CN113945255A - Aircraft fuel measurement and management system - Google Patents
Aircraft fuel measurement and management system Download PDFInfo
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- CN113945255A CN113945255A CN202111123745.3A CN202111123745A CN113945255A CN 113945255 A CN113945255 A CN 113945255A CN 202111123745 A CN202111123745 A CN 202111123745A CN 113945255 A CN113945255 A CN 113945255A
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- 239000000446 fuel Substances 0.000 title claims abstract description 111
- 238000005259 measurement Methods 0.000 title claims abstract description 44
- 239000003921 oil Substances 0.000 claims abstract description 86
- 239000000295 fuel oil Substances 0.000 claims abstract description 37
- 238000012545 processing Methods 0.000 claims abstract description 8
- 238000007726 management method Methods 0.000 claims description 29
- 239000002828 fuel tank Substances 0.000 claims description 19
- 238000012423 maintenance Methods 0.000 claims description 9
- 238000004364 calculation method Methods 0.000 claims description 5
- 238000010977 unit operation Methods 0.000 claims description 5
- 238000010586 diagram Methods 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- 238000012805 post-processing Methods 0.000 claims description 3
- 238000012546 transfer Methods 0.000 claims description 3
- 238000001514 detection method Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 description 7
- 238000004458 analytical method Methods 0.000 description 6
- 238000006243 chemical reaction Methods 0.000 description 4
- 230000002159 abnormal effect Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000012544 monitoring process Methods 0.000 description 3
- 238000004132 cross linking Methods 0.000 description 2
- 238000003672 processing method Methods 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000001739 density measurement Methods 0.000 description 1
- 238000009795 derivation Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F23/00—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm
- G01F23/22—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water
- G01F23/26—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields
- G01F23/263—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields by measuring variations in capacitance of capacitors
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F23/00—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm
- G01F23/30—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by floats
- G01F23/64—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by floats of the free float type without mechanical transmission elements
- G01F23/66—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by floats of the free float type without mechanical transmission elements using mechanically actuated indicating means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/16—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Electromagnetism (AREA)
- Thermal Sciences (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The application provides an aircraft fuel measurement management system includes: fuel measurement divides system and fuel management branch system, wherein: the fuel oil measuring subsystem comprises a fuel oil measuring computer, an oil mass sensor, a dielectric constant sensor, a density sensor, a temperature sensor and an oil level annunciator, and determines the fuel oil amount of the oil tank through data processing operation according to the signals of the oil mass sensor, the density sensor, the node constant sensor, the temperature sensor, the oil level annunciator, flight attitude information and the like; and the fuel management subsystem realizes the display of fuel system control and fuel system state detection according to the fuel measurement result, the electromechanical system signal and the like.
Description
Technical Field
The application belongs to the technical field of aviation fuel systems, and particularly relates to an aircraft fuel measurement management system.
Background
The aircraft fuel oil system is a key system related to aircraft safety, the performance of the fuel oil system directly influences the flight safety and the task execution capacity of the aircraft, accurate and stable fuel tank oil mass measurement and timely and effective fuel oil system management have important significance, the control requirement of a complex multi-working-condition system is met, the control accuracy is improved, the operation burden of a unit is reduced, enough warning and display and maintenance information are provided for a user, faults can be accurately positioned, the air-ground service workload is reduced, the aircraft maintenance time is shortened, the aircraft maintenance cost is reduced, and the aircraft fuel oil system has positive significance for improving the safety of the aircraft and enhancing the maintainability and testability of the aircraft.
Disclosure of Invention
It is an object of the present application to provide an aircraft fuel measurement management system to address or mitigate at least one of the above problems.
The technical scheme provided by the application is as follows: an aircraft fuel measurement management system comprising: fuel measurement divides system and fuel management branch system, wherein:
the fuel oil measuring subsystem comprises a fuel oil measuring computer, an oil mass sensor, a dielectric constant sensor, a density sensor, a temperature sensor and an oil level annunciator, and determines the fuel oil quantity through data processing operation according to the signals of the oil mass sensor, the density sensor, the node constant sensor, the temperature sensor, the oil level annunciator, flight attitude information and the like;
the fuel management subsystem is used for realizing fuel supply control of an engine/APU (auxiliary Power Unit), pressure refueling control, ground oil discharge control, fuel oil transfer control between ground oil tank groups, air emergency oil discharge control and fuel tank inerting system control, and comprises the steps of collecting fuel oil pump pressure and fuel oil valve switch position fuel oil system parameters through electromechanical management equipment, executing logical resolving of fuel oil system unit alarm, top control panel button lamp display, simplified diagram page display, system maintenance fault judgment, flight parameter data recording and the like by combining unit operation instructions, and transmitting results to avionic equipment for display and storage.
