A method and apparatus for determining hydraulic power requirements for an aircraft flight control system

Abstract

This application belongs to the field of aircraft design technology and relates to a method and apparatus for determining the hydraulic power requirements of an aircraft flight control system. The method includes steps S1: determining the theoretical hydraulic power requirements of each hydraulic system associated with each control surface; step S2: for each control surface, obtaining the actual supply pressure values ​​of each hydraulic system associated with that control surface; step S3: based on the relationship between the actual supply pressure values ​​of each hydraulic system and a set threshold value, determining the selector output value indicating whether the hydraulic system participates in pressure supply; step S4: multiplying the selector output of each hydraulic system by the theoretical hydraulic power requirements of the corresponding hydraulic system and then summing the results to obtain the actual hydraulic power requirements of the control surface; and step S5: determining the hydraulic power requirements of the aircraft flight control system based on the actual hydraulic power requirements of each control surface. This application improves the iterative speed of determining the hydraulic power requirements of the flight control system while reducing the calculation error rate.

Description

Technical Field

[0001] This application belongs to the field of aircraft design technology, and specifically relates to a method and device for determining the hydraulic power requirements of an aircraft flight control system. Background Technology

[0002] Aircraft flight control systems are the primary users of hydraulic systems, which currently rely heavily on hydraulic power. Throughout the aircraft system design phase, the hydraulic power requirements of the flight control system need to be continuously calculated iteratively to provide data for power assessment. As the number of control surfaces in aircraft flight control systems increases, their combinations become more complex, and hydraulic power redundancy increases, the determination of hydraulic power requirements faces more and more challenging conditions. Traditional manual calculation methods are no longer sufficient, severely impacting design iteration speed. Therefore, a rapid method for determining the hydraulic power requirements of flight control systems is urgently needed. Summary of the Invention

[0003] To address at least one of the aforementioned technical problems, this application presents a method and apparatus for determining the hydraulic power requirements of an aircraft flight control system, in order to address the determination of hydraulic power requirements under various control surface combinations and operating conditions.

[0004] The first aspect of this application provides a method for determining the hydraulic power requirements of an aircraft flight control system, mainly including:

[0005] Step S1: Determine the theoretical hydraulic power requirements of each hydraulic system associated with each control surface, wherein the aircraft flight control system includes multiple control surfaces, and each control surface is supplied with pressure by one or more hydraulic systems.

[0006] Step S2: For each control surface, obtain the actual supply pressure value of each hydraulic system associated with that control surface;

[0007] Step S3: For each control surface, based on the relationship between the actual supply pressure value of each hydraulic system and the set threshold value, determine the selector output value used to indicate whether the hydraulic system participates in the supply pressure. When the actual supply pressure value of the hydraulic system exceeds the threshold value, the selector output of the hydraulic system is set to 1, and otherwise set to 0.

[0008] Step S4: For each control surface, multiply the selector output of each hydraulic system by the theoretical hydraulic power requirement of the corresponding hydraulic system, and add up the multiplication results of each hydraulic system to obtain the actual hydraulic power requirement of the control surface.

[0009] Step S5: Determine the hydraulic power requirements of the aircraft flight control system based on the actual hydraulic power requirements of each control surface.

[0010] Preferably, step S1 further includes:

[0011] Step S11: Obtain the maximum aerodynamic load requirement and deflection rate for each control surface;

[0012] Step S12: Multiply the maximum pneumatic load requirement by the deflection rate, and then amplify it using a set amplification factor to obtain the theoretical hydraulic power requirement of each hydraulic system.

[0013] Preferably, when the number of hydraulic systems associated with the control surface is n, the amplification factor is set to 1 / n of a threshold value, wherein the threshold value is taken from any value between 1.08 and 1.12.

[0014] Preferably, step S3 further includes:

[0015] When the hydraulic system associated with the control surface includes only the main hydraulic system, the selector output of the main hydraulic system is set to 1 when the actual supply pressure of the main hydraulic system exceeds the threshold value, and set to 0 otherwise.

