Static Strength Test Method and System for Gas Rudder Control Mechanism

Abstract

The present application provides a static strength test method and system for a gas rudder control mechanism; the method includes: obtaining a first static strength value of the gas rudder control mechanism under torsional load; obtaining a second static strength value of the gas rudder control mechanism under service load; establishing a reliability mathematical model according to the first static strength value and the second static strength value; generating a first static strength reliability value according to the reliability mathematical model; generating a second static strength reliability value according to the reliability mathematical model. The reliability of the static strength value is evaluated through a mathematical model, and the reliability characteristic quantity of the gas rudder control mechanism can be determined through test measurement, providing a reasonable means for evaluating the ultimate bearing capacity of the gas rudder control mechanism and solving the problem of reliability evaluation of the gas rudder control mechanism.

Description

Technical Field

[0001] The present application relates to the technical field of aerospace test devices, and in particular to a static strength test method and system for a gas rudder control mechanism. Background Art

[0002] Under the action of the engine jet, the gas rudder surface will generate a very large aerodynamic force, and the gas rudder control mechanism, as a key component that drives the gas rudder surface to rotate, should have sufficient load-bearing strength to ensure that it can complete its movement function when subjected to aerodynamic loads. In the design process of the gas rudder control mechanism, two key issues need to be solved in terms of static strength: one is whether the strength of its various components can meet the design requirements when the gas rudder moves to the extreme position; the other is how to assess the ultimate load-bearing capacity of the control mechanism.

[0003] At present, the most common way to obtain the static strength of key components of the gas rudder control mechanism is to use finite element simulation analysis software for simulation calculation. However, the model accuracy, boundary condition settings, and uncertainty in material parameters will have a certain impact on the results of finite element simulation analysis. At the same time, as a key component of the aircraft structure, the gas rudder control mechanism needs to carry out a static strength reliability assessment of the control mechanism when conducting a reliability assessment of the aircraft structure. However, how to determine the reliability characteristic quantity of the gas rudder control mechanism and how to measure the characteristic quantity through experiments are urgent problems to be solved; therefore, the inventor is committed to researching and improving the above-mentioned problems, and is committed to proposing a static strength test method that can meet the static strength test requirements of the gas rudder control mechanism and determine the main performance parameters in the reliability characteristic quantity. Summary of the invention

[0004] In view of this, the purpose of this application is to propose a static strength test method and system for a gas rudder control mechanism, which provides a reasonable means to assess the load-bearing capacity of the gas rudder control mechanism and solves the problem of reliability assessment of the gas rudder control mechanism.

[0005] Based on the above objectives, the present application provides a static strength test method and system for a gas rudder control mechanism.

[0006] In a first aspect, a static strength test method for a gas rudder control mechanism is disclosed, the method comprising:

[0007] Obtaining a first static strength value of the gas rudder control mechanism under a torsional load;

[0008] Obtaining a second static strength value of the gas rudder control mechanism under a use load;

[0009] Establishing a reliability mathematical model according to the first static strength value and the second static strength value;

[0010] Generate the first static strength reliability value according to the reliability mathematical model;

[0011] Generate the second static strength reliability value according to the reliability mathematical model.

[0012] Further on the above basis, the first static strength value includes a first load torque value and a second load torque value, and the second static strength value includes a first service load force value and a second service load force value;

[0013] The gas rudder control mechanism includes a mounting base, a rudder surface, a support, a rocker arm, and a control rod. The holes at both ends of the rudder surface are connected to horizontal hydraulic cylinders in different directions. The support is located on the mounting base. A rudder shaft connected to the rudder surface is provided on the support. The rudder shaft is connected to the rocker arm, and one end of the rocker arm is connected to the control rod. The other end of the control rod is connected to the base.

[0014] In an alternative embodiment, obtaining the first static strength value of the gas rudder control mechanism under torsional load further includes the following steps:

[0015] Obtain the first load torque value;

[0016] Wherein, the first load torque value is generated based on the specification parameters of the gas rudder control mechanism;

[0017] Control the hydraulic cylinders to apply first tensile forces in different directions to both ends of the rudder surface, and gradually increase the first tensile forces to the first load torque value;

[0018] Unload the first tensile forces and check the working conditions of the rocker arm and the control rod;

[0019] When it is determined that the working conditions of the rocker arm and the control rod are damaged, it is determined that the gas rudder control mechanism does not meet the basic static strength requirements under torsional load;

[0020] When it is determined that the working conditions of the rocker arm and the control rod are normal, continue to apply the first tensile forces until the working conditions of the rocker arm and the control rod are damaged, unload the first tensile forces, and record the first tensile forces at this time as the second load torque value.

