Civil aircraft reliability tradeoff design method about functions and architecture

Abstract

The invention relates to the technical field of aircraft reliability analysis, in particular to a civil aircraft reliability balance design method about functions and architectures, which comprises the following steps: acquiring a reliability requirement corresponding to an undercarriage system function of a civil aircraft; constructing a fault transmission model corresponding to each function failure mode of the undercarriage system; obtaining reliability influence factors influencing the functions of the undercarriage system; obtaining a plurality of architecture schemes of the undercarriage system; and an optimal architecture scheme is obtained, and an undercarriage system of the civil aircraft is designed. According to the method, the optimal architecture scheme is obtained, and the reliability of civil aircraft design is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft reliability analysis, and in particular to a civil aircraft reliability trade-off design method regarding function and architecture. Background Art

[0002] Reliability and safety analysis are important components of civil aircraft design, and are related to the safety of crew members and passengers. Reasonable reliability design can greatly improve the safety of aircraft operations, and considering the system framework trade-off of reliability is an important task in system design. The architecture trade-off design considering reliability is to distribute the overall product reliability indicators specified in the development task book or technical contract to the specified levels of the product according to certain methods and procedures, and use this as the goal of product reliability design at each relevant level.

[0003] Traditional architectural trade-off design methods tend to ignore reliability requirements and lack quantitative indicators in the process of evaluating architecture, which affects the safety of aircraft use, that is, the aircraft operation reliability is low.

[0004] Therefore, it is necessary to provide a civil aircraft reliability trade-off design method regarding functions and architecture to solve the above problems. Summary of the invention

[0005] The present invention provides a civil aircraft reliability trade-off design method regarding functions and architectures. By using the AHP method, reliability influencing factors are considered, and the reliability design of an architecture scheme is quantitatively evaluated to obtain an optimal architecture scheme, so as to solve the problem that the existing architecture trade-off design method easily ignores reliability requirements during the architecture evaluation process and lacks quantitative indicators in the process, thereby affecting the safety of the aircraft during use, that is, the problem of low aircraft operation reliability.

[0006] A civil aircraft reliability trade-off design method for functions and architectures of the present invention adopts the following technical solution: comprising:

[0007] Obtain the reliability requirements corresponding to the landing gear system functions of civil aircraft;

[0008] The state machine diagram based on the SysML model builds the corresponding fault transfer model in each functional failure mode of the landing gear system;

[0009] Obtain the reliability influencing factors that affect the landing gear system function, including: system complexity, technology maturity, environmental conditions and economic importance;

[0010] Based on the reliability requirements of the landing gear system functions and the corresponding fault transmission model under each functional failure mode of the landing gear system, the designed architecture needs to include corresponding functional components to achieve relevant requirements or avoid corresponding functional failures, and build various architecture solutions for the landing gear system based on SysML block diagrams;

[0011] According to the reliability influencing factors and architecture schemes, the optimal architecture scheme among multiple architecture schemes is obtained by using the hierarchical analysis method, and the landing gear system of the civil aircraft is designed based on the optimal architecture scheme.

[0012] Preferably, the reliability requirements of the landing gear system functions of the civil aircraft are obtained based on the civil aircraft functions and tasks of the supply chain. The reliability requirements include: fault isolation requirements of the landing gear system, hydraulic oil circuit leakage prevention requirements of the landing gear system, turning transmission guarantee requirements of the landing gear system, landing gear redundant operation requirements and landing gear swing damping requirements.

[0013] Preferably, the architecture scheme of the landing gear system includes: characteristic components for realizing the functions of the landing gear system and signal / energy transmission methods between the characteristic components.

[0014] Preferably, the steps of constructing multiple architecture solutions of the landing gear system are:

[0015] Determine characteristic components of the landing gear system according to reliability requirements corresponding to the functions of the landing gear system, wherein the characteristic components include: a turn signal input component, a mechanical structure, and a hydraulic system;

[0016] Design implementation plans for each feature component based on the fault transmission model;

[0017] Design the signal / energy transmission method between each feature component;

[0018] Select feature components designed according to implementation schemes of different feature components, and connect the feature components designed according to different implementation schemes through corresponding signal / energy transfer methods to form a variety of architectural schemes.

