Double-body track capturing wind tunnel test method considering unsteady effect of disturbing flow field

Abstract

The invention belongs to the technical field of wind tunnel tests, and discloses a dual-body track capturing wind tunnel test method considering an unsteady effect of a disturbing flow field. The invention discloses a dual-body capture trajectory wind tunnel test method considering an unsteady effect of a disturbing flow field. The method comprises the following steps: determining a dynamic derivative needing to be simulated; calculating a dynamic derivative under the disturbing flow field by adopting a numerical forced oscillation method; designing and manufacturing a test device; installing a test device; starting the separated body model jet flow simulation device; starting a wind tunnel, and performing a double-body track capturing wind tunnel test; and analyzing and processing dual-body capture track wind tunnel test data. According to the dual-body capture track wind tunnel test method considering the unsteady effect of the disturbing flow field, dynamic characteristic influence quantity taking a key dynamic derivative as a characterization parameter is coupled in a capture track test process with relatively high precision, so that dual-body dynamic aerodynamic characteristics and separation tracks which are closer to a real separation process are obtained; the test simulation accuracy is improved, and the engineering practical value is achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of wind tunnel tests, and in particular relates to a twin-body capture trajectory wind tunnel test method taking into account the unsteady effects of an interfering flow field. Background Art

[0002] The twin-body capture track wind tunnel test technology is based on the single-body capture track ( Captive Trajectory Simulation, CTS ) technology, it can synchronously simulate the motion trajectory and aerodynamic characteristics of the separated body and the main body when the two bodies are separated in the wind tunnel.

[0003] The twin-body synchronous separation capture trajectory wind tunnel test technology is a controllable trajectory test technology. It can simulate the complex separation conditions and special flight states of the main body and the separated body in the wind tunnel test through computer software. It can directly give the separation trajectory of the main body and the separated body in the wind tunnel test and timely evaluate the separation characteristics. The twin-body synchronous separation capture trajectory wind tunnel test technology can not only obtain the separation trajectory, but also directly measure the aerodynamic loads of the main body and the separated body at each separation trajectory point, which is conducive to the analysis of the aerodynamic characteristics of the main body and the separated body, and its prediction accuracy is high. Usually, the wind tunnel test results can be used as benchmark data for the study of multi-body separation problems.

[0004] Despite the above advantages, the twin-body synchronous separation capture trajectory wind tunnel test technology is essentially a steady-state technology. It cannot measure the angular motion-induced effects of the main body and the separated body, especially for the main body and the separated body with jet flow. During the twin-body separation process, when the unsteady effects caused by the large angular velocity are obvious, the capture trajectory test results, as a steady-state result, cannot truly reflect the unsteady characteristics of the twin-body separation process, which can easily lead to simulation distortion.

[0005] In order to simulate the above-mentioned twin-body separation process with jet and obvious unsteady effects, it is urgent to develop a twin-body capture trajectory wind tunnel test method that takes into account the unsteady effects of the interfering flow field. Summary of the invention

[0006] The technical problem to be solved by the present invention is to provide a twin-body capture trajectory wind tunnel test method taking into account the unsteady effects of the interfering flow field based on the dynamic derivative, an important characterization parameter of the unsteady effect, so as to overcome the defects of the prior art.

