CTS test system and method for large off-axis maneuvering separation

Abstract

The invention discloses a large off-axis maneuvering separation CTS test system, which is characterized in that the front / rear end of a strain balance is connected with a belly support assembly, and the belly support assembly is connected with a six-degree-of-freedom movement mechanism through a rolling movement mechanism; one rod end of an L-shaped abdominal support front rod of the abdominal support assembly is detachably connected with a connecting section, and the connecting section is detachably connected with an abdominal support rear rod; the other rod end of the L-shaped belly support front rod extends into the belly of the suspender model and is connected with the front / rear end of the strain balance; the abdominal support rear rod is connected with the six-degree-of-freedom movement mechanism through the rolling movement mechanism; the CTS test system forms a pre-deflection-free web support system and a pre-deflection web support system by replacing and adjusting the connecting section; a pre-bias-free abdominal support system is used for a CTS test in an attack angle range of 0-60 degrees or-120 degrees to-180 degrees; in the pre-bias belly bracing system, during the CTS test, a pre-bias attack angle is set for the suspension model firstly, and the pre-bias belly bracing system is used for the CTS test within the attack angle range of-60 degrees to-120 degrees. According to the invention, the capturing test method for the 0-180-degree large off-axis maneuvering separation track of the suspended object can be realized.

Description

Technical Field

[0001] The invention belongs to the technical field of experimental aerodynamics, and in particular relates to a CTS test system and method for large off-axis maneuver separation. Background Art

[0002] At present, omnidirectional projection capability is the development trend and direction of the new generation of air-launched suspensions. It requires the suspension to have the over-stall over-the-shoulder launch technology, that is, the ability to fly with rapid turns. The omnidirectional projection technology based on off-axis launch enables the carrier aircraft to project suspensions at any angle of 360° around the target. However, this omnidirectional projection is centered on the target, and the target must be in front of the aircraft during projection. The emergence of over-the-shoulder launch frees the carrier aircraft from this limitation, and can control the suspension it carries to project at any direction within 360° around the carrier aircraft, thus achieving true omnidirectional projection.

[0003] As an advanced multi-body separation ground simulation technology, the trajectory capture wind tunnel test technology organically combines wind tunnel model tests with flight mechanics. Its outstanding advantages are high prediction accuracy, the ability to obtain test results that are basically consistent with full-scale flight test data, and the ability to simulate complex separation conditions (such as auxiliary throwing force, the thrust of the external attachment itself, etc.) and special flight states (such as pitch, climb or accelerated flight, etc.) of external attachments in the test through computer software. It is suitable for launches under certain envelope flight states of the aircraft, and can directly give the external attachment separation trajectory in the test, timely evaluate the separation characteristics, and modify the relevant parameters at any time for testing when necessary. The test can not only obtain the full-scale condition separation trajectory, but also directly measure the aerodynamic load of the external attachment at each measurement point on the separation trajectory, which is conducive to the analysis and improvement of the external attachment separation characteristics. Therefore, the capture trajectory test is a type of wind tunnel test that must be carried out before the air-launched weapon model is finalized.

[0004] Limited by the movement ability and actuation space of the mechanism itself, the existing trajectory capture wind tunnel test method can usually only achieve movement in the direction of attack angle not exceeding 90° with the help of relay technology, and does not have the test simulation capability of 0-180°, and cannot meet the test requirements of large off-axis maneuverable launch after the separation of the suspension. Therefore, it is urgent to develop corresponding simulation capabilities to broaden the scope of use of this type of test technology. The present invention is proposed under such a practical background. Summary of the invention

[0005] The purpose of the present invention is to provide a CTS test system and method for large off-axis maneuvering separation. The present invention can realize a capture test method for a suspension object with a large off-axis maneuvering separation trajectory of 0 to -180 degrees.

