CN102289584A - Correction method for deformation of fuel tank for measuring fuel quantity of bombing transportation type airplane - Google Patents
Correction method for deformation of fuel tank for measuring fuel quantity of bombing transportation type airplane Download PDFInfo
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- CN102289584A CN102289584A CN2011102325945A CN201110232594A CN102289584A CN 102289584 A CN102289584 A CN 102289584A CN 2011102325945 A CN2011102325945 A CN 2011102325945A CN 201110232594 A CN201110232594 A CN 201110232594A CN 102289584 A CN102289584 A CN 102289584A
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Abstract
The invention belongs to a fuel quantity measuring technique for an airplane and particularly relates to a correction method for the deformation of a fuel tank for measuring the fuel quantity of a bombing transportation type airplane. Based on an airplane-mounted fuel quantity measuring and resolving system comprising an airplane fuel quantity characteristic database and a fuel tank liquid level sensor, the correction method provided by the invention comprises the following steps: establishing a deformation correction curve of the fuel tank for measuring the fuel quantity of the airplane and carrying out the measuring correction for the fuel quantity. The method provided by the invention improves the measuring accuracy for the fuel quantity of the bombing transportation type airplane and meets the requirements for measuring the high-accuracy fuel quantity of a modern bombing transportation type airplane.
Description
Technical field
The invention belongs to aircraft fuel oil measurement amount technology, relate to a kind of Hong fortune class aircraft fuel oil and measure the masuring tank distortion correction method.
Background technology
Fuel tank oil mass and distribution thereof are the important Back ground Informations of aircraft, and stable, accurate amount of fuel is measured significant to improving the overall aircraft performance.On the one hand, accurate amount of fuel measurement is the needs that the center of gravity of airplane is controlled.Amount of fuel is the changeable weight of aircraft maximum, general aircraft fuel oil amount account for whole machine weight 30%～60% between, by accurate measurement, be convenient to adjust the distribution of fuel oil at each fuel tank to each oil tank fuel amount in the aircraft, the control of the realization center of gravity of airplane, guarantee that the center of gravity of airplane remains within institute's allowed band, and center of gravity of airplane deviation is huge to the flying quality influence, gently then owing to need the horizontal tail trim to increase flight resistance, increase oil consumption, influence economy, heavy then influence is grasped steady, brings safety issue.On the other hand, accurate amount of fuel measurement is the needs of enforcement science flight management.In real time, accurately measure Fuel Oil Remaining in the fuel tank can the accurate Calculation aircraft cruising time, guarantee aircraft safety flight.
At present, domestic and international modal aircraft fuel oil measuring method is: measure fuel head by the fuel-quantity transducer that is dispersed throughout the fuel tank different parts, inquiry characterizes the fuel oil quality property database of fuel head and amount of fuel corresponding relation then, obtains the oil measurement result after difference is resolved.Wherein the reliability of fuel oil quality property database and rationality are one of key factors of the final oil measurement precision of influence.
The basis of setting up the fuel oil quality property database is to characterize the fuel tank cavity volume model that fluid took up space, for banging the wing one-piece construction fuel tank that fortune class aircraft generally adopts, because its span is big, extraneous load (fuel oil gravity and flight aerodynamic force) is very big to the deformation effect of Oiltank structure, with ground shutdown and aerial cruising condition is example, only be subjected to the effect of fuel oil gravity and wing structure gravity under the stopped status of ground owing to Oiltank structure, Oiltank structure is in curved state down, aloft under the cruising condition because under the effect of aerodynamic loading more upwards, Oiltank structure is in the state of upwarping; Certain model transporter Oiltank structure deformation analysis result shows: under equal fuel load situation; shut down and nearly 1 meter of aerial cruising condition lower fuel tank structure outermost end displacement deviation on ground; therefore, Hong fortune class aircraft different operating state lower fuel tank cavity volume model is widely different.In principle in order to improve the oil measurement precision, need set up the fuel oil quality property database respectively according to different modular design operating modes carries out oil mass and resolves, but because the restriction of computer data memory space and computation complexity, generally speaking, can only select 1 or 2 standard design operating modes to set up the fuel oil quality property database.Great majority directly select for use oil tank type frame cavity volume model to set up a fuel oil quality property database as the standard design operating mode in the existing type both at home and abroad; More advanced aircraft selects two standard design operating modes to set up the fuel oil quality property database, is generally ground and shuts down the standard load state and the standard load state that cruises in the air.The shortcoming of Hong fortune class aircraft fuel oil measuring method is at present: the precision of measurement is lower.Reason is: because various different operating mode lower fuel tank cavity volume model differences are big, if under other operating mode, directly carrying out oil mass according to standard design operating mode fuel oil quality property database resolves, do not revise, the oil measurement precision will obviously reduce, be difficult to reach the requirement of American army mark MIL-G-26988C Class III class precision, can not satisfy the needs that modern Hong fortune class aircraft high precision amount of fuel is measured.Do not retrieve the document that relevant Hong fortune class aircraft fuel oil measures the masuring tank distortion correction method both at home and abroad.