[0021] In an alternative embodiment, obtaining the second static strength value of the gas rudder control mechanism under service load includes the following steps:

[0022] Adjust the horizontal height of the hydraulic cylinders so that the horizontal height of the axes of the hydraulic cylinders is on the same horizontal line as the height of the middle hole of the rudder surface;

[0023] Obtain the first service load force value;

[0024] Wherein, the first applied load force value is the second tensile force applied by the hydraulic cylinder to the rudder surface in the axial direction, and the second tensile force is obtained through a gas rudder force measurement test;

[0025] Unload the second tensile force and check the working conditions of the mounting bearings connecting the support and the rudder shaft;

[0026] When it is determined that the mounting bearings connecting the support and the rudder shaft are damaged, it is determined that the gas rudder control mechanism does not meet the basic static strength requirements of the applied load;

[0027] When it is determined that the working conditions of the mounting bearings connecting the support and the rudder shaft are normal, continue to apply the second tensile force until the mounting bearings connecting the support and the rudder shaft are damaged, unload the second tensile force, and record the second tensile force at this time as the second applied load force value.

[0028] In an alternative embodiment, generating the first static strength reliability value according to the reliability mathematical model includes the following steps:

[0029] Collect multiple groups of the second load torque values and the second applied load force values;

[0030] Evaluate and generate the torsional load static strength reliability value according to the second load torque value;

[0031] Evaluate and generate the applied load static strength reliability value according to the second applied load force value;

[0032] Generate the gas rudder control mechanism reliability value according to the torsional load static strength reliability value and the applied load static strength reliability value.

[0033] In an alternative embodiment, evaluating and generating the torsional load static strength reliability value according to the second load torque value further includes the following steps:

[0034] Obtain the mean value and standard deviation of multiple groups of the second load torque values;

[0035] Establish a mathematical model to obtain the first strength mean value and the first stress mean value;

[0036] Calculate the first confidence lower limit according to the first strength mean value and the first stress mean value.

[0037] In an alternative embodiment, evaluating and generating the torsional load static strength reliability value according to the second load torque value is implemented according to the following steps:

[0038] Obtain the mean value of multiple groups of the second load torque values, which is achieved through the following formula:

[0039]

[0040] Wherein, P 2,i is the second load torque value, is the mean value of the second load torque value, and n is the number of samples of the second load torque value;

[0041] Obtain the standard deviation of the second load torque value of the multiple sample groups, which is achieved through the following formula:

[0042]

[0043] Wherein, P 2,i is the second load torque value, is the mean value of the second load torque value, σ P2 is the standard deviation of the second load torque value, and n is the number of samples of the second load torque value;

[0044] The first strength mean value is achieved through the following formula:

[0045]

[0046] Wherein, μ S1 is the first strength mean value under the test conditions; C S1 is the strength variation coefficient, u γ is the normal probability coefficient;

[0047] The strength variation coefficient C S1 is obtained through the following formula:

[0048]

[0049] The first confidence lower limit of the torsional load static strength reliability value R S1 is calculated through the following formula:

[0050]

[0051] Wherein, Φ represents the standard normal distribution function, and γ is the confidence level.

[0052] In an alternative embodiment, when evaluating and generating the service load static strength reliability value according to the second service load force value, the following steps are further included:

[0053] Obtain the mean value and standard deviation of multiple groups of the second service load force values;

[0054] Establish a mathematical model to obtain the second strength mean value and the second stress mean value;

[0055] Calculate the second confidence lower limit according to the second strength mean value and the second stress mean value.

[0056] In an alternative embodiment, when evaluating and generating the service load static strength reliability value according to the second service load force value, it is achieved according to the following steps:

[0057] Obtain the mean value of the second service load force values in the diverse group, which is achieved by the following formula:

[0058]

[0059] In the formula, F 2,i is the second service load force value, is the mean value of the second service load force values, and n is the sample number of the second service load force values;

[0060] Obtain the standard deviation of the second service load force values in the diverse group, which is achieved by the following formula:

[0061]

[0062] In the formula, σ F2 is the standard deviation of the second service load force values;

[0063] The second strength mean value is achieved by the following formula:

[0064]

[0065] In the formula, μ S2 is the second strength mean value under the test conditions; C S2 is the strength variation coefficient, u γ is the normal probability coefficient;

[0066] The strength variation coefficient C S2 is obtained by the following formula:

[0067]

[0068] The lower second confidence limit of the reliability value R S2 of the service load static strength is calculated by the following formula:

[0069]

[0070] In the formula, Φ represents the standard normal distribution function, and γ is the confidence level.

[0071] On the basis of the above, as an optional embodiment, generating the reliability value of the gas rudder control mechanism according to the reliability value of the torsional load static strength and the reliability value of the service load static strength includes the following steps:

[0072] The reliability value of the gas rudder control mechanism is calculated based on the following formula:

[0073]

[0074] In the formula, R γis the reliability value of the gas rudder control mechanism, R γ,S1 is the reliability value of the static strength under torsional load, R γ,S2 is the reliability value of the static strength under service load.

