Double-body track capturing wind tunnel test method suitable for multi-jet interference

Abstract

The invention belongs to the technical field of wind tunnel tests, and discloses a double-body track capturing wind tunnel test method suitable for multi-jet interference. The invention discloses a double-body track capturing wind tunnel test method suitable for multi-jet interference. The method comprises the following steps: determining a segmented continuous simulation test scheme; designing and manufacturing a test device; installing a test device; carrying out a double-jet-flow capture track wind tunnel test; carrying out a three-jet-flow capture track wind tunnel test; carrying out a single jet flow capture track wind tunnel test; and analyzing and processing segmented test data. According to the double-body capture track wind tunnel test method suitable for the multi-jet-flow interference, segmented continuing is carried out according to the jet flow opening time in a multi-jet-flow complex interference scene, whole-process simulation of a double-body complex separation process with the multi-jet-flow interference is achieved, and the method has engineering practical value.

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 suitable for multi-jet interference. Background Art

[0002] In recent years, with the rapid development of aircraft, the problems faced are more complicated. When the main body and the separated body with the same mass and volume are separated, the complex flow interference between the main body and the separated body during the separation process will cause the flight posture of both bodies to change significantly. In this case, one body is fixed and the other body is in the capture trajectory (the single body capture trajectory Captive Trajectory Simulation,CTS ) test technology can no longer meet the simulation needs. For this reason, the twin-body capture trajectory wind tunnel test technology was born, which can simultaneously simulate the motion trajectory and aerodynamic characteristics of the twin bodies when they are separated in the wind tunnel.

[0003] Usually, in a twin-body capture trajectory wind tunnel test, given the initial separation state, the separation trajectory and aerodynamic characteristics of the twin bodies affected by the initial separation state can be obtained in one blowing test. However, for some separations with jet power, especially complex separation scenarios that require switching between different jet conditions during the separation process, it is difficult to obtain trajectory capture and aerodynamic characteristics under all jet conditions in one blowing test due to limitations in model space, difficulty in jet device layout, and wind tunnel operation time.

[0004] The typical complex separation process of two bodies with multi-jet interference is described as follows: (1) Double-jet stage: the axial separation engine of the separation body (front body) works, causing the separation body to move axially away from the main body (rear body); (2) Three-jet stage: the normal separation engine of the separation body starts to work, and the normal separation engine and the axial engine work together to push the separation body to deviate from the axial movement; (3) Single-jet stage: the axial engine is shut down, and the separation body continues to move under the action of the normal engine, away from the main body.

[0005] In order to realize the full process simulation of the typical twin-body complex separation process with multi-jet interference, it is urgent to develop a twin-body capture trajectory wind tunnel test method suitable for multi-jet interference. 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 suitable for multi-jet interference.