Summary of the invention
The objective of the invention is: propose a kind of Hong fortune class aircraft fuel oil and measure the masuring tank distortion correction method, to satisfy the needs that modern Hong fortune class aircraft high precision amount of fuel is measured.
Technical solution of the present invention is: Hong fortune class aircraft fuel oil measures the masuring tank distortion correction method, resolves system based on a Fuel On Board measurement amount that comprises aircraft fuel oil quality characteristics data storehouse and oil tank liquid level sensor, and the step of correction is:
1, set up aircraft fuel oil and measure masuring tank distortion fair curve: aircraft fuel oil measures masuring tank distortion fair curve and is made up of ground fuel tank distortion fair curve and aerial fuel tank distortion fair curve;
1.1, set up aircraft fuel oil measurement amount ground fuel tank distortion fair curve:
1.1.1, divide the ground design conditions: be in the ground stopped status at aircraft, do not comprise under the standard load situation of fuel oil, on average be divided into n operating mode by zero oil to expiring oil according to fuel load, n=6～10, the first ground design conditions are zero oil condition, and last ground design conditions is full oil condition;
1.1.2, obtain the fuel tank cavity volume distorted pattern of each ground design conditions:
1.1.2.1, obtain the external envelope face of oil tank type frame cavity volume model: according to oil tank type frame three-dimensional digital model, stripping oil box frame cavity volume model, simultaneously, on oil tank type frame cavity volume model based, the external envelope face of stripping oil box frame cavity volume model;
1.1.2.2, determine the load data under each ground design conditions: carry out the fuel weight Distribution calculation according to the geostatic pressure fueling state, determine the fuel oil load data, obtain the Oiltank structure load data according to oil tank type frame three-dimensional digital model, fuel oil load data and Oiltank structure load data constitute the load data under the design conditions of ground jointly;
1.1.2.3, carry out each ground design conditions lower fuel tank deformation analysis: the finite element model of setting up oil tank type frame three-dimensional digital model, carry out the malformation analysis according to the load data under each ground design conditions, obtain comprising the destination file of node initial coordinate and deformation displacement;
1.1.2.4, obtain each ground design conditions lower fuel tank cavity volume distorted pattern: the initial coordinate and the deformation displacement that extract node on each ground design conditions lower fuel tank type frame cavity volume model external envelope face according to the The above results file; Based on this, construct each ground design conditions lower fuel tank cavity volume model external envelope cloud data, the fuel tank cavity volume model enveloping surface after cloud data is carried out match and obtains being out of shape, and construct each ground design conditions lower fuel tank cavity volume distorted pattern on this basis;
1.1.3, calculate the fuel tank distortion correction factor of each ground design conditions: at the fuel tank cavity volume distorted pattern under the first ground design conditions, determine the fuel load Q of the first ground design conditions correspondence
1Oily plane in this operating mode lower fuel tank cavity volume distorted pattern, and this oily plane is imported Fuel On Board measurement amount resolve system obtains amount of fuel and resolves the result and be S
1, calculate Q
1With S
1Ratio a
1Fuel tank distortion correction factor as these ground design conditions; Calculate second the fuel tank distortion correction factor a to last ground design conditions after the same method
2To a
n
1.1.4, match ground fuel tank distortion fair curve: by linear interpolation or other high-order interpolation methods fuel tank distortion correction factor a with each ground design conditions
iFit to ground fuel tank distortion fair curve, the natural number of i=1～n; The horizontal ordinate of this ground fuel tank distortion fair curve is the numerical value of fuel load, and ordinate is the numerical value of fuel tank distortion correction factor;
1.2, set up the aerial fuel tank of aircraft fuel oil measurement amount distortion fair curve:
1.2.1, divide aerial design conditions: be under aerial cruising condition, the standard load situation at aircraft, on average be divided into p operating mode according to the aircraft general assembly (TW) by empty weight to maximum take-off weight, p=8～12, the first aerial design conditions are empty machine state, and last aerial design conditions is the maximum take-off weight state;
1.2.2, obtain the fuel tank cavity volume distorted pattern of each aerial design conditions:
1.2.2.1, obtain the external envelope face of oil tank type frame cavity volume model: according to oil tank type frame three-dimensional digital model, stripping oil box frame cavity volume model, simultaneously, on oil tank type frame cavity volume model based, the external envelope face of stripping oil box frame cavity volume model;
1.2.2.2, determine the load data under each aerial design conditions: carry out the fuel weight Distribution calculation according to aerial normal oil consumption state, determine the fuel oil load data, obtain the Oiltank structure load data according to oil tank type frame three-dimensional digital model blowing load data, the common load data that constitutes under the aerial design conditions of fuel oil load data and Oiltank structure load data;
1.2.2.3, carry out each aerial design conditions lower fuel tank deformation analysis: the finite element model of setting up oil tank type frame three-dimensional digital model, carry out the malformation analysis according to the load data under each aerial design conditions, obtain comprising the destination file of node initial coordinate and deformation displacement;
1.2.2.4, obtain each aerial design conditions lower fuel tank cavity volume distorted pattern: the initial coordinate and the deformation displacement that extract node on each aerial design conditions lower fuel tank type frame cavity volume model external envelope face according to the The above results file; Based on this, construct each aerial design conditions lower fuel tank cavity volume model external envelope cloud data, the fuel tank cavity volume model enveloping surface after cloud data is carried out match and obtains being out of shape, and construct each aerial design conditions lower fuel tank cavity volume distorted pattern on this basis;
1.2.3, calculate the fuel tank distortion correction factor of each aerial design conditions: at the fuel tank cavity volume distorted pattern under the first aerial design conditions, determine the pairing fuel load M of the first aerial design conditions
1Oily plane in this operating mode lower fuel tank cavity volume distorted pattern, and this oily plane is imported Fuel On Board measurement amount resolve system obtains amount of fuel and resolves the result and be N
1, calculate M
1With N
1Ratio b
1Fuel tank distortion correction factor as these aerial design conditions; Calculate second the fuel tank distortion correction factor b to last aerial design conditions after the same method
2To b
p
1.2.4, the aerial fuel tank of match distortion fair curve: by linear interpolation or other high-order interpolation methods fuel tank distortion correction factor b with each aerial design conditions
jFit to aerial fuel tank distortion fair curve, the natural number of j=1～p; The horizontal ordinate of this aerial fuel tank distortion fair curve is the numerical value of aircraft general assembly (TW), and ordinate is the numerical value of fuel tank distortion correction factor;
2, carry out amount of fuel and measure correction:
2.1, select fuel tank distortion fair curve: Fuel On Board measurement amount is resolved system according to aircraft liftoff selection fuel tank distortion fair curve whether, and aircraft is liftoff, and aerial fuel tank distortion fair curve is selected in the back, otherwise selects ground fuel tank distortion fair curve;
2.2, determine current amount of fuel correction factor: aircraft is liftoff, and the back is a horizontal ordinate with the aircraft general assembly (TW) data that fly guard system and provide, and finds out current amount of fuel correction factor in the fair curve of fuel tank distortion aloft; Otherwise resolving the current amount of fuel that system resolves with Fuel On Board measurement amount is horizontal ordinate, finds out current amount of fuel correction factor in ground fuel tank distortion fair curve;
2.3, the amount of fuel correction: Fuel On Board measurement amount is resolved current amount of fuel that system resolves multiply by current amount of fuel correction factor and obtain revised amount of fuel measurement result.
Advantage of the present invention is: improved the precision of Hong fortune class aircraft fuel oil measurement amount, satisfied the needs that modern Hong fortune class aircraft high precision amount of fuel is measured.
