Aero-engine lubricating oil system attitude analysis method and device

Abstract

The invention belongs to the technical field of aero-engines, and provides an attitude analysis method and device for a lubricating oil system of an aero-engine, and the method comprises the steps: obtaining a set working state of a to-be-detected engine lubricating oil part, and correspondingly building an engine lubricating oil part model; building an aircraft positioning coordinate system based on the engine lubricating oil component model; the flight state parameters are obtained for corresponding airplane stress analysis; the lubricating oil liquid level height of the aircraft is obtained, and the mapping relation between the flight state parameters and the lubricating oil liquid level is constructed; actual flight state parameters are obtained, and the matching relation between the actual lubricating oil liquid level and an engine of the to-be-tested aircraft is obtained; and analyzing the lubricating oil system of the to-be-tested aircraft based on the matching relationship. According to the method, a coordinate conversion and overload synthesis method and stress analysis are adopted, the mapping relation between the flight state parameters and the lubricating oil liquid level is established, determination of the lubricating oil liquid level is achieved, and analysis of the attitude of the lubricating oil system is achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aeroengines, and particularly relates to a method and device for attitude analysis of an aeroengine lubricating oil system. Background Art

[0002] The lubricating oil system of an aeroengine undertakes key lubricating and cooling functions during flight. During the design, testing, and maintenance of an aeroengine, it is necessary to evaluate the performance of the lubricating oil system under different flight attitudes.

[0003] Currently, the attitude analysis method for the aeroengine lubricating oil system mainly adopts the line marking analysis method. Its basic principle is to place the engine according to the attitude angle, assume that the liquid level is horizontal without change, and observe at the oil return port to evaluate whether the lubricating oil can completely enter the oil return port. If it cannot enter the oil return port, evaluate whether the remaining oil submerges the bearings, gears, dynamic sealing devices, or leaks from the driven sealing device.

[0004] However, the above method does not consider that during actual flight, with the changes of flight state parameters such as the aircraft attitude angle and three-axis overload, the liquid level position and shape of the lubricating oil in lubricating oil components such as the aeroengine lubricating oil tank and oil sump are distorted, nor does it consider the change of the liquid level in the fuel tank caused by the hidden amount of the lubricating oil chamber due to the system-level circulation of the lubricating oil system, and thus cannot perform system-level continuous dynamic attitude analysis.

[0005] In view of this, overcoming the defects of the above-mentioned prior art is an urgent problem to be solved in this technical field. Summary of the Invention

[0006] In view of the above problems, the present invention proposes a method for attitude analysis of an aeroengine lubricating oil system, including the following steps:

[0007] Obtain the set working state of the engine lubricating oil components to be measured, and correspondingly establish an engine lubricating oil component model;

[0008] Construct an aircraft positioning coordinate system based on the engine lubricating oil component model;

[0009] Obtain flight state parameters, and perform corresponding aircraft force analysis in combination with the aircraft positioning coordinate system;

[0010] Obtain the lubricating oil liquid level height of the aircraft based on the aircraft force analysis, and further construct the mapping relationship between the flight state parameters and the lubricating oil liquid level;

[0011] Obtain the actual flight state parameters, obtain the actual lubricating oil liquid level based on the mapping relationship, and further obtain the matching relationship between the actual lubricating oil liquid level and the engine of the aircraft to be measured;

[0012] Analyze the lubricating oil system of the aircraft to be measured based on the matching relationship.

[0013] Furthermore, the aircraft positioning coordinate system is constructed based on the engine lubricating oil component model, which specifically includes the following steps:

[0014] Based on the engine lubricating oil component model, the aircraft vertical coordinate system, the aircraft body coordinate system, and the engine model coordinate system are constructed respectively;

[0015] Calculate the conversion relationship between the aircraft plumb coordinate system, aircraft body coordinate system, and engine model coordinate system.

[0016] Furthermore, the flight status parameters specifically include: attitude angle, synthetic comprehensive overload coefficient and relative position of the aircraft and engine;

[0017] Attitude angles include: yaw angle, pitch angle, and roll angle;

[0018] The synthetic comprehensive overload coefficient includes: three-way overload, three-way angular velocity, three-way angular acceleration, turning radius, and flying engine center of mass distance.

