CN107145693A - The dynamic measurement method of the irregular fuel tank fuel quantity of aircraft - Google Patents
The dynamic measurement method of the irregular fuel tank fuel quantity of aircraft Download PDFInfo
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- CN107145693A CN107145693A CN201710499057.4A CN201710499057A CN107145693A CN 107145693 A CN107145693 A CN 107145693A CN 201710499057 A CN201710499057 A CN 201710499057A CN 107145693 A CN107145693 A CN 107145693A
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Abstract
The present invention relates to technical field of liquid level measurement, specifically provide a kind of dynamic measurement method of the irregular fuel tank fuel quantity of aircraft, obtain every sensor fluid bulk properties data, choose suitable function formula, the all of every sensor data can be fitted in measuring angle, and calculate worst error and relative error, if meeting error criterion, then adopt this formula, other formula are chosen if index is unsatisfactory for or segmentation cutting are carried out to being unsatisfactory for index point, untill index is met, receive sensing data, aspect parameter, obtain effective sensor formula fitting parameter, calculate the fluid volume that every sensor is solved, obtain the fluid bulking value of single fuel tank, further according to experiment or test flight data, pasta angle of being got off the plane to dynamic condition is synchronized with sensor height information, obtain more accurate fuel tank fluid volume.
Description
Technical field
The present invention relates to the dynamic measurement method of technical field of liquid level measurement, the more particularly to irregular fuel tank fuel quantity of aircraft.
Background technology
In aircraft floor maintenance and flight course, the fuel tank fuel quantity under different aspects is to ensure safety to fly and return
The key factor of boat.By the measurement to each fuel tank fuel quantity on aircraft, by the Fuel Oil Remaining of aircraft, fuel consumption speed and oil
Case oil mass feedback of status is to pilot, it is ensured that pilot knows that on the one hand fuel oil service condition can improve flight safety in time
Property；On the other hand active center-of-gravity regulating can be aided in, improves economy, increases aircraft radius.
Present generation aircraft is generally by wing or fuselage frame and wallboard construction overall structure fuel tank, as fuel storage,
The part such as shape and the different pipeline of volume, pump, valve is installed inside it, due to the scrambling of fuel tank and internal part, led
Cause under aircraft dynamic condition that oil mass becomes extremely difficult in accurate measurement fuel tank, the method generally used in engineering is by by oil
Case threedimensional model is discrete to turn to finite model, or fuel tank entity is cut into many thin slices by the addition method of cutting into slices, and obtains volume
Performance data, then by look-up interpolations, calculates fluid volume.
The computational methods have the shortcomings that following several respects：
1st, look-up table needs to take a large amount of memory spaces and computing resource, in the case of airborne computer resource-constrained,
Limit by reducing sampling interval, increase sampling table come the space of improving measurement accuracy；
2nd, because fuel tank is in irregular shape and internal part difference, by the performance data form of compression, using complete
The consistent interpolation algorithm of office calculates fuel bulk, and its computational accuracy is difficult to meet active gravity's center control requirement；
3rd, change the dynamic response poor effect for causing pasta to change with aspect, often lead to occur with air maneuver
The phenomenon that oil mass is acutely beated.
The content of the invention
To overcome at least one defect that above-mentioned prior art is present, the invention provides a kind of irregular fuel tank oil of aircraft
The dynamic measurement method of amount, comprises the following steps：
Step one, the fluid bulk properties data of irregular fuel tank are obtained；
Step 2, packet sequencing is carried out to performance data, removes the point of violation trend, and carry out school to the point for violating trend
Core, the concrete mode of check is：According to the three-dimensional digital-to-analogue of attitude-simulating fuel tank at jump, and reacquire the volume at the point
Performance data；
Step 3, formula is chosen according to the performance data trend in each pasta angle theoretical value combination range, and to volume
Performance data is fitted；
Step 4, calculates the maximum absolute error and relative error of volume, is chosen if formula meets precision index requirement
This formula, otherwise returns to step 3 and chooses formula again, or carries out segmentation cutting to being unsatisfactory for index point, is fitted again, directly
Untill index is met；
Step 5, obtains airborne sensor data, and it includes aspect parameter and sensor infiltration height, the aircraft
Attitude parameter includes pitching α, roll β, three-dimensional acceleration；
Step 6, the on-board data to reception carries out the disposal of gentle filter, removes hopped data and invalid data, the nothing
Data are imitated by data acquisition circuit and given threshold to judge；
Step 7, pasta angle actual value is obtained according to calculating, the fitting parameter of the formula of acquisition effective sensor, and according to
The fitting parameter calculates the corresponding fluid volume of each sensor, carries out the disposal of gentle filter again afterwards, obtains the oil of single fuel tank
Liquid product value；
Step 8, according to test data or test flight data, pasta angle of being got off the plane to dynamic condition and sensor height information
Synchronize, and optimize filtering and smoothing algorithm, and then obtain more accurate fuel tank fluid volume.