[0006] The technical solution of the present invention is as follows: a CTS test system for large off-axis maneuverable separation, including a suspension model, a strain balance is arranged inside the suspension model, the front / rear end of the strain balance is connected to the belly support assembly, and the belly support assembly is connected to the six-degree-of-freedom motion mechanism via a rolling motion mechanism; the belly support assembly includes an L-shaped belly support front rod, one rod end of the L-shaped belly support front rod is detachably connected to a connecting section, and the connecting section is detachably connected to a belly support rear rod; the other rod end of the L-shaped belly support front rod extends into the abdomen of the suspension model and is connected to the front / rear end of the strain balance; the belly support rear rod is connected to the six-degree-of-freedom motion mechanism via a rolling motion mechanism The CTS test system is connected with a degree of freedom motion mechanism; the connection section is replaced and adjusted to make the CTS test system constitute a non-prebiased belly support system and a pre-biased belly support system; the non-prebiased belly support system is used for CTS tests with an angle of attack ranging from 0° to -60° or -120° to -180°; in the pre-biased belly support system, during the CTS test, the suspension model is first set with a pre-biased angle of attack, and the pre-biased angle of attack is any angle within the range of 0 to -180°, and the pre-biased belly support system is used for CTS tests with an angle of attack ranging from -60° to -120°; the pre-biased angle of attack is the angle between the suspension model and the horizontal plane.

[0007] In the aforementioned CTS test system for large off-axis maneuver separation, the CTS test is conducted within the angle of attack range of 0° to -60° for the belly brace system without pre-biased brace, and the front rod of the L-shaped belly brace is connected to the rear end of the strain balance; the CTS test is conducted within the angle of attack range of -60° to -90° for the belly brace system with pre-biased brace, and the front rod of the L-shaped belly brace is connected to the rear end of the strain balance; the CTS test is conducted within the angle of attack range of -90° to -120° for the belly brace system with pre-biased brace, and the front rod of the L-shaped belly brace is connected to the front end of the strain balance; the CTS test is conducted within the angle of attack range of -120° to -180° for the belly brace system without pre-biased brace, and the front rod of the L-shaped belly brace is connected to the front end of the strain balance.

[0008] In the aforementioned CTS test system for large off-axis maneuver separation, the horizontal cross-section of the support rod connecting the L-shaped belly support front rod and the suspension model is an aerodynamic surface.

[0009] In the aforementioned CTS test system for large off-axis maneuver separation, the pre-bias angle of attack is within the angle of attack range of the CTS test.

[0010] In the aforementioned CTS test system for large off-axis maneuver separation, the pre-biased angle of attack is the middle value of the angle of attack range of the CTS test.

[0011] The test method of the CTS test system for large off-axis maneuver separation described above includes the following steps:

[0012] S1. Build CTS test system based on requirements;

[0013] S2. Construct a numerical simulation correction database of the suspension model with Mach number, angle of attack and sideslip angle as variables to obtain the corrected aerodynamic quantity;

[0014] S3. The six-degree-of-freedom motion mechanism moves the suspension model in the CTS test system to the initial position and initial posture;

[0015] S4. Obtain the initial time t through the strain balance 0 The aerodynamic force and aerodynamic moment of the suspension model are calculated and corrected according to the corrected aerodynamic quantity in the numerical simulation database;

[0016] S5. According to time t 0 The aerodynamic force, aerodynamic moment, flow field airflow parameters and preset suspension parameters of the suspension model are solved by the six-degree-of-freedom motion equation to obtain the suspension model at the next moment t 1 The attitude angle and position of the suspension object are calculated by presetting the scale relationship of the suspension object parameters to obtain the suspension object model t 1 The attitude angle and position in the wind tunnel at the moment; the six-degree-of-freedom motion mechanism adjusts the suspension model in the wind tunnel to the moment t 1 The attitude angle and position of 1 The aerodynamic force, aerodynamic moment, flow field airflow parameters and preset suspension parameters are solved at the time t 2 The attitude angle and position of the suspension model in the wind tunnel; and so on, until the end of the suspension large off-axis maneuver separation movement stage t n , the simulation time or simulation travel reaches the termination value.

[0017] In the aforementioned method of using the CTS test system for large off-axis maneuver separation, the flow field airflow parameters include wind tunnel dynamic pressure, static pressure and Mach number.

[0018] In the aforementioned method of using the CTS test system for large off-axis maneuver separation, the preset suspension object parameters include the reference length and reference area of ​​the real suspension object, and the reference length and reference area of ​​the suspension object model.

