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CN-115828618-B - Method and device for determining hydraulic power demand of aircraft flight control system

CN115828618BCN 115828618 BCN115828618 BCN 115828618BCN-115828618-B

Abstract

The application belongs to the technical field of aircraft design, and relates to a method and a device for determining hydraulic power requirements of an aircraft flight control system. The method comprises the steps of S1, determining theoretical hydraulic power requirements of hydraulic systems associated with control surfaces, S2, obtaining actual pressure supply values of the hydraulic systems associated with the control surfaces for each control surface, S3, determining selector output values used for representing whether the hydraulic systems participate in pressure supply according to the magnitude relation between the actual pressure supply values of the hydraulic systems and a set threshold value, S4, multiplying the selector output of each hydraulic system by the theoretical hydraulic power requirements of the corresponding hydraulic systems, and then superposing the selector output of each hydraulic system to obtain the actual hydraulic power requirements of the control surfaces, and S5, determining the hydraulic power requirements of aircraft flight control systems according to the actual hydraulic power requirements of the control surfaces. The application improves the iteration speed of the determination of the hydraulic power requirement of the flight control system on the basis of reducing the calculation error rate.

Inventors

  • ZHANG JIASHENG
  • DU XIAODONG
  • HE JINGJING

Assignees

  • 中国航空工业集团公司西安飞机设计研究所

Dates

Publication Date
20260505
Application Date
20221220

Claims (10)

  1. 1. A method of determining hydraulic power demand of an aircraft flight control system, comprising: step S1, determining a theoretical hydraulic power requirement of each hydraulic system associated with each control surface, wherein the aircraft flight control system comprises a plurality of control surfaces, and each control surface is pressurized by one or more hydraulic systems; S2, obtaining an actual pressure supply value of each hydraulic system associated with each control surface for each control surface; Step S3, determining a selector output value used for indicating whether the hydraulic system participates in pressure supply according to the magnitude relation between the actual pressure supply value of each hydraulic system and a set threshold value for each control surface, wherein when the actual pressure supply value of the hydraulic system exceeds the threshold value, the selector output value of the hydraulic system is set to 1, and otherwise, is set to 0; S4, multiplying the selector output of each hydraulic system by the theoretical hydraulic power requirement of the corresponding hydraulic system for each control surface, and superposing the multiplication results of the hydraulic systems to obtain the actual hydraulic power requirement of the control surface; and S5, determining the hydraulic power requirement of the aircraft flight control system according to the actual hydraulic power requirement of each control surface.
  2. 2. The aircraft flight control system hydraulic power demand determination method of claim 1, wherein step S1 further comprises: S11, acquiring the maximum demand and the deflection rate of the pneumatic load of each control surface; And step S12, multiplying the maximum pneumatic load requirement by the deflection rate, and amplifying by a set amplification factor to obtain the theoretical hydraulic power requirement of each hydraulic system.
  3. 3. The method of determining hydraulic power demand for aircraft flight control systems according to claim 2, wherein when the number of hydraulic systems associated with the control surface is n, the set amplification factor is 1/n of a threshold value, wherein the threshold value is taken to be any value between 1.08 and 1.12.
  4. 4. The aircraft flight control system hydraulic power demand determination method of claim 1, wherein step S3 further comprises: When the hydraulic system related to the control surface only comprises a main hydraulic system, setting 1 to the selector output of the main hydraulic system when the actual pressure supply value of the main hydraulic system exceeds the threshold value, and setting 0 to the opposite value; When the hydraulic system related to the control surface comprises a main hydraulic system and a backup hydraulic system, when the actual pressure supply value of the main hydraulic system exceeds the threshold value, setting 1 the selector output of the main hydraulic system, and setting 0 the selector of the backup hydraulic system, otherwise, setting 0 the selector output of the main hydraulic system when the actual pressure supply value of the main hydraulic system does not exceed the threshold value, and simultaneously judging the actual pressure supply value of the backup hydraulic system and the magnitude of the set threshold value, and when the actual pressure supply value of the backup hydraulic system exceeds the threshold value, setting 1 the selector output of the backup hydraulic system, otherwise, setting 0.
  5. 5. The method for determining hydraulic power demand of an aircraft flight control system of claim 1, wherein the set threshold value is 4MPa.
  6. 6. An aircraft flight control system hydraulic power demand determination apparatus, comprising: A theoretical hydraulic power demand determination module for determining a theoretical hydraulic power demand of each hydraulic system associated with each control surface, wherein the aircraft flight control system comprises a plurality of control surfaces, each control surface being pressurized by one or more hydraulic systems; The actual pressure supply value acquisition module is used for acquiring the actual pressure supply value of each hydraulic system associated with each control surface; The selector output module is used for determining a selector output value used for indicating whether the hydraulic system participates in pressure supply or not according to the magnitude relation between the actual pressure supply value of each hydraulic system and a set threshold value for each control surface, wherein when the actual pressure supply value of the hydraulic system exceeds the threshold value, the selector output of the hydraulic system is set to 1, and otherwise, is set to 0; The control surface actual hydraulic power calculation module is used for multiplying the selector output of each hydraulic system with the theoretical hydraulic power requirement of the corresponding hydraulic system for each control surface, and superposing the multiplication results of the hydraulic systems to obtain the actual hydraulic power requirement of the control surface; And the flight control system hydraulic power demand calculation module is used for determining the hydraulic power demand of the aircraft flight control system according to the actual hydraulic power demand of each control surface.
  7. 7. The aircraft flight control system hydraulic power demand determination device of claim 6, wherein the theoretical hydraulic power demand determination module comprises: The pneumatic load and deflection rate acquisition unit is used for acquiring the maximum requirements and deflection rates of the pneumatic loads of the control surfaces; And the theoretical hydraulic power demand calculation unit is used for multiplying the maximum pneumatic load demand by the deflection rate and amplifying the pneumatic load demand by the set amplification coefficient to obtain the theoretical hydraulic power demand of each hydraulic system.
  8. 8. The aircraft flight control system hydraulic power demand determining device according to claim 7, wherein when the number of hydraulic systems associated with the control surface is n, the set amplification factor is 1/n of a threshold value, wherein the threshold value is taken from any value between 1.08 and 1.12.
  9. 9. The aircraft flight control system hydraulic power demand determination device of claim 6, wherein the selector output module comprises: The hydraulic system distribution unit without backup is used for setting 1 of the selector output of the main hydraulic system when the actual pressure supply value of the main hydraulic system exceeds the threshold value and setting 0 of the selector output of the main hydraulic system when the hydraulic system associated with the control surface only comprises the main hydraulic system; And the backup hydraulic system distribution unit is used for setting 1 for the selector output of the main hydraulic system and setting 0 for the selector of the backup hydraulic system when the actual pressure supply value of the main hydraulic system exceeds the threshold value when the hydraulic system related to the control surface comprises the main hydraulic system and the backup hydraulic system, otherwise setting 0 for the selector output of the main hydraulic system when the actual pressure supply value of the main hydraulic system does not exceed the threshold value, and judging the actual pressure supply value of the backup hydraulic system and the magnitude of the set threshold value, and setting 1 for the selector output of the backup hydraulic system and otherwise setting 0 for the selector output of the backup hydraulic system when the actual pressure supply value of the backup hydraulic system exceeds the threshold value.
  10. 10. The aircraft flight control system hydraulic power demand determination device of claim 6, wherein the set threshold value is 4MPa.