It is preferred that, by cutting into slices stacked system or three-dimensional digital-to-analogue discretization mode obtains case fluid bulk properties in step one
Data.
It is preferred that, the bulk properties data include the angle of pitch, roll angle, fuel tank volume, each sensor infiltration height.
It is preferred that, the mode that formula is chosen in step 3 is specially：According to the scatterplot connection of volume in characteristic, it is determined that
Choose linear, multinomial, rolling average, index or logarithm, the mathematical function formula of power.
It is preferred that, the disposal of gentle filter in step 6 and step 7 be by way of removing office of being made even after jump,
Or carried out using Kalman filtering algorithm or Wavelets Filtering Algorithm.
The dynamic measurement method for the irregular fuel tank fuel quantity of aircraft that the present invention is provided, has the advantages that：
1st, calculation accuracy is high, can reach that absolute error is less than 3 liters, relative error is less than 0.5% precision, and error is less than
Existing measuring method, and influenceed to measure extremely accurate under very little, dynamic condition by the various motor-driven postures of aircraft；
2nd, take computer storage and calculation resources are small, if using look-up interpolations, reaching the situation of this calculation accuracy
Under, more than 50M memory space and internal memory is at least needed, and inquiring arithmetic is complicated, takes high CPU calculation resources, uses
After the method for this patent, it is only necessary to minimum memory space and internal memory, storage and calculation resources have greatly been saved.
Brief description of the drawings
Fig. 1 is not using the oil mass and consumption comparison diagram before the measuring method of the invention provided.
Fig. 2 is using the oil mass and consumption comparison diagram after the measuring method of the invention provided.
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.
It should be noted that：The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to for explaining this hair
It is bright, and be not considered as limiting the invention.In the accompanying drawings, same or similar label represents same or like from beginning to end
Element or element with same or like function.Described embodiment is a part of embodiment of the invention, rather than entirely
The embodiment in portion, in the case where not conflicting, the feature in embodiment and embodiment in the application can be mutually combined.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
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 meaning
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention guarantor
Protect the limitation of scope.
The invention provides a kind of dynamic measurement method of the irregular fuel tank fuel quantity of aircraft, comprise the following steps：
Step one, by cutting into slices stacked system or three-dimensional digital-to-analogue discretization mode obtains case fluid bulk properties data, institute
Stating bulk properties data includes the angle of pitch, roll angle, fuel tank volume, each sensor infiltration height, and partial data is as shown in table 1；
The fluid bulk properties partial data of table 1
Bulk properties data are carried out packet sequencing by step 2：Performance data is pre-processed, pretreatment is i.e. by characteristic
Data are grouped according to roll angle, the angle of pitch, and then are ranked up according to sensor height stepping, remove violation trend
Point, violating the point of trend includes jump, and jump, which refers to, does not meet current pasta angle degree lower sensor height and volume rule
Value, such as the point that instead height increase volume falls sharply, and the point for violating trend is checked, the concrete mode of check is：Press
According to the three-dimensional digital-to-analogue of attitude-simulating fuel tank at jump, and reacquire the bulk properties data at the point；
Bulk properties data after packet sequencing are carried out data fitting by step 3：According to each pasta angle theoretical value group
Performance data trend in the range of conjunction chooses formula, and bulk properties data are fitted, in the present embodiment preferably, choosing
The mode for taking formula is specially：According to the scatterplot connection of volume in characteristic, it is determined that choose linear, multinomial, rolling average,
Index or logarithm, the mathematical function formula of power, select formula that is simple and meeting curvilinear characteristic trend to the greatest extent, pass through Matlab as far as possible
Write script and carry out data automatic Fitting；
Whether step 4, the formula being fitted to data that checking is chosen meets requirement：The fitting formula of selection is entered
Row verification, brings sensor height into formula and obtains amendment volume, compare calculated value and actual value, pass through calculated value and actual value
The maximum absolute error and relative error of volume are calculated, this formula is chosen if formula meets precision index requirement, otherwise returns to
Step 3 simultaneously chooses formula again, or carries out segmentation cutting to being unsatisfactory for index point, is fitted again, untill index is met,
By automatic Check means, confirm that fitting result both meets required precision, be not in diverging again, except the abnormity point such as zero, such as institute
There is formula to be unsatisfactory for the method that index can then be cut using segmentation, and to carry out the diverging processing of cut point.Error calculation
As a result it is as shown in table 2：
The error calculation result of table 2
Step 5, obtains airborne sensor data, and it includes aspect parameter and sensor infiltration height, the aircraft
Attitude parameter includes pitching α, roll β, three-dimensional acceleration；
Step 6, the on-board data to reception carries out the disposal of gentle filter, removes hopped data and invalid data, the nothing
Data are imitated by data acquisition circuit and given threshold to judge；
Step 7, pasta angle actual value is obtained according to calculating, the fitting parameter of the formula of acquisition effective sensor, and according to
The fitting parameter calculates the corresponding fluid volume of each sensor, carries out the disposal of gentle filter again afterwards, obtains the oil of single fuel tank
Liquid product value；
Step 8, according to test data or test flight data, pasta angle of being got off the plane to dynamic condition and sensor height information
Synchronize, and optimize filtering and smoothing algorithm, and then obtain more accurate fuel tank fluid volume.
