CN111256787A - Online high-precision calibration method for flowmeter of launching site surface filling system - Google Patents

Online high-precision calibration method for flowmeter of launching site surface filling system Download PDF

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CN111256787A
CN111256787A CN202010147967.8A CN202010147967A CN111256787A CN 111256787 A CN111256787 A CN 111256787A CN 202010147967 A CN202010147967 A CN 202010147967A CN 111256787 A CN111256787 A CN 111256787A
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flowmeter
filling
rocket
coefficient
propellant
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高家智
相有桓
张平
石刚
廖乐平
崔本廷
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No63729 Troops Pla
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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01FMEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
    • G01F25/00Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume
    • G01F25/10Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume of flowmeters

Abstract

The invention discloses an on-line high-precision calibration method for a flowmeter of a launching site ground filling system. Aiming at the defects of the calibration method of the flow meter of the filling system of the domestic launching site, the invention provides an on-line calibration method of the flow meter of the filling system based on the marking liquid level of a rocket storage tank. According to the method, on the basis of an initial K coefficient, the flowmeter is calibrated through the rocket tank marking liquid level, and the high-precision flowmeter K coefficient is obtained through calculation. The method effectively improves the filling metering precision of the rocket propellant, and has important significance for ensuring the successful launch of the rocket.

Description

Online high-precision calibration method for flowmeter of launching site surface filling system
Technical Field
The invention relates to an online high-precision calibration method for a flowmeter of a launching site ground filling system, and belongs to the technical field of spaceflight launching site flowmeter calibration.
Background
The filling system is an important component of ground equipment of an aerospace launching site, and mainly completes tasks such as filling, back venting, back flow beating, propellant temperature regulation, transfer and the like of rocket propellant (Helong, xuguang, plum bud and the like. application of computer control technology in the propellant filling system [ J ]. missile and aerospace carrying technology, 2015, (4):58-61., Suyongzhi, Lijun. The flowmeter is a key device of a filling system and is mainly used for metering the filling amount when the rocket propellant is filled. At present, in the conventional propellant filling system of the rocket in the domestic aerospace launching site, the propellant filling amount calculated by the rocket data elements is measured by adopting a method of combining the liquid level of a rocket storage tank and a flowmeter of the launching site surface filling system. The propellant charge consists of a base charge (I, II level) and a supplemental charge. Wherein the vast majority of the filling amount (i.e. the basic filling amount) is determined by the liquid level scale on the arrow, the liquid level of I, II on the arrow is a standard value with high precision, and the filling amount of the part is accurate. The supplement amount is obtained by the measurement of the ground flowmeter, and the precision of the supplement amount is limited by the measurement precision of the ground flowmeter.
The precise metering of the amount of filling is a key factor in ensuring the successful launch of the rocket. Both excessive and insufficient injection can cause the Rocket dynamics Model parameters to change, thereby affecting the Control performance and precision thereof, and in severe cases, the engine shutdown condition can not be satisfied, thereby causing the failure of launching (Xiao YH, Zhang P, Liu WD. filling adaptation analysis of the Rocket project Based on the Flowmeter Measuring Model [ C ].12th International Conference on information in Control, Automation and Robotics, Colmar, France, July21-23,2015, Xie FS, Li Y, Way. Performance on winding system of systematic of marketing [ J ]. Asia-Pacific joint engineering,2017,12(6): 1011). Therefore, the metering accuracy of the filling system flow meter must be ensured. In order to ensure the metering precision, each launching site regularly calibrates the K coefficient of the flow meter used during the filling, and the calibration methods are different, and respectively adopt on-line calibration tank calibration (calibration by the calibration tank of the launching site surface filling system), on-line propellant storage tank calibration (calibration by the propellant storage tank of the launching site surface filling system) or external standard (the flow meter is disassembled and sent to a unit with calibrated qualification in China for calibration), and the like (Suzhou hua, Liang Wei, Shengjia, flow metering and testing [ M ]. Beijing: China metering and publishing Co., 2007.).
