Real-time calculation method and device for residual life of undercarriage

Abstract

The invention provides a method and device for calculating the remaining life of an undercarriage in real time, and belongs to the technical field of fatigue life evaluation.The method comprises the steps that firstly, strain measurement data of undercarriage ground loads are decoupled, and ground three-way loads are obtained; calculating finite element stress of a key force bearing part of the undercarriage based on the ground three-way load; the finite element stress is decomposed to each part in the key force bearing part; based on the stress of each component, the equivalent stress of the component is calculated; according to the calculated equivalent stress, the number of cycles of applying the equivalent stress when the part is damaged is determined; counting the total flight duration of the current helicopter, and determining the damage degree of each part of the undercarriage of the current helicopter based on the total flight duration and the cycle index; based on the cycle index of the equivalent stress when each part is damaged and the damage degree of the corresponding part, the remaining life of the part is obtained; the minimum value of the remaining life of all the components serves as the remaining life of the landing gear; and the calculation is efficient, the practicability is high, and a more accurate real-time residual life analysis result can be obtained.

Description

Technical Field

[0001] The invention belongs to the technical field of fatigue life assessment, and in particular relates to a real-time calculation method and device for the remaining life of a landing gear. Background Art

[0002] The landing gear is an important load-bearing component that provides functions such as cushioning and ground maneuverability during aircraft take-off and landing and ground movement. It is used to transfer landing and ground operating loads and is usually designed to have the same lifespan as the aircraft body structure.

[0003] At present, the calculation of the remaining life of the landing gear fatigue life is given by calculation or experiment in the design stage. First, the load spectrum is edited according to the operating conditions, and then the stress is calculated and corrected. Combined with the structural SN characteristic curve, the cumulative damage theory is used to calculate the structural fatigue life.

[0004] Combined with the main remaining life calculation methods in current engineering applications, there are mainly the following limitations and shortcomings: the landing gear life prediction is only given in the design stage. When the product is subjected to large loads exceeding the design considerations during subsequent service, the landing gear fatigue life performance cannot be quickly updated; the landing gear life prediction is only given in the design stage. When the product is always subjected to loads lower than the design considerations during subsequent service, it is impossible to accurately propose measures to extend the landing gear life; most parts of the landing gear structure are only subject to some visual inspections during regular inspections, and there is no real-time prediction of the remaining life, and it is impossible to grasp the health status of the landing gear in real time, effectively and accurately. Summary of the invention

[0005] In order to solve the technical problems in the prior art that the fatigue life performance of the landing gear cannot be quickly updated, measures to extend the life of the landing gear cannot be accurately proposed, and the remaining life cannot be predicted in real time, the present invention provides a real-time remaining life calculation method and device for the landing gear, which has high calculation efficiency, strong feasibility, and can obtain more accurate real-time remaining life analysis results. The technical solution is as follows:

[0006] In a first aspect, a method for real-time calculation of the remaining life of a landing gear is provided, the method comprising:

[0007] Decouple the strain measurement data of the landing gear ground load to obtain the three-dimensional ground load;

[0008] Calculate the finite element stress of the key load-bearing parts of the landing gear based on the three-axis ground load;

[0009] Decompose the finite element stress into each component in the key load-bearing parts to obtain the stress of each component;

[0010] Based on the stress of each component, calculate the equivalent stress of the component;

[0011] Determine the number of cycles of applying the equivalent stress when the component is destroyed based on the calculated equivalent stress;

[0012] The total flight time of the current helicopter is counted, and the damage degree of each landing gear component of the sortie is determined based on the total flight time and the number of cycles;

[0013] Based on the number of cycles of equivalent stress when each component is destroyed and the damage degree of the corresponding component, the remaining life of the component is obtained;

[0014] The minimum value of the remaining life of all components is taken as the remaining life of the landing gear.