In the present embodiment preferably, the disposal of gentle filter in step 6 and step 7 is to be taken by removing after jump
The mode of draw, or carried out using Kalman filtering algorithm or Wavelets Filtering Algorithm.The disposal of gentle filter algorithm should be according to reality
Border situation is chosen, and can both select the simple algorithm for removing jump and then office of making even, and can also choose the Kalman of complexity
The complicated algorithms such as filtering, wavelet filtering, but should be noted the speed and precision of solution.
As shown in Figures 1 and 2, wherein curve A is the angle of pitch, and curve B is roll angle, and curve C is using before this method
The total oil mass of aircraft, curve C ＇ are that, using the total oil mass of aircraft after this method, curve D is full machine fuel consumption, can from Fig. 1
Oil pump capacity has larger difference with consumption, and oil mass is influenceed fluctuation very big by air maneuver, and as can be seen from Figure 2 oil mass and consumption
Amount is resolved in whole flight course to reach unanimity completely, and is influenceed survey under very little, dynamic condition by the various motor-driven postures of aircraft
Amount is extremely accurate.
The dynamic measurement method of the irregular fuel tank fuel quantity of aircraft provided using the present invention, is contrasted with initial data form,
It can reach that absolute error is less than 3 liters, relative error is less than 0.5% precision, and the storage of occupancy computer and calculation resources are small,
If using look-up interpolations, in the case of reaching this calculation accuracy, more than 50M memory space and internal memory is at least needed, and
Inquiring arithmetic is complicated, high CPU calculation resources is taken, after the method for this patent, it is only necessary to 4.3M memory space and interior
Depositing, and solve the volume data of a sensor only needs 5 floating-points and 6 this add operation, has greatly saved storage and computing
Resource.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can be readily occurred in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (5)
1. a kind of dynamic measurement method of the irregular fuel tank fuel quantity of aircraft, it is characterised in that comprise the following steps：
Step one, the fluid bulk properties data of irregular fuel tank are obtained；
Step 2, packet sequencing is carried out to performance data, removes the point of violation trend, and the point for violating trend is checked,
The concrete mode of check is：According to the three-dimensional digital-to-analogue of attitude-simulating fuel tank at jump, and it is special to reacquire the volume at the point
Property data；
Step 3, formula is chosen according to the performance data trend in each pasta angle theoretical value combination range, and to bulk properties
Data are fitted；
Step 4, calculates the maximum absolute error and relative error of volume, this is chosen if formula meets precision index requirement public
Formula, otherwise returns to step 3 and chooses formula again, or carries out segmentation cutting to being unsatisfactory for index point, is fitted again, until full
Toe is designated as stopping；
Step 5, obtains airborne sensor data, and it includes aspect parameter and sensor infiltration height, the aspect
Parameter includes pitching α, roll β, three-dimensional acceleration；
Step 6, the on-board data to reception carries out the disposal of gentle filter, removes hopped data and invalid data, the invalid number
Judge according to by data acquisition circuit and given threshold；
Step 7, pasta angle actual value is obtained according to calculating, and obtains the fitting parameter of the formula of effective sensor, and according to the plan
Close parameter and calculate the corresponding fluid volume of each sensor, carry out the disposal of gentle filter again afterwards, obtain the fluid body of single fuel tank
Product value；
Step 8, according to test data or test flight data, pasta angle of being got off the plane to dynamic condition is carried out with sensor height information
It is synchronous, and optimize filtering and smoothing algorithm, and then obtain more accurate fuel tank fluid volume.
2. dynamic measurement method according to claim 1, it is characterised in that pass through stacked system or three of cutting into slices in step one
Dimension mould discretization mode obtains case fluid bulk properties data.
3. dynamic measurement method according to claim 1, it is characterised in that the bulk properties data include the angle of pitch,
Roll angle, fuel tank volume, each sensor infiltration height.