Embodiment
Below the present invention is described in further details.Hong fortune class aircraft fuel oil measures the masuring tank distortion correction method, resolves system based on a Fuel On Board measurement amount that comprises aircraft fuel oil quality characteristics data storehouse and oil tank liquid level sensor, and the step of correction is:
1, set up aircraft fuel oil and measure masuring tank distortion fair curve: aircraft fuel oil measures masuring tank distortion fair curve and is made up of ground fuel tank distortion fair curve and aerial fuel tank distortion fair curve;
1.1, set up aircraft fuel oil measurement amount ground fuel tank distortion fair curve:
1.1.1, divide the ground design conditions: be in the ground stopped status at aircraft, do not comprise under the standard load situation of fuel oil, on average be divided into n operating mode by zero oil to expiring oil according to fuel load, n=6～10, the first ground design conditions are zero oil condition, and last ground design conditions is full oil condition;
1.1.2, obtain the fuel tank cavity volume distorted pattern of each ground design conditions:
1.1.2.1, obtain the external envelope face of oil tank type frame cavity volume model: according to oil tank type frame three-dimensional digital model, stripping oil box frame cavity volume model, simultaneously, on oil tank type frame cavity volume model based, the external envelope face of stripping oil box frame cavity volume model;
1.1.2.2, determine the load data under each ground design conditions: carry out the fuel weight Distribution calculation according to the geostatic pressure fueling state, determine the fuel oil load data, obtain the Oiltank structure load data according to oil tank type frame three-dimensional digital model, fuel oil load data and Oiltank structure load data constitute the load data under the design conditions of ground jointly;
1.1.2.3, carry out each ground design conditions lower fuel tank deformation analysis: the finite element model of setting up oil tank type frame three-dimensional digital model, carry out the malformation analysis according to the load data under each ground design conditions, obtain comprising the destination file of node initial coordinate and deformation displacement;
1.1.2.4, obtain each ground design conditions lower fuel tank cavity volume distorted pattern: the initial coordinate and the deformation displacement that extract node on each ground design conditions lower fuel tank type frame cavity volume model external envelope face according to the The above results file; Based on this, construct each ground design conditions lower fuel tank cavity volume model external envelope cloud data, the fuel tank cavity volume model enveloping surface after cloud data is carried out match and obtains being out of shape, and construct each ground design conditions lower fuel tank cavity volume distorted pattern on this basis;
1.1.3, calculate the fuel tank distortion correction factor of each ground design conditions: at the fuel tank cavity volume distorted pattern under the first ground design conditions, determine the fuel load Q of the first ground design conditions correspondence
1Oily plane in this operating mode lower fuel tank cavity volume distorted pattern, and this oily plane is imported Fuel On Board measurement amount resolve system obtains amount of fuel and resolves the result and be S
1, calculate Q
1With S
1Ratio a
1Fuel tank distortion correction factor as these ground design conditions; Calculate second the fuel tank distortion correction factor a to last ground design conditions after the same method
2To a
n
1.1.4, match ground fuel tank distortion fair curve: by linear interpolation or other high-order interpolation methods fuel tank distortion correction factor a with each ground design conditions
iFit to ground fuel tank distortion fair curve, the natural number of i=1～n; The horizontal ordinate of this ground fuel tank distortion fair curve is the numerical value of fuel load, and ordinate is the numerical value of fuel tank distortion correction factor;
1.2, set up the aerial fuel tank of aircraft fuel oil measurement amount distortion fair curve:
1.2.1, divide aerial design conditions: be under aerial cruising condition, the standard load situation at aircraft, on average be divided into p operating mode according to the aircraft general assembly (TW) by empty weight to maximum take-off weight, p=8～12, the first aerial design conditions are empty machine state, and last aerial design conditions is the maximum take-off weight state;
1.2.2, obtain the fuel tank cavity volume distorted pattern of each aerial design conditions:
1.2.2.1, obtain the external envelope face of oil tank type frame cavity volume model: according to oil tank type frame three-dimensional digital model, stripping oil box frame cavity volume model, simultaneously, on oil tank type frame cavity volume model based, the external envelope face of stripping oil box frame cavity volume model;
1.2.2.2, determine the load data under each aerial design conditions: carry out the fuel weight Distribution calculation according to aerial normal oil consumption state, determine the fuel oil load data, obtain the Oiltank structure load data according to oil tank type frame three-dimensional digital model blowing load data, the common load data that constitutes under the aerial design conditions of fuel oil load data and Oiltank structure load data;