[0015] Optionally, the strain measurement data of the landing gear ground load is decoupled to obtain the ground three-axis load, including:

[0016] Obtaining strain measurement data of the landing gear ground load, the strain measurement data includes strain measurement data of strain gauge 201, strain gauge 202, and strain gauge 203, which are ε1, ε2, and ε3 respectively. Strain gauge 201 and strain gauge 202 are arranged on the outer wall of the landing gear axle, and the midpoint connection line of strain gauge 201 and strain gauge 202 is parallel to the length direction of the landing gear axle; strain gauge 203 and strain gauge 201 are located on the same radial section of the landing gear axle, and the angle between the two is 90°;

[0017] Based on ε1, ε2, ε3, the three-dimensional ground loads Px, Py, and Pz are calculated according to the following formula:

[0018]

[0019] Among them, the three-dimensional ground loads Px, Py, and Pz are the quantities to be solved, E represents the elastic modulus of the wheel axle material, A represents the cross-sectional area of ​​the wheel axle, W represents the bending section coefficient, b1 is the lever arm from the attachment position of the strain gauge 201 to the load application point, b2 is the lever arm from the attachment position of the strain gauge 202 to the load application point, and R is the distance from the load application point to the wheel axle axis.

[0020] Optionally, determining the number of cycles of applying the equivalent stress when the component is destroyed according to the calculated equivalent stress includes:

[0021] Step 1: Obtain the SN characteristic curve of each component. The SN characteristic curve records the corresponding relationship between the equivalent stress and the number of cycles of applying the equivalent stress when the component is damaged: the SN characteristic curve consists of 4 parts, the AB segment is a curve, and the BC, CD and DE segments are straight line segments.

[0022] The AB segment curve is determined according to the following formula:

[0023] Where N is the number of cycles when the part is damaged under the corresponding equivalent stress; Sa is the fatigue stress, σ -1 represents the average fatigue limit of the structure, A represents the ordinate value of the shape of the structural fatigue characteristic curve, and α represents the abscissa value of the shape of the structural fatigue characteristic curve;

[0024] Then, the intersection points (N1, S1), (N2, S2), (N3, S3) of the AB segment and the straight line segments BC, CD and DE are solved by the material parameters and structural parameters of the components to obtain the remaining part of the SN characteristic curve;

[0025] Step 2: When the equivalent stress of the component changes, directly find the number of cycles corresponding to the equivalent stress from the SN characteristic curve obtained in step 1.

[0026] Optionally, the damage degree of each landing gear component of the sortie is determined based on the total flight time, including:

[0027] The damage degree Dn of each component is calculated according to the following formula:

[0028] Among them, N is the number of cycles when the part is damaged under the corresponding equivalent stress, Hn represents the total flight time accumulated in the current sortie, and n represents the flight number of the current helicopter.

[0029] Optionally, based on the number of cycles of equivalent stress when each component is destroyed and the degree of damage of the corresponding component, the remaining life of the component is obtained, including:

[0030] The remaining life of the component after m flights is calculated according to the following formula:

[0031] Among them, Hm is the cumulative flight time of the mth flight, Hm+1 is the cumulative flight time of the m+1th flight, Dm+1 is the damage degree of the components in the m+1th flight, and Lm is the remaining life of the components after the mth flight.

[0032] In a second aspect, a device for real-time calculation of the remaining life of a landing gear is provided, comprising:

[0033] A determination module is used to decouple the strain measurement data of the landing gear ground load to obtain the ground three-dimensional load;

[0034] Compute module for:

[0035] Calculate the finite element stress of the key load-bearing parts of the landing gear based on the three-axis ground load;

[0036] Decompose the finite element stress into each component in the key load-bearing parts to obtain the stress of each component;

[0037] Based on the stress of each component, calculate the equivalent stress of the component;

[0038] Determine the number of cycles of applying the equivalent stress when the component is destroyed based on the calculated equivalent stress;

[0039] The total flight time of the current helicopter is counted, and the damage degree of each landing gear component of the sortie is determined based on the total flight time and the number of cycles;

[0040] Based on the number of cycles of equivalent stress when each component is destroyed and the damage degree of the corresponding component, the remaining life of the component is obtained;

[0041] The minimum value of the remaining life of all components is taken as the remaining life of the landing gear.

