CN107131924A - A kind of aircraft fuel measuring system and the aircraft with it - Google Patents
A kind of aircraft fuel measuring system and the aircraft with it Download PDFInfo
- Publication number
- CN107131924A CN107131924A CN201710203374.7A CN201710203374A CN107131924A CN 107131924 A CN107131924 A CN 107131924A CN 201710203374 A CN201710203374 A CN 201710203374A CN 107131924 A CN107131924 A CN 107131924A
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- China
- Prior art keywords
- aircraft
- fuel
- sensor
- fuel tank
- oil measurement
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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
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention discloses a kind of aircraft fuel measuring system and the aircraft with it.The aircraft fuel measuring system includes：The first oil measurement sensor and the second oil measurement sensor are provided with first oil measurement sensor and the second oil measurement sensor, port wing fuel tank；The first oil measurement sensor and the second oil measurement sensor are provided with starboard wing fuel tank；First processing units and second processing unit are provided with fuel measurement computer, fuel measurement computer, first processing units are connected with the first oil measurement sensor；Second processing unit is connected with the second oil measurement sensor.The aircraft fuel measuring system of the present invention, first processing units mutually transmit information with second processing unit, so as to obtain the information that other side is obtained, when any one breaks down in the first oil measurement sensor or the second oil measurement sensor, oil measurement can be carried out by another oil measurement sensor.
Description
Technical field
The present invention relates to Aviation Fuel System design technology field, more particularly to a kind of aircraft fuel measuring system and
Aircraft with it.
Background technology
As aeronautical technology progressively develops, fuel measuring system is while measurement accuracy is pursued, also can to higher
With property and relatively low weight cost aspect effort.On the premise of system largely uses goods shelf productses, how less biography is used
Sensor ensures measurement accuracy, and improves system availability as designer's difficult point urgently to be resolved hurrily.Ensuring fuel measurement system
The MTBF (MTBF) of system on the basis of 12000FH is not less than, builds a kind of rational fuel measuring system
There will be considerable influence to economy.
The fuel measuring system that aircraft is used, main configuration 18 fuel measurement sensors, twin-channel measurement controls
Unit processed etc..Twin-channel measure-controlling unit is integrated in a physics cabinet, but is passed between two passages without signal
Defeated, the development to single passage ensures that class requirement is high, and management and repair spare part cost are higher.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
Overcome it is an object of the invention to provide a kind of aircraft fuel measuring system or at least mitigate prior art
At least one drawbacks described above.
To achieve the above object, the present invention provides a kind of aircraft fuel measuring system, and the fuel tank fuel quantity for aircraft is visited
Survey, the aircraft includes port wing fuel tank and starboard wing fuel tank, the aircraft fuel measuring system includes：First oil mass is surveyed
Be provided with quantity sensor and the second oil measurement sensor, the port wing fuel tank multiple first oil measurement sensors with
And multiple second oil measurement sensors；Multiple first oil measurement sensors are provided with the starboard wing fuel tank and multiple
Second oil measurement sensor；It is provided with fuel measurement computer, the fuel measurement computer at first mutually communicated
Unit and second processing unit are managed, the first processing units are connected with the first oil measurement sensor each described；It is described
Second processing unit is connected with the second oil measurement sensor each described；Wherein, the first processing units are used to receive institute
State the signal of the first oil measurement sensor；The second processing unit is used for the letter for receiving the second oil measurement sensor
Number；The first processing units are mutually communicated with the second processing unit, so as to obtain the signal that other side is obtained, and then are obtained
Obtain the port wing fuel tank of the aircraft and total oil mass of the starboard wing fuel tank.
Preferably, the first oil measurement sensor and the second oil measurement sensor are identical oil measurement
Sensor.
Preferably, the cable of each the first oil measurement sensor was by sealing frame joint and the described first processing
Unit is connected；The cable of each the second oil measurement sensor is connected by sealing frame joint with the second processing unit
Connect.
Preferably, the aircraft fuel measuring system further comprises：First high fuel level annunciator and the second high oil
Face signalling means, the first high fuel level annunciator is arranged in port wing fuel tank, and the second high fuel level annunciator is arranged on the right side
In wing tank；The first high fuel level annunciator is connected with the first processing units；The second high fuel level annunciator with
The second processing unit connection.
Preferably, the aircraft fuel measuring system further comprises：First low fuel level annunciator and the second low oil
Face signalling means, the first low fuel level annunciator is arranged in port wing fuel tank, and the second low fuel level annunciator is arranged on the right side
In wing tank；The first low fuel level annunciator is connected with the first processing units；The second low fuel level annunciator with
The second processing unit connection.
