Method and system for calculating engine dynamic loads

Abstract

The application relates to a method and system for calculating engine dynamic load, which comprises collecting flight height and flight speed when an airplane is flying; calculating z-direction speed and acceleration according to the collected flight height of adjacent two times, and calculating x-direction acceleration according to the x-direction flight speed of adjacent two times; calculating x-direction dynamic load and z-direction dynamic load at the engine mass center based on the x-direction acceleration and the z-direction acceleration; calculating the mean value of the x-direction dynamic load and the z-direction dynamic load; calculating the x-direction dynamic load of the main mounting section according to the mean value of the x-direction dynamic load, and calculating the z-direction dynamic load of the main mounting section and the auxiliary mounting section according to the mean value of the z-direction dynamic load. The application can obtain the damage of each part of the engine more accurately by calculating the x-direction and z-direction dynamic load of the engine in the process of helicopter flight based on flight parameters, so that the real-time monitoring of the life damage of the engine can be realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aero-engine design, and particularly to a method and system for calculating engine maneuver load. BACKGROUND

[0002] The helicopter-mounted aero-turboshaft engine (hereinafter referred to as turboshaft engine) has translational acceleration in the x (forward and backward) direction, y (lateral) direction and z (up and down) direction, and angular velocity and angular acceleration around the x, y and z axes during the flight of the helicopter, which will generate inertial force, or "maneuver overload force", and these forces may cause damage to the parts of the engine, so they should be considered in the strength design. At present, the "flight envelope" is often used to consider the effect of the maneuver load. However, with the development of technology, higher requirements are put forward for the real-time monitoring of the life damage of the engine.

[0003] Therefore, it is urgent to provide a method and system for calculating engine maneuver load, so as to realize the real-time monitoring of the life damage of the engine. SUMMARY

[0004] Therefore, the technical problem to be solved by the present application is to overcome the technical defects in the prior art, and to provide a method and system for calculating engine maneuver load, which can calculate the x and z direction maneuver loads of the engine in the flight process of the helicopter based on flight parameters, and can more accurately obtain the damage of each part of the engine, so as to realize the real-time monitoring of the life damage of the engine.

[0005] To solve the above technical problems, the present application provides a method for calculating engine maneuver load, an engine is provided with a main mounting section and an auxiliary mounting section, the main mounting section is connected with a helicopter transmission system, wherein the main mounting section is used to transmit x and z direction loads, and the auxiliary mounting section is used to transmit z direction load, and the method comprises the following steps:

[0006] S1: collecting flight parameters during the flight of the aircraft, wherein the flight parameters include flight height and flight speed;

[0007] S2: calculating z direction speed according to the flight height of adjacent two times, calculating z direction acceleration according to the z direction speed, and calculating x direction acceleration according to the x direction flight speed of adjacent two times;

[0008] S3: calculating the x direction maneuver load of the engine mass center based on the x direction acceleration, and calculating the z direction maneuver load of the engine mass center based on the z direction acceleration;

[0009] S4: calculating the mean value of the x direction maneuver load and the z direction maneuver load;

[0010] S5: calculating the x-direction maneuver load on the main mounting node according to the mean value of the x-direction maneuver load and calculating the z-direction maneuver load on the main mounting node and the auxiliary mounting node according to the mean value of the z-direction maneuver load.

[0011] In an embodiment of the present application, the formula for calculating the z-direction velocity is:

[0012]

[0013] wherein, z-direction velocity, , denotes the flight height of the adjacent two times, denotes the data acquisition period.

[0014] In an embodiment of the present application, in S2, the formula for calculating the z-direction acceleration and the x-direction acceleration is:

[0015]

[0016]

[0017] wherein, z-direction acceleration, , denotes the z-direction velocity of the adjacent two times, denotes the data acquisition period, x-direction acceleration, , denotes the x-direction flight velocity of the adjacent two times.