[0042] According to a third aspect, a real-time calculation device for the remaining life of a landing gear is provided, comprising a processor and a memory, wherein the processor is configured to execute instructions stored in the memory, and the processor implements any method described in the first aspect by executing the instructions.

[0043] According to a fourth aspect, a computer-readable storage medium is provided, wherein instructions are stored in the computer-readable storage medium. When the instructions are executed on a processing component of a computer, the processing component executes any of the methods described in the first aspect.

[0044] According to a fifth aspect, a computer program product comprising instructions is provided, and when the computer program product is run on a computer, the computer is caused to execute any method described in the first aspect.

[0045] The beneficial effects of the present invention are at least:

[0046] The present invention collects loads and inputs them into the digital twin of the landing gear. Through finite element stress calculation, structural SN characteristic calculation, damage calculation and real-time remaining life calculation, the real-time remaining life of the landing gear after each flight is obtained. The maintenance plan for the landing gear can be dynamically adjusted to improve the structural safety and maintenance cost of the landing gear. In the present invention, when the landing gear is subjected to a large load exceeding the design consideration during subsequent service, the fatigue life performance of the landing gear can be quickly updated; when the landing gear is always subjected to a load lower than the design consideration during subsequent service, measures to extend the life of the landing gear can be accurately proposed; most parts of the landing gear structure can be combined with visual inspection during regular inspections to predict the remaining life in real time, and the health status of the landing gear can be grasped in real time, effectively and accurately. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Figure 1 A flowchart of a real-time calculation method for the remaining life of a landing gear is shown;

[0048] Figure 2This is a schematic diagram of the landing gear life calculation architecture;

[0049] Figure 3 Schematic diagram of decoupling landing gear and ground loads for strain measurement;

[0050] Figure 4 Calculate stresses using finite element method for digital twin landing gear rocker assembly;

[0051] Figure 5 Schematic diagram of typical safety SN fatigue characteristic curve of the structure. DETAILED DESCRIPTION

[0052] The present invention is further described in detail below through specific implementation modes and drawings.

[0053] The present invention combines the landing gear design and the concept of digital twins, and proposes a real-time life calculation method for digital twin landing gears. This calculation method measures the landing and ground loads of each sortie through strain measurement, and then uses the real service load and working condition of the landing gear as input, and uses the finite element method to analyze the stress level of the landing gear, calculate the equivalent stress, and analyze the real-time remaining fatigue life. The present invention has high calculation efficiency and strong feasibility, and can obtain more accurate real-time remaining life analysis results.

[0054] The present invention, as Figure 1 and Figure 2 As shown, the main processes are:

[0055] 101. Load decoupling,

[0056] 102. Finite element stress calculation,

[0057] 103. Component stress extraction,

[0058] 104. Equivalent stress calculation,

[0059] 105. Calculation of the number of cycles of destruction,

[0060] 106. Calculation of total flight hours,

[0061] 107. Damage calculation for this flight:

[0062] 108. Real-time remaining life calculation,

[0063] The specific steps include:

[0064] Step 1: Load decoupling: Figure 3 Three point strains are measured at the corresponding positions of the axle 200, namely the first strain gauge 201, the second strain gauge 202, and the third strain gauge 203, and the strain values ​​are ε1, ε2, and ε3 respectively. When the load point is subjected to Px, Py, and Pz loads, the value and strain have the following relationship:

[0065]

[0066] Among them, ε1, ε2, ε3 are the measured values ​​of the three strain gauges, and the three-axis ground loads Px, Py, and Pz are the quantities to be solved. E represents the elastic modulus of the wheel axle material, A represents the cross-sectional area of ​​the wheel axle, W represents the bending section coefficient, b1 is the arm of the distance between the attachment position of the strain gauge 201 / 203 and the load application point, b2 is the arm of the distance between the attachment position of the strain gauge 202 and the load application point, and R is the distance from the load application point to the wheel axle axis.

