance testing, real-time monitoring and numerical simulation calculation methods, the problem of high test costs and long cycles of damaged helicopter components is solved, and high-fidelity life prediction of complex damaged helicopter components is achieved, reducing the test costs and time.
Patent Information
- Application Number
- CN202411319911.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-20
- Publication Date
- 2025-01-03
AI Technical Summary
Fracture accidents caused by structural fatigue account for more than 80% during the flight of helicopters. The existing methods use tests to obtain the remaining performance of damaged structural parts for a long time and costly. A high-fidelity prediction method is required to reduce the cost and cycle of fatigue testing.
Using methods including fatigue performance testing platform, real-time monitoring platform and numerical simulation computing platform, the fatigue damage of damaged structural parts is monitored and calculated in real time through test fixtures, high-definition cameras and high-performance computers, and the prediction model is corrected based on the test data to predict the Remaining lifespan.
High-fidelity residual life prediction of damaged helicopter components is achieved, reducing the cost and cycle of fatigue tests, and improving the accuracy and efficiency of prediction.
Smart Images
Figure CN119249816A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of life prediction, and in particular to a high-fidelity prediction method for the remaining life of a complex damaged component of a helicopter. Background Art
[0002] As an indispensable means of transportation for modern military and civilian use, helicopters play an increasingly important role in life. They can be mainly used for tasks such as disaster relief, support, and material transportation. However, due to the complexity of helicopter structures and the many environmental factors they face during flight, higher requirements are placed on the safety performance of helicopters. According to statistics, more than 80% of fracture accidents during helicopter flight are caused by fatigue, and structural fatigue is one of the serious problems that helicopters need to face during flight. Usually, the most effective way to obtain the remaining performance of damaged helicopter structures is to conduct relevant tests. However, the tests require a lot of manpower and material resources, and the cycle is long and the test cost is high. Therefore, there is an urgent need for a high-fidelity prediction method for the remaining life of complex damaged components to solve the problem of the remaining life of damaged helicopter structures. Based on numerical simulation technology, this paper combines fatigue test data to make real-time corrections to the calculation model to solve the problems of high fatigue test cost and long test cycle of damaged helicopter structures. Summary of the invention
[0003] The purpose of the present invention is to provide a high-fidelity prediction method for the remaining life of complex damaged components of a helicopter, so as to solve the problems of high fatigue test cost and long test cycle of damaged helicopter structural parts.
[0004] To achieve this object, the present invention adopts the following technical solutions:
[0005] A high-fidelity prediction method for the remaining life of complex damaged components of helicopters, including a fatigue performance testing platform, a real-time monitoring platform and a numerical simulation calculation platform.
[0006] Specifically, the fatigue performance test platform includes a test fixture, a fatigue testing machine and damaged structural parts, which are used to test the remaining performance and life of the damaged structural parts;
[0007] Specifically, the real-time monitoring platform includes a high-definition camera for real-time monitoring and storage of the fatigue damage failure process of damaged structural parts;
[0008] Specifically, the numerical simulation computing platform includes a high-performance computer for simulating the fatigue failure of damaged structural parts and calculating and predicting their remaining life.
[0009] Preferably, during the calculation process, the numerical simulation calculation platform makes real-time corrections to the prediction model based on the data from the fatigue performance test platform and the real-time monitoring platform to achieve high-fidelity prediction of the remaining life of damaged structural parts.
[0010] As a preference, the method specifically comprises the following steps:
[0011] Step 1: Install the damaged structural parts on the test fixture, start the fatigue testing machine, and set the test parameters, including test plan, stress ratio, peak load, frequency, temperature, etc.
[0012] Step 2: Build a real-time monitoring platform, turn on a high-definition camera, set up the camera on one side of the damaged structural part, adjust the camera position until the damaged structural part is within the camera's field of view, and conduct real-time monitoring during the fatigue test;
[0013] Step 3: Establish a corresponding finite element model in a high-performance computer based on the clamping settings of the damaged structural parts during the fatigue test, set the corresponding material damage failure model according to the material type of the damaged structural parts, and start the calculation after completing the settings;
[0014] Step 4: Check the calculation results in real time during the calculation process, and make real-time corrections to the calculation model based on the data obtained from the real-time monitoring in step 2;
[0015] Step 5: After the calculation is completed, the numerical calculation results and fatigue test results are compared, and a statistical method is used to establish a correlation database model between process parameters and the state of damaged components and remaining life.
[0016] The beneficial effects of the present invention are:
[0017] The purpose of the present invention is to provide a high-fidelity prediction method for the remaining life of complex damaged components of a helicopter, so as to solve the problems of high fatigue test cost and long test cycle of damaged helicopter structural parts. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 It is a schematic diagram of a fatigue performance testing platform and a real-time monitoring platform provided by a specific embodiment of the present invention;
[0019] Figure 2 It is an operation flow chart of the life prediction method provided by a specific embodiment of the present invention.
[0020] In the figure:
[0021] 1. Test fixture; 2. Fatigue testing machine; 3. Damaged composite honeycomb sandwich structure; 4. High-definition camera. DETAILED DESCRIPTION
[0022] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.
