CN116933400A - Method for constructing aerodynamic moment model of coupling uncertainty - Google Patents
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Abstract
The invention discloses a construction method of an aerodynamic moment model with coupling uncertainty, and belongs to the field of aerodynamic force and flight mechanics. The aerodynamic moment model comprises a rolling moment model, a pitching moment model and a yawing moment model, wherein under the starting and non-starting states of a wind tunnel, sinusoidal oscillation data of rolling, yawing and pitching of the model are respectively collected, a formula is utilized to calculate a dynamic derivative at a balance point of each periodic oscillation, influence of uncertainty on moment dynamic characteristics is introduced, and the aerodynamic moment model with complex state simulation capability is constructed. Compared with the traditional linear dynamic derivative model, the model can describe the nonlinear unsteady characteristic of the aircraft more accurately, avoids the problem of mismatching of static data zero value and dynamic data zero value caused by adopting multi-sampling period average processing, can predict the wingtip loss and limit cycle oscillation of the aircraft more accurately, and provides a more real simulation effect.
Description
Technical Field
The invention belongs to the field of aerodynamic force and flight mechanics, and particularly relates to a construction method of an aerodynamic moment model with coupling uncertainty.
Background
Along with the progress of flight control technology and the requirement that pilots utilize simulators to develop complex state training, flight envelope lines such as aircraft attack angles and sideslip angles are expanded to a large attack angle nonlinear unsteady area, and the relevant airworthiness regulations of the flight simulators put clear demands on the simulation capability of a large attack angle complex state pneumatic model such as limit cycle oscillation and wingtip dropping. The research result shows that the position relation between the static zero value and the dynamic derivative zero value of the moment is the key of predicting limit cycle oscillation, wingtip loss and other phenomena, the steady linearization moment model parameters mainly pass through static and dynamic derivative tests, the two test data processing processes adopt a multipoint average linearization processing mode, and the two tests generally adopt different test systems and correction methods, so that the position relation between the static zero value and the dynamic derivative zero value of the moment has deviation, and the capability of predicting complex state phenomena of the pneumatic model is affected. Thus, there is a need for a aerodynamic moment model of coupling uncertainty.
Disclosure of Invention
In order to solve the problems, the invention provides a method for constructing an aerodynamic moment model with coupling uncertainty, which introduces the influence of uncertainty on moment dynamic characteristics, constructs the aerodynamic moment model with complex state simulation capability and is used for improving the complex state simulation capability of a flight simulator.
The technical scheme adopted by the invention is as follows: a method for constructing a aerodynamic moment model with coupling uncertainty comprises a rolling moment model, a pitching moment model and a yawing moment model, and the method comprises the following steps:
s1: the wind tunnel test model is connected with a wind tunnel supporting system through a six-component strain balance, balance data are collected by a wind tunnel test data collection system, and the wind tunnel test data collection system has a real-time synchronous collection function of balance data and the motion gesture of the wind tunnel test model;
s2: changing the attitude angle of the wind tunnel test model through a wind tunnel support system to reach a target attitude position, and giving an oscillation balance point, an amplitude and an oscillation frequency;
s3: respectively collecting 20 period data of the rolling sinusoidal oscillation of the wind tunnel test model in the starting and non-starting states of the wind tunnel;
s4: identifying and extracting pneumatic data of 20 periods by utilizing the relation among the mass, inertia, mass center position and oscillation parameters;
s5: calculating the dynamic derivative at the balance point of each periodic oscillation by adopting a formula (3);
s6: calculated by the formula (4)Then calculate by equation (5)Then calculate through the formula (6) and the formula (7)And；
s7: repeating the steps s 2-s 6 to obtain rolling moment models under different attitude angles, wherein the rolling moment models are shown in the formula (1)Is obtained through a wind tunnel static force test,obtained through a wind tunnel side-shifting oscillation test, and all the formulas (1) are obtainedThe value of the parameter, the formula (1) is a rolling moment model expression of the coupling uncertainty, and the rolling moment model in a non-test state is obtained by a data table look-up interpolation method, wherein the rolling moment model is constructed by the following formula:
（1）
（2）
（3）
（4）
（5）
（6）
（7）
