CN108120581B - Rotating missile pitching derivative high-speed wind tunnel test device and method - Google Patents
Rotating missile pitching derivative high-speed wind tunnel test device and method Download PDFInfo
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Abstract
A rotating missile pitching derivative high-speed wind tunnel test device and a method are provided. The device includes: a high speed wind tunnel; the supporting mechanism is used for supporting the missile in the high-speed wind tunnel and can drive the missile to rotate and perform forced pitching vibration; the dynamic derivative balance is arranged inside the missile and used for measuring a moment signal of the missile; the displacement element is arranged on the supporting mechanism and used for measuring a vibration angular displacement signal of the missile; a processor that calculates a pitch derivative for each angle of attack in the sequence of angles of attack. When the missile rotates around the axis of the missile in the high-speed wind tunnel, the missile is driven by the supporting mechanism to perform forced pitching vibration, and the pitching derivative of the rotating missile in the high-speed wind tunnel can be accurately, simply and conveniently calculated.
Description
Technical Field
The invention relates to the field of test aerodynamics, in particular to a rotating missile pitching derivative high-speed wind tunnel test device and method.
Background
The control system of the missile can be simplified by rotating flight, and the control in the pitching direction and the yawing direction can be realized by using one control channel; the adverse effect of asymmetric factors such as thrust eccentricity, mass eccentricity and aerodynamic eccentricity on the flight performance can be reduced. However, the rotating flight also brings a series of complicated aerodynamic problems, when the aircraft rotates around the axis of the aircraft, the shearing effect of the rotation on the boundary layer causes the asymmetric separation of the body vortex and the asymmetry of the transition region of the boundary layer, thereby further causing the change of the aerodynamic characteristics, especially the change of the dynamic derivative characteristics.
The pitching derivative is an important dynamic parameter of tactical flight weapons, and is indispensable data for dynamic quality analysis and control system design. The method for acquiring the dynamic derivative parameters through the high-speed wind tunnel test is one of the main research methods. High speed wind tunnel tests typically measure the dynamic derivative using vibration methods, which can be generally classified into two types: one is a free vibration method and the other is a forced vibration method. Practice proves that the forced vibration method has small calculation workload and is accurate.
When the pitching dynamic derivative parameter under the rotation condition is researched through a wind tunnel test, early researchers hope to combine the aerodynamic data of stable rotation and the single-degree-of-freedom dynamic derivative test data to estimate the oscillating dynamic derivative under the rotation flow field, but the method is not reliable. Jaccob Kay has conducted a rotating balance forced oscillation test in a 12-foot vertical wind tunnel, and test data shows that in a large attack angle range, unsteady aerodynamic characteristics of oscillation rotation are greatly different from steady rotation, and stronger nonlinearity is reflected. Therefore, research institutions at home and abroad successively develop respective test technologies to perform related research, but mainly perform research in low-speed wind tunnels. The flight speed of the rotating missile is generally in a high-speed range, the pitching derivative characteristic of the rotating missile is mainly researched by numerical calculation at present and is limited by factors such as high-speed wind tunnel load, size, blockage degree and the like, and ground simulation in a high-speed wind tunnel is rare. Therefore, it is necessary to develop a rotating missile pitching derivative high-speed wind tunnel test device and method.
Disclosure of Invention
The invention provides a rotating missile pitching derivative high-speed wind tunnel test device and method, wherein a missile is driven to do forced pitching vibration by a supporting mechanism while rotating around the axis of the missile in a high-speed wind tunnel, and the pitching derivative of the rotating missile in the high-speed wind tunnel can be accurately, simply and conveniently calculated.
According to one aspect of the invention, a rotating missile pitching derivative high-speed wind tunnel test device is provided, which comprises: a high speed wind tunnel; the supporting mechanism is used for supporting the missile in the high-speed wind tunnel and can drive the missile to rotate and perform forced pitching vibration; the dynamic derivative balance is arranged inside the missile and used for measuring a moment signal of the missile; the displacement element is arranged on the supporting mechanism and used for measuring a vibration angular displacement signal of the missile; a processor that calculates, for each angle of attack in a sequence of angles of attack, the derivative of pitch according to the following equation (1):
wherein C is the derivative of pitching motion,
is the moment coefficient of pitch time difference, CmqAs a function of the pitch damping moment coefficient,
for the fundamental amplitude of the aerodynamic moment, λ is the phase difference between the vibration angular displacement signal and the total moment signal, θ0Amplitude of fluctuation, q, of angular displacement∞Is dynamic pressure, S is the reference area of the missile, cAIs the reference length of the missile and K is the reduction frequency.
