CN115114864A - CFD-based aircraft full-envelope pneumatic database generation method - Google Patents
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Abstract
The invention discloses a CFD-based aircraft full-envelope pneumatic database generation method, which is characterized in that negative expansion of an attack angle sideslip angle is carried out by utilizing a control surface combination mode correspondence and symbol transformation method; the invention is mainly used for data expansion by adopting the principles of data correspondence of different states and symbol transformation, has less data iteration and mutual operation process, brings small rounding error and is not easy to make mistakes.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a CFD-based aircraft full-envelope pneumatic database generation method.
Background
The CFD (computational Fluid dynamics) simulation technology is widely applied to the field of aerospace, and has the advantages of low cost, high efficiency, good repeatability and stability, capability of simulating limit conditions and the like compared with model tests. When the aircraft design research is carried out, considering the complexity of the flight state, a large number of flight states are generally calculated by using a CFD simulation technology, and an aircraft pneumatic database is established to provide technical support for the aircraft design. Due to the symmetry of the aircraft, a full envelope pneumatic database can be generated according to the expansion of partial pneumatic data.
At present, patent CN 112214834a discloses a method for establishing an axisymmetric aircraft aerodynamic database, which is applicable to the shape of an axisymmetric body of a reentry module, and performs rotation around the body by different angles according to a total attack angle and original aerodynamic data of a calculated sample, and solves the attack angle, the sideslip angle and corresponding aerodynamic data by using a triangle and an inverse trigonometric function according to a projection principle, thereby achieving the purpose of data expansion.
Disclosure of Invention
The invention aims to provide a method for generating a full-envelope pneumatic database on the basis of the prior art, which mainly utilizes a control surface combination mode correspondence and sign conversion method to carry out negative expansion of an attack angle sideslip angle, and ensures the accuracy of a result because positive and negative rudder and positive and negative pneumatic data are self-defined and kept consistent.
In order to realize the purpose, the invention adopts the following technical scheme:
a CFD-based aircraft full-envelope pneumatic database generation method comprises the following steps:
s1, acquiring original pneumatic data of CFD simulation calculation;
s2: expanding the original pneumatic data into pneumatic data under a negative attack angle positive sideslip state, pneumatic data under a positive attack angle negative sideslip state and pneumatic data under a negative attack angle negative sideslip state respectively;
s3: calculating lift and resistance of all states before and after expansion;
s4: and merging all the pneumatic data before and after expansion, performing custom sorting after merging, and outputting the merged pneumatic data into a full-envelope pneumatic database according to a format.
In the above technical solution, the process of S1 includes the following steps:
s11: identifying all data line numbers in the original pneumatic data;
s12: detecting whether the original pneumatic data has data loss or not;
s13: if the original pneumatic data has data missing, recording the state position of the missing pneumatic data;
s14: and automatically identifying the rudder deflection state in the original pneumatic data, and storing the original pneumatic data according to different rudder deflection states.
In the above technical solution, the original aerodynamic data is expanded into aerodynamic data in a negative attack angle and a positive sideslip state, and the expansion formula is:
| variable names | Target state | Extended formula |
| Coefficient of axial force C xt | Negative angle of attack positive sideslip | Cxt -α+β (d(x)d(y)d(z))= Cxt +α+β (d(-x)d(y)d(-z)) |
| Coefficient of normal force C yt | Negative angle of attack positive sideslip | Cyt -α+β (d(x)d(y)d(z))= -Cyt +α+β (d(-x)d(y)d(-z)) |
| Coefficient of lateral force C zt | Negative angle of attack positive sideslip | Czt -α+β (d(x)d(y)d(z))= Czt +α+β (d(-x)d(y)d(-z)) |