[0007] The twin-body capture trajectory wind tunnel test method suitable for multi-jet interference 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 segmented connection simulation test plan; The wind tunnel test of the twin-body capture trajectory with multi-jet segmented interference was divided into three tests according to the jet opening time, namely the double-jet capture trajectory wind tunnel test, the triple-jet capture trajectory wind tunnel test and the single-jet capture trajectory wind tunnel test, to simulate the whole process of the complex separation process of the twin-body with multi-jet interference. S20. Design and manufacture test equipment; The test device includes a separation model, a separation model support, a separation model six-component force balance, a separation model jet simulation device, and a main body model, a main body model support, and a main body model six-component force balance; the separation model jet simulation device independently realizes three jet conditions of double jet condition, triple jet condition and single jet condition through a regulator; S30. Install the test device; The separation model is mounted upright 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 into the separation model; the separation model jet simulation device is pre-set to three jet conditions of double jet conditions, triple jet conditions and single jet conditions according to the segmented test plan; the main body model is mounted upright 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 into the main body model; the separation model and the main body model are collectively referred to as a double-body model; S40. Conduct dual jet capture trajectory wind tunnel tests; Before the test, the jet working condition of the separation model jet simulation device was set to the dual jet state; the positions and attitude angles of the separation model and the main body model were given respectively, and the separation model was moved to the separation initial posture point S1, and the main body model was moved to the separation initial posture point X1; Conduct a wind tunnel test on the dual jet capture trajectory; start the separation model jet simulation device to perform dual jets until the jet flow field is stable; start the wind tunnel, and after the wind tunnel inflow flow field is stable, 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 calculated to distribute the motion; 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 body model to move according to the planned trajectory, and the data is collected, the pneumatic solution is calculated, and the motion distribution is performed at the Nth measurement point before the double-body model moves from the initial posture points S1 and X1 to the trajectory points S2 and X2, and the same method as that of the trajectory of S1~S2 and the trajectory of X1~X2 is adopted. The S2~S3 segment trajectory and the X2~X3 segment trajectory are planned in the same way; again, before reaching the trajectory points S2 and X2, the twin-body model always moves according to the previously planned trajectories. When moving to the trajectory points S2 and X2, the twin-body model moves according to the S2~S3 segment and X2~X3 trajectories planned respectively; then, the same way is adopted until the twin-body model moves to the final trajectory points Sn and Xn; at this point, the wind tunnel test of the dual jet capture trajectory is over, the twin-body models have completed their respective separation trajectory capture, and the attitude angles and displacements (θ, ψ, φ, X , Y , Z ) Separation trajectory and aerodynamic characteristics with separation time; Finally, the wind tunnel is closed; Among them, θ is the pitch angle, ψ is the yaw angle, and φ is the roll angle. X is the axial displacement, Y is the normal displacement, Z is the lateral displacement; S50. Conduct three-jet capture trajectory wind tunnel test; Before the test, the jet flow condition of the separation model jet flow simulation device was set to the three-jet state; The final trajectory points Sn and Xn of the twin-body model at the end of the double-jet capture trajectory wind tunnel test are defined as the separation initial posture points S1 and X1 of the triple-jet capture trajectory wind tunnel test; Repeat the double jet capture trajectory wind tunnel test process of S40 to complete the triple jet capture trajectory wind tunnel test; obtain the aerodynamic characteristics and separation trajectory of the twin-body model under the triple jet state; S60. Conduct single jet capture trajectory wind tunnel test; Before the test, the jet flow condition of the separation model jet flow simulation device was set to a single jet flow state; The final trajectory points Sn and Xn of the catamaran model at the end of the three-jet capture trajectory wind tunnel test are defined as the separation initial posture points S1 and X1 of the single-jet capture trajectory wind tunnel test; Repeat the double jet capture trajectory wind tunnel test process of S40 and complete the single jet capture trajectory wind tunnel test; obtain the aerodynamic characteristics and separation trajectory of the twin-body model under the three-jet state; S70. Analyze and process segmented test data; The test results of the double-jet capture trajectory wind tunnel test, the triple-jet capture trajectory wind tunnel test and the single-jet capture trajectory wind tunnel test were connected according to the jet opening time during the aircraft separation process to obtain the separation trajectory and aerodynamic characteristics of the entire separation process of the twin-body model under multi-jet interference.

[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 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.

[0009] Furthermore, the trajectory capture sets the gravity influence amount according to the test requirements.

[0010] Further, the aerodynamic solution described in S40 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.

[0011] Furthermore, the initial conditions of the dual-jet working condition 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; for the three-jet working condition, the position, jet thrust and speed at the end of the dual-jet capture trajectory wind tunnel test are used as input parameters; for the single-jet working condition, the position, jet thrust and speed at the end of the three-jet capture trajectory wind tunnel test are used as input parameters.

[0012] In short, the twin-body capture trajectory wind tunnel test method suitable for multi-jet interference of the present invention is, first, to carry out the twin-body capture trajectory wind tunnel test under the dual-jet working condition under the given initial attack angle, sideslip angle, relative posture, and jet thrust, and then to carry out the twin-body capture trajectory wind tunnel test under the triple-jet working condition with the twin-body posture, jet thrust, and speed at the end of the dual jets as input parameters, and then to carry out the twin-body capture trajectory wind tunnel test under the single-jet working condition with the posture, jet thrust, and speed at the end of the three jets as input parameters, and obtain the twin-body separation trajectory and aerodynamic characteristics under the three jet working conditions in sections. Finally, the results of the three twin-body capture trajectory wind tunnel tests are connected according to the jet opening time in the actual separation process, and finally the full process simulation of the complex separation process of the twin-body with multi-jet interference is realized.

[0013] The twin-body capture trajectory wind tunnel test method suitable for multi-jet interference of the present invention performs segmented connection according to the jet opening time in a multi-jet complex interference scenario, realizes the full process simulation of the twin-body complex separation process with multi-jet interference, and has engineering practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 The present invention is a flow chart of a twin-body capture trajectory wind tunnel test method suitable for multi-jet interference. DETAILED DESCRIPTION

