Method, system and aircraft for predicting remaining useful life of aircraft

Abstract

The present invention provides a method, system and aircraft for predicting the remaining service life of an aircraft, the method comprising: determining the target torque of the aircraft's motor by operating an electronic speed regulator input by a ground operator, collecting the actual torque of the aircraft's motor according to the torque sensor on the motor; determining the corresponding fluctuation coefficient according to the target torque and actual torque of the aircraft's motor at the same time; determining the vibration state of the aircraft according to the fluctuation coefficient and the corresponding flight conditions; and determining the remaining service life of the aircraft according to the aircraft vibration state. The present invention first determines the fluctuation coefficient at this time according to the target torque and actual torque at the same time, and the flight conditions of the aircraft at this time can be reflected by the fluctuation coefficient. Under different flight conditions, the corresponding fluctuation coefficient can be used as the difference between the target torque and the actual torque to obtain the corresponding aircraft vibration state, and the remaining service life of the aircraft can be accurately predicted in real time through the aircraft vibration state.

Description

Technical Field

[0001] The present invention relates to the field of aircraft technology, and in particular to a method and system for predicting the remaining useful life of an aircraft, and an aircraft. Background Art

[0002] The service life of an aircraft refers to the period of time during which the aircraft can maintain safe flight performance under normal use and maintenance. The length of an aircraft's service life is affected by many factors, including manufacturing quality, flight conditions, maintenance and driving habits.

[0003] Currently, the remaining useful life of an aircraft is usually estimated by its years of use. However, due to different flight conditions and different control and driving habits of operators, the estimated remaining useful life of an aircraft is very inaccurate. Summary of the invention

[0004] The problem solved by the present invention is how to improve the prediction accuracy of the remaining service life of an aircraft.

[0005] In order to solve the above problems, the present invention provides a method, system and aircraft for predicting the remaining useful life of an aircraft.

[0006] According to a first embodiment, the present invention provides a method for predicting the remaining useful life of an aircraft, comprising: The target torque of the aircraft's motor is determined by the ground operator operating the electronic speed regulator input, and the actual torque of the aircraft's motor is collected by the torque sensor on the motor; Determine the corresponding fluctuation coefficient according to the target torque and the actual torque of the aircraft motor at the same time; Determining the vibration state of the aircraft based on the fluctuation coefficient and the corresponding flight conditions recorded; A remaining useful life of the aircraft is determined based on the aircraft vibration state.

[0007] Optionally, determining the fluctuation coefficient according to the target torque and the actual torque includes: The fluctuation coefficient is determined according to the target torque and the actual torque, wherein the actual torque is obtained by a torque sensor.

[0008] Optionally, determining the fluctuation coefficient according to the target torque and the actual torque includes: The fluctuation coefficient is determined according to the target torque and the actual torque, wherein the influencing factors include wind, rain and other conditions.

[0009] Optionally, recording the flight conditions includes: After the aircraft takes off, the flight conditions are recorded using the recorder of the aircraft.

[0010] Optionally, determining the aircraft vibration state according to the fluctuation coefficient includes: Determining the vibration state of the aircraft according to the fluctuation coefficient according to a preset corresponding relationship, wherein the preset corresponding relationship is determined by an aircraft vibration calibration test; The vibration state of the aircraft is determined according to the fluctuation coefficient and the preset corresponding relationship.

[0011] Optionally, determining the remaining service life of the aircraft according to the vibration state of the aircraft includes: determining the fatigue life of the aircraft based on the vibration state of the aircraft; The remaining service life is determined according to a preset expected aircraft life and a fatigue life of the aircraft.

[0012] According to a second aspect embodiment, the present invention provides an aircraft remaining useful life prediction system, comprising a computer-readable storage medium storing a computer program and a processor, wherein the computer program is read and executed by the computer processor to implement the aircraft remaining useful life prediction method.

[0013] According to a third aspect of the embodiment, the present invention provides an aircraft, comprising the above-mentioned aircraft remaining useful life prediction system.