[0018] In an embodiment of the present application, in S3, the formula for calculating the x-direction maneuver load and the z-direction maneuver load on the engine mass center is respectively:

[0019]

[0020] wherein, x-direction maneuver load on the engine mass center, z-direction maneuver load on the engine mass center, x-direction acceleration, z-direction acceleration, engine mass.

[0021] In an embodiment of the present application, in S4, the formula for calculating the mean value of the x-direction maneuver load and the mean value of the z-direction maneuver load is:

[0022]

[0023] wherein, represents the average of the x-direction maneuver load, represents the average of the z-direction maneuver load, represents the x-direction maneuver load at the engine mass center, represents the z-direction maneuver load at the engine mass center, I = 0, 1, 2…M, M = (N-2) / n, n represents the number of data used for average calculation, and N represents the total number of data of each flight parameter collected.

[0024] In one embodiment of the present application, in S5, the calculation formula of the x-direction maneuver load at the main mounting node is:

[0025]

[0026] wherein, represents the x-direction maneuver load at the main mounting node, represents the average of the x-direction maneuver load.

[0027] In one embodiment of the present application, in S5, the calculation formula of the z-direction maneuver load at the main mounting node and the z-direction maneuver load at the auxiliary mounting node are respectively:

[0028]

[0029]

[0030] wherein, represents the z-direction maneuver load at the main mounting node, represents the z-direction maneuver load at the auxiliary mounting node, represents the average of the z-direction maneuver load, b represents the distance from the engine gravity center to the auxiliary mounting node, a represents the distance from the engine gravity center to the main mounting node, and L represents the distance from the main mounting node to the auxiliary mounting node.

[0031] Further, the present application also provides a system for calculating engine maneuver load, a main mounting node and an auxiliary mounting node are installed on an engine, the main mounting node is connected with a helicopter transmission system, wherein the main mounting node is used for transmitting x-direction and z-direction loads, and the auxiliary mounting node is used for transmitting z-direction load, and the system comprises:

[0032] a data acquisition module, which is used for acquiring flight parameters during flight of an airplane, wherein the flight parameters include flight height and flight speed;

[0033] The computing module is used for calculating the z-direction velocity according to the flight height of the adjacent two times of collection, calculating the z-direction acceleration according to the z-direction velocity, and calculating the x-direction acceleration according to the x-direction flight velocity of the adjacent two times; the x-direction maneuver load suffered at the engine mass center is calculated based on the x-direction acceleration, and the z-direction maneuver load suffered at the engine mass center is calculated based on the z-direction acceleration; the mean value of the x-direction maneuver load and the z-direction maneuver load is calculated; the x-direction maneuver load suffered by the main mounting section is calculated according to the mean value of the x-direction maneuver load, and the z-direction maneuver load suffered by the main mounting section and the auxiliary mounting section is calculated according to the mean value of the z-direction maneuver load.

[0034] Moreover, the application further provides a computer device, comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, wherein the processor implements the steps of the method for calculating the engine maneuver load when executing the computer program.

[0035] Furthermore, the application further provides a computer readable storage medium, wherein a computer program is stored on the medium, and the program implements the steps of the method for calculating the engine maneuver load when executed by a processor.

[0036] The above technical solution of the application has the following advantages compared with the prior art:

[0037] The method and system for calculating the engine maneuver load can calculate the x-direction and z-direction maneuver loads suffered by the engine in the flight process of the helicopter in real time based on flight parameters, can more accurately obtain the damage of each part of the engine, and thus can realize real-time monitoring of the life damage of the engine, and can significantly improve the safety, reliability and economy of the engine. BRIEF DESCRIPTION OF DRAWINGS

[0038] In order to make the content of the application more easily understood, the application will be further described in detail below according to specific embodiments of the application and in combination with the drawings.

[0039] Figure 1 is a structural schematic view of the main mounting section C and the auxiliary mounting section D of the engine.