[0019] Preferably, the steps of obtaining the optimal architecture solution among multiple architecture solutions are:

[0020] With reliability influencing factors as the influencing layer, architecture solutions as the solution layer, and the optimal architecture solution as the target layer, a hierarchical architecture trade-off diagram of the architecture solution is constructed;

[0021] Obtain a judgment matrix of the importance of reliability influencing factors in the impact layer of the architecture tradeoff diagram;

[0022] The judgment matrix is ​​checked for consistency, and the judgment matrix that does not meet the consistency is corrected using the expert scoring method until the consistency of the judgment matrix is ​​met, and the eigenvector of the judgment matrix is ​​obtained;

[0023] Obtain the comparison result matrix corresponding to each reliability influencing factor for multiple architecture solutions in the solution layer of the architecture tradeoff diagram, and obtain the eigenvector of each comparison result matrix;

[0024] Obtain the weight matrix of reliability influencing factors according to the eigenvectors of all comparison result matrices;

[0025] The weight of each architecture scheme for the landing gear system is obtained according to the eigenvectors of the weight matrix and the judgment matrix;

[0026] The architecture scheme corresponding to the maximum weight is taken as the optimal architecture scheme.

[0027] Preferably, the step of obtaining a judgment matrix of the importance of reliability influencing factors in the influence layer of the architecture tradeoff diagram is:

[0028] The importance of each reliability influencing factor relative to each reliability influencing factor is obtained by using the expert scoring method;

[0029] According to the importance of each reliability influencing factor relative to each reliability influencing factor, a judgment matrix is ​​constructed.

[0030] Preferably, the step of obtaining the comparison result matrix corresponding to each reliability influencing factor of multiple architecture solutions in the solution layer of the architecture tradeoff diagram is:

[0031] The expert scoring method is used to compare the result values ​​of the same reliability influencing parameters of each architecture scheme with each other;

[0032] According to the comparison result values ​​of the same reliability impact parameter between each architecture scheme and each architecture scheme, the corresponding comparison result matrix under each reliability impact factor is obtained.

[0033] Preferably, the eigenvector of each comparison result matrix is ​​used as an element of each row of the weight matrix of the reliability influencing factors, so as to obtain the weight matrix of the reliability influencing factors.

[0034] Preferably, the product of the weight matrix and the eigenvector of the judgment matrix is ​​used as the target weight matrix of the architecture scheme for the landing gear system; each parameter in the target weight matrix is ​​the weight corresponding to each architecture scheme for the landing gear system.

[0035] The beneficial effects of the present invention are:

[0036] Obtain the reliability requirements corresponding to the functions of the landing gear system of the civil aircraft, and build a fault transfer model based on the SysML state machine diagram; analyze the reliability influencing factors affecting the functions and tasks of the landing gear system of the civil aircraft; use the hierarchical allocation method to obtain the optimal architecture scheme among multiple architecture schemes, and design the landing gear system of the civil aircraft based on the optimal architecture scheme. Therefore, in the process of analyzing the factors affecting the reliability of the landing gear of the present invention, the aircraft landing gear system is not only the basic support for the operation of the aircraft, but also has an important impact on flight safety, performance, passenger comfort, and maintenance costs. Therefore, it is considered to be one of the most critical systems on the aircraft, and its normal operation and high reliability are crucial to the development of the aviation industry and flight safety. The performance and reliability of the landing gear system directly affect the operating cost of the aircraft. An efficient and reliable landing gear system can reduce maintenance and repair costs and reduce the operating expenses of airlines. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0038] Figure 1 A flow chart of a civil aircraft reliability trade-off design method regarding functions and architectures of the present invention;

[0039] Figure 2 is a state machine diagram of the turning function failure mode in this embodiment;

[0040] Figure 3 is a schematic diagram of a structural scheme 1 of the front landing gear in this embodiment;

[0041] Figure 4 is a schematic diagram of a structural scheme 2 of the front landing gear in this embodiment;

[0042] Figure 5 is a schematic diagram of a structural scheme 3 of the front landing gear in this embodiment;

[0043] Figure 6 A schematic diagram of the framework for constructing an architectural trade-off diagram using the AHP method;

[0044] Figure 7 This is the architecture trade-off diagram obtained by using the hierarchical analysis method of the present invention. DETAILED DESCRIPTION

[0045] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0046] An embodiment of a civil aircraft reliability trade-off design method for functions and architectures of the present invention is as follows: Figure 1 As shown, including:

[0047] S1. Obtain the reliability requirements corresponding to the landing gear system functions of civil aircraft;

[0048] Since the capture of civil aircraft function and mission reliability requirements is based on the supply chain-based reliability requirements capture method, the purpose is to establish the selection principles and analysis standards for the factors affecting function and mission reliability, and to ensure the scientificity, rationality and operability of the architecture trade-offs. Therefore, in this embodiment, a general stakeholder model based on the supply chain process is used as the basic model. From the market perspective, the upstream, midstream and downstream stakeholders of the product are captured, each stakeholder is further classified, and specific stakeholder instances are sorted out and filled in, and finally the stakeholder requirements are captured. According to the stakeholder requirements, the reliability requirements corresponding to the landing gear system functions of civil aircraft can be obtained.