4. dynamic measurement method according to claim 1, it is characterised in that the mode that formula is chosen in step 3 is specific
For：According to the scatterplot connection of volume in characteristic, it is determined that choosing linear, multinomial, rolling average, index or logarithm, power
Mathematical function formula.
5. dynamic measurement method according to claim 1, it is characterised in that at the smothing filtering in step 6 and step 7
Reason is carried out by way of removing office of being made even after jump, or using Kalman filtering algorithm or Wavelets Filtering Algorithm.
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| CN201710499057.4A CN107145693B (en) | 2017-06-27 | 2017-06-27 | Dynamic measuring method for oil mass of irregular oil tank of airplane |
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Cited By (9)
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|---|---|---|---|---|
| CN107745826A (en) * | 2017-09-12 | 2018-03-02 | 陕西飞机工业（集团）有限公司 | The more fuel tank vent system string oil test measuring methods of aircraft |
| CN109238547A (en) * | 2018-08-28 | 2019-01-18 | 西北工业大学 | A kind of edge filling method of aircraft airborne equipment monitoring data |
| CN110569481A (en) * | 2019-10-12 | 2019-12-13 | 中铁四局集团有限公司 | Oil quantity calculation method for any oil tank |
| CN110889227A (en) * | 2019-11-28 | 2020-03-17 | 四川泛华航空仪表电器有限公司 | Aircraft fuel oil measuring method based on multi-sensor information fusion |
| CN111008217A (en) * | 2019-11-28 | 2020-04-14 | 四川泛华航空仪表电器有限公司 | Airplane fuel oil quantity three-dimensional linear interpolation table look-up calculation method |
| CN111159909A (en) * | 2019-12-31 | 2020-05-15 | 中国船舶重工集团公司第七0三研究所 | Gas compressor characteristic data processing and characteristic cloud picture drawing method |
| CN114565032A (en) * | 2022-02-21 | 2022-05-31 | 中国石油大学(北京) | Fracturing sand blocking early warning method and device based on pressure data |
| CN115017721A (en) * | 2022-06-22 | 2022-09-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and device for identifying cruise characteristics of airplane and flight control system |
| CN115218986A (en) * | 2022-09-07 | 2022-10-21 | 中航(成都)无人机系统股份有限公司 | Aircraft oil quantity calculation method, device, equipment and storage medium |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107745826A (en) * | 2017-09-12 | 2018-03-02 | 陕西飞机工业（集团）有限公司 | The more fuel tank vent system string oil test measuring methods of aircraft |
| CN109238547A (en) * | 2018-08-28 | 2019-01-18 | 西北工业大学 | A kind of edge filling method of aircraft airborne equipment monitoring data |
| CN110569481B (en) * | 2019-10-12 | 2023-01-24 | 中铁四局集团有限公司 | Oil quantity calculation method for any oil tank |
| CN110569481A (en) * | 2019-10-12 | 2019-12-13 | 中铁四局集团有限公司 | Oil quantity calculation method for any oil tank |
| CN110889227A (en) * | 2019-11-28 | 2020-03-17 | 四川泛华航空仪表电器有限公司 | Aircraft fuel oil measuring method based on multi-sensor information fusion |
| CN111008217A (en) * | 2019-11-28 | 2020-04-14 | 四川泛华航空仪表电器有限公司 | Airplane fuel oil quantity three-dimensional linear interpolation table look-up calculation method |
| CN111159909A (en) * | 2019-12-31 | 2020-05-15 | 中国船舶重工集团公司第七0三研究所 | Gas compressor characteristic data processing and characteristic cloud picture drawing method |
| CN111159909B (en) * | 2019-12-31 | 2023-05-16 | 中国船舶重工集团公司第七0三研究所 | Method for processing characteristic data and drawing characteristic cloud picture of air compressor |
| CN114565032A (en) * | 2022-02-21 | 2022-05-31 | 中国石油大学(北京) | Fracturing sand blocking early warning method and device based on pressure data |
| CN115017721B (en) * | 2022-06-22 | 2023-03-14 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and device for identifying cruise characteristics of airplane and flight control system |
| CN115017721A (en) * | 2022-06-22 | 2022-09-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and device for identifying cruise characteristics of airplane and flight control system |
| CN115218986B (en) * | 2022-09-07 | 2022-12-09 | 中航(成都)无人机系统股份有限公司 | Aircraft oil quantity calculation method, device, equipment and storage medium |
| CN115218986A (en) * | 2022-09-07 | 2022-10-21 | 中航(成都)无人机系统股份有限公司 | Aircraft oil quantity calculation method, device, equipment and storage medium |
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