Furthermore, in the fuel measurement subsystem, a plurality of fuel quantity sensors are distributed in different fuel tank ribs, so that the fuel tank is divided into a plurality of measurement units, and after each measurement unit is respectively measured, a plurality of measurement units are gathered to obtain a total fuel tank measurement result.
Further, the process of obtaining the measurement result of the oil tank through the oil quantity sensor is as follows:
measuring the height of the oil level by oil quantity sensors distributed at different positions in each measuring and calculating unit; and (3) combining oil surface angle measurement, then inquiring a fuel quality characteristic database representing corresponding relations among oil surface height, oil surface angle, fuel quantity, fuel gravity center and the like, and finally obtaining an oil quantity measurement result through difference calculation and information post-processing.
Further, the oil quantity sensor is a capacitance type oil quantity sensor.
Further, the fuel management subsystem is based on the fuel quantity measuring result, and when the fuel filtering change of the fuel tank meets the preset condition, the fuel is judged to be leaked, and an alarm is given.
Further, the predetermined condition is: the amount of fuel is reduced by a predetermined weight of fuel for a predetermined time.
The method determines a reasonable fuel system data processing method based on the comprehensive logic of system working condition analysis and the system architecture of redundancy fault safety, particularly processes open position signals and closed position signals of a fuel electric valve to obtain comprehensive valve position signals, and ensures the stability and convenient use of the system signals; the reasonable control panel switch and system control logic design is adopted, the accuracy and reliability of system control are ensured, the emergency oil drainage automatic control is particularly arranged, the unit operation burden is reduced, and the intelligent control level of the system is improved; the fuel oil leakage alarm is set, the alarm is based on high-precision and stable oil mass measurement, abnormal fuel oil mass data change is used for completing fuel oil leakage alarm judgment, technical support is provided for unit safety operation, and the energy requirement of air service is reduced.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic view of an aircraft fuel measurement management system according to the present application.
Fig. 2 is a schematic diagram of fuel measurement according to the present application.
Fig. 3 shows a layout result of a fuel level sensor of a fuel tank according to an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
As shown in fig. 1, the aircraft fuel measurement management method provided by the application includes a fuel measurement subsystem and a fuel management subsystem, wherein:
as shown in fig. 2, the fuel oil measuring subsystem includes a fuel oil measuring computer, an oil mass sensor, a dielectric constant sensor, a density sensor, a temperature sensor, and an oil level annunciator, and determines the fuel oil amount through data processing and calculation according to the oil mass sensor signal, the density sensor, the node constant sensor, the temperature sensor, the oil level annunciator, flight attitude information, and the like.
S1, firstly, the whole oil tank is partitioned according to the sealing performance of the rib between the oil tanks and the fuel oil communication performance to form a plurality of measuring and calculating units.
In the case of an exemplary fuel tank sensor arrangement of an aircraft of the type shown in fig. 3, the fuel tank is divided into 10 measuring and calculating units (in the region enclosed by the thick solid line and the optional frame, for example, between the ribs 31 to 28, the first measuring and calculating unit is shown) depending on the fuel tank structure;
according to the oil model of each measuring and calculating unit, the minimum unmeasured oil quantity at the bottom and the top of the system is considered, and the final layout result of the fuel oil quantity measuring sensor is obtained by combining installation interference analysis in the oil tank and meeting the requirement of measuring continuity.
The total number of the oil sensors is 56, and the left wing and the right wing are symmetrically distributed. The number of the outer oil tanks is 18, and the number of the inner oil tanks is 10 as shown in figure 3.
S2, measuring the oil level height of the capacitive oil mass sensors distributed at different positions in each measuring and calculating unit, measuring by combining an oil level angle, and then inquiring a fuel quality characteristic database representing the corresponding relation between the oil level height, the oil level angle, the fuel quantity, the fuel gravity center and the like;
and S3, finally obtaining an oil mass measuring result through difference calculation and information post-processing.
The measuring result comprises the oil quantity and the total oil quantity of each oil tank; measuring the fuel temperature; and measuring the low fuel level, thereby realizing liquid level height measurement, oil level angle measurement, virtual liquid level height calculation, three-dimensional table lookup and interpolation, density measurement, density derivation by temperature and the like.