[0040] Figure 2 is a flowchart of the method for calculating the engine maneuver load according to an embodiment of the application. DETAILED DESCRIPTION

[0041] The application will be further described below in combination with the drawings and specific embodiments, so that those skilled in the art can better understand the application and implement the application, but the embodiments are not used as limitations to the application.

[0042] Referring toFigure 1 As shown, Figure 1 The schematic view of the structure of the main mounting section C and the auxiliary mounting section D installed on the engine, wherein the main mounting section C is connected with the helicopter transmission system, the main mounting section C is used for transmitting the x and z direction loads, the auxiliary mounting section D is installed on the engine in the form of hanging, the auxiliary mounting section D allows the x direction movement, and therefore the auxiliary mounting section D can only transmit the z direction load.

[0043] On the basis of the prior art, Figure 1 The embodiment of the present application provides a method for calculating the engine maneuvering load, please refer to Figure 2 As shown, the method comprises the following steps:

[0044] S1: collecting the flight parameters during the flight of the aircraft, wherein the flight parameters comprise the flight height and the flight speed;

[0045] S2: calculating the z direction speed according to the flight heights collected in the adjacent two times, calculating the z direction acceleration according to the z direction speed, and calculating the x direction acceleration according to the x direction flight speeds in the adjacent two times;

[0046] S3: calculating the x direction maneuvering load at the engine mass center based on the x direction acceleration, and calculating the z direction maneuvering load at the engine mass center based on the z direction acceleration;

[0047] S4: calculating the mean values of the x direction maneuvering load and the z direction maneuvering load;

[0048] S5: calculating the x direction maneuvering load of the main mounting section according to the mean value of the x direction maneuvering load, and calculating the z direction maneuvering load of the main mounting section and the auxiliary mounting section according to the mean value of the z direction maneuvering load.

[0049] The method for calculating the engine maneuvering load provided by the present application can calculate the x and z direction maneuvering loads of the engine in the flight process of the helicopter in real time based on the flight parameters, and can more accurately obtain the damage of each part of the engine, so that the real-time monitoring of the life damage of the engine is realized, and the safety, reliability and economy of the engine are significantly improved.

[0050] In step S1, the flight parameters are collected at the collection frequency Freq (unit: Hz, or times / second), and the corresponding collection period is T=1 / Freq (unit: second), that is, how many times a data is collected.

[0051] In step S2, the method for calculating the z direction speed according to the flight heights collected in the adjacent two times comprises: setting the flight heights collected in the adjacent two times as , At this time, the speed of the flight height in the z direction is:

[0052] (1)

[0053] wherein, denotes the z-direction velocity, , denotes the flight height of the adjacent two times, denotes the data acquisition period.

[0054] wherein, in step S2, the method for calculating the z-direction acceleration according to the z-direction velocity comprises: the acceleration of the flight height in the z-direction is:

[0055] (2)

[0056] wherein, denotes the z-direction acceleration, , denotes the adjacent two times of the z-direction velocity, denotes the data acquisition period.

[0057] wherein, in step S2, the method for calculating the x-direction acceleration according to the adjacent two times of the x-direction flight velocity comprises: similarly, assuming that the x-direction flight velocity acquired in the adjacent two times is , the acceleration in the x-direction is:

[0058] (3)

[0059] wherein, denotes the x-direction acceleration, , denotes the adjacent two times of the x-direction flight velocity, denotes the data acquisition period.

[0060] wherein, in step S3, the method for calculating the x-direction maneuver load borne by the engine mass center based on the x-direction acceleration and the z-direction maneuver load borne by the engine mass center based on the z-direction acceleration comprises: assuming that the mass of the engine is m, the x-direction and z-direction maneuver loads borne by the engine mass center are:

[0061] (4)

[0062] (5)

[0063] wherein, denotes the x-direction maneuver load borne by the engine mass center, denotes the z-direction maneuver load borne by the engine mass center, denotes the x-direction acceleration, represents the z-direction acceleration, represents the engine mass.