[0007] The twin-body capture trajectory wind tunnel test method considering the unsteady effect of the interference flow field of the present invention is based on the existing twin-body capture trajectory test system, which is used to support the twin-body model of the main body and the separated body and perform trajectory simulation; the twin-body capture trajectory test system includes a six-degree-of-freedom CTS mechanism located at the upper part, a five-degree-of-freedom CTS mechanism located at the lower part, an upper computer, a lower computer, a data acquisition system, a real-time pneumatic solution module and a control system; wherein the six degrees of freedom of the six-degree-of-freedom CTS mechanism are respectively X 1 axis movement, Y 1 axis movement, Z 1 axis movement, α 1 angle rotation, β 1 angle rotation and c 1 angular rotation; the five degrees of freedom of the five-degree-of-freedom CTS mechanism are X 2-axis movement, Y 2-axis movement, α 2 angle rotation, β 2 Angular Rotation and c 2-angle rotation; including the following steps: S10. Determine the dynamic derivative to be simulated; According to the motion characteristics of the separation body and the main body during separation, the dynamic derivatives to be simulated are determined, and the dynamic derivatives include direct damping derivatives, time difference derivatives and cross derivatives; S20. Calculate the dynamic derivatives under the disturbed flow field using the numerical forced oscillation method; The numerical forced oscillation method is used to calculate the dynamic derivatives of the flow field with jet-type two-body separation disturbance. S30. Design and manufacture test equipment; The test device includes a separation model, a separation model support, a six-component force balance of the separation model, a separation model jet simulation device, and a main body model, a main body model support, and a six-component force balance of the main body model; S40. Install the test device; The separation model is mounted on a five-degree-of-freedom CTS mechanism through a separation model support, and a separation model jet simulation device and a separation model six-component force balance are built in the separation model; the main body model is mounted on a six-degree-of-freedom CTS mechanism through a main body model support, and a main body model six-component force balance is built in the main body model; the position and attitude angle of the separation model and the main body model are given respectively, the separation model is moved to the separation initial posture point S1, and the main body model is moved to the separation initial posture point X1; the separation model and the main body model are collectively referred to as a double-body model; S50. Start the separation model jet simulation device; Start the separation model jet simulation device to perform jet flow until the jet flow field is stable; S60. Start the wind tunnel and conduct a twin-body capture trajectory wind tunnel test; Start the wind tunnel, and after the wind tunnel inflow field stabilizes, t Starting from time 1, the aerodynamic data of the twin-body model at the separation initial posture points S1 and X1 are collected simultaneously; then the twin-body model is continuously controlled from its respective separation initial posture points S1 and X1, and the aerodynamic data of the twin-body model is collected synchronously; the continuous trajectory control process is as follows: First, the next moment is calculated by aerodynamic solution based on the aerodynamic data of the separated initial pose points S1 and X1 t 2, the posture and velocity of the corresponding trajectory points S2 and X2 are used for motion allocation; the trajectory of S1~S2 and the trajectory of X1~X2 are planned, and N measurement points are set in the trajectory of S1~S2 and the trajectory of X1~X2, respectively, with N≥10; secondly, the six-degree-of-freedom CTS mechanism and the five-degree-of-freedom CTS mechanism drive the separation model and the main model to move according to the planned trajectory respectively, and data collection, pneumatic solution, and motion are performed at the Nth measurement point before the double-body model moves from the initial posture points S1 and X1 of the separation to the trajectory points S2 and X2. Allocate and plan the S2~S3 and X2~X3 trajectories in the same way as the S1~S2 and X1~X2 trajectories; again, before reaching the trajectory points S2 and X2, the twin-body model always moves according to the previously planned trajectories, and when moving to the trajectory points S2 and X2, the twin-body model moves according to the planned S2~S3 and X2~X3 trajectories; then, the same method is used until the twin-body model moves to the final trajectory points Sn and Xn; finally, the twin-body capture trajectory wind tunnel test is completed and the wind tunnel is closed; S70. Analyze and process twin-body capture trajectory wind tunnel test data; In the twin-body capture trajectory wind tunnel test, the twin-body models completed their respective separation trajectory captures, and the attitude angles and displacements (θ, ψ, φ, X , Y , Z ) The separation trajectory and aerodynamic characteristics with the separation time t; where θ is the pitch angle, ψ is the yaw angle, φ is the roll angle, X is the axial displacement, Y is the normal displacement, Z is the lateral displacement; the aerodynamic characteristics and separation trajectories of the separation body model and the main body model considering the unsteady effects of the disturbing flow field are obtained through analysis and processing.

[0008] Furthermore, the double-body capture trajectory test system distributes the Z-direction displacement of the five-degree-of-freedom CTS mechanism to the Z-direction displacement of the six-degree-of-freedom CTS mechanism, solving the problem that the five-degree-of-freedom CTS mechanism does not have ZIn order to solve the problem of freedom in the Z direction, on the basis of ensuring that the relative motion position relationship of the twin-body model in the Z direction remains unchanged, the six-degree-of-freedom motion of each twin-body model is realized, that is, the trajectory capture of the twelve degrees of freedom of the twin-body model as a whole is achieved.

[0009] Furthermore, the numerical forced oscillation method described in S20 comprises the following steps: S21. The aerodynamic forces and moments on the body axis are obtained by solving the time-accurate unsteady RANS equations in the jet two-body separation interference flow field; S22. Taking the free flow density, free flow velocity, reference length and reference area as reference quantities, the aerodynamic force and moment under the body axis system are dimensionless to obtain the aerodynamic force coefficient and moment coefficient; S23. The aerodynamic coefficients and moment coefficients are linearly processed using linear flight mechanics theory to obtain the dynamic derivatives under the disturbed flow field that needs to be simulated.

