Rotary jet flow interference wind tunnel test system and test method

Abstract

The invention provides a rotary jet flow interference wind tunnel test system and a test method, and aims to solve the problem of unsteady aerodynamic characteristic research of aircrafts such as rotary missiles and the like under jet flow interference conditions. The system comprises a rotation driving and supporting subsystem, a high-precision force measurement and control subsystem and a rotation jet flow generation system, and active controllable rotation of a test model in a wind tunnel and real-time synchronous accurate measurement of six-component aerodynamic force / torque in a rotation state are realized. And high-pressure jet flow is stably supplied through the hollow main shaft and the rotary sealing joint. According to the test method, on the basis of a simulation criterion that the pressure ratio, the momentum ratio and the Slowhaal number are similar, the rotating speed of the model, the incoming flow Mach number and the jet flow pressure ratio are adjusted, and the system studies the rotation and jet flow coupled unsteady aerodynamic interference rule. According to the invention, a key ground test means is provided for aerodynamic characteristic research and optimization design of a rotary aircraft direct force control technology.

Description

Technical Field

[0001] This invention relates to the field of aerodynamic ground simulation test technology, specifically to a rotating jet interference wind tunnel test system and test method, which is particularly suitable for studying the aerodynamic characteristics of direct force jet control technology under projectile rotation conditions. Background Technology

[0002] With the development of precision-guided weapon technology, achieving rapid response and high maneuverability through direct force control has become a key technology for rotating missiles. Direct force control typically involves arranging several attitude control nozzles laterally on the missile body. During the missile's rotating flight, the attitude control nozzles are activated to generate lateral control forces, achieving rapid attitude control. This process involves multiple nonlinear coupling problems, including rotational motion, lateral jet flow, and unsteady complex aerodynamic disturbances. Ground-based wind tunnel testing is the core means of verifying its aerodynamic characteristics and control laws.

[0003] Existing wind tunnel jet testing technology only simulates the aerodynamic interference of static models on the ground, and cannot simulate the dynamic process of the interaction between rotational conditions and jets. Currently, there is literature on wind tunnel tests of lateral jets from rotating aircraft, but numerical methods lack validation. Conventional jet interference test model support structures cannot achieve integrated active rotation and air supply for the model. Furthermore, air supply and signal transmission are easily interfered with during rotation, and it is difficult to accurately synchronize force measurement signals with the rotation phase. In addition, the centrifugal force effect caused by rotation and errors in dynamic aerodynamic force measurement also limit the test accuracy. Therefore, there is an urgent need for an integrated test system that can achieve controllable model rotation speed, accurate phase output, synchronous control of the acquisition system and the rotation system, and sealed air supply under rotational conditions. Summary of the Invention

[0004] The purpose of this invention is to provide a rotating jet interference wind tunnel test system and test method, which can realize the ground simulation of direct force jet control during the flight of a rotating missile, solve the simulation problem of rotation and jet coupling interference, and provide a reliable test platform for the ground verification of direct force control technology.

[0005] According to one objective of the present invention, the present invention provides a rotating jet interference wind tunnel test system, comprising: The rotary drive and support subsystem is used to drive and support the test model to achieve active and controllable axial roll motion in the wind tunnel; The high-precision force measurement and control subsystem is used to measure the six-component aerodynamic forces and torques acting on the model in real time under rotation, and to monitor the rotation angle of the model simultaneously. A rotating jet generation system is used to stably supply high-pressure gas to generate a jet under model rotation conditions and to monitor the jet pressure.

[0006] Furthermore, the rotary drive and support subsystem includes a drive motor, a transmission mechanism, a rotary spindle, a support rod, a rotary support inner sleeve, and bearings; one end of the rotary spindle is fixedly connected to the test model, and the other end is connected to the drive motor through the transmission mechanism; the support rod has a hollow structure; the rotary support inner sleeve is connected to the test model through the bearings, and the inner wall of the rotary support inner sleeve is fixedly connected to the balance in the high-precision force measurement and control subsystem.

[0007] Furthermore, the transmission mechanism is a gear transmission mechanism.

[0008] Furthermore, one end of the support rod is used to connect to the wind tunnel angle of attack mechanism, and the other end is connected to the balance.

[0009] Furthermore, the high-precision force measurement and control subsystem includes a six-component balance, a phase sensor, and a high-frequency data acquisition system; the six-component balance is installed between the inner sleeve of the rotating support and the support rod; the phase sensor is used to output the model rotation angle in real time; the high-frequency data acquisition system is used to synchronously acquire the force / torque signal and rotation angle signal output by the balance.

