CN100510655C - Aerial craft oil mass measurement error correcting method - Google Patents
Aerial craft oil mass measurement error correcting method Download PDFInfo
- Publication number
- CN100510655C CN100510655C CNB2007103041785A CN200710304178A CN100510655C CN 100510655 C CN100510655 C CN 100510655C CN B2007103041785 A CNB2007103041785 A CN B2007103041785A CN 200710304178 A CN200710304178 A CN 200710304178A CN 100510655 C CN100510655 C CN 100510655C
- Authority
- CN
- China
- Prior art keywords
- fuel
- oil
- measurement error
- aircraft
- survey
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Landscapes
- Measuring Volume Flow (AREA)
Abstract
The invention discloses an aircraft fuel content measurement error correction method, which comprises the following steps of: calculating and correcting engine specific fuel consumption, determining measurement error of a fuel content sensor, and correcting the fuel content measurement error. The invention aircraft fuel content measurement error correction method can meet the accuracy requirement that is unattainable in theoretical calculation, eliminate the cumulative error arising from theoretical calculation, and avoid the accidental measurement error of the fuel content sensor arising from other interference factors, so that the residual fuel content measurement of the aircraft is more accurate, the flight speed can be accurately set, and the flight is safer and more reliable.
Description
Technical field
The invention belongs to the aeronautical technology field, relate in particular to a kind of modification method of aerial craft oil mass measurement error.
Background technology
For long unmanned plane in cruising time, can collect more complete information, also can provide than satellite detailed condition more, and flight path is more flexibly than the satellite system based on the space, so this unmanned plane has become the target that various countries give priority at present.
Because this class unmanned plane has determined it must carry a large amount of fuel oils and could satisfy mission requirements.Such as the large-scale high-altitude long-range unmanned aerial vehicle " global hawk " of the U.S., its Gross Weight Takeoff 11612Kg, maximum fuel weight 6577Kg, fuel weight accounts for more than 56% of whole machine weight; The high and medium long-range unmanned aerial vehicle " predator " of the U.S. for another example, its Gross Weight Takeoff 3175Kg, maximum fuel weight 1588Kg, fuel weight accounts for 50% of whole machine weight.Big fuel load has satisfied mission requirements on the one hand, has also brought some problems of unmanned plane use aspect on the other hand.In order to guarantee flight safety, under different flying weights, must select suitable flying speed, with the flight attitude that keeps aircraft in suitable angle-of-attack range.For the unmanned plane of long-time flight, the fuel weight proportion is bigger, and therefore the flying weight difference is very big when full oil condition and empty machine state, and corresponding flying speed value also differs bigger.In order to select suitable flying speed, must measure accurately, calculate the Fuel Oil Remaining of aircraft.Fuel Oil Remaining with aircraft adds the empty weight of boarding a plane, and can obtain the current flying weight of aircraft, then according to formula G=ρ V
2Sc
y/ 2 obtain the flying speed V under this weight, and G is a flying weight in the formula, and ρ is an atmospheric density, and S is a wing area, c
yBe the airplane ascensional force coefficient.
At present, can determine Fuel Oil Remaining on the machine by two kinds of methods, a kind of is method by calculating, and another kind is directly to measure by fuel-quantity transducer.Adopt the method for calculating to save fuel-quantity transducer,, call for Control Software as long as ground test result or Theoretical Calculation result are stored in the flight control computer; Adopt fuel-quantity transducer directly to measure Fuel Oil Remaining, it is comparatively convenient to use.But these two kinds of methods all have its intrinsic shortcoming, are difficult to obtain Fuel Oil Remaining accurately in actual use.First method need be done a large amount of ground experiments, so not only need to expend a large amount of financial resources, manpower, and aircraft aloft state of flight is more, the engine behavior that is difficult to a pair of various states by ground experiment is tested, so can not obtain very comprehensive data in this way; Though and by calculating the oil consumption rate that can obtain engine under the various situations, according to present research situation, result of calculation is very inaccurate, the long-time use calculated the result, is easy to generate bigger cumulative errors.Though second method more easily realizes, but fuel-quantity transducer is relatively more responsive for environmental factor, factor such as fuel qualities, temperature all can cause than mistake measurement result, and aspect, fuel tank shape also can cause the saltus step of measurement result, thereby cause flight safety hidden danger.