[0075] Second aspect, a static strength test system for a gas rudder control mechanism, comprising a gas rudder control mechanism, a test platform, load-bearing columns and a horizontal hydraulic cylinder;

[0076] The gas rudder control mechanism and the load-bearing columns are placed on the test platform. The load-bearing columns are located on both sides of the test platform. The gas rudder control mechanism is located between the load-bearing columns on both sides. The horizontal hydraulic cylinder is fixed on the load-bearing columns. The horizontal hydraulic cylinder is parallel to the test platform. The horizontal hydraulic cylinder is connected to the gas rudder control mechanism to apply a tensile force to the gas rudder control mechanism.

[0077] As can be seen from the above, a static strength test method and system for a gas rudder control mechanism provided by the present application have the following beneficial effects:

[0078] By analyzing the working characteristics of the gas rudder control mechanism, the present application can obtain two failure modes of it. One is that the gas rudder control mechanism is damaged under the action of the load torque. The other is that the strength of the load-bearing parts of the gas rudder control mechanism fails under the action of the axial force. Furthermore, by applying torsional load and service load to the gas rudder control mechanism respectively for static strength tests, the load-bearing capacity of the components of the gas rudder control mechanism can be detected, and it can be known whether the components meet the basic force requirements. And further, the ultimate bearing capacity of the stressed components can be obtained through the tests. After completing the static strength test, a mathematical model is further established to evaluate the static strength reliability of the control mechanism, providing a reasonable means for evaluating the ultimate bearing capacity of the gas rudder control mechanism and solving the problem of reliability evaluation of the gas rudder control mechanism. Description of the Drawings

[0079] In order to more clearly illustrate the technical solutions in the present application or related technologies, the following will briefly introduce the drawings required for use in the embodiments or related technology descriptions. Obviously, the drawings in the following description are only the embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0080] Figure 1 is the logic block diagram of the static strength test method for the gas rudder control mechanism of the embodiment of the present application;

[0081] Figure 2 is the structural schematic diagram of the static strength test system for the gas rudder control mechanism of the embodiment of the present application;

[0082] Figure 3Schematic structural diagram of the gas rudder control mechanism according to an embodiment of the present application;

[0083] Figure 4 Front view of the gas rudder control mechanism according to an embodiment of the present application;

[0084] Figure 5 Schematic sectional view of the gas rudder control mechanism according to an embodiment of the present application;

[0085] Figure 6 Schematic diagram of the rudder shaft of the gas rudder control mechanism according to an embodiment of the present application;

[0086] Figure 7 Schematic diagram of the mounting base of the gas rudder control mechanism according to an embodiment of the present application;

[0087] Figure 8 Left view of the gas rudder control mechanism according to an embodiment of the present application;

[0088] Figure 9 Partial explosion diagram of the gas rudder control mechanism according to an embodiment of the present application. Detailed implementation manners

[0089] To make the objectives, technical solutions and advantages of the present application clearer and more understandable, the following further describes the present application in detail with reference to specific embodiments and the accompanying drawings.

[0090] It should be noted that unless otherwise defined, the technical terms or scientific terms used in the embodiments of the present application should have the ordinary meanings understood by those of ordinary skill in the field to which the present application belongs. The "first", "second" and similar terms used in the embodiments of the present application do not denote any order, quantity or importance, but are only used to distinguish different components. The terms such as "including" or "comprising" mean that the elements or objects appearing before this term cover the elements or objects listed after this term and their equivalents, without excluding other elements or objects. The terms such as "connected" or "coupled" are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. The terms such as "upper", "lower", "left" and "right" are only used to represent relative positional relationships, and when the absolute position of the object being described changes, the relative positional relationship may also change accordingly.

[0091] Before specifically describing the static strength test method and system of the gas rudder control mechanism provided by the present application, the application scenario and inventive concept of the present application are first described.

[0092] Under the action of the engine jet flow, a very large aerodynamic force will be generated on the gas rudder surface. As a key component that drives the gas rudder surface to rotate, the gas rudder control mechanism should have sufficient load-bearing strength to ensure that it can complete the motion function when bearing the aerodynamic load. During the design process of the gas rudder control mechanism, two key problems need to be solved in terms of static strength: one is whether the strength of each component can meet the design requirements when the gas rudder moves to the limit position; the other is how to evaluate the ultimate load-bearing capacity of the control mechanism. The inventor also takes the two problems existing in terms of static strength as the starting point, and considering the simulation calculations carried out by existing finite element simulation analysis software, it is the most common way to obtain the static strength of the key components of the gas rudder control mechanism; and considering that the model accuracy, the setting of boundary conditions, and the uncertainty of material parameters will all have a certain impact on the finite element simulation analysis results. Therefore, it is necessary to improve the deficiencies of the existing methods, and as a key component of the aircraft structure, when evaluating the reliability of the aircraft structure, it is necessary to carry out the reliability assessment of the static strength of the control mechanism; be committed to determining the reliability characteristic quantity of the gas rudder control mechanism, and be able to measure this reliability characteristic quantity through experimental means.