[0067] Then, the expressions of Px, Py, Pz with respect to ε1, ε2, ε3 can be solved to realize the conversion from measured data to load decoupled data.

[0068]

[0069] Step 2: Finite element stress calculation: Px, Py, and Pz obtained by load decoupling are input into the finite element model in the landing gear digital twin as load boundary conditions, and submitted to the solver (ANSYS, Abaqus, Nastran, etc.) for static analysis calculation, such as Figure 4 shown.

[0070] Step 3: After the solution is completed, the results are post-processed to extract the stress of each component, and the stress of fatigue-sensitive areas / high-stress areas is extracted, such as the axle, various ears, weak sections of each component, connecting bolts, etc.

[0071] Step 4: Calculate the static stress and dynamic stress respectively according to the loading conditions, and use Goodman linear correction to calculate the equivalent stress of each component.

[0072] Step 5: Determine the number of cycles of applying the equivalent stress when the component is damaged based on the calculated equivalent stress. Specifically:

[0073] Step 51, obtain the SN characteristic curve of each component, the SN characteristic curve records the equivalent stress and the number of cycles of applying the equivalent stress when the component is destroyed: the SN characteristic curve consists of 4 parts (AB segment, BC segment, CD segment and DE segment), wherein the AB segment is a curve, and the BC, CD and DE segments are straight line segments. The AB segment curve is determined by the following formula.

[0074]

[0075] Where N is the number of cyclic loads when the part is damaged under the corresponding equivalent stress, 1e6 times; Sa is the fatigue stress, in MPa, σ -1 represents the average fatigue limit of the structure, A and α represent the shape coefficient of the structural fatigue characteristic curve, which are constants.

[0076] Then, through the relevant parameters such as material and structural form (such as curve shape parameters, structural fatigue limit, material yield strength, reduction coefficient, life dispersion coefficient, etc.), the intersection points (N1, S1), (N2, S2), (N3, S3) of the curve segment AB and the straight line segments BC, CD and DE are solved to obtain the complete SN characteristic curve, such as Figure 5 shown.

[0077] Step 52: Find the number of cycles corresponding to the equivalent stress from the SN characteristic curve.

[0078] The SN characteristic curve obtains the number of load cycles when the structural parts are damaged under the corresponding stress conditions according to the equivalent stress distribution of the components. Because the landing gear has different ground loads under different working conditions, the equivalent stresses borne by each component are also different. Through this curve, the material life N under different stress amplitudes can be quickly queried for subsequent damage calculations.

[0079] Step 6: Calculate the total flight hours: Calculate the total flight hours H. For the specific process, please refer to the relevant technology.

[0080] Step 7: Use fatigue damage accumulation theory and combine the historical data of the digital twin landing gear to calculate the damage degree D of each component in this flight.

[0081]

[0082] Wherein, N is the number of cycles corresponding to the equivalent stress Sa, Dn represents the damage assessment value of each landing gear component of the current sortie, and Hn represents the accumulated flight time of the current sortie.

[0083] Step 8. Calculate the remaining life: Calculate the remaining life of each component according to the following formula:

[0084]

[0085] Among them, Hm is the accumulated flight time of the mth flight, Hm+1 is the accumulated flight time of the m+1th flight, Dm+1 is the damage assessment value of each component of the m+1th flight, Lm is the remaining life of each component after the mth flight, and L101 is the remaining life of each component after the m+1th flight. Taking 100 flights as an example, the calculation method is shown in Table 1.

[0086] Table 1 Remaining life data after 100 flights

[0087]

[0088] Step 9: According to the calculated remaining life L of each target component, select the minimum value as the remaining life of the landing gear system.

[0089] For example, taking the axle as the calculation object, the implementation process is as follows:

[0090] 1. Select a landing gear axle, select structural steel material, the elastic modulus of the axle material is E = 2x10^5Mpa, the distance from the load point to the axle axis is R = 120mm, the inner diameter of the axle is d = 30mm, the outer diameter is D = 40mm, the arm of force b1 from the pasting position of strain gauge 201 / 203 to the load point is b1 = 50mm, the arm of force b2 from the pasting position of strain gauge 202 to the load point is b2 = 80mm, the cross-sectional area of ​​the axle is A = 2198mm^3, and the bending section coefficient is W = 34361mm^3.