Description

Method and device for determining hydraulic power demand of aircraft flight control system Technical Field The application belongs to the technical field of aircraft design, and particularly relates to a method and a device for determining hydraulic power requirements of an aircraft flight control system. Background The aircraft flight control system is a main user of a hydraulic system, the hydraulic system is mainly used as a main energy source at present, and the hydraulic energy power requirement of the flight control system needs to be calculated repeatedly in the whole design stage of the aircraft system, and then the hydraulic energy power requirement is provided for the hydraulic system for power evaluation. With the increasing number of control surfaces of an aircraft flight control system, the increasing complexity of using combination and the increasing configuration of hydraulic energy redundancy, the increasing working conditions for determining the hydraulic power requirement of the flight control system are met, the requirement cannot be met by the traditional method relying on manual calculation, the design iteration speed is seriously influenced, and a rapid method for determining the hydraulic power requirement of the flight control system is needed. Disclosure of Invention In order to solve at least one of the technical problems, the application designs a method and a device for determining the hydraulic power requirement of an aircraft flight control system, which are used for determining the hydraulic power requirements of various control surface combinations and various working conditions. The first aspect of the application provides a method for determining hydraulic power demand of an aircraft flight control system, which mainly comprises the following steps: step S1, determining a theoretical hydraulic power requirement of each hydraulic system associated with each control surface, wherein the aircraft flight control system comprises a plurality of control surfaces, and each control surface is pressurized by one or more hydraulic systems; S2, obtaining an actual pressure supply value of each hydraulic system associated with each control surface for each control surface; Step S3, determining a selector output value used for indicating whether the hydraulic system participates in pressure supply according to the magnitude relation between the actual pressure supply value of each hydraulic system and a set threshold value for each control surface, wherein when the actual pressure supply value of the hydraulic system exceeds the threshold value, the selector output value of the hydraulic system is set to 1, and otherwise, is set to 0; S4, multiplying the selector output of each hydraulic system by the theoretical hydraulic power requirement of the corresponding hydraulic system for each control surface, and superposing the multiplication results of the hydraulic systems to obtain the actual hydraulic power requirement of the control surface; and S5, determining the hydraulic power requirement of the aircraft flight control system according to the actual hydraulic power requirement of each control surface. Preferably, step S1 further comprises: S11, acquiring the maximum demand and the deflection rate of the pneumatic load of each control surface; And step S12, multiplying the maximum pneumatic load requirement by the deflection rate, and amplifying by a set amplification factor to obtain the theoretical hydraulic power requirement of each hydraulic system. Preferably, when the number of hydraulic systems associated with the control surface is n, the set amplification factor is 1/n of a threshold value, wherein the threshold value is any value between 1.08 and 1.12. Preferably, step S3 further includes: When the hydraulic system related to the control surface only comprises a main hydraulic system, setting 1 to the selector output of the main hydraulic system when the actual pressure supply value of the main hydraulic system exceeds the threshold value, and setting 0 to the opposite value; When the hydraulic system related to the control surface comprises a main hydraulic system and a backup hydraulic system, when the actual pressure supply value of the main hydraulic system exceeds the threshold value, setting 1 the selector output of the main hydraulic system, and setting 0 the selector of the backup hydraulic system, otherwise, setting 0 the selector output of the main hydraulic system when the actual pressure supply value of the main hydraulic system does not exceed the threshold value, and simultaneously judging the actual pressure supply value of the backup hydraulic system and the magnitude of the set threshold value, and when the actual pressure supply value of the backup hydraulic system exceeds the threshold value, setting 1 the selector output of the backup hydraulic system, otherwise, setting 0. Preferably, the set threshold value is 4MPa. In a second aspect, the present appl