Engine lubrication system control method, device, aircraft, medium and product

Abstract

This application relates to the field of engine technology, and more particularly to a method, device, aircraft, medium, and product for controlling an engine's lubrication system. The method includes: detecting the actual tilt angle of the aircraft; if the actual tilt angle exceeds the maximum tilt angle allowed by the engine's lubrication system, determining a target action based on the actual tilt angle to ensure that the angle between the oil level and the oil pan of the lubrication system does not exceed the maximum angle; and controlling the aircraft to execute the target action. This solves the problem in related technologies where the aircraft cannot achieve a greater tilt angle due to the need to ensure normal engine operation.

Description

Technical Field

[0001] The present application relates to the field of engine technology, and in particular to a method, device, aircraft, medium and product for controlling a lubrication system of an engine. Background Art

[0002] Current engine lubrication system control methods typically rely solely on the control system to limit the engine's attitude to within the permitted tilt angle of the ground engine. This approach cannot meet the potentially greater maneuvering requirements of aircraft. Simply put, current control methods fail to achieve coupled control of acceleration and tilt in all directions, instead implementing independent, unidirectional control. This limits the potential of engines for aircraft applications.

[0003] For example, if an engine's lubrication system requires a tilt angle of no more than 40°, traditional control methods would ensure that the engine's tilt angle in the aircraft does not exceed 40°, or that its acceleration does not exceed tan40°g. However, in some cases, the aircraft may not be able to be controlled within this range, which could lead to failure of the engine's lubrication system, resulting in engine damage or even more serious consequences. Summary of the Invention

[0004] The present application provides an engine lubrication system control method, device, aircraft, medium and product to solve the problem that the aircraft cannot achieve the operation requirement of a larger tilt angle due to the related technology in order to ensure the normal operation of the engine.

[0005] A first aspect of the present application provides a method for controlling a lubrication system of an engine, comprising the following steps: detecting an actual tilt angle of an aircraft; if the actual tilt angle exceeds a maximum tilt angle allowed by the lubrication system of the engine, determining a target action in which the angle between the oil level of the lubrication system and the oil pan does not exceed a maximum angle based on the actual tilt angle; and controlling the aircraft to execute the target action.

[0006] Optionally, a target action is determined based on the actual tilt angle so that the angle between the oil level of the lubrication system and the oil pan does not exceed the maximum angle, including: determining a target vertical acceleration applied to the oil pan based on the actual tilt angle; and generating a target action based on the target vertical acceleration.

[0007] Optionally, determining the target vertical acceleration applied to the oil pan according to the actual tilt angle includes: acquiring a correspondence between the actual tilt angle and the target vertical acceleration; and determining the target vertical acceleration by searching the correspondence according to the actual tilt angle.

[0008] Optionally, a target action is generated based on the target vertical acceleration, including: obtaining the total acceleration of the aircraft; determining the target angle between the aircraft and the normal of the plane in which the longitudinal and axial directions of the aircraft are located based on the total acceleration, the target vertical acceleration and the maximum angle; and controlling the actual tilt angle of the aircraft based on the target angle.

[0009] A second aspect of the present application provides an engine lubrication system control device, including: a detection module for detecting the actual tilt angle of an aircraft; a determination module for determining a target action in which the angle between the oil level of the lubrication system and the oil pan does not exceed the maximum angle if the actual tilt angle exceeds the maximum tilt angle allowed by the engine's lubrication system; and a control module for controlling the aircraft to perform the target action.

[0010] Optionally, the determination module is further configured to: determine a target vertical acceleration applied to the oil pan according to the actual tilt angle; and generate a target action according to the target vertical acceleration.

[0011] Optionally, the determination module is further configured to: obtain a correspondence between the actual tilt angle and the target vertical acceleration; and determine the target vertical acceleration by searching for the correspondence according to the actual tilt angle.

[0012] Optionally, the determination module is further used to: obtain the total acceleration of the aircraft; determine the target angle between the aircraft and the normal of the plane in which the longitudinal and axial directions of the aircraft are located based on the total acceleration, the target vertical acceleration and the maximum angle; and control the actual tilt angle of the aircraft based on the target angle.

