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 PDFInfo
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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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- 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
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- 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
- G06F17/10—Complex mathematical operations
- G06F17/11—Complex mathematical operations for solving equations, e.g. nonlinear equations, general mathematical optimization problems
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
Technical field
The present invention relates to the aerodynamic data modification methods based on aerodynamic derivative identification result, belong to Aircraft Conceptual Design neck
Domain.
Background technique
Pneumatic Identification is to obtain the important means of aerodynamic characteristics of vehicle using test flight data, is the pneumatic number of amendment
According to important evidence.Aerodynamic derivative is one of core achievement of Pneumatic Identification, how to the indication aerodynamic data before flight test
It is modified, is one of the key problem that Aircraft Conceptual Design unit is concerned about.
Traditionally, the inclined position data of tromming tab obtained using flight test, set with theoretical tromming tab deviation compared with,
If there is difference, then it is assumed that there are systematic bias for aerodynamic moment coefficient.Modification method are as follows: by tromming tab partially near two groups
Aerodynamic moment coefficient is translated (keep slope constant) so that tromming tab corresponding to the aerodynamic moment coefficient after translation partially with
Flight test result is consistent.This method correctly on condition that, indicate that derivative of the aerodynamic data near trim condition is accurate.
When the premise is incorrect, result is also mistake.
Summary of the invention
Technology of the invention solves the problems, such as: overcoming the deficiencies of the prior art and provide a kind of based on aerodynamic derivative identification knot
The aerodynamic data modification method of fruit can obtain standard no matter whether derivative of the indication aerodynamic data near trim condition be accurate
True aerodynamic data.
The technical solution of the invention is as follows: a kind of aerodynamic data modification method based on aerodynamic derivative identification result, step
It is rapid as follows:
Step 1: aerodynamic derivative is calculated according to indication aerodynamic data；
Step 2: it is as follows to establish aerodynamic data update equation:
Wherein, Δ CA、ΔCN、ΔCZ、ΔCmx、ΔCmy、ΔCmzFor the correction amount of six component of aerodynamic force, Δ CA0、ΔCN0、
ΔCZ0、ΔCmx0、ΔCmy0、ΔCmz0For six component zero degree item correction amount of aerodynamic force, For the correction amount of i-th of variable aerodynamic derivative in aerodynamic data table, a1…anIt is pneumatic
Variable in tables of data；
Step 3: the aerodynamic derivative order obtained by aerodynamic derivative identification is calculated in conjunction with step 1 indication aerodynamic data
Obtained aerodynamic derivative calculates in six component zero degree item correction amount of aerodynamic force and pneumatic tables of data i-th of variable aerodynamic derivative
Correction amount；
Step 4: according to variables all in aerodynamic data table and pneumatic data correction equation, six component of aerodynamic force is calculated
Correction amount completes the amendment of corresponding aerodynamic data using the correction amount.
The calculation formula of six component zero degree item correction amount of aerodynamic force is as follows in the step 3:
The zero degree item aerodynamic derivative obtained is recognized for aerodynamic derivative,
CA0、CN0、CZ0、Cmx0、Cmy0、Cmz0To indicate the calculated zero degree item aerodynamic derivative of aerodynamic data.
The calculation method of i-th of variable aerodynamic derivative correction amount is as follows in aerodynamic data table in the step 3:
The aerodynamic derivative order that judgement is obtained by aerodynamic derivative identification, when the aerodynamic derivative that aerodynamic derivative identification obtains is
When m rank,
Wherein,It is obtained for i-th of variable by aerodynamic derivative identification
Single order aerodynamic derivative,It is recognized and is obtained by aerodynamic derivative for i-th of variable
J rank aerodynamic derivative,It is calculated for i-th of variable according to indication aerodynamic data
Aerodynamic derivative.
The present invention has the beneficial effect that compared with prior art
The present invention is on the basis of indicating aerodynamic data derivative, and the aerodynamic derivative for making full use of Pneumatic Identification to obtain is to indication gas
Dynamic data are modified, and this method mechanism understands, independent of assumed condition, basis is reliable, and method is easy, strong operability.
Detailed description of the invention
Fig. 1 is traditional modification method schematic diagram；
Fig. 2 is aerodynamic moment coefficient single order modification method schematic diagram；
Fig. 3 is aerodynamic moment coefficient second order modification method schematic diagram；
Fig. 4 is the method for the present invention flow chart.
Specific embodiment
As shown in figure 4, step of the invention is as follows:
A kind of aerodynamic data modification method based on aerodynamic derivative identification result, steps are as follows:
Step 1: aerodynamic derivative is calculated according to indication aerodynamic data.
Step 2: it is as follows to establish aerodynamic data update equation:
Wherein, Δ CA、ΔCN、ΔCZ、ΔCmx、ΔCmy、ΔCmzFor the correction amount of six component of aerodynamic force, Δ CA0、ΔCN0、
ΔCZ0、ΔCmx0、ΔCmy0、ΔCmz0For six component zero degree item correction amount of aerodynamic force, For the correction amount of i-th of variable aerodynamic derivative in aerodynamic data table, a1…anIt is pneumatic
Variable in tables of data.Variable in aerodynamic data table is six component of aerodynamic force.
Step 3: the aerodynamic derivative order obtained by aerodynamic derivative identification is calculated in conjunction with step 1 indication aerodynamic data
Obtained aerodynamic derivative calculates in six component zero degree item correction amount of aerodynamic force and pneumatic tables of data i-th of variable aerodynamic derivative
Correction amount；
The calculation formula of six component zero degree item correction amount of aerodynamic force is as follows:
The zero degree item aerodynamic derivative obtained is recognized for aerodynamic derivative,
CA0、CN0、CZ0、Cmx0、Cmy0、Cmz0To indicate the calculated zero degree item aerodynamic derivative of aerodynamic data.
