Aircraft hydraulic power conversion method and apparatus

Abstract

The application belongs to the technical field of aircraft design and relates to an aircraft hydraulic energy conversion method and device. The method comprises the following steps: S1, acquiring a pressure signal of a main hydraulic system; S2, starting timing when the pressure of the main hydraulic system is reduced below a first threshold value; S3, acquiring an oil tank oil amount signal of the main hydraulic system when the timing time exceeds a set value; S4, acquiring a pressure signal of a backup hydraulic system when the oil tank oil amount of the main hydraulic system is within a given normal interval; and S5, when the pressure of the backup hydraulic system is higher than a second threshold value, controlling a selection valve installed at a junction to switch the main hydraulic system pipeline connected with an input pipeline to the backup hydraulic system pipeline. The application not only meets the configuration requirement of a multi-path hydraulic energy system of a user, but also avoids the fault spreading among multi-path hydraulic systems, and greatly improves the safety of an aircraft system.

Description

A method and apparatus for converting hydraulic energy in aircraft Technical Field

[0001] This application belongs to the field of aircraft design technology, and specifically relates to a method and device for converting hydraulic energy in aircraft. Background Technology

[0002] Current and future aircraft have increasingly stringent safety requirements for control surfaces, often necessitating multiple hydraulic power sources to meet these demands. However, the number of hydraulic actuators (hydraulic users) driving the control surfaces is often limited. Therefore, a backup hydraulic system is needed to provide redundancy. To address this, an energy selection valve is commonly used. This valve is installed at the user's end, requiring pressure from two hydraulic systems (main and backup). When switching is needed, it can automatically or passively switch between the two systems. Currently, both domestically and internationally, energy selection valves switch when the main hydraulic system is under pressure. However, when the main hydraulic system experiences leakage, especially near the user's pipeline, the conventional switching algorithm assumes low pressure and switches the system connected to the user's pipeline to the backup system. This energy switch can then cause continued leakage in the backup system, leading to a cascading failure and potentially compromising aircraft safety. Summary of the Invention

[0003] In order to solve at least one of the above-mentioned technical problems, this application designs a method and device for aircraft hydraulic energy conversion to avoid the spread of faults between multiple hydraulic systems.

[0004] The first aspect of this application provides a method for converting hydraulic energy in an aircraft. The aircraft hydraulic system includes a main hydraulic system and a backup hydraulic system. At the junction of the main hydraulic system and the backup hydraulic system, a selector valve selectively connects one of the pipelines to the input pipeline of the airborne control surface actuator. The method includes:

[0005] Step S1: Obtain the pressure signal of the main hydraulic system;

[0006] Step S2: Determine whether the pressure of the main hydraulic system has dropped below the first threshold. If the pressure of the main hydraulic system drops below the first threshold, start timing; otherwise, return to step S1 and continue monitoring the pressure signal of the main hydraulic system.

[0007] Step S3: Determine whether the timing time exceeds the set value. When the timing time exceeds the set value, obtain the oil level signal of the main hydraulic system's oil tank.

[0008] Step S4: Determine whether the oil level in the main hydraulic system's tank is within the given normal range. If the oil level in the main hydraulic system's tank is within the given normal range, obtain the pressure signal of the backup hydraulic system.

[0009] Step S5: Determine that the pressure of the backup hydraulic system is higher than the second threshold. When the pressure of the backup hydraulic system is higher than the second threshold, control the selector valve installed at the junction to switch the main hydraulic system pipeline connected to the input pipeline to the backup hydraulic system pipeline.

[0010] Preferably, in step S2, the first threshold value is selected as any value between 9 and 11 MPa.

[0011] Preferably, in step S3, the set value is 4 to 6 seconds.

[0012] Preferably, in step S4, determining whether the oil level in the main hydraulic system's tank is within a given normal range includes:

[0013] Obtain the estimated current oil level in the main hydraulic system's tank from the onboard computing system;

[0014] Within a set time period, it is determined whether the oil level in the tank has dropped significantly. If the oil level in the tank has dropped significantly, the oil level in the main hydraulic system is not within the given normal range; otherwise, the oil level in the main hydraulic system is within the given normal range.

[0015] The determination of whether the oil tank level has dropped significantly includes determining whether the rate of drop in the oil tank level exceeds a set value within a set time period.

[0016] Preferably, in step S5, the second threshold value is selected as any value between 13 and 15 MPa.

[0017] A second aspect of this application provides an aircraft hydraulic energy conversion device. The aircraft hydraulic system includes a main hydraulic system and a backup hydraulic system. At the junction of the main hydraulic system and the backup hydraulic system, a selector valve selectively connects one of them to the input line of the airborne control surface actuator. The device includes:

[0018] The pressure signal acquisition module of the main hydraulic system is used to acquire the pressure signal of the main hydraulic system;

[0019] The timing module is used to determine whether the pressure of the main hydraulic system has dropped below a first threshold. When the pressure of the main hydraulic system drops below the first threshold, timing starts and the pressure signal acquisition module of the main hydraulic system is invoked to continuously monitor the pressure signal of the main hydraulic system.

