A dual-channel control pitch moment parameter test method

Abstract

This invention discloses a dual-channel control pitch moment parameter testing method. The method first employs a wind tunnel force measurement experiment to obtain the pitch moment parameter data C of the projectile under single-channel conditions. MZ Then control the angle of attack α of the dual-channel environment. 双 and sideslip angle β 双 Convert to simulated angle of attack A; when α 双 <0 and β 双 When α < 0, the simulated angle of attack is when α 双 >0 or β 双 When the angle of attack is greater than 0, the final step in simulating the angle of attack is to calculate the pitch moment parameter C in the dual-channel arbitrary control environment. mz When A > 0, when A ≤ 0, when A > 0, when A ≤ 0, the test method of the present invention can perform corresponding conversion on the limited single-channel aerodynamic parameters to obtain the true dual-channel aerodynamic parameters, reducing the number of working conditions required for ground blowing tests, and thus greatly reducing the project development cost.

Description

Technical Field

[0001] This invention relates to a dual-channel control method for testing pitch moment parameters, belonging to the field of projectile and rocket technology. Background Technology

[0002] Conventional missiles and rockets typically fly under single-channel control, meaning that the angle of attack and sideslip angle do not occur simultaneously during flight. With the increasingly severe international situation, modern warfare demands higher levels of lethality and precision in guided rocket weapons. More and more products require precise control of both landing velocity and angle of attack simultaneously, necessitating simultaneous control of the incoming flow angle of attack and sideslip angle. Under dual-channel control, conducting ground-based wind tests or calculations based on actual operating conditions (with both angle of attack and sideslip angle present) would result in an enormous number of operating scenarios, which is uneconomical and impractical from the perspective of controlling product development progress and costs. Therefore, for conventional aerodynamic layout missiles and rockets with a slenderness ratio of 20 or less, a method needs to be found that utilizes single-channel aerodynamic data to obtain the dual-channel aerodynamic parameters required for actual flight under multi-channel control. This ensures the accuracy and reliability of the final aerodynamic parameters while significantly saving economic and time costs in project development. Summary of the Invention

[0003] The purpose of this invention is to solve the problems of large number of working conditions and high testing cost in traditional dual-channel control pitch moment parameter testing methods, and to provide a dual-channel control pitch moment parameter testing method.

[0004] The objective of this invention is achieved through the following technical solution:

[0005] This invention provides a dual-channel control pitch moment parameter testing method, which is applicable to conventional aerodynamic layout projectiles with a length-to-slenderness ratio of less than 20.

[0006] The specific testing steps are as follows:

[0007] 1) Using wind tunnel force measurement experiments, the single-channel pitching moment parameter data C of the projectile under different Mach numbers, different rudder deflection angles, and different angles of attack α were obtained. MZ ;

[0008] 2) The angle of attack α of the dual-channel control environment 双 and sideslip angle β 双 Convert to simulated angle of attack A:

[0009] When α 双 <0 and β 双 When <0,

[0010] When α 双 >0 or β 双 When >0,

[0011] 3) When When A>0, calculate the pitch moment parameter C of the dual-channel arbitrary control environment according to the following formula 3). mz :

[0012]

[0013] Where, δ z双 For the pitch deflection angle of the dual-channel control environment, the C MZ (α 单 =A,δ z单 =-|δ z双 |) represents the single-channel pitch moment parameter data that has the same Mach number as the dual-channel control environment under test, and the yaw deflection angle δ. y单 0, pitch deflection δ z单 -|δ z双 | Angle of attack α 单 It is equal to the single-channel pitch moment parameter value corresponding to the simulated angle of attack A;

[0014] when When A≤0, calculate the pitch moment parameter C of the dual-channel arbitrary control environment according to the following formula 4). mz :

[0015]

