Method and system for monitoring service life of intermittent working electric pump of airplane

Abstract

The invention belongs to the technical field of aircraft hydraulic systems, and discloses a method and a system for monitoring the service life of an intermittent working electric pump of an aircraft, which are used for detecting the outlet pressure and the rotating speed of all electric pumps on the aircraft in real time, and comprise the following steps: collecting the outlet pressure of each electric pump, collecting the rotating speed of each electric pump, and calculating the service life of each electric pump; the method comprises the following steps: acquiring the outlet pressure of each electric pump, judging whether the rotating speed is normal or not, independently recording the working time of each electric pump according to signals of the outlet pressure and the rotating speed of each electric pump, transmitting the working time of each electric pump to an OMS (Open Management System) and accumulating, and sending a replacement prompt to the electric pump of which the accumulated working time is higher than or close to a life threshold according to the life threshold of the electric pump. The service time of the intermittent working electric pump of the aircraft is automatically calculated in real time through the computer, the service life of the intermittent working electric pump can be accurately calculated, the service time of the intermittent working electric pump on the aircraft is prolonged, and the operation cost of the aircraft is reduced.

Description

Technical Field

[0001] This invention belongs to the field of aircraft hydraulic system technology, and relates to an electric pump maintenance system in an aircraft hydraulic system, specifically to a method and system for monitoring the life of an intermittently operating electric pump in an aircraft. Background Technology

[0002] Some electric pumps on aircraft are used to supplement the system during periods of high flow demand or as backup power in the event of a main pump failure. These electric pumps operate intermittently, therefore their lifespan cannot be calculated based on aircraft flight hours. Currently, the common method is for designers to use statistical data combined with equipment failure rates to comprehensively assess and convert this data into flight hours for electric pump lifespan control. However, this lifespan monitoring method has poor accuracy, significantly shortens the service life of electric pumps, and increases aircraft operating costs. Summary of the Invention

[0003] To address the aforementioned problems, this invention provides a method and system for monitoring the lifespan of intermittently operating electric pumps in aircraft. This method can accurately monitor the usage time of each electric pump, extend the onboard lifespan of intermittently operating electric pumps, and reduce aircraft operating costs.

[0004] The technical solution of the present invention is as follows: A method for monitoring the lifespan of intermittently operating electric pumps on an aircraft, which involves real-time monitoring of the outlet pressure and rotational speed of all electric pumps on the aircraft, includes the following steps: S1, collects the outlet pressure of each electric pump; S2, collect the rotational speed of each electric pump and determine whether the rotational speed is normal; S3 records the working time of each electric pump individually based on the signals of the outlet pressure and speed of each electric pump; S4 transmits the operating time of each electric pump to the OMS system and accumulates it; S5 issues a replacement reminder for electric pumps whose cumulative working time is higher than or close to the lifespan threshold, based on the electric pump's lifespan threshold.

[0005] Furthermore, in S2, the speed is judged to be normal based on the physical property of the electric pump speed reaching the extreme value and the range of the speed sensor. If the speed of an electric pump is judged to be abnormal, the signal of abnormal electric pump speed sensor and electric pump ID number are output to the OMS system, and the speed judgment result of the corresponding electric pump is ignored in subsequent steps.

[0006] Furthermore, in S3, the computer starts timing when it senses a high outlet pressure signal or a speed signal from the electric pump, and stops timing when it senses a low pressure signal or no speed signal, calculating the continuous working time of the electric pump for one cycle, which is recorded as... .

[0007] Furthermore, in S3, during ground maintenance, the continuous operating time of the electric pump is recorded via the ground maintenance panel and counted as... .

[0008] Furthermore, in S3, the algorithm for the cumulative working time of the electric pump is as follows:

[0009] In the formula: —Total cumulative working time of the i-th electric pump; —The operating time of the i-th electric pump during aircraft operation; —The single working time of the i-th electric pump during mechanical maintenance; —Number of times the i-th electric pump operates; —Number of maintenance tasks performed on the i-th electric pump.