[0020] The main hydraulic system's oil tank oil level signal acquisition module is used to determine whether the timing time exceeds the set value. When the timing time exceeds the set value, it acquires the main hydraulic system's oil tank oil level signal.

[0021] The backup hydraulic system pressure signal acquisition module is used to determine whether the oil level in the main hydraulic system tank is within a given normal range. When the oil level in the main hydraulic system tank is within a given normal range, the pressure signal of the backup hydraulic system is acquired.

[0022] The main backup system switching module is used to determine whether the pressure of the backup hydraulic system is higher than the second threshold. When the pressure of the backup hydraulic system is higher than the second threshold, it controls the selector valve installed at the junction to switch the main hydraulic system pipeline connected to the input pipeline to the backup hydraulic system pipeline.

[0023] Preferably, the pressure signal acquisition module of the backup hydraulic system includes:

[0024] The oil level estimate acquisition unit is used to acquire the current oil level estimate of the main hydraulic system's oil tank given by the airborne computing system;

[0025] The oil tank level drop detection unit is used to determine whether the oil tank level has dropped significantly within a set time period. If the oil tank level drops significantly, the oil level in the main hydraulic system is not within the given normal range; otherwise, the oil level in the main hydraulic system is within the given normal range.

[0026] The determination of whether the oil tank level has dropped significantly includes determining whether the rate of drop in the oil tank level exceeds a set value within a set time period.

[0027] This application, through the design of control logic for controlling the switching of energy selection valves, not only meets the user's configuration requirements for multi-channel hydraulic energy systems, but also avoids the spread of faults between multiple hydraulic systems, greatly improving the safety of aircraft systems. Attached Figure Description

[0028] Figure 1 is a flowchart of a preferred embodiment of the aircraft hydraulic energy conversion method of this application.

[0029] Figure 2 is a schematic diagram of data and oil circuit interaction between the system and the main hydraulic system, backup hydraulic system and hydraulic user of a preferred embodiment of the aircraft hydraulic energy conversion device of this application. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0031] The first aspect of this application provides a method for converting hydraulic energy in an aircraft. The aircraft hydraulic system includes a main hydraulic system and a backup hydraulic system. At the junction of the main and backup hydraulic systems, a selector valve connects one of the pipelines to the input pipeline of the airborne control surface actuator. As shown in Figure 1, the method mainly includes:

[0032] Step S1: Obtain the pressure signal of the main hydraulic system;

[0033] Step S2: Determine whether the pressure of the main hydraulic system has dropped below the first threshold. If the pressure of the main hydraulic system drops below the first threshold, start timing; otherwise, return to step S1 and continue monitoring the pressure signal of the main hydraulic system.

[0034] Step S3: Determine whether the timing time exceeds the set value. When the timing time exceeds the set value, obtain the oil level signal of the main hydraulic system's oil tank.

[0035] Step S4: Determine whether the oil level in the main hydraulic system's tank is within the given normal range. If the oil level in the main hydraulic system's tank is within the given normal range, obtain the pressure signal of the backup hydraulic system.

[0036] Step S5: Determine that the pressure of the backup hydraulic system is higher than the second threshold. When the pressure of the backup hydraulic system is higher than the second threshold, control the selector valve installed at the junction to switch the main hydraulic system pipeline connected to the input pipeline to the backup hydraulic system pipeline.

[0037] In step S2, the first threshold value is selected as any value between 9 and 11 MPa. In step S3, the set value is 4 to 6 seconds. In step S5, the second threshold value is selected as any value between 13 and 15 MPa. The following three embodiments will illustrate this further.

[0038] Example 1

[0039] Referring to Figure 2, this application incorporates an energy selection valve into a traditional dual-path hydraulic energy system (divided into a main hydraulic system and a backup hydraulic system). The control computer acquires the pressure signals of the main and backup hydraulic systems and the oil level signal of the main hydraulic system tank. The software in the control computer realizes the energy conversion between the main and backup hydraulic systems through logical judgment.

[0040] Referring to Figure 1, when the main hydraulic system pressure is normal, the control computer does not issue an energy conversion signal after logical judgment. This main hydraulic system outputs to the downstream user through the energy selection valve. When the main hydraulic system pressure received by the control computer drops below 10 MPa and remains below 10 MPa for 5 seconds, if the oil level in the main hydraulic system tank does not decrease significantly, the control computer then judges the received backup hydraulic system pressure signal. If the backup hydraulic system pressure is higher than 14 MPa, the control computer issues an energy conversion signal. The energy selection valve switches, isolating the main hydraulic system and outputting the backup hydraulic system to the downstream user. If any of the above judgment conditions are not met, the control computer does not issue an energy conversion signal and continues to output the main hydraulic system to the downstream user.