wherein ,in order to provide a roll moment,is a static roll moment coefficient and is used for the control of the vehicle,for the derivative of the roll moment sink time difference,for the roll damping derivative,for the roll damping derivative of the i-th cycle,andis the roll moment coefficient of the positive and negative angular velocity over the balance point in the ith oscillation period,in order to achieve a roll angle speed,andrespectively the positive angular velocity and the negative angular velocity of the rolling over the balance point in the ith oscillation period, Q is the rapid pressure, S is the reference area of the wind tunnel test model, b is the span of the wind tunnel test model,for the wind speed of the wind,as the standard deviation of the derivative of the roll torque,as the mean value of the derivative of the roll moment,andthe maximum value and the minimum value of the derivative of the rolling moment are taken as a maximum value and a minimum value, and N is the number of cycles of a single test;
s8: changing the attitude angle of the wind tunnel test model through the wind tunnel support system again to reach the target attitude position, and giving an oscillation balance point, an amplitude and an oscillation frequency;
s9: respectively collecting 20 period data of yaw sinusoidal oscillation of a wind tunnel test model in the starting and non-starting states of the wind tunnel;
s10: identifying and extracting pneumatic data of 20 periods by utilizing the relation among the mass, inertia, mass center position and oscillation parameters;
s11: calculating the dynamic derivative at the balance point of each periodic oscillation by adopting a formula (10);
s12: calculated by the formula (11)Then calculate by formula (12)Then calculate by equation (13) and equation (14)And；
s13: repeating the steps s 8-s 12 to obtain yaw moment models under different attitude angle states, wherein the yaw moment models are shown in the formula (8)Is obtained through a wind tunnel static force test,obtaining values of all parameters of a formula (8) through a wind tunnel side-shifting oscillation test, wherein the formula (8) is a yaw moment model expression of coupling uncertainty, and a yaw moment model in a non-test state is obtained through a data lookup table interpolation method, wherein the construction formula of the yaw moment model is as follows:
（8）
（9）
（10）
（11）
（12）
（13）
（14）
wherein ,for the yaw moment,is a static yaw moment coefficient and is used for controlling the yaw moment,for the yaw moment wash time difference derivative,for the yaw damping derivative,for the yaw damping derivative of the i-th period,andfor a yaw moment coefficient at which the positive and negative angular velocity crosses the equilibrium point in the ith oscillation period,in order to achieve a yaw rate,andthe yaw positive and negative angular velocities of the over-balance point in the ith oscillation period,for the wind speed of the wind,as the sum of the yaw moment derivative standard deviationsAs the mean value of the derivative of the yaw moment,andthe yaw moment derivative maximum value and the yaw moment derivative minimum value are obtained;
s14: changing the attitude angle of the wind tunnel test model through the wind tunnel support system again to reach the target attitude position, and giving an oscillation balance point, an amplitude and an oscillation frequency;
s15: respectively acquiring 20 period data of pitching sinusoidal oscillation of the wind tunnel test model under the starting and non-starting states of the wind tunnel motor;
s16: identifying and extracting pneumatic data of 20 periods by utilizing the relation among the mass, inertia, mass center position and oscillation parameters;
s17: calculating the dynamic derivative at the balance point of each periodic oscillation by adopting a formula (17);
s18: calculated by equation (18)Then calculate by formula (19)Then calculate through the formula (20) and the formula (21)And；
s19: repeating the steps s 14-s 18 to obtain pitching moment models under different attitude angle states, wherein the pitching moment models are shown in the formula (15)Is obtained through a wind tunnel static force test,obtaining values of all parameters of a formula (15) through a wind tunnel heave oscillation test, wherein the formula (15) is a pitching moment model expression of coupling uncertainty, and a pitching moment model in a non-test state is obtained through a data table look-up interpolation method, wherein the pitching moment model is constructed as follows:
（15）
（16）
（17）
（18）
（19）
（20）
（21）
wherein ,in order to be a pitching moment,is a coefficient of the static pitching moment,for the derivative of the pitch moment wash time difference,for the pitch damping derivative,for the pitch damping derivative of the i-th period,andis the pitch moment coefficient of the positive and negative angular velocity over the balance point in the ith oscillation period,for the pitch angle rate,andrespectively the positive angular velocity and the negative angular velocity of pitching of the over-balance point in the ith oscillation period, c is the average pneumatic chord length of the wind tunnel test model,for the wind speed of the wind,as the sum of standard deviation of the derivative of pitching momentAs the mean value of the derivative of the pitching moment,andthe pitch moment derivative maximum and minimum values.
