Pulse-type radiation-driven test platform and operating method therefor

Abstract

A pulse-type radiation-driven test platform and an operating method therefor. The test platform comprises a rail support system (10), and a driven section (4), an auxiliary film-clamping mechanism (5), a spray pipe (6) and a test section (8), which are coaxially connected in sequence and can move along a surface of the rail support system; a magnetohydrodynamic acceleration system (7) is provided in the spray pipe (6); the interior of the test section (8) is in communication with a vacuum system (9); and the interior of the driven section (4) is in communication with a gas supply system (11). In order to improve the performance of the test platform, a main film-clamping mechanism (3) and a driving section (2) are mounted upstream of the driven section (4), and a radiation source (1) can act on one side at the top of the driving section (2) or the driven section (4).

Description

A pulsed radiation-driven test platform and its operation method

[0001] This application claims priority to Chinese Patent Application No. 2024119723947, filed on December 30, 2024, entitled "A Pulsed Radiation Driven Test Platform and Its Operation Method", the entire contents of which are incorporated herein by reference. Technical Field

[0002] This invention relates to the field of wind tunnel testing technology, and in particular to a pulsed radiation-driven test platform and its operation method, which can simulate the extreme aerodynamic environment encountered by high-speed aircraft when re-entering the atmosphere. Background Technology

[0003] With the development of advanced high-speed aircraft, there is still a significant gap in our current understanding and research capabilities regarding the aerodynamic problems encountered by high-speed aircraft when entering the atmosphere. This is particularly evident in the lack of basic models for high-temperature gases, inaccurate simulations of high-temperature flows, and unclear understanding of the mechanisms of action. There is an urgent need for a ground-based test platform capable of simulating high speeds.

[0004] Considering the conditions for reproducing ultra-high-speed or local high-enthalpy flow fields, relatively pure flow, and available effective time, the simulation capabilities of shock tunnels and expansion tunnels are insufficient. A ground-based simulation platform capable of conducting high-temperature rarefied flows, thermal radiation environments, and high-temperature non-equilibrium flows is needed. A ground-based simulation platform can establish relevant datasets, support research on high-temperature gas chemical reaction models, and validate high-temperature flow prediction methods.

[0005] For the reasons mentioned above, this invention proposes a pulsed radiation-driven test platform and its operation method, which can simulate the extreme aerodynamic environment encountered by high-speed aircraft when re-entering the atmosphere. Summary of the Invention

[0006] The purpose of this invention is to provide a pulsed radiation-driven test platform and its operation method. The test platform takes into account the reproduction of ultra-high speed flow or local high enthalpy flow field, relatively pure flow, available effective time and wide operating condition wind tunnel simulation capability. Moreover, the test platform has multiple operating modes, which expand the flight envelope of wind tunnel simulation, giving it a wide operating condition flight environment and improving the simulation capability of wind tunnel.

[0007] On one hand, the present invention provides a pulsed radiation-driven test platform, comprising: a track support system and a driven section, a sub-film clamping mechanism, a nozzle and a test section coaxially connected in sequence and capable of moving along its surface. The nozzle is provided with a magnetohydrodynamic acceleration system, the test section is connected to a vacuum system, the driven section is connected to a gas supply system, and a radiation source is provided on one side of the top of the driven section, the radiation source acting on the driven section.

[0008] Preferably, a main clamping mechanism and a driving section are sequentially arranged on the side of the driven section away from the sub-clamping mechanism and coaxially connected thereto. The interior of the driving section is connected to the gas supply system. The radiation source is located on the top side of the driving section and acts on the driving section.

[0009] Preferably, the radiation source is a high-energy radiation device, and the radiation energy emitted by the high-energy radiation device is any one of electrical energy, chemical energy and particle energy. The radiation source stores energy through a capacitor bank and converts electrical energy into radiation energy through rapid discharge when needed. The emitted radiation energy is used to heat the gas in the driving section or the driven section to generate high-temperature plasma.

[0010] Preferably, the radiation source is equipped with a focusing and orientation system, which is used to accurately focus the radiation energy onto a specific area of ​​the test platform. The focusing and orientation system is an optical or electromagnetic focusing system that can adjust the size and shape of the heating area as needed.