[0010] Furthermore, in the working time recording in S3, the start time is based on whichever comes first, the high outlet pressure signal or the speed signal of the electric pump. That is, the recording of the electric pump's working time begins as soon as either the high outlet pressure signal or the speed signal arrives first.

[0011] Furthermore, in the working time record in S3, the end time is based on the later of the low outlet pressure signal and the no speed signal of the electric pump. That is, the recording of the electric pump working time ends when either the low outlet pressure signal or the no speed signal is reached.

[0012] An aircraft intermittent working electric pump life monitoring system is used to run the aforementioned aircraft intermittent working electric pump life monitoring method. It includes a management computer, an OMS system, pressure sensors, speed sensors, and a ground maintenance panel. Each electric pump is equipped with a pressure sensor and a speed sensor. The signals from all pressure sensors and speed sensors are transmitted to the management computer. The management computer is communicatively connected to the OMS system. The ground maintenance panel is connected to the management computer through an aircraft maintenance input interface.

[0013] Technical effects: 1. This invention uses a computer to automatically calculate the usage time of intermittent electric pumps in real time, which can accurately calculate the service life of intermittent electric pumps, extend the usage time of intermittent electric pumps on the aircraft, and reduce the operating costs of the aircraft.

[0014] 2. This invention can perform individual life calculations for all electric pumps in the entire aircraft, and the calculations will not stop during flight or ground maintenance. Therefore, the calculated data is accurate and can determine the specific electric pumps that need to be replaced. Attached Figure Description

[0015] Figure 1 This is a structural diagram of the aircraft intermittent electric pump life monitoring system provided by the present invention; Figure 2 This is a flowchart of the life monitoring method for intermittently operating electric pumps in aircraft provided by the present invention. Detailed Implementation

[0016] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific design details are set forth in the following detailed description to provide a more complete understanding of the invention. However, it will be apparent to those skilled in the art that the invention can be practiced without some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setup and method set forth below, but covers any improvements, substitutions, and modifications to the structures, methods, and devices without departing from the spirit of the invention. In the drawings and the following description, any parts not exhaustively described are considered to be common knowledge or conventional practices in the art.

[0017] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0018] Example 1: A method for monitoring the lifespan of intermittently operating electric pumps on an aircraft, which involves real-time monitoring of the outlet pressure and rotational speed of all electric pumps on the aircraft, includes the following steps: S1, collects the outlet pressure of each electric pump; S2, collect the rotational speed of each electric pump and determine whether the rotational speed is normal; S3 records the working time of each electric pump individually based on the signals of the outlet pressure and speed of each electric pump; S4 transmits the operating time of each electric pump to the OMS system and accumulates it; S5 issues a replacement reminder for electric pumps whose cumulative working time is higher than or close to the lifespan threshold, based on the electric pump's lifespan threshold.

[0019] In S2, the speed is determined to be normal based on the physical properties of the electric pump speed reaching the extreme value and the range of the speed sensor. If the speed of an electric pump is determined to be abnormal, a signal indicating that the electric pump speed sensor is abnormal and the electric pump ID number are output to the OMS system, and the speed determination result of the corresponding electric pump is ignored in subsequent steps.

[0020] In S3, the computer starts timing when it senses a high pressure signal or a speed signal from the electric pump outlet, and stops timing when it senses a low pressure signal or no speed signal. It then calculates the continuous working time of one cycle of the electric pump, which is recorded as... .

[0021] In S3, during ground maintenance, the continuous operating time of the electric pump is recorded via the ground maintenance panel and counted as [duration]. .

[0022] In S3, the algorithm for the cumulative working time of the electric pump is as follows:

[0023] In the formula: —Total cumulative working time of the i-th electric pump; —The operating time of the i-th electric pump during aircraft operation; —The single working time of the i-th electric pump during mechanical maintenance; —Number of times the i-th electric pump operates; —Number of maintenance tasks performed on the i-th electric pump.