[0093] Therefore, the inventor takes this as the technical background, to build a complete set of test systems that can meet the requirements of static strength tests, and proposes corresponding test methods to determine the main performance parameters of the reliability characteristic quantity, as the original intention of the invention, to develop and implement a static strength test method and system for a gas rudder control mechanism.

[0094] Combined with Figure 1 As shown, in some embodiments, a static strength test method for a gas rudder control mechanism is disclosed. The second method relies on the structure of the gas rudder control mechanism and the static strength test system. The method includes:

[0095] S1: Obtain the first static strength value of the second gas rudder control mechanism under torsional load;

[0096] S2: Obtain the second static strength value of the second gas rudder control mechanism under service load;

[0097] S3: Establish a reliability mathematical model according to the first static strength value and the second static strength value;

[0098] S4: Generate the first static strength reliability value according to the second reliability mathematical model;

[0099] S5: Generate the second static strength reliability value according to the second reliability mathematical model.

[0100] Among them, the first static strength value includes a first load torque value and a second load torque value, and the second static strength value includes a first service load force value and a second service load force value. The first load torque value is the maximum hinge torque of the gas rudder, which is the torsional load applied by the hydraulic cylinder to the components of the gas rudder control mechanism. The second load torque value is the maximum torsional load torque that causes component damage. The first service load force value is the resultant force of the maximum normal force and the maximum axial force of the gas rudder's rudder surface, which is the service load applied by the hydraulic cylinder to the rudder surface of the gas rudder. The second service load force value is the maximum service load that causes component damage.

[0101] Further, in some alternative embodiments, step S1 may further include the following steps:

[0102] S101: Obtain the first load torque value;

[0103] Among them, the second first load torque value is generated based on the specification parameters of the second gas rudder control mechanism, determined based on a certain bearing capacity required by the gas rudder control mechanism, and selected and changed according to the actual situation of the gas rudder control mechanism;

[0104] S102: Control the second hydraulic cylinder to apply first tensile forces in different directions to both ends of the second rudder surface, and gradually increase the second first tensile force to the second first load torque value;

[0105] S103: Unload the second first tensile force and check the working conditions of the second rocker arm and the control rod;

[0106] S104: When it is determined that the working conditions of the second rocker arm and the control rod are damaged, determine that the second gas rudder control mechanism does not meet the basic static strength requirements for torsional load;

[0107] S105: When it is determined that the working conditions of the second rocker arm and the control rod are normal, continue to apply the first tensile force until the working conditions of the second rocker arm and the control rod are damaged, unload the second first tensile force, and record the first tensile force at this time as the second second load torque value.

[0108] Further, in some alternative embodiments, step S2 may further include the following steps:

[0109] S201: Adjust the horizontal height of the second hydraulic cylinder so that the horizontal height of the axis of the second hydraulic cylinder is on the same horizontal line as the height of the middle hole of the second rudder surface;

[0110] S202: Obtain the first service load force value;

[0111] Among them, the second first service load force value is the second tensile force applied by the second hydraulic cylinder to the second rudder surface in the axial direction, and the second second tensile force is obtained through a gas rudder force measurement test;

[0112] S203: Unload the second tensile force and check the working conditions of the mounting bearings connecting the second support and the rudder shaft;

[0113] S204: When it is determined that the mounting bearings connecting the support and the rudder shaft are damaged, it is determined that the second gas rudder control mechanism does not meet the basic static strength requirements of the service load;

[0114] S205: When it is determined that the working conditions of the mounting bearings connecting the second support and the rudder shaft are normal, continue to apply the second tensile force until the mounting bearings connecting the second support and the rudder shaft are damaged, then unload the second tensile force, and record the second tensile force at this time as the second service load force value.

[0115] And record each obtained parameter value.

[0116] In some alternative embodiments, step S3 may further include the following steps:

[0117] S301: Collect multiple groups of second load torque values and second service load force values;

[0118] S302: Evaluate and generate the reliability value of the torsional load static strength based on the second load torque values;

[0119] S303: Evaluate and generate the reliability value of the service load static strength based on the second service load force values;

[0120] S304: Generate the reliability value of the gas rudder control mechanism based on the second torsional load static strength reliability value and the second service load static strength reliability value.

[0121] Furthermore, step S302 may further include the following steps:

[0122] S3021: Obtain the mean and standard deviation of multiple groups of second load torque values;

[0123] S3022: Establish a mathematical model to obtain the first strength mean and the first stress mean;

[0124] S3023: Calculate the first confidence lower limit based on the second first strength mean and the first stress mean.

[0125] Furthermore, step S303 may further include the following steps:

[0126] S3031: Obtain the mean and standard deviation of multiple groups of second service load force values;

[0127] S3032: Establish a mathematical model to obtain the second strength mean and the second stress mean;

[0128] S3033: Calculate the second confidence lower limit based on the second second strength mean and the second stress mean.