[0013] A third aspect of the present application provides an aircraft, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to execute the engine lubrication system control method as described in the above embodiment.

[0014] A fourth aspect of the present application provides a computer-readable storage medium having a computer program or instructions stored thereon, which is executed by a processor to perform the engine lubrication system control method as described in the above embodiment.

[0015] The fifth embodiment of the present application provides a computer program product, including a computer program or instructions. When the computer program or instructions are executed, the engine lubrication system control method as described in the above embodiment is implemented.

[0016] Therefore, this application has at least the following beneficial effects:

[0017] When the actual tilt angle of the aircraft exceeds the maximum tilt angle allowed by the engine's lubrication system, embodiments of the present application can determine a target action based on the actual tilt angle to ensure that the angle between the engine oil level and the oil pan does not exceed the maximum angle. The aircraft can then be controlled to execute the target action, maintaining the angle between the engine oil level and the oil pan within a safe range. This allows the aircraft to achieve greater tilt or acceleration capabilities, meeting greater operational requirements, improving aircraft performance, and avoiding engine failure caused by the angle between the engine oil level and the oil pan exceeding the maximum angle in the engine's lubrication system. This resolves the technical problem in related technologies where aircraft cannot achieve operational requirements for greater tilt angles in order to ensure normal engine operation.

[0018] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0020] Figure 1 This is a flow chart of a method for controlling a lubrication system of an engine according to an embodiment of the present application;

[0021] Figure 2 This is an example diagram of a lubrication system control device for an engine provided according to an embodiment of the present application;

[0022] Figure 3 This is a schematic diagram of the structure of an aircraft provided according to an embodiment of the present application. DETAILED DESCRIPTION

[0023] The following describes in detail embodiments of the present application, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present application, and should not be construed as limiting the present application.

[0024] The following describes the engine lubrication system control method, device, aircraft, medium and product of the embodiment of the present application with reference to the accompanying drawings. In response to the problem that the current control method mentioned in the above background technology does not realize the coupled control of acceleration and tilt in all directions, but performs independent one-way control, which limits the application potential of internal combustion engines in aircraft, the present application provides an engine lubrication system control method, in which when the actual tilt angle of the aircraft exceeds the maximum tilt angle allowed by the engine's lubrication system, a target action of determining that the angle between the oil level and the oil pan does not exceed the maximum angle based on the actual tilt angle is determined, and the aircraft is controlled to perform the target action, so that the aircraft can obtain greater tilting ability or acceleration ability. Therefore, it solves the problem that the related technology cannot achieve the operational requirements of a larger tilt angle due to the normal operation of the engine.

[0025] Specifically, Figure 1 This is a flow chart of the engine lubrication system control method provided in an embodiment of the present application.

[0026] like Figure 1 As shown, the engine lubrication system control method includes the following steps:

[0027] In step S101 , the actual tilt angle of the aircraft is detected.

[0028] It is understandable that the embodiments of the present application can detect the actual tilt angle of the aircraft so as to subsequently determine the target action of the aircraft based on the actual tilt angle.

[0029] In step S102 , if the actual tilt angle exceeds the maximum tilt angle allowed by the engine's lubrication system, a target action is determined based on the actual tilt angle to ensure that the angle between the oil level of the lubrication system and the oil pan does not exceed the maximum angle.

[0030] Among them, the maximum tilt angle allowed by the engine's lubrication system can be obtained through ground tilt tests or theoretical analysis. The maximum angle is the maximum angle at which the engine's lubrication system can tilt. If the maximum angle is exceeded, the engine may not be able to operate stably and may fail.

[0031] It can be understood that the embodiment of the present application can determine the target action of ensuring that the angle between the oil level of the lubrication system and the oil pan does not exceed the maximum angle based on the actual tilt angle when the actual tilt angle of the aircraft exceeds the maximum tilt angle allowed by the engine's lubrication system.

[0032] In an embodiment of the present application, a target action is performed to determine that the angle between the oil level of the lubrication system and the oil pan does not exceed a maximum angle based on the actual tilt angle, including: determining a target vertical acceleration applied to the oil pan based on the actual tilt angle; and generating a target action based on the target vertical acceleration.