[0091] The measured value of strain gauge 201 is ε1 = -336.5 με, the measured value of strain gauge 202 is ε2 = -511.1 με, and the measured value of strain gauge 203 is ε3 = -511.1 με.

[0092] Substituting ε1, ε2, ε3 into formula (2), the ground three-dimensional loads Px = 5000N, Py = 5000N, Pz = 20000N are obtained.

[0093] 2. Input the three-axis ground load Px=5000N, Py=5000N, Pz=20000N into the finite element software, perform stress analysis on the axle, extract the stress distribution in the fatigue sensitive area, and obtain the equivalent stress of 120Mpa.

[0094] 3. Substitute the equivalent stress into formula (3) to obtain the curve shape formula of segment AB. Solve the intersection points (N1, S1), (N2, S2), (N3, S3) of segment AB and straight line segments BC, CD and DE through relevant parameters such as material and structural form (such as curve shape parameters, structural fatigue limit, material yield strength, reduction coefficient, life dispersion coefficient, etc.) to obtain the complete SN characteristic curve.

[0095] 4. Draw the SN characteristic curve, the number of cycles corresponding to the equivalent stress of 120Mpa is N1=4x10^6.

[0096] 5. The flight time of the first flight of the landing gear axle is 1 hour, and the total flight hours are H1 = 1 hour. Substituting H1 and N1 into formula (4), the damage degree of the first flight axle is obtained as D1 = 2.5x10^(-7).

[0097] 6. Substituting D1 and H1 into formula (5), we can obtain the remaining life of the axle after the first flight: L1 = (1 / D1) - H1 = (2.5x10^6-1) hours.

[0098] 7. Obtain the strain gauge measurement data of the second flight, obtain the ground load solution, and obtain the equivalent stress of 200Mpa through finite element software.

[0099] 8. Query the SN characteristic curve and obtain the number of cycles N2=3x10^5 corresponding to the equivalent stress of 200Mpa.

[0100] 9. The flight time of the second flight of the landing gear axle is 2 hours, and the total flight hours are H2=1+2=3 hours. Substituting H2 and N2 into formula (4), the damage degree of the axle in the second flight is obtained as D2=1.1x10^(-6).

[0101] 10. Substituting H1, L1, D2, and H2 into formula (5), we can obtain the remaining life of the axle after the second flight: L2 = (6.7x10^5-3) hours.

[0102]

[0103] The advantages of the present invention are:

[0104] 1. The method of measuring strain and decoupling load is used to calculate landing and ground loads. It is highly versatile for landing gears of different configurations and has low strain measurement cost.

[0105] 2. No need to pre-compile load spectrum, the remaining life after each flight is calculated based on the actual historical load history of the landing gear, which is more accurate;

[0106] 3. Based on the remaining life results of the digital twin and combined with actual physical inspection, the landing gear structure safety assessment can be guided to improve the reference value;

[0107] 4. Based on the remaining life results of the digital twin, the landing gear maintenance plan can be dynamically adjusted to improve the structural safety and maintenance costs of the landing gear.

[0108] The key points of the present invention are as follows:

[0109] 1. A landing gear landing load measurement decoupling method is proposed to obtain the landing load as the input of the digital twin landing gear load boundary condition;

[0110] 2. Use finite element method to calculate the stress of each landing gear component under the real load, and use the linear Goodman curve correction principle to obtain fatigue stress;

[0111] 3. Use theoretical analytical methods to determine the structural SN characteristic equation and curve, and calculate the number of structural failure cycles under different fatigue stresses;

[0112] 4. Use the historical data of the digital twin landing gear to update the load spectrum, and actually generate an isolated load spectrum for each flight. The method does not need to simplify the load spectrum separately;

[0113] 5. The present invention adopts real-time iterative calculation of the remaining life after each flight, and can use the digital twin landing gear to monitor the remaining life status of the landing gear, which makes the calculation more efficient and the results more accurate.