[0016] When the hydraulic system associated with the control surface includes a main hydraulic system and a backup hydraulic system, if the actual supply pressure of the main hydraulic system exceeds the threshold value, the selector output of the main hydraulic system is set to 1, and the selector output of the backup hydraulic system is set to 0. Conversely, if the actual supply pressure of the main hydraulic system does not exceed the threshold value, the selector output of the main hydraulic system is set to 0. At the same time, the actual supply pressure of the backup hydraulic system is compared with the set threshold value. If the actual supply pressure of the backup hydraulic system exceeds the threshold value, the selector output of the backup hydraulic system is set to 1, and otherwise set to 0.

[0017] Preferably, the set threshold value is 4 MPa.

[0018] The second aspect of this application provides a hydraulic power demand determination device for an aircraft flight control system, mainly comprising:

[0019] The theoretical hydraulic power requirement determination module is used to determine the theoretical hydraulic power requirement of each hydraulic system associated with each control surface, wherein the aircraft flight control system includes multiple control surfaces, each control surface is supplied with pressure by one or more hydraulic systems;

[0020] The actual pressure value acquisition module is used to acquire the actual pressure value of each hydraulic system associated with each control surface.

[0021] The selector output module is used to determine, for each control surface, a selector output value indicating whether the hydraulic system participates in the pressure supply, based on the relationship between the actual supply pressure value of each hydraulic system and the set threshold value. Specifically, when the actual supply pressure value of the hydraulic system exceeds the threshold value, the selector output of the hydraulic system is set to 1, and otherwise set to 0.

[0022] The actual hydraulic power calculation module for the control surface is used to multiply the selector output of each hydraulic system with the theoretical hydraulic power requirement of the corresponding hydraulic system for each control surface, and then add up the multiplication results of each hydraulic system to obtain the actual hydraulic power requirement of the control surface.

[0023] The flight control system hydraulic power requirement calculation module is used to determine the hydraulic power requirements of the aircraft flight control system based on the actual hydraulic power requirements of each control surface.

[0024] Preferably, the theoretical hydraulic power requirement determination module includes:

[0025] Aerodynamic load and deflection rate acquisition unit, used to acquire the maximum aerodynamic load requirement and deflection rate of each control surface;

[0026] The theoretical hydraulic power demand calculation unit is used to multiply the maximum pneumatic load demand by the deflection rate and then amplify it by a set amplification factor to obtain the theoretical hydraulic power demand of each hydraulic system.

[0027] Preferably, when the number of hydraulic systems associated with the control surface is n, the amplification factor is set to 1 / n of a threshold value, wherein the threshold value is taken from any value between 1.08 and 1.12.

[0028] Preferably, the selector output module includes:

[0029] The hydraulic system distribution unit without backup is used to set the selector output of the main hydraulic system to 1 when the actual supply pressure of the main hydraulic system exceeds the threshold value, and to set it to 0 otherwise when the hydraulic system associated with the control surface only includes the main hydraulic system.

[0030] A backup hydraulic system allocation unit is provided. When the hydraulic system associated with the control surface includes a main hydraulic system and a backup hydraulic system, if the actual supply pressure of the main hydraulic system exceeds the threshold value, the selector output of the main hydraulic system is set to 1, and the selector output of the backup hydraulic system is set to 0. Conversely, if the actual supply pressure of the main hydraulic system does not exceed the threshold value, the selector output of the main hydraulic system is set to 0. At the same time, the unit determines the magnitude of the actual supply pressure of the backup hydraulic system compared with the set threshold value. If the actual supply pressure of the backup hydraulic system exceeds the threshold value, the selector output of the backup hydraulic system is set to 1; otherwise, it is set to 0.

[0031] Preferably, the set threshold value is 4 MPa.

[0032] This application significantly improves the iteration speed for determining the hydraulic power requirements of the flight control system while reducing the calculation error rate. Attached Figure Description

[0033] Figure 1 This is a flowchart of a preferred embodiment of the method for determining the hydraulic power requirements of the aircraft flight control system according to this application.