| Roll moment coefficient M x | Negative angle of attack positive sideslip | Mx -α+β (d(x)d(y)d(z))= -Mx +α+β (d(-x)d(y)d(-z)) |
| Yaw moment coefficient M y | Negative angle of attack positive sideslip | My -α+β (d(x)d(y)d(z))= My +α+β (d(-x)d(y)d(-z)) |
| Coefficient of pitching moment M z | Negative angle of attack positive sideslip | Mz -α+β (d(x)d(y)d(z))= -Mz +α+β (d(-x)d(y)d(-z)) |
In the above technical solution, the original aerodynamic data is expanded into aerodynamic data in a positive attack angle negative side slip state, and the expansion formula is:
| variable names | Target state | Extended formula |
| Coefficient of axial force C xt | Positive angle of attack negative sideslip | Cxt +α-β (d(x)d(y)d(z))= Cxt +α+β (d(-x)d(-y)d(z)) |
| Coefficient of normal force C yt | Positive angle of attack negative sideslip | Cyt +α-β (d(x)d(y)d(z))= Cyt +α+β (d(-x)d(-y)d(z)) |
| Coefficient of lateral force C zt | Positive angle of attack and negative sideslip | Czt +α-β (d(x)d(y)d(z))= -Czt +α+β (d(-x)d(-y)d(z)) |
| Roll moment coefficient M x | Positive angle of attack negative sideslip | Mx +α-β (d(x)d(y)d(z))= -Mx +α+β (d(-x)d(-y)d(z)) |
| Yaw moment coefficient M y | Positive angle of attack and negative sideslip | My +α-β (d(x)d(y)d(z))= -My +α+β (d(-x)d(-y)d(z)) |
| Coefficient of pitching moment M z | Positive angle of attack negative sideslip | Mz +α-β (d(x)d(y)d(z))= Mz +α+β (d(-x)d(-y)d(z)) |
In the above technical solution, the original pneumatic data is expanded into pneumatic data in a negative-attack-angle negative-side slip state, and the expansion formula is as follows:
| variable names | Target state | Extended formula |
| Coefficient of axial force C xt | Negative side slip with negative attack angle | Cxt -α-β (d(x)d(y)d(z))= Cxt +α+β (d(x)d(-y)d(-z)) |
| Coefficient of normal force C yt | Negative angle of attack and negative sideslip | Cyt -α-β (d(x)d(y)d(z))= -Cyt +α+β (d(x)d(-y)d(-z)) |
| Coefficient of lateral force C zt | Negative angle of attack and negative sideslip | Czt -α-β (d(x)d(y)d(z))= -Czt +α+β (d(x)d(-y)d(-z)) |
| Roll moment coefficient M x | Negative angle of attack and negative sideslip | Mx -α-β (d(x)d(y)d(z))= Mx +α+β (d(x)d(-y)d(-z)) |
| Yaw moment coefficient M y | Negative angle of attack and negative sideslip | My -α-β (d(x)d(y)d(z))= -My +α+β (d(x)d(-y)d(-z)) |
| Coefficient of pitching moment M z | Negative angle of attack and negative sideslip | Mz -α-β (d(x)d(y)d(z))= -Mz +α+β (d(x)d(-y)d(-z)) |
In the formula: alpha is an attack angle, beta is a sideslip angle, d (X) is an X-axis positive rudder deflection angle, d (-X) is an X-axis negative rudder deflection angle, d (Y) is a Y-axis positive rudder deflection angle, d (-Y) is a Y-axis negative rudder deflection angle, d (Z) is a Z-axis positive rudder deflection angle, and d (-Z) is a Z-axis negative rudder deflection angle.
In the above technical solution, in S3:
the resistance calculation formula is as follows:
the lift force calculation formula is as follows:
C D is a coefficient of resistance, C L Is a coefficient of lift, C xt Is the axial force coefficient, C yt Is the normal force coefficient, C zt Is the lateral force coefficient, alpha is the angle of attack and beta is the sideslip angle.
In the technical scheme, the target objects in the custom sequencing comprise five variables of Mach number, attack angle, sideslip angle, X-axis rudder deflection angle, Y-axis rudder deflection angle and Z-axis rudder deflection angle.
In the above technical solution, the aircraft is based on a shape in which the body axis is symmetrical in the left-right and up-down directions.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
saving computing resources, if a computing sample comprises 10 working conditions, 5 positive and negative attack angles are considered, and 5 positive and negative sideslip angle computing conditions are considered, the number of the working conditions needing to be computed is 10 × 5 × 2= 1000; by adopting the method to realize negative expansion of the attack angle and the sideslip angle, the number of the working conditions needing to be calculated is 10 x 5=250, and 75% of calculation resources are saved.
The method mainly adopts the principles of data correspondence in different states and symbol transformation to carry out data expansion, has less data iteration and mutual operation processes, brings small rounding errors and is not easy to make mistakes.
The method is wide in application range, and the aircraft meeting the characteristics of the shape can be applicable to the shape based on the shape of the axisymmetric aircraft with four X-shaped or cross-shaped control surface controls.