[0019] In the aforementioned method of using the CTS test system for large off-axis maneuver separation, in step 2, a numerical simulation correction database is constructed as follows: numerical simulations are carried out on the individual suspension models, and the connection configurations of the belly support assembly and the suspension model under the preset test aerodynamic parameter range, angle of attack range of 0 to -180°, and sideslip angle range of -10° to 10°, and the corrected aerodynamic quantities are calculated based on the aerodynamic quantities obtained by simulation and the aerodynamic quantities of the connection configuration obtained by measurement; by adjusting parameters, an optimizable Gaussian regression method is used to interpolate the corrected aerodynamic quantities under the corresponding Mach number, angle of attack, and sideslip angle conditions, and the corresponding aerodynamic correction data are extracted to construct a numerical simulation correction database.

[0020] In the method of using the CTS test system for large off-axis maneuver separation described above, in step 2, the aerodynamic quantity A is corrected R Calculated according to the following formula:

[0021] A R =A 0 +(A 2 -A 1 )

[0022] In the formula, A 0 is the measured aerodynamic quantity of the connection configuration, A 1 is the aerodynamic quantity of the connection configuration obtained by numerical simulation, A 2 is the aerodynamic quantity of a single suspension model obtained by numerical simulation.

[0023] Beneficial effects of the present invention:

[0024] 1. The present invention provides a capture test method for realizing a 0-180° large off-axis maneuvering separation trajectory of a suspended object in a wind tunnel. In the capture trajectory wind tunnel test, the wind tunnel simulation of the large off-axis maneuvering launch process of the suspended object can be realized by relay mode, and a method and specific measures for correcting the model shape damage and support interference caused by the belly support are proposed;

[0025] 2. The trajectory capture method of the present invention is used to carry out wind tunnel tests to obtain the trajectory and attitude angle changes of the suspension object during the large off-axis maneuvering separation process relative to the aircraft, and determine the safety of separation; the present invention has the advantage of simulating the large off-axis maneuvering separation process of the suspension object with little disturbance. In addition, the present invention has developed a CTS (capture trajectory) test system for the large off-axis maneuvering separation of the suspension object, and established a new correction method;

[0026] 3. The present invention can realize the change of the angle of attack direction of the suspension model in the range of 0 to -180° in the wind tunnel trajectory capture test, obtain the trajectory and attitude angle changes of the entire rollover maneuver process, greatly broaden the test capability, obtain more complete test data, and develop a numerical correction method to correct the support interference of the belly support model, thereby ensuring the reliability and accuracy of the test results. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of the trajectory capture CTS test of the present invention;

[0028] Figure 2 It is a schematic diagram of the connection between the non-pre-biased abdominal support system of the present invention and the rear end of the strain balance;

[0029] Figure 3 It is a schematic diagram of the connection between the pre-biased abdominal support system of the present invention and the rear end of the strain balance;

[0030] Figure 4 It is a schematic diagram of the connection between the non-prebiased abdominal support system of the present invention and the front end of the strain balance;

[0031] Figure 5The present invention is a schematic diagram of the connection between the pre-biased abdominal support system and the front end of the strain balance. DETAILED DESCRIPTION

[0032] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0033] Example 1. A CTS test system for large off-axis maneuver separation, see Figure 1-Figure 5 , including a suspension model 1, a strain balance 2 is arranged inside the suspension model 1, the front / rear end of the strain balance 2 is connected to the belly support assembly 3, and the belly support assembly 3 is connected to the six-degree-of-freedom motion mechanism 5 via a rolling motion mechanism 4; the belly support assembly 3 includes an L-shaped belly support front rod 31, one rod end of the L-shaped belly support front rod 31 is detachably connected to a connecting section 32, and the connecting section 32 is detachably connected to a belly support rear rod 33; the other rod end of the L-shaped belly support front rod 31 extends into the abdomen of the suspension model 1 and is connected to the front / rear end of the strain balance 2; the belly support rear rod 33 is connected to the six-degree-of-freedom motion mechanism 5 via a rolling motion mechanism 4 The connecting section 32 is replaced and adjusted to make the CTS test system constitute a non-prebiased abdominal support system and a pre-biased abdominal support system; the non-prebiased abdominal support system is used for CTS tests with an angle of attack ranging from 0° to -60° or -120° to -180°; in the pre-biased abdominal support system, during the CTS test, the suspension model 1 is first set with a pre-biased angle of attack, and the pre-biased angle of attack is any angle within the range of 0 to -180°, and the pre-biased abdominal support system is used for CTS tests with an angle of attack ranging from -60° to -120°; the pre-biased angle of attack is the angle between the suspension model 1 and the horizontal plane.