[0064] wherein, in step S4, the x-direction maneuver load and the z-direction maneuver load are respectively subjected to the following average processing in order to obtain smoother data:

[0065] (6)

[0066] (7)

[0067] I = 0, 1, 2…M

[0068] M = (N-2) / n (integer)

[0069] wherein, represents the x-direction maneuver load average, represents the z-direction maneuver load average, represents the x-direction maneuver load at the engine mass center, represents the z-direction maneuver load at the engine mass center, I = 0, 1, 2…M, M = (N-2) / n, n represents the number of data used for average calculation, and N represents the total number of data of each flight parameter collected. When n = 1, no average processing is performed.

[0070] wherein, in step S5, the x-direction maneuver load at the main mounting section C is:

[0071] (8)

[0072] wherein, represents the x-direction maneuver load at the main mounting section, represents the x-direction maneuver load average;

[0073] The z-direction maneuver load at the main mounting section C and the auxiliary mounting section D is:

[0074] The main mounting section C:

[0075] (9)

[0076] wherein, represents the z-direction maneuver load at the main mounting section, represents the z-direction maneuver load average, b represents the distance from the engine center of gravity to the auxiliary mounting section, and L represents the distance from the main mounting section to the auxiliary mounting section.

[0077] The auxiliary mounting section D:

[0078] (10)

[0079] wherein, represents the z-direction maneuver load borne by the auxiliary mounting node, represents the z-direction maneuver load average, a represents the distance from the engine gravity center to the main mounting node, and L represents the distance from the main mounting node to the auxiliary mounting node.

[0080] Corresponding to the above-mentioned method, the embodiment of the present application also provides a computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the above-mentioned method for calculating the engine maneuver load when executing the computer program.

[0081] In addition, the present application also provides a computer readable storage medium, which stores a computer program, wherein the program implements the steps of the above-mentioned method for calculating the engine maneuver load when executed by a processor.

[0082] The following describes a system for calculating the engine maneuver load according to the embodiment of the present application, which can be correspondingly referred to the above-mentioned method for calculating the engine maneuver load.

[0083] The embodiment of the present application also provides a system for calculating the engine maneuver load, wherein an engine is provided with a main mounting node and an auxiliary mounting node, the main mounting node is connected with a helicopter transmission system, wherein the main mounting node is used for transmitting x-direction and z-direction loads, and the auxiliary mounting node is used for transmitting z-direction load, and the system comprises:

[0084] a data acquisition module, which is used for acquiring flight parameters during flight of an aircraft, wherein the flight parameters comprise flight height and flight speed;

[0085] a calculation module, which is used for calculating z-direction speed according to the acquired flight height of adjacent two times, and calculating z-direction acceleration according to the z-direction speed, and calculating x-direction acceleration according to x-direction flight speed of adjacent two times; calculating x-direction maneuver load borne by the engine mass center according to the x-direction acceleration, and calculating z-direction maneuver load borne by the engine mass center according to the z-direction acceleration; calculating the average of the x-direction maneuver load and the z-direction maneuver load; calculating x-direction maneuver load borne by the main mounting node according to the average of the x-direction maneuver load, and calculating z-direction maneuver load borne by the main mounting node and the auxiliary mounting node according to the average of the z-direction maneuver load.

[0086] The system for calculating engine dynamic load can calculate the x and z direction dynamic load of the engine in the flight process of the helicopter based on the flight parameters, can more accurately obtain the damage of each part of the engine, and thus realizes real-time monitoring of the life damage of the engine, and significantly improves the safety, reliability and economy of the engine.

[0087] The system for calculating engine dynamic load of the embodiment is used for implementing the method for calculating engine dynamic load, and thus the specific implementation of the system can refer to the description of the method for calculating engine dynamic load in the foregoing embodiment part, and will not be described here.