[0014] The present invention first determines the fluctuation coefficient according to the target torque and the actual torque corresponding to the same time, determines the vibration state of the aircraft according to the fluctuation coefficient and the preset corresponding relationship, and determines the remaining service life of the aircraft according to the vibration state of the aircraft. The aircraft does not need to add too many hardware systems, so the implementation cost is very low. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 The figure is a flow chart of a method for predicting the remaining useful life of an aircraft according to an embodiment of the present invention.

[0016] Figure 2 This is a block diagram of an aircraft according to an embodiment of the present invention.

[0017] Figure 3 The figure is a schematic diagram of the structure of an electronic device in an aircraft according to an embodiment of the present invention. DETAILED DESCRIPTION

[0018] Existing technologies generally estimate the remaining useful life of an aircraft by the years of use; The remaining useful life of an aircraft is a very complex issue that requires a comprehensive assessment based on various factors. Due to a combination of factors such as driving habits, flight conditions, and maintenance, estimating the remaining useful life of an aircraft based on years of use will result in a very inaccurate estimate of the remaining useful life.

[0019] In order to more clearly understand the above-mentioned objects, features and advantages of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that although certain embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be interpreted as being limited to the embodiments described herein. On the contrary, these embodiments are provided to provide a more thorough and complete understanding of the present invention. It should be understood that the drawings and embodiments of the present invention are only for exemplary purposes and are not intended to limit the scope of protection of the present invention.

[0020] It should be understood that the various steps described in the method implementation of the present invention may be performed in different orders, and furthermore, the method implementation may include other additional steps. The scope of the present invention is not limited in this respect.

[0021] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on", the term "one embodiment" means "at least one embodiment"; the term "optionally" means "optional embodiment". It should be noted that the concepts of "first", "second", etc. mentioned in the present invention are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0022] like Figure 1 As shown, an embodiment of the present invention provides a method for predicting the remaining useful life of an aircraft, comprising: The target torque of the aircraft's motor is determined by the ground operator operating the electronic speed regulator input, and the actual torque of the aircraft's motor is collected based on the torque sensor on the motor.

[0023] Specifically, there is a close relationship between the target torque and the electronic speed governor controlled by the ground operator. The input value of the electronic speed governor determines the target torque of the aircraft. The realization of the target torque needs to be completed through the adjustment of the aircraft motor control system so that it can adapt to various flight conditions. Specifically, it includes: Electronic speed governor output: The electronic speed governor is used by ground operators to control the output power of the aircraft motor by rotating the electronic speed governor knob; Motor control system adjustment: The motor control unit will output the parameters of the aircraft motor according to the control of the ground operator and the flight status at the same time, and produce an output that meets the target torque; Motor torque response: The torque output by the aircraft motor is transmitted to the rotor through the transmission system, ultimately driving the aircraft.

[0024] Compare the target torque and actual torque of the aircraft motor at the same time to determine the corresponding fluctuation coefficient.

[0025] Specifically, after the aircraft is powered on, during the flight of the aircraft, the target torque and actual torque of the aircraft motor at the same time are compared to determine the corresponding fluctuation coefficient. The fluctuation coefficient during the flight of the aircraft is related to the operating habits of ground operators, flight conditions, and weather conditions. These factors combined may cause the aircraft and its components to receive huge loads and stresses during the flight, thereby affecting the durability and fatigue life of the aircraft and its components.

[0026] Among them, the flight conditions include various flight conditions such as the aircraft's ascent and takeoff phase, deceleration flight phase, acceleration flight phase, constant speed flight phase, rainy environment, strong wind environment, high temperature environment, cold environment, etc.

[0027] The vibration state of the aircraft is determined according to the fluctuation coefficient and the preset corresponding relationship.

[0028] Specifically, the vibration state of the aircraft is determined according to the fluctuation coefficient and the preset corresponding relationship, and the fatigue status of the components can be reflected through the vibration state of the entire aircraft.

[0029] Among them, aircraft parts are subjected to various static and dynamic loads during flight, which can lead to fatigue of parts. Fatigue is the gradual accumulation of strain deformation caused by alternating stress changes in structural materials, which can eventually lead to component failure.

[0030] A remaining useful life of the aircraft is determined based on the aircraft vibration state.