[0114] The present invention also provides a real-time calculation device for the remaining life of a landing gear, comprising:

[0115] A determination module is used to decouple the strain measurement data of the landing gear ground load to obtain the ground three-dimensional load;

[0116] Compute module for:

[0117] Calculate the finite element stress of the key load-bearing parts of the landing gear based on the three-axis ground load;

[0118] Decompose the finite element stress into each component in the key load-bearing parts to obtain the stress of each component;

[0119] Based on the stress of each component, calculate the equivalent stress of the component;

[0120] Determine the number of cycles of applying the equivalent stress when the component is destroyed based on the calculated equivalent stress;

[0121] The total flight time of the current helicopter is counted, and the damage degree of each landing gear component of the sortie is determined based on the total flight time and the number of cycles;

[0122] Based on the number of cycles of equivalent stress when each component is destroyed and the damage degree of the corresponding component, the remaining life of the component is obtained;

[0123] The minimum value of the remaining life of all components is taken as the remaining life of the landing gear.

[0124] The specific execution process of each module in the present invention can refer to the specific process of the relevant steps of the above method, which will not be repeated here.

[0125] An embodiment of the present invention further provides a device for real-time calculation of the remaining life of a landing gear, comprising a processor and a memory, wherein the processor is configured to execute instructions stored in the memory, and the processor implements the method for real-time calculation of the remaining life of a landing gear described in the present invention by executing the instructions.

[0126] Another embodiment of the present invention provides a computer-readable storage medium, wherein the computer-readable storage medium stores instructions, and when the instructions are executed on a processing component of a computer, the processing component executes the real-time calculation method for the remaining life of a landing gear described in the present invention.

[0127] Yet another embodiment of the present invention provides a computer program product comprising instructions, which, when executed on a computer, enables the computer to execute the method for real-time calculation of the remaining life of a landing gear of the present invention.

[0128] The above only expresses the implementation mode of the present invention, and its description is relatively specific and detailed, but it cannot be understood as limiting the scope of the patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. In addition, the parts not detailed in the present invention are all conventional technologies.

Claims

1. A real-time calculation method for the remaining life of a landing gear, characterized in that: The method comprises: Decouple the strain measurement data of the landing gear ground load to obtain the three-dimensional ground load; Calculate the finite element stress of the key load-bearing parts of the landing gear based on the three-axis ground load; Decompose the finite element stress into each component in the key load-bearing parts to obtain the stress of each component; Based on the stress of each component, calculate the equivalent stress of the component; Determine the number of cycles of applying the equivalent stress when the component is destroyed based on the calculated equivalent stress; The total flight time of the current helicopter is counted, and the damage degree of each landing gear component of the sortie is determined based on the total flight time and the number of cycles; Based on the number of cycles of equivalent stress when each component is destroyed and the degree of damage of the corresponding component, the remaining life of the component is obtained; The minimum value of the remaining life of all components is taken as the remaining life of the landing gear.

2. The method according to claim 1, characterized in that Decouple the strain measurement data of the landing gear ground load to obtain the three-dimensional ground load, including: Acquiring strain measurement data of a landing gear ground load, the strain measurement data comprising strain measurement data of a first strain gauge (201), a second strain gauge (202), and a third strain gauge (203), which are ε1, ε2, and ε3 respectively, wherein the first strain gauge (201) and the second strain gauge (202) are arranged on the outer wall of the landing gear axle, and a midpoint connection line of the first strain gauge (201) and the second strain gauge (202) is parallel to the length direction of the landing gear axle; the third strain gauge (203) and the first strain gauge (201) are located on the same radial cross section of the landing gear axle, and an angle between the third strain gauge (203) and the first strain gauge (201) is 90°; Based on ε1, ε2, ε3, the three-dimensional ground loads Px, Py, and Pz are calculated according to the following formula: Among them, the three-dimensional ground loads Px, Py, and Pz are the quantities to be solved, E represents the elastic modulus of the wheel axle material, A represents the cross-sectional area of ​​the wheel axle, W represents the bending section coefficient, b1 is the force arm from the first strain gauge (201) pasting position to the load application point, b2 is the force arm from the second strain gauge (202) pasting position to the load application point, and R is the distance from the load application point to the wheel axle axis.