[0041] Example 2

[0042] When the main hydraulic system pressure is normal, the control computer does not issue an energy conversion signal after logical judgment. The main hydraulic system outputs to the downstream user through the energy selection valve. When the main hydraulic system pressure received by the control computer drops below 9 MPa and remains below 9 MPa for 6 seconds, if the oil level in the main hydraulic system tank does not decrease significantly, the control computer then judges the received backup hydraulic system pressure signal. If the backup hydraulic system pressure is higher than 14 MPa, the control computer issues an energy conversion signal. The energy selection valve switches, isolating the main hydraulic system and outputting the backup hydraulic system to the downstream user. If any of the above judgment conditions are not met, the control computer does not issue an energy conversion signal and continues to output the main hydraulic system to the downstream user.

[0043] Example 3

[0044] When the main hydraulic system pressure is normal, the control computer does not issue an energy conversion signal after logical judgment. The main hydraulic system outputs to the downstream user through the energy selection valve. When the main hydraulic system pressure received by the control computer drops below 11 MPa and remains below 11 MPa for 4 seconds, if the oil level in the main hydraulic system tank does not decrease significantly, the control computer then judges the received backup hydraulic system pressure signal. If the backup hydraulic system pressure is higher than 15 MPa, the control computer issues an energy conversion signal. The energy selection valve switches, isolating the main hydraulic system and outputting the backup hydraulic system to the downstream user. If any of the above judgment conditions are not met, the control computer does not issue an energy conversion signal and continues to output the main hydraulic system to the downstream user.

[0045] In some optional implementations, step S4, determining whether the oil level in the main hydraulic system's tank is within a given normal range, includes:

[0046] Obtain the estimated current oil level in the main hydraulic system's tank from the onboard computing system;

[0047] Within a set time period, it is determined whether the oil level in the tank has dropped significantly. If the oil level in the tank has dropped significantly, the oil level in the main hydraulic system is not within the given normal range; otherwise, the oil level in the main hydraulic system is within the given normal range.

[0048] The determination of whether the oil tank level has dropped significantly includes determining whether the rate of drop in the oil tank level exceeds a set value within a set time period.

[0049] In this embodiment, the rate of drop exceeding the set value is mainly used to determine whether the oil tank level has dropped significantly. Typically, for a hydraulic oil capacity of about 300L, if the oil tank level drops below 240L within 1 minute, the calculated rate of drop indicates that the oil tank level has dropped significantly, which is very likely caused by oil leakage in the downstream pipeline. In this case, the backup hydraulic circuit should not be switched, as this could cause the backup hydraulic system failure to spread. Instead, the failure should be reported and user-side maintenance should be performed.

[0050] A second aspect of this application provides an aircraft hydraulic energy conversion device. The aircraft hydraulic system includes a main hydraulic system and a backup hydraulic system. At the junction of the main hydraulic system and the backup hydraulic system, a selector valve selectively connects one of them to the input line of the airborne control surface actuator. The device includes:

[0051] The pressure signal acquisition module of the main hydraulic system is used to acquire the pressure signal of the main hydraulic system;

[0052] The timing module is used to determine whether the pressure of the main hydraulic system has dropped below a first threshold. When the pressure of the main hydraulic system drops below the first threshold, timing starts and the pressure signal acquisition module of the main hydraulic system is invoked to continuously monitor the pressure signal of the main hydraulic system.

[0053] The main hydraulic system's oil tank oil level signal acquisition module is used to determine whether the timing time exceeds the set value. When the timing time exceeds the set value, it acquires the main hydraulic system's oil tank oil level signal.

[0054] The backup hydraulic system pressure signal acquisition module is used to determine whether the oil level in the main hydraulic system tank is within a given normal range. When the oil level in the main hydraulic system tank is within a given normal range, the pressure signal of the backup hydraulic system is acquired.

[0055] The main backup system switching module is used to determine whether the pressure of the backup hydraulic system is higher than the second threshold. When the pressure of the backup hydraulic system is higher than the second threshold, it controls the selector valve installed at the junction to switch the main hydraulic system pipeline connected to the input pipeline to the backup hydraulic system pipeline.

[0056] In some optional embodiments, the pressure signal acquisition module of the backup hydraulic system includes:

[0057] The oil level estimate acquisition unit is used to acquire the current oil level estimate of the main hydraulic system's oil tank given by the airborne computing system;

[0058] The oil tank level drop detection unit is used to determine whether the oil tank level has dropped significantly within a set time period. If the oil tank level drops significantly, the oil level in the main hydraulic system is not within the given normal range; otherwise, the oil level in the main hydraulic system is within the given normal range.