[0049] Among them, the reliability requirements corresponding to the landing gear system functions of the civil aircraft in this embodiment are: fault isolation requirements of the landing gear system, hydraulic oil circuit leakage prevention requirements of the landing gear system, turning transmission guarantee requirements of the landing gear system, landing gear redundant operation requirements and landing gear swing damping requirements, as shown in Table 1.

[0050] Table 1

[0051]

[0052] S2. Constructing a fault transfer model corresponding to each functional failure mode of the landing gear system;

[0053] The state machine diagram based on the SysML model constructs the corresponding fault transfer model under each functional failure mode of the landing gear system; since the functional failure modes of the landing gear system include: the failure mode of the ground turning function and the failure mode of the braking function, this embodiment takes the failure mode of the ground turning function in the functional failure mode of the landing gear system as the top event, determines the failure criterion according to the functions and performance requirements of each component of the landing gear system, and uses the event and logic gate symbols dedicated to the fault transfer model to express the logical reasoning relationship between the fault events of each component of the system. The fault transfer model is established by the state machine diagram based on the SysML model. The construction of the fault transfer model is based on the analysis of the function, and describes the failure influence relationship between each functional object and its objects, including the system structure, function and fault information. Specifically, Figure 2 It shows the state machine diagram corresponding to the failure mode of the ground turning function, namely the fault transmission model.

[0054] S3. Obtain the reliability influencing factors that affect the landing gear system function;

[0055] Reliability needs to be considered from the design stage. With the attributes of the product's entire life cycle, when considering the factors affecting architecture reliability, the reliability level of the product should be comprehensively considered from the aspects of design, manufacturing, operation and maintenance to see whether it meets the requirements. Therefore, the system complexity is selected to evaluate the reliability parameters in the architecture design process, the architecture manufacturing reliability is comprehensively evaluated through technology maturity, the reliability of the aircraft maintenance process is evaluated through environmental conditions, and the reliability of the operation process is evaluated with economic maturity to obtain the reliability influencing factors that affect the landing gear system function. The reliability influencing factors include: system complexity, technology maturity, environmental conditions and economic importance.

[0056] Specifically, in this embodiment, the system complexity is evaluated based on the number of next-level units that make up the system. Subsystems and equipment with high complexity should be assigned lower reliability indicators. Technical maturity: The possibility of equipment failure is evaluated based on historical data and experience, and the technical development level of the system is determined by weighing the scoring results of each subsystem or equipment that makes up the system. For technically immature products, a lower reliability indicator should be assigned. Environmental conditions: Evaluated based on the environment in which the equipment is located. The harsher the environmental conditions, the greater the possibility of failure. For products working under harsh environmental conditions, a lower reliability indicator should be assigned. Fourth, economic importance: Evaluated based on the relative size of the economic loss caused by the failure of the subsystem to the entire system. The greater the economic importance, the greater the economic loss caused to the entire system by the failure of the system, and a higher reliability indicator should be assigned.

[0057] S4. Obtain various architecture solutions for the landing gear system;

[0058] Taking the reliability requirements corresponding to the landing gear system functions and the corresponding fault transmission model under each functional failure mode of the landing gear system as constraints, various architecture schemes of the landing gear system are constructed based on the SysML block diagram. Specifically, according to the reliability requirements corresponding to the landing gear system functions, the characteristic components of the landing gear system are determined; based on the fault transmission model, the implementation plan of each characteristic component is designed; the signal / energy transmission method between each characteristic component is designed; the characteristic components designed by the implementation plans of different characteristic components are selected, and the characteristic components designed by different implementation plans are connected through the corresponding signal / energy transmission method to form various architecture schemes.