[0015] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0016] Example: Figure 1 As shown, the twin-body capture trajectory wind tunnel test method suitable for multi-jet interference 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, α1 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 segmented connection simulation test plan; The wind tunnel test of the twin-body capture trajectory with multi-jet segmented interference was divided into three tests according to the jet opening time, namely the double-jet capture trajectory wind tunnel test, the triple-jet capture trajectory wind tunnel test and the single-jet capture trajectory wind tunnel test, to simulate the whole process of the complex separation process of the twin-body with multi-jet interference. S20. Design and manufacture test equipment; The test device includes a separation model, a separation model support, a separation model six-component force balance, a separation model jet simulation device, and a main body model, a main body model support, and a main body model six-component force balance; the separation model jet simulation device independently realizes three jet conditions of double jet condition, triple jet condition and single jet condition through a regulator; S30. Install the test device; The separation model is mounted upright 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 into the separation model; the separation model jet simulation device is pre-set to three jet conditions of double jet conditions, triple jet conditions and single jet conditions according to the segmented test plan; the main body model is mounted upright 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 into the main body model; the separation model and the main body model are collectively referred to as a double-body model; S40. Conduct dual jet capture trajectory wind tunnel tests; Before the test, the jet working condition of the separation model jet simulation device was set to the dual jet state; the positions and attitude angles of the separation model and the main body model were given respectively, and the separation model was moved to the separation initial posture point S1, and the main body model was moved to the separation initial posture point X1; Conduct a wind tunnel test on the dual jet capture trajectory; start the separation model jet simulation device to perform dual jets until the jet flow field is stable; start the wind tunnel, and after the wind tunnel inflow flow field is stable, 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 calculated to distribute the motion; 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 body model to move according to the planned trajectory, and the data is collected, the pneumatic solution is calculated, and the motion distribution is performed at the Nth measurement point before the double-body model moves from the initial posture points S1 and X1 to the trajectory points S2 and X2, and the same method as that of the trajectory of S1~S2 and the trajectory of X1~X2 is adopted. The S2~S3 segment trajectory and the X2~X3 segment trajectory are planned in the same way; again, before reaching the trajectory points S2 and X2, the twin-body model always moves according to the previously planned trajectories. When moving to the trajectory points S2 and X2, the twin-body model moves according to the S2~S3 segment and X2~X3 trajectories planned respectively; then, the same way is adopted until the twin-body model moves to the final trajectory points Sn and Xn; at this point, the wind tunnel test of the dual jet capture trajectory is over, the twin-body models have completed their respective separation trajectory capture, and the attitude angles and displacements (θ, ψ, φ, X , Y , Z ) Separation trajectory and aerodynamic characteristics with separation time; Finally, the wind tunnel is closed; Among them, θ is the pitch angle, ψ is the yaw angle, and φ is the roll angle. X is the axial displacement, Y is the normal displacement, Z is the lateral displacement; S50. Conduct three-jet capture trajectory wind tunnel test; Before the test, the jet flow condition of the separation model jet flow simulation device was set to the three-jet state; The final trajectory points Sn and Xn of the twin-body model at the end of the double-jet capture trajectory wind tunnel test are defined as the separation initial posture points S1 and X1 of the triple-jet capture trajectory wind tunnel test; Repeat the double jet capture trajectory wind tunnel test process of S40 to complete the triple jet capture trajectory wind tunnel test; obtain the aerodynamic characteristics and separation trajectory of the twin-body model under the triple jet state; S60. Conduct single jet capture trajectory wind tunnel test; Before the test, the jet flow condition of the separation model jet flow simulation device was set to a single jet flow state; The final trajectory points Sn and Xn of the catamaran model at the end of the three-jet capture trajectory wind tunnel test are defined as the separation initial posture points S1 and X1 of the single-jet capture trajectory wind tunnel test; Repeat the double jet capture trajectory wind tunnel test process of S40 and complete the single jet capture trajectory wind tunnel test; obtain the aerodynamic characteristics and separation trajectory of the twin-body model under the three-jet state; S70. Analyze and process segmented test data; The test results of the double-jet capture trajectory wind tunnel test, the triple-jet capture trajectory wind tunnel test and the single-jet capture trajectory wind tunnel test were connected according to the jet opening time during the aircraft separation process to obtain the separation trajectory and aerodynamic characteristics of the entire separation process of the twin-body model under multi-jet interference.

[0017] 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.

[0018] Furthermore, the trajectory capture sets the gravity influence amount according to the test requirements.

[0019] Further, the aerodynamic solution described in S40 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.

[0020] Furthermore, the initial conditions of the dual-jet working condition 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; for the three-jet working condition, the position, jet thrust and speed at the end of the dual-jet capture trajectory wind tunnel test are used as input parameters; for the single-jet working condition, the position, jet thrust and speed at the end of the three-jet capture trajectory wind tunnel test are used as input parameters.