Further, the deviation between the mass center of the wind tunnel test model and the moment reference point is smaller than 10mm.
Further, the amplitude of the sinusoidal oscillation is less than or equal to 5 degrees, and the frequency is less than or equal to 3Hz.
The invention has the advantages and beneficial effects that: compared with the traditional linear dynamic derivative model, the aerodynamic moment model can describe the nonlinear unsteady characteristic of the aircraft more accurately, avoids the problem of mismatching of static data zero value and dynamic data zero value caused by adopting multi-sampling period average processing, can predict the wing tip loss and limit cycle oscillation of the aircraft more accurately, can be widely applied to flight simulators and flight simulation systems, and provides more real simulation effect.
Drawings
FIG. 1 is a schematic diagram of the overall flow of the present invention;
FIG. 2 is a graph of the course of the roll angle over time obtained by a free roll motion test of a wind tunnel test model;
FIG. 3 is a graph comparing the free rolling motion histories predicted by the aerodynamic moment model of the present invention coupled with the conventional dynamic derivative model.
Detailed Description
The invention is further illustrated by the following examples according to the drawings of the specification:
example 1
As shown in fig. 1, a method for constructing an uncertainty coupled aerodynamic moment model, where the aerodynamic moment model includes a rolling moment model, a pitching moment model and a yawing moment model, and the constructed uncertainty aerodynamic moment model obeys normal distribution, and may be arranged according to data features, where the method includes the following steps:
s1: connecting a wind tunnel test model with a wind tunnel support system through a six-component strain balance, and acquiring balance data by using a wind tunnel test data acquisition system, wherein the wind tunnel test data acquisition system has the functions of synchronously acquiring balance data and the motion gesture of the wind tunnel test model in real time, and the deviation between the centroid of the wind tunnel test model and a moment reference point is less than 10mm;
s2: changing the attitude angle of the wind tunnel test model through a wind tunnel support system to reach a target attitude position, and giving an oscillation balance point, an amplitude and an oscillation frequency;
s3: under the starting and non-starting states of the wind tunnel, respectively collecting 20 period data of the rolling sinusoidal oscillation of the wind tunnel test model, wherein the amplitude of the sinusoidal oscillation is less than or equal to 5 degrees, and the frequency is less than or equal to 3Hz;
s4: identifying and extracting pneumatic data of 20 periods by utilizing the relation among the mass, inertia, mass center position and oscillation parameters;
s5: calculating the dynamic derivative at the balance point of each periodic oscillation by adopting a formula (3);
s6: calculated by the formula (4)Then calculate by equation (5)Then calculate through the formula (6) and the formula (7)And；
s7: repeating the steps s 2-s 6 to obtain rolling moment models under different attitude angles, wherein the rolling moment models are shown in the formula (1)Is obtained through a wind tunnel static force test,obtaining the values of all parameters of the formula (1) through a wind tunnel side-shifting oscillation test, wherein the formula (1) is obtainedNamely, a rolling moment model expression of the coupling uncertainty is obtained by a data table look-up interpolation method, wherein a rolling moment model in a non-test state is constructed according to the following formula:
（1）
（2）
（3）
（4）
（5）
（6）
（7）
wherein ,in order to provide a roll moment,is a static roll moment coefficient and is used for the control of the vehicle,for the derivative of the roll moment sink time difference,for the roll damping derivative,for the roll damping derivative of the i-th cycle,andis the roll moment coefficient of the positive and negative angular velocity over the balance point in the ith oscillation period,in order to achieve a roll angle speed,andrespectively the positive angular velocity and the negative angular velocity of the rolling over the balance point in the ith oscillation period, Q is the rapid pressure, S is the reference area of the wind tunnel test model, b is the span of the wind tunnel test model,for the wind speed of the wind,as the standard deviation of the derivative of the roll torque,as the mean value of the derivative of the roll moment,andthe maximum value and the minimum value of the derivative of the rolling moment are taken as a maximum value and a minimum value, and N is the number of cycles of a single test;