[0034] The strain balance 2 is used to measure the aerodynamic force on the suspension model 1 during the test, and provide the aerodynamic input before correction for the trajectory capture solution program.

[0035] In the non-prebiased abdominal support system, the axis of the abdominal support rear rod 33 is parallel to the axis of the suspension model 1;

[0036] The aforementioned non-prebiased abdominal brace system is subjected to a CTS test within the angle of attack range of 0° to -60°, and the L-shaped abdominal brace front rod 31 is connected to the rear end of the strain balance 2; the pre-biased abdominal brace system is subjected to a CTS test within the angle of attack range of -60° to -90°, and the L-shaped abdominal brace front rod 31 is connected to the rear end of the strain balance 2; the pre-biased abdominal brace system is subjected to a CTS test within the angle of attack range of -90° to -120°, and the L-shaped abdominal brace front rod 31 is connected to the front end of the strain balance 2; the non-prebiased abdominal brace system is subjected to a CTS test within the angle of attack range of -120° to -180°, and the L-shaped abdominal brace front rod 31 is connected to the front end of the strain balance 2.

[0037] The horizontal cross-section of the support rod connecting the aforementioned L-shaped belly support front rod 31 and the suspension model 1 is a pneumatic surface to reduce support interference.

[0038] The aforementioned pre-bias angle of attack is within the angle of attack range of the CTS test.

[0039] Preferably, the aforementioned pre-bias angle of attack is a middle value of the angle of attack range of the CTS test.

[0040] The test method of the CTS test system for large off-axis maneuver separation described above includes the following steps:

[0041] S1. Build CTS test system based on requirements;

[0042] S2. Construct a numerical simulation correction database of the suspension model 1 with Mach number, angle of attack and sideslip angle as variables to obtain the corrected aerodynamic quantity;

[0043] S3. The six-degree-of-freedom motion mechanism 5 moves the suspension model 1 in the CTS test system to the initial position and initial posture;

[0044] S4. Obtain the initial time t through the strain balance 2 0 The aerodynamic force and aerodynamic moment of the suspension model 1 are corrected according to the corrected aerodynamic quantity in the numerical simulation database; to avoid the support interference of the belly support component 3

[0045] S5. According to time t 0 The aerodynamic force, aerodynamic moment, flow field airflow parameters and preset suspension parameters of the suspension model 1 are solved by the six-degree-of-freedom motion equation to obtain the suspension model 1 at the next moment t 1 The attitude angle and position of the suspension object are calculated by the scaled relationship of the preset suspension object parameters to obtain the suspension object model 1t 1 The six-degree-of-freedom motion mechanism 5 adjusts the suspension model 1 in the wind tunnel to the time t 1 The attitude angle and position of 1 The aerodynamic force, aerodynamic moment, flow field airflow parameters and preset suspension parameters are solved at the time t 2 The attitude angle and position of the suspension model 1 in the wind tunnel; and so on, until the end of the suspension large off-axis maneuver separation movement stage t n , the simulation time or simulation travel reaches the termination value.

[0046] The aforementioned flow field airflow parameters include wind tunnel dynamic pressure, static pressure and Mach number.

[0047] The aforementioned preset hanging object parameters include a reference length and a reference area of ​​a real hanging object, and a reference length and a reference area of ​​a hanging object model.

[0048] In the aforementioned step 2, the numerical simulation correction database is constructed as follows: numerical simulations are carried out on the connection configurations of the separate suspension model 1, the belly support assembly 3 and the suspension model 4 under the preset test aerodynamic parameter range, the angle of attack range of 0 to -180°, and the sideslip angle range of -10° to 10°, and the corrected aerodynamic quantities are calculated based on the aerodynamic quantities obtained by simulation and the aerodynamic quantities of the connection configuration obtained by measurement; by adjusting parameters, the corrected aerodynamic quantities under the corresponding Mach number, angle of attack and sideslip angle conditions are interpolated using the optimizable Gaussian regression method, the corresponding aerodynamic correction data are extracted, and a numerical simulation correction database is constructed.