The calculation method of i-th of variable aerodynamic derivative correction amount is as follows in aerodynamic data table:
The aerodynamic derivative order that judgement is obtained by aerodynamic derivative identification, when the aerodynamic derivative that aerodynamic derivative identification obtains is
When m rank,
Wherein,It is obtained for i-th of variable by aerodynamic derivative identification
Single order aerodynamic derivative,It is recognized and is obtained by aerodynamic derivative for i-th of variable
J rank aerodynamic derivative,It is calculated for i-th of variable according to indication aerodynamic data
Aerodynamic derivative.
Such as when the aerodynamic derivative that aerodynamic derivative identification obtains is single order,
Step 4: according to variables all in aerodynamic data table and pneumatic data correction equation, six component of aerodynamic force is calculated
Correction amount completes the amendment of corresponding aerodynamic data using the correction amount.
With pitching aerodynamic moment coefficient CmzFor, the comparison of the present invention and traditional modification method is as follows:
Traditionally, aerodynamic moment coefficient modification method is as shown in Figure 1.Assuming that -5 ° of pitching moment coefficient and+5 ° of rudders are partially corresponding
Torque coefficient be respectivelyWithIndicate that tromming tab is 0 ° partially, is calculated by linear differential and is pneumatically led
Number isAnd it is 1.5 ° that tromming tab is obtained after flight test partially.On the basis of slope constant hypothesis, by torque coefficient
Translation obtains revised torque coefficientWith
The present invention is as follows using the modification method principle of aerodynamic derivative identification result:
If identification result shows that aerodynamic derivative has first-order characteristics after flight test, that is, obtain single order aerodynamic derivativeWith the inclined δ of tromming tabz=1.5 °.As shown in Fig. 2,It is that aerodynamic derivative is distinguished for the slope of dash-dotted gray line in Fig. 2
Know result.It is the aerodynamic derivative for indicating aerodynamic data for the slope of black dotted lines.WhenWhen, then illustrate the derivative for indicating aerodynamic data there are deviation, needs to correct aerodynamic data single order.Revised data areRevised data are
If the aerodynamic derivative that can obtain trim position after flight test has second-order characteristics, that is, obtains single order and pneumatically lead
NumberWith second order aerodynamic derivativeThen illustrate the derivative for indicating aerodynamic data there are deviation, needs to pneumatic number
It is corrected according to second order, as shown in Figure 3.Revised data are Revised data are
From comparison above as can be seen that conventional method places one's entire reliance upon and indicates aerodynamic data leading near trim condition
Number, when derivative of the indication aerodynamic data near trim condition is there are the amendment data inaccuracy for when deviation, leading to conventional method,
The method of the present invention is on the basis of indicating aerodynamic data derivative, and the aerodynamic derivative for making full use of Pneumatic Identification to obtain is to the pneumatic number of indication
According to being modified, no matter indicate that derivative of the aerodynamic data near trim condition with the presence or absence of deviation, can obtain correctly
Aerodynamic data.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (3)
1. a kind of aerodynamic data modification method based on aerodynamic derivative identification result, it is characterised in that steps are as follows:
Step 1: aerodynamic derivative is calculated according to indication aerodynamic data；
Step 2: it is as follows to establish aerodynamic data update equation:
Wherein, Δ CA、ΔCN、ΔCZ、ΔCmx、ΔCmy、ΔCmzFor the correction amount of six component of aerodynamic force, Δ CA0、ΔCN0、ΔCZ0、
ΔCmx0、ΔCmy0、ΔCmz0For six component zero degree item correction amount of aerodynamic force, For the correction amount of i-th of variable aerodynamic derivative in aerodynamic data table, a1…anIt is pneumatic
Variable in tables of data；
Step 3: the aerodynamic derivative order obtained by aerodynamic derivative identification is calculated in conjunction with step 1 indication aerodynamic data
Aerodynamic derivative, calculate the amendment of i-th of variable aerodynamic derivative in six component zero degree item correction amount of aerodynamic force and pneumatic tables of data
Amount；
Step 4: according to variables all in aerodynamic data table and pneumatic data correction equation, the amendment of six component of aerodynamic force is calculated
Amount completes the amendment of corresponding aerodynamic data using the correction amount.
2. a kind of aerodynamic data modification method based on aerodynamic derivative identification result according to claim 1, feature exist
In: the calculation formula of six component zero degree item correction amount of aerodynamic force is as follows in the step 3:
For the zero degree item aerodynamic derivative that aerodynamic derivative identification obtains, CA0、
CN0、CZ0、Cmx0、Cmy0、Cmz0To indicate the calculated zero degree item aerodynamic derivative of aerodynamic data.
3. a kind of aerodynamic data modification method based on aerodynamic derivative identification result according to claim 1, feature exist
In: the calculation method of i-th of variable aerodynamic derivative correction amount is as follows in aerodynamic data table in the step 3:
The aerodynamic derivative order that judgement is obtained by aerodynamic derivative identification, when the aerodynamic derivative that aerodynamic derivative identification obtains is m rank
When,
Wherein,The single order obtained for i-th of variable by aerodynamic derivative identification
Aerodynamic derivative,The j rank obtained for i-th of variable by aerodynamic derivative identification
Aerodynamic derivative,It is i-th of variable according to the indication calculated gas of aerodynamic data
Dynamic derivative.
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| 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 |
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