[0033] It is understandable that, in the embodiment of the present application, the target vertical acceleration applied to the oil pan can be determined based on the actual tilt angle, and the target action can be generated based on the target vertical acceleration.

[0034] In an embodiment of the present application, determining the target vertical acceleration applied to the oil pan according to the actual tilt angle includes: obtaining a correspondence between the actual tilt angle and the target vertical acceleration; and determining the target vertical acceleration by searching the correspondence according to the actual tilt angle.

[0035] The corresponding relationship can be calibrated in advance.

[0036] It is understandable that, in the embodiment of the present application, the target vertical acceleration applied to the oil pan can be determined by searching for a corresponding relationship based on the actual tilt angle.

[0037] In an embodiment of the present application, a target action is generated based on the target vertical acceleration, including: obtaining the total acceleration of the aircraft; determining the target angle between the aircraft and the normal of the plane in which the longitudinal and axial directions of the aircraft are located based on the total acceleration, the target vertical acceleration and the maximum angle; and controlling the actual tilt angle of the aircraft based on the target angle.

[0038] It can be understood that the embodiments of the present application can obtain the total velocity of the aircraft in all directions, determine the target angle between the aircraft and the normal of the plane in which the longitudinal and axial directions of the aircraft are located based on the total acceleration, target vertical acceleration and maximum angle, and then control the actual tilt angle of the aircraft based on the target angle.

[0039] Because a vertical acceleration is applied to the bottom of the oil pan, when the aircraft's tilt angle exceeds the maximum tilt angle allowed by the engine's lubrication system, the angle between the oil level and the oil pan does not exceed the maximum angle. This allows the aircraft to achieve greater tilting or acceleration capabilities, thereby improving aircraft performance and preventing engine failure.

[0040] The embodiment of the present application can obtain the acceleration of the aircraft in the longitudinal direction X, axial direction Y and direction perpendicular to the longitudinal and axial directions Z, respectively: and Calculate the total acceleration of the aircraft based on the acceleration in each direction

[0041] In step S103 , the aircraft is controlled to perform a target action.

[0042] The target action is to control the actual tilt angle of the aircraft according to the target angle.

[0043] It can be understood that the embodiments of the present application can control the aircraft to perform the target action, so that even when the actual tilt angle of the aircraft is too large, the aircraft can be controlled to perform the target action, which can enable the aircraft to obtain greater tilting ability or acceleration ability, thereby improving the performance of the aircraft and avoiding engine failure caused by the angle between the oil level of the engine's lubrication system and the oil pan exceeding the maximum angle.

[0044] Specifically, the engine lubrication system control method of the embodiment of the present application includes the following steps:

[0045] 1. Confirm the engine's allowable tilt angle θ;

[0046] 2. Acceleration sensors in various directions of the aircraft obtain acceleration values ​​in various directions of the engine, with the aircraft longitudinal direction being X, the aircraft axial direction being Y, and the acceleration perpendicular to the XY plane being Z. It is also stated that these acceleration values ​​include the components of gravity acceleration in each direction (whether or not the acceleration sensors include this component is within the scope of this patent protection; the only difference is the method of expression. The description here only includes the case where the acceleration sensors include this component).

[0047] 3. The aircraft controller calculates the total acceleration as

[0048] 4. The aircraft only needs to be controlled The angle with the normal to the XY plane only needs to be smaller than θ.

[0049] For example, if the aircraft needs to tilt backwards more than 40° or generate an acceleration of tan40°g, it only needs to apply a corresponding acceleration in the vertical direction of the bottom surface of the engine oil pan to ensure that the angle between the oil level and the oil pan does not exceed 40°. This will enable the aircraft to have greater tilting or acceleration capabilities, thereby improving aircraft performance and preventing engine failure.

[0050] According to the engine lubrication system control method proposed in the embodiment of the present application, when the actual tilt angle of the aircraft exceeds the maximum tilt angle allowed by the engine's lubrication system, a target action can be determined based on the actual tilt angle to ensure that the angle between the oil level and the oil pan does not exceed the maximum angle, and the aircraft can be controlled to perform the target action to keep the angle between the oil level and the oil pan within a safe range. The aircraft can also obtain greater tilting ability or acceleration ability, meet the aircraft's greater operating requirements, improve the performance of the aircraft, and avoid engine failure caused by the angle between the oil level and the oil pan of the engine's lubrication system exceeding the maximum angle.

