CN102254041A - Standard design working condition determining method used for building quality characteristic database of spirit of boomer and carrier aircrafts - Google Patents

Abstract

Translated fromChinese

本发明属于飞机燃油测量技术，涉及对用于建立轰运类飞机燃油质量特性数据库的标准设计工况确定方法的改进。标准设计工况包括地面标准设计工况和空中标准设计工况，其特征在于，确定的步骤如下：确定地面标准设计工况；确定空中标准设计工况；以地面标准设计工况和空中标准设计工况下的油箱容腔变形模型作为建立轰运类飞机燃油质量特性数据库的基础。本发明大幅度减小了标准设计工况下油箱容腔模型与其他工况下油箱容腔模型的误差，从而提高了燃油测量精度。The invention belongs to aircraft fuel oil measurement technology, and relates to the improvement of a standard design working condition determination method for establishing a fuel quality characteristic database of bomber aircraft. The standard design conditions include ground standard design conditions and air standard design conditions, characterized in that the determination steps are as follows: determine the ground standard design conditions; determine the air standard design conditions; use the ground standard design conditions and air standard design conditions The deformation model of the fuel tank cavity under working conditions is used as the basis for establishing a database of fuel quality characteristics for bomber aircraft. The invention greatly reduces the error between the fuel tank cavity model under the standard design working condition and the fuel tank cavity model under other working conditions, thereby improving the fuel oil measurement accuracy.

Description

Be used to set up the standard design operating mode of banging fortune class aircraft fuel oil quality characteristics data storehouse and determine method

Technical field

The invention belongs to the aircraft fuel oil measuring technique, relate to and determine the improvement of method being used to set up the standard design operating mode of banging fortune class aircraft fuel oil quality characteristics data storehouse.

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 formula 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 type 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 standard design operating mode in existing both at home and abroad Hong fortune class aircraft fuel oil quality characteristics data storehouse determines that method causes the fuel measurement precision low easily, its reason is: the standard design operating mode in existing Hong fortune class aircraft fuel oil quality characteristics data storehouse determines that method do not consider the influence of fuel tank distortion to oil measurement, the standard design operating mode of choosing is random strong, cause the error of standard design operating mode lower fuel tank cavity volume model and other operating mode lower fuel tank cavity volume models very big, be difficult to take into account simultaneously the multiple common duty in the aircraft course of work, 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 relevant document that the standard design operating mode of banging fortune class aircraft fuel oil quality characteristics data storehouse is determined method that is used to set up.

Summary of the invention

The objective of the invention is: determine method thereby propose a kind of standard design operating mode of banging fortune class aircraft fuel oil quality characteristics data storehouse that is used to set up that can reduce the error raising fuel measurement precision of standard design operating mode lower fuel tank cavity volume model and other operating mode lower fuel tank cavity volume models.

Technical solution of the present invention is: be used to set up the standard design operating mode of banging fortune class aircraft fuel oil quality characteristics data storehouse and determine method, the standard design operating mode comprises ground standard design conditions and aerial standard design operating mode, it is characterized in that the step of determining is as follows:

1, determine ground standard design operating mode:

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;

1.2, obtain the fuel tank cavity volume distorted pattern of each ground design conditions:

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;

1.2.2, 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;

1.2.3, 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;

1.2.4, 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;

1.3, calculate the volume error algebraic sum of each ground design conditions lower fuel tank cavity volume distorted pattern:

At the fuel tank cavity volume distorted pattern under the first ground design conditions, with m+1 surface level the volume of fuel tank cavity volume distorted pattern is divided into m part by zero oil to full oil, m=10～20 obtain the individual oily plane of m+1; With the oily plane of the m+1 that the obtains fuel tank cavity volume distorted pattern of cutting second to last ground design conditions respectively, volume that obtains the following first ground design conditions fuel tank cavity volume distorted pattern in each oily plane respectively and second the absolute value of difference of volume of fuel tank cavity volume distorted pattern to last ground design conditions, above-mentioned absolute value is formed an absolute value matrix M that n-1 is capable, m+1 is listed as_{I, j}, i=1,2 ... n-1, j=1,2 ..., m+1, wherein M_1,1The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under first oily plane and the second ground design conditions fuel tank cavity volume distorted pattern, M_N-1,1The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under first oily plane and last ground design conditions fuel tank cavity volume distorted pattern, M_1,2The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under second oily plane and the second ground design conditions fuel tank cavity volume distorted pattern, M_{1, m+1}The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under m+1 the oily plane and the second ground design conditions fuel tank cavity volume distorted pattern; Calculate the absolute value matrix M_{I, j}Each element sum as the volume error algebraic sum of the first ground design conditions lower fuel tank cavity volume distorted pattern, be designated as Q₁According to the method described above, obtain the absolute value matrix of the second ground design conditions respectively, calculate the volume error algebraic sum Q of the second ground design conditions fuel tank cavity volume distorted pattern then to last ground design conditions fuel tank cavity volume distorted pattern₂Volume error algebraic sum Q to n ground design conditions fuel tank cavity volume distorted pattern_n

1.4, select ground standard design operating mode:

Find out Q₁～Q_nMinimum value, with the ground design conditions of this minimum value correspondence as the ground standard design conditions;

2, determine aerial standard design operating mode:

2.1, divide aerial design conditions: be in aerial cruising condition, on average be divided into p operating mode by empty weight to maximum take-off weight at aircraft according to the aircraft general assembly (TW), p=8～12, the first aerial design conditions are empty machine state, and last aerial design conditions is the maximum take-off weight state;

2.2, obtain the fuel tank cavity volume distorted pattern of each aerial design conditions:

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;

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;

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;

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;

2.3, calculate the volume error algebraic sum of each aerial design conditions lower fuel tank cavity volume distorted pattern:

At the fuel tank cavity volume distorted pattern under the first aerial design conditions, with m+1 surface level the volume of fuel tank cavity volume distorted pattern is divided into m part by zero oil to full oil, m=10～20 obtain the individual oily plane of m+1; With the oily plane of the m+1 that the obtains fuel tank cavity volume distorted pattern of cutting second to last aerial design conditions respectively, the volume that obtains the following first aerial design conditions fuel tank cavity volume distorted pattern in each oily plane respectively and second the absolute value of difference of volume of fuel tank cavity volume distorted pattern to last aerial design conditions, the absolute value matrix N that p-1 of above-mentioned absolute value composition is capable, m+1 is listed as_{K, j}, k=1,2 ... p-1, j=1,2 ..., m+1, wherein N_1,1The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under first oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern, N_P-1,1The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under first oily plane and last aerial design conditions fuel tank cavity volume distorted pattern, N_1,2The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under second oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern, N_{1, m+1}The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under m+1 the oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern; Calculate the absolute value matrix N_{K, j}Each element sum as the volume error algebraic sum of the first aerial design conditions lower fuel tank cavity volume distorted pattern, be designated as S₁According to the method described above, obtain the absolute value matrix of the second aerial design conditions respectively, calculate the volume error algebraic sum S of the second aerial design conditions fuel tank cavity volume distorted pattern then to last aerial design conditions fuel tank cavity volume distorted pattern₂Volume error algebraic sum S to the aerial design conditions fuel tank of p cavity volume distorted pattern_P

2.4, select aerial standard design operating mode: find out S₁～S_PMinimum value, with the aerial design conditions of this minimum value correspondence as aerial standard design operating mode;

3, bang the basis of transporting class aircraft fuel oil quality characteristics data storehouse with the fuel tank cavity volume distorted pattern under ground standard design conditions and the aerial standard design operating mode as setting up.

Advantage of the present invention is: reduced the error of standard design operating mode lower fuel tank cavity volume model and other operating mode lower fuel tank cavity volume models significantly, thereby improved the fuel measurement precision.