[0129] Furthermore, a reliability value of the gas rudder control mechanism is generated based on the static strength reliability value of the torsional load and the static strength reliability value of the second service load.

[0130] For the specific calculation method of the above steps, refer to the following embodiments.

[0131] In some alternative embodiments, the calculation method for reliability assessment may be:

[0132] For step S4, first evaluate the static strength reliability R of the torsional load S1 , obtain the mean value of the second load torque values of the diverse group, which is achieved through the following formula (1):

[0133]

[0134] In the formula, P 2,i is the second load torque value, is the mean value of the second load torque values, and n is the number of samples of the second load torque values;

[0135] Obtain the standard deviation of the second load torque values of the diverse group, which is achieved through the following formula:

[0136]

[0137] In the formula, P 2,i is the second load torque value, is the mean value of the second load torque values, σ P2 is the standard deviation of the second load torque values, and n is the number of samples of the second load torque values;

[0138] Use μ S1 to represent the strength under this test condition, the confidence level γ, and the corresponding normal probability coefficient (the upper quantile of the normal distribution) is represented as u γ ;

[0139] The mean value of the second first strength is achieved through the following formula:

[0140]

[0141] In the formula, μ S1 is the mean value of the first strength under the test condition; C S1 is the strength variation coefficient, and u γ is the normal probability coefficient;

[0142] In the formula, when the sample is small, the strength variation coefficient C S1 can be determined by an empirical value, generally taking 0.05, or it can also be calculated through the following method:

[0143] The strength variation coefficient C S1Obtained by the following formula:

[0144]

[0145] According to the stress-strength interference model, calculate the reliability R S1 Lower confidence limit:

[0146] The reliability value R of the static strength under torsional load S1 The first lower confidence limit is calculated by the following formula:

[0147]

[0148] In the formula, Φ represents the standard normal distribution function, and γ is the confidence level.

[0149] For the inventive concept with the same calculation method as above, for step S5, re-evaluate the reliability R of the static strength of the applied load S2 ;

[0150] Obtain the mean value of the second applied load force values of the diverse group, which is achieved by the following formula:

[0151]

[0152] In the formula, F 2,i is the second applied load force value, is the mean value of the second applied load force values, and n is the sample number of the second applied load force values;

[0153] Obtain the standard deviation of the second applied load force values of the diverse group, which is achieved by the following formula:

[0154]

[0155] In the formula, σ F2 is the standard deviation of the second applied load force values;

[0156] The second mean strength is achieved by the following formula:

[0157]

[0158] In the formula, μ S2 is the second mean strength under the test conditions; C S2 is the strength coefficient of variation, u γ is the normal probability coefficient;

[0159] The strength coefficient of variation C S2 is obtained by the following formula:

[0160]

[0161] The reliability value R of the static strength of the applied load S2The second lower confidence limit is calculated by the following formula:

[0162]

[0163] In the formula, Φ represents the standard normal distribution function, and γ is the confidence level.

[0164] During the reliability assessment, considering the influence of factors such as the design and processing cycle, test funds, and test time, generally, a large sample is not used to conduct the static strength test of the gas rudder control mechanism. Therefore, this test belongs to a small-sample reliability test. Thus, the processing method for small-sample problems of structural strength reliability is adopted for reliability assessment. In this embodiment, two tests, S1 and S2, are successively carried out on n (n≥5) sets of gas rudder control mechanisms.

[0165] Based on the analysis of the working characteristics and failure modes of the gas rudder control mechanism, considering the two failure modes as a series model, the reliability R calculation formula of the gas rudder control mechanism is:

[0166] R = R S1 ·R S2 (11)

[0167] In the formula, R S1 is the static strength reliability value under torsional load, and R S2 is the static strength reliability value under service load.

[0168] When evaluating the reliability of the entire set of gas rudder control mechanisms, substituting Equation (5) and Equation (10) into Equation (11), the lower confidence limit of the reliability of the gas rudder control mechanism is obtained:

[0169]

[0170] In practical engineering applications, the dispersions of the maximum load torque and the maximum service load can be not considered, and the tolerance limits of the above two performance parameters are given as a fixed value, that is, the standard deviations σ L1 and the standard deviation σ L2 are both taken as 0. At this time, Equation (12) can be simplified to:

[0171]

[0172] With the same inventive concept as the above-mentioned static strength test method of the gas rudder control mechanism, in the second aspect, an embodiment also discloses a static strength test system for a gas rudder control mechanism;

[0173] Combined with Figure 2 as shown, the static strength test system of the gas rudder control mechanism consists of a hydraulic loading device and the gas rudder control mechanism 3 and tooling. The hydraulic loading device includes a test platform 1, a bearing column 2, and a horizontal hydraulic cylinder 4.