[0010] Furthermore, the dynamic derivative described in S20 is a damping derivative.

[0011] Furthermore, the aerodynamic solution described in S60 includes the following steps: When the twin-body capture trajectory test system collects data, the aerodynamic loads of the twin-body models under the interference of the jet are measured by the six-component measuring balances of the twin-body models, and the aerodynamic coefficients of the twin-body models are calculated by the lower computer. According to the initial conditions and input parameters of the twin-body models, the six-degree-of-freedom rigid body motion equations of the full-scale twin-body models are solved by the lower computer to obtain the acceleration of the twin-body models at the initial position and attitude angle, and the velocity, position and attitude angle of the twin-body models after the time interval Δt are obtained by integration, and then converted to the position and velocity of the trajectory points S2 and X2 of the twin-body models in the wind tunnel through the sky and the earth.

[0012] Furthermore, the initial conditions are the starting position, angle and speed; the input parameters are the attitude angle, flight altitude, Mach number of each of the two-body models, and the mass, moment of inertia, damping derivative, thrust and ejection force of each of the two-body models.

[0013] Furthermore, a direct damping torque is added to the six-degree-of-freedom rigid body motion equation, and the direct damping torque is calculated by a direct damping torque coefficient in combination with a corresponding reference dimension, and the direct damping torque coefficient is calculated by a corresponding dynamic derivative and a dimensionless angular velocity.

[0014] Furthermore, the trajectory capture described in S70 sets the gravity influence amount according to the test requirements.

[0015] The twin-body capture trajectory wind tunnel test method of the present invention, which takes into account the unsteady effects of the interfering flow field, couples the dynamic characteristic influencing quantities with key dynamic derivatives as characterization parameters during the capture trajectory test with high precision, thereby obtaining the twin-body dynamic aerodynamic characteristics and separation trajectory that are closer to the actual separation process, thereby improving the accuracy of the test simulation and having practical engineering value. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The present invention is a flow chart of a twin-body capture trajectory wind tunnel test method taking into account the unsteady effects of the interfering flow field. DETAILED DESCRIPTION