The fast development of current unmanned plane for how controlling unmanned plane is accurately had higher requirement, and in order to adapt to this development trend, need improve for above two kinds of oil measurement methods.
Summary of the invention
The objective of the invention is to use the uncertainty that is had respectively separately at existing theoretical calculation method and sensor measurement, a kind of method of oil mass measurement error correction is provided, adopt computing method to combine with the sensor direct method of measurement, by mutual verification, determine the Fuel Oil Remaining of different phase aircraft accurately, improved aircraft safety and reliability.
Oil mass measurement error correcting method provided by the invention comprises 3 steps, i.e. the correction of the determining of the calculating of engine oil consumption rate and correction, fuel-quantity transducer measuring error, oil mass measurement error.
The calculating of step 1, engine oil consumption rate and correction.Select several duties, adopt the oil consumption rate of theoretical analysis method calculating aircraft under these several duties; By the ground stand test, survey the oil consumption rate under the various duties.Relatively theoretical analysis and calculation and ground stand test findings are revised theoretical calculation method.
Determining of step 2, fuel-quantity transducer measuring error.Measure the measuring error of fuel-quantity transducer under the different service conditions by ground experiment, determine maximum oil mass measurement error.
The correction of step 3, oil mass measurement error.The maximum oil mass measurement error that obtains in the revised theoretical calculation method that obtains in the step 1, the step 2 is bound into flight control computer; Flight control computer is determined flying speed V according to the Fuel Oil Remaining of aircraft flight; By theoretical calculation value and measurement value sensor relatively carry out mutual correction, make aircraft determine flying speed according to remaining oil value accurately.
Use aerial craft oil mass measurement error correcting method of the present invention, both can satisfy the unapproachable accuracy requirement of Theoretical Calculation, eliminate the cumulative errors that Theoretical Calculation is brought, avoided again because other disturbing factors cause the accidental measuring error of fuel-quantity transducer, make the Fuel Oil Remaining measurement of aircraft more accurate, flying speed can accurately be set, and makes flight course more safe and reliable.
Description of drawings
Fig. 1 is the correction process flow diagram of error correcting method of the present invention;
Fig. 2 is the estimated value curve map of aircraft Fuel Oil Remaining in the actual use;
Fig. 3 is the measured value curve map of aircraft Fuel Oil Remaining in the actual use.
Embodiment
The present invention is described in further detail below in conjunction with drawings and Examples.
The present invention provides a kind of aerial craft oil mass measurement error correcting method, according to independent use theoretical calculation method Fuel Oil Remaining is calculated cumulative errors that exists and the accidental error of using sensor that oil measurement is existed separately, and a kind of modification method that puts forward.As shown in Figure 2 be the estimated value curve of aircraft Fuel Oil Remaining in the actual use, the aircraft Fuel Oil Remaining measured value curve map that shown in Figure 3 is in the actual use, as seen from Figure 3, in the starting stage, the measured value of fuel-quantity transducer has produced bigger saltus step, the measured value that can judge fuel-quantity transducer provides is an apparent error, thinks that estimated value and actual value are approaching this moment, therefore determines flying speed according to estimated value.After one period flight time, measured value and estimated value are identical substantially, and flying speed is determined according to measured value again, and with measured value estimated value revised.According to such correction principle, oil mass measurement error correcting method provided by the present invention is realized as follows:
Step 1: the calculating of engine oil consumption rate and correction.Comprise the steps:
(1) chooses one group of typical engine behavior, adopt a kind of theoretical calculation method to ask in the typical engine of this group oil consumption rate q under every kind of duty
i
(2) by the ground stand test, survey the oil consumption rate of the typical engine of this group under every kind of duty
(3) oil consumption rate that obtains of two kinds of methods of Theoretical Calculation and ground stand test q as a result relatively
iWith
, and the oil consumption rate that obtains with ground stand
For benchmark is revised theoretical calculation method, up to the oil consumption rate q that uses Theoretical Calculation to obtain
iThe oil consumption rate of result and ground stand experiment
The result conforms to, the theoretical calculation method that obtains revising;
(4) revised theoretical calculation method is bound into flight control computer, uses in order to revising the fuel-quantity transducer measured value.