Preferably, the support means is in the form of a fan having a blockage of less than 10%.
Preferably, the processor determines the aerodynamic moment fundamental wave amplitude by: subtracting inertia moment from a total moment signal to obtain a change curve of the aerodynamic moment, wherein the total moment signal is obtained by measuring through the dynamic derivative balance under the condition of wind, and the inertia moment is obtained based on the inertia moment signal obtained by measuring through the dynamic derivative balance under the condition of no wind; and determining the amplitude of the fundamental wave of the aerodynamic moment according to the variation curve of the aerodynamic moment.
Preferably, the processor determines the moment of inertia for each angle of attack by: and under the attack angle, measuring an inertia moment signal in a forced pitching vibration period at a specified sampling interval, and taking the average value of the inertia moment signals measured in the period as the inertia moment corresponding to the attack angle.
Preferably, the processor calculates the reduction frequency by the following equation (2):
K＝ωcA/(2V) (2)
where ω is the forced pitch vibration frequency and V is the wind speed.
Preferably, said rotation is a self-rotation about the axis of the missile itself and said forced pitch vibration is a sinusoidal forced pitch vibration about the missile centre of mass.
According to another aspect of the invention, a rotating missile pitching derivative high-speed wind tunnel test method is provided, which may include: under the condition of no wind, aiming at each attack angle in the attack angle sequence, the missile is made to rotate and forcedly vibrate in a pitching mode under the attack angle, and the inertia moment corresponding to each attack angle is determined; under the windy condition, aiming at each attack angle in the attack angle sequence, enabling the missile to rotate and perform forced pitching vibration under the attack angle, measuring a total moment signal corresponding to each attack angle, and collecting a vibration angle displacement signal corresponding to each attack angle, wherein under the windy condition and the windless condition, the rotation speed of the missile and the vibration angle speed and amplitude of the forced pitching vibration are the same; for each angle of attack in the sequence of angles of attack, calculating the derivative of pitch according to the following equation (1):
wherein C is the derivative of pitching motion,
is the moment coefficient of pitch time difference, CmqAs a function of the pitch damping moment coefficient,
for the fundamental amplitude of the aerodynamic moment, λ is the phase difference between the vibration angular displacement signal and the total moment signal, θ0Amplitude of fluctuation, q, of angular displacement∞Is dynamic pressure, S is the reference area of the missile, cAIs the reference length of the missile and K is the reduction frequency.
Preferably, the aerodynamic moment fundamental wave amplitude is determined by: subtracting the inertia moment from the total moment signal to obtain a aerodynamic moment variation curve; and determining the amplitude of the fundamental wave of the aerodynamic moment according to the variation curve of the aerodynamic moment.
Preferably, the moment of inertia for each angle of attack is determined by: and under the attack angle, measuring an inertia moment signal in a forced pitching vibration period at a specified sampling interval, and taking the average value of the inertia moment signals measured in the period as the inertia moment corresponding to the attack angle.
Preferably, the reduction frequency is calculated by the following formula (2):
K＝ωcA/(2V) (2)
where ω is the forced pitch vibration frequency and V is the wind speed.
Preferably, said rotation is a self-rotation about the axis of the missile itself and said forced pitch vibration is a sinusoidal forced pitch vibration about the missile centre of mass.
The invention has the beneficial effects that: when the missile rotates around the axis of the missile in the high-speed wind tunnel, the rotating missile is driven by the supporting mechanism to do forced pitching vibration, and the problem of measuring the pitching derivative when the missile rotates in the high-speed wind tunnel is solved.
The method and apparatus of the present invention have other features and advantages which will be apparent from or are set forth in detail in the accompanying drawings and the following detailed description, which are incorporated herein, and which together serve to explain certain principles of the invention.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts.
FIG. 1 shows a schematic diagram of a rotating missile pitch derivative high-speed wind tunnel test device according to one embodiment of the invention.
FIG. 2 shows a flow chart of the steps of a rotating missile pitch derivative high speed wind tunnel test method according to the invention.
Description of reference numerals:
1. a high speed wind tunnel; 2. a missile; 3. a support mechanism; 4. a dynamic derivative balance; 5. a displacement element.
Detailed Description
The invention will be described in more detail below with reference to the accompanying drawings. While the preferred embodiments of the present invention are shown in the drawings, it should be understood that the present invention may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
FIG. 1 shows a schematic diagram of a rotating missile pitch derivative high-speed wind tunnel test device according to one embodiment of the invention.
