CN106932164B - A kind of aerodynamic data modification method based on aerodynamic derivative identification result - Google Patents

A kind of aerodynamic data modification method based on aerodynamic derivative identification result Download PDF

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CN106932164B
CN106932164B CN201710083871.8A CN201710083871A CN106932164B CN 106932164 B CN106932164 B CN 106932164B CN 201710083871 A CN201710083871 A CN 201710083871A CN 106932164 B CN106932164 B CN 106932164B
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pneumatic
aerodynamic
derivative
data
correction
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CN106932164A (en
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张鹏宇
陈芳
王颖
程璞
肖振
王毓栋
闵昌万
陈敏
刘秀明
杨丁
秦小丽
张宁宁
吴小华
陈安宏
黄兴李
朱广生
阎君
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China Academy of Launch Vehicle Technology CALT
Beijing Institute of Near Space Vehicles System Engineering
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China Academy of Launch Vehicle Technology CALT
Beijing Institute of Near Space Vehicles System Engineering
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
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    • G06F17/11—Complex mathematical operations for solving equations, e.g. nonlinear equations, general mathematical optimization problems

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Abstract

A kind of aerodynamic data modification method based on aerodynamic derivative identification result, aerodynamic derivative is calculated according to indication aerodynamic data first, then aerodynamic data update equation is established, then the aerodynamic derivative order obtained by aerodynamic derivative identification, calculate the correction amount of i-th of variable aerodynamic derivative in six component zero degree item correction amount of aerodynamic force and pneumatic tables of data, finally according to variables all in aerodynamic data table and pneumatic data correction equation, six component correction amount of aerodynamic force is calculated, the amendment of corresponding aerodynamic data is completed using the correction amount.For the present invention on the basis of indicating aerodynamic data derivative, the aerodynamic derivative for making full use of Pneumatic Identification to obtain is modified indication aerodynamic data, no matter whether derivative of the indication aerodynamic data near trim condition be accurate, can obtain accurate aerodynamic data.