The three methods all belong to volumetric calibration, and each method has the advantages, but has certain defects. The system for calibrating the flowmeter by adopting the online calibration tank cannot calibrate the calibration tank per se at regular intervals, and the accuracy of the calibration tank per se after the calibration tank is used for many years is difficult to ensure; the system for calibrating the flowmeter by adopting the online propellant storage tank is characterized in that the storage tank is provided with a corresponding liquid level volume meter, and the liquid level volume meter is not accurate enough due to the fact that the storage tank is large in volume and the volume difference between continuous adjacent liquid levels is large. Although the defects of the two methods can be overcome by adopting an external standard method, the inner diameter of a system pipeline and the installation mode of the flowmeter of the system adopting the external standard flowmeter are different from those of a filling system, the medium in the external standard system is water, and the medium in the actual filling system is propellant, so that the flowmeter has larger system error in metering. Taking a certain space launching field filling system as an example, an external standard method is adopted for calibrating a flowmeter of the space launching field filling system. In recent years, when the filling system fills primary oxidant, the liquid level metering value of a flowmeter I and the theoretical value of the liquid level of a rocket storage tank I have large deviation for many times, so that a commander judges that the liquid level of the rocket primary storage tank I fails according to a preset scheme. The storehouse sends out the simulation I liquid level signal, but the storehouse receives the rocket storage tank I liquid level signal again soon. Although the phenomenon does not affect the filling precision of the actual liquid level I of the rocket propellant, the judgment of a commander is affected, so that a plan is adopted in the filling process, and adverse effects are caused. In addition, the rocket propellant supplement amount is measured by a flowmeter of a launching site filling system, and if the measurement accuracy of the flowmeter is not high, the supplement amount measurement is not accurate enough, so that the filling accuracy of the rocket propellant is influenced.
In conclusion, the existing calibration method for the flowmeter of the ground filling system has the defect of low calibration precision or instability. Therefore, the method for calibrating the flow meter of the launching ground filling system on line with high precision is provided. The method utilizes the high-precision rocket storage tank I liquid level value during filling to calibrate the ground flowmeter on line, and the filling and metering precision of the rocket propellant is expected to be further improved.
Disclosure of Invention
The invention aims to provide an on-line high-precision calibration method for a flowmeter of a launching site ground filling system. The method utilizes the high-precision rocket storage tank I liquid level value during filling to calibrate the ground flowmeter on line so as to further improve the filling and metering precision of the rocket propellant; the method solves the defects of low calibration precision or instability in the existing ground filling system flowmeter calibration method.
The invention provides an on-line high-precision calibration method for a flowmeter of a launching site ground filling system, which is used for calibrating the flowmeter of a launching site by adopting a rocket storage tank. The method calibrates the flowmeter through the liquid level I of the rocket storage tank on the basis of the initial K coefficient, and calculates to obtain the high-precision flowmeter coefficient, Kic
The method specifically comprises the following steps:
step one, filling rocket propellant, and obtaining accurate liquid volume Q according to rocket storage tank parameters when the liquid level of the propellant reaches special liquid levels (including but not limited to liquid level I, liquid level II, liquid level III and liquid level IV) of a first-stage or second-stage storage tank of the rocketiYjReading the metering data of the flowmeter to obtain the measurement volume Qiyj
Step two, correcting the K coefficient of the flowmeter to obtain the real coefficient K of the flowmeter during the i-time fillingiThe specific calculation process is as follows:
(1) firstly, i times of filling are respectively calculated, and the flow meter coefficient, K, calibrated according to the specific liquid levels of the first stage and the second stage of the rocket storage tanki1And Ki2The calculation formula is as follows:
Figure BDA0002401428880000021
in the formula: ki-1The coefficient of the last calibration of the flowmeter is the coefficient of an external standard when a new flowmeter is used for the first time; qiyjThe method comprises the following steps of measuring a primary specific liquid level metering value and a secondary specific liquid level metering value of a rocket oxidizer storage tank by a flow meter when the ith propellant is filled, wherein a subscript j value is 1 or 2, and the primary specific liquid level metering value or the secondary specific liquid level metering value indicates the primary specific liquid level or the secondary specific liquid level of the rocket oxidizer storage tank; qiYjFirst-stage and second-stage specific liquid of rocket oxidizer storage tank during ith propellant fillingTheoretical value β is the coefficient of volume expansion of the propellant in the filled state, (° c)-1(ii) a k is the compression coefficient of the propellant in the filling state, Pa-1;(θs)ij,(θm)ijThe temperature of the propellant at the first stage, the second stage and the flowmeter of the rocket oxidizer storage tank during the ith propellant filling is measured at DEG C; (p)s)ij,(pm)ijAnd (3) the pressure, Pa, of the propellant at the first stage, the second stage and the flowmeter of the rocket propellant storage tank during the ith propellant filling.
(2) And (3) the ith rocket propellant filling work, and the K coefficient of the flow meter is calculated according to the following formula:
Figure BDA0002401428880000031
step three, utilizing KiCalibration of flowmeter coefficients, KicThe calculation formula of (a) is as follows:
Figure BDA0002401428880000032
to obtain KicAnd the method is used for the i +1 st filling metering.
When the online calibration times of the flowmeter are less than 3 times (including), the average value of all K coefficient detection values is adopted; and when the online calibration times of the flowmeter are more than 3, adopting the average value of the K coefficient detection values of the last 3 times. The calibration method of the K coefficient of the flow meter of the combustion agent filling system is the same as that of the oxidant.