[0059] The determination of whether the oil tank level has dropped significantly includes determining whether the rate of drop in the oil tank level exceeds a set value within a set time period.

[0060] This application, through the design of control logic for controlling the switching of energy selection valves, not only meets the user's configuration requirements for multi-channel hydraulic energy systems, but also avoids the spread of faults between multiple hydraulic systems, greatly improving the safety of aircraft systems.

[0061] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for converting hydraulic energy in an aircraft, wherein the aircraft hydraulic system includes a main hydraulic system and a backup hydraulic system, and the pipelines of the main hydraulic system and the backup hydraulic system are connected to the input pipeline of the airborne control surface actuator via a selector valve at the junction of the two systems, characterized in that, The method includes: Step S1, acquiring the pressure signal of the main hydraulic system; Step S2, determining whether the pressure of the main hydraulic system has dropped below a first threshold value; if the pressure of the main hydraulic system drops below the first threshold value, starting a timer; otherwise, returning to Step S1 and continuously monitoring the pressure signal of the main hydraulic system; Step S3, determining whether the timer exceeds a set value; if the timer exceeds the set value, acquiring the oil level signal of the main hydraulic system's tank; Step S4, determining whether the oil level of the main hydraulic system's tank is within a given normal range; if the oil level of the main hydraulic system's tank is within a given normal range, acquiring the pressure signal of the backup hydraulic system; Step S5, determining whether the pressure of the backup hydraulic system is higher than a second threshold value; if the pressure of the backup hydraulic system is higher than the second threshold value, controlling the selector valve installed at the junction to switch the main hydraulic system pipeline connected to the input pipeline to the backup hydraulic system pipeline.

2. The aircraft hydraulic energy conversion method as described in claim 1, characterized in that, In step S2, the first threshold value is selected as any value between 9 and 11 MPa.

3. The aircraft hydraulic energy conversion method as described in claim 1, characterized in that, In step S3, the set value is 4 to 6 seconds.

4. The aircraft hydraulic energy conversion method as described in claim 1, characterized in that, In step S4, determining whether the oil level in the main hydraulic system's tank is within a given normal range includes: obtaining the estimated current oil level in the main hydraulic system's tank given by the airborne computing system; determining whether the tank level has significantly decreased within a set time period; if the tank level has significantly decreased, then the oil level in the main hydraulic system's tank is not within the given normal range; otherwise, the oil level in the main hydraulic system's tank is within the given normal range; wherein, determining whether the tank level has significantly decreased includes the rate of decrease of the tank level exceeding a set value within the set time period.

5. The aircraft hydraulic energy conversion method as described in claim 1, characterized in that, In step S5, the second threshold value is selected as any value between 13 and 15 MPa.

6. An aircraft hydraulic energy conversion device, wherein the aircraft hydraulic system includes a main hydraulic system and a backup hydraulic system, and the pipelines of the main hydraulic system and the backup hydraulic system are connected to the input pipeline of the airborne control surface actuation mechanism via a selector valve at the junction, characterized in that, The device includes: a pressure signal acquisition module for the main hydraulic system, used to acquire the pressure signal of the main hydraulic system; a timing module, used to determine whether the pressure of the main hydraulic system has dropped below a first threshold value, and when the pressure of the main hydraulic system drops below the first threshold value, to start timing and call the pressure signal acquisition module of the main hydraulic system to continuously monitor the pressure signal of the main hydraulic system; a tank oil level signal acquisition module for the main hydraulic system, used to determine whether the timing time has exceeded a set value, and when the timing time has exceeded the set value, to acquire the tank oil level signal of the main hydraulic system; a pressure signal acquisition module for the backup hydraulic system, used to determine whether the tank oil level of the main hydraulic system is within a given normal range, and when the tank oil level of the main hydraulic system is within the given normal range, to acquire the pressure signal of the backup hydraulic system; and a main / backup system switching module, used to determine whether the pressure of the backup hydraulic system is higher than a second threshold value, and when the pressure of the backup hydraulic system is higher than the second threshold value, to control the selector valve installed at the junction to switch the main hydraulic system pipeline connected to the input pipeline to the backup hydraulic system pipeline.

7. The aircraft hydraulic energy conversion device as described in claim 6, characterized in that, The pressure signal acquisition module of the backup hydraulic system includes: an oil level prediction acquisition unit, used to acquire the current oil level prediction of the main hydraulic system's oil tank given by the airborne computing system; and an oil tank level drop identification unit, used to determine whether the oil tank level has dropped significantly within a set time period. If the oil tank level has dropped significantly, the oil level of the main hydraulic system's oil tank is not within the given normal range; otherwise, the oil level of the main hydraulic system's oil tank is within the given normal range. Determining whether the oil tank level has dropped significantly includes determining whether the rate of drop in the oil tank level exceeds a set value within the set time period.

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