[0019] Furthermore, the engine lubricating oil component includes a tank component and a mating component. The lubricating oil level of the aircraft is obtained based on the aircraft force analysis, specifically including the following steps:

[0020] Obtain the normal vector direction of the lubricating oil surface based on aircraft force analysis;

[0021] Selecting the liquid surface direction of the mating component based on the normal vector direction of the lubricating oil surface;

[0022] The liquid level direction of the mating component is brought into the engine lubricating oil component model, and the maximum hidden amount of lubricating oil in the mating component is calculated as the liquid level height of the mating component;

[0023] Obtain the maximum oil filling volume and lubricating oil consumption of the oil tank components;

[0024] The difference between the maximum oil filling amount of the selected tank component, the lubricating oil consumption of the tank component, and the maximum hidden amount of the matching component is taken as the remaining oil amount of the tank component;

[0025] The remaining oil volume of the oil tank component is brought into the engine lubricating oil component model, and the liquid level height of the oil tank component is calculated as the lubricating oil level height.

[0026] Furthermore, the maximum amount of oil hidden in the mating component is calculated, which specifically includes the following steps:

[0027] Bring the liquid surface direction of the mating component into the engine lubricating oil component model, draw the initial liquid surface at the lowest point of the oil return port of the mating component, and obtain the oil volume corresponding to the initial liquid surface as the initial oil volume of the mating component;

[0028] Obtain the oil supply amount and time step of the matching component, and take the product of the oil supply amount and the time step as the increase amount of the matching component;

[0029] Take the sum of the initial oil quantity of the mating component and the increase in the mating component as the maximum concealment quantity of the mating component.

[0030] Furthermore, obtaining the matching relationship between the actual lubricating oil level and the engine of the aircraft to be tested includes the following steps:

[0031] Obtain the specification parameters of the engine and set the altitude range;

[0032] When the liquid level height of the actual lubricating oil level belongs to the altitude range, it is determined that the matching relationship is healthy;

[0033] When the liquid level height of the actual lubricating oil level is lower than or exceeds the altitude range, calculate the ultimate working duration of the engine, and obtain the ultimate working duration in combination with the specification parameters of the engine;

[0034] When the ultimate working duration is greater than the ultimate working duration, it is determined that the matching relationship is healthy;

[0035] When the ultimate working duration is less than the ultimate working duration, it is determined that the matching relationship is unhealthy.

[0036] Furthermore, evaluating the lubricating oil system of the aircraft to be tested based on the matching relationship specifically includes the following steps:

[0037] When it is determined that the matching relationship is healthy, it is judged that the lubricating oil system of the aircraft to be tested is qualified.

[0038] When it is determined that the matching relationship is unhealthy, it is judged that the lubricating oil system of the aircraft to be tested is unqualified.

[0039] The present invention also proposes an attitude analysis device for an aero-engine lubricating oil system, including:

[0040] A data acquisition unit for acquiring the set working state of the engine lubricating oil components to be tested and correspondingly establishing an engine lubricating oil component model;

[0041] A first construction unit for constructing an aircraft positioning coordinate system based on the engine lubricating oil component model;

[0042] A first analysis unit for acquiring flight state parameters and performing corresponding aircraft force analysis in combination with the aircraft positioning coordinate system;

[0043] A second construction unit for obtaining the lubricating oil level of the aircraft based on the aircraft force analysis, and further constructing a mapping relationship between the flight state parameters and the lubricating oil level;

[0044] A second analysis unit for acquiring the actual flight state parameters, obtaining the actual lubricating oil level based on the mapping relationship, and further obtaining the matching relationship between the actual lubricating oil level and the engine of the aircraft to be tested;

[0045] A judging unit for analyzing the lubricating oil system of an aircraft to be tested based on the matching relationship.

[0046] Furthermore, the first construction unit is specifically used for:

[0047] Constructing an aircraft vertical coordinate system, an aircraft body coordinate system, and an engine model coordinate system respectively based on the engine lubricating oil component model;

[0048] Calculating the conversion relationships between the aircraft vertical coordinate system, the aircraft body coordinate system, and the engine model coordinate system.

[0049] Furthermore, the engine lubricating oil components include a fuel tank component and a mating component. The second construction unit is specifically used for:

[0050] Obtaining the normal vector direction of the lubricating oil liquid surface based on the force analysis of the aircraft;

[0051] Selecting the liquid surface direction of the mating component based on the normal vector direction of the lubricating oil liquid surface;

[0052] Substituting the liquid surface direction of the mating component into the engine lubricating oil component model to calculate the maximum hidden amount of lubricating oil in the mating component as the liquid level height of the mating component;

[0053] Obtaining the maximum fuel injection amount and the lubricating oil consumption of the fuel tank component;

[0054] Selecting the difference between the maximum fuel injection amount of the fuel tank component and the lubricating oil consumption of the fuel tank component and the maximum hidden amount of the mating component as the remaining oil amount of the fuel tank component;

[0055] Substituting the remaining oil amount of the fuel tank component into the engine lubricating oil component model to calculate the liquid level height of the fuel tank component as the lubricating oil liquid surface height, and then constructing the mapping relationship between the flight state parameters and the lubricating oil liquid surface.