[0049] In the above step 2, the pneumatic quantity A is corrected R Calculated according to the following formula:

[0050] A R =A 0 +(A 2 -A 1 )

[0051] In the formula, A 0 is the measured aerodynamic quantity of the connection configuration, A 1 is the aerodynamic quantity of the connection configuration obtained by numerical simulation, A 2 is the aerodynamic quantity of the single suspension model 1 obtained by numerical simulation.

[0052] For example, under certain conditions, the aerodynamic quantity of the suspension model 4 connecting head support mechanism test is A 0 , at this time, the angle of the model under the local wind axis is (ɑ, β); under the same conditions, through the optimized Gaussian interpolation, the aerodynamic quantity corresponding to the belly support interference at (ɑ, β) can be obtained from the numerical simulation correction database as A 1 ; Under the same conditions, through the optimized Gaussian interpolation, the aerodynamic quantity corresponding to the clean suspension model at (ɑ, β) can be obtained from the numerical simulation correction database as A 2 , the corrected aerodynamic quantity A R =A 0 -(A 2 -A 1 ). The corrected aerodynamic quantity A R The six-degree-of-freedom dynamic equation of the suspended object is input and solved to obtain its position and posture in the wind tunnel at the next moment. The support interference caused by the belly support assembly 3 can be corrected by the above method.

[0053] In the present invention, it is necessary to consider non-interference with the opening of the suspension model during design. The strut size and the opening form and size of the suspension model at the position where the belly link extends are determined by estimating the aerodynamic load and corresponding elastic deformation of the model, so as to ensure that the suspension model does not collide with the belly support strut during the entire test process and to minimize the damage to the original appearance of the suspension model.

[0054] In the present invention, the number of segments and specific segment angles of the angle of attack range are not limited. Specifically, within the angle of attack range of 0° to -45°, there is no connection between the pre-biased belly support system and the strain balance, within the angle of attack range of -45° to -135°, there is a connection between the pre-biased belly support system and the strain balance, and within the angle of attack range of -135° to -180°, there is no connection between the pre-biased belly support system and the strain balance. It is particularly important to point out that the displacements of the model in the three directions and the attitude angles in the three directions at the relay point remain exactly the same.

[0055] The above is only a specific embodiment of the present invention, and the present invention is described in detail. The unexplained part is a conventional technology. However, the protection scope of the present invention is not limited to this. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. The protection scope of the present invention shall be based on the protection scope of the claims.

Claims

1. A CTS test system for large off-axis maneuver separation, characterized in that: The invention comprises a suspension model (1), wherein a strain balance (2) is arranged inside the suspension model (1), wherein the front / rear end of the strain balance (2) is connected to a belly support assembly (3), and the belly support assembly (3) is connected to a six-degree-of-freedom motion mechanism (5) via a rolling motion mechanism (4); the belly support assembly (3) comprises an L-shaped belly support front rod (31), wherein one rod end of the L-shaped belly support front rod (31) is detachably connected to a connecting section (32), and the connecting section (32) is detachably connected to a belly support rear rod (33); the other rod end of the L-shaped belly support front rod (31) extends into the abdomen of the suspension model (1) and is connected to the front / rear end of the strain balance (2); the belly support rear rod (33) The rolling motion mechanism (4) is connected to the six-degree-of-freedom motion mechanism (5); the CTS test system is configured as a non-prebiased belly support system and a prebiased belly support system by replacing and adjusting the connecting section (32); the non-prebiased belly support system is used for CTS tests with an angle of attack ranging from 0° to -60° or -120° to -180°; in the prebiased belly support system, during the CTS test, the suspension model (1) is first set with a prebiased angle of attack, and the prebiased angle of attack is any angle within the range of 0 to -180°, and the prebiased belly support system is used for CTS tests with an angle of attack ranging from -60° to -120°; the prebiased angle of attack is the angle between the suspension model (1) and the horizontal plane.

2. The CTS test system for large off-axis maneuver separation according to claim 1, characterized in that: The CTS test of the non-prebiased belly brace system is carried out within the range of 0° to -60° angle of attack, and the L-shaped belly brace front rod (31) is connected to the rear end of the strain balance (2); the CTS test of the prebiased belly brace system is carried out within the range of -60° to -90° angle of attack, and the L-shaped belly brace front rod (31) is connected to the rear end of the strain balance (2); the CTS test of the prebiased belly brace system is carried out within the range of -90° to -120° angle of attack, and the L-shaped belly brace front rod (31) is connected to the front end of the strain balance (2); the CTS test of the non-prebiased belly brace system is carried out within the range of -120° to -180° angle of attack, and the L-shaped belly brace front rod (31) is connected to the front end of the strain balance (2).