Preferably, the aircraft fuel measuring system further comprises：First compensation sensor and the second compensation are passed
Sensor, the first compensation sensor is arranged in port wing fuel tank, and the second compensation sensor is arranged on starboard wing fuel tank
It is interior；The first compensation sensor is connected with the first processing units；The second compensation sensor and the second processing
Unit is connected.
Preferably, the aircraft fuel measuring system further comprises：First temperature sensor and second temperature are passed
Sensor, first temperature sensor is arranged in port wing fuel tank, and the second temperature sensor is arranged on the starboard wing
In fuel tank；First temperature sensor is connected with the first processing units；The second temperature sensor and described second
Processing unit is connected.
Preferably, the quantity of the first oil measurement sensor in the port wing fuel tank is four, the second oil measurement
The quantity of sensor is four；The quantity of the first oil measurement sensor in the starboard wing fuel tank is four, the second oil mass
The quantity of measurement sensor is four.
Present invention also provides a kind of aircraft, the aircraft includes port wing fuel tank and starboard wing fuel tank, the aircraft
Further comprise aircraft fuel measuring system as described above.
In aircraft fuel measuring system in the present invention, first processing units mutually transmit letter with second processing unit
Breath, so that the information that other side is obtained is obtained, it is any one in the first oil measurement sensor or the second oil measurement sensor
It is individual when breaking down, oil measurement can be carried out by another oil measurement sensor, so as to ensure that the detection of oil mass in fuel tank.
Brief description of the drawings
Fig. 1 is the structural representation of aircraft fuel measuring system according to an embodiment of the invention.
Reference
| 1 | Port wing fuel tank | 7 | First high fuel level annunciator |
| 2 | Starboard wing fuel tank | 8 | Second high fuel level annunciator |
| 3 | First oil measurement sensor | 9 | First low fuel level annunciator |
| 4 | Second oil measurement sensor | 10 | Second low fuel level annunciator |
| 5 | Fuel measurement computer | 11 | First compensation sensor |
| 51 | First processing units | 12 | Second compensation sensor |
| 52 | Second processing unit | 13 | First temperature sensor |
| 6 | Sealed frame joint | 14 | Second temperature sensor |
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention protection
The limitation of scope.
Fig. 1 is the structural representation of aircraft fuel measuring system according to an embodiment of the invention.
Fuel tank fuel quantity for aircraft as shown in Figure 1 is detected, and aircraft includes port wing fuel tank 1 and starboard wing fuel tank 2,
Aircraft fuel measuring system includes：First oil measurement sensor 3 and the second oil measurement sensor 4 and fuel measurement
Computer 5.
Multiple first oil measurement sensors 3 and multiple second oil measurement sensors are provided with port wing fuel tank 1
4；Multiple first oil measurement sensors 3 and multiple second oil measurement sensors 4 are provided with starboard wing fuel tank 2；
The first processing units 51 mutually communicated and second processing unit 52 are provided with fuel measurement computer 5, the
One processing unit 51 is connected with each the first oil measurement sensor 3；Second processing unit 52 is passed with each second oil measurement
Sensor 4 is connected；Wherein, first processing units 51 are used for the signal for receiving the first oil measurement sensor 3；Second processing unit 52
Signal for receiving the second oil measurement sensor 4；First processing units 51 are mutually communicated with second processing unit 52, so that
The signal that other side is obtained is obtained, and then obtains the port wing fuel tank 1 of aircraft and total oil mass of starboard wing fuel tank 2.
It is understood that the first processing units in the application are in communication with each other i.e. mutual transmission two with second processing unit
The respective information of person, so that first processing units can obtain the information of second processing unit, second processing unit can be obtained
Take the information in first processing units.
In aircraft fuel measuring system in the present invention, first processing units mutually transmit letter with second processing unit
Breath, so that the signal that other side is obtained is obtained, it is any one in the first oil measurement sensor or the second oil measurement sensor
It is individual when breaking down, oil measurement can be carried out by another oil measurement sensor, so as to ensure that the detection of oil mass in fuel tank.
In the present embodiment, the first oil measurement sensor 3 and the second oil measurement sensor 4 are identical oil measurement
Sensor.
Using identical oil measurement sensor, due to measurement accuracy, measurement range of each oil measurement sensor etc.
All same, will not be caused between first processing units and second processing unit due to error due to detecting that obtained data are different
And produce and interfere.