[0056] Compared with the prior art, the embodiments of the present invention have at least the following advantages:

[0057] On the basis of introducing the flight state parameters in actual flight, the present invention adopts the coordinate transformation and overload synthesis methods, and then based on the force analysis, establishes a one-to-one mapping relationship between the flight state parameters and the lubricating oil liquid surface. Based on the normal vector of the lubricating oil liquid surface, according to the oil supply amount and time of lubricating oil components such as bearing chambers, reducers, and fuel tanks, calculate the oil amount in the lubricating oil component cavity at each moment, and determine the liquid level height accordingly to realize the determination of the lubricating oil liquid surface; then based on the relative positions of the lubricating oil liquid surface and components such as the oil return port and the oil supply port, judge the working state of the lubricating oil components, thereby judging the working state of the engine and realizing the analysis of the attitude of the lubricating oil system.

[0058] Other features and advantages of the present invention will be set forth in the following description, and in part will be obvious from the description, or may be learned by practice of the present invention. The objectives and other advantages of the present invention may be realized and attained by the structure particularly pointed out in the specification and the drawings. Brief Description of the Drawings

[0059] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following briefly introduces the drawings required for describing the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0060] Figure 1 Fig. shows a schematic diagram of the attitude analysis method for the lubricating oil system of an aeroengine in an embodiment of the present invention;

[0061] Figure 2 Fig. shows a structural block diagram of the attitude analysis device for the lubricating oil system of an aeroengine in an embodiment of the present invention;

[0062] Figure 3 Fig. shows a partial flow schematic diagram of the attitude analysis method for the lubricating oil system of an aeroengine in an embodiment of the present invention. Detailed Embodiments

[0063] The following description provides many different embodiments or examples for implementing different features of the present invention. The elements and arrangements described in the following specific examples are only used to concisely express the present invention, and are only examples, not intended to limit the present invention.

[0064] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following clearly and completely describes the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0065] It should be noted that the aircraft attitude envelope refers to the maximum range that the state parameters of the aircraft (the aircraft state parameters include attitude angle, three-axis overload, three-axis angular velocity, three-axis angular acceleration, turning radius, and distance from the aircraft's center of mass) can reach during flight, that is, the limit range of the attitude change of the aircraft under different flight states.

[0066] The engine attitude envelope refers to the normal operating range of the engine under different flight states and operating conditions.

[0067] The present invention provides a method for attitude analysis of an aero-engine lubricating oil system. Figure 1 The flow schematic diagram of the method for attitude analysis of an aero-engine lubricating oil system in an embodiment of the present invention is shown. Refer to Figure 1 and Figure 3 , the method for attitude analysis of an aero-engine lubricating oil system includes the following steps:

[0068] S101. Obtain the set working state of the engine lubricating oil components at the location to be measured, and correspondingly establish an engine lubricating oil component model;

[0069] Among them, the lubricating oil components include a fuel tank component and a mating component; correspondingly, the fuel tank component represents the engine fuel tank, and the mating components include, but are not limited to, the bearing cavity and the reducer inside the engine, etc.

[0070] Therefore, the number of engine lubricating oil component models is multiple, including: an engine fuel tank component model, an engine mating component model; among them, the engine mating component model further includes: an engine bearing cavity model, an engine reducer model, etc. The lubricating oil components are common knowledge for those skilled in the art and will not be further expanded here.

[0071] S102. Construct an aircraft positioning coordinate system based on the engine lubricating oil component model;

[0072] Specifically, based on multiple engine lubricating oil component models, an aircraft vertical coordinate system, an aircraft body coordinate system, and an engine model coordinate system are respectively constructed;

[0073] And calculate the conversion relationship for numerical conversion between the aircraft vertical coordinate system, the aircraft body coordinate system, and the engine model coordinate system;

[0074] The aircraft vertical coordinate system is used to describe the height change of the aircraft in the vertical direction;

[0075] The aircraft body coordinate system of the aircraft is a reference system relative to the aircraft itself and is used to describe the maneuvering actions of the aircraft;

[0076] The engine model coordinate system is used to describe the specific position of the engine and its state relative to other parts of the aircraft.