[0010] Furthermore, the rotating jet generation system includes a nozzle section, a pressure sensor, a rotary sealing joint, and a high-pressure gas connection; the rotating main shaft is a hollow structure, with one end connected to the nozzle section and the other end connected to the rotary sealing joint; the rotary sealing joint is connected to an external high-pressure gas source through the high-pressure gas connection; the pressure sensor is located on the side wall of the nozzle section.

[0011] According to another objective of the present invention, the present invention provides a method for testing wind tunnels with rotating jet interference, employing the above-described testing system, and comprising the following steps: The test model was installed in the wind tunnel test section and connected to the air and electrical circuits; Based on the similarity criterion, the required model rotational angular velocity, incoming Mach number, and jet pressure ratio parameters for the experiment are determined. Start the drive motor to make the test model rotate stably at the set angular velocity; Start the wind tunnel, establish a stable incoming flow at the set Mach number, and record the baseline aerodynamic data under the condition of no jet flow; A high-pressure gas source is activated to generate a jet stream. Simultaneously, the model rotation angle, six-component aerodynamic force, and torque data are collected to obtain the unsteady aerodynamic characteristics under jet stream disturbance.

[0012] Furthermore, the similarity criteria include ensuring that the pressure ratio, momentum ratio, and Strouhal number are similar between the test and flight conditions.

[0013] Furthermore, the experiment also includes the following steps: changing at least one of the parameters, such as rotational angular velocity, incoming Mach number, and jet pressure ratio, and repeating the experiment to systematically study the interference law of the rotating jet under different parameters.

[0014] Furthermore, the sampling frequency of the high-frequency data acquisition system is not less than 1 kHz.

[0015] This invention, through the integrated design of a rotary drive, high-precision dynamic measurement and control, and a rotary sealed gas supply system, achieves synchronous simulation of active high-speed rotation of a rotating model and jet interference in a wind tunnel, solving the technical challenge that traditional static tests cannot reflect the unsteady characteristics of rotation-jet coupling. The system features precise controllability of rotational speed and phase, real-time synchronous acquisition of aerodynamic forces / torques, and stable supply of high-pressure gas during rotation, significantly improving the reliability and spatiotemporal resolution of experimental data. This compact experimental system, with minimal interference to the flow field, provides an efficient and reliable ground-based testing platform for the study and optimization design of aerodynamic characteristics in direct force control of rotating missiles and highly maneuverable aircraft, possessing significant engineering application value. Attached Figure Description

[0016] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the system structure according to an embodiment of the present invention; In the figure: 1. Drive motor; 2. Transmission mechanism; 3. Rotary spindle; 4. Support rod; 5. Rotary support inner sleeve; 6. Bearing; 7. Balance; 8. Nozzle section; 9. Pressure sensor; 10. Rotary sealing joint; 11. High-pressure air circuit joint; 12. Test model. Detailed Implementation

[0018] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0020] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly; for example, they may refer to a fixed connection, a detachable connection, or an integral connection; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; and they may refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0021] Example 1 like Figure 1 As shown, a rotating jet interference wind tunnel test system is available. This system is suitable for transonic or supersonic wind tunnel tests and is used to simulate the direct force jet control process of a rotating missile. The system includes a rotating drive and support subsystem, a high-precision force measurement and control subsystem, and a rotating jet generation system, wherein: The rotary drive and support subsystem includes a drive motor 1, a transmission mechanism 2, a rotary spindle 3, a support rod 4, a rotary support inner sleeve 5, and a bearing 6, wherein: Transmission mechanism 2 is a gear transmission mechanism. One end of the rotating main shaft 3 is fixedly connected to the test model 12, and the other end is connected to the drive motor 1 through the gear transmission mechanism. The test model 12 is actively and controllably rotated in the wind tunnel airflow by the drive motor 1. The support rod 4 is a hollow structure, with one end connected to the internal balance 7 of the test model 12 and the other end connected to the wind tunnel angle of attack mechanism; The inner wall of the inner sleeve 5 of the rotating support is fixedly connected to the balance 7, and the outer wall is connected to the test model 12 through the bearing 6, which is used to realize the test model 12 to roll along the axial direction. The high-precision force measurement and control subsystem includes a six-component balance, a phase sensor, and a high-frequency data acquisition system, among which: A six-component balance is installed between the inner sleeve 5 and the support rod 4 of the rotating support of the test model to measure the aerodynamic forces and torques acting on the rotating model, especially the periodically changing lateral forces and rolling torques; a phase sensor monitors and outputs the model's rotation angle in real time; a high-frequency data acquisition system synchronously records force, torque, and angle signals, with a sampling frequency of not less than 1 kHz.