[0017] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0018] Example: Figure 1 As shown, the twin-body capture trajectory wind tunnel test method considering the unsteady effect of the interference flow field of this embodiment is based on the existing twin-body capture trajectory test system, which is used to support the twin-body model of the main body and the separated body and perform trajectory simulation; the twin-body capture trajectory test system includes a six-degree-of-freedom CTS mechanism located at the upper part, a five-degree-of-freedom CTS mechanism located at the lower part, an upper computer, a lower computer, a data acquisition system, a real-time pneumatic solution module and a control system; wherein the six degrees of freedom of the six-degree-of-freedom CTS mechanism are respectively X 1 axis movement, Y 1 axis movement, Z 1 axis movement, α 1 angle rotation, β 1 angle rotation and c 1 angular rotation; the five degrees of freedom of the five-degree-of-freedom CTS mechanism are X 2-axis movement, Y 2-axis movement, α 2 angle rotation, β 2 Angular Rotation and c 2-angle rotation; including the following steps: S10. Determine the dynamic derivative to be simulated; According to the motion characteristics of the separation body and the main body during separation, the dynamic derivatives to be simulated are determined, and the dynamic derivatives include direct damping derivatives, time difference derivatives and cross derivatives; S20. Calculate the dynamic derivatives under the disturbed flow field using the numerical forced oscillation method; The numerical forced oscillation method is used to calculate the dynamic derivatives of the flow field with jet separation. S30. Design and manufacture test equipment; The test device includes a separation model, a separation model support, a six-component force balance of the separation model, a separation model jet simulation device, and a main body model, a main body model support, and a six-component force balance of the main body model; S40. Install the test device; The separation model is mounted on a five-degree-of-freedom CTS mechanism through a separation model support, and a separation model jet simulation device and a separation model six-component force balance are built in the separation model; the main body model is mounted on a six-degree-of-freedom CTS mechanism through a main body model support, and a main body model six-component force balance is built in the main body model; the position and attitude angle of the separation model and the main body model are given respectively, the separation model is moved to the separation initial posture point S1, and the main body model is moved to the separation initial posture point X1; the separation model and the main body model are collectively referred to as a double-body model; S50. Start the separation model jet simulation device; Start the separation model jet simulation device to perform jet flow until the jet flow field is stable; S60. Start the wind tunnel and conduct a twin-body capture trajectory wind tunnel test; Start the wind tunnel, and after the wind tunnel inflow field stabilizes, t Starting from time 1, the aerodynamic data of the twin-body model at the separation initial posture points S1 and X1 are collected simultaneously; then the twin-body model is continuously controlled from its respective separation initial posture points S1 and X1, and the aerodynamic data of the twin-body model is collected synchronously; the continuous trajectory control process is as follows: First, the next moment is calculated by aerodynamic solution based on the aerodynamic data of the separated initial pose points S1 and X1 t 2, the posture and velocity of the corresponding trajectory points S2 and X2 are used for motion allocation; the trajectory of S1~S2 and the trajectory of X1~X2 are planned, and N measurement points are set in the trajectory of S1~S2 and the trajectory of X1~X2, respectively, with N≥10; secondly, the six-degree-of-freedom CTS mechanism and the five-degree-of-freedom CTS mechanism drive the separation model and the main model to move according to the planned trajectory respectively, and data collection, pneumatic solution, and motion are performed at the Nth measurement point before the double-body model moves from the initial posture points S1 and X1 of the separation to the trajectory points S2 and X2. Allocate and plan the S2~S3 and X2~X3 trajectories in the same way as the S1~S2 and X1~X2 trajectories; again, before reaching the trajectory points S2 and X2, the twin-body model always moves according to the previously planned trajectories, and when moving to the trajectory points S2 and X2, the twin-body model moves according to the planned S2~S3 and X2~X3 trajectories; then, the same method is used until the twin-body model moves to the final trajectory points Sn and Xn; finally, the twin-body capture trajectory wind tunnel test is completed and the wind tunnel is closed; S70. Analyze and process twin-body capture trajectory wind tunnel test data; In the twin-body capture trajectory wind tunnel test, the twin-body models completed their respective separation trajectory captures, and the attitude angles and displacements (θ, ψ, φ,X , Y , Z ) The separation trajectory and aerodynamic characteristics with the separation time t; where θ is the pitch angle, ψ is the yaw angle, φ is the roll angle, X is the axial displacement, Y is the normal displacement, Z is the lateral displacement; the aerodynamic characteristics and separation trajectories of the separation body model and the main body model considering the unsteady effects of the disturbing flow field are obtained through analysis and processing.

[0019] Furthermore, the double-body capture trajectory test system distributes the Z-direction displacement of the five-degree-of-freedom CTS mechanism to the Z-direction displacement of the six-degree-of-freedom CTS mechanism, solving the problem that the five-degree-of-freedom CTS mechanism does not have Z In order to solve the problem of freedom in the Z direction, on the basis of ensuring that the relative motion position relationship of the twin-body model in the Z direction remains unchanged, the six-degree-of-freedom motion of each twin-body model is realized, that is, the trajectory capture of the twelve degrees of freedom of the twin-body model as a whole is achieved.

[0020] Furthermore, the numerical forced oscillation method described in S20 comprises the following steps: S21. The aerodynamic forces and moments on the body axis are obtained by solving the time-accurate unsteady RANS equations in the jet two-body separation interference flow field; S22. Taking the free flow density, free flow velocity, reference length and reference area as reference quantities, the aerodynamic force and moment under the body axis system are dimensionless to obtain the aerodynamic force coefficient and moment coefficient; S23. The aerodynamic coefficients and moment coefficients are linearly processed using linear flight mechanics theory to obtain the dynamic derivatives under the disturbed flow field that needs to be simulated.

[0021] Furthermore, the dynamic derivative described in S20 is a damping derivative.

[0022] Furthermore, the aerodynamic solution described in S60 includes the following steps: When the twin-body capture trajectory test system collects data, the aerodynamic loads of the twin-body models under the interference of the jet are measured by the six-component measuring balances of the twin-body models, and the aerodynamic coefficients of the twin-body models are calculated by the lower computer. According to the initial conditions and input parameters of the twin-body models, the six-degree-of-freedom rigid body motion equations of the full-scale twin-body models are solved by the lower computer to obtain the acceleration of the twin-body models at the initial position and attitude angle, and the velocity, position and attitude angle of the twin-body models after the time interval Δt are obtained by integration, and then converted to the position and velocity of the trajectory points S2 and X2 of the twin-body models in the wind tunnel through the sky and the earth.