[0077] Through the conversion relationship, the physical quantities between different coordinate systems are converted to facilitate the unified comparison of data.

[0078] S103. Obtain the flight state parameters, and perform corresponding aircraft force analysis in combination with the aircraft positioning coordinate system;

[0079] In engineering applications, the operating conditions of an aircraft are commonly described by steady pitching, sharp pitching, yaw maneuver, roll maneuver, vertical gust, and lateral overload, etc. After refinement, these operating conditions can all be described by flight state parameters. Flight state parameters include attitude angles, combined comprehensive overload factor, and the relative position between the engine and the aircraft; attitude angles include: yaw angle, pitch angle, roll angle; the combined comprehensive overload factor includes: three-directional overload, three-directional angular velocity, three-directional angular acceleration, turning radius, and the distance from the aircraft's center of mass.

[0080] Among them, the attitude angles and the combined comprehensive overload factor are defined and given in the aircraft body coordinate system;

[0081] In the process of constructing the aircraft positioning coordinate system based on the engine lubricating oil component model, the fuel tank, bearing cavity, fuel tank oil supply port, bearing cavity oil return port, reducer, etc. are defined and given in the engine model coordinate system;

[0082] The relative position between the engine and the aircraft and the aircraft's own gravity are defined in the aircraft vertical coordinate system;

[0083] The final conversion relationship is calculated and completed in the aircraft body coordinate system.

[0084] S104. Obtain the lubricating oil liquid level height of the aircraft based on the aircraft force analysis, and then construct the mapping relationship between the flight state parameters and the lubricating oil liquid level;

[0085] Among them, the specific steps to obtain the lubricating oil liquid level height of the aircraft based on the aircraft force analysis are as follows:

[0086] Obtain the normal vector direction of the lubricating oil liquid level based on the aircraft force analysis;

[0087] Determine the tangential direction of the lubricating oil liquid level of the mating component based on the normal vector direction of the lubricating oil liquid level, and select the tangential direction of the lubricating oil liquid level of the mating component as the liquid level direction of the mating component;

[0088] Substitute the liquid level direction of the mating component into the engine lubricating oil component model, draw the initial liquid level at the lowest point of the oil return port of the mating component, and obtain the oil quantity corresponding to the initial liquid level as the initial oil quantity h1 of the mating component;

[0089] Obtain the oil supply quantity △h and time step t of the mating component, and take the product of the oil supply quantity △h and time step t as the increase amount △H of the mating component;

[0090] Take the sum of the initial oil quantity h1 of the mating component and the increase amount △H of the mating component as the maximum concealment amount H of the mating component 隐 , which is expressed by the formula:

[0091] H 隐 = h1 + △h * t (1)

[0092] In the formula, H 隐It represents the maximum concealment volume of the mating components, h1 represents the initial oil volume of the mating components, △h represents the oil supply volume of the mating components, and t represents the time step.

[0093] It should be supplemented and explained that the mating components here include each non-tank component; for example, taking the mating components including the bearing chamber and the reducer as an example for explanation; then the sum of the maximum concealment volume of the bearing chamber and the maximum concealment volume of the reducer should be used as the maximum concealment volume of the mating components.

[0094] Set the maximum concealment volume of the mating components as the liquid level height of the mating components.

[0095] At the same time, obtain the maximum fuel injection volume H of the fuel tank component 注 and the lubricating oil consumption H of the fuel tank component 消 ;

[0096] Select the maximum fuel injection volume H of the fuel tank component 注 and the lubricating oil consumption H of the fuel tank component 消 , the difference between the maximum concealment volume H of the mating components 隐 is used as the remaining oil volume H of the fuel tank component, and the formula is expressed as:

[0097] H = H 注 - H 消 - H 隐 (2)

[0098] In the formula, H represents the remaining oil volume of the fuel tank component, H 注 represents the maximum fuel injection volume of the fuel tank component, H 消 represents the lubricating oil consumption of the fuel tank component, H 隐 represents the maximum concealment volume of the mating components.

[0099] Substitute the remaining oil volume of the fuel tank component into the engine lubricating oil component model, and calculate the liquid level height of the fuel tank component as the lubricating oil liquid level height of the aircraft lubricating oil system.

[0100] S105. Obtain the actual flight state parameters, obtain the actual lubricating oil liquid level based on the mapping relationship, and then obtain the matching relationship between the actual lubricating oil liquid level and the engine attitude envelope, refer to Figure 1 , specifically:

[0101] Obtain the specification parameters of the engine, including obtaining the heights of the oil return port, oil supply port, ventilation hole, bearing gear, and sealing device in the engine, and then set the height range.