The method is easy to implement, has definite target and clear principle, and is convenient for computer programming to carry out batch data processing and database one-key generation.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a flow chart of a generation method of the present invention;
FIG. 2 is a plot of yaw moment coefficients versus angle of attack for different sideslip angles in a fully-enclosed aerodynamic database.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
In this embodiment, the X-axis rudder deflection angle includes an X-axis positive rudder deflection angle and an X-axis negative rudder deflection angle, d (X) and d (-X), respectively, the Y-axis rudder deflection angle includes a Y-axis positive rudder deflection angle and a Y-axis negative rudder deflection angle, d (Y) and d (-Y), respectively, and the Z-axis rudder deflection angle includes a Z-axis positive rudder deflection angle and a Z-axis negative rudder deflection angle, d (Z) and d (-Z), respectively;
as shown in the flowchart of fig. 1, first, the original aerodynamic data calculated by CFD simulation is read, and the original aerodynamic data of this embodiment includes lift Coefficients (CL), drag Coefficients (CD), axial force coefficients (Cxt), normal force coefficients (Cyt), lateral force coefficients (Czt), roll moment coefficients (Mx), yaw moment coefficients (My), and pitch moment coefficients (Mz) corresponding to states where the attack angle is 0 °, 2 °, 5 °, 10 °, 15 °, 20 °, 25 °, the sideslip angle is 0 °, 5 °, 10 °, 15 °, the X-axis rudder angle is-10 °, 0 °, 10 °, the Z-axis rudder angle is-10 °, 0 °, 10 °, and mach number of 10 ° is 0.85.
And identifying the number of lines of each file data in the original pneumatic data, detecting whether the original pneumatic data has data loss, if the original pneumatic data has data loss, prompting the state position of the lost pneumatic data, and if not, entering the next step.
And automatically identifying the rudder deflection state in the original pneumatic data according to the name of the original pneumatic data folder, and storing the original pneumatic data according to different rudder deflection states.
The method comprises the steps of performing attack angle expansion on original aerodynamic data according to an attack angle expansion formula, namely adding aerodynamic data after expansion, wherein the added aerodynamic data comprise lift Coefficient (CL), drag Coefficient (CD), axial force coefficient (Cxt), normal force coefficient (Cyt), lateral force coefficient (Czt), roll moment coefficient (Mx), yaw moment coefficient (My) and pitch moment coefficient (Mz) in corresponding states of attack angles of-2 degrees, -5 degrees, -10 degrees, -15 degrees, -20 degrees, -25 degrees, side slip angles of 0 degrees, 5 degrees, 10 degrees, 15 degrees, X-axis rudder deflection angles of-10 degrees, 0 degrees, 10 degrees, Y-axis rudder deflection angles of-10 degrees, 0.85 degrees, Z-axis rudder deflection angles of-10 degrees, 0.32 degrees, and Z-axis rudder deflection angles of-10 degrees.
And performing sideslip angle expansion on the original aerodynamic data according to a sideslip angle expansion formula, namely newly added aerodynamic data after expansion comprises lift Coefficients (CL), resistance Coefficients (CD), axial force coefficients (Cxt), normal force coefficients (Cyt), lateral force coefficients (Czt), roll moment coefficients (Mx), yaw moment coefficients (My) and pitch moment coefficients (Mz) in corresponding states, wherein the attack angle is 0 degrees, 2 degrees, 5 degrees, 10 degrees, 15 degrees, 20 degrees, 25 degrees, the sideslip angle is-5 degrees, -10 degrees, -15 degrees, the X-axis rudder deflection angle is-10 degrees, 0 degrees, 10 degrees, the Y-axis rudder deflection angle is-10 degrees, 0.85 degrees, the Z-axis rudder deflection angle is-10 degrees, 0 degrees and 10 degrees Mach numbers.
The method comprises the steps of performing attack angle sideslip angle expansion on original aerodynamic data according to an attack angle sideslip angle expansion formula, namely newly adding aerodynamic data after expansion, wherein the newly added aerodynamic data comprise lift Coefficients (CL), drag Coefficients (CD), axial force coefficients (Cxt), normal force coefficients (Cyt), lateral force coefficients (Czt), roll moment coefficients (Mx), yaw moment coefficients (My) and pitch moment coefficients (Mz) in corresponding states, wherein the attack angle is-2 degrees, -5 degrees, -10 degrees, -15 degrees, -20 degrees, -25 degrees, the sideslip angle is-5 degrees, -10 degrees, -15 degrees, the X-axis rudder deflection angle is-10 degrees, 0 degrees and 10 degrees, the Y-axis rudder deflection angle is-10 degrees, the Z-axis rudder deflection angle is-10 degrees, the 0.85-degree Mach number is-10 degrees, and the axial force Coefficients (CD), the axial force coefficients (Cxt), the normal force coefficients (Cyt), the lateral force coefficients (Czt), the roll moment coefficients (Mx), the yaw moment coefficients (My) and the pitch moment coefficients (Mz).