[0024] In the working time record in S3, the start time is based on whichever comes first, the high outlet pressure signal or the speed signal of the electric pump. That is, the recording of the electric pump working time begins as soon as either the high outlet pressure signal or the speed signal arrives first.

[0025] In the working time record in S3, the end time is based on the later of the low outlet pressure signal and the no speed signal of the electric pump. That is, the recording of the electric pump working time ends when either the low outlet pressure signal or the no speed signal is reached.

[0026] An aircraft intermittent working electric pump life monitoring system is used to run the aforementioned aircraft intermittent working electric pump life monitoring method. It includes a management computer, an OMS system, pressure sensors, speed sensors, and a ground maintenance panel. Each electric pump is equipped with a pressure sensor and a speed sensor. The signals from all pressure sensors and speed sensors are transmitted to the management computer. The management computer is communicatively connected to the OMS system. The ground maintenance panel is connected to the management computer through an aircraft maintenance input interface.

[0027] Example 2: See Figure 1 This is a structural diagram of an embodiment of the aircraft intermittent electric pump life monitoring system provided by the present invention.

[0028] The electric pump outlet pressure signal sensor collects the electric pump outlet pressure and converts it into an electrical signal, which is then sent to the management computer. The electric pump speed sensor and force sensor collect the electric pump speed and convert it into an electrical signal, which is then sent to the management computer. The management computer supplies power to the electric pump outlet pressure signaler and the electric pump speed sensor, and receives and processes the electric pump outlet pressure and electric pump speed signals. At the same time, it judges the status of the speed sensor according to the preset threshold and issues corresponding alarms. The management computer is equipped with a ground maintenance interface for receiving and storing the working time records of the electric pump operated by the maintenance crew; The management computer calculates the operating time of the electric pump during aircraft operation based on the collected electric pump outlet pressure and electric pump speed. The management computer sums the calculated electric pump operating time during aircraft operation and during aircraft maintenance to obtain the electric pump operating time, and compares it with the pre-built electric pump lifespan, outputting corresponding prompts and alarms. The OMS system receives relevant maintenance and alarm information from the management computer and informs the maintenance personnel using the onboard maintenance display screen.

[0029] See Figure 2 This is a flowchart of the life monitoring method for intermittently operating electric pumps in aircraft provided by the present invention.

[0030] The present invention provides a method for monitoring the lifespan of an intermittently operating electric pump in aircraft. In specific implementation, the method includes the following steps: Step 1: Collect and determine the outlet pressure of the electric pump; Step 2: Collect and determine the electric pump speed; if a fault occurs, output the corresponding sensor alarm. Step 3: Collect and store the time when the ground maintenance crew uses the electric pump; Step 4: Calculate the total working time of the electric pump according to the corresponding algorithm; Step 5: Establish the electric pump lifespan threshold; Step 6: Compare the electric pump's operating time with its lifespan threshold and send the relevant information to the onboard OMS system.

[0031] Example 3: To achieve the objective of this invention, a method for monitoring the lifespan of an intermittently operating electric pump in an aircraft is provided according to a first aspect of the invention, characterized by comprising the following steps: S1: The outlet pressure of the i-th intermittently operating electric pump is collected, i=1,2,3……n; S2: Collect the speed of the i-th intermittently operating electric pump and determine whether the speed is normal; S3: Read and record the maintenance working time of the i-th intermittent electric pump; S4: Construct the algorithm for the working time of the i-th intermittent electric pump; S5: Calculate the working time of the i-th intermittent electric pump according to the algorithm and transmit the data to the OMS system; S6: Establish lifespan thresholds for electric pumps; S7: Compare the calculated working time of the i-th intermittent electric pump with the electric pump lifespan threshold. If it exceeds the electric pump lifespan threshold, report that the electric pump needs to be replaced. The logic for determining whether the rotational speed is normal in step S2 is based on the physical properties of the electric pump's rotational speed and the range of the speed sensor. In this example, it is [-50 r / min, +10000 r / min]. If the rotational speed exceeds this range, an abnormality is output to the OMS system for the electric pump speed sensor. The algorithm for constructing the intermittent electric pump timing in step S4 is as follows: the computer starts timing when it senses a high-pressure signal or a speed signal at the electric pump outlet, and stops timing when it senses a low-pressure signal or no speed signal, calculating the duration of one cycle of the electric pump. To ensure that the operating time of the electric pump is also recorded when the maintenance crew is performing ground maintenance (with the HECU not powered on), this operating time is counted as... The algorithm for calculating the cumulative working time of the electric pump is as follows:

[0032] In the formula: —Total cumulative working time of the i-th electric pump; —Single working time of the i-th electric pump during aircraft operation; —Single working time during the maintenance of the i-th electric pump; —Number of times the i-th electric pump operates; —Number of maintenance tasks performed on the i-th electric pump.

[0033] The electric pump's outlet pressure and speed signal are determined by whichever arrives first; that is, the electric pump's working time is recorded starting from whichever signal arrives first. If the speed signal is faulty and alarmed, the outlet pressure is used directly for calculation. The low outlet pressure and no speed signal of the S electric pump are based on the last signal received. That is, the recording of the electric pump's working time ends when the last signal arrives. If it is a speed signal fault alarm, the outlet pressure is used directly for calculation. The high pressure at the outlet of the electric pump is determined based on the physical relationship between the working pressure build-up and the working pressure of the electric pump in the system. In this embodiment, the high pressure threshold at the outlet of the electric pump is 11 MPa, and the low pressure threshold is 9 MPa. A hysteresis loop is set between the high pressure and low pressure thresholds for signal filtering. The speed of the electric pump is determined based on the physical relationship of the electric pump's starting speed in the system and the accuracy of the speed sensor. In this embodiment, the speed threshold of the electric pump is higher than 100 r / min, and the speed threshold is 50 r / min. A hysteresis loop is set for the speed threshold and the speed threshold for signal filtering. The lifespan threshold of the i-th electric pump in step S6 is obtained based on the data from the lifespan test of each electric pump. Generally, it is given with a margin of about 5 typical flight sorties based on the lifespan test results. In this example, the electric pump lifespan is 450 hours, and after giving a 30-hour margin, the alarm threshold is 420 hours. When the electric pump operating time calculated by the algorithm in S9 is lower than this value, a prompt indicating that the i-th electric pump needs to be replaced is output to the OMS system, and the prompt is in amber color. If it continues to be used until 440 hours, a warning that the i-th electric pump needs to be replaced is output to the OMS system, and the warning is in red color, and at the same time, an alarm that the aircraft should not be released before the electric pump is replaced is given.

[0034] According to a second aspect of the present invention, a life monitoring system for an intermittently operating electric pump for aircraft is provided, characterized in that it comprises: The electric pump outlet pressure signaler is used to collect the electric pump outlet pressure and send the data packet to the management computer; An electric pump speed sensor is used to collect the electric pump speed and send the data packet to the management computer; The management computer is used to determine whether the electric pump speed sensor is working properly and to calculate and determine whether the electric pump's operating time exceeds the electric pump's lifespan threshold, and sends the results to the onboard OMS system. The OMS system receives alarm signals output by the management computer and sends relevant equipment maintenance information to the maintenance department. The number of electric pumps is n, where n is greater than or equal to 1; The pressure signal generator and speed sensor are connected to the management computer via power cables and are powered by the management computer; the speed sensor is connected to the management computer via a signal cable and transmits the generated electrical signal to the management computer. The OMS system is connected to the management computer via a cable. Signals are transmitted between the management computer and the OMS system via a bus, and the bus protocol may be any of the conventional buses.

[0035] In one possible embodiment, the connection between the management computer and the OMS system may also be transmitted via analog signals.

[0036] In one possible embodiment, the electric pump speed sensor may be powered by a separate power supply.