[0059] It should be noted that the characteristic components include: turning signal input components, mechanical structures and hydraulic systems. Attention should be paid to fault isolation and redundant design between the characteristic components. Different design schemes have different focuses, and their satisfaction of needs is also different. The corresponding characteristic components are designed according to their focuses. Taking the landing gear signal input as an example, there are many ways to achieve landing gear turning, including joint control by handwheel and pedal, and handwheel control with differential brakes to assist in turning. Signals or energy need to be transmitted between components. According to the principle of fault isolation, the transmission path is designed. Taking the landing gear turning system as an example, it includes the conversion of input signals into rotational torque, and the energy transmission of hydraulic system assisted rotation. A characteristic component may have multiple inputs and outputs. The specific interface of each input and output should be determined in the design stage. Figure 3 to Figure 4 If there is a flow input / output from the same interface, it should be reflected in the same interface.

[0060] Specifically, in this embodiment, three landing gear design schemes are constructed with reference to other civil aircraft landing gear turning system design schemes.

[0061] Architecture 1: Figure 3 As shown, the turning scheme of this scheme is realized by the steering mechanism, and the hydraulic source is connected through the landing gear transmission valve to provide power for the landing gear. The signal of landing gear steering is input through the hand wheel, and the turning is assisted by the pedal signal. The two operating signals and the hydraulic source are isolated through the comparison rod and the steering adjustment valve. At the same time, the damper provides the damping required for the front wheel swing array. There are two sets of hydraulic sources for front wheel deflection, rudder deflection and braking. When one set of hydraulic sources fails, it can be guaranteed that the control is still available.

[0062] Architecture 2: Based on a series of aircraft, the ground direction control method of the aircraft is as follows: Figure 4As shown in the figure, the control method uses a hand wheel to operate the turning assembly for the main turning control, and uses brakes and rudders to assist in turning control. Braking and turning share a control unit, and hydraulics are used as the driving energy. Two sets of hydraulic systems are used, represented by yellow and green respectively. When one set of hydraulic sources fails, it can ensure that the control is still available. The accumulator plays a certain damping role. The rudder is transmitted through the electric transmission system, isolated from the brake and turning system, and damping control is performed through the limiter unit and yaw damper to assist steering. The flap actuation uses the yellow hydraulic system as the power source.

[0063] Architecture 3: Based on a series of aircraft, the ground direction control method of the aircraft is as follows: Figure 5 As shown in the figure, when realizing the turning function, the pilot will operate the turning hand wheel or rudder pedal. The operation signal will be transmitted to the turning actuator after processing, and the actuator will be driven to rotate the gear through the hydraulic oil control. The gear and rack are meshed and the gear rotation will cause the rack to move; the rack will output torque to drive the torque arm to transmit the torque to the wheel frame, and the wheel frame will realize the ground turning function with the help of the tire. At the same time, the swing kinetic energy in the turning process will be absorbed and neutralized by the torque arm or the inner and outer cylinders of the buffer, thereby avoiding the vibration and swing problems of the landing gear. In addition. Two sets of hydraulic systems are used, namely the yellow and green hydraulic systems, which can ensure that the control is still available when one hydraulic source fails. The electronic control, mechanical and hydraulic systems are also well isolated. In the event of any failure among them, the turning function will not be affected. At the same time, considering the influence of the fault transmission model, the multi-input source is designed to avoid the failure of the turning function due to the failure of the gear rack structure and the failure of the hydraulic pressure.

[0064] S5. Obtain the optimal architecture solution and design the landing gear system of the civil aircraft;

[0065] According to the reliability influencing factors and architecture schemes, the optimal architecture scheme among multiple architecture schemes is obtained by using the hierarchical analysis method, and the landing gear system of the civil aircraft is designed based on the optimal architecture scheme.

[0066] Specifically, the steps of using the hierarchical analysis method to obtain the optimal architecture solution among multiple architecture solutions in this embodiment are:

[0067] Step 51: Figure 6 Combined with the AHP flowchart, with reliability influencing factors as the influencing layer, architecture solutions as the solution layer, and the optimal architecture solution as the target layer, we can get the following: Figure 7 The architectural trade-off diagram shown is a hierarchical hierarchy of architectural options.