Rotatory guided missile every single move derivative high-speed wind tunnel test device includes: the high-speed wind tunnel 1 has a Mach number range of 0.3-4.0; the supporting mechanism 3 is used for supporting the missile 2 in the high-speed wind tunnel 1, and can drive the missile 2 to rotate and perform forced pitching vibration; the dynamic derivative balance 4 is arranged inside the missile 2 and used for measuring a moment signal of the missile 2; the displacement element 5 is arranged on the supporting mechanism 3 and used for measuring a vibration angular displacement signal of the missile 2; a processor that calculates, for each angle of attack in the sequence of angles of attack, a derivative of pitch according to the following equation (1):
wherein C is the derivative of pitching motion,
is the moment coefficient of pitch time difference, CmqAs a function of the pitch damping moment coefficient,
for the fundamental amplitude of the aerodynamic moment, λ is the phase difference between the vibration angular displacement signal and the total moment signal, θ0Amplitude of fluctuation, q, of angular displacement∞Is dynamic pressure, S is the reference area of missile 2, cAIs the reference length of the missile 2 and K is the reduction frequency.
Specifically, the pitching derivative in the formula (1) is the sum of the pitching time difference torque coefficient and the pitching damping torque coefficient, and in practical application, the pitching time difference torque coefficient and the pitching damping torque coefficient are used in combination as the pitching derivative, so that the pitching derivative is calculated according to the formula (1) in the present invention.
In one example, the supporting mechanism 3 is in a fan shape, the blockage degree of the supporting mechanism is less than 10%, namely the ratio of the windward area of the supporting mechanism 3 to the cross-sectional area of the high-speed wind tunnel 1 is less than 10%, the load of the high-speed wind tunnel 1 can be borne, and the size requirement of the high-speed wind tunnel 1 is met.
In one example, the processor determines the aerodynamic moment fundamental amplitude by: subtracting the inertia moment from the total moment signal to obtain a change curve of the aerodynamic moment, wherein the total moment signal is obtained by measuring through a dynamic derivative balance 4 under the condition of wind, and the inertia moment is obtained based on the inertia moment signal obtained by measuring through the dynamic derivative balance 4 under the condition of no wind; and determining the amplitude of the fundamental wave of the aerodynamic moment according to the variation curve of the aerodynamic moment.
In one example, the processor determines the moment of inertia for each angle of attack by: under the attack angle, measuring an inertia moment signal in a forced pitching vibration period at a specified sampling interval, and taking the average value of the inertia moment signals measured in the period as the inertia moment corresponding to the attack angle.
In one example, the processor calculates the reduction frequency by equation (2) below:
K＝ωcA/(2V) (2)
where ω is the forced pitch vibration frequency and V is the wind speed.
In one example, the rotation is a self-rotation about the axis of the missile 2 itself, and the forced pitch vibration is a sinusoidal forced pitch vibration about the missile center of mass.
In one example, the processor calculates the dynamic pressure by equation (3) below:
wherein q is∞Is dynamic pressure, M∞Is Mach number, p∞The static pressure is measured by a high-speed wind tunnel measurement and control system.
Specifically, the high-speed wind tunnel 1 can provide blowing conditions and control Mach number, the wind speed can be determined through the Mach number, and the Mach number range is 0.3-4.0; the supporting mechanism 3 is used for supporting the missile 2 in the high-speed wind tunnel 1 and can drive the missile 2 to rotate and perform forced pitching vibration, wherein the rotation is self-rotation around the axis of the missile 2, and the forced pitching vibration is sine forced pitching vibration, particularly sine forced pitching vibration around the center of mass of the missile; the processor may be a computer.
FIG. 2 shows a flow chart of the steps of a rotating missile pitch derivative high speed wind tunnel test method according to the invention.
In this embodiment, the rotating missile pitching derivative high-speed wind tunnel test method according to the invention may include:
specifically, under the windless condition, the missile is firstly adjusted to a specified attack angle through the supporting mechanism, then the missile is driven to rotate through the supporting mechanism and is driven to do forced pitching vibration, and a corresponding inertia moment signal is measured through the dynamic derivative balance. And then, adjusting the missile to the next attack angle, and repeating the process until the measurement of each attack angle in the attack angle sequence is completed.