Step 2: the determining of fuel-quantity transducer measuring error.Promptly, obtain the maximum oil mass measurement error of fuel-quantity transducer, comprise the steps: by the earth station test
(1) be m with known weight
iFuel oil add fuel tank;
(2) according to the fuel-quantity transducer service condition, adjust factors such as aspect, fuel qualities, temperature, measure the fuel weight that fuel-quantity transducer measures under the different service conditions
(3) the fuel-quantity transducer oil mass measurement error Δ e under the calculating different condition
i,
Determine maximum oil measurement error delta e, Δ e=Max (Δ e
i);
(4) maximum oil measurement error delta e is bound into flight control computer, as the basis for estimation of fuel-quantity transducer inefficacy.
Step 3: the correction of oil mass measurement error, revise flow process as shown in Figure 1:
(1) take off before with fuel oil initial weight value m
0Be bound into flight control computer;
(2) flight control computer is according to fuel oil initial value m
0Select flying speed V;
(3) behind at interval certain flight time Δ t,, adopt the revised theoretical calculation method that obtains in the step 1 can determine corresponding oil consumption rate q according to parameters such as aircraft flight height, speed, joint air door, airscrewpistons, and then according to formula
m
Estimate=m
0-q * Δ t
Estimate the residual mass m of fuel oil on the machine
Estimate
(4) the Fuel Oil Remaining measured value m of fuel-quantity transducer on the reading machine
SurveyCalculate m
EstimateWith m
SurveyDifference DELTA m, Δ m=|m
Estimate-m
Survey|;
(5) if Δ m≤Δ e then makes m
0=m
Survey, according to m
SurveyDetermine flying speed V;
(6) if Δ m〉Δ e, then make m
0=m
Estimate, according to m
EstimateDetermine flying speed V;
(7) repeat (3)～(6) step, just can obtain aircraft accurately, realize selection aircraft flight speed at difference flying weight constantly.
Embodiment:Further specify oil measurement modification method provided by the invention below by the specific embodiment data, as shown in Figures 2 and 3 be the curve map that aircraft Fuel Oil Remaining in certain flight course is measured estimated value and measured value, adopt two fuel-quantity transducers (model is respectively GUC-61/1, GUC-61/2) that fuel consumption is monitored in real time, concrete steps are:
Step 1: the calculating of engine oil consumption rate and correction, select several duties, adopt the oil consumption rate of theoretical analysis method calculating aircraft under these several duties; By the ground stand test, survey the oil consumption rate under the various duties; Relatively theoretical analysis and calculation and ground stand test findings are revised theoretical calculation method.Obtain revised theoretical calculation method, revised theoretical calculation method is bound into flight control computer, use in order to revising the fuel-quantity transducer measured value.
Step 2: the determining of fuel-quantity transducer measuring error; In ground experiment, measure the measuring error of fuel-quantity transducer under the different service conditions by fuel-quantity transducer, determine maximum oil measurement error delta e=50kg, maximum oil measurement error delta e is bound into flight control computer, as the basis for estimation of fuel-quantity transducer inefficacy.
Step 3: the correction of oil mass measurement error.
1) will take off preceding fuel oil initial weight m
0=260kg is bound into flight control computer;
2) in the initial 1s moment, saltus step has taken place in fuel-quantity transducer, as shown in Figure 3, and according to fuel oil initial weight m
0=260kg selects flying speed V;
3),, determine that according to the theoretical calculation method of the correction that obtains in the step 1 corresponding oil consumption rate is q=14.5Kg/h, then the estimated value of Fuel Oil Remaining on the machine according to data such as flying height, speed, joint air door and airscrewpistons through after 0.5 hour:
m
Estimate=m
0-q * Δ t=260-14.5 * 0.5=252.75 (kg);
4) read the measured value m of two fuel-quantity transducers
Survey, m
Survey=255Kg as shown in Figure 3, calculates m
EstimateWith m
SurveyDifference DELTA m, Δ m=|m
Estimate-m
Survey|=| 252.75-255|=2.25 (Kg);
5) because of Δ m=2.25＜50, so make m
0=m
Survey=255Kg is according to m
Survey=255Kg determines flying speed V; Can see from Fig. 2 that have a small stair on the oil mass estimated value curve this moment, this is the correction that the oil measurement value is carried out the oil mass estimated value.