[0102] For further explanation, compare the heights of the oil return port, oil supply port, ventilation hole, bearing gear, and sealing device with the liquid level height of the actual lubricating oil liquid level;

[0103] Judge according to the continuous working criterion. When the liquid level height of the actual lubricating oil surface is higher than the height of the oil return port, lower than the height of the oil supply port, lower than the height of the ventilation hole, higher than the height of the bearing gear, and lower than the height of the sealing device, it indicates that the liquid level height of the actual lubricating oil surface belongs to the height category, and the matching relationship between the actual lubricating oil surface and the engine attitude envelope is judged to be healthy. That is, it means that under the current actual flight state parameter requirements, the aircraft engine and the lubricating oil system meet the continuous working requirements and are marked as the continuous blank area attitude envelope.

[0104] It should be noted that the liquid level height of the actual lubricating oil surface is higher than the height of the oil return port to meet the requirement of the lubricating oil reflux operation in the lubricating oil system;

[0105] The liquid level height of the actual lubricating oil surface is lower than the height of the oil supply port to avoid the problem of reverse flow of the lubricating oil in the lubricating oil system. Exemplarily, the height difference is 25.4 mm.

[0106] The liquid level height of the actual lubricating oil surface is lower than the height of the ventilation hole to avoid the problem of reverse flow of the lubricating oil in the ventilation hole;

[0107] The liquid level height of the actual lubricating oil surface is higher than the height of the bearing gear to achieve the immersion of the lubricating oil in the bearing gear to ensure the lubrication of the bearing gear;

[0108] The liquid level height of the actual lubricating oil surface is lower than the height of the sealing device to avoid the leakage of the lubricating oil from the sealing device.

[0109] When the liquid level height of the actual lubricating oil surface is lower than or exceeds the height category, calculate the limit working duration of the engine. It should be noted that the required limit working durations of different models of engines are different. The limit working duration of a conventional engine is 30 s or 20 s or 10 s.

[0110] Judge according to the limit working criterion. When the limit working duration is greater than the limit working duration, it is judged that the matching relationship is healthy, that is, it means that under the current actual flight state parameter requirements, the aircraft engine and the lubricating oil system cannot meet the continuous working requirements, but meet the limit working duration requirements and are marked as the shaded area attitude envelope.

[0111] Judge according to the limit working criterion. When the limit working duration is less than the limit working duration, it is judged that the matching relationship is unhealthy, that is, it means that under the current actual flight state parameter requirements, the aircraft engine and the lubricating oil system cannot meet the continuous working requirements and cannot meet the limit working duration requirements either.

[0112] S106. Evaluate the lubricating oil system of the aircraft to be tested based on the matching relationship, specifically:

[0113] When it is determined that the matching relationship is healthy, the lubricating oil system of the aircraft to be tested is judged to be qualified.

[0114] When it is determined that the matching relationship is unhealthy, the lubricating oil system of the aircraft to be tested is judged to be unqualified.

[0115] The present invention proposes here to obtain 12 relevant parameters, specifically including: yaw angle, pitch angle, roll angle in the attitude angle; three-way overload, three-way angular velocity, three-way angular acceleration, turning radius, distance from the aircraft's mass center to the engine in the synthetic comprehensive overload coefficient; relative position between the aircraft and the engine, as well as the aircraft's vertical coordinate system, aircraft body coordinate system, and engine model coordinate system. Based on these 12 relevant parameters, the aircraft's force analysis is carried out by substituting them into the engine lubricating oil component model, and then the corresponding lubricating oil liquid level of the aircraft is obtained. Combining with the matching relationship with the engine of the aircraft to be tested, the operating state of the lubricating oil system is evaluated.

[0116] Based on the above technical solution principle, the technical solution of the present invention is further expanded.

[0117] Among the 12 relevant parameters, any 11 relevant parameters can be obtained, and the 12th relevant parameter is deduced according to the constraint conditions of the matching relationship of the engine of the aircraft to be tested and the already determined engine lubricating oil component model.

[0118] Reference Figure 1 , for specific illustration, given any 11 of the 12 relevant parameters, calculate the range of the remaining 12th parameter. Taking the calculation of the Z-direction overload range in the three-way overload as an example, the detailed calculation method is as follows:

[0119] Given the aircraft's yaw angle, pitch angle, roll angle, three-way angular velocity, three-way angular acceleration, turning radius, distance from the aircraft's mass center to the engine, and the X-direction overload range and Y-direction overload range in the three-way overload;

[0120] According to the aircraft's usage scenario, a preliminary value of the Z-direction overload is given, forming a complete set of aircraft flight parameters with the known 11 relevant parameters, and calculating the corresponding lubricating oil liquid level.