[0068] Step 52: Obtain a judgment matrix of the importance of reliability influencing factors in the impact layer of the architecture tradeoff diagram;

[0069] The importance of each reliability influencing factor relative to each reliability influencing factor is obtained by using the expert scoring method; a judgment matrix is ​​constructed according to the importance of each reliability influencing factor relative to each reliability influencing factor. In this embodiment, a judgment scale needs to be established for the reliability influencing factors. The judgment scale refers to the basis for scoring the comparison results of the influencing factors or unit products compared with each other. The scoring adopts the expert scoring method. Table 2 shows a recommended value of the judgment scale obtained by the expert scoring method; A in Table 2 i A represents the i-th reliability influencing factor; j It represents the jth reliability influencing factor i, j = 1, 2, L, k, k is the number of reliability influencing factors. During the allocation process, the score of the judgment scale can also be adjusted according to the actual situation.

[0070] Table 2

[0071]

[0072]

[0073] Step 53, performing consistency check on the judgment matrix, and correcting the judgment matrix that does not meet the consistency using the expert scoring method until the consistency of the judgment matrix is ​​met, and obtaining the eigenvector of the judgment matrix;

[0074] Form a judgment matrix based on expert scores The maximum eigenvalue of the judgment matrix is ​​4.0206, and the eigenvector of the judgment matrix is ​​(0.2577, 0.6305, 0.2315, 0.6946). The eigenvector of the judgment matrix is ​​normalized, and the normalized eigenvector is ω A ′=[0.1420,0.3475,0.1276,0.3828];Consistency test:CI=(mean(w A )-4) / 3=6.866×10 -3 , satisfying CI≤0.1 and meeting the compatibility requirements.

[0075] Step 54: Obtain the comparison result matrix corresponding to each reliability influencing factor of the three architecture solutions in the solution layer of the architecture tradeoff diagram, and obtain the eigenvector of each comparison result matrix;

[0076] The expert scoring method is used to compare the result values ​​of the same reliability influencing parameters of each architecture scheme with each other; according to the comparison result values ​​of the same reliability influencing parameters of each architecture scheme with each other, the corresponding comparison result matrix under each reliability influencing factor is obtained. The comparison result matrix P of the three architecture schemes under each reliability influencing factor is BmThere are four influencing factors, so four comparison result matrices need to be established. The four comparison result matrices are as follows:

[0077] Comparison matrix of three architecture solutions under system complexity:

[0078] The maximum eigenvalue and eigenvector are: After normalization, we have

[0079] Comparison matrix of the three architecture solutions in terms of technology maturity:

[0080] The maximum eigenvalue and eigenvector of are: After normalization, we have

[0081] Comparison matrix of the three architecture solutions under environmental conditions:

[0082] The maximum eigenvalue and eigenvector of are: After normalization, we have

[0083] Comparison matrix of the three architecture solutions in terms of economic importance:

[0084] The maximum eigenvalue and eigenvector of are: After normalization, we have

[0085] S55, obtaining a weight matrix of reliability influencing factors according to the eigenvectors of all comparison result matrices;

[0086] Calculate the weights of the relative influencing factors, establish the weight matrix of the relative influencing factors, and find the mth comparison result matrix The maximum eigenvalue of and The corresponding eigenvector is normalized to obtain the weight vector is the weight of the rth architecture solution method relative to the influencing factor m; the calculation result matrix The compatibility index CI of: If CI≤0.1, the result matrix Meet the compatibility requirements; otherwise, re-establish the result matrix based on the expert scoring method Recalculate the weight of the design architecture relative reliability influencing factor m. After calculating the weight vectors of the unit product relative to all influencing factors, these weight vectors are combined into a weight matrix PC.

[0087]

[0088] Step 56: Obtain the weight of each architecture scheme for the landing gear system according to the eigenvectors of the weight matrix and the judgment matrix; and take the architecture scheme corresponding to the maximum weight as the optimal architecture scheme.

[0089] The weight matrix ω of the architecture scheme for the landing gear system Z for:

[0090]

[0091] Weight matrix ω Z The architecture scheme corresponding to the maximum weight value is the optimal architecture scheme.

[0092] At this point, the design of civil aircraft can be carried out based on the optimal architectural solution.

[0093] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A civil aircraft reliability trade-off design method for functions and architectures, characterized in that: include: Obtain the reliability requirements corresponding to the landing gear system functions of civil aircraft; The state machine diagram based on the SysML model builds the corresponding fault transfer model in each functional failure mode of the landing gear system; Obtain the reliability influencing factors that affect the landing gear system function, including: system complexity, technology maturity, environmental conditions and economic importance; Taking the reliability requirements corresponding to the landing gear system functions and the corresponding fault transfer model under each functional failure mode of the landing gear system as constraints, various architecture schemes of the landing gear system are constructed based on SysML block diagrams; According to the reliability influencing factors and architecture schemes, the optimal architecture scheme among multiple architecture schemes is obtained by using the hierarchical analysis method, and the landing gear system of the civil aircraft is designed based on the optimal architecture scheme.