[0011] Preferably, the magnetohydrodynamic acceleration system is installed within the expansion section of the nozzle. Through the coupling effect of an external electric field and a magnetic field, it converts the electrical energy of the injected conductive fluid into kinetic energy, thereby accelerating the airflow. The magnetohydrodynamic acceleration system includes an electrode coil coaxially arranged on the inner wall of the nozzle and an electromagnetic coil arranged around the nozzle. The electrode coil is used to generate a strong electric field, and the electromagnetic coil is used to generate a magnetic field. The magnetic field lines are parallel to the airflow direction or the angle between the magnetic field lines and the airflow direction is less than the angle of the maximum axial section of the nozzle when it has maximum expansion.

[0012] Preferably, the track support system adopts parallel double tracks, which has initial alignment function, fine-tuning calibration function and intelligent automatic reset adjustment function.

[0013] Preferably, the membrane breaking method of the main clamping membrane mechanism is single membrane breaking or double membrane breaking. When double membrane breaking is used, the membrane thicknesses are different, and the thickness of the membrane near the driving section is 1.1 to 1.5 times that of the membrane near the driven section.

[0014] On the other hand, the present invention provides an operating method based on the above-mentioned pulsed radiation-driven test platform, including the following operating modes:

[0015] a: The radiation source acts on the driven section, the magnetohydrodynamic acceleration system is activated, and the test speed is obtained with a maximum speed of not less than 7km / s;

[0016] b: The radiation source acts on the driven section, the magnetohydrodynamic acceleration system is not activated, and the test speed is obtained with a maximum speed of not less than 3km / s;

[0017] c: The radiation source acts on the drive section, the magnetohydrodynamic acceleration system is activated, and the test speed is obtained with a maximum speed of not less than 12km / s;

[0018] d: The radiation source acts on the drive section, the magnetohydrodynamic acceleration system is not activated, and the test speed is obtained with a maximum speed of not less than 9 km / s.

[0019] Preferably, the nozzle used in operating mode b is an expansion nozzle, and the nozzles used in operating modes a, c, and d are contraction-expansion nozzles.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1. This invention establishes a driven section, a secondary membrane clamping mechanism, a nozzle, and a test section on a test platform. The test section is connected to a vacuum system, which allows for evacuation of the test section, driven section, and nozzle. A gas supply system is connected to the driven section to supply gas. A magnetohydrodynamic (MHD) acceleration system is installed inside the nozzle. A radiation source is located on one side of the top of the driven section to heat the gas inside, generating high-temperature plasma. The MHD acceleration system accelerates the high-temperature plasma flow in the nozzle. This invention achieves different operating modes by varying the way the radiation source acts on the driven and driven sections, and by whether the MHD acceleration system is activated. This enables the pulsed radiation-driven test platform to simulate different velocity and flow domains.

[0022] 2. This invention utilizes pulsed radiation to generate high-temperature gas within milliseconds or even microseconds to simulate the extreme aerodynamic environment encountered by aircraft in the atmosphere;

[0023] 3. The test platform of this invention takes into account the reproduction of ultra-high speed flow or local high enthalpy flow field, relatively pure flow, available effective time and wide operating condition wind tunnel simulation capability. In addition, the test platform has multiple operating modes, which expand the flight envelope of wind tunnel simulation, giving it a wide operating condition flight environment and improving the simulation capability of wind tunnel. Attached Figure Description

[0024] 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.

[0025] Figure 1 is a schematic diagram of the structure of the test platform of Embodiment 1 of the present invention;

[0026] Figure 2 is a schematic diagram of the structure of the test platform in Embodiment 2 of the present invention;

[0027] Figure 3 is a schematic diagram of the double-track structure of the track support system in this invention;

[0028] Explanation of reference numerals in the attached figures: 1: Radiation source; 2: Drive section; 3: Main membrane clamping mechanism; 4: Driven section; 5: Secondary membrane clamping mechanism; 6: Nozzle; 7: Magnetohydrodynamic acceleration system; 8: Test section; 9: Vacuum system; 10: Track support system; 11: Gas supply system. Detailed Implementation

[0029] 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.

[0030] 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.

[0031] 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.

[0032] Example 1

[0033] As shown in Figures 1 and 3, this embodiment provides a pulsed radiation-driven test platform, including: a track support system 10 and a driven section 4, a sub-film clamping mechanism 5, a nozzle 6, and a test section 8, which are coaxially connected and can move along its surface. The test section 8 is connected to a vacuum system 9, which is used to evacuate the connected components such as the driven section 4, the nozzle 6, and the test section 8. The driven section 4 is connected to a gas supply system 11, which is used to supply gas to the driven section 4. A radiation source 1 is provided on one side of the top of the driven section 4. The radiation source 1 acts on the driven section 4 to heat the gas inside it, generating high-temperature plasma. A magnetohydrodynamic acceleration system 7 is provided inside the nozzle 6, which is used to accelerate the high-temperature plasma flow inside the nozzle 6.