[0016] The C MZ (α 单 =-A,δ z单 =-|δ z双 |) represents the single-channel pitch moment parameter data that has the same Mach number as the dual-channel control environment under test, and the yaw deflection angle δ. y单 0, pitch deflection δ z单 -|δ z双 | Angle of attack α 单 The single-channel pitch moment parameter value is equal to the negative simulated angle of attack -A;

[0017] when When A>0, calculate the pitch moment parameter C of the dual-channel arbitrary control environment according to the following formula 5). mz :

[0018]

[0019] The C MZ (α 单 =A,δ z单 =|δ z双 |) represents the single-channel pitch moment parameter data that has the same Mach number as the dual-channel control environment under test, and the yaw deflection angle δ. y单 0, pitch deflection δz单 For |δ z双 | Angle of attack α 单 It is equal to the single-channel pitch moment parameter value corresponding to the simulated angle of attack A;

[0020] when When A≤0, calculate the pitch moment parameter C of the dual-channel arbitrary control environment according to the following formula 6). mz :

[0021]

[0022] The C MZ (α 单 =-A,δ z单 =|δ z双 |) represents the single-channel pitch moment parameter data that has the same Mach number as the dual-channel control environment under test, and the yaw deflection angle δ. y单 0, pitch deflection δ z单 For |δ z双 | Angle of attack α 单 The single-channel pitch moment parameter value is equal to the negative simulated angle of attack -A.

[0023] Beneficial effects

[0024] The testing method of this invention solves the problems of high cost (large number of test conditions) and long cycle of obtaining key aerodynamic parameters under dual-channel control of normal aerodynamic layout projectiles with a length-to-slenderness ratio of less than 20. It can convert the aerodynamic parameters under limited single-channel conditions to obtain the true dual-channel aerodynamic parameters, reduce the number of test conditions required for ground blowing tests, and thus greatly reduce the project development cost. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the aerodynamic shape of the projectile product tested by the method of the present invention; Detailed Implementation

[0026] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0027] Example

[0028] Taking the testing of the dual-channel control pitch moment parameters of a certain projectile product as an example, the structural parameters of the projectile product are as follows: Figure 1 As shown, this projectile consists of an oval projectile 1, a cylindrical projectile body 2, four leading edge fins 3 located in the middle of the cylindrical projectile body 2, and four rudder fins 4 located at the tail of the cylindrical projectile body 2. The diameter of the cylindrical projectile body 2 is D, and the total length is 6D to 8D. The four leading edge fins 3 and the four rudder fins 4 are symmetrically distributed in a cross-shaped layout. The test conditions for this projectile are shown in Table 1, with a total of 9680 tests.

[0029] Table 1 shows the test conditions for the dual-channel ground wind tunnel experiment.

[0030]

[0031] The specific testing steps using the testing method of this invention are as follows:

[0032] 1) Using wind tunnel force measurement experiments, the characteristics of the projectile at different angles of attack α under different Mach numbers and rudder deflection angles were obtained. 单 Single-channel pitch moment parameter data C MZ The specific test conditions are shown in Table 2, with a total of 880 tests conducted.

[0033] Table 2 shows the test conditions for single-channel ground wind tunnel experiments.

[0034]

[0035] 2) The angle of attack α of the dual-channel control environment 双 and sideslip angle β 双 Convert to simulated angle of attack A:

[0036] When α 双 <0 and β 双 When <0, simulated angle of attack

[0037] When α 双 >0 or β 双 When >0, simulated angle of attack

[0038] 3) When When A>0, calculate the pitch moment parameter C of the dual-channel arbitrary control environment according to the following formula 3). mz :

[0039]

[0040] Where, δ z双 For the pitch deflection angle of the dual-channel control environment, the C MZ (α 单 =A,δ z单 =-|δ z双 |) represents the single-channel pitch moment parameter data that has the same Mach number as the dual-channel control environment under test, and the yaw deflection angle δ. y单 0, pitch deflection δ z单 -|δ z双 | Angle of attack α 单 It is equal to the single-channel pitch moment parameter value corresponding to the simulated angle of attack A;