102, under the windy condition, aiming at each attack angle in an attack angle sequence, enabling the missile to rotate and perform forced pitching vibration under the attack angle, measuring a total moment signal corresponding to each attack angle, and acquiring a vibration angle displacement signal corresponding to each attack angle, wherein under the windy condition and the windless condition, the rotating speed of the missile is the same as the vibration angular speed and the amplitude of the forced pitching vibration;
specifically, the high-speed wind tunnel is started, the high-speed wind tunnel provides blowing conditions, the Mach number can be controlled, the wind speed in the high-speed wind tunnel can be determined through the Mach number, and the Mach number range is 0.3-4.0. After the flow field in the high-speed wind tunnel is stabilized to the appointed Mach number, the guided missile is adjusted to the appointed attack angle through the supporting mechanism, the guided missile is driven to rotate through the supporting mechanism and is driven to do forced pitching vibration, the corresponding total moment signal is measured through the dynamic derivative balance, and the vibration angle displacement signal of the guided missile is measured through the displacement element. And then, adjusting the missile to the next attack angle, and repeating the process until the measurement of each attack angle in the attack angle sequence is completed.
wherein C is the derivative of pitching motion,
is the moment coefficient of pitch time difference, CmqAs a function of the pitch damping moment coefficient,
for the fundamental amplitude of the aerodynamic moment, λ is the phase difference between the vibration angular displacement signal and the total moment signal, θ0Amplitude of fluctuation, q, of angular displacement∞Is dynamic pressure, S is the reference area of the missile, cAIs the reference length of the missile and K is the reduction frequency.
In one example, the aerodynamic moment fundamental amplitude is determined by: subtracting the inertia moment from the total moment signal to obtain a pneumatic moment variation curve; and determining the amplitude of the fundamental wave of the aerodynamic moment according to the variation curve of the aerodynamic moment.
In one example, the moment of inertia for each angle of attack is determined by: under the attack angle, measuring an inertia moment signal in a forced pitching vibration period at a specified sampling interval, and taking the average value of the inertia moment signals measured in the period as the inertia moment corresponding to the attack angle.
In one example, the reduction frequency is calculated by the following equation (2):
K＝ωcA/(2V) (2)
where ω is the forced pitch vibration frequency and V is the wind speed.
In one example, the rotation is a self-rotation about the missile's own axis and the forced pitch vibration is a sinusoidal forced pitch vibration about the missile's center of mass.
In one example, the inertia moment signal, the total moment signal, and the vibration angular displacement signal may be filtered and then calculated accordingly.
According to the invention, when the rotating missile rotates around the axis of the rotating missile in the high-speed wind tunnel, the rotating missile is driven to do forced pitching vibration by the support mechanism, so that the problem of pitching derivative measurement when the rotating missile rotates in the high-speed wind tunnel is solved.
To facilitate understanding of the solution of the embodiments of the present invention and the effects thereof, three specific application examples are given below. It will be understood by those skilled in the art that this example is merely for the purpose of facilitating an understanding of the present invention and that any specific details thereof are not intended to limit the invention in any way.
Application example 1
Rotatory guided missile every single move derivative high-speed wind tunnel test device includes: the high-speed wind tunnel 1 provides blowing conditions and controls Mach number, and determines wind speed according to the Mach number; the supporting mechanism 3 is in a fan shape and is used for supporting the missile 2 in the high-speed wind tunnel 1 and driving the missile 2 to rotate and perform forced pitching vibration, wherein the rotation is self-rotation around the axis of the missile 2, and the forced pitching vibration is sinusoidal forced pitching vibration around the center of mass of the missile; the dynamic derivative balance 4 is arranged inside the missile 2 and used for measuring a moment signal of the missile 2; the displacement element 5 is arranged on the support mechanism 3 and used for measuring a vibration angular displacement signal of the missile 2; the processor is a computer, measures an inertia moment signal in a forced pitching vibration period through the dynamic derivative balance 4 at a specified sampling interval under the condition of no wind according to each attack angle in the attack angle sequence, takes the average value of the inertia moment signals measured in the period as the inertia moment corresponding to the attack angle, obtains a total moment signal through the measurement of the dynamic derivative balance 4 under the condition of wind, subtracts the inertia moment from the total moment signal to obtain an aerodynamic moment change curve, determines the fundamental wave amplitude of the aerodynamic moment according to the aerodynamic moment change curve, obtains dynamic pressure through wind speed calculation, and calculates the pitching dynamic derivative according to a formula (1), wherein the shrinkage reduction frequency is calculated through the formula (2).
