CN106932164B - A Pneumatic Data Correction Method Based on Aerodynamic Derivative Identification Results - Google Patents

A Pneumatic Data Correction Method Based on Aerodynamic Derivative Identification Results 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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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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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

一种基于气动导数辨识结果的气动数据修正方法A Pneumatic Data Correction Method Based on Aerodynamic Derivative Identification Results

技术领域technical field

本发明涉及基于气动导数辨识结果的气动数据修正方法，属于飞行器总体设计领域。The invention relates to an aerodynamic data correction method based on aerodynamic derivative identification results, and belongs to the field of overall design of aircraft.

背景技术Background technique

气动辨识是利用飞行试验数据，获取飞行器气动特性的重要手段，是修正气动数据的重要依据。气动导数是气动辨识的核心成果之一，如何对飞行试验前的预示气动数据进行修正，是飞行器总体设计单位关心的核心问题之一。Aerodynamic identification is an important means to obtain the aerodynamic characteristics of an aircraft using flight test data, and an important basis for correcting aerodynamic data. Aerodynamic derivative is one of the core achievements of aerodynamic identification. How to correct the predicted aerodynamic data before the flight test is one of the core issues concerned by the overall design unit of the aircraft.

传统上，利用飞行试验获得的配平舵偏位置数据，与理论的配平舵偏位置相比较，如果存在差异，则认为气动力矩系数存在系统性偏差。修正方法为：将配平舵偏附近的两组气动力矩系数进行平移(保持斜率不变)，使得平移后的气动力矩系数所对应的配平舵偏与飞行试验结果一致。该方法正确的前提是，预示气动数据在配平状态附近的导数是准确的。当该前提不正确时，其结果也是错误的。Traditionally, the trim rudder offset position data obtained from the flight test are compared with the theoretical trim rudder offset position. If there is a difference, it is considered that there is a systematic deviation in the aerodynamic moment coefficient. The correction method is to translate the two sets of aerodynamic moment coefficients near the trim rudder offset (keeping the slope unchanged), so that the trim rudder offset corresponding to the translated aerodynamic moment coefficient is consistent with the flight test results. The premise of the correctness of this method is that the derivative of the predicted aerodynamic data around the trim state is accurate. When the premise is incorrect, the result is also false.

发明内容SUMMARY OF THE INVENTION

本发明的技术解决问题是：克服现有技术的不足，提供一种基于气动导数辨识结果的气动数据修正方法，不论预示气动数据在配平状态附近的导数是否准确，均能得到准确的气动数据。The technical solution of the present invention is to overcome the deficiencies of the prior art and provide an aerodynamic data correction method based on aerodynamic derivative identification results, which can obtain accurate aerodynamic data regardless of whether the derivative of the predicted aerodynamic data near the trim state is accurate.

本发明的技术解决方案是：一种基于气动导数辨识结果的气动数据修正方法，步骤如下：The technical solution of the present invention is: an aerodynamic data correction method based on aerodynamic derivative identification results, the steps are as follows:

步骤一：根据预示气动数据计算出气动导数；Step 1: Calculate the aerodynamic derivative according to the predicted aerodynamic data;

步骤二：建立气动数据修正方程如下：Step 2: Establish the aerodynamic data correction equation as follows:

其中，ΔCA、ΔCN、ΔCZ、ΔCmx、ΔCmy、ΔCmz为气动力六分量的修正量，ΔCA0、ΔCN0、ΔCZ0、ΔCmx0、ΔCmy0、ΔCmz0为气动力六分量零次项修正量， 为气动数据表中第i个变量气动导数的修正量，a1…an为气动数据表中的变量；Among them, ΔC A , ΔC N , ΔC Z , ΔC mx , ΔC my , and ΔC mz are the correction amounts of the six-component aerodynamic force, and ΔC A0 , ΔC N0 , ΔC Z0 , ΔC mx0 , ΔC my0 , and ΔC mz0 are the six-component aerodynamic force Zeroth order correction amount, is the correction amount of the aerodynamic derivative of the ith variable in the aerodynamic data table, a 1 ... an n is the variable in the aerodynamic data table;

步骤三：通过气动导数辨识获得的气动导数阶次，结合步骤一预示气动数据计算得到的气动导数，计算气动力六分量零次项修正量和气动数据表中第i个变量气动导数的修正量；Step 3: Calculate the aerodynamic derivative order obtained through aerodynamic derivative identification, combined with the aerodynamic derivative calculated from the predicted aerodynamic data in step 1, calculate the correction amount of the zero-order term of the six-component aerodynamic force and the correction amount of the aerodynamic derivative of the i-th variable in the aerodynamic data table ;

步骤四：根据气动数据表中所有变量和气动数据修正方程，计算出气动力六分量修正量，利用该修正量完成对应气动数据的修正。Step 4: According to all the variables in the aerodynamic data table and the aerodynamic data correction equation, calculate the six-component correction amount of the aerodynamic force, and use the correction amount to complete the correction of the corresponding aerodynamic data.