[0041] when When A≤0, calculate the pitch moment parameter C of the dual-channel arbitrary control environment according to the following formula 4). mz :

[0042]

[0043] The C MZ (α 单 =-A,δ z单 =-|δ z双 |) represents the single-channel pitch moment parameter data that has the same Mach number as the dual-channel control environment under test, and the yaw deflection angle δ. y单 0, pitch deflection δ z单 -|δ z双 | Angle of attack α 单 The single-channel pitch moment parameter value is equal to the negative simulated angle of attack -A;

[0044] when When A>0, calculate the pitch moment parameter C of the dual-channel arbitrary control environment according to the following formula 5). mz :

[0045]

[0046] The C MZ (α 单 =A,δ z单 =|δ z双 |) represents the single-channel pitch moment parameter data that has the same Mach number as the dual-channel control environment under test, and the yaw deflection angle δ. y单 0, pitch deflection δ z单 For |δ z双 | Angle of attack α 单 It is equal to the single-channel pitch moment parameter value corresponding to the simulated angle of attack A;

[0047] when When A≤0, calculate the pitch moment parameter C of the dual-channel arbitrary control environment according to the following formula 6). mz :

[0048]

[0049] The C MZ (α 单 =-A,δ z单 =|δ z双 |) represents the single-channel pitch moment parameter data that has the same Mach number as the dual-channel control environment under test, and the yaw deflection angle δ. y单 0, pitch deflection δ z单 For |δ z双 | Angle of attack α 单 The single-channel pitch moment parameter value is equal to the negative simulated angle of attack -A.

[0050] In the dual-channel control pitch moment parameter test conditions, four sets of conditions Q1 to Q4 as shown in Table 3 were selected for verification.

[0051] Table 3 Test conditions for dual-channel control pitch moment parameters

[0052] Q1 10 -5 1.52 5 -10 Q2 15 10 2.01 -10 -15 Q3 -15 -10 2.01 10 15 Q4 20 -5 2.01 -10 -10

[0053] Among them, the dual-channel pitch moment parameter value C of working condition Q1 mz The solution process is as follows:

[0054] First, let's consider the angle of attack α in condition Q1. 双 and sideslip angle β 双 Converting to a simulated angle of attack A, and substituting into equation 2), we obtain the simulated angle of attack A for condition Q1 as 11.2.

[0055] Given A = 11.2 > 0, and,

[0056] Then, by querying the single-channel pitch moment parameter data C obtained in step 1), MZ The value is calculated by linear interpolation, and the approximate value is obtained by solving the dual-channel pitch moment parameter C under working condition Q1 according to Equation 3). mz For: C mz =C MZ (α 单 =11.2,δ z =-5)·5 / 11.2

[0057] =0.7125×5 / 11.2=0.3181.

[0058] Dual-channel pitch moment parameter C under operating condition Q2 mz The solution process is as follows:

[0059] First, let's consider the angle of attack α in condition Q2. 双 and sideslip angle β 双 Converting to a simulated angle of attack A, and substituting into equation 1), we obtain the simulated angle of attack A for condition Q2 as -18°.

[0060] Given A = -18 < 0, and

[0061] Then, by querying the single-channel pitch moment parameter data C obtained in step 1), MZ The value is calculated by linear interpolation, and the approximate value is obtained by solving the dual-channel pitch moment parameter C under working condition Q2 according to Equation 4). mz For: C mz =-C MZ (α 单 =18,δ z=-10)·(-10) / (-18)

[0062] =-1.2859×10 / 18=-0.7144.

[0063] Dual-channel pitch moment parameter C under operating condition Q3 mz The solution process is as follows:

[0064] First, let's consider the angle of attack α in operating condition Q3. 双 and sideslip angle β 双 Converting to a simulated angle of attack A, and substituting into equation 2), we obtain that the simulated angle of attack A for condition Q3 is 15.8.