s8: changing the attitude angle of the wind tunnel test model through the wind tunnel support system again to reach the target attitude position, and giving an oscillation balance point, an amplitude and an oscillation frequency;
s9: respectively collecting 20 period data of yaw sinusoidal oscillation of a wind tunnel test model in a wind tunnel starting state and a wind tunnel non-starting state, wherein the amplitude of the sinusoidal oscillation is less than or equal to 5 degrees, and the frequency is less than or equal to 3Hz;
s10: identifying and extracting pneumatic data of 20 periods by utilizing the relation among the mass, inertia, mass center position and oscillation parameters;
s11: calculating the dynamic derivative at the balance point of each periodic oscillation by adopting a formula (10);
s12: calculated by the formula (11)Then calculate by formula (12)Then calculate by equation (13) and equation (14)And；
s13: repeating the steps s 8-s 12 to obtain yaw moment models under different attitude angle states, wherein the yaw moment models are shown in the formula (8)Is obtained through a wind tunnel static force test,obtaining values of all parameters of a formula (8) through a wind tunnel side-shifting oscillation test, wherein the formula (8) is a yaw moment model expression of coupling uncertainty, and a yaw moment model in a non-test state is obtained through a data lookup table interpolation method, wherein the construction formula of the yaw moment model is as follows:
（8）
（9）
（10）
（11）
（12）
（13）
（14）
wherein ,for the yaw moment,is a static yaw moment coefficient and is used for controlling the yaw moment,for the yaw moment wash time difference derivative,for the yaw damping derivative,for the yaw damping derivative of the i-th period,andfor a yaw moment coefficient at which the positive and negative angular velocity crosses the equilibrium point in the ith oscillation period,in order to achieve a yaw rate,andthe yaw positive and negative angular velocities of the over-balance point in the ith oscillation period,for the wind speed of the wind,as the sum of the yaw moment derivative standard deviationsAs the mean value of the derivative of the yaw moment,andthe yaw moment derivative maximum value and the yaw moment derivative minimum value are obtained;
s14: changing the attitude angle of the wind tunnel test model through the wind tunnel support system again to reach the target attitude position, and giving an oscillation balance point, an amplitude and an oscillation frequency;
s15: respectively collecting 20 period data of pitching sinusoidal oscillation of a wind tunnel test model in the starting and non-starting states of the wind tunnel motor, wherein the amplitude of the sinusoidal oscillation is less than or equal to 5 degrees, and the frequency is less than or equal to 3Hz;
s16: identifying and extracting pneumatic data of 20 periods by utilizing the relation among the mass, inertia, mass center position and oscillation parameters;
s17: calculating the dynamic derivative at the balance point of each periodic oscillation by adopting a formula (17);
s18: calculated by equation (18)Then calculate by formula (19)Then calculate through the formula (20) and the formula (21)And；
s19: repeating the steps s 14-s 18 to obtain pitching moment models under different attitude angle states, wherein the pitching moment models are shown in the formula (15)Is obtained through a wind tunnel static force test,obtaining values of all parameters of a formula (15) through a wind tunnel heave oscillation test, wherein the formula (15) is a pitching moment model expression of coupling uncertainty, and a pitching moment model in a non-test state is obtained through a data table look-up interpolation method, wherein the pitching moment model is constructed as follows:
（15）
（16）
（17）
（18）
（19）
（20）
（21）
wherein ,in order to be a pitching moment,is a coefficient of the static pitching moment,for the derivative of the pitch moment wash time difference,for the pitch damping derivative,for the pitch damping derivative of the i-th period,andis the pitch moment coefficient of the positive and negative angular velocity over the balance point in the ith oscillation period,for the pitch angle rate,andrespectively the positive angular velocity and the negative angular velocity of pitching of the over-balance point in the ith oscillation period, c is the average pneumatic chord length of the wind tunnel test model,for the wind speed of the wind,as the sum of standard deviation of the derivative of pitching momentAs the mean value of the derivative of the pitching moment,andthe pitch moment derivative maximum and minimum values.