[0034] Figure 2 This is a schematic diagram illustrating the theoretical hydraulic power requirements of a preferred embodiment of this application.

[0035] Figure 3 For this application Figure 2 The illustrated embodiment shows a power distribution block diagram for a backupless hydraulic system.

[0036] Figure 4 For this application Figure 2 The illustrated embodiment has a backup hydraulic system power distribution block diagram. Detailed Implementation

[0037] 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.

[0038] The first aspect of this application provides a method for determining the hydraulic power requirements of an aircraft flight control system, such as... Figure 1 As shown, it mainly includes:

[0039] Step S1: Determine the theoretical hydraulic power requirements of each hydraulic system associated with each control surface, wherein the aircraft flight control system includes multiple control surfaces, and each control surface is supplied with pressure by one or more hydraulic systems.

[0040] Step S2: For each control surface, obtain the actual supply pressure value of each hydraulic system associated with that control surface;

[0041] Step S3: For each control surface, based on the relationship between the actual supply pressure value of each hydraulic system and the set threshold value, determine the selector output value used to indicate whether the hydraulic system participates in the supply pressure. When the actual supply pressure value of the hydraulic system exceeds the threshold value, the selector output of the hydraulic system is set to 1, and otherwise set to 0.

[0042] Step S4: For each control surface, multiply the selector output of each hydraulic system by the theoretical hydraulic power requirement of the corresponding hydraulic system, and add up the multiplication results of each hydraulic system to obtain the actual hydraulic power requirement of the control surface.

[0043] Step S5: Determine the hydraulic power requirements of the aircraft flight control system based on the actual hydraulic power requirements of each control surface.

[0044] In some alternative implementations, step S1 further includes:

[0045] Step S11: Obtain the maximum aerodynamic load requirement and deflection rate for each control surface;

[0046] Step S12: Multiply the maximum pneumatic load requirement by the deflection rate, and then amplify it using a set amplification factor to obtain the theoretical hydraulic power requirement of each hydraulic system.

[0047] In some alternative implementations, when the number of hydraulic systems associated with the control surface is n, the amplification factor is set to 1 / n of a threshold value, wherein the threshold value is taken from any value between 1.08 and 1.12.

[0048] In this embodiment, if each control surface is supplied with pressure by only one hydraulic system, the amplification factor is 1.08 to 1.12. If a control surface is supplied with pressure by two hydraulic systems, the amplification factor is between 5.04 and 5.06. For example, when each control surface of the aircraft flight control system is supplied with pressure by only one hydraulic system, the amplification factor is set to 1.1. (Refer to...) Figure 2 Multiplying the maximum aerodynamic load and the deflection rate, and then amplifying by 1.1 times, yields the theoretical hydraulic power required for the control surface.

[0049] In some alternative implementations, step S3 further includes:

[0050] When the hydraulic system associated with the control surface includes only the main hydraulic system, the selector output of the main hydraulic system is set to 1 when the actual supply pressure of the main hydraulic system exceeds the threshold value, and set to 0 otherwise.

[0051] When the hydraulic system associated with the control surface includes a main hydraulic system and a backup hydraulic system, if the actual supply pressure of the main hydraulic system exceeds the threshold value, the selector output of the main hydraulic system is set to 1, and the selector output of the backup hydraulic system is set to 0. Conversely, if the actual supply pressure of the main hydraulic system does not exceed the threshold value, the selector output of the main hydraulic system is set to 0. At the same time, the actual supply pressure of the backup hydraulic system is compared with the set threshold value. If the actual supply pressure of the backup hydraulic system exceeds the threshold value, the selector output of the backup hydraulic system is set to 1, and otherwise set to 0.