[0065] Given A = 18 > 0, and

[0066] Then, by querying the single-channel pitch moment parameter data C obtained in step 1), MZ The value is calculated by linear interpolation, and the approximate value is obtained by solving the dual-channel pitch moment parameter C under working condition Q3 according to Equation 5). mz For: C mz =C MZ (α 单 =18,δ z =-10)·10 / 18

[0067] =1.2859 × 10 / 18 = 0.7144

[0068] Dual-channel pitch moment parameter value C for operating condition Q4 mz The solution process is as follows:

[0069] First, the angle of attack α in condition Q4 is... 双 and sideslip angle β 双 Converting to a simulated angle of attack A and substituting into equation 1), we obtain the simulated angle of attack A for condition Q4 as -14.1.

[0070] Given A = -14.1 < 0, and,

[0071] Then, by querying the single-channel pitch moment parameter data C obtained in step 1), MZ The value is calculated by linear interpolation, and the approximate value is obtained by solving the dual-channel pitch moment parameter C under working condition Q4 according to Equation 6). mz For: C mz =-C MZ (α 单 =14.1,δ z =5)·(-10) / (-14.1)

[0072] =-0.9304×10 / 14.1=-0.6598.

[0073] Wind tunnel force measurement experiments were conducted to test the dual-channel pitching moment parameters of the projectile under operating conditions Q1 to Q4. For operating condition Q1, the value was 0.3211, and the deviation rate was -0.93% compared to the parameter obtained using the example method. For operating condition Q2, the value was -0.7558, and the deviation rate was -5.5%. For operating condition Q3, the value was 0.7678, and the deviation rate was -6.9%. For operating condition Q4, the value was -0.6243, and the deviation rate was +5.7%.

Claims

1. A method for testing pitch moment parameters using dual-channel control, characterized in that: This method is applicable to conventional aerodynamic layout projectiles with a slenderness ratio of 20 or less; The specific testing steps are as follows: 1) Using wind tunnel force measurement experiments, the characteristics of the missile body at different angles of attack under different Mach numbers and different rudder deflection angles were obtained. Single-channel pitch moment parameter data C MZ ; 2) The angle of attack α of the dual-channel control environment 双 and sideslip angle β 双 Convert to simulated angle of attack A: when and Simulated angle of attack 1) when or Simulated angle of attack 2) 3) When ,and At that time, calculate the pitch moment parameter value C of the dual-channel arbitrary control environment according to the following formula 3). mz : 3) in, For the pitch deflection angle of the dual-channel control environment, the For the single-channel pitch moment parameter data, the Mach number is the same as that of the dual-channel control environment under test, and the yaw deflection angle δ is... y单 0, pitch deflection δ z单 for Angle of attack 单 It equals the single-channel pitch moment parameter value corresponding to the simulated angle of attack A; when ,and At that time, calculate the pitch moment parameter value C of the dual-channel arbitrary control environment according to the following formula 4). mz : 4） The For the single-channel pitch moment parameter data, the Mach number is the same as that of the dual-channel control environment under test, and the yaw deflection angle δ is... y单 0, pitch deflection δ z单 for Angle of attack 单 The single-channel pitch moment parameter value is equal to the negative simulated angle of attack A. when ,and At that time, calculate the pitch moment parameter value C of the dual-channel arbitrary control environment according to the following formula 5). mz : 5) The For the single-channel pitch moment parameter data, the Mach number is the same as that of the dual-channel control environment under test, and the yaw deflection angle δ is... y单 0, pitch deflection δ z单 for Angle of attack 单 It equals the single-channel pitch moment parameter value corresponding to the simulated angle of attack A; when ,and At that time, calculate the pitch moment parameter value C of the dual-channel arbitrary control environment according to the following formula 6). mz : 6） The For the single-channel pitch moment parameter data, the Mach number is the same as that of the dual-channel control environment under test, and the yaw deflection angle δ is... y单 0, pitch deflection δ z单 for Angle of attack 单 The single-channel pitching moment parameter value is equal to the negative simulated angle of attack A.

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