[0051] Next, the engine lubrication system control device proposed in accordance with an embodiment of the present application will be described with reference to the accompanying drawings.

[0052] Figure 2 It is a block diagram of a lubrication system control device of an engine according to an embodiment of the present application.

[0053] like Figure 2 As shown, the engine lubrication system control device 10 includes: a detection module 100 , a determination module 200 and a control module 300 .

[0054] Among them, the detection module 100 is used to detect the actual tilt angle of the aircraft; the determination module 200 is used to determine the target action of ensuring that the angle between the oil level of the lubrication system and the oil pan does not exceed the maximum angle if the actual tilt angle exceeds the maximum tilt angle allowed by the engine's lubrication system; and the control module 300 is used to control the aircraft to perform the target action.

[0055] In the embodiment of the present application, the determination module 200 is further configured to: determine a target vertical acceleration applied to the oil pan according to the actual tilt angle; and generate a target action according to the target vertical acceleration.

[0056] In the embodiment of the present application, the determination module 200 is further used to: obtain the corresponding relationship between the actual tilt angle and the target vertical acceleration; and determine the target vertical acceleration by searching the corresponding relationship according to the actual tilt angle.

[0057] In an embodiment of the present application, the determination module 200 is further used to: obtain the total acceleration of the aircraft; determine the target angle between the aircraft and the normal of the plane in which the longitudinal and axial directions of the aircraft are located based on the total acceleration, the target vertical acceleration and the maximum angle; and control the actual tilt angle of the aircraft based on the target angle.

[0058] It should be noted that the above explanation of the embodiment of the engine lubrication system control method is also applicable to the engine lubrication system control device of this embodiment, and will not be repeated here.

[0059] According to the engine lubrication system control device proposed in the embodiment of the present application, when the actual tilt angle of the aircraft exceeds the maximum tilt angle allowed by the engine's lubrication system, the control device can determine a target action based on the actual tilt angle so that the angle between the oil level and the oil pan does not exceed the maximum angle, and control the aircraft to perform the target action so that the angle between the oil level and the oil pan is maintained within a safe range. The control device can also enable the aircraft to obtain greater tilting ability or acceleration ability, meet the aircraft's greater operating requirements, improve the performance of the aircraft, and avoid engine failure caused by the angle between the oil level and the oil pan of the engine's lubrication system exceeding the maximum angle.

[0060] Figure 3 This is a schematic diagram of the structure of an aircraft provided in an embodiment of the present application. The aircraft may include:

[0061] Memory 301 , processor 302 , and computer programs stored in the memory 301 and executable on the processor 302 .

[0062] When the processor 302 executes the program, the engine lubrication system control method provided in the above embodiment is implemented.

[0063] Furthermore, the aircraft also includes:

[0064] The communication interface 303 is used for communication between the memory 301 and the processor 302 .

[0065] The memory 301 is used to store computer programs that can be run on the processor 302 .

[0066] The memory 301 may include a high-speed RAM memory, and may also include a non-volatile memory (non-volatile memory), such as at least one disk memory.

[0067] If the memory 301, processor 302, and communication interface 303 are implemented independently, the communication interface 303, memory 301, and processor 302 can be interconnected via a bus and communicate with each other. The bus can be an Industry Standard Architecture (ISA) bus, a Peripheral Component Interconnect (PCI) bus, or an Extended Industry Standard Architecture (EISA) bus. The bus can be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 3 Only one thick line is used in the diagram, but this does not mean that there is only one bus or one type of bus.

[0068] Optionally, in a specific implementation, if the memory 301, the processor 302 and the communication interface 303 are integrated on a chip, the memory 301, the processor 302 and the communication interface 303 can communicate with each other through an internal interface.

[0069] The processor 302 may be a central processing unit (CPU), an application specific integrated circuit (ASIC), or one or more integrated circuits configured to implement the embodiments of the present application.

[0070] An embodiment of the present application further provides a computer-readable storage medium having a computer program or instruction stored thereon. When the computer program or instruction is executed by a processor, the above-mentioned engine lubrication system control method is implemented.