And calculating lift coefficient and resistance coefficient of all states before and after expansion according to a lift and resistance calculation formula.
All the pneumatic data before and after expansion are merged, the data are sequentially ordered according to 5 variables of Mach number, attack angle (alpha), sideslip angle (beta), X-axis rudder deflection angle, Y-axis rudder deflection angle and Z-axis rudder deflection angle according to actual needs, the data are output, and a full-envelope pneumatic database is generated, wherein a yaw moment coefficient (My) change curve is shown in FIG. 2.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (8)
1. A CFD-based aircraft full-envelope pneumatic database generation method is characterized by comprising the following steps:
s1, acquiring original pneumatic data of CFD simulation calculation;
s2: expanding the original pneumatic data into pneumatic data under a negative attack angle positive sideslip state, pneumatic data under a positive attack angle negative sideslip state and pneumatic data under a negative attack angle negative sideslip state respectively;
s3: calculating lift and resistance of all states before and after expansion;
s4: and merging all the pneumatic data before and after expansion, performing custom sequencing after merging, and outputting the merged pneumatic data to a full-envelope pneumatic database according to a format.
2. The CFD-based aircraft full-envelope pneumatic database generation method of claim 1, wherein during S1, the method comprises the following steps:
s11: identifying all data line numbers in the original pneumatic data;
s12: detecting whether the original pneumatic data has data loss or not;
s13: if the original pneumatic data has data missing, recording the state position of the missing pneumatic data;
s14: and automatically identifying the rudder deflection state in the original pneumatic data, and storing the original pneumatic data according to different rudder deflection states.
3. The CFD-based aircraft full envelope pneumatic database generation method of claim 1, wherein the original pneumatic data is expanded to pneumatic data in a negative attack angle and positive sideslip state by the expansion formula:
in the formula: alpha is an attack angle, beta is a sideslip angle, d (X) is an X-axis positive rudder deflection angle, d (-X) is an X-axis negative rudder deflection angle, d (Y) is a Y-axis positive rudder deflection angle, d (-Y) is a Y-axis negative rudder deflection angle, d (Z) is a Z-axis positive rudder deflection angle, and d (-Z) is a Z-axis negative rudder deflection angle.
4. The CFD-based aircraft full envelope pneumatic database generation method of claim 1, wherein the original pneumatic data is expanded to pneumatic data in a positive angle of attack negative side slip state by the formula:
in the formula: alpha is an attack angle, beta is a sideslip angle, d (X) is an X-axis positive rudder deflection angle, d (-X) is an X-axis negative rudder deflection angle, d (Y) is a Y-axis positive rudder deflection angle, d (-Y) is a Y-axis negative rudder deflection angle, d (Z) is a Z-axis positive rudder deflection angle, and d (-Z) is a Z-axis negative rudder deflection angle.
5. The CFD-based aircraft full envelope pneumatic database generation method of claim 1, wherein the original pneumatic data is expanded to pneumatic data in a negative-angle-of-attack negative-side-slip state by the expansion formula:
in the formula: alpha is an attack angle, beta is a side slip angle, d (X) is an X-axis positive rudder deflection angle, d (-X) is an X-axis negative rudder deflection angle, d (Y) is a Y-axis positive rudder deflection angle, d (-Y) is a Y-axis negative rudder deflection angle, d (Z) is a Z-axis positive rudder deflection angle, and d (-Z) is a Z-axis negative rudder deflection angle.
6. The CFD-based aircraft full-envelope pneumatic database generation method of claim 1, wherein in S3:
the resistance calculation formula is as follows:
the lift force calculation formula is as follows:
C D is a coefficient of resistance, C L Is the coefficient of lift, C xt Is the axial force coefficient, C yt Is the normal force coefficient, C zt Is the lateral force coefficient, alpha is the angle of attack and beta is the sideslip angle.
7. The CFD-based aircraft full envelope pneumatic database generation method of claim 1, wherein the custom ordered target objects include five variables of Mach number, angle of attack, sideslip angle, X-axis rudder deflection angle, Y-axis rudder deflection angle, and Z-axis rudder deflection angle.
8. A CFD-based aircraft full envelope pneumatic database generation method according to any of claims 1-7, wherein: the aircraft is based on the symmetrical appearance of body axis left and right and upper and lower direction.
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| CN116225073A (en) * | 2023-05-09 | 2023-06-06 | 中国空气动力研究与发展中心计算空气动力研究所 | CFD method-based method for rapidly determining attack angle of plane |
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