In the present embodiment, the cable of each the first oil measurement sensor 3 is handled by sealing frame joint 6 and first
Unit 51 is connected；
The cable of each the second oil measurement sensor 4 is connected by sealing frame joint 6 with second processing unit 52.
Due to being required for ensureing good seal due to each fuel tank, therefore, fuel tank can be ensured by sealing frame joint
Sealing.
In the present embodiment, aircraft fuel measuring system further comprises：First high fuel level annunciator 7 and second is high
Fuel level annunciator 8, the first high fuel level annunciator 7 is arranged in port wing fuel tank 1, and the second high fuel level annunciator 8 is arranged on right machine
In wing fuel tank 2；First high fuel level annunciator 7 is connected with first processing units 51；Second high fuel level annunciator 8 and second processing list
Member 52 is connected.
First high fuel level annunciator is used to detect the oil mass in port wing fuel tank, and feeds back to first processing units, second
High fuel level annunciator is used to detecting oil mass in starboard wing fuel tank, and feeds back to second processing unit, can be for measuring each
The oiling of fuel tank is no more than precalculated position.
And first processing units are mutually communicated with second processing unit, so, when two fuel tanks refuel simultaneously, Neng Gourang
It is average that user knows whether two fuel tanks refuel.
In the present embodiment, aircraft fuel measuring system further comprises：First low fuel level annunciator 9 and second is low
Fuel level annunciator 10, the first low fuel level annunciator 9 is arranged in port wing fuel tank 1, and the second low fuel level annunciator 10 is arranged on the right side
In wing tank 2；First low fuel level annunciator 9 is connected with first processing units 52；At second low fuel level annunciator 10 and second
Reason unit 52 is connected.
First low fuel level annunciator is used to detect the oil mass in port wing fuel tank, and feeds back to first processing units, second
Low fuel level annunciator is used to detecting oil mass in starboard wing fuel tank, and feeds back to second processing unit, can be for measuring each
The oiling of fuel tank is no more than precalculated position.
In the present embodiment, aircraft fuel measuring system further comprises：First compensation sensor 11 and second is mended
Sensor 12 is repaid, the first compensation sensor 11 is arranged in port wing fuel tank 1, and the second compensation sensor 12 is arranged on starboard wing oil
In case 2；First compensation sensor 11 is connected with first processing units 51；Second compensation sensor 12 connects with second processing unit 52
Connect.
First compensation sensor and the second compensation sensor are used to distinguish the oil mass of port wing fuel tank and starboard wing fuel tank
Pass to first processing units and second processing unit.
Referring to Fig. 1, in the present embodiment, aircraft fuel measuring system further comprises：First temperature sensor 13 with
And second temperature sensor 14, the first temperature sensor 13 is arranged in port wing fuel tank 1, and second temperature sensor 14 is arranged on
In starboard wing fuel tank 2；First temperature sensor 13 is connected with first processing units 51；Second temperature sensor 14 and second processing
Unit 52 is connected.
First temperature sensor is used to measure the temperature in port wing fuel tank, and second temperature sensor is used to measure starboard wing
Temperature in fuel tank.
In the present embodiment, the quantity of the first oil measurement sensor in port wing fuel tank is four, the survey of the second oil mass
The quantity of quantity sensor is four；The quantity of the first oil measurement sensor in starboard wing fuel tank is four, the survey of the second oil mass
The quantity of quantity sensor is four.
Present invention also provides a kind of aircraft, the aircraft includes port wing fuel tank and starboard wing fuel tank, the aircraft
Further comprise aircraft fuel measuring system as described above.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (9)
1. a kind of aircraft fuel measuring system, the fuel tank fuel quantity for aircraft is detected, the aircraft includes port wing fuel tank (1)
And starboard wing fuel tank (2), it is characterised in that the aircraft fuel measuring system includes：
It is provided with first oil measurement sensor (3) and the second oil measurement sensor (4), the port wing fuel tank (1)
Multiple first oil measurement sensors (3) and multiple second oil measurement sensors (4)；Set in the starboard wing fuel tank (2)
It is equipped with multiple first oil measurement sensors (3) and multiple second oil measurement sensors (4)；
The first processing units (51) mutually communicated are provided with fuel measurement computer (5), the fuel measurement computer (5)
And second processing unit (52), the first processing units (51) are connected with the first oil measurement sensor (3) each described；
The second processing unit (52) is connected with the second oil measurement sensor (4) each described；Wherein,
The first processing units (51) are used for the signal for receiving the first oil measurement sensor (3)；The second processing
Unit (52) is used for the signal for receiving the second oil measurement sensor (4)；The first processing units (51) and described the
Two processing units (52) are mutually communicated, so as to obtain the signal that other side is obtained, and then obtain the port wing fuel tank of the aircraft
(1) and the starboard wing fuel tank (2) total oil mass.