[0022] The rotating jet generation system includes a nozzle section 8, a pressure sensor 9, a rotary sealing joint 10, and a high-pressure air connection 11, wherein: The rotating main shaft 3 is a hollow structure, with one end connected to the model nozzle section 8 and the other end connected to the rotary sealing joint 10 located at the tail. The rotary sealing joint 10 is connected to a high-pressure gas source through a high-pressure gas line connector 11 to achieve high-pressure gas supply for the rotating jet. A pressure sensor 9 is provided on the side wall of the nozzle section 8 to measure the pressure in the nozzle section storage chamber. The pressure sensor 9 is a high-frequency dynamic pressure sensor.

[0023] A method for testing wind tunnel interference caused by rotating jets, using the above-mentioned system, includes the following steps: S1. Install the model and connect the air and electrical circuits; S2. Determine experimental parameters based on similarity criteria; S3. Start the motor to rotate the model; S4. Turn on the wind tunnel and establish a stable airflow, and record the baseline data without jet flow. S5. Start the jet stream and collect data synchronously; S6. By varying the parameters, the system studies the interference patterns.

[0024] Specifically, in S2, the similarity criteria include pressure ratio similarity, momentum ratio similarity, and Strouhal number similarity.

[0025] The test parameters include rotational angular velocity, incoming Mach number, and jet pressure ratio.

[0026] In S5, data acquisition includes model rotation angle, six-component aerodynamic forces, and torques.

[0027] In S6, the variable parameters include changing at least one of the following: rotational speed, incoming Mach number, or jet pressure ratio, and the test steps are repeated.

[0028] Specifically, the method is used to study unsteady aerodynamic characteristics under rotating jet disturbance.

[0029] Example 2 like Figure 1As shown, this embodiment, in order to study the unsteady aerodynamic interference characteristics of a rotating missile jet through wind tunnel testing, designed a rotating jet interference wind tunnel test system and conducted experimental method research. This embodiment provides a rotating jet interference wind tunnel test system, the system construction of which is as follows: Rotation drive and support subsystem: includes drive motor 1, gear transmission mechanism, rotating main shaft 3, hollow tail support rod, rotating support inner sleeve 5, and bearing 6. The rotating main shaft 3 is fixedly connected to the test model 12 and is driven by drive motor 1 to achieve controllable rotation; the rotating support inner sleeve 5 connects the test model 12 and the balance 7 through bearing 6 to ensure rotational stability.

[0030] High-precision force measurement and control subsystem: A six-component balance is installed between the inner sleeve 5 and the support rod 4 of the rotating support. The phase sensor collects the rotation angle in real time, and the high-frequency data acquisition system records the force, torque and angle signals simultaneously.

[0031] Rotary jet generation system: The hollow rotating main shaft 3 connects the model nozzle and the rotary sealing joint 10, and is supplied with air through a high-pressure air source. A pressure sensor is installed in the nozzle section 8 to monitor the pressure in the storage chamber.

[0032] The experimental steps in this embodiment are as follows: (1) The rotating missile model to be tested is installed in the wind tunnel test section through the support rod 4, and all air and electrical circuits are connected; (2) Based on the missile's rotational angular velocity and jet parameters under actual flight conditions, and based on the simulation criteria of the rotating jet interference wind tunnel test, determine the rotational angular velocity and jet parameters of the test condition model; (3) Start drive motor 1 and adjust it to the target rotational angular velocity so that the model rotates stably at the set speed; (4) Turn on the wind tunnel and establish a stable airflow under the set Mach number conditions. After the flow field stabilizes, record the reference aerodynamic data under the no-jet condition. (5) Start the high-pressure gas source and the data acquisition system synchronously records the model rotation angle and the six-component aerodynamic force / torque output by the balance to obtain the unsteady aerodynamic characteristics under jet interference; (6) By changing parameters such as rotation speed, incoming Mach number, and jet pressure ratio, the interference law of rotating jet is systematically studied.