Description

Pneumatic data correction method based on pneumatic derivative identification result
Technical Field
The invention relates to a pneumatic data correction method based on a pneumatic derivative identification result, and belongs to the field of overall design of aircrafts.
Background
The pneumatic identification is an important means for acquiring the pneumatic characteristics of the aircraft by using flight test data, and is an important basis for correcting the pneumatic data. The aerodynamic derivative is one of the core achievements of aerodynamic identification, and how to correct the predictive aerodynamic data before the flight test is one of the core problems concerned by the overall design unit of the aircraft.
Conventionally, the offset position data of the trim rudder obtained by flight tests is compared with the offset position of the theoretical trim rudder, and if the offset exists, the aerodynamic moment coefficient is considered to have systematic offset. The correction method comprises the following steps: and translating the two groups of aerodynamic moment coefficients near the offset of the trim rudder (keeping the slope unchanged), so that the offset of the trim rudder corresponding to the translated aerodynamic moment coefficients is consistent with the flight test result. The method is correct on the premise that the derivative of the predictive aerodynamic data near the trim state is accurate. When the precondition is incorrect, the result is also erroneous.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the method overcomes the defects of the prior art, and provides a pneumatic data correction method based on the pneumatic derivative identification result, so that accurate pneumatic data can be obtained no matter whether the derivative of the pneumatic data near the trim state is accurate or not.
The technical solution of the invention is as follows: a pneumatic data correction method based on pneumatic derivative identification results comprises the following steps:
the method comprises the following steps: calculating a pneumatic derivative according to the predictive pneumatic data;
step two: the pneumatic data correction equation is established as follows:
wherein, isA、ΔCN、ΔCZ、ΔCmx、ΔCmy、ΔCmzAs a correction of six components of aerodynamic force, Δ CA0、ΔCN0、ΔCZ0、ΔCmx0、ΔCmy0、ΔCmz0Is a zero-order correction quantity of six components of aerodynamic force, correction of the pneumatic derivative of the ith variable, a, in a pneumatic data sheet1…anAre variables in the pneumatic data table;
step three: calculating the correction quantity of the sixth-component zero-order term of the aerodynamic force and the correction quantity of the pneumatic derivative of the ith variable in the pneumatic data table by combining the pneumatic derivative order obtained by identifying the pneumatic derivative and the pneumatic derivative obtained by calculating the predictive pneumatic data in the first step;
step four: and calculating six-component aerodynamic correction according to all variables in the aerodynamic data table and the aerodynamic data correction equation, and finishing the correction of corresponding aerodynamic data by using the correction.
The calculation formula of the aerodynamic six-component zero-order term correction in the step three is as follows:
pneumatic derivative of the zero order, C, obtained for pneumatic derivative identificationA0、CN0、CZ0、Cmx0、Cmy0、Cmz0The zero-order pneumatic derivative calculated for the predictive pneumatic data.
The method for calculating the pneumatic derivative correction quantity of the ith variable in the pneumatic data table in the third step is as follows:
judging the pneumatic derivative order obtained by pneumatic derivative identification, when the pneumatic derivative obtained by pneumatic derivative identification is m order,
wherein,the first pneumatic derivative obtained by pneumatic derivative identification for the ith variable,the j-order pneumatic derivative obtained by pneumatic derivative identification for the ith variable,the aerodynamic derivative calculated from the predictive aerodynamic data for the ith variable.
Compared with the prior art, the invention has the beneficial effects that:
the method takes the derivative of the predicted pneumatic data as the reference, and fully utilizes the pneumatic derivative obtained by pneumatic identification to correct the predicted pneumatic data.
Drawings
FIG. 1 is a schematic diagram of a conventional correction method;
FIG. 2 is a schematic diagram of a first-order correction method for aerodynamic moment coefficients;
FIG. 3 is a schematic diagram of a second-order aerodynamic moment coefficient correction method;
FIG. 4 is a flow chart of the method of the present invention.
Detailed Description
As shown in fig. 4, the steps of the present invention are as follows:
a pneumatic data correction method based on pneumatic derivative identification results comprises the following steps:
the method comprises the following steps: and calculating a pneumatic derivative according to the predictive pneumatic data.
Step two: the pneumatic data correction equation is established as follows:
wherein, isA、ΔCN、ΔCZ、ΔCmx、ΔCmy、ΔCmzAs a correction of six components of aerodynamic force, Δ CA0、ΔCN0、ΔCZ0、ΔCmx0、ΔCmy0、ΔCmz0Is a zero-order correction quantity of six components of aerodynamic force, correction of the pneumatic derivative of the ith variable, a, in a pneumatic data sheet1…anAre variables in the pneumatic data sheet. The variables in the aerodynamic data table are six components of aerodynamic force.
Step three: calculating the correction quantity of the sixth-component zero-order term of the aerodynamic force and the correction quantity of the pneumatic derivative of the ith variable in the pneumatic data table by combining the pneumatic derivative order obtained by identifying the pneumatic derivative and the pneumatic derivative obtained by calculating the predictive pneumatic data in the first step;
the calculation formula of the aerodynamic six-component zero-order term correction is as follows:
pneumatic derivative of the zero order, C, obtained for pneumatic derivative identificationA0、CN0、CZ0、Cmx0、Cmy0、Cmz0The zero-order pneumatic derivative calculated for the predictive pneumatic data.
The method for calculating the pneumatic derivative correction quantity of the ith variable in the pneumatic data table is as follows:
judging the pneumatic derivative order obtained by pneumatic derivative identification, when the pneumatic derivative obtained by pneumatic derivative identification is m order,
wherein,the first pneumatic derivative obtained by pneumatic derivative identification for the ith variable,the j-order pneumatic derivative obtained by pneumatic derivative identification for the ith variable,the aerodynamic derivative calculated from the predictive aerodynamic data for the ith variable.
Such as when the pneumatic derivative is first order as obtained by pneumatic derivative identification,
step four: and calculating six-component aerodynamic correction according to all variables in the aerodynamic data table and the aerodynamic data correction equation, and finishing the correction of corresponding aerodynamic data by using the correction.
By the coefficient of pitching aerodynamic moment CmzFor example, the comparison between the present invention and the conventional correction method is as follows:
conventionally, an aerodynamic moment coefficient correction method is shown in fig. 1. The moment coefficients corresponding to-5 degrees and +5 degrees of rudder deflection of the pitching moment coefficient are respectively assumed to beAndthe deviation of the trim rudder is predicted to be 0 degrees, and the pneumatic derivative is obtained through linear difference calculationTo flyAfter the test, a trim rudder deflection of 1.5 ° was obtained. On the basis of the assumption that the slope is not changed, the moment coefficient is translated to obtain a corrected moment coefficientAnd
the principle of the correction method using the identification result of the pneumatic derivative is as follows:
if the identification result after the flight test shows that the pneumatic derivative has the first-order characteristic, namely the first-order pneumatic derivative is obtainedAnd trim rudder offset deltaz1.5 degrees. As shown in figure 2 of the drawings, in which,the slope of the gray dashed line in fig. 2 is the pneumatic derivative identification result.The slope of the black dashed line is the pneumatic derivative of the predictive pneumatic data. When in useAnd if so, indicating that the derivative of the pneumatic data has deviation and needing first-order correction on the pneumatic data.The corrected data areThe corrected data are
If the aerodynamic derivative of the trim position obtained after the flight test has the second orderCharacteristic, i.e. obtaining the first aerodynamic derivativeAnd second aerodynamic derivativeThis indicates that a deviation in the derivative of the predicted aerodynamic data is present and a second order correction to the aerodynamic data is required, as shown in figure 3.The corrected data are The corrected data are
The method takes the derivative of the predicted pneumatic data as a reference, and fully utilizes the pneumatic derivative obtained by pneumatic identification to correct the predicted pneumatic data, so that correct pneumatic data can be obtained no matter whether the derivative of the predicted pneumatic data in the vicinity of the trim state has the deviation or not.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.