Embodiment

Below the present invention is described in further details.Be used to set up the standard design operating mode of banging fortune class aircraft fuel oil quality characteristics data storehouse and determine method, the standard design operating mode comprises ground standard design conditions and aerial standard design operating mode, it is characterized in that the step of determining is as follows:

1, determine ground standard design operating mode:

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;

1.2, obtain the fuel tank cavity volume distorted pattern of each ground design conditions:

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;

1.2.2, 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;

1.2.3, 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;

1.2.4, 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;

1.3, calculate the volume error algebraic sum of each ground design conditions lower fuel tank cavity volume distorted pattern:

At the fuel tank cavity volume distorted pattern under the first ground design conditions, with m+1 surface level the volume of fuel tank cavity volume distorted pattern is divided into m part by zero oil to full oil, m=10～20 obtain the individual oily plane of m+1; With the oily plane of the m+1 that the obtains fuel tank cavity volume distorted pattern of cutting second to last ground design conditions respectively, volume that obtains the following first ground design conditions fuel tank cavity volume distorted pattern in each oily plane respectively and second the absolute value of difference of volume of fuel tank cavity volume distorted pattern to last ground design conditions, above-mentioned absolute value is formed an absolute value matrix M that n-1 is capable, m+1 is listed as_{I, j}, i=1,2 ... n-1, j=1,2 ..., m+1, wherein M_1,1The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under first oily plane and the second ground design conditions fuel tank cavity volume distorted pattern, M_N-1,1The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under first oily plane and last ground design conditions fuel tank cavity volume distorted pattern, M_1,2The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under second oily plane and the second ground design conditions fuel tank cavity volume distorted pattern, M_{1, m+1}The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under m+1 the oily plane and the second ground design conditions fuel tank cavity volume distorted pattern; Calculate the absolute value matrix M_{I, j}Each element sum as the volume error algebraic sum of the first ground design conditions lower fuel tank cavity volume distorted pattern, be designated as Q₁According to the method described above, obtain the absolute value matrix of the second ground design conditions respectively, calculate the volume error algebraic sum Q of the second ground design conditions fuel tank cavity volume distorted pattern then to last ground design conditions fuel tank cavity volume distorted pattern₂Volume error algebraic sum Q to n ground design conditions fuel tank cavity volume distorted pattern_n

1.4, select ground standard design operating mode:

Find out Q₁～Q_nMinimum value, with the ground design conditions of this minimum value correspondence as the ground standard design conditions;

2, determine aerial standard design operating mode:

2.1, divide aerial design conditions: be in aerial cruising condition, on average be divided into p operating mode by empty weight to maximum take-off weight at aircraft according to the aircraft general assembly (TW), p=8～12, the first aerial design conditions are empty machine state, and last aerial design conditions is the maximum take-off weight state;

2.2, obtain the fuel tank cavity volume distorted pattern of each aerial design conditions:

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;

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;

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;

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;

2.3, calculate the volume error algebraic sum of each aerial design conditions lower fuel tank cavity volume distorted pattern:

At the fuel tank cavity volume distorted pattern under the first aerial design conditions, with m+1 surface level the volume of fuel tank cavity volume distorted pattern is divided into m part by zero oil to full oil, m=10～20 obtain the individual oily plane of m+1; With the oily plane of the m+1 that the obtains fuel tank cavity volume distorted pattern of cutting second to last aerial design conditions respectively, the volume that obtains the following first aerial design conditions fuel tank cavity volume distorted pattern in each oily plane respectively and second the absolute value of difference of volume of fuel tank cavity volume distorted pattern to last aerial design conditions, the absolute value matrix N that p-1 of above-mentioned absolute value composition is capable, m+1 is listed as_{K, j}, k=1,2 ... p-1, j=1,2 ..., m+1, wherein N_1,1The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under first oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern, N_P-1,1The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under first oily plane and last aerial design conditions fuel tank cavity volume distorted pattern, N_1,2The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under second oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern, N_{1, m+1}The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under m+1 the oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern; Calculate the absolute value matrix N_{K, j}Each element sum as the volume error algebraic sum of the first aerial design conditions lower fuel tank cavity volume distorted pattern, be designated as S₁According to the method described above, obtain the absolute value matrix of the second aerial design conditions respectively, calculate the volume error algebraic sum S of the second aerial design conditions fuel tank cavity volume distorted pattern then to last aerial design conditions fuel tank cavity volume distorted pattern₂Volume error algebraic sum S to the aerial design conditions fuel tank of p cavity volume distorted pattern_P