3. The method according to claim 1, characterized in that The number of cycles to apply the equivalent stress when the component is destroyed is determined based on the calculated equivalent stress, including: Step 1: Obtain the SN characteristic curve of each component. The SN characteristic curve records the corresponding relationship between the equivalent stress and the number of cycles of applying the equivalent stress when the component is damaged: the SN characteristic curve consists of 4 parts, the AB segment is a curve, and the BC, CD and DE segments are straight line segments. The AB segment curve is determined according to the following formula: Where N is the number of cycles when the part is damaged under the corresponding equivalent stress; Sa is the fatigue stress, σ -1 represents the average fatigue limit of the structure, A represents the ordinate value of the shape of the structural fatigue characteristic curve, and α represents the abscissa value of the shape of the structural fatigue characteristic curve; Then, the intersection points (N1, S1), (N2, S2), (N3, S3) of the AB segment and the straight line segments BC, CD and DE are solved by the material parameters and structural parameters of the components to obtain the remaining part of the SN characteristic curve; Step 2: When the equivalent stress of the component changes, directly find the number of cycles corresponding to the equivalent stress from the SN characteristic curve obtained in step 1.

4. The method according to claim 1, characterized in that Determine the damage degree of each landing gear component based on the total flight time, including: The damage degree Dn of each component is calculated according to the following formula: Among them, N is the number of cycles when the part is damaged under the corresponding equivalent stress, Hn represents the total flight time accumulated in the current sortie, and n represents the flight number of the current helicopter.

5. The method according to claim 1, characterized in that Based on the number of cycles of equivalent stress when each component is destroyed and the degree of damage of the corresponding component, the remaining life of the component is obtained, including: The remaining life of the component after m flights is calculated according to the following formula: Among them, Hm is the cumulative flight time of the mth flight, Hm+1 is the cumulative flight time of the m+1th flight, Dm+1 is the damage degree of the components in the m+1th flight, and Lm is the remaining life of the components after the mth flight.

6. A real-time calculation device for the remaining life of a landing gear, characterized in that: include: A determination module is used to decouple the strain measurement data of the landing gear ground load to obtain the ground three-dimensional load; Compute module for: Calculate the finite element stress of the key load-bearing parts of the landing gear based on the three-axis ground load; Decompose the finite element stress into each component in the key load-bearing parts to obtain the stress of each component; Based on the stress of each component, calculate the equivalent stress of the component; Determine the number of cycles of applying the equivalent stress when the component is destroyed based on the calculated equivalent stress; The total flight time of the current helicopter is counted, and the damage degree of each landing gear component of the sortie is determined based on the total flight time and the number of cycles; Based on the number of cycles of equivalent stress when each component is destroyed and the degree of damage of the corresponding component, the remaining life of the component is obtained; The minimum value of the remaining life of all components is taken as the remaining life of the landing gear.

7. A real-time calculation device for the remaining life of a landing gear, characterized in that: The invention comprises a processor and a memory, wherein the processor is configured to execute instructions stored in the memory, and the processor implements the real-time calculation method for the remaining life of the landing gear as claimed in any one of claims 1 to 5 by executing the instructions.

8. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores instructions, and when the instructions are executed on a processing component of a computer, the processing component executes the real-time calculation method for the remaining life of a landing gear as claimed in any one of claims 1 to 5.

9. A computer program product comprising instructions, characterized in that When the computer program product is run on a computer, the computer is enabled to execute the real-time calculation method for the remaining life of a landing gear according to any one of claims 1 to 5.

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