Meanwhile, the temperature of the fuel is measured through a temperature sensor, and a low oil level alarm is sent through a low oil level annunciator.
The fuel management system aims at the cross-linking relation between the fuel system and other systems (a power system, an electromechanical management system, a power supply system, an environmental control system, a hydraulic system, a fire protection system, an avionic system and the like)
Aiming at the complex full flight profile, multi-input and multi-mode control requirements of the fuel system, multi-input signal selection, judgment and correlation characteristics, and according to the control input, state conversion conditions and state conversion logic of each state of the control requirements, the method comprises the following steps of (1) selecting, judging and correlating the control input, the state conversion conditions and the state conversion logic of each state of the fuel system; and (3) detecting and accurately isolating system faults.
The fuel management system is based on the requirements of the fuel system in the aspects of control, display, alarm, maintenance and the like, and combines the top-level architecture scheme of the electromechanical management system to formulate the hardware composition and the functional logic suitable for the fuel management system.
1. The fuel management system is mainly used for realizing fuel system control and fuel system state monitoring. The fuel system control comprises engine/APU fuel supply control, pressure fuel filling control, ground oil drainage control, fuel oil transfer control between ground oil filling tank groups, air emergency oil drainage control and fuel tank inerting system control. The fuel system state monitoring comprises the steps of collecting fuel system parameters such as fuel pump pressure, fuel valve switch position and the like through electromechanical management equipment, executing logical resolving such as fuel system unit alarm, top control panel button lamp display, sketch page display, system maintenance fault judgment, flight parameter data recording and the like by combining unit operation instructions, and sending results to avionic equipment for display and storage;
2. and (3) fuel system data processing:
2.1 bus redundancy data processing: determining data according to the on-line state of a bus of a computer;
2.2 the fuel electric valve has an open position signal and a close position signal to obtain a comprehensive valve position signal, and the data processing logic is shown in table 1:
TABLE 1 Fuel valve position Signal processing logic definition
3. Important parts of an aircraft fuel system, such as an oil supply pump, an oil supply cut-off valve, a delivery valve, an emergency oil drain valve and the like, are provided with a manual control mode; manual control overrides automatic control when manual and automatic control modes coexist; the unit needs special attention and an automatic control mode is provided; the method comprises a plurality of operation steps and an automatic control mode; the operation without great influence is only set in the automatic control mode.
3.1 the fuel supply and delivery control of the fuel system is manual control, and the control of 8 alternating current fuel supply pumps, 1 direct current pump, 4 engine fuel supply cut-off valves and 4 alternating current delivery pumps is realized through corresponding control buttons on a fuel top control board;
3.2 three modes are set for aerial emergency oil drainage: minimum oil drain, maximum oil drain, manual, through "begin oil drain" button manual start emergency oil drain. When the mode of 'least oil drainage' or 'most oil drainage' is selected, the computer controls to close emergency oil drainage according to the appointed residual oil quantity, so that the operation burden of a unit is reduced, wherein 'least oil drainage' represents that oil drainage is carried out to the maximum landing weight, the economy is embodied on the premise that safe landing of the airplane is ensured, and 'most oil drainage' represents that oil drainage to a system cannot discharge fuel oil. If the manual mode is selected, the driver is required to close the emergency oil drainage system through a 'stop oil drainage' button;
3.3 in order to reduce the burden of the unit, the inerting and ventilating system is automatically controlled by a computer as much as possible, only an inerting starting control button is arranged on a fuel oil top control panel, the unit only needs to start the inerting ventilating system to work through the button, and the unit is a full-automatic process under normal conditions without paying attention to the unit;
3.4 ground pressure refueling modes are divided into automatic and manual modes. In the automatic mode, the total fuel filling amount can be selected optionally, 4 groups of fuel tanks can be filled with fuel in a balanced manner according to the automatic fuel filling sequence after the completion of the presetting, and in the manual mode, an operator needs to observe the fuel amount and stops filling fuel manually.