3. The CTS test system for large off-axis maneuver separation according to claim 1, characterized in that: The horizontal cross section of the support rod connecting the L-shaped belly support front rod (31) and the suspension model (1) is a pneumatic surface.

4. The CTS test system for large off-axis maneuver separation according to claim 2, characterized in that: The pre-biased angle of attack is within the angle of attack range of the CTS test.

5. The CTS test system for large off-axis maneuver separation according to claim 4, characterized in that: The pre-biased angle of attack is the middle value of the angle of attack range of the CTS test.

6. A test method for a CTS test system for large off-axis maneuver separation as claimed in any one of claims 1 to 5, characterized in that: The steps include: S1. Build CTS test system based on requirements; S2. construct a numerical simulation correction database of the suspension model (1) with Mach number, angle of attack and sideslip angle as variables to obtain the corrected aerodynamic quantity; S3. The six-degree-of-freedom motion mechanism (5) moves the suspension model (1) in the CTS test system to an initial position and initial posture; S4. Obtaining the aerodynamic force and aerodynamic moment of the suspension model (1) at the initial time t0 by means of a strain balance (2), and correcting the aerodynamic force according to the corrected aerodynamic quantity in the numerical simulation database; S5. According to the aerodynamic force, aerodynamic moment, flow field and airflow parameters of the suspension model (1) at time t0 and the preset suspension parameters, the six-degree-of-freedom motion equation is solved to obtain the attitude angle and position of the suspension model (1) at the next time t1, and the attitude angle and position of the suspension model (1) in the wind tunnel at time t1 are obtained through the scaled relationship calculated by the preset suspension parameters; the six-degree-of-freedom motion mechanism (5) adjusts the suspension model (1) in the wind tunnel to the attitude angle and position at time t1; then, based on the aerodynamic force, aerodynamic moment, flow field and airflow parameters at time t1 and the preset suspension parameters, the attitude angle and position of the suspension model (1) in the wind tunnel at time t2 are solved; and so on, until the end of the suspension large off-axis maneuvering separation movement stage at time t n , the simulation time or simulation travel reaches the termination value.

7. The method for using the CTS test system for large off-axis maneuver separation according to claim 6, characterized in that: The flow field airflow parameters include wind tunnel dynamic pressure, static pressure and Mach number.

8. The method for using the CTS test system for large off-axis maneuver separation according to claim 6, characterized in that: The preset hanging object parameters include a reference length and a reference area of ​​a real hanging object, and a reference length and a reference area of ​​a hanging object model.

9. The method for using the CTS test system for large off-axis maneuver separation according to claim 6, characterized in that: In step 2, a numerical simulation correction database is constructed as follows: numerical simulations are performed on the connection configurations of the individual suspension model (1), the belly support assembly (3) and the suspension model (4) under the conditions of a preset test aerodynamic parameter range, an angle of attack range of 0 to -180°, and a sideslip angle range of -10° to 10°, respectively; based on the aerodynamic quantities obtained by simulation and the aerodynamic quantities of the connection configuration obtained by measurement, the corrected aerodynamic quantities are calculated; by adjusting parameters, an optimizable Gaussian regression method is used to interpolate the corrected aerodynamic quantities under the corresponding Mach number, angle of attack and sideslip angle conditions, and the corresponding aerodynamic correction data are extracted to construct a numerical simulation correction database.

10. The method for using the CTS test system for large off-axis maneuver separation according to claim 9, characterized in that: In step 2, correct the aerodynamic quantity A R Calculated according to the following formula: <h2 style=";text-align:left;direction:ltr">A<h2 style=";text-align:left;direction:ltr"> R <h2 style=";text-align:left;direction:ltr"> (A0+(A2-A1) Wherein, A0 is the aerodynamic quantity of the connection configuration obtained by measurement, A1 is the aerodynamic quantity of the connection configuration obtained by numerical simulation, and A2 is the aerodynamic quantity of the separate suspension model (1) obtained by numerical simulation.

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