[0031] Specifically, the fatigue service life of the aircraft is determined according to the vibration state of the aircraft, and then the fatigue service life is subtracted from the expected life of the aircraft production to obtain the remaining service life of the aircraft.

[0032] Another embodiment of the present invention provides an aircraft remaining useful life prediction system, including a computer-readable storage medium storing a computer program and a processor, wherein the computer program is read and executed by the computer processor to implement the aircraft remaining useful life prediction method.

[0033] Another embodiment of the present invention provides an aircraft, Figure 2As shown, it includes the above-mentioned aircraft remaining service life prediction system.

[0034] Another embodiment of the present invention provides an electronic device, which may be the above-mentioned aircraft remaining service life prediction system, combined with Figure 3 As shown, the electronic device includes a central processing unit 301, which can perform various appropriate actions and processes according to the program stored in the memory 302. Various programs and data required for the operation of the electronic device 300 are stored in the memory 302. Removable media 305, such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, etc., the central processing unit 301, the memory 302, the receiver 303, the transmitter 304, and the removable media 305 are connected to each other through a bus 306.

[0035] The functions described herein may be implemented in hardware, software executed by a processor, firmware, or any combination thereof. If implemented in software executed by a processor, the functions may be stored as one or more instructions or codes on a computer-readable medium or transmitted via a computer-readable medium. Other examples and implementations are within the scope and spirit of the present application and the appended claims. For example, due to the nature of software, the functions described above may be implemented using software executed by a processor, hardware, firmware, hard wiring, or a combination of any of these. In addition, each functional unit may be integrated into a processing unit, each unit may exist physically separately, or two or more units may be integrated into one unit.

[0036] Although the present invention is disclosed as above, the protection scope of the present invention is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A method for predicting the remaining useful life of an aircraft, characterized in that: include: The target torque of the aircraft's motor is determined by the ground operator operating the electronic speed regulator input, and the actual torque of the aircraft's motor is collected by the torque sensor on the motor; Determine the corresponding fluctuation coefficient according to the target torque and the actual torque of the aircraft motor at the same time; Determining the vibration state of the aircraft based on the fluctuation coefficient and the corresponding flight conditions; A remaining useful life of the aircraft is determined based on the aircraft vibration state.

2. The method for predicting the remaining useful life of an aircraft according to claim 1, characterized in that: Determining the fluctuation coefficient according to the target torque and the actual torque includes: The fluctuation coefficient is determined according to the target torque and the actual torque, wherein the actual torque is obtained by a torque sensor.

3. The method for predicting the remaining useful life of an aircraft according to claim 2, characterized in that: Determining the fluctuation coefficient according to the target torque and the actual torque includes: The fluctuation coefficient is determined according to the target torque and the actual torque, wherein the influencing factors include wind, rain and other conditions.

4. The method for predicting the remaining useful life of an aircraft according to claim 1, characterized in that: The recorded flight conditions include: After the aircraft takes off, the flight conditions are recorded using the recorder of the aircraft.

5. The method for predicting the remaining useful life of an aircraft according to claim 1, characterized in that: Determining the aircraft vibration state according to the fluctuation coefficient comprises: According to a preset corresponding relationship, determining the vibration state of the aircraft according to the fluctuation coefficient, wherein the preset corresponding relationship is determined by an aircraft vibration calibration test; The vibration state of the aircraft is determined according to the fluctuation coefficient and the preset corresponding relationship.

6. The method for predicting the remaining useful life of an aircraft according to claim 5, characterized in that: Determining the remaining service life of the aircraft according to the vibration state of the aircraft comprises: determining the fatigue life of the aircraft based on the vibration state of the aircraft; The remaining service life is determined according to a preset expected aircraft life and a fatigue life of the aircraft.

7. An aircraft remaining useful life prediction system, characterized in that: It comprises a computer-readable storage medium storing a computer program and a processor, wherein the computer program is read and executed by the computer processor to implement the aircraft remaining service life prediction method as claimed in claims 1 to 6.

8. An aircraft, characterized in that: The invention comprises the aircraft remaining useful life prediction system as described in claim 7.

Images