4, monitoring the state of the fuel system:
4.1, fault mode influence analysis and safety analysis are carried out on the fuel system, specific system alarm information and alarm logic are determined, except for common alarms of oil pump faults, fuel imbalance and the like of the fuel system, a fuel leakage alarm is particularly set, the alarm is based on high-precision and stable fuel quantity measurement, abnormal fuel quantity data change of a fuel tank (the fuel quantity reduction amount is more than 50kg every 30 s) is used for completing fuel leakage alarm judgment, technical support is provided for unit safety operation, and the energy requirement of air service is reduced;
and 4.2 based on the traditional layout and the external relation of the fuel system equipment, the cross-linking relation between a maintenance object and a potential fault reason is analyzed and determined on the basis of equipment-level and system-level fault influence analysis, and the maintenance logic of the fuel system is set.
The invention designs a comprehensive logic based on system working condition analysis and a system architecture of redundancy fault safety, determines a reasonable fuel system data processing method, particularly processes open position signals and closed position signals of a fuel electric valve to obtain comprehensive valve position signals, and ensures the stability and convenient use of the system signals; the reasonable control panel switch and system control logic design is adopted, the accuracy and reliability of system control are ensured, the emergency oil drainage automatic control is particularly arranged, the unit operation burden is reduced, and the intelligent control level of the system is improved; the fuel oil leakage alarm is set, the alarm is based on high-precision and stable oil mass measurement, abnormal fuel oil mass data change is used for completing fuel oil leakage alarm judgment, technical support is provided for unit safety operation, and the energy requirement of air service is reduced.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. An aircraft fuel measurement management system, comprising: fuel measurement divides system and fuel management branch system, wherein:
the fuel oil measuring subsystem comprises a fuel oil measuring computer, an oil mass sensor, a dielectric constant sensor, a density sensor, a temperature sensor and an oil level annunciator, and determines the fuel oil quantity through data processing operation according to the signals of the oil mass sensor, the density sensor, the node constant sensor, the temperature sensor, the oil level annunciator, flight attitude information and the like;
the fuel management subsystem is used for realizing fuel supply control of an engine/APU (auxiliary Power Unit), pressure refueling control, ground oil discharge control, fuel oil transfer control between ground oil tank groups, air emergency oil discharge control and fuel tank inerting system control, and comprises the steps of collecting fuel oil pump pressure and fuel oil valve switch position fuel oil system parameters through electromechanical management equipment, executing logical resolving of fuel oil system unit alarm, top control panel button lamp display, simplified diagram page display, system maintenance fault judgment, flight parameter data recording and the like by combining unit operation instructions, and transmitting results to avionic equipment for display and storage.
2. An aircraft fuel measurement management method according to claim 1, wherein in the fuel measurement subsystem, the fuel tank is divided into a plurality of measurement units by distributing a plurality of fuel level sensors among different fuel tank ribs, and the plurality of measurement units are aggregated to obtain a total fuel tank measurement result after each measurement unit is subjected to measurement.
3. An aircraft fuel measurement and management system according to claim 2, wherein the fuel tank measurements obtained by the fuel level sensor are obtained by:
measuring the height of the oil level by oil quantity sensors distributed at different positions in each measuring and calculating unit; and (3) combining oil surface angle measurement, then inquiring a fuel quality characteristic database representing corresponding relations among oil surface height, oil surface angle, fuel quantity, fuel gravity center and the like, and finally obtaining an oil quantity measurement result through difference calculation and information post-processing.
4. An aircraft fuel measurement and management system according to claim 3, wherein the fuel level sensor is a capacitive fuel level sensor.
5. An aircraft fuel measurement and management system according to claim 1, wherein the fuel management subsystem determines that fuel is leaked and provides an alarm when a fuel tank fuel filter change satisfies a predetermined condition based on the fuel quantity measurement.
6. An aircraft fuel measurement and management system according to claim 5, wherein the predetermined conditions are: the amount of fuel is reduced by a predetermined weight of fuel for a predetermined time.
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| CN202111123745.3A CN113945255A (en) | 2021-09-24 | 2021-09-24 | Aircraft fuel measurement and management system |
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| CN202111123745.3A CN113945255A (en) | 2021-09-24 | 2021-09-24 | Aircraft fuel measurement and management system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114488771A (en) * | 2022-01-27 | 2022-05-13 | 中国商用飞机有限责任公司 | Emergency oil drainage comprehensive control system |
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2021
- 2021-09-24 CN CN202111123745.3A patent/CN113945255A/en active Pending
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114488771A (en) * | 2022-01-27 | 2022-05-13 | 中国商用飞机有限责任公司 | Emergency oil drainage comprehensive control system |
| CN114488771B (en) * | 2022-01-27 | 2024-02-20 | 中国商用飞机有限责任公司 | Emergency oil drain integrated control system |
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