[0088] In addition, the system for calculating engine dynamic load of the embodiment is used for implementing the method for calculating engine dynamic load, and thus the function thereof corresponds to the function of the method, which will not be described here.

[0089] Those skilled in the art should understand that the embodiments of the present application can be provided as a method, a system or a computer program product. Therefore, the present application can adopt a completely hardware embodiment, a completely software embodiment or an embodiment combining software and hardware aspects. Moreover, the present application can adopt a computer program product implemented on one or more computer usable storage media containing computer usable program codes (including but not limited to disk memory, CD-ROM, optical memory, etc.).

[0090] The present application is described with reference to flowcharts and / or block diagrams of the method, device (system) and computer program product according to the embodiments of the present application. It should be understood that each flow and / or block in the flowcharts and / or block diagrams, and the combination of the flows and / or blocks in the flowcharts and / or block diagrams can be implemented by computer program instructions. These computer program instructions can be provided to a general-purpose computer, a special-purpose computer, an embedded processor or other programmable data processing devices to produce a machine, so that the instructions executed by the computer or other programmable data processing devices produce a device for implementing the functions specified in the flowcharts and / or block diagrams. Figure 1 The functions specified in one or more flows and / or blocks Figure 1 The computer device that implements the functions specified in one or more flows and / or blocks.

[0091] These computer program instructions can also be stored in a computer readable memory capable of guiding the computer or other programmable data processing devices to work in a specific way, so that the instructions stored in the computer readable memory produce a product including an instruction computer device, which implements the functions specified in the flowcharts and / or block diagrams. Figure 1 The functions specified in one or more flows and / or blocks Figure 1 The computer device that implements the functions specified in one or more flows and / or blocks.

[0092] These computer program instructions can also be loaded into computer or other programmable data processing devices, so that a series of operation steps are performed on the computer or other programmable data processing devices to generate computer-implemented processes, thus the instructions executed on the computer or other programmable data processing devices provide processes for implementing the functions specified in the flowcharts Figure 1 one flow or multiple flows and / or one block or multiple blocks. Figure 1 the steps of the functions specified in one block or multiple blocks.

[0093] Obviously, the above embodiments are only examples for clearly illustrating the present application, and are not intended to limit the embodiments. Based on the above description, other different forms of changes or variations can be made by those skilled in the art. Here, all the embodiments are not required to be exhausted, and the obvious changes or variations derived therefrom are still within the protection scope of the present application.

Claims

1. A method for calculating engine maneuvering loads, wherein a main mounting section and an auxiliary mounting section are mounted on the engine, the main mounting section being connected to a helicopter transmission system, wherein the main mounting section is used to transmit loads in the x and z directions, and the auxiliary mounting section is used to transmit loads in the z direction, characterized in that: This method Includes the following steps: S1: Collect flight parameters of the aircraft during flight, including flight altitude and flight speed; S2: Calculate the z-direction velocity based on two consecutive flight altitudes, calculate the z-direction acceleration based on the z-direction velocity, and calculate the x-direction acceleration based on two consecutive x-direction flight velocities; S3: Calculate the x-direction maneuvering load at the engine center of mass based on x-direction acceleration, and calculate the z-direction maneuvering load at the engine center of mass based on z-direction acceleration; S4: Calculate the average values ​​of the x-direction maneuvering load and the z-direction maneuvering load; S5: Calculate the x-direction kinematic load on the main mounting section based on the average value of the x-direction kinematic load, and calculate the z-direction kinematic load on the main mounting section and the auxiliary mounting section based on the average value of the z-direction kinematic load; In S5, the formula for calculating the kinematic load in the x-direction on the main mounting section is: in, This indicates the kinematic load in the x-direction experienced by the main mounting section. This represents the mean value of the kinematic load in the x-direction; In S5, the calculation formulas for the z-direction kinematic load on the main mounting section and the z-direction kinematic load on the auxiliary mounting section are as follows: in, This indicates the kinematic load in the z-direction experienced by the main mounting section. This indicates the kinematic load in the z-direction experienced by the auxiliary mounting section. denoted by z, b represents the average value of the motor load in the z-direction, a represents the distance from the engine center of gravity to the auxiliary mounting section, and L represents the distance from the engine center of gravity to the main mounting section.