[0121] According to the matching relationship between the lubricating oil liquid level and the engine of the aircraft to be tested, obtain the envelope area where the lubricating oil system does not meet the continuous operation requirement;

[0122] Based on the lubricating oil liquid level calculated according to the preliminary value of the Z-direction overload, and judge whether the lubricating oil liquid level is within the envelope area;

[0123] If it is within the envelope area, the requirement cannot be met, adjust the value of the Z-direction overload, and recalculate;

[0124] If it is not within the envelope area, record the value of the Z-direction overload at this time and include it in the overload range.

[0125] It can be seen that in the lubricating oil liquid level calculation method of the present invention, based on the definition and conversion of the coordinate system, force analysis is carried out under the conditions of aircraft three-axis overload, attitude angle, three-axis angular velocity, three-axis angular acceleration, flight mass centroid distance, and turning radius, and then the lubricating oil liquid level is calculated to form a mapping relationship between aircraft flight state parameters and the lubricating oil liquid level.

[0126] Through the forward matching calculation method, based on the calculation of the lubricating oil liquid level and the analysis of the leakage amount, according to the continuous working criterion and the limit working criterion of the lubricating oil system, and according to the change relationship of aircraft flight state parameters with time, the aircraft attitude envelope is transformed into the engine attitude envelope, so as to realize the analysis of the lubricating oil system, obtain unsafe flight conditions in advance, and facilitate the staff to limit and adjust the lubricating oil system and the aircraft attitude envelope, improving the safety of the aircraft engine during use.

[0127] The reverse matching calculation method can also be used to put forward overload requirements for the aircraft according to the continuous working criterion of the engine, so as to realize the two-way conversion between the aircraft attitude envelope and the engine attitude envelope.

[0128] On the basis of introducing the flight state parameters in actual flight, the present invention adopts the coordinate transformation and overload synthesis method, and then based on the force analysis, establishes a one-to-one mapping relationship between the flight state parameters and the lubricating oil liquid level. Based on the normal vector of the lubricating oil liquid level, according to the oil supply amount and time of lubricating oil components such as bearing chambers, reducers, and fuel tanks, the oil amount in the lubricating oil component chambers at each moment is calculated, and the liquid level height is determined accordingly to realize the determination of the lubricating oil liquid level; then based on the relative positions of the lubricating oil liquid level and components such as the oil return port and the oil supply port, the working state of the lubricating oil components is judged, so as to judge the working state of the engine and realize the analysis of the lubricating oil system attitude.

[0129] Starting from the working states of lubricating oil components such as bearing chambers, reducers, and fuel tanks, the present invention establishes a matching relationship between the flight state parameters of the aircraft and the engine attitude envelope, and then realizes the two-way conversion between the flight state parameters of the aircraft and the engine attitude envelope.

[0130] In addition, referring to Figure 2 , the present invention also discloses an attitude analysis device for an aero-engine lubricating oil system, including:

[0131] A data acquisition unit, configured to acquire the set working states of the engine lubricating oil components to be measured and correspondingly establish an engine lubricating oil component model;

[0132] A first construction unit, configured to construct an aircraft positioning coordinate system based on the engine lubricating oil component model;

[0133] A first analysis unit, configured to acquire flight state parameters and perform corresponding aircraft force analysis in combination with the aircraft positioning coordinate system;

[0134] A second construction unit, configured to obtain the height of the lubricating oil level of an aircraft based on the force analysis of the aircraft, and then construct a mapping relationship between the flight state parameters and the lubricating oil level;

[0135] A second analysis unit, configured to obtain the actual flight state parameters, obtain the actual lubricating oil level based on the mapping relationship, and then obtain the matching relationship between the actual lubricating oil level and the engine of the aircraft to be tested;

[0136] A judging unit, configured to judge the lubricating oil system of the aircraft to be tested based on the matching relationship.

[0137] Wherein, the first construction unit is specifically configured to:

[0138] Construct an aircraft vertical coordinate system, an aircraft body coordinate system, and an engine model coordinate system respectively based on the engine lubricating oil component model;[[ID=|14]]

[0139] Calculate the conversion relationships between the aircraft vertical coordinate system, the aircraft body coordinate system, and the engine model coordinate system.