[0023] Furthermore, the initial conditions are the starting position, angle and speed; the input parameters are the attitude angle, flight altitude, Mach number of each of the two-body models, and the mass, moment of inertia, damping derivative, thrust and ejection force of each of the two-body models.

[0024] Furthermore, a direct damping torque is added to the six-degree-of-freedom rigid body motion equation, and the direct damping torque is calculated by a direct damping torque coefficient in combination with a corresponding reference dimension, and the direct damping torque coefficient is calculated by a corresponding dynamic derivative and a dimensionless angular velocity.

[0025] Furthermore, the trajectory capture described in S70 sets the gravity influence amount according to the test requirements.

[0026] Although the embodiments of the present invention have been disclosed as above, they are not limited to the applications listed in the specification and implementation modes. For those familiar with the art, all features disclosed in the present invention, or steps in all methods or processes disclosed, except for mutually exclusive features and / or steps, can be combined in any way without departing from the principles of the present invention. The present invention is not limited to the specific details and illustrations shown and described herein.

Claims

1. A twin-body capture trajectory wind tunnel test method considering the unsteady effect of the interfering flow field is based on the existing twin-body capture trajectory test system, which is used to support the twin-body model of the main body and the separated body and perform trajectory simulation; the twin-body capture trajectory test system includes a six-degree-of-freedom CTS mechanism located at the upper part, a five-degree-of-freedom CTS mechanism located at the lower part, a host computer, a slave computer, a data acquisition system, a real-time aerodynamic solution module and a control system; wherein, The six degrees of freedom of the six-degree-of-freedom CTS mechanism are: X 1 axis movement, Y 1 axis movement, Z 1 axis movement, α 1 angle rotation, β 1 angle rotation and γ 1 angular rotation; the five degrees of freedom of the five-degree-of-freedom CTS mechanism are X 2-axis movement, Y 2-axis movement, α 2 angle rotation, β 2 Angular Rotation and γ 2-angle rotation; characterized in that it includes the following steps: S10. Determine the dynamic derivative to be simulated; According to the motion characteristics of the separation body and the main body during separation, the dynamic derivatives to be simulated are determined, and the dynamic derivatives include direct damping derivatives, time difference derivatives and cross derivatives; S20. Calculate the dynamic derivatives under the disturbed flow field using the numerical forced oscillation method; The numerical forced oscillation method is used to calculate the dynamic derivatives of the flow field with jet separation. S30. Design and manufacture test equipment; The test device includes a separation model, a separation model support, a six-component force balance of the separation model, a separation model jet simulation device, and a main body model, a main body model support, and a six-component force balance of the main body model; S40. Install the test device; The separation model is mounted on a five-degree-of-freedom CTS mechanism through a separation model support, and a separation model jet simulation device and a separation model six-component force balance are built in the separation model; the main body model is mounted on a six-degree-of-freedom CTS mechanism through a main body model support, and a main body model six-component force balance is built in the main body model; the position and attitude angle of the separation model and the main body model are given respectively, the separation model is moved to the separation initial posture point S1, and the main body model is moved to the separation initial posture point X1; the separation model and the main body model are collectively referred to as a double-body model; S50. Start the separation model jet simulation device; Start the separation model jet simulation device to perform jet flow until the jet flow field is stable; S60. Start the wind tunnel and conduct a twin-body capture trajectory wind tunnel test; Start the wind tunnel, and after the wind tunnel inflow field stabilizes, t Starting from time 1, the aerodynamic data of the twin-body model at the separation initial posture points S1 and X1 are collected simultaneously; then the twin-body model is continuously controlled from its respective separation initial posture points S1 and X1, and the aerodynamic data of the twin-body model is collected synchronously; the continuous trajectory control process is as follows: First, the next moment is calculated by aerodynamic solution based on the aerodynamic data of the separated initial pose points S1 and X1 t 2, the posture and velocity of the corresponding trajectory points S2 and X2 are used for motion allocation; the trajectory of S1~S2 and the trajectory of X1~X2 are planned, and N measurement points are set in the trajectory of S1~S2 and the trajectory of X1~X2, respectively, with N≥10; secondly, the six-degree-of-freedom CTS mechanism and the five-degree-of-freedom CTS mechanism drive the separation model and the main model to move according to the planned trajectory respectively, and data collection, pneumatic solution, and motion are performed at the Nth measurement point before the double-body model moves from the initial posture points S1 and X1 of the separation to the trajectory points S2 and X2. Allocate and plan the S2~S3 and X2~X3 trajectories in the same way as the S1~S2 and X1~X2 trajectories; again, before reaching the trajectory points S2 and X2, the twin-body model always moves according to the previously planned trajectories, and when moving to the trajectory points S2 and X2, the twin-body model moves according to the planned S2~S3 and X2~X3 trajectories; then, the same method is used until the twin-body model moves to the final trajectory points Sn and Xn; finally, the twin-body capture trajectory wind tunnel test is completed and the wind tunnel is closed; S70. Analyze and process twin-body capture trajectory wind tunnel test data; In the twin-body capture trajectory wind tunnel test, the twin-body models completed their respective separation trajectory captures, and the attitude angles and displacements (θ, ψ, φ, X , Y , Z ) The separation trajectory and aerodynamic characteristics with the separation time t; where θ is the pitch angle, ψ is the yaw angle, φ is the roll angle, X is the axial displacement, Y is the normal displacement, Z is the lateral displacement; the aerodynamic characteristics and separation trajectories of the separation body model and the main body model considering the unsteady effects of the disturbing flow field are obtained through analysis and processing.