As shown in fig. 2-3, the aerodynamic moment model with the uncertainty of coupling can describe the nonlinear unsteady characteristic of the aircraft more accurately, avoid the problem of mismatching of static data zero value and dynamic data zero value caused by adopting multi-sampling period average processing, predict the wing tip loss and limit cycle oscillation of the aircraft more accurately, can be widely applied to flight simulators and flight simulation systems, and provide more real simulation effect.
Claims (3)
1. The method for constructing the aerodynamic moment model with the coupling uncertainty comprises a rolling moment model, a pitching moment model and a yawing moment model, and is characterized by comprising the following steps of:
s1: the wind tunnel test model is connected with a wind tunnel supporting system through a six-component strain balance, balance data are collected by a wind tunnel test data collection system, and the wind tunnel test data collection system has a real-time synchronous collection function of balance data and the motion gesture of the wind tunnel test model;
s2: changing the attitude angle of the wind tunnel test model through a wind tunnel support system to reach a target attitude position, and giving an oscillation balance point, an amplitude and an oscillation frequency;
s3: respectively collecting 20 period data of the rolling sinusoidal oscillation of the wind tunnel test model in the starting and non-starting states of the wind tunnel;
s4: identifying and extracting pneumatic data of 20 periods by utilizing the relation among the mass, inertia, mass center position and oscillation parameters;
s5: calculating the dynamic derivative at the balance point of each periodic oscillation by adopting a formula (3);
s6: calculated by the formula (4)After that, the +.>Then calculate through the formula (6) and the formula (7) and />；
s7: repeating the steps s 2-s 6 to obtain rolling moment models under different attitude angles, wherein the rolling moment models are shown in the formula (1)Obtaining by wind tunnel static force test, < >>Obtaining values of all parameters of a formula (1) through a wind tunnel side-shifting oscillation test, wherein the formula (1) is a rolling moment model expression of coupling uncertainty, and a rolling moment model in a non-test state is obtained through a data table look-up interpolation method, wherein the rolling moment model is constructed by the following formula:
（1）
（2）
（3）
（4）
（5）
（6）
（7）
wherein ,for roll moment, < >>For the static roll moment coefficient, +.>For the derivative of the roll moment wash time difference, +.>For the roll damping derivative +.>Roll damping derivative for the ith period, +.> and />Is the roll moment coefficient of positive and negative angular velocity over the balance point in the ith oscillation period,/>For roll angle speed, +.> and />Respectively the positive angular velocity and the negative angular velocity of the rolling over the balance point in the ith oscillation period, Q is the rapid pressure, S is the reference area of the wind tunnel test model, b is the span of the wind tunnel test model,for wind speed>For the rolling moment derivative standard deviation, +.>For the mean value of the roll moment derivative +.> and />The maximum value and the minimum value of the derivative of the rolling moment are taken as a maximum value and a minimum value, and N is the number of cycles of a single test;
s8: changing the attitude angle of the wind tunnel test model through the wind tunnel support system again to reach the target attitude position, and giving an oscillation balance point, an amplitude and an oscillation frequency;
s9: respectively collecting 20 period data of yaw sinusoidal oscillation of a wind tunnel test model in the starting and non-starting states of the wind tunnel;
s10: identifying and extracting pneumatic data of 20 periods by utilizing the relation among the mass, inertia, mass center position and oscillation parameters;
s11: calculating the dynamic derivative at the balance point of each periodic oscillation by adopting a formula (10);