[0140] Wherein, the aircraft lubricating oil components include a fuel tank component and a mating component, and the second construction unit is specifically configured to:

[0141] Obtain the normal vector direction of the lubricating oil level based on the force analysis of the aircraft;

[0142] Select the liquid level direction of the mating component based on the normal vector direction of the lubricating oil level;

[0143] Substitute the liquid level direction of the mating component into the engine lubricating oil component model, and calculate the maximum hidden amount of lubricating oil in the mating component as the liquid level height of the mating component;

[0144] Obtain the maximum fuel injection amount and the lubricating oil consumption of the fuel tank component;

[0145] Select the difference between the maximum fuel injection amount of the fuel tank component and the lubricating oil consumption of the fuel tank component and the maximum hidden amount of the mating component as the remaining oil amount of the fuel tank component;

[0146] Substitute the remaining oil amount of the fuel tank component into the engine lubricating oil component model, calculate the liquid level height of the fuel tank component as the lubricating oil level height, and then construct a mapping relationship between the flight state parameters and the lubricating oil level.

[0147] Meanwhile, compared with the prior art which relies on lubricating oil system attitude tests, engine whole-machine attitude tests, and even empty-platform flight tests for analysis, the present invention avoids the delay of the research and development progress and the waste of resources, and greatly improves the efficiency and accuracy of the attitude analysis of the aero-engine lubricating oil system.

[0148] In the description of the present invention, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of the described features. In the description of the present invention, "a plurality of" means two or more unless otherwise specifically defined.

[0149] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, the terms "installed", "connected", and "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection, an electrical connection, or a connection that allows for mutual communication; it may be directly connected, or indirectly connected through an intermediate medium, and it may be the internal communication of multiple components or the interaction relationship of multiple components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0150] In the description of the present invention, it should be understood that all terms indicating orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the indicated device or element must have a specific orientation, be constructed and operated in a specific orientation, and should not be construed as a limitation of the present invention.

[0151] Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for attitude analysis of an aero-engine lubricating oil system, characterized in that, It includes the following steps: Obtain the set working state of the engine lubricating oil components to be tested, and correspondingly establish an engine lubricating oil component model; Construct an aircraft positioning coordinate system based on the engine lubricating oil component model; Obtain flight state parameters, and conduct corresponding aircraft force analysis in combination with the aircraft positioning coordinate system; Obtain the lubricating oil liquid level height of the aircraft based on the aircraft force analysis, and then construct the mapping relationship between the flight state parameters and the lubricating oil liquid level; Obtain the actual flight state parameters, obtain the actual lubricating oil liquid level based on the mapping relationship, and then obtain the matching relationship between the actual lubricating oil liquid level and the engine of the aircraft to be tested; Analyze the lubricating oil system of the aircraft to be tested based on the matching relationship.

2. The attitude analysis method of the aero-engine lubricating oil system according to claim 1, characterized in that The construction of the aircraft positioning coordinate system based on the engine lubricating oil component model specifically includes the following steps: Construct an aircraft vertical coordinate system, an aircraft body coordinate system, and an engine model coordinate system based on the engine lubricating oil component model respectively; Calculate the conversion relationships between the aircraft vertical coordinate system, the aircraft body coordinate system, and the engine model coordinate system.

3. The attitude analysis method of the aero-engine lubricating oil system according to claim 1, characterized in that The flight state parameters specifically include: attitude angle, combined comprehensive overload coefficient, and relative position of the engine and the aircraft; The attitude angle includes: yaw angle, pitch angle, and roll angle; The combined comprehensive overload coefficient includes: three-way overload, three-way angular velocity, three-way angular acceleration, turning radius, and distance from the center of mass of the aircraft and the engine; 4. The attitude analysis method of the aero-engine lubricating oil system according to claim 1, wherein, The engine lubricating oil components include a fuel tank component and a mating component. The obtaining of the lubricating oil liquid level height of the aircraft based on the aircraft force analysis specifically includes the following steps: Obtain the normal vector direction of the lubricating oil liquid level based on the aircraft force analysis; Select the liquid level direction of the mating component based on the normal vector direction of the lubricating oil liquid level; Substitute the liquid level direction of the mating component into the engine lubricating oil component model, and calculate the maximum hidden amount of lubricating oil in the mating component as the liquid level height of the mating component; Obtain the maximum fuel injection amount and lubricating oil consumption of the fuel tank component; Select the difference between the maximum fuel injection amount of the fuel tank component and the lubricating oil consumption of the fuel tank component and the maximum hidden amount of the mating component as the remaining oil amount of the fuel tank component; Substitute the remaining oil amount of the fuel tank component into the engine lubricating oil component model, and calculate the liquid level height of the fuel tank component as the lubricating oil liquid level height.