6) repeat 3)～5) step, just can determine the flying speed in the whole flight course accurately.In whole flight course, the oil measurement value is constantly revised estimated value, has eliminated the cumulative errors that estimated value brought; And when accidental saltus step error appears in the oil measurement value, estimated value is proofreaied and correct measured value again, eliminated accidental error, therefore method provided by the invention effectively raises the accuracy that the aircraft Fuel Oil Remaining is measured, for the accurate selection of unmanned plane during flying speed is got ready.
Claims (2)
1, a kind of aerial craft oil mass measurement error correcting method is characterized in that comprising the steps:
The calculating of step 1, engine oil consumption rate and correction; Select several duties, adopt the oil consumption rate of theoretical analysis method calculating aircraft under these several duties; By the ground stand test, survey the oil consumption rate under each duty; Relatively theoretical analysis and calculation and ground stand test findings are revised theoretical calculation method;
Determining of step 2, fuel-quantity transducer measuring error; Measure the measuring error of fuel-quantity transducer under the different service conditions by ground experiment, determine maximum oil mass measurement error;
The correction of step 3, oil mass measurement error; The maximum oil mass measurement error that obtains in the revised theoretical calculation method that obtains in the step 1, the step 2 is bound into flight control computer; Flight control computer is determined flying speed V according to the Fuel Oil Remaining of aircraft flight; By theoretical calculation value and measurement value sensor relatively carry out mutual correction, make aircraft determine flying speed according to remaining oil value accurately.
2, aerial craft oil mass measurement error correcting method according to claim 1 is characterized in that described step 3 comprises:
(a) take off before with revised oil mass theoretical calculation method, maximum oil measurement error delta e, fuel oil initial value m
0Be bound into flight control computer;
(b) flight control computer is according to fuel oil initial value m
0Select flying speed V;
(c) behind at interval certain flight time Δ t,, adopt revised theoretical calculation method can determine corresponding oil consumption rate q according to aircraft flight height, speed, joint air door, airscrewpiston parameter, and then according to formula m
Estimate=m
0-q * Δ t estimates the residual mass m of fuel oil on the machine
Estimate
(d) the Fuel Oil Remaining measured value of fuel-quantity transducer on the difference reading machine is got its mean value as m
SurveyCalculate m
EstimateWith m
SurveyDifference DELTA m, Δ m=|m
Estimate-m
Survey|;
(e) if Δ m≤Δ e then makes m
0=m
Survey, according to m
SurveyDetermine flying speed V;
(f) if Δ m〉Δ e, then make m
0=m
Estimate, according to m
EstimateDetermine flying speed V;
(g) repeat (c)～(f) step, just can obtain aircraft accurately, realize determining aircraft flight speed at difference flying weight constantly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007103041785A CN100510655C (en) | 2007-12-25 | 2007-12-25 | Aerial craft oil mass measurement error correcting method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007103041785A CN100510655C (en) | 2007-12-25 | 2007-12-25 | Aerial craft oil mass measurement error correcting method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101210839A CN101210839A (en) | 2008-07-02 |
| CN100510655C true CN100510655C (en) | 2009-07-08 |
Family
ID=39611014
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2007103041785A Expired - Fee Related CN100510655C (en) | 2007-12-25 | 2007-12-25 | Aerial craft oil mass measurement error correcting method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100510655C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11193810B2 (en) | 2020-01-31 | 2021-12-07 | Pratt & Whitney Canada Corp. | Validation of fluid level sensors |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101634612B (en) * | 2009-08-21 | 2011-01-05 | 北京航空航天大学 | Method for determining long-endurance flight parameter of unmanned plane |
| CN101929887B (en) * | 2010-08-31 | 2011-11-16 | 北京航空航天大学 | Method for measuring weight of airplane |