[0052] The first case is as follows: Figure 3 As shown, when there is no backup hydraulic system on the control surface, the no-backup hydraulic system allocation algorithm is selected. In the power allocation of the no-backup hydraulic system, when the hydraulic system pressure is greater than a certain threshold value T (in some optional embodiments, the set threshold value is 4MPa, and in alternative embodiments, it can also be 3MPa, 5MPa, or other values), the selector selects to output 1; otherwise, it selects 0. Then, in step S4, the selection result is multiplied by the power calculated by the hydraulic power calculation module to obtain the actual power requirement of the corresponding hydraulic system.

[0053] For the second case, such as Figure 4 As shown, when the control surface has a backup hydraulic system, the backup hydraulic system allocation algorithm is selected. When the main hydraulic system's pressure supply is greater than or equal to a certain threshold value T (in some optional embodiments, the set threshold value is 4MPa; in alternative embodiments, it can also be 3MPa, 5MPa, or other values), the selector outputs 1, simultaneously disabling the backup hydraulic system. When the main working hydraulic system's pressure supply is less than or equal to a certain threshold value T, the main hydraulic system selector selects 0, and the backup hydraulic system begins to be selected for output. Then, in step S4, the selection result is multiplied by the power calculated by the hydraulic power calculation module to obtain the actual power requirement of the corresponding hydraulic system. It can be understood that in this embodiment, when the main hydraulic system is supplying oil, it is preferable to set the main hydraulic system selector to 1, and the backup hydraulic system does not participate in the calculation. Conversely, when the main hydraulic system is not supplying oil, it is then determined whether the backup main hydraulic system is supplying oil.

[0054] In step S4, if a certain control surface is supplied with oil by only one hydraulic system, the selector of that hydraulic system is set to 1, indicating that the actual hydraulic power requirement of the control surface is the same as the theoretical hydraulic power requirement in step S1. The theoretical hydraulic power requirement of the hydraulic system in step S1 is also the theoretical hydraulic power requirement of the control surface. If a certain control surface is supplied with oil by two hydraulic systems, and the actual supply pressure values ​​of both hydraulic systems are greater than a set threshold, then the theoretical hydraulic power requirement of each hydraulic system in step S1 is a component of the actual hydraulic power requirement in step S4. In fact, the sum of the theoretical hydraulic power requirements of each hydraulic system in step S1 is the theoretical hydraulic power requirement of the control surface. Similarly, the sum of the actual hydraulic power requirements of each hydraulic system in step S4 is the sum of the actual hydraulic power requirements of the control surface. Therefore, this application essentially determines whether the actual hydraulic power requirement of each control surface is equal to the theoretical hydraulic power requirement based on whether each hydraulic system participates in operation, as determined in step S3.

[0055] A second aspect of this application provides a hydraulic power demand determination device for an aircraft flight control system corresponding to the above method, mainly comprising:

[0056] The theoretical hydraulic power requirement determination module is used to determine the theoretical hydraulic power requirement of each hydraulic system associated with each control surface, wherein the aircraft flight control system includes multiple control surfaces, each control surface is supplied with pressure by one or more hydraulic systems;

[0057] The actual pressure value acquisition module is used to acquire the actual pressure value of each hydraulic system associated with each control surface.

[0058] The selector output module is used to determine, for each control surface, a selector output value indicating whether the hydraulic system participates in the pressure supply, based on the relationship between the actual supply pressure value of each hydraulic system and the set threshold value. Specifically, when the actual supply pressure value of the hydraulic system exceeds the threshold value, the selector output of the hydraulic system is set to 1, and otherwise set to 0.

[0059] The actual hydraulic power calculation module for the control surface is used to multiply the selector output of each hydraulic system with the theoretical hydraulic power requirement of the corresponding hydraulic system for each control surface, and then add up the multiplication results of each hydraulic system to obtain the actual hydraulic power requirement of the control surface.

[0060] The flight control system hydraulic power requirement calculation module is used to determine the hydraulic power requirements of the aircraft flight control system based on the actual hydraulic power requirements of each control surface.