2. The twin-body capture trajectory wind tunnel test method considering the unsteady effect of the disturbing flow field according to claim 1 is characterized in that: The double-body capture trajectory test system distributes the Z-direction displacement of the five-degree-of-freedom CTS mechanism to the Z-direction displacement of the six-degree-of-freedom CTS mechanism, solving the problem that the five-degree-of-freedom CTS mechanism does not have Z In order to solve the problem of freedom in the Z direction, on the basis of ensuring that the relative motion position relationship of the twin-body model in the Z direction remains unchanged, the six-degree-of-freedom motion of each twin-body model is realized, that is, the trajectory capture of the twelve degrees of freedom of the twin-body model as a whole is achieved.

3. The twin-body capture trajectory wind tunnel test method considering the unsteady effect of the disturbing flow field according to claim 1 is characterized in that: The numerical forced oscillation method described in S20 comprises the following steps: S21. The aerodynamic forces and moments on the body axis are obtained by solving the time-accurate unsteady RANS equations in the jet two-body separation interference flow field; S22. Taking the free flow density, free flow velocity, reference length and reference area as reference quantities, the aerodynamic force and moment under the body axis system are dimensionless to obtain the aerodynamic force coefficient and moment coefficient; S23. The aerodynamic coefficients and moment coefficients are linearly processed using linear flight mechanics theory to obtain the dynamic derivatives under the disturbed flow field that needs to be simulated.

4. The twin-body capture trajectory wind tunnel test method considering the unsteady effect of the disturbing flow field according to claim 1 is characterized in that: The dynamic derivative described in S20 is a damping derivative.

5. The twin-body capture trajectory wind tunnel test method considering the unsteady effect of the disturbing flow field according to claim 1 is characterized in that: The aerodynamic solution described in S60 includes the following steps: When the twin-body capture trajectory test system collects data, the aerodynamic loads of the twin-body models under the interference of the jet are measured by the six-component measuring balances of the twin-body models, and the aerodynamic coefficients of the twin-body models are calculated by the lower computer. According to the initial conditions and input parameters of the twin-body models, the six-degree-of-freedom rigid body motion equations of the full-scale twin-body models are solved by the lower computer to obtain the acceleration of the twin-body models at the initial position and attitude angle, and the velocity, position and attitude angle of the twin-body models after the time interval Δt are obtained by integration, and then converted to the position and velocity of the trajectory points S2 and X2 of the twin-body models in the wind tunnel through the sky and the earth.

6. The twin-body capture trajectory wind tunnel test method considering the unsteady effect of the disturbing flow field according to claim 5 is characterized in that: The initial conditions are the starting position, angle and speed; the input parameters are the attitude angle, flight altitude, Mach number of each of the two-body models, and the mass, moment of inertia, damping derivative, thrust and ejection force of each of the two-body models.

7. The twin-body capture trajectory wind tunnel test method considering the unsteady effect of the disturbing flow field according to claim 5 is characterized in that: A direct damping torque is added to the six-degree-of-freedom rigid body motion equation. The direct damping torque is calculated by a direct damping torque coefficient in combination with a corresponding reference size. The direct damping torque coefficient is calculated by a corresponding dynamic derivative and a dimensionless angular velocity.

8. The twin-body capture trajectory wind tunnel test method considering the unsteady effect of the disturbing flow field according to claim 1 is characterized in that: The trajectory capture described in S70 sets the gravity influence amount according to the test requirements.

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