Use of flowmeter K-factor in rocket propellant filling: binding an external standard K coefficient or a coefficient calibrated by a check tank system when the flowmeter is newly purchased and used for the first time; when the flowmeter is used for the second time and later, the K coefficient obtained by the last calculation based on the formula (3) is bound.
The invention has the beneficial effects that:
the online calibration method for the flowmeter of the aerospace launching site filling system based on the liquid level of the rocket storage tank I is a high-precision flowmeter calibration method; the method is simple, convenient, efficient and reliable, and can be calibrated in time, thereby greatly reducing the deviation of the metering value of the flow meter, making up the deficiency of the flow meter calibration method of the domestic launching site filling system, and effectively improving the filling metering precision of the rocket propellant; and a calibration tank is not required to be installed, and the calibration precision is higher than that of an external standard method.
Drawings
FIG. 1 is a comparison of K coefficients obtained by an external standard method and an online calibration method proposed by the present invention;
FIG. 2 shows a comparison of the measured deviation values for two K-factors.
Detailed Description
The present invention is further illustrated by, but is not limited to, the following examples.
Example 1:
taking continuous 5 times of propellant filling work of a certain launching site filling system as an example, K for calibrating a flowmeter based on the I liquid level of a rocket primary storage tank and a rocket secondary storage tank on lineicThe coefficients are estimated, and the calculation formula is as follows.
(1) Firstly, i times of filling are respectively calculated, and the flow meter coefficient, K, calibrated according to the specific liquid levels of the first stage and the second stage of the rocket storage tanki1And Ki2The calculation formula is as follows:
Figure BDA0002401428880000041
in the formula: ki-1The coefficient of the last calibration of the flowmeter is the coefficient of an external standard when a new flowmeter is used for the first time; qiyjThe method comprises the following steps of measuring a primary specific liquid level metering value and a secondary specific liquid level metering value of a rocket oxidizer storage tank by a flow meter when the ith propellant is filled, wherein a subscript j value is 1 or 2, and the primary specific liquid level metering value or the secondary specific liquid level metering value indicates the primary specific liquid level or the secondary specific liquid level of the rocket oxidizer storage tank; qiYjThe theoretical values of the primary and secondary specific liquid levels of the rocket oxidizer storage tank during the ith propellant filling are β is the coefficient of volume expansion of the propellant in the filling state (DEG C)-1(ii) a k is the compression coefficient of the propellant in the filling state, Pa-1;(θs)ij,(θm)ijThe temperature of the propellant at the first stage, the second stage and the flowmeter of the rocket oxidizer storage tank during the ith propellant filling is measured at DEG C; (p)s)ij,(pm)ijAnd (3) the pressure, Pa, of the propellant at the first stage, the second stage and the flowmeter of the rocket propellant storage tank during the ith propellant filling.
(2) And (3) the ith rocket propellant filling work, and the K coefficient of the flow meter is calculated according to the following formula:
Figure BDA0002401428880000042
step three, utilizing KiCalibration of the flowmeter, KicThe calculation formula of (a) is as follows:
Figure BDA0002401428880000043
obtaining the flow meter coefficient K of the calibration after the five times of fillingic
In fig. 1, the abscissa is the number of times of filling, and the ordinate is the value of K coefficient; the ZX _ K curve represents the calibration coefficient K of the flow meter based on the liquid level of the rocket storage tank IicThe WB _ K curve represents the external standard coefficient K0. As can be seen from the figure, the online calibration coefficient is gradually increased, the change rate at the beginning is larger, the online calibration coefficient tends to be more stable after the online calibration coefficient is larger, and the online calibration coefficient is basically consistent with the change rule of the metering deviation of the flowmeter under the external standard K coefficient.
In order to verify the effect of the online calibration method of the flow meter based on the liquid level of the rocket storage tank I, taking 5 times of filling work as an example, taking the K coefficient obtained by the online calibration method of the flow meter based on the liquid level of the rocket storage tank I as a reference, calculating to obtain a deviation value between the I liquid level metering value of the flow meter under the K coefficient and the theoretical value of the liquid level of the storage tank I, and comparing the deviation value with the deviation value based on the external standard K coefficient, as shown in FIG. 2.
In FIG. 2, the abscissa is the number of times of filling and the ordinate is the deviation of the I level gauge from the theoretical value. The ZX _ K histogram represents the flow meter deviation based on rocket tank I liquid level, and the WB _ K histogram represents the external standard coefficient metering deviation. As can be seen from the figure, the online calibration method provided by the invention can effectively reduce the propellant metering deviation, and compared with the metering deviation based on an external standard coefficient, the deviation value is reduced by about 70% on average.