[0023] In the description of the present invention, unless otherwise clearly specified and limited, the term "one side" should be understood in a broad sense, and a person skilled in the art can understand the specific meaning of the above term in the present invention according to specific circumstances.
[0024] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.
[0025] In the description of this embodiment, terms such as "up", "down", "right", etc., are used based on the orientations or positional relationships shown in the accompanying drawings and are only for the convenience of description and simplification of operation. They do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present invention.
[0026] The present invention provides a high-fidelity prediction method for the remaining life of a complex damaged component of a helicopter, which is characterized by comprising a fatigue performance testing platform, a real-time monitoring platform and a numerical simulation calculation platform.
[0027] Specifically, the fatigue performance test platform is as follows Figure 1 As shown, it includes a three-point bending test fixture 1, a fatigue testing machine 2 and a damaged composite honeycomb sandwich structure 3, which are used to test the remaining performance and life of the damaged composite honeycomb sandwich structure;
[0028] Specifically, the real-time monitoring platform includes a high-definition camera 4 for real-time monitoring and storage of the fatigue damage failure process of the damaged structural component;
[0029] Specifically, the numerical simulation computing platform includes a high-performance computer for simulating the fatigue failure of damaged structural parts and calculating and predicting their remaining life.
[0030] Specifically, during the calculation process, the numerical simulation computing platform makes real-time corrections to the prediction model based on the data from the fatigue performance testing platform and the real-time monitoring platform, thereby achieving high-fidelity prediction of the remaining life of damaged structural parts.
[0031] Specifically, the method comprises the following steps:
[0032] Step 1: Install the damaged composite honeycomb sandwich structure 3 on the three-point bending test fixture 1, start the fatigue testing machine 2, and set the test parameters, including the test plan, stress ratio, peak load, frequency, temperature, etc.;
[0033] Step 2: Build a real-time monitoring platform, turn on the high-definition camera 4, build the camera on the right side of the damaged structural member, adjust the camera position until the damaged structural member is within the camera's field of view, and perform real-time monitoring during the fatigue test;
[0034] Step 3: Based on the clamping setting of the damaged structural parts during the fatigue test, a three-point bending fatigue finite element model of the corresponding damaged composite honeycomb sandwich structural parts is established in a high-performance computer, and the ABAQUS finite element simulation software is imported. The UMAT subroutine is written based on the Hashin composite material failure criterion and the Roe fatigue damage evolution criterion, and the calculation is carried out after the setting is completed;
[0035] Step 4: Check the calculation results in real time during the calculation process, and make real-time corrections to the subroutine and finite element model based on the data obtained by real-time monitoring in step 2;
[0036] Step 5: After the calculation is completed, the numerical calculation results and fatigue test results are compared, and a statistical method is used to establish a correlation database model between fatigue test parameters and the damage size and remaining life of composite honeycomb sandwich structural components.
[0037] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. For those skilled in the art, various obvious changes, readjustments and substitutions can be made without departing from the protection scope of the present invention. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.
Claims
1. A high-fidelity prediction method for the remaining life of complex damaged components of helicopters, characterized in that: Including fatigue performance testing platform, real-time monitoring platform and numerical simulation computing platform, The fatigue performance testing platform comprises a test fixture (1), a fatigue testing machine (2) and a damaged structural part (3), and is used to test the remaining performance and life of the damaged structural part; The real-time monitoring platform comprises a high-definition camera (4) for real-time monitoring and storage of the fatigue damage failure process of the damaged structural component; The numerical simulation computing platform includes a high-performance computer for simulating fatigue failure of damaged structural parts and calculating and predicting their remaining life.
2. A high-fidelity prediction method for the remaining life of a complex damaged component of a helicopter according to claim 1, characterized in that: During the calculation process, the numerical simulation calculation platform makes real-time corrections to the prediction model based on the data from the fatigue performance test platform and the real-time monitoring platform, thereby achieving high-fidelity prediction of the remaining life of damaged structural parts.
3. A high-fidelity prediction method for the remaining life of a complex damaged component of a helicopter according to claim 1, characterized in that: The specific steps include: Step 1: Install the damaged structural component (3) on the test fixture (1), start the fatigue testing machine (2), and set the test parameters, including the test plan, stress ratio, peak load, frequency, temperature, etc.; Step 2: Set up a real-time monitoring platform, turn on a high-definition camera (4), set up the camera on one side of the damaged structural member, adjust the camera position until the damaged structural member is within the camera's field of view, and perform real-time monitoring during the fatigue test; Step 3: Establish a corresponding finite element model in a high-performance computer based on the clamping settings of the damaged structural parts during the fatigue test, set the corresponding material damage failure model according to the material type of the damaged structural parts, and start the calculation after completing the settings; Step 4: Check the calculation results in real time during the calculation process, and make real-time corrections to the calculation model based on the data obtained from the real-time monitoring in step 2; Step 5: After the calculation is completed, the numerical calculation results and fatigue test results are compared, and a statistical method is used to establish a correlation database model between process parameters and the state of damaged components and remaining life.