[0021] 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 suitable for multi-jet interference, based on an existing twin-body capture trajectory test system, which is used to support a twin-body model of a main body and a 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: 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 segmented connection simulation test plan; The wind tunnel test of the twin-body capture trajectory with multi-jet segmented interference was divided into three tests according to the jet opening time, namely the double-jet capture trajectory wind tunnel test, the triple-jet capture trajectory wind tunnel test and the single-jet capture trajectory wind tunnel test, to simulate the whole process of the complex separation process of the twin-body with multi-jet interference. S20. Design and manufacture test equipment; The test device includes a separation model, a separation model support, a separation model six-component force balance, a separation model jet simulation device, and a main body model, a main body model support, and a main body model six-component force balance; the separation model jet simulation device independently realizes three jet conditions of double jet condition, triple jet condition and single jet condition through a regulator; S30. Install the test device; The separation model is mounted upright 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 into the separation model; the separation model jet simulation device is pre-set to three jet conditions of double jet conditions, triple jet conditions and single jet conditions according to the segmented test plan; the main body model is mounted upright 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 into the main body model; the separation model and the main body model are collectively referred to as a double-body model; S40. Conduct dual jet capture trajectory wind tunnel tests; Before the test, the jet working condition of the separation model jet simulation device was set to the dual jet state; the positions and attitude angles of the separation model and the main body model were given respectively, and the separation model was moved to the separation initial posture point S1, and the main body model was moved to the separation initial posture point X1; Conduct a wind tunnel test on the dual jet capture trajectory; start the separation model jet simulation device to perform dual jets until the jet flow field is stable; start the wind tunnel, and after the wind tunnel inflow flow field is stable, 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 calculated to distribute the motion; 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 body model to move according to the planned trajectory, and the data is collected, the pneumatic solution is calculated, and the motion distribution is performed at the Nth measurement point before the double-body model moves from the initial posture points S1 and X1 to the trajectory points S2 and X2, and the same method as that of the trajectory of S1~S2 and the trajectory of X1~X2 is adopted. The S2~S3 segment trajectory and the X2~X3 segment trajectory are planned in the same way; again, before reaching the trajectory points S2 and X2, the twin-body model always moves according to the previously planned trajectories. When moving to the trajectory points S2 and X2, the twin-body model moves according to the S2~S3 segment and X2~X3 trajectories planned respectively; then, the same way is adopted until the twin-body model moves to the final trajectory points Sn and Xn; at this point, the wind tunnel test of the dual jet capture trajectory is over, the twin-body models have completed their respective separation trajectory capture, and the attitude angles and displacements (θ, ψ, φ, X , Y , Z ) Separation trajectory and aerodynamic characteristics with separation time; Finally, the wind tunnel is closed; Among them, θ is the pitch angle, ψ is the yaw angle, and φ is the roll angle. X is the axial displacement, Y is the normal displacement, Z is the lateral displacement; S50. Conduct three-jet capture trajectory wind tunnel test; Before the test, the jet flow condition of the separation model jet flow simulation device was set to the three-jet state; The final trajectory points Sn and Xn of the twin-body model at the end of the double-jet capture trajectory wind tunnel test are defined as the separation initial posture points S1 and X1 of the triple-jet capture trajectory wind tunnel test; Repeat the double jet capture trajectory wind tunnel test process of S40 to complete the triple jet capture trajectory wind tunnel test; obtain the aerodynamic characteristics and separation trajectory of the twin-body model under the triple jet state; S60. Conduct single jet capture trajectory wind tunnel test; Before the test, the jet flow condition of the separation model jet flow simulation device was set to a single jet flow state; The final trajectory points Sn and Xn of the catamaran model at the end of the three-jet capture trajectory wind tunnel test are defined as the separation initial posture points S1 and X1 of the single-jet capture trajectory wind tunnel test; Repeat the dual jet capture trajectory wind tunnel test process of S40 to complete the single jet capture trajectory wind tunnel test; obtain the aerodynamic characteristics and separation trajectory of the twin-body model under the three-jet state; S70. Analyze and process segmented test data; The test results of the double-jet capture trajectory wind tunnel test, the triple-jet capture trajectory wind tunnel test and the single-jet capture trajectory wind tunnel test were connected according to the jet opening time during the aircraft separation process to obtain the separation trajectory and aerodynamic characteristics of the entire separation process of the twin-body model under multi-jet interference.

2. The twin-body capture trajectory wind tunnel test method applicable to multi-jet interference 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 applicable to multi-jet interference according to claim 1 is characterized in that: The trajectory capture described sets the gravity influence amount according to the test requirements.

4. The twin-body capture trajectory wind tunnel test method applicable to multi-jet interference according to claim 1 is characterized in that: The aerodynamic solution described in S40 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.

5. The twin-body capture trajectory wind tunnel test method applicable to multi-jet interference according to claim 4 is characterized in that: The initial conditions of the dual-jet working condition are the starting position, angle and speed; the input parameters are the attitude angle, flight altitude, Mach number of each of the twin-body models, as well as the mass, moment of inertia, damping derivative, thrust and ejection force of each of the twin-body models; the triple-jet working condition uses the posture, jet thrust and speed at the end of the dual-jet capture trajectory wind tunnel test as input parameters; the single-jet working condition uses the posture, jet thrust and speed at the end of the triple-jet capture trajectory wind tunnel test as input parameters.

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