Application example 2
The rotating missile pitching derivative high-speed wind tunnel test method comprises the following steps:
step 101: under the condition of no wind, aiming at 0 degrees in an attack angle sequence, the missile is enabled to rotate and perform forced pitching vibration under the attack angle of 0 degrees, wherein the rotation is self-rotation around the axis of the missile, the rotating speed is 300r/min, the forced pitching vibration is sine forced pitching vibration around the center of mass of the missile, and the vibration equation is theta which is 3 degrees sin (2 pi t). Under an attack angle of 0 degree, measuring an inertia moment signal in a forced pitching vibration period at a specified sampling interval, and taking the average value of the inertia moment signals measured in the period as the inertia moment corresponding to the attack angle;
step 102: the method comprises the steps that a high-speed wind tunnel is started, blowing conditions are provided, the Mach number is controlled to be 0.6, the wind speed is determined through the Mach number, the missile is enabled to rotate and perform forced pitching vibration under the attack angle of 0 degrees in an attack angle sequence under the condition of wind, a total moment signal corresponding to the attack angle of 0 degrees is measured, and a vibration angle displacement signal corresponding to the attack angle of 0 degrees is collected, wherein the rotating speed of the missile is 300r/min under the condition of wind and no wind, and the forced pitching vibration equation is theta-3-degree sin (2 pi t);
step 103: subtracting the inertia moment from the total moment signal to obtain a aerodynamic moment change curve aiming at 0 DEG in the attack angle sequence; determining the fundamental wave amplitude of the aerodynamic moment according to the variation curve of the aerodynamic moment, obtaining the dynamic pressure through wind speed calculation, calculating the reference area and the reference length of the missile as the basic information of the missile, calculating the reduction frequency through a formula (2), and further calculating the pitching derivative to be-2.03 rad according to the formula (1)-1。
Application example 3
The rotating missile pitching derivative high-speed wind tunnel test method comprises the following steps:
step 101: under the condition of no wind, aiming at 0 degrees in an attack angle sequence, the missile is enabled to rotate and perform forced pitching vibration under the attack angle of 0 degrees, wherein the rotation is self-rotation around the axis of the missile, the rotating speed is 600r/min, the forced pitching vibration is sine forced pitching vibration around the center of mass of the missile, and the vibration equation is theta which is 3 degrees sin (4 pi t). Under an attack angle of 0 degree, measuring an inertia moment signal in a forced pitching vibration period at a specified sampling interval, and taking the average value of the inertia moment signals measured in the period as the inertia moment corresponding to the attack angle;
step 102: the method comprises the steps that a high-speed wind tunnel is started, blowing conditions are provided, the Mach number is controlled to be 0.8, the wind speed is determined through the Mach number, the missile is enabled to rotate and perform forced pitching vibration under the attack angle of 0 degrees in an attack angle sequence under the condition of wind, a total moment signal corresponding to the attack angle of 0 degrees is measured, and a vibration angle displacement signal corresponding to the attack angle of 0 degrees is collected, wherein the rotating speed of the missile is 600r/min under the condition of wind and no wind, and the forced pitching vibration equation is theta-3-degree sin (4 pi t);
step 103: subtracting the inertia moment from the total moment signal to obtain a aerodynamic moment change curve aiming at 0 DEG in the attack angle sequence; determining the fundamental wave amplitude of the aerodynamic moment according to the variation curve of the aerodynamic moment, obtaining the dynamic pressure through wind speed calculation, calculating the reference area and the reference length of the missile as the basic information of the missile, calculating the shrinkage reduction frequency through a formula (2), and further calculating the pitching derivative to be-2.48 rad according to the formula (1)-1。
In conclusion, the rotating missile is driven to do forced pitching vibration by the supporting mechanism while rotating around the axis of the rotating missile in the high-speed wind tunnel, and the problem of measurement of pitching derivative of the rotating missile in the high-speed wind tunnel during rotation is solved.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (9)
1. The utility model provides a rotatory missile every single move derivative high-speed wind tunnel test device which characterized in that, the device includes:
a high speed wind tunnel;
the supporting mechanism is used for supporting the missile in the high-speed wind tunnel and can drive the missile to rotate and perform forced pitching vibration;
the dynamic derivative balance is arranged inside the missile and used for measuring a moment signal of the missile;
the displacement element is arranged on the supporting mechanism and used for measuring a vibration angular displacement signal of the missile;
a processor that calculates, for each angle of attack in a sequence of angles of attack, the derivative of pitch according to the following equation (1):
wherein C is the derivative of pitching motion,
is the moment coefficient of pitch time difference, CmqAs a function of the pitch damping moment coefficient,
for the fundamental amplitude of the aerodynamic moment, λ is the phase difference between the vibration angular displacement signal and the total moment signal, θ0Amplitude of fluctuation, q, of angular displacement∞Is dynamic pressure, S is the reference area of the missile, cAIs the reference length of the missile, and K is the reduction frequency;
wherein, the supporting mechanism is in a fan shape, and the blocking degree of the supporting mechanism is less than 10 percent;
wherein the processor determines the aerodynamic moment fundamental amplitude by:
subtracting an inertia moment from a total moment signal to obtain a change curve of the aerodynamic moment, wherein the total moment signal is obtained by measuring through the dynamic derivative balance under the condition of wind, and the inertia moment is obtained based on the inertia moment signal obtained by measuring through the dynamic derivative balance under the condition of no wind;
determining the amplitude of the fundamental wave of the aerodynamic moment according to the variation curve of the aerodynamic moment;
the inertial moment signal, the total moment signal and the vibration angular displacement signal are filtered, and then corresponding calculation is carried out.