1.2.2.3, carry out each aerial design conditions lower fuel tank deformation analysis: the finite element model of setting up oil tank type frame three-dimensional digital model, carry out the malformation analysis according to the load data under each aerial design conditions, obtain comprising the destination file of node initial coordinate and deformation displacement;
1.2.2.4, obtain each aerial design conditions lower fuel tank cavity volume distorted pattern: the initial coordinate and the deformation displacement that extract node on each aerial design conditions lower fuel tank type frame cavity volume model external envelope face according to the The above results file; Based on this, construct each aerial design conditions lower fuel tank cavity volume model external envelope cloud data, the fuel tank cavity volume model enveloping surface after cloud data is carried out match and obtains being out of shape, and construct each aerial design conditions lower fuel tank cavity volume distorted pattern on this basis;
1.2.3, calculate the fuel tank distortion correction factor of each aerial design conditions: at the fuel tank cavity volume distorted pattern under the first aerial design conditions, determine the pairing fuel load M of the first aerial design conditions
1Oily plane in this operating mode lower fuel tank cavity volume distorted pattern, and this oily plane is imported Fuel On Board measurement amount resolve system obtains amount of fuel and resolves the result and be N
1, calculate M
1With N
1Ratio b
1Fuel tank distortion correction factor as these aerial design conditions; Calculate second the fuel tank distortion correction factor b to last aerial design conditions after the same method
2To b
p
1.2.4, the aerial fuel tank of match distortion fair curve: by linear interpolation or other high-order interpolation methods fuel tank distortion correction factor b with each aerial design conditions
jFit to aerial fuel tank distortion fair curve, the natural number of j=1～p; The horizontal ordinate of this aerial fuel tank distortion fair curve is the numerical value of aircraft general assembly (TW), and ordinate is the numerical value of fuel tank distortion correction factor;
2, carry out amount of fuel and measure correction:
2.1, select fuel tank distortion fair curve: Fuel On Board measurement amount is resolved system according to aircraft liftoff selection fuel tank distortion fair curve whether, and aircraft is liftoff, and aerial fuel tank distortion fair curve is selected in the back, otherwise selects ground fuel tank distortion fair curve;
2.2, determine current amount of fuel correction factor: aircraft is liftoff, and the back is a horizontal ordinate with the aircraft general assembly (TW) data that fly guard system and provide, and finds out current amount of fuel correction factor in the fair curve of fuel tank distortion aloft; Otherwise resolving the current amount of fuel that system resolves with Fuel On Board measurement amount is horizontal ordinate, finds out current amount of fuel correction factor in ground fuel tank distortion fair curve;
2.3, the amount of fuel correction: Fuel On Board measurement amount is resolved current amount of fuel that system resolves multiply by current amount of fuel correction factor and obtain revised amount of fuel measurement result.
Principle of work of the present invention is: the present invention proposes a kind of Hong fortune class aircraft fuel oil and measure the masuring tank distortion correction method, this method is resolved system based on a Fuel On Board measurement amount that comprises aircraft fuel oil quality characteristics data storehouse and oil tank liquid level sensor, comprises that setting up aircraft fuel oil measures masuring tank distortion fair curve and carry out two steps of amount of fuel measurement correction.Aircraft fuel oil measures masuring tank distortion fair curve and is made up of ground fuel tank distortion fair curve and aerial fuel tank distortion fair curve, by division to ground and aerial design conditions, carry out the fuel tank deformation analysis, obtain the fuel tank cavity volume distorted pattern under each ground and the aerial design conditions; On this basis, by calculating each ground and aerial design conditions with respect to the fuel tank distortion correction factor of standard condition separately, fuel tank is out of shape correction factor carries out match, obtain with the fuel load is that horizontal ordinate, correction factor are the ground fuel tank distortion fair curve of ordinate and are that horizontal ordinate, correction factor are the aerial fuel tank distortion fair curve of ordinate with the aircraft general assembly (TW), carrying out oil measurement when resolving, according to the aircraft known conditions, the interpolation of tabling look-up is determined the correction factor of current oil mass, and multiplies each other with measured value and to obtain revising back oil mass value; The method can reduce the oil mass measurement error that various different operating mode lower fuel tank cavity volume model differences are brought greatly significantly, has improved the precision of Hong fortune class aircraft fuel oil measurement amount, has satisfied the needs that modern Hong fortune class aircraft high precision amount of fuel is measured.