[0174] The gas rudder control mechanism 3 and the bearing columns are placed on the test platform 1. The bearing columns 2 are located on both sides of the test platform 1, and the gas rudder control mechanism 3 is located between the bearing columns 2 on both sides. The horizontal hydraulic cylinder 4 is fixed on the bearing column 2, parallel to the test platform 1. The horizontal hydraulic cylinder 4 is connected to the gas rudder control mechanism 3 to apply a tensile force to the gas rudder control mechanism 3.

[0175] By analyzing the working characteristics of the gas rudder control mechanism as above, two failure modes can be obtained: one is that the gas rudder control mechanism is damaged under the action of the load torque; the other is that the strength of the load-bearing parts of the gas rudder control mechanism fails under the action of the axial force.

[0176] The hydraulic loading device may also include bearing columns, anchor bolts, hydraulic actuators, chains, tension sensors, ball joint connectors, double-ear connectors, etc., mainly to provide simulated loads for the gas rudder control mechanism. The bearing columns are fixed on the test bench base through 4 anchor bolts to provide installation and support conditions for the hydraulic actuators. One end of the hydraulic actuator is fixed on the bearing column by 4 screws through an adapter joint, and the other end is connected to the tension sensor through a stud bolt to ensure that the loading direction of the hydraulic actuator is in the same horizontal position as the axis of the upper hole of the simulated rudder shaft. Then, the hydraulic actuator is held in this position by a chain; at the same time, the other end of the tension sensor is connected to the double-ear connector through a stud bolt. After the double-ear connector and the single-ear connector are connected by bolts, the tail screw of the single-ear connector is connected to one end of the ball joint connector, and the other end of the ball joint connector is connected to the screw passing through the upper end of the simulated rudder surface. Furthermore, the hydraulic actuator is limited by the chain to keep the hydraulic actuator in a horizontal state. In this way, the hydraulic loading device and the gas rudder control mechanism simulation device are completed in cooperation, and the loading of the control mechanism can be realized. When the control mechanism reaches the failure limit, the simulated rudder surface will deflect. At this time, this connection method of the ball joint connector cooperating with the single ear can play a certain protective role for the hydraulic cylinder.

[0177] Since the gas rudder surface generates normal force and axial force under the engine jet flow, and the normal force forms a hinge moment on the rudder shaft. When the gas rudder deflects to the limit position, the normal force of the rudder surface is the largest, and the hinge moment value generated at this time is also the largest. The load torque of the gas rudder servo mechanism is usually determined according to the maximum hinge moment value of the rudder surface under the aerodynamic load. Therefore, the gas rudder control mechanism should ensure that it does not break under the requirement of the maximum load torque. At the same time, the axial force is applied to the load-bearing parts such as bearings, supports, and bolts in the gas rudder control mechanism, and the strength of these load-bearing parts should meet the reliability requirements.

[0178] Among them, as an independent mechanism of the present invention and relying on the static strength test system.

[0179] Combined with Figures 3 - 9As shown in the figure, the gas rudder control mechanism includes a mounting base 301, a rudder surface 302, a heat-insulating partition 303, a support 304, a first fixing bolt 305, a second fixing bolt 306, a first connecting bolt 307, a first spherical plain bearing 308, a control rod 309, a second connecting bolt 310, a second spherical plain bearing 311, a rocker arm 312, a taper pin 313, a first through hole 3011, a second through hole 3012, a third through hole 3013, a fourth through hole 3014, a first threaded hole 3015, a second threaded hole 3016, a bearing mounting groove 3017, a bearing mounting hole 3018, a fifth through hole 3021, a sixth through hole 3022, a seventh through hole 3023, a tapered hole 3024, a first mounting bearing 314, a second mounting bearing 315, and a rudder shaft 316.

[0180] The holes at both ends of the rudder surface 302 are connected to horizontal hydraulic cylinders 4 in different directions. The support 304 is located on the mounting base 301. A rudder shaft connected to the rudder surface 302 is provided on the support 304. The rudder shaft 316 is connected to the rocker arm 312. The rocker arm 312 is connected to one end of the control rod 309, and the other end of the control rod 309 is connected to the mounting base 301.

[0181] The mounting base 301 is connected to the test bench through 4 through holes; the support 304 is connected to the first threaded hole 3015 and the second threaded hole 3016 of the mounting base 301 by bolts; the first mounting bearing 314 and the second mounting bearing 315 are installed on the support 304, and the rudder shaft 316 simulating the rudder surface 302 passes through the heat-insulating partition 303, the rocker arm 312, the first mounting bearing 314, and the second mounting bearing 315; the first spherical plain bearing 308 is installed in the bearing mounting hole 3018 of the mounting base, and the second spherical plain bearing 311 is installed on the rocker arm 312; both ends of the control rod 309 pass through the inner rings of the first and second spherical plain bearings through the first and second connecting bolts respectively; the rocker arm 312 is fitted with the rudder shaft taper pin through the taper pin with screwed tail 313; the distance between the 3 through holes of the rudder surface 302 is 50 mm. The upper and lower holes are used to apply torque, and the middle hole is used to apply axial force.