2. The method for calculating engine dynamic load according to claim 1, characterized in that: In S2, the formula for calculating the velocity in the z-direction is: in, Represents the velocity in the z-direction. , Indicates the flight altitude between two consecutive intervals. Indicates the data collection cycle.

3. The method for calculating engine dynamic load according to claim 2, characterized in that: In S2, the formulas for calculating the acceleration in the z-direction and the acceleration in the x-direction are: in, This represents acceleration in the z-direction. , This represents the velocity in the z-direction between two consecutive intervals. Indicates the data collection period. This represents acceleration in the x-direction. , This represents the flight speed in the x-direction between two consecutive intervals.

4. The method for calculating engine dynamic load according to claim 3, characterized in that: In S3, the formulas for calculating the x-direction and z-direction kinematic loads at the engine's center of mass are as follows: in, This represents the kinematic load in the x-direction experienced at the engine's center of mass. This represents the kinematic load in the z-direction at the engine's center of mass. This represents acceleration in the x-direction. This represents acceleration in the z-direction. Indicates engine mass.

5. The method for calculating engine dynamic load according to claim 4, characterized in that: In S4, the formulas for calculating the mean values ​​of the x-direction and z-direction maneuvering loads are as follows: in, This represents the mean value of the kinematic load in the x-direction. This represents the mean value of the kinematic load in the z-direction. This represents the kinematic load in the x-direction experienced at the engine's center of mass. The z-direction maneuver load at the engine's center of mass is represented by I = 0, 1, 2…M, where M = (N-2) / n, n represents the number of data points used for averaging, and N represents the total number of data points for each flight parameter collected.

6. A system for calculating engine maneuvering loads, wherein a main mounting section and an auxiliary mounting section are mounted on the engine, the main mounting section being connected to a helicopter transmission system, wherein the main mounting section is used to transmit loads in the x and z directions, and the auxiliary mounting section is used to transmit loads in the z direction, characterized in that: The system includes: The data acquisition module is used to collect flight parameters of the aircraft during flight, including flight altitude and flight speed. The calculation module is used to calculate the z-direction velocity based on two consecutive flight altitudes, and the z-direction acceleration based on the z-direction velocity, and the x-direction acceleration based on two consecutive x-direction flight velocities; calculate the x-direction maneuvering load at the engine center of mass based on the x-direction acceleration, and calculate the z-direction maneuvering load at the engine center of mass based on the z-direction acceleration; calculate the average value of the x-direction maneuvering load and the z-direction maneuvering load; calculate the x-direction maneuvering load on the main mounting section based on the average value of the x-direction maneuvering load, and calculate the z-direction maneuvering load on the main mounting section and the auxiliary mounting section based on the average value of the z-direction maneuvering load; In the calculation module, the formula for calculating the kinematic load in the x-direction on the main mounting section is: in, This indicates the kinematic load in the x-direction experienced by the main mounting section. This represents the mean value of the kinematic load in the x-direction; In the calculation module, the calculation formulas for the z-direction kinematic load on the main mounting section and the z-direction kinematic load on the auxiliary mounting section are as follows: in, This indicates the kinematic load in the z-direction experienced by the main mounting section. This indicates the kinematic load in the z-direction experienced by the auxiliary mounting section. denoted by z, b represents the average value of the motor load in the z-direction, a represents the distance from the engine center of gravity to the auxiliary mounting section, and L represents the distance from the engine center of gravity to the main mounting section.

7. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the steps of a method for calculating engine dynamic load as described in any one of claims 1 to 5.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that, When executed by a processor, the program implements the steps of a method for calculating engine dynamic load as described in any one of claims 1 to 5.

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