| CN102853871B (en) * | 2011-06-30 | 2015-07-22 | 艾默生网络能源有限公司 | Oil level monitoring method and system |
| DE102012002504A1 (en) * | 2012-02-10 | 2013-08-14 | Hella Kgaa Hueck & Co. | Method for evaluating oil level of vehicle in idle state using control and evaluation electronics of oil level sensor, involves determining tilt-induced offset from oil level measured in idle state of vehicle and from compensation value |
| CN104048733A (en) * | 2014-05-23 | 2014-09-17 | 苏州佳世达光电有限公司 | Oil mass measuring method and oil mass measuring system |
| CN110781457B (en) * | 2019-10-24 | 2024-03-08 | 深圳市瑞达飞行科技有限公司 | Method and device for processing oil consumption data in departure stage, electronic equipment and storage medium |
| CN110889227B (en) * | 2019-11-28 | 2023-05-05 | 四川泛华航空仪表电器有限公司 | Aircraft fuel measurement method based on multi-sensor information fusion |
| CN111767608B (en) * | 2020-05-22 | 2021-10-08 | 成都飞机工业（集团）有限责任公司 | Cruise section oil consumption correction method based on test flight data standard weight |
| CN112046762B (en) * | 2020-09-07 | 2021-10-22 | 南京航空航天大学 | Turboprop engine-based hybrid unmanned aerial vehicle and take-off and landing control method thereof |
| CN112903050A (en) * | 2021-02-20 | 2021-06-04 | 四川腾盾科技有限公司 | Method for calculating real-time fuel quantity of unmanned aerial vehicle |
| CN113008489A (en) * | 2021-05-25 | 2021-06-22 | 四川腾盾科技有限公司 | Method and system for detecting oil leakage of oil tank in flight process of unmanned aerial vehicle |
-
2007
- 2007-12-25 CN CNB2007103041785A patent/CN100510655C/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11193810B2 (en) | 2020-01-31 | 2021-12-07 | Pratt & Whitney Canada Corp. | Validation of fluid level sensors |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101210839A (en) | 2008-07-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100510655C (en) | Aerial craft oil mass measurement error correcting method | |
| CN110928201B (en) | Semi-physical test method and system for aircraft avionics system | |
| Ray et al. | Flight test techniques used to evaluate performance benefits during formation flight | |
| Kimberlin | Flight testing of fixed wing aircraft | |
| CN103064421B (en) | Automatic Landing method and apparatus of the aircraft on heavy grade runway | |
| CN105093130A (en) | Unmanned aerial vehicle cruising capacity monitoring system and method | |
| CN105539843A (en) | Electric unmanned plane and cruising ability estimating method thereof | |
| Vachon et al. | F/A-18 aircraft performance benefits measured during the autonomous formation flight project | |
| Morelli et al. | Real-time dynamic modeling: data information requirements and flight-test results | |
| CN101929887B (en) | Method for measuring weight of airplane | |
| CN103994748B (en) | A kind of method adopting flight and wind tunnel test data estimation unmanned plane trim angle of attack | |
| CN101858748A (en) | Fault-tolerance autonomous navigation method of multi-sensor of high-altitude long-endurance unmanned plane | |
| CN109710961A (en) | A kind of High Altitude UAV ceiling data processing method based on GPS data | |
| US8666698B2 (en) | Aircraft takeoff weight calculating method and system | |
| CN105628112A (en) | Method for measuring oil quantities | |
| CN105807087A (en) | Method and device for determining the wind speed to be taken into account in order to optimize the takeoff weight of an aircraft | |
| Lee et al. | Closed-form takeoff weight estimation model for air transportation simulation | |
| Trainelli et al. | Innovative helicopter in-flight noise monitoring systems enabled by rotor-state measurements | |
| CN113460328A (en) | System and method for civil aircraft ground comprehensive dynamic detection | |
| Smith et al. | Longitudinal aerodynamic modeling of the adaptive compliant trailing edge flaps on a GIII aircraft and comparisons to flight data | |
| CN116107347A (en) | Test flight planning method for verifying maximum range index of piston power unmanned aerial vehicle | |
| Curry et al. | Dynamic ground effect for a cranked arrow wing airplane | |
| Siu et al. | Flight test results of an angle of attack and angle of sideslip calibration method using Output-Error optimization | |
| Harigae et al. | Development of GPS Aided Inertial Navigation System for High Speed Flight Demonstrator | |
| Myers et al. | The dynamic icing detection system (DIDS) |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090708 Termination date: 20111225 |