Embodiment
Certain type aircraft Maximum Fuel is 40t, and the standard load amount is 20t, and standard load is a center of gravity state in the middle of the aircraft, and empty weight is 58t, and maximum take-off weight is 108t, and the step of carrying out amount of fuel measurement fuel tank distortion correction is as follows:
1, set up aircraft fuel oil and measure masuring tank distortion fair curve: aircraft fuel oil measures masuring tank distortion fair curve and is made up of ground fuel tank distortion fair curve and aerial fuel tank distortion fair curve;
1.1, set up aircraft fuel oil measurement amount ground fuel tank distortion fair curve:
1.1.1, divide the ground design conditions: be in the ground stopped status at aircraft, do not comprise under the situation of standard load 20t of fuel oil, on average be divided into 9 operating modes by zero oil to expiring oil according to fuel load, first to the 9th operating mode is respectively ground and shuts down oily 0t, 5t, 10t, 15t, 20t, 25t, 30t, 35t, the 40t state of carrying;
1.1.2, obtain the fuel tank cavity volume distorted pattern of each ground design conditions:
1.1.2.1, obtain the external envelope face of oil tank type frame cavity volume model: according to oil tank type frame three-dimensional digital model, stripping oil box frame cavity volume model, simultaneously, on oil tank type frame cavity volume model based, the external envelope face of stripping oil box frame cavity volume model;
1.1.2.2, determine the load data under each ground design conditions: carry out the fuel weight Distribution calculation according to the geostatic pressure fueling state, determine the fuel oil load data, obtain the Oiltank structure load data according to oil tank type frame three-dimensional digital model, fuel oil load data and Oiltank structure load data constitute the load data under the design conditions of ground jointly;
1.1.2.3, carry out each ground design conditions lower fuel tank deformation analysis: the finite element model of setting up oil tank type frame three-dimensional digital model, carry out the malformation analysis according to the load data under each ground design conditions, obtain comprising the destination file of node initial coordinate and deformation displacement;
1.1.2.4, obtain each ground design conditions lower fuel tank cavity volume distorted pattern: the initial coordinate and the deformation displacement that extract node on each ground design conditions lower fuel tank type frame cavity volume model external envelope face according to the The above results file; Based on this, construct each ground design conditions lower fuel tank cavity volume model external envelope cloud data, the fuel tank cavity volume model enveloping surface after cloud data is carried out match and obtains being out of shape, and construct each ground design conditions lower fuel tank cavity volume distorted pattern on this basis;
1.1.3, calculate the fuel tank distortion correction factor of each ground design conditions: at the fuel tank cavity volume distorted pattern under the first ground design conditions, determine the fuel load Q of the first ground design conditions correspondence
1Oily plane in this operating mode lower fuel tank cavity volume distorted pattern, and this oily plane is imported Fuel On Board measurement amount resolve system obtains amount of fuel and resolves the result and be S
1, calculate Q
1With S
1Ratio a
1Fuel tank distortion correction factor as these ground design conditions; Calculate the fuel tank distortion correction factor a under second to the 9th ground design conditions after the same method
2To a
9
1.1.4, match ground fuel tank distortion fair curve: by the fuel tank distortion correction factor a of linear interpolation method with each ground design conditions
iFit to ground fuel tank distortion fair curve, the natural number of i=1～9; The horizontal ordinate of this ground fuel tank distortion fair curve is the numerical value of fuel load, and ordinate is the numerical value of fuel tank distortion correction factor;
1.2, set up the aerial fuel tank of aircraft fuel oil measurement amount distortion fair curve:
1.2.1, divide aerial design conditions: be in aerial cruising condition at aircraft, on average be divided into 11 operating modes according to the aircraft general assembly (TW) by 58t to 108t, the first to the 11 operating mode is respectively aerial cruiser gross weight 58t, 63t, 68t, 73t, 78t, 83t, 88t, 93t, 98t, 103t, the 108t state, the charging capacity of the first to the 11 operating mode correspondence is respectively 0t, 5t, 10t, 15t, 20t, 20t, 20t, 20t, 20t, 20t, 20t, loading is the middle center of gravity state of aircraft, and the fuel load of the first to the 11 operating mode correspondence is respectively 0t, 0t, 0t, 0t, 0t, 5t, 10t, 15t, 20t, 25t, 30t;
1.2.2, obtain the fuel tank cavity volume distorted pattern of each aerial design conditions:
1.2.2.1, obtain the external envelope face of oil tank type frame cavity volume model: according to oil tank type frame three-dimensional digital model, stripping oil box frame cavity volume model, simultaneously, on oil tank type frame cavity volume model based, the external envelope face of stripping oil box frame cavity volume model;
1.2.2.2, determine the load data under each aerial design conditions: carry out the fuel weight Distribution calculation according to aerial normal oil consumption state, determine the fuel oil load data, obtain the Oiltank structure load data according to oil tank type frame three-dimensional digital model blowing load data, the common load data that constitutes under the aerial design conditions of fuel oil load data and Oiltank structure load data;
1.2.2.3, carry out each aerial design conditions lower fuel tank deformation analysis: the finite element model of setting up oil tank type frame three-dimensional digital model, carry out the malformation analysis according to the load data under each aerial design conditions, obtain comprising the destination file of node initial coordinate and deformation displacement;