[0061] In some alternative implementations, the theoretical hydraulic power requirement determination module includes:

[0062] Aerodynamic load and deflection rate acquisition unit, used to acquire the maximum aerodynamic load requirement and deflection rate of each control surface;

[0063] The theoretical hydraulic power demand calculation unit is used to multiply the maximum pneumatic load demand by the deflection rate and then amplify it by a set amplification factor to obtain the theoretical hydraulic power demand of each hydraulic system.

[0064] In some alternative implementations, when the number of hydraulic systems associated with the control surface is n, the amplification factor is set to 1 / n of a threshold value, wherein the threshold value is taken from any value between 1.08 and 1.12.

[0065] In some alternative implementations, the selector output module includes:

[0066] The hydraulic system distribution unit without backup is used to set the selector output of the main hydraulic system to 1 when the actual supply pressure of the main hydraulic system exceeds the threshold value, and to set it to 0 otherwise when the hydraulic system associated with the control surface only includes the main hydraulic system.

[0067] A backup hydraulic system allocation unit is provided. When the hydraulic system associated with the control surface includes a main hydraulic system and a backup hydraulic system, if the actual supply pressure of the main hydraulic system exceeds the threshold value, the selector output of the main hydraulic system is set to 1, and the selector output of the backup hydraulic system is set to 0. Conversely, if the actual supply pressure of the main hydraulic system does not exceed the threshold value, the selector output of the main hydraulic system is set to 0. At the same time, the unit determines the magnitude of the actual supply pressure of the backup hydraulic system compared with the set threshold value. If the actual supply pressure of the backup hydraulic system exceeds the threshold value, the selector output of the backup hydraulic system is set to 1; otherwise, it is set to 0.

[0068] In some alternative implementations, the set threshold value is 4 MPa.

[0069] This application significantly improves the iteration speed for determining the hydraulic power requirements of the flight control system while reducing the calculation error rate.

[0070] 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 determining the hydraulic power requirements of an aircraft flight control system, characterized in that, include: Step S1: Determine the theoretical hydraulic power requirements of each hydraulic system associated with each control surface, wherein the aircraft flight control system includes multiple control surfaces, and each control surface is supplied with pressure by one or more hydraulic systems. Step S2: For each control surface, obtain the actual supply pressure value of each hydraulic system associated with that control surface; Step S3: For each control surface, based on the relationship between the actual supply pressure value of each hydraulic system and the set threshold value, determine the selector output value used to indicate whether the hydraulic system participates in the supply pressure. When the actual supply pressure value of the hydraulic system exceeds the threshold value, the selector output of the hydraulic system is set to 1, and otherwise set to 0. Step S4: For each control surface, multiply the selector output of each hydraulic system by the theoretical hydraulic power requirement of the corresponding hydraulic system, and add up the multiplication results of each hydraulic system to obtain the actual hydraulic power requirement of the control surface. Step S5: Determine the hydraulic power requirements of the aircraft flight control system based on the actual hydraulic power requirements of each control surface.

2. The method for determining the hydraulic power requirements of an aircraft flight control system as described in claim 1, characterized in that, Step S1 further includes: Step S11: Obtain the maximum aerodynamic load requirement and deflection rate for each control surface; Step S12: Multiply the maximum pneumatic load requirement by the deflection rate, and then amplify it using a set amplification factor to obtain the theoretical hydraulic power requirement of each hydraulic system.

3. The method for determining the hydraulic power requirements of an aircraft flight control system as described in claim 2, characterized in that, When the number of hydraulic systems associated with the control surface is n, the amplification factor is set to 1 / n of the threshold, wherein the threshold is any value between 1.08 and 1.

12.