[0182] A certain angle θ is designed between the upper mounting surface of the mounting base 301 and the horizontal plane to simulate the extreme deflection state of the gas rudder control mechanism 3; a bearing mounting groove 3017 is provided at the protruding position of the control rod 309, a vertical rib is provided at the bottom of the groove, and a bearing mounting hole 3018 is provided for installing the first spherical plain bearing 311 to simulate the actual installation state.

[0183] In the present invention, a static strength test is carried out on the gas rudder control mechanism under the application of torsional load and service load. The static strength under two failure modes is tested. By applying load to the gas rudder control mechanism, the bearing capacity of the components of the gas rudder control mechanism is detected, whether the components meet the required force conditions can be obtained, and when the maximum tolerable static strength value at which the components are damaged is further tested, the ultimate bearing capacity of the stressed components can be known.

[0184] The static strength test system of the gas rudder control mechanism of the present invention can fully simulate the actual working conditions of the gas rudder, ensuring the accuracy and objectivity of the test boundary conditions; and it is easy to install, can improve the operation efficiency and save labor costs; the static strength test method of the gas rudder control mechanism of the present invention is simple and reliable, meeting the engineering requirements for the reliability assessment of the gas rudder control mechanism. The reliability of the static strength value is evaluated through a mathematical model, and the reliability characteristic quantities of the gas rudder control mechanism can be determined through test measurement, providing a reasonable means for assessing the ultimate bearing capacity of the gas rudder control mechanism and solving the problem of the reliability assessment of the gas rudder control mechanism.

[0185] It should be noted that some embodiments of the present application are described above. Other embodiments are within the scope of the appended claims. In some cases, the structures or connection manners recited in the claims can be implemented differently from those described in the above embodiments and still achieve the desired results. Additionally, the structures depicted in the drawings do not necessarily require the specific structures shown to achieve the desired results.

[0186] Those of ordinary skill in the art should understand that: the discussion of any above embodiments is only exemplary and is not intended to imply that the scope of the present application (including the claims) is limited to these examples; under the concept of the present application, the technical features between the above embodiments or different embodiments can also be combined, the steps can be implemented in any order, and there are many other variations in different aspects of the embodiments of the present application as described above, which are not provided in detail for the sake of brevity.

[0187] In addition, for the sake of simplifying the description and discussion and in order not to make the embodiments of the present application difficult to understand, although the present application has been described in conjunction with specific embodiments of the present application, many substitutions, modifications, and variations of these embodiments will be obvious to those of ordinary skill in the art based on the foregoing description.

[0188] The embodiments of the present application are intended to cover all such substitutions, modifications, and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the embodiments of the present application shall be included within the protection scope of the present application.

Claims

1. Static strength test method for a gas rudder control mechanism, characterized in that, The gas rudder control mechanism includes a mounting base, a rudder surface, a support, a rocker arm, and a control rod. The holes at both ends of the rudder surface are connected to horizontal hydraulic cylinders in different directions. The support is located on the mounting base. A rudder shaft connected to the rudder surface is provided on the support. The rudder shaft is connected to the rocker arm. One end of the rocker arm is connected to the control rod, and the other end of the control rod is connected to the base. The method includes: Obtaining a first static strength value of the gas rudder control mechanism under torsional load; wherein, the first static strength value includes a first load torque value and a second load torque value. Then, obtaining the first static strength value of the gas rudder control mechanism under torsional load includes the following steps: Obtaining the first load torque value; wherein, the first load torque value is generated based on the specification parameters of the gas rudder control mechanism; Controlling the hydraulic cylinders to apply first tensile forces in different directions to both ends of the rudder surface, and gradually increasing the first tensile forces to the first load torque value; Unloading the first tensile forces and checking the working conditions of the rocker arm and the control rod; When it is determined that the working conditions of the rocker arm and the control rod are damaged, it is determined that the gas rudder control mechanism does not meet the basic static strength requirements under torsional load; When it is determined that the working conditions of the rocker arm and the control rod are normal, continue to apply the first tensile forces until the working conditions of the rocker arm and the control rod are damaged, unload the first tensile forces, and record the first tensile forces at this time as the second load torque value; Obtaining a second static strength value of the gas rudder control mechanism under service load; wherein, the second static strength value includes a first service load force value and a second service load force value. Then, obtaining the second static strength value of the gas rudder control mechanism under service load includes the following steps: Adjusting the horizontal height of the hydraulic cylinders so that the horizontal height of the axis of the hydraulic cylinders is at the same horizontal line as the height of the middle hole of the rudder surface; Obtaining the first service load force value; wherein, the first service load force value is the second tensile force applied by the hydraulic cylinders to the rudder surface in the axial direction, and the second tensile force is obtained through a gas rudder force measurement test; Unloading the second tensile force and checking the working conditions of the mounting bearings connected to the support and the rudder shaft; When it is determined that the mounting bearings connected to the support and the rudder shaft are damaged, it is determined that the gas rudder control mechanism does not meet the basic static strength requirements under service load; When it is determined that the working conditions of the mounting bearings connected to the support and the rudder shaft are normal, continue to apply the second tensile force until the mounting bearings connected to the support and the rudder shaft are damaged, unload the second tensile force, and record the second tensile force at this time as the second service load force value; Establishing a reliability mathematical model based on the first static strength value and the second static strength value; Generating a first static strength reliability value according to the reliability mathematical model; Generating a second static strength reliability value according to the reliability mathematical model.