2. The method for designing a civil aircraft reliability trade-off between functions and architecture according to claim 1, characterized in that: The reliability requirements of the landing gear system functions of civil aircraft are obtained based on the civil aircraft functions and tasks of the supply chain. The reliability requirements include: fault isolation requirements of the landing gear system, hydraulic oil circuit leakage prevention requirements of the landing gear system, turning transmission guarantee requirements of the landing gear system, landing gear redundant operation requirements and landing gear swing damping requirements.

3. The method for designing a civil aircraft reliability trade-off between functions and architecture according to claim 1, characterized in that: The architecture of the landing gear system includes: characteristic components for realizing the functions of the landing gear system and the signal / energy transmission method between the characteristic components.

4. The method for designing a civil aircraft reliability trade-off between functions and architecture according to claim 1, characterized in that: The steps to build various architecture solutions for the landing gear system are: Determine characteristic components of the landing gear system according to reliability requirements corresponding to the functions of the landing gear system, wherein the characteristic components include: a turn signal input component, a mechanical structure, and a hydraulic system; Design implementation plans for each feature component based on the fault transmission model; Design the signal / energy transmission method between each feature component; Select feature components designed according to implementation schemes of different feature components, and connect the feature components designed according to different implementation schemes through corresponding signal / energy transfer methods to form a variety of architectural schemes.

5. The method for designing a civil aircraft reliability trade-off between functions and architecture according to claim 1, characterized in that: The steps to obtain the optimal architecture solution among multiple architecture solutions are: With reliability influencing factors as the influencing layer, architecture solutions as the solution layer, and the optimal architecture solution as the target layer, a hierarchical architecture trade-off diagram of the architecture solution is constructed; Obtain a judgment matrix of the importance of reliability influencing factors in the impact layer of the architecture tradeoff diagram; The judgment matrix is ​​checked for consistency, and the judgment matrix that does not meet the consistency is corrected using the expert scoring method until the consistency of the judgment matrix is ​​met, and the eigenvector of the judgment matrix is ​​obtained; Obtain the comparison result matrix corresponding to each reliability influencing factor for multiple architecture solutions in the solution layer of the architecture tradeoff diagram, and obtain the eigenvector of each comparison result matrix; Obtain the weight matrix of reliability influencing factors according to the eigenvectors of all comparison result matrices; The weight of each architecture scheme for the landing gear system is obtained according to the eigenvectors of the weight matrix and the judgment matrix; The architecture scheme corresponding to the maximum weight is taken as the optimal architecture scheme.

6. The method for designing a civil aircraft reliability trade-off between functions and architecture according to claim 5, characterized in that: The steps to obtain the judgment matrix of the importance of reliability influencing factors in the impact layer of the architecture tradeoff diagram are: The importance of each reliability influencing factor relative to each reliability influencing factor is obtained by using the expert scoring method; According to the importance of each reliability influencing factor relative to each reliability influencing factor, a judgment matrix is ​​constructed.

7. The method for designing a civil aircraft reliability trade-off between functions and architecture according to claim 5, characterized in that: The steps for obtaining the comparison result matrix corresponding to each reliability influencing factor for multiple architecture solutions in the solution layer of the architecture tradeoff diagram are as follows: The expert scoring method is used to compare the result values ​​of the same reliability influencing parameters of each architecture scheme with each architecture scheme; according to the comparison result values ​​of the same reliability influencing parameters of each architecture scheme with each architecture scheme, the corresponding comparison result matrix under each reliability influencing factor is obtained.

8. The method for designing a civil aircraft reliability trade-off between functions and architecture according to claim 5, characterized in that: The weight matrix of reliability influencing factors can be obtained by taking the eigenvector of each comparison result matrix as the element of each row of the weight matrix of reliability influencing factors.

9. The method for designing a civil aircraft reliability trade-off between functions and architecture according to claim 5, characterized in that: The product of the weight matrix and the eigenvector of the judgment matrix is ​​used as the target weight matrix of the architecture scheme for the landing gear system; each parameter in the target weight matrix is ​​the weight corresponding to each architecture scheme for the landing gear system.

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