[0034] In this embodiment, the track support system 10 adopts parallel double tracks, and each component can move easily on the parallel double tracks and is coaxially and sealed to each other. It has an initial alignment function, a fine fine-tuning calibration function and an intelligent automatic reset adjustment function, ensuring that each component is on the same axis, ensuring high efficiency and reliability in practical applications, facilitating alignment calibration and switching between multiple operating modes.

[0035] In this embodiment, radiation source 1 is a high-energy radiation device, and the radiation energy emitted by the high-energy radiation device is any one of electrical energy, chemical energy, and particle energy generated by a particle accelerator. Radiation source 1 stores energy through a capacitor bank and converts electrical energy into radiation energy through rapid discharge when needed. When radiation source 1 is activated, the instantaneously emitted high-energy radiation is absorbed by the gas in the wind tunnel, causing the gas temperature to rise rapidly and generating a high-temperature plasma flow.

[0036] In this embodiment, the radiation source 1 is equipped with a focusing and orientation system, which is used to accurately focus the radiation energy onto a specific area of ​​the test platform. The focusing and orientation system is an optical or electromagnetic focusing system, which can adjust the size and shape of the heating area as needed.

[0037] In this embodiment, the magnetohydrodynamic acceleration system 7 is installed inside the expansion section of the nozzle 6. Through the coupling effect of an external electric field and a magnetic field, it converts the electrical energy of the injected conductive fluid into kinetic energy, thereby accelerating the airflow. The magnetohydrodynamic acceleration system 7 includes an electrode coil coaxially arranged on the inner wall of the nozzle 6 and an electromagnetic coil arranged around the nozzle 6. The electrode coil is perpendicular to the airflow direction. A high voltage is applied between the electrodes to generate a strong electric field between them. The electromagnetic coil is used to generate a magnetic field. The magnetic field lines are parallel to the airflow direction or the angle between the magnetic field lines and the airflow direction is less than the angle of the maximum axial section of the nozzle when it is at its maximum expansion.

[0038] The operation method of the above-mentioned pulsed radiation-driven test platform includes the following operation modes:

[0039] a: Radiation source 1 acts on driven section 4, magnetohydrodynamic acceleration system 7 is activated, and a test speed of not less than 7 km / s is obtained.

[0040] b: Radiation source 1 acts on driven section 4, magnetohydrodynamic acceleration system 7 is not activated, and a test speed of not less than 3km / s is obtained.

[0041] In this embodiment, the nozzle 6 used in operation mode a is a contraction-expansion type nozzle, and the nozzle 6 used in operation mode b is an expansion type nozzle. The nozzle 6 is made of low carbon steel or aluminum alloy without iron elements, and the driven section 4 is made of aluminum alloy when conducting radiation tests.

[0042] Example 2

[0043] As shown in Figures 2 and 3, this embodiment provides a pulsed radiation-driven test platform, including: a track support system 10 and a drive section 2, a main clamping mechanism 3, a driven section 4, a secondary clamping mechanism 5, a nozzle 6, and a test section 8, which are coaxially connected from left to right and can move along its surface. The test section 8 is connected to a vacuum system 9, which is used to evacuate the connected components such as the drive section 2, the main clamping mechanism 3, the driven section 4, the nozzle 6, and the test section 8. The drive section 2 and the driven section 4 are both connected to a gas supply system 11, which supplies gas to the drive section 2 and the driven section 4. A radiation source 1 is provided on one side of the top of the drive section 2. The radiation source 1 acts on the drive section 2 to heat the gas inside it, generating high-temperature plasma. A magnetohydrodynamic acceleration system 7 is provided inside the nozzle 6 to accelerate the high-temperature plasma flow inside the nozzle 6.

[0044] In this embodiment, the track support system 10 adopts parallel double tracks, and each component can move easily on the parallel double tracks and is coaxially and sealed to each other. It has an initial alignment function, a fine fine-tuning calibration function and an intelligent automatic reset adjustment function, ensuring that each component is on the same axis, ensuring high efficiency and reliability in practical applications, facilitating alignment calibration and switching between multiple operating modes.