s12: calculated by the formula (11)After that, the +.>Then calculate +.sup.via equation (13) and equation (14)> and />；
s13: repeating the steps s 8-s 12 to obtain yaw moment models under different attitude angle states, wherein the yaw moment models are shown in the formula (8)Obtaining by wind tunnel static force test, < >>Obtaining values of all parameters of a formula (8) through a wind tunnel side-shifting oscillation test, wherein the formula (8) is a yaw moment model expression of coupling uncertainty, and a yaw moment model in a non-test state is obtained through a data lookup table interpolation method, wherein the construction formula of the yaw moment model is as follows:
（8）
（9）
（10）
（11）
（12）
（13）
（14）
wherein ,for yaw moment>Is a static yaw moment coefficient->For yaw moment wash time difference derivative, +.>For yaw damping derivative>Yaw damping derivative for the ith period, < + >> and />For the yaw moment coefficient of positive and negative angular velocity over the balance point in the ith oscillation period,/>For yaw rate> and />Yaw positive and negative angular velocities, respectively, of an overbalance point in the ith oscillation periodSpeed (I)>For yaw moment derivative standard deviation sum +>For yaw moment derivative mean +.> and />The yaw moment derivative maximum value and the yaw moment derivative minimum value are obtained;
s14: changing the attitude angle of the wind tunnel test model through the wind tunnel support system again to reach the target attitude position, and giving an oscillation balance point, an amplitude and an oscillation frequency;
s15: respectively acquiring 20 period data of pitching sinusoidal oscillation of the wind tunnel test model under the starting and non-starting states of the wind tunnel motor;
s16: identifying and extracting pneumatic data of 20 periods by utilizing the relation among the mass, inertia, mass center position and oscillation parameters;
s17: calculating the dynamic derivative at the balance point of each periodic oscillation by adopting a formula (17);
s18: calculated by equation (18)After that, the +.>Then calculate +.sup.via equation (20) and equation (21)> and />；
s19: repeating the steps s 14-s 18 to obtain different attitude anglesThe lower pitching moment model, in equation (15)Obtaining by wind tunnel static force test, < >>Obtaining values of all parameters of a formula (15) through a wind tunnel heave oscillation test, wherein the formula (15) is a pitching moment model expression of coupling uncertainty, and a pitching moment model in a non-test state is obtained through a data table look-up interpolation method, wherein the pitching moment model is constructed as follows:
（15）
（16）
（17）
（18）
（19）
（20）
（21）
wherein ,for pitching moment +.>Is a static pitching moment coefficient->For the derivative of the pitch moment wash time difference, +.>For the pitch damping derivative +.>Pitch damping derivative for the ith period, < + >> and />For the pitch moment coefficient of positive and negative angular velocity over the balance point in the ith oscillation period,/>For pitch angle speed +.> and />Respectively representing the positive angular velocity and the negative angular velocity of pitching of an over-balance point in the ith oscillation period, wherein c represents the average pneumatic chord length of the wind tunnel test model, and +.>For the standard deviation sum of the derivative of the pitching moment +.>For the mean value of the derivative of the pitching moment> and />The pitch moment derivative maximum and minimum values.
2. The method for constructing a aerodynamic moment model with coupling uncertainty according to claim 1, wherein the deviation between the centroid of the wind tunnel test model and the moment reference point is less than 10mm.
3. The method for constructing a aerodynamic moment model with coupling uncertainty according to claim 1 or 2, wherein the sinusoidal oscillation amplitude is 5 ° or less and the frequency is 3Hz or less.
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