[0071] An embodiment of the present application also provides a computer program product, including a computer program or instructions, which, when executed, implements the above engine lubrication system control method.

[0072] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or N embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0073] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of technical features indicated. Thus, a feature specified as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of this application, "N" means at least two, for example, two, three, etc., unless otherwise specifically defined.

[0074] Any process or method description in a flowchart or otherwise described herein may be understood to represent a module, fragment or portion of code comprising one or N executable instructions for implementing a custom logical function or process step, and the scope of the preferred embodiments of the present application includes alternative implementations in which functions may be performed in a different order than shown or discussed, including performing functions in a substantially simultaneous manner or in a reverse order depending on the functions involved, which should be understood by those skilled in the art to which the embodiments of the present application pertain.

[0075] It should be understood that various parts of the present application can be implemented using hardware, software, firmware, or a combination thereof. In the above embodiment, the N steps or methods can be implemented using software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented using hardware, as in another embodiment, it can be implemented using any one or a combination of the following technologies known in the art: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, an application-specific integrated circuit having a suitable combination of logic gate circuits, a programmable gate array (PGA), a field programmable gate array (FPGA), etc.

[0076] Those skilled in the art will understand that all or part of the steps in the method of the above embodiment can be completed by instructing related hardware through a program, and the program can be stored in a computer-readable storage medium. When the program is executed, it includes one or a combination of the steps of the method embodiment.

Claims

1. A method for controlling a lubrication system of an engine, characterized in that: The following steps are involved: Detect the actual tilt angle of the aircraft; If the actual tilt angle exceeds the maximum tilt angle allowed by the engine's lubrication system, determining a target action in which the angle between the oil level of the lubrication system and the oil pan does not exceed the maximum angle based on the actual tilt angle; The aircraft is controlled to perform the target action.

2. The engine lubrication system control method according to claim 1, characterized in that: The target action of determining, based on the actual tilt angle, that the angle between the oil level of the lubrication system and the oil pan does not exceed the maximum angle includes: determining a target vertical acceleration applied to the oil pan according to the actual tilt angle; The target motion is generated according to the target vertical acceleration.

3. The engine lubrication system control method according to claim 2, characterized in that: Determining a target vertical acceleration applied to the oil pan according to the actual tilt angle includes: Obtaining a correspondence between the actual tilt angle and the target vertical acceleration; The target vertical acceleration is determined by searching for a corresponding relationship according to the actual tilt angle.

4. The engine lubrication system control method according to claim 2, characterized in that: Generating the target action according to the target vertical acceleration includes: Obtaining the total acceleration of the aircraft; determining a target angle between the aircraft and a normal to a plane containing a longitudinal direction and an axial direction of the aircraft based on the total acceleration, the target vertical acceleration, and the maximum angle; The actual tilt angle of the aircraft is controlled according to the target angle.

5. A lubrication system control device for an engine, characterized in that: include: A detection module is used to detect the actual tilt angle of the aircraft; a determination module configured to determine, if the actual tilt angle exceeds a maximum tilt angle allowed by a lubrication system of the engine, a target action in which the angle between the oil level of the lubrication system and the oil pan does not exceed the maximum angle based on the actual tilt angle; A control module is used to control the aircraft to perform the target action.

6. The engine lubrication system control device according to claim 5, characterized in that: The determining module is further configured to: determining a target vertical acceleration applied to the oil pan according to the actual tilt angle; The target motion is generated according to the target vertical acceleration.

7. The engine lubrication system control device according to claim 6, characterized in that: The determining module is further configured to: Obtaining a correspondence between the actual tilt angle and the target vertical acceleration; The target vertical acceleration is determined by searching for a corresponding relationship according to the actual tilt angle.

8. An aircraft, characterized in that: include: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the engine lubrication system control method according to any one of claims 1 to 4.

9. A computer-readable storage medium having a computer program or instruction stored thereon, characterized in that: The computer program or instruction is executed by a processor to implement the engine lubrication system control method according to any one of claims 1 to 4.

10. A computer program product comprising a computer program or instructions, characterized in that When the computer program or instruction is executed, the engine lubrication system control method according to any one of claims 1 to 4 is implemented.

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