1.2.2.4, obtain each aerial design conditions lower fuel tank cavity volume distorted pattern: the initial coordinate and the deformation displacement that extract node on each aerial design conditions lower fuel tank type frame cavity volume model external envelope face according to the The above results file; Based on this, construct each aerial design conditions lower fuel tank cavity volume model external envelope cloud data, the fuel tank cavity volume model enveloping surface after cloud data is carried out match and obtains being out of shape, and construct each aerial design conditions lower fuel tank cavity volume distorted pattern on this basis;
1.2.3, calculate the fuel tank distortion correction factor of each aerial design conditions: at the fuel tank cavity volume distorted pattern under the first aerial design conditions, determine the pairing fuel load M of the first aerial design conditions
1Oily plane in this operating mode lower fuel tank cavity volume distorted pattern, and this oily plane is imported Fuel On Board measurement amount resolve system obtains amount of fuel and resolves the result and be N
1, calculate M
1With N
1Ratio b
1Fuel tank distortion correction factor as these aerial design conditions; Calculate the fuel tank distortion correction factor b under the second to the 11 aerial design conditions after the same method
2To b
11
1.2.4, the aerial fuel tank of match distortion fair curve: by the fuel tank distortion correction factor b of linear interpolation method with each aerial design conditions
jFit to aerial fuel tank distortion fair curve, the natural number of j=1～11; The horizontal ordinate of this aerial fuel tank distortion fair curve is the numerical value of aircraft general assembly (TW), and ordinate is the numerical value of fuel tank distortion correction factor;
2, carry out amount of fuel and measure correction:
2.1, select fuel tank distortion fair curve: Fuel On Board measurement amount is resolved system according to aircraft liftoff selection fuel tank distortion fair curve whether, and aircraft is liftoff, and aerial fuel tank distortion fair curve is selected in the back, otherwise selects ground fuel tank distortion fair curve;
2.2, determine current amount of fuel correction factor: aircraft is liftoff, and the back is a horizontal ordinate with the aircraft general assembly (TW) data that fly guard system and provide, and finds out current amount of fuel correction factor in the fair curve of fuel tank distortion aloft; Otherwise resolving the current amount of fuel that system resolves with Fuel On Board measurement amount is horizontal ordinate, finds out current amount of fuel correction factor in ground fuel tank distortion fair curve;
2.3, the amount of fuel correction: Fuel On Board measurement amount is resolved current amount of fuel that system resolves multiply by current amount of fuel correction factor and obtain revised amount of fuel measurement result.
Claims (1)
1. Hong fortune class aircraft fuel oil measures the masuring tank distortion correction method, resolves system based on a Fuel On Board measurement amount that comprises aircraft fuel oil quality characteristics data storehouse and oil tank liquid level sensor, and the step of correction is:
1.1, set up aircraft fuel oil and measure masuring tank distortion fair curve: aircraft fuel oil measures masuring tank distortion fair curve and is made up of ground fuel tank distortion fair curve and aerial fuel tank distortion fair curve;
1.1.1, set up aircraft fuel oil measurement amount ground fuel tank distortion fair curve:
1.1.1.1, divide the ground design conditions: be in the ground stopped status at aircraft, do not comprise under the standard load situation of fuel oil, on average be divided into n operating mode by zero oil to expiring oil according to fuel load, n=6～10, the first ground design conditions are zero oil condition, and last ground design conditions is full oil condition;
1.1.1.2, obtain the fuel tank cavity volume distorted pattern of each ground design conditions:
1.1.1.2.1, obtain the external envelope face of oil tank type frame cavity volume model: according to oil tank type frame three-dimensional digital model, stripping oil box frame cavity volume model, simultaneously, on oil tank type frame cavity volume model based, the external envelope face of stripping oil box frame cavity volume model;
1.1.1.2.2, determine the load data under each ground design conditions: carry out the fuel weight Distribution calculation according to the geostatic pressure fueling state, determine the fuel oil load data, obtain the Oiltank structure load data according to oil tank type frame three-dimensional digital model, fuel oil load data and Oiltank structure load data constitute the load data under the design conditions of ground jointly;
1.1.1.2.3, carry out each ground design conditions lower fuel tank deformation analysis: the finite element model of setting up oil tank type frame three-dimensional digital model, carry out the malformation analysis according to the load data under each ground design conditions, obtain comprising the destination file of node initial coordinate and deformation displacement;
1.1.1.2.4, obtain each ground design conditions lower fuel tank cavity volume distorted pattern: the initial coordinate and the deformation displacement that extract node on each ground design conditions lower fuel tank type frame cavity volume model external envelope face according to the The above results file; Based on this, construct each ground design conditions lower fuel tank cavity volume model external envelope cloud data, the fuel tank cavity volume model enveloping surface after cloud data is carried out match and obtains being out of shape, and construct each ground design conditions lower fuel tank cavity volume distorted pattern on this basis;