[0037] In one possible embodiment, the number of pressure signals generated by the electric pump outlet pressure signaler is greater than or equal to 1, and the multi-channel electrical signals are used by a management computer to comprehensively determine the magnitude of the electric pump outlet pressure.

[0038] In one possible embodiment, the electric pump speed sensor generates a speed signal of more than or equal to 1, and the multi-channel speed signals are used by a management computer to comprehensively determine the speed of the electric pump.

[0039] The above description is only a preferred embodiment of the present invention. It should be noted that those skilled in the art can make several improvements without departing from the principle of the present invention, and these improvements should also be considered within the scope of protection of the present invention.

Claims

1. A method for monitoring the lifespan of an intermittently operating electric pump in an aircraft, characterized in that, Real-time monitoring of the outlet pressure and speed of all electric pumps on the aircraft includes the following steps: S1, collects the outlet pressure of each electric pump; S2, collect the rotational speed of each electric pump and determine whether the rotational speed is normal; S3 records the working time of each electric pump individually based on the signals of the outlet pressure and speed of each electric pump; S4 transmits the operating time of each electric pump to the OMS system and accumulates it; S5 issues a replacement reminder for electric pumps whose cumulative working time is higher than or close to the lifespan threshold, based on the electric pump's lifespan threshold.

2. The method for monitoring the lifespan of an intermittently operating electric pump in an aircraft according to claim 1, characterized in that, In S2, the speed is determined to be normal based on the physical properties of the electric pump speed reaching the extreme value and the range of the speed sensor. If the speed of an electric pump is determined to be abnormal, a signal indicating that the electric pump speed sensor is abnormal and the electric pump ID number are output to the OMS system, and the speed determination result of the corresponding electric pump is ignored in subsequent steps.

3. The method for monitoring the lifespan of an intermittently operating electric pump in an aircraft according to claim 1, characterized in that, In S3, the computer starts timing when it senses a high pressure signal or a speed signal from the electric pump outlet, and stops timing when it senses a low pressure signal or no speed signal. It then calculates the continuous working time of one cycle of the electric pump, which is recorded as... .

4. The method for monitoring the lifespan of an intermittently operating electric pump in an aircraft according to claim 3, characterized in that, In S3, during ground maintenance, the continuous operating time of the electric pump is recorded via the ground maintenance panel and counted as [duration]. .

5. The method for monitoring the lifespan of an intermittently operating electric pump in an aircraft according to claim 4, characterized in that, In S3, the algorithm for the cumulative working time of the electric pump is as follows: In the formula: —Total cumulative working time of the i-th electric pump; —The operating time of the i-th electric pump during aircraft operation; —The single working time of the i-th electric pump during mechanical maintenance; —Number of times the i-th electric pump operates; —Number of maintenance tasks performed on the i-th electric pump.

6. The method for monitoring the lifespan of an intermittently operating electric pump in an aircraft according to claim 3, characterized in that, In the working time record in S3, the start time is based on whichever comes first, the high outlet pressure signal or the speed signal of the electric pump. That is, the recording of the electric pump working time begins as soon as either the high outlet pressure signal or the speed signal arrives first.

7. The method for monitoring the lifespan of an intermittently operating electric pump in an aircraft according to claim 3, characterized in that, In the working time record in S3, the end time is based on the later of the low outlet pressure signal and the no speed signal of the electric pump. That is, the recording of the electric pump working time ends when either the low outlet pressure signal or the no speed signal is reached.

8. A life monitoring system for an intermittently operating electric pump for aircraft, used to operate the life monitoring method for an intermittently operating electric pump for aircraft as described in any one of claims 1-7, characterized in that, It includes a management computer, an OMS system, pressure sensors, speed sensors, and a ground maintenance panel. Each electric pump is equipped with a pressure sensor and a speed sensor. All signals from the pressure and speed sensors are transmitted to the management computer, which communicates with the OMS system. The ground maintenance panel is connected to the management computer through a machine input interface.

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