2. aircraft fuel measuring system as claimed in claim 1, it is characterised in that the first oil measurement sensor
(3) it is identical oil measurement sensor with the second oil measurement sensor (4).
3. aircraft fuel measuring system as claimed in claim 2, it is characterised in that each described first oil measurement sensing
The cable of device (3) is connected by sealing frame joint (6) with the first processing units (51)；
The cable of each the second oil measurement sensor (4) was by sealing frame joint (6) and the second processing unit
(52) connect.
4. aircraft fuel measuring system as claimed in claim 3, it is characterised in that the aircraft fuel measuring system is entered
One step includes：First high fuel level annunciator (7) and the second high fuel level annunciator (8), the first high fuel level annunciator (7) set
Put in port wing fuel tank (1), the second high fuel level annunciator (8) is arranged in starboard wing fuel tank (2)；Described first high oil
Face signalling means (7) is connected with the first processing units (51)；The second high fuel level annunciator (8) and the second processing list
First (52) connection.
5. aircraft fuel measuring system as claimed in claim 4, it is characterised in that the aircraft fuel measuring system is entered
One step includes：First low fuel level annunciator (9) and the second low fuel level annunciator (10), the first low fuel level annunciator (9)
It is arranged in port wing fuel tank (1), the second low fuel level annunciator (10) is arranged in starboard wing fuel tank (2)；Described first
Low fuel level annunciator (9) is connected with the first processing units (52)；The second low fuel level annunciator (10) and described second
Processing unit (52) is connected.
6. aircraft fuel measuring system as claimed in claim 5, it is characterised in that the aircraft fuel measuring system is entered
One step includes：First compensation sensor (11) and the second compensation sensor (12), the first compensation sensor (11) are set
In port wing fuel tank (1), the second compensation sensor (12) is arranged in starboard wing fuel tank (2)；First compensation is passed
Sensor (11) is connected with the first processing units (51)；The second compensation sensor (12) and the second processing unit
(52) connect.
7. aircraft fuel measuring system as claimed in claim 6, it is characterised in that the aircraft fuel measuring system is entered
One step includes：First temperature sensor (13) and second temperature sensor (14), first temperature sensor (13) are set
In port wing fuel tank (1), the second temperature sensor (14) is arranged in the starboard wing fuel tank (2)；First temperature
Degree sensor (13) is connected with the first processing units (51)；The second temperature sensor (14) and the second processing list
First (52) connection.
8. aircraft fuel measuring system as claimed in claim 1, it is characterised in that the first oil in the port wing fuel tank
The quantity for measuring quantity sensor is four, the quantity of the second oil measurement sensor is four；In the starboard wing fuel tank
The quantity of one oil measurement sensor is four, the quantity of the second oil measurement sensor is four.
9. a kind of aircraft, the aircraft includes port wing fuel tank and starboard wing fuel tank, it is characterised in that the aircraft is further
Including aircraft fuel measuring system as claimed in any of claims 1 to 8 in one of claims.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710203374.7A CN107131924A (en) | 2017-03-30 | 2017-03-30 | A kind of aircraft fuel measuring system and the aircraft with it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710203374.7A CN107131924A (en) | 2017-03-30 | 2017-03-30 | A kind of aircraft fuel measuring system and the aircraft with it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107131924A true CN107131924A (en) | 2017-09-05 |
Family
ID=59715891
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710203374.7A Pending CN107131924A (en) | 2017-03-30 | 2017-03-30 | A kind of aircraft fuel measuring system and the aircraft with it |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107131924A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112208781A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业集团有限责任公司 | Low oil level warning system of dual-redundancy aircraft fuel tank |
| CN113203448A (en) * | 2021-04-29 | 2021-08-03 | 陕西飞机工业有限责任公司 | Aircraft oil level measurement anti-interference system |
-
2017
- 2017-03-30 CN CN201710203374.7A patent/CN107131924A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112208781A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业集团有限责任公司 | Low oil level warning system of dual-redundancy aircraft fuel tank |
| CN113203448A (en) * | 2021-04-29 | 2021-08-03 | 陕西飞机工业有限责任公司 | Aircraft oil level measurement anti-interference system |
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Legal Events
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| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170905 |