所述步骤三中气动力六分量零次项修正量的计算公式如下：The calculation formula of the correction amount of the aerodynamic six-component zero-order term in the step 3 is as follows:

为气动导数辨识获得的零次项气动导数，CA0、CN0、CZ0、Cmx0、Cmy0、Cmz0为预示气动数据计算出的零次项气动导数。 C A0 , C N0 , C Z0 , C mx0 , C my0 , C mz0 are the zero-order aerodynamic derivatives calculated from the predicted aerodynamic data.

所述步骤三中气动数据表中第i个变量气动导数修正量的计算方法如下：The calculation method of the i-th variable aerodynamic derivative correction amount in the aerodynamic data table in the step 3 is as follows:

判断通过气动导数辨识获得的气动导数阶次，当气动导数辨识获得的气动导数为m阶时，Determine the order of the aerodynamic derivative obtained by the aerodynamic derivative identification. When the aerodynamic derivative obtained by the aerodynamic derivative identification is of order m,

其中,为第i个变量通过气动导数辨识获得的一阶气动导数，为第i个变量通过气动导数辨识获得的j阶气动导数，为第i个变量根据预示气动数据计算出的气动导数。in, is the first-order aerodynamic derivative obtained by the aerodynamic derivative identification of the i-th variable, is the j-th order aerodynamic derivative obtained by the aerodynamic derivative identification of the ith variable, The aerodynamic derivative calculated from the predicted aerodynamic data for the ith variable.

本发明与现有技术相比有益效果为：Compared with the prior art, the present invention has the following beneficial effects:

本发明以预示气动数据导数为基准，充分利用气动辨识获得的气动导数对预示气动数据进行修正，该方法机理清楚，不依赖于假设条件，基础可靠，方法简便，可操作性强。The invention takes the predictive aerodynamic data derivative as a benchmark, and makes full use of the aerodynamic derivative obtained by aerodynamic identification to correct the predictive aerodynamic data.

附图说明Description of drawings

图1为传统修正方法示意图；Fig. 1 is a schematic diagram of a traditional correction method;

图2为气动力矩系数一阶修正方法示意图；Figure 2 is a schematic diagram of a first-order correction method for aerodynamic torque coefficient;

图3为气动力矩系数二阶修正方法示意图；Figure 3 is a schematic diagram of a second-order correction method for aerodynamic torque coefficient;

图4为本发明方法流程图。Figure 4 is a flow chart of the method of the present invention.

具体实施方式Detailed ways

如图4所示，本发明的步骤如下：As shown in Figure 4, the steps of the present invention are as follows:

一种基于气动导数辨识结果的气动数据修正方法，步骤如下：An aerodynamic data correction method based on aerodynamic derivative identification results, the steps are as follows:

步骤一：根据预示气动数据计算出气动导数。Step 1: Calculate the aerodynamic derivative based on the predicted aerodynamic data.

步骤二：建立气动数据修正方程如下：Step 2: Establish the aerodynamic data correction equation as follows:

其中，ΔCA、ΔCN、ΔCZ、ΔCmx、ΔCmy、ΔCmz为气动力六分量的修正量，ΔCA0、ΔCN0、ΔCZ0、ΔCmx0、ΔCmy0、ΔCmz0为气动力六分量零次项修正量， 为气动数据表中第i个变量气动导数的修正量，a1…an为气动数据表中的变量。气动数据表中的变量为气动力六分量。Among them, ΔC A , ΔC N , ΔC Z , ΔC mx , ΔC my , and ΔC mz are the correction amounts of the six-component aerodynamic force, and ΔC A0 , ΔC N0 , ΔC Z0 , ΔC mx0 , ΔC my0 , and ΔC mz0 are the six-component aerodynamic force Zeroth order correction amount, is the correction amount of the aerodynamic derivative of the ith variable in the aerodynamic data table, a 1 ... an n is the variable in the aerodynamic data table. The variable in the aerodynamic data sheet is the aerodynamic six-component.

步骤三：通过气动导数辨识获得的气动导数阶次，结合步骤一预示气动数据计算得到的气动导数，计算气动力六分量零次项修正量和气动数据表中第i个变量气动导数的修正量；Step 3: Calculate the aerodynamic derivative order obtained through aerodynamic derivative identification, combined with the aerodynamic derivative calculated from the predicted aerodynamic data in step 1, calculate the correction amount of the zero-order term of the six-component aerodynamic force and the correction amount of the aerodynamic derivative of the i-th variable in the aerodynamic data table ;

气动力六分量零次项修正量的计算公式如下：The formula for calculating the correction amount of the zero-order term of the six-component aerodynamic force is as follows:

为气动导数辨识获得的零次项气动导数，CA0、CN0、CZ0、Cmx0、Cmy0、Cmz0为预示气动数据计算出的零次项气动导数。 C A0 , C N0 , C Z0 , C mx0 , C my0 , C mz0 are the zero-order aerodynamic derivatives calculated from the predicted aerodynamic data.