Claims (7)

1. An online high-precision calibration method for a flowmeter of a launching site ground filling system is characterized by comprising the following steps:
step one, filling rocket propellant, and obtaining accurate liquid volume Q according to rocket storage tank parameters when the liquid level of the propellant reaches the special liquid level of the rocket storage tankiYjReading the metering data of the flowmeter to obtain the measurement volume Qiyj
The special liquid level comprises a liquid level I, a liquid level II, a liquid level III or a liquid level IV;
step two, correcting the K coefficient of the flowmeter to obtain the real coefficient K of the flowmeter during the i-time fillingi
Step three, utilizing KiCalibration of the flowmeter, KicThe calculation formula of (a) is as follows:
Figure FDA0002401428870000011
to obtain KicAnd the method is used for the i +1 st filling metering.
2. The online high-precision calibration method for the flowmeter of the ground filling system of the launching site according to claim 1, characterized in that the specific process of the second step is as follows:
(1) firstly, i times of filling are respectively calculated, and the flow meter coefficient, K, calibrated according to the specific liquid levels of the first stage and the second stage of the rocket storage tanki1And Ki2The calculation formula is as follows:
Figure FDA0002401428870000012
in the formula: ki-1The coefficient of the last calibration of the flowmeter is the coefficient of an external standard when a new flowmeter is used for the first time; qiyjThe subscript j value is 1 or 2, and represents the first-stage or second-stage specific liquid level metering value of the rocket oxidizer storage tank measured by a flow meter during the ith propellant filling process;QiYjThe theoretical values of the primary and secondary specific liquid levels of the rocket oxidizer storage tank during the ith propellant filling are β is the coefficient of volume expansion of the propellant in the filling state (DEG C)-1(ii) a k is the compression coefficient of the propellant in the filling state, Pa-1;(θs)ij,(θm)ijThe temperature of the propellant at the first stage, the second stage and the flowmeter of the rocket oxidizer storage tank during the ith propellant filling is measured at DEG C; (p)s)ij,(pm)ijThe pressure of a propellant meter, Pa, at the first stage, the second stage and the flowmeter of a rocket propellant storage tank during the ith propellant filling;
(2) and (3) the ith rocket propellant filling work, and the K coefficient of the flow meter is calculated according to the following formula:
Figure FDA0002401428870000013
3. the method for calibrating the flow meter of the ground filling system of the launching field in an online high-precision manner according to claim 1, wherein the flow meter comprises an electromagnetic flow meter.
4. The method for on-line high-precision calibration of a flow meter of a launch site surface filling system according to claim 3, wherein the electromagnetic flow meter comprises a turbine flow meter or a vortex shedding flow meter.
5. The method for on-line high-precision calibration of a flow meter of a ground launching system at a launch site according to claim 1, wherein the rocket tank comprises a rocket primary or secondary tank.
6. The on-line high-precision calibration method for the flowmeter of the ground filling system of the launching field according to claim 1,
when the online calibration times of the flowmeter are 3 times or less than 3 times, the average value of all K coefficient detection values is adopted; and when the online calibration times of the flowmeter are more than 3, adopting the average value of the K coefficient detection values of the last 3 times.
7. The on-line high-precision calibration method for the flowmeter of the ground filling system of the launching field according to claim 1,
use of flowmeter K-factor in rocket propellant filling: binding an external standard K coefficient or a coefficient calibrated by a check tank system when the flowmeter is newly purchased and used for the first time; when the flowmeter is used for the second time and later, the K coefficient obtained by the last calculation based on the formula (3) is bound.
CN202010147967.8A 2020-03-05 2020-03-05 Online high-precision calibration method for flowmeter of launching site surface filling system Pending CN111256787A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113588047A (en) * 2021-08-04 2021-11-02 西安航天动力试验技术研究所 Flowmeter calibration system and method for low-temperature propellant rocket engine
CN114458477A (en) * 2020-12-14 2022-05-10 北京天兵科技有限公司 Low-fluctuation liquid level low-temperature online in-situ flow calibration method and system

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CN106338323A (en) * 2016-09-07 2017-01-18 武汉市度量衡管理所 Site calibration method and calibration system of flowmeter

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114458477A (en) * 2020-12-14 2022-05-10 北京天兵科技有限公司 Low-fluctuation liquid level low-temperature online in-situ flow calibration method and system
CN114458477B (en) * 2020-12-14 2023-08-22 北京天兵科技有限公司 Low-fluctuation liquid level and low-temperature on-line in-situ flow calibration method and system
CN113588047A (en) * 2021-08-04 2021-11-02 西安航天动力试验技术研究所 Flowmeter calibration system and method for low-temperature propellant rocket engine

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Application publication date: 20200609