2. The static strength test method according to claim 1, characterized in that The generating the first static strength reliability value according to the reliability mathematical model includes the following steps: Collecting multiple groups of the second load torque values and the second service load force values; Evaluating and generating a torsional load static strength reliability value according to the second load torque values; Evaluate and generate the static strength reliability value of the service load according to the second service load force value; Generate the reliability value of the gas rudder control mechanism according to the static strength reliability value of the torsional load and the static strength reliability value of the service load.

3. The static strength test method according to claim 2, wherein The step of evaluating and generating the static strength reliability value of the torsional load according to the second load torque value further includes the following steps: Obtain the mean and standard deviation of multiple groups of the second load torque values; Establish a mathematical model to obtain the first strength mean and the first stress mean; Calculate the first confidence lower limit according to the first strength mean and the first stress mean.

4. The static strength test method according to claim 3, characterized in that, The step of evaluating and generating the static strength reliability value of the torsional load according to the second load torque value is implemented according to the following steps: Obtain the mean of multiple groups of the second load torque values, which is achieved by the following formula: ； In the formula, P 2,i is the second load torque value, is the mean value of the second load torque value, n is the number of samples of the second load torque value; Obtain the standard deviation of multiple groups of the second load torque values, which is achieved by the following formula: ； In the formula, P 2,i is the second load torque value, is the mean value of the second load torque value, σ P2 is the standard deviation of the second load torque value, and n is the number of samples of the second load torque value; The first strength mean is achieved by the following formula: ； Wherein, μ S1 is the first strength mean value under test conditions; C S1 is the coefficient of variation of strength, u γ is the normal probability coefficient; Coefficient of variation of strength C S1 Obtained by the following formula: ； Static strength reliability value R of torsional load S1 The first confidence lower limit is calculated by the following formula: ； where Φ represents the standard normal distribution function, γ is the confidence level.

5. The static strength test method according to claim 3, characterized in that, The step of evaluating and generating the static strength reliability value of the service load according to the second service load force value further includes the following steps: Obtain the mean and standard deviation of multiple groups of the second service load force values; Establish a mathematical model to obtain the second strength mean and the second stress mean; Calculate the second confidence lower limit according to the second strength mean and the second stress mean.

6. The static strength test method according to claim 5, characterized in that, The step of evaluating and generating the static strength reliability value of the service load according to the second service load force value is implemented according to the following steps: Obtain the mean of multiple groups of the second service load force values, which is achieved by the following formula: ； In the formula, F 2,i is the second service load force value, is the mean value of the second service load force value, n is the number of samples of the second service load force value; Obtain the standard deviation of multiple groups of the second service load force values, which is achieved by the following formula: ； In the formula, σ F2 is the standard deviation of the second service load force value; The second strength mean is achieved by the following formula: ； In the formula, μ S2 is the second strength mean value under test conditions; C S2 is the coefficient of variation of strength, u γ is the normal probability coefficient; Coefficient of variation of strength C S2 Obtained by the following formula: ； The second confidence lower limit of the static strength reliability value R of the service load is calculated by the following formula: S2 ​ ； In the formula, Φ represents the standard normal distribution function, and γ is the confidence level.

7. According to the static strength test method described in claim 6, the step of generating the reliability value of the gas rudder control mechanism according to the static strength reliability value of the torsional load and the static strength reliability value of the service load includes the following steps: The reliability value of the gas rudder control mechanism is calculated based on the following formula: Wherein, R γ is the reliability value of the gas rudder control mechanism, R γ,S1 is the reliability value of the static strength under torsional load, R γ，S2 is the reliability value of the static strength under service load.

8. A static strength test system for a gas rudder control mechanism for implementing the static strength test method of the gas rudder control mechanism described in any one of claims 1 to 7, characterized in that: It includes a gas rudder control mechanism, a test platform, load-bearing columns, and a horizontal hydraulic cylinder; The gas rudder control mechanism and the load-bearing columns are placed on the test platform. The load-bearing columns are located on both sides of the test platform. The gas rudder control mechanism is located between the load-bearing columns on both sides. The horizontal hydraulic cylinder is fixed on the load-bearing columns. The horizontal hydraulic cylinder is parallel to the test platform. The horizontal hydraulic cylinder is connected to the gas rudder control mechanism to apply a pulling force to the gas rudder control mechanism.

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