气动数据表中第i个变量气动导数修正量的计算方法如下：The calculation method of the aerodynamic derivative correction of the i-th variable in the aerodynamic data table is as follows:

判断通过气动导数辨识获得的气动导数阶次，当气动导数辨识获得的气动导数为m阶时，Determine the order of the aerodynamic derivative obtained by the aerodynamic derivative identification. When the aerodynamic derivative obtained by the aerodynamic derivative identification is of order m,

其中,为第i个变量通过气动导数辨识获得的一阶气动导数，为第i个变量通过气动导数辨识获得的j阶气动导数，为第i个变量根据预示气动数据计算出的气动导数。in, is the first-order aerodynamic derivative obtained by the aerodynamic derivative identification of the i-th variable, is the j-th order aerodynamic derivative obtained by the aerodynamic derivative identification of the ith variable, The aerodynamic derivative calculated from the predicted aerodynamic data for the ith variable.

如当气动导数辨识获得的气动导数为一阶时， For example, when the aerodynamic derivative obtained by the aerodynamic derivative identification is first-order,

步骤四：根据气动数据表中所有变量和气动数据修正方程，计算出气动力六分量修正量，利用该修正量完成对应气动数据的修正。Step 4: According to all the variables in the aerodynamic data table and the aerodynamic data correction equation, calculate the six-component correction amount of the aerodynamic force, and use the correction amount to complete the correction of the corresponding aerodynamic data.

以俯仰气动力矩系数Cmz为例，本发明和传统修正方法的对比如下：Taking the pitching aerodynamic moment coefficient C mz as an example, the comparison between the present invention and the traditional correction method is as follows:

传统上，气动力矩系数修正方法如图1所示。假设俯仰力矩系数-5°和+5°舵偏对应的力矩系数分别为和预示配平舵偏为0°，通过线性差分计算得到气动导数为而飞行试验后获得配平舵偏为1.5°。在斜率不变假设基础上，将力矩系数平移得到修正后的力矩系数和 Traditionally, the aerodynamic torque coefficient correction method is shown in Figure 1. It is assumed that the moment coefficients corresponding to the pitch moment coefficients -5° and +5° rudder deflection are respectively and It indicates that the trim rudder deflection is 0°, and the aerodynamic derivative obtained by linear difference calculation is After the flight test, the trim rudder deflection was 1.5°. On the basis of the assumption of constant slope, the modified moment coefficient is obtained by translating the moment coefficient and

本发明利用气动导数辨识结果的修正方法原理如下：The present invention utilizes the principle of the correction method of the aerodynamic derivative identification result as follows:

若飞行试验后辨识结果表明，气动导数具有一阶特性，即获得了一阶气动导数和配平舵偏δz＝1.5°。如图2所示，为图2中灰色虚线的斜率，是气动导数辨识结果。为黑色虚线的斜率，是预示气动数据的气动导数。当时，则说明预示气动数据的导数存在偏差，需要对气动数据一阶修正。修正后的数据为修正后的数据为 If the identification results after the flight test show that the aerodynamic derivatives have first-order characteristics, the first-order aerodynamic derivatives are obtained. and trim rudder offset δ z = 1.5°. as shown in picture 2, is the slope of the gray dotted line in Fig. 2, which is the identification result of aerodynamic derivatives. The slope of the black dashed line is the aerodynamic derivative that predicts the aerodynamic data. when When , it indicates that there is a deviation in the derivative of the aerodynamic data, and a first-order correction of the aerodynamic data is required. The corrected data is The corrected data is

若飞行试验后可以获得配平位置的气动导数具有二阶特性，即获得了一阶气动导数和二阶气动导数则说明预示气动数据的导数存在偏差，需要对气动数据二阶修正，如图3所示。修正后的数据为 修正后的数据为 If the aerodynamic derivative of the trim position can be obtained after the flight test with second-order characteristics, that is, the first-order aerodynamic derivative is obtained. and the second aerodynamic derivative It means that there is a deviation in the derivative of the aerodynamic data, and a second-order correction of the aerodynamic data is required, as shown in Figure 3. The corrected data is The corrected data is

从上面的对比可以看出，传统方法完全依赖于预示气动数据在配平状态附近的导数，当预示气动数据在配平状态附近的导数存在偏差时，导致传统方法的修正数据不准确，本发明方法以预示气动数据导数为基准，充分利用气动辨识获得的气动导数对预示气动数据进行修正，无论预示气动数据在配平状态附近的导数是否存在偏差，均能够得到正确的气动数据。It can be seen from the above comparison that the traditional method completely relies on the derivative of the predicted aerodynamic data near the trim state. When there is a deviation in the derivative of the predicted aerodynamic data near the trim state, the correction data of the traditional method is inaccurate. The method of the present invention is based on The predicted aerodynamic data derivative is used as the benchmark, and the aerodynamic data obtained by the aerodynamic identification is fully utilized to correct the predicted aerodynamic data. Regardless of whether there is a deviation in the derivative of the predicted aerodynamic data near the trim state, the correct aerodynamic data can be obtained.

本发明说明书中未作详细描述的内容属本领域技术人员的公知技术。The content not described in detail in the specification of the present invention belongs to the well-known technology of those skilled 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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