2.4, select aerial standard design operating mode: find out S₁～S_pMinimum value, with the aerial design conditions of this minimum value correspondence as aerial standard design operating mode;

3, bang the basis of transporting class aircraft fuel oil quality characteristics data storehouse with the fuel tank cavity volume distorted pattern under ground standard design conditions and the aerial standard design operating mode as setting up.

Principle of work of the present invention is: the present invention proposes a kind of standard design operating mode that is used to set up Hong fortune class aircraft fuel oil quality characteristics data storehouse and determine method, this method comprises determines ground standard design operating mode and aerial two parts of standard design operating mode, be out of shape most important factor-fuel load the state of ground is divided into a plurality of ground design conditions to influence the ground fuel tank in the ground standard design conditions deterministic process, be out of shape most important factor-planeload aerial state is divided into a plurality of aerial design conditions to influence aerial fuel tank in the aerial standard design operating mode deterministic process, on the basis that design conditions are divided, carry out the fuel tank deformation analysis, obtain the fuel tank cavity volume distorted pattern under each ground and the aerial design conditions, by calculating the volume error algebraic sum of each ground and aerial design conditions lower fuel tank cavity volume distorted pattern, with the ground of volume error algebraic sum minimum value correspondence and aerial design conditions as ground and aerial standard design operating mode, volume error algebraic sum minimum shows the comprehensive deviation minimum of this operating mode lower fuel tank cavity volume distorted pattern and other operating mode lower fuel tank cavity volume distorted patterns, with the fuel tank cavity volume distorted pattern under this ground and the aerial standard design operating mode is that the basis is set up the fuel oil quality property database and just can well be taken into account multiple common duty in the aircraft course of work, improve the rationality of fuel oil quality property database, and then improved the fuel measurement precision.

Embodiment

Certain type aircraft Maximum Fuel is 40t, the standard load amount is 20t, standard load is a center of gravity state in the middle of the aircraft, empty weight is 58t, maximum take-off weight is 108t, and it is as follows to determine that this aircraft is set up the required standard design operating mode step of fuel oil quality property database: the standard design operating mode comprises ground standard design conditions and aerial standard design operating mode:

1, determine ground standard design operating mode:

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;

1.2, obtain the fuel tank cavity volume distorted pattern of each ground design conditions:

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;

1.2.2, 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;

1.2.3, 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;

1.2.4, 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;

1.3, calculate the volume error algebraic sum of each ground design conditions lower fuel tank cavity volume distorted pattern:

At the fuel tank cavity volume distorted pattern under the first ground design conditions, with 16 surface levels the volume of fuel tank cavity volume distorted pattern is divided into 15 parts by zero oil to full oil, obtain 16 oily planes; With the fuel tank cavity volume distorted pattern under 16 that obtain oily planes difference cutting second to the 9th design conditions, obtain the volume of the following first ground design conditions fuel tank cavity volume distorted pattern in each oily plane and the absolute value of the difference of the volume of the fuel tank cavity volume distorted pattern under second to the 9th ground design conditions respectively, above-mentioned absolute value is formed one 8 row, the 16 absolute value matrix M that are listed as_{I, j}, i=1,2 ... 8, j=1,2 ..., 16, M wherein_1,1The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under first oily plane and the second ground design conditions fuel tank cavity volume distorted pattern, M_8,1The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under first oily plane and the 9th ground design conditions fuel tank cavity volume distorted pattern, M_1,2The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under second oily plane and the second ground design conditions fuel tank cavity volume distorted pattern, M_1,16The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under the 16th the oily plane and the second ground design conditions fuel tank cavity volume distorted pattern; Calculate the absolute value matrix M_{I, j}Each element sum as the volume error algebraic sum of the first ground design conditions lower fuel tank cavity volume distorted pattern, be designated as Q₁According to the method described above, obtain the absolute value matrix of the second ground design conditions to the, nine ground design conditions fuel tank cavity volume distorted patterns respectively, calculate the volume error algebraic sum Q of the second ground design conditions fuel tank cavity volume distorted pattern then₂Volume error algebraic sum Q to the 9th ground design conditions fuel tank cavity volume distorted pattern₉Q₁To Q₉Value be respectively: 43.96,37.26,30.98,22.82,26.65,31.24,34.50,39.31,46.26;