[0033] In this embodiment, the simulation criterion for the rotating jet interference wind tunnel test is to ensure that the pressure-force ratio, momentum ratio, and Strouhal number are similar between the ground and flight conditions, that is, to satisfy the static pressure P at the outlet of the variable thrust nozzle under the wind tunnel test conditions. 试验喷管j With the static pressure P of the wind tunnel inflow 风洞∞ The ratio of P 试验喷管j / P 风洞∞ Equal to the static pressure P at the engine nozzle exit under flight conditions 飞行喷管j Static pressure P of incoming flow under flight conditions飞行∞ The ratio of P 飞行喷管j / P 飞行∞ The nozzle exit momentum M under wind tunnel test conditions 试验喷管j With the flow rate M from the wind tunnel 风洞∞ The ratio of M 试验喷管j / M 风洞∞ Equal to the flight condition control engine nozzle exit momentum M 飞行喷管j Flow rate M in relation to flight conditions 飞行∞ The ratio of M 飞行喷管 / M 飞行∞ The Strouhal number of the rotating missile under flight conditions is equal to that of the missile model under test conditions.

[0034] This invention enables active high-speed rotation and precise phase acquisition control of the model under wind tunnel test conditions, simulating the dynamic process of direct force control of a rotating missile. Through the integrated design of tail support, rotation drive, and high-pressure gas path, the overall structure is compact and has minimal interference with the flow field. This invention system can be widely used in ground wind tunnel simulation tests in fields such as high-maneuverability missiles and spacecraft attitude control, and has significant engineering application value.

[0035] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A rotating jet interference wind tunnel test system, characterized in that, include: The rotary drive and support subsystem is used to drive and support the test model to achieve active and controllable axial roll motion in the wind tunnel; The high-precision force measurement and control subsystem is used to measure the six-component aerodynamic forces and torques acting on the model in real time under rotation, and to monitor the rotation angle of the model simultaneously. A rotating jet generation system is used to stably supply high-pressure gas to generate a jet under model rotation conditions and to monitor the jet pressure.

2. The rotating jet interference wind tunnel test system according to claim 1, characterized in that, The rotary drive and support subsystem includes a drive motor, a transmission mechanism, a rotary spindle, a support rod, a rotary support inner sleeve, and bearings. One end of the rotary spindle is fixedly connected to the test model, and the other end is connected to the drive motor through the transmission mechanism. The support rod has a hollow structure. The rotary support inner sleeve is connected to the test model through the bearings, and the inner wall of the rotary support inner sleeve is fixedly connected to the balance in the high-precision force measurement and control subsystem.

3. The rotating jet interference wind tunnel test system according to claim 2, characterized in that, The transmission mechanism is a gear transmission mechanism.

4. The rotating jet interference wind tunnel test system according to claim 2, characterized in that, One end of the support rod is used to connect to the wind tunnel angle of attack mechanism, and the other end is connected to the balance.

5. The rotating jet interference wind tunnel test system according to claim 1, characterized in that, The high-precision force measurement and control subsystem includes a six-component balance, a phase sensor, and a high-frequency data acquisition system. The six-component balance is installed between the inner sleeve of the rotating support and the support rod. The phase sensor is used to output the model rotation angle in real time. The high-frequency data acquisition system is used to synchronously acquire the force / torque signal and rotation angle signal output by the balance.

6. The rotating jet interference wind tunnel test system according to claim 1, characterized in that, The rotating jet generation system includes a nozzle section, a pressure sensor, a rotary sealing joint, and a high-pressure gas connection joint; the rotating main shaft is a hollow structure, with one end connected to the nozzle section and the other end connected to the rotary sealing joint; the rotary sealing joint is connected to an external high-pressure gas source through the high-pressure gas connection joint; the pressure sensor is located on the side wall of the nozzle section.

7. A method for testing wind tunnels with rotating jet interference, employing the testing system described in any one of claims 1-6, characterized in that, Includes the following steps: The test model was installed in the wind tunnel test section and connected to the air and electrical circuits; Based on the similarity criterion, the required model rotational angular velocity, incoming Mach number, and jet pressure ratio parameters for the experiment are determined. Start the drive motor to make the test model rotate stably at the set angular velocity; Start the wind tunnel, establish a stable incoming flow at the set Mach number, and record the baseline aerodynamic data under the condition of no jet flow; A high-pressure gas source is activated to generate a jet stream. Simultaneously, the model rotation angle, six-component aerodynamic force, and torque data are collected to obtain the unsteady aerodynamic characteristics under jet stream disturbance.

8. The test method according to claim 7, characterized in that, The similarity criteria include ensuring that the pressure ratio, momentum ratio, and Strouhal number are similar between the test and flight conditions.

9. The test method according to claim 7, characterized in that, It also includes the following steps: changing at least one of the parameters, such as rotational angular velocity, incoming Mach number, and jet pressure ratio, and repeating the experiment to systematically study the interference law of rotating jets under different parameters.

10. The rotating jet interference wind tunnel test system according to claim 5, characterized in that, The sampling frequency of the high-frequency data acquisition system is not less than 1 kHz.

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