5. The attitude analysis method for the lubricating oil system of an aero-engine according to claim 4, characterized in that, The calculation of the maximum hidden amount of lubricating oil in the mating component specifically includes the following steps: Substitute the liquid level direction of the mating component into the engine lubricating oil component model, draw an initial liquid level at the lowest point of the oil return port of the mating component, and obtain the oil amount corresponding to the initial liquid level as the initial oil amount of the mating component; Obtain the fuel supply amount and time step of the mating component, and use the product of the fuel supply amount and the time step as the increase amount of the mating component; Use the sum of the initial oil amount of the mating component and the increase amount of the mating component as the maximum hidden amount of the mating component.

6. The attitude analysis method of the aero-engine lubricating oil system according to claim 1, characterized in that The obtaining of the matching relationship between the actual lubricating oil liquid level and the engine of the aircraft to be tested includes the following steps: Obtain the specification parameters of the engine and set the height range; When the liquid level height of the actual lubricating oil liquid level belongs to the height range, determine that the matching relationship is healthy; When the liquid level height of the actual lubricating oil liquid level is lower than or exceeds the height range, calculate the limit working duration of the engine, and obtain the limit working duration in combination with the specification parameters of the engine; When the limit working duration is greater than the limit working duration, determine that the matching relationship is healthy; When the limit working duration is less than the limit working duration, it is determined that the matching relationship is unhealthy.

7. The attitude analysis method for the lubricating oil system of an aero-engine according to claim 6, characterized in that, The method for evaluating the lubricating oil system of the aircraft to be tested based on the matching relationship specifically includes the following steps: When it is determined that the matching relationship is healthy, it is judged that the lubricating oil system of the aircraft to be tested is qualified. When it is determined that the matching relationship is unhealthy, it is judged that the lubricating oil system of the aircraft to be tested is unqualified.

8. An attitude analysis device for an aero-engine lubricating oil system, characterized in that, It includes: A data acquisition unit, configured to acquire the set working state of the engine lubricating oil components to be tested, and correspondingly establish an engine lubricating oil component model; A first construction unit, configured to construct an aircraft positioning coordinate system based on the engine lubricating oil component model; A first analysis unit, configured to acquire flight state parameters, and perform corresponding aircraft force analysis in combination with the aircraft positioning coordinate system; A second construction unit, configured to obtain the lubricating oil liquid level height of the aircraft based on the aircraft force analysis, and further construct a mapping relationship between the flight state parameters and the lubricating oil liquid level; A second analysis unit, configured to acquire the actual flight state parameters, obtain the actual lubricating oil liquid level based on the mapping relationship, and further obtain the matching relationship between the actual lubricating oil liquid level and the engine of the aircraft to be tested; A judgment unit, configured to analyze the lubricating oil system of the aircraft to be tested based on the matching relationship.

9. The attitude analysis device for an aero-engine lubricating oil system according to claim 8, wherein, The first construction unit is specifically configured to: Construct an aircraft vertical coordinate system, an aircraft body coordinate system, and an engine model coordinate system respectively based on the engine lubricating oil component model; Calculate the conversion relationship between the aircraft vertical coordinate system, the aircraft body coordinate system, and the engine model coordinate system.

10. The attitude analysis device for an aero-engine lubricating oil system according to claim 8, wherein The engine lubricating oil components include a fuel tank component and a mating component. The second construction unit is specifically configured to: Obtain the normal vector direction of the lubricating oil liquid level based on the aircraft force analysis; Select the liquid level direction of the mating component based on the normal vector direction of the lubricating oil liquid level; Substitute the liquid level direction of the mating component into the engine lubricating oil component model, and calculate the maximum hidden amount of lubricating oil in the mating component as the liquid level height of the mating component; Obtain the maximum fuel injection amount and lubricating oil consumption amount of the fuel tank component; Select the difference between the maximum fuel injection amount of the fuel tank component and the lubricating oil consumption amount of the fuel tank component and the maximum hidden amount of the mating component as the remaining oil amount of the fuel tank component; Substitute the remaining oil amount of the fuel tank component into the engine lubricating oil component model, calculate the liquid level height of the fuel tank component as the lubricating oil liquid level height, and further construct a mapping relationship between the flight state parameters and the lubricating oil liquid level.

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