[0045] In this embodiment, radiation source 1 is a high-energy radiation device, and the radiation energy emitted by the high-energy radiation device is any one of electrical energy, chemical energy, and particle energy generated by a particle accelerator. Radiation source 1 stores energy through a capacitor bank and converts electrical energy into radiation energy through rapid discharge when needed. When radiation source 1 is activated, the instantaneously emitted high-energy radiation is absorbed by the gas in the wind tunnel, causing the gas temperature to rise rapidly and generating a high-temperature plasma flow.

[0046] In this embodiment, the radiation source 1 is equipped with a focusing and orientation system, which is used to accurately focus the radiation energy onto a specific area of ​​the test platform. The focusing and orientation system is an optical or electromagnetic focusing system, which can adjust the size and shape of the heating area as needed.

[0047] In this embodiment, the magnetohydrodynamic acceleration system 7 is installed inside the expansion section of the nozzle 6. Through the coupling effect of an external electric field and a magnetic field, it converts the electrical energy of the injected conductive fluid into kinetic energy, thereby accelerating the airflow. The magnetohydrodynamic acceleration system 7 includes an electrode coil coaxially arranged on the inner wall of the nozzle 6 and an electromagnetic coil arranged around the nozzle 6. The electrode coil is perpendicular to the airflow direction. A high voltage is applied between the electrodes to generate a strong electric field between them. The electromagnetic coil is used to generate a magnetic field. The magnetic field lines are parallel to the airflow direction or the angle between the magnetic field lines and the airflow direction is less than the angle of the maximum axial section of the nozzle when it is at its maximum expansion.

[0048] In this embodiment, the membrane breaking method of the main clamping membrane mechanism 3 is either single membrane breaking or double membrane breaking. When double membrane breaking is used, the membrane thicknesses are different, and the thickness of the membrane near the driving section is 1.1 to 1.5 times that of the membrane near the driven section.

[0049] The operation method of the above-mentioned pulsed radiation-driven test platform includes the following operation modes:

[0050] c: Radiation source 1 acts on drive section 2, magnetohydrodynamic acceleration system 7 is activated, and a test speed of not less than 12km / s is obtained;

[0051] d: Radiation source 1 acts on drive section 2, magnetohydrodynamic acceleration system 7 is not activated, and a test speed of not less than 9 km / s is obtained;

[0052] In this embodiment, the nozzles 6 used in operating modes c and d are both contraction-expansion type nozzles, and the driven section 4 and the nozzle 6 are made of low carbon steel or aluminum alloy without iron.

[0053] This invention achieves different operating modes by applying radiation source 1 to the driving section 2 and the driven section 4 in different ways, and by whether the magnetohydrodynamic acceleration system 7 is activated. This enables the pulsed radiation-driven test platform to simulate different velocity and flow domains, thereby simulating the extreme aerodynamic environment encountered by high-speed aircraft when re-entering the atmosphere. It expands the flight envelope of wind tunnel simulation, giving it a wide range of flight conditions and improving the simulation capability of the wind tunnel.

[0054] 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; and these 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 pulsed radiation-driven experimental platform, characterized in that, include: The track support system and the driven section, the sub-film clamping mechanism, the nozzle and the test section are coaxially connected in sequence and can move along its surface. The nozzle is equipped with a magnetohydrodynamic acceleration system. The test section is connected to a vacuum system. The driven section is connected to a gas supply system. A radiation source is provided on one side of the top of the driven section. The radiation source acts on the driven section.

2. The pulsed radiation-driven test platform according to claim 1, characterized in that, On the side of the driven section away from the sub-clamping mechanism, a main clamping mechanism and a driving section are sequentially arranged and coaxially connected thereto. The interior of the driving section is connected to the gas supply system. The radiation source is located on the top side of the driving section and acts on the driving section.

3. The pulsed radiation-driven test platform according to claim 1 or 2, characterized in that, The radiation source is a high-energy radiation device, and the radiation energy emitted by the high-energy radiation device is any one of electrical energy, chemical energy and particle energy. The radiation source stores energy through a capacitor bank and converts electrical energy into radiation energy through rapid discharge when needed. The emitted radiation energy is used to heat the gas in the driving section or the driven section to generate high-temperature plasma.

4. The pulsed radiation-driven test platform according to claim 3, characterized in that, The radiation source is equipped with a focusing and orientation system, which is used to accurately focus the radiation energy onto a specific area of ​​the test platform. The focusing and orientation system is an optical or electromagnetic focusing system, which can adjust the size and