1.4, select ground standard design operating mode:

Find out Q₁～Q₉Minimum value be 22.82, shut down with the ground of this minimum value correspondence and carry oily 15t operating mode as the ground standard design conditions;

2, determine aerial standard design operating mode:

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;

2.2, obtain the fuel tank cavity volume distorted pattern of each aerial design conditions:

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;

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;

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;

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;

2.3, calculate the volume error algebraic sum of each aerial design conditions lower fuel tank cavity volume distorted pattern:

At the fuel tank cavity volume distorted pattern under the first aerial design conditions, with 15 surface levels the volume of fuel tank cavity volume distorted pattern is divided into 14 parts by zero oil to full oil, obtain 15 oily planes; With the fuel tank cavity volume distorted pattern under 15 that obtain oily planes difference cutting the second to the 15 aerial design conditions, obtain the volume of the following first aerial design conditions fuel tank cavity volume distorted pattern in each oily plane and the absolute value of the difference of the volume of the fuel tank cavity volume distorted pattern under the second to the 15 aerial design conditions respectively, one 10 row of above-mentioned absolute value composition, the 15 absolute value matrix N that are listed as_{K, j}, k=1,2 ... 10, j=1,2 ..., 15, N wherein_1,1The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under first oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern, N_10,1The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under first oily plane and the 15 aerial design conditions fuel tank cavity volume distorted pattern, N_1,2The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under second oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern, N_1,15The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under the 15th the oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern; Calculate the absolute value matrix N_{K, j}Each element sum as the volume error algebraic sum of the first aerial design conditions lower fuel tank cavity volume distorted pattern, be designated as S₁According to the method described above, obtain the absolute value matrix of second aerial design conditions to the 15 aerial design conditions fuel tank cavity volume distorted patterns respectively, calculate the volume error algebraic sum S of the second aerial design conditions fuel tank cavity volume distorted pattern then₂Volume error algebraic sum S to the 11 aerial design conditions fuel tank cavity volume distorted pattern₁₁S₁To S₁₁Value be respectively: 90.46,88.65,81.31,68.27,51.55,42.53,42.48,56.96,67.25,74.25,81.69;

2.4, select aerial standard design operating mode: find out S₁～S₁₁Minimum value be 42.48, with the general assembly (TW) 88t operating mode of cruising in the air of this minimum value correspondence as aerial standard design operating mode;

3, bang the basis of transporting class aircraft fuel oil quality characteristics data storehouse with the fuel tank cavity volume distorted pattern under ground standard design conditions and the aerial standard design operating mode as setting up.

Claims (1)

1. be used to set up the standard design operating mode of banging fortune class aircraft fuel oil quality characteristics data storehouse and determine method, the standard design operating mode comprises ground standard design conditions and aerial standard design operating mode, it is characterized in that the step of determining is as follows:

1.1, determine ground standard design operating mode:

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 volume error algebraic sum of each ground design conditions lower fuel tank cavity volume distorted pattern:

At the fuel tank cavity volume distorted pattern under the first ground design conditions, with m+1 surface level the volume of fuel tank cavity volume distorted pattern is divided into m part by zero oil to full oil, m=10～20 obtain the individual oily plane of m+1; With the oily plane of the m+1 that the obtains fuel tank cavity volume distorted pattern of cutting second to last ground design conditions respectively, volume that obtains the following first ground design conditions fuel tank cavity volume distorted pattern in each oily plane respectively and second the absolute value of difference of volume of fuel tank cavity volume distorted pattern to last ground design conditions, above-mentioned absolute value is formed an absolute value matrix M that n-1 is capable, m+1 is listed as_{I, j}, i=1,2 ... n-1, j=1,2 ..., m+1, wherein M_1,1The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under first oily plane and the second ground design conditions fuel tank cavity volume distorted pattern, M_N-1,1The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under first oily plane and last ground design conditions fuel tank cavity volume distorted pattern, M_1,2The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under second oily plane and the second ground design conditions fuel tank cavity volume distorted pattern, M_{1, m+1}The absolute value of representing the volume difference of the volume of the first ground design conditions fuel tank cavity volume distorted pattern under m+1 the oily plane and the second ground design conditions fuel tank cavity volume distorted pattern; Calculate the absolute value matrix M_{I, j}Each element sum as the volume error algebraic sum of the first ground design conditions lower fuel tank cavity volume distorted pattern, be designated as Q₁According to the method described above, obtain the absolute value matrix of the second ground design conditions respectively, calculate the volume error algebraic sum Q of the second ground design conditions fuel tank cavity volume distorted pattern then to last ground design conditions fuel tank cavity volume distorted pattern₂Volume error algebraic sum Q to n ground design conditions fuel tank cavity volume distorted pattern_n

1.1.4, select ground standard design operating mode:

Find out Q₁～Q_nMinimum value, with the ground design conditions of this minimum value correspondence as the ground standard design conditions;

1.2, determine aerial standard design operating mode:

1.2.1, divide aerial design conditions: be in aerial cruising condition, on average be divided into p operating mode by empty weight to maximum take-off weight at aircraft according to the aircraft general assembly (TW), 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 volume error algebraic sum of each aerial design conditions lower fuel tank cavity volume distorted pattern:

At the fuel tank cavity volume distorted pattern under the first aerial design conditions, with m+1 surface level the volume of fuel tank cavity volume distorted pattern is divided into m part by zero oil to full oil, m=10～20 obtain the individual oily plane of m+1; With the oily plane of the m+1 that the obtains fuel tank cavity volume distorted pattern of cutting second to last aerial design conditions respectively, the volume that obtains the following first aerial design conditions fuel tank cavity volume distorted pattern in each oily plane respectively and second the absolute value of difference of volume of fuel tank cavity volume distorted pattern to last aerial design conditions, the absolute value matrix N that p-1 of above-mentioned absolute value composition is capable, m+1 is listed as_{K, j}, k=1,2 ... p-1, j=1,2 ..., m+1, wherein N_1,1The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under first oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern, N_P-1,1The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under first oily plane and last aerial design conditions fuel tank cavity volume distorted pattern, N_1,2The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under second oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern, N_{1, m+1}The absolute value of representing the volume difference of the volume of the first aerial design conditions fuel tank cavity volume distorted pattern under m+1 the oily plane and the second aerial design conditions fuel tank cavity volume distorted pattern; Calculate the absolute value matrix N_{K, j}Each element sum as the volume error algebraic sum of the first aerial design conditions lower fuel tank cavity volume distorted pattern, be designated as S₁According to the method described above, obtain the absolute value matrix of the second aerial design conditions respectively, calculate the volume error algebraic sum S of the second aerial design conditions fuel tank cavity volume distorted pattern then to last aerial design conditions fuel tank cavity volume distorted pattern₂Volume error algebraic sum S to the aerial design conditions fuel tank of p cavity volume distorted pattern_P

1.2.4, select aerial standard design operating mode: find out S₁～S_PMinimum value, with the aerial design conditions of this minimum value correspondence as aerial standard design operating mode;

1.3, with the fuel tank cavity volume distorted pattern under ground standard design conditions and the aerial standard design operating mode as the basis of setting up Hong fortune class aircraft fuel oil quality characteristics data storehouse.