Claims (3)

1. A pneumatic data correction method based on pneumatic derivative identification results is characterized by comprising the following steps:
the method comprises the following steps: calculating a pneumatic derivative according to the predictive pneumatic data;
step two: the pneumatic data correction equation is established as follows:
wherein, isA、ΔCN、ΔCZ、ΔCmx、ΔCmy、ΔCmzAs a correction of six components of aerodynamic force, Δ CA0、ΔCN0、ΔCZ0、ΔCmx0、ΔCmy0、ΔCmz0Is a zero-order correction quantity of six components of aerodynamic force, correction of the pneumatic derivative of the ith variable, a, in a pneumatic data sheet1…anAre variables in the pneumatic data table;
step three: calculating the correction quantity of the sixth-component zero-order term of the aerodynamic force and the correction quantity of the pneumatic derivative of the ith variable in the pneumatic data table by combining the pneumatic derivative order obtained by identifying the pneumatic derivative and the pneumatic derivative obtained by calculating the predictive pneumatic data in the first step;
step four: and calculating six-component aerodynamic correction according to all variables in the aerodynamic data table and the aerodynamic data correction equation, and finishing the correction of corresponding aerodynamic data by using the correction.
2. The pneumatic data correction method based on pneumatic derivative identification result of claim 1, wherein: the calculation formula of the aerodynamic six-component zero-order term correction in the step three is as follows:
pneumatic derivative of the zero order, C, obtained for pneumatic derivative identificationA0、CN0、CZ0、Cmx0、Cmy0、Cmz0The zero-order pneumatic derivative calculated for the predictive pneumatic data.
3. The pneumatic data correction method based on pneumatic derivative identification result of claim 1, wherein: the method for calculating the pneumatic derivative correction quantity of the ith variable in the pneumatic data table in the third step is as follows:
judging the pneumatic derivative order obtained by pneumatic derivative identification, when the pneumatic derivative obtained by pneumatic derivative identification is m order,
wherein,the first pneumatic derivative obtained by pneumatic derivative identification for the ith variable,the j-order pneumatic derivative obtained by pneumatic derivative identification for the ith variable,the aerodynamic derivative calculated from the predictive aerodynamic data for the ith variable.
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Publication number Priority date Publication date Assignee Title
CN112393876B (en) * 2019-08-16 2022-04-12 北京空天技术研究所 Dynamic pneumatic derivative prediction method suitable for internal and external flow integrated appearance
CN114608786B (en) * 2022-05-11 2022-07-29 中国空气动力研究与发展中心设备设计与测试技术研究所 Aircraft dynamic derivative test data processing method

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1253495A2 (en) * 2001-04-26 2002-10-30 General Electric Company Method and system for assessing adjustment factors in testing or monitoring process
JP2005250599A (en) * 2004-03-01 2005-09-15 Fuji Heavy Ind Ltd Flow analyzing device and method using virtual boundary method
CN105258916A (en) * 2015-11-18 2016-01-20 中国空气动力研究与发展中心高速空气动力研究所 Method for correcting influence of high-speed wind tunnel model afterbody distortion on lateral-directional aerodynamic characteristics
CN105628333A (en) * 2014-10-29 2016-06-01 北京临近空间飞行器系统工程研究所 Method for determining pneumatic error on the condition of high altitude and high Mach number
CN106407601A (en) * 2016-10-18 2017-02-15 中国运载火箭技术研究院 Aerodynamic characteristic data processing method based on data mining technology

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8099265B2 (en) * 2007-12-31 2012-01-17 Exocortex Technologies, Inc. Fast characterization of fluid dynamics
FR2942038B1 (en) * 2009-02-09 2012-06-08 Airbus France METHOD FOR DETERMINING A RIGID VALUE OF AERODYNAMIC COEFFICIENT
US10520389B2 (en) * 2013-11-27 2019-12-31 United States Of America As Represented By The Administrator Of Nasa Aerodynamic modeling using flight data

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1253495A2 (en) * 2001-04-26 2002-10-30 General Electric Company Method and system for assessing adjustment factors in testing or monitoring process
JP2005250599A (en) * 2004-03-01 2005-09-15 Fuji Heavy Ind Ltd Flow analyzing device and method using virtual boundary method
CN105628333A (en) * 2014-10-29 2016-06-01 北京临近空间飞行器系统工程研究所 Method for determining pneumatic error on the condition of high altitude and high Mach number
CN105258916A (en) * 2015-11-18 2016-01-20 中国空气动力研究与发展中心高速空气动力研究所 Method for correcting influence of high-speed wind tunnel model afterbody distortion on lateral-directional aerodynamic characteristics
CN106407601A (en) * 2016-10-18 2017-02-15 中国运载火箭技术研究院 Aerodynamic characteristic data processing method based on data mining technology

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
一种无人机气动参数辨识的实现方法;李寒冰 等;《飞行力学》;20140430;第32卷(第2期);第183-188页
用于气动导数辨识的试飞数据处理方法研究;刘超 等;《航空工程进展》;20140531;第5卷(第2期);第187-198页
飞行器气动参数估计不确定度评价方法研究;王贵东 等;《航空学报》;20130925;第34卷(第9期);第2057-2063页

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