2. The rotating missile pitch derivative high-speed wind tunnel test device of claim 1, wherein the processor determines the moment of inertia for each angle of attack by:
and under the attack angle, measuring an inertia moment signal in a forced pitching vibration period at a specified sampling interval, and taking the average value of the inertia moment signals measured in the period as the inertia moment corresponding to the attack angle.
3. The rotating missile pitch derivative high speed wind tunnel test device of claim 1, wherein the processor calculates the reduction frequency by the following equation (2):
K＝ωcA/(2V) (2)
where ω is the forced pitch vibration frequency and V is the wind speed.
4. The rotating missile pitching derivative high-speed wind tunnel test device according to claim 1, wherein the rotation is self-rotation around the axis of the missile, and the forced pitching vibration is sinusoidal forced pitching vibration around the missile center of mass.
5. A rotating missile pitching derivative high-speed wind tunnel test method by using the rotating missile pitching derivative high-speed wind tunnel test device according to claim 1, wherein the method comprises the following steps:
under the condition of no wind, aiming at each attack angle in the attack angle sequence, the missile is made to rotate and forcedly vibrate in a pitching mode under the attack angle, and the inertia moment corresponding to each attack angle is determined;
under the windy condition, aiming at each attack angle in the attack angle sequence, enabling the missile to rotate and perform forced pitching vibration under the attack angle, measuring a total moment signal corresponding to each attack angle, and collecting a vibration angle displacement signal corresponding to each attack angle, wherein under the windy condition and the windless condition, the rotation speed of the missile and the vibration angle speed and amplitude of the forced pitching vibration are the same;
for each angle of attack in the sequence of angles of attack, calculating the derivative of pitch according to the following equation (1):
wherein C is the derivative of pitching motion,
is the moment coefficient of pitch time difference, CmqAs a function of the pitch damping moment coefficient,
for the fundamental amplitude of the aerodynamic moment, λ is the phase difference between the vibration angular displacement signal and the total moment signal, θ0Amplitude of fluctuation, q, of angular displacement∞Is dynamic pressure, S is the reference area of the missile, cAIs the reference length of the missile, and K is the reduction frequency;
the inertial moment signal, the total moment signal and the vibration angular displacement signal are filtered, and then corresponding calculation is carried out.
6. The rotating missile pitching derivative high-speed wind tunnel test method according to claim 5, wherein the amplitude of the aerodynamic moment fundamental wave is determined by the following steps:
subtracting the inertia moment from the total moment signal to obtain a aerodynamic moment variation curve;
and determining the amplitude of the fundamental wave of the aerodynamic moment according to the variation curve of the aerodynamic moment.
7. The rotating missile pitch derivative high-speed wind tunnel test method according to claim 5, wherein the moment of inertia corresponding to each angle of attack is determined by the following steps:
and under the attack angle, measuring an inertia moment signal in a forced pitching vibration period at a specified sampling interval, and taking the average value of the inertia moment signals measured in the period as the inertia moment corresponding to the attack angle.
8. The rotating missile pitch derivative high speed wind tunnel test method of claim 5, wherein the reduction frequency is calculated by the following equation (2):
K＝ωcA/(2V) (2)
where ω is the forced pitch vibration frequency and V is the wind speed.
9. The rotating missile pitching derivative high-speed wind tunnel test method according to claim 5, wherein the rotation is self-rotation around the axis of the missile, and the forced pitching vibration is sinusoidal forced pitching vibration around the missile center of mass.
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