1.1.1.3, calculate the fuel tank distortion correction factor of each ground design conditions: at the fuel tank cavity volume distorted pattern under the first ground design conditions, determine the fuel load Q of the first ground design conditions correspondence
1Oily plane in this operating mode lower fuel tank cavity volume distorted pattern, and this oily plane is imported Fuel On Board measurement amount resolve system obtains amount of fuel and resolves the result and be S
1, calculate Q
1With S
1Ratio a
1Fuel tank distortion correction factor as these ground design conditions; Calculate second the fuel tank distortion correction factor a to last ground design conditions after the same method
2To a
n
1.1.1.4, match ground fuel tank distortion fair curve: by linear interpolation or other high-order interpolation methods fuel tank distortion correction factor a with each ground design conditions
iFit to ground fuel tank distortion fair curve, the natural number of i=1～n; The horizontal ordinate of this ground fuel tank distortion fair curve is the numerical value of fuel load, and ordinate is the numerical value of fuel tank distortion correction factor;
1.1.2, set up the aerial fuel tank of aircraft fuel oil measurement amount distortion fair curve:
1.1.2.1, divide aerial design conditions: be under aerial cruising condition, the standard load situation at aircraft, on average be divided into p operating mode according to the aircraft general assembly (TW) by empty weight to maximum take-off weight, p=8～12, the first aerial design conditions are empty machine state, and last aerial design conditions is the maximum take-off weight state;
1.1.2.2, obtain the fuel tank cavity volume distorted pattern of each aerial design conditions:
1.1.2.2.1, obtain the external envelope face of oil tank type frame cavity volume model: according to oil tank type frame three-dimensional digital model, stripping oil box frame cavity volume model, simultaneously, on oil tank type frame cavity volume model based, the external envelope face of stripping oil box frame cavity volume model;
1.1.2.2.2, determine the load data under each aerial design conditions: carry out the fuel weight Distribution calculation according to aerial normal oil consumption state, determine the fuel oil load data, obtain the Oiltank structure load data according to oil tank type frame three-dimensional digital model blowing load data, the common load data that constitutes under the aerial design conditions of fuel oil load data and Oiltank structure load data;
1.1.2.2.3, carry out each aerial design conditions lower fuel tank deformation analysis: the finite element model of setting up oil tank type frame three-dimensional digital model, carry out the malformation analysis according to the load data under each aerial design conditions, obtain comprising the destination file of node initial coordinate and deformation displacement;
1.1.2.2.4, obtain each aerial design conditions lower fuel tank cavity volume distorted pattern: the initial coordinate and the deformation displacement that extract node on each aerial design conditions lower fuel tank type frame cavity volume model external envelope face according to the The above results file; Based on this, construct each aerial design conditions lower fuel tank cavity volume model external envelope cloud data, the fuel tank cavity volume model enveloping surface after cloud data is carried out match and obtains being out of shape, and construct each aerial design conditions lower fuel tank cavity volume distorted pattern on this basis;
1.1.2.3, calculate the fuel tank distortion correction factor of each aerial design conditions: at the fuel tank cavity volume distorted pattern under the first aerial design conditions, determine the pairing fuel load M of the first aerial design conditions
1Oily plane in this operating mode lower fuel tank cavity volume distorted pattern, and this oily plane is imported Fuel On Board measurement amount resolve system obtains amount of fuel and resolves the result and be N
1, calculate M
1With N
1Ratio b
1Fuel tank distortion correction factor as these aerial design conditions; Calculate second the fuel tank distortion correction factor b to last aerial design conditions after the same method
2To b
p
1.1.2.4, the aerial fuel tank of match distortion fair curve: by linear interpolation or other high-order interpolation methods fuel tank distortion correction factor b with each aerial design conditions
jFit to aerial fuel tank distortion fair curve, the natural number of j=1～p; The horizontal ordinate of this aerial fuel tank distortion fair curve is the numerical value of aircraft general assembly (TW), and ordinate is the numerical value of fuel tank distortion correction factor;
1.2, carry out amount of fuel and measure to revise:
1.2.1, select fuel tank distortion fair curve: Fuel On Board measurement amount is resolved system according to aircraft liftoff selection fuel tank distortion fair curve whether, and aircraft is liftoff, and aerial fuel tank distortion fair curve is selected in the back, otherwise selects ground fuel tank distortion fair curve;
1.2.2, determine current amount of fuel correction factor: aircraft is liftoff, and the back is a horizontal ordinate with the aircraft general assembly (TW) data that fly guard system and provide, and finds out current amount of fuel correction factor in the fair curve of fuel tank distortion aloft; Otherwise resolving the current amount of fuel that system resolves with Fuel On Board measurement amount is horizontal ordinate, finds out current amount of fuel correction factor in ground fuel tank distortion fair curve;
1.2.3, the amount of fuel correction: Fuel On Board measurement amount is resolved current amount of fuel that system resolves multiply by current amount of fuel correction factor and obtain revised amount of fuel measurement result.
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