4. The method for determining the hydraulic power requirements of an aircraft flight control system as described in claim 1, characterized in that, Step S3 further includes: When the hydraulic system associated with the control surface includes only the main hydraulic system, the selector output of the main hydraulic system is set to 1 when the actual supply pressure of the main hydraulic system exceeds the threshold value, and set to 0 otherwise. When the hydraulic system associated with the control surface includes a main hydraulic system and a backup hydraulic system, if the actual supply pressure of the main hydraulic system exceeds the threshold value, the selector output of the main hydraulic system is set to 1, and the selector output of the backup hydraulic system is set to 0. Conversely, if the actual supply pressure of the main hydraulic system does not exceed the threshold value, the selector output of the main hydraulic system is set to 0. At the same time, the actual supply pressure of the backup hydraulic system is compared with the set threshold value. If the actual supply pressure of the backup hydraulic system exceeds the threshold value, the selector output of the backup hydraulic system is set to 1, and otherwise set to 0.

5. The method for determining the hydraulic power requirements of an aircraft flight control system as described in claim 1, characterized in that, The set threshold value is 4 MPa.

6. A device for determining the hydraulic power demand of an aircraft flight control system, characterized in that, include: The theoretical hydraulic power requirement determination module is used to determine the theoretical hydraulic power requirement of each hydraulic system associated with each control surface, wherein the aircraft flight control system includes multiple control surfaces, each control surface is supplied with pressure by one or more hydraulic systems; The actual pressure value acquisition module is used to acquire the actual pressure value of each hydraulic system associated with each control surface. The selector output module is used to determine, for each control surface, a selector output value indicating whether the hydraulic system participates in the pressure supply, based on the relationship between the actual supply pressure value of each hydraulic system and the set threshold value. Specifically, when the actual supply pressure value of the hydraulic system exceeds the threshold value, the selector output of the hydraulic system is set to 1, and otherwise set to 0. The actual hydraulic power calculation module for the control surface is used to multiply the selector output of each hydraulic system with the theoretical hydraulic power requirement of the corresponding hydraulic system for each control surface, and then add up the multiplication results of each hydraulic system to obtain the actual hydraulic power requirement of the control surface. The flight control system hydraulic power requirement calculation module is used to determine the hydraulic power requirements of the aircraft flight control system based on the actual hydraulic power requirements of each control surface.

7. The hydraulic power demand determination device for an aircraft flight control system as described in claim 6, characterized in that, The theoretical hydraulic power requirement determination module includes: Aerodynamic load and deflection rate acquisition unit, used to acquire the maximum aerodynamic load requirement and deflection rate of each control surface; The theoretical hydraulic power demand calculation unit is used to multiply the maximum pneumatic load demand by the deflection rate and then amplify it by a set amplification factor to obtain the theoretical hydraulic power demand of each hydraulic system.

8. The hydraulic power demand determination device for an aircraft flight control system as described in claim 7, characterized in that, When the number of hydraulic systems associated with the control surface is n, the amplification factor is set to 1 / n of the threshold, wherein the threshold is any value between 1.08 and 1.

12.

9. The hydraulic power demand determination device for an aircraft flight control system as described in claim 6, characterized in that, The selector output module includes: The hydraulic system distribution unit without backup is used to set the selector output of the main hydraulic system to 1 when the actual supply pressure of the main hydraulic system exceeds the threshold value, and to set it to 0 otherwise when the hydraulic system associated with the control surface only includes the main hydraulic system. A backup hydraulic system allocation unit is provided. When the hydraulic system associated with the control surface includes a main hydraulic system and a backup hydraulic system, if the actual supply pressure of the main hydraulic system exceeds the threshold value, the selector output of the main hydraulic system is set to 1, and the selector output of the backup hydraulic system is set to 0. Conversely, if the actual supply pressure of the main hydraulic system does not exceed the threshold value, the selector output of the main hydraulic system is set to 0. At the same time, the unit determines the magnitude of the actual supply pressure of the backup hydraulic system compared with the set threshold value. If the actual supply pressure of the backup hydraulic system exceeds the threshold value, the selector output of the backup hydraulic system is set to 1; otherwise, it is set to 0.

10. The hydraulic power demand determination device for an aircraft flight control system as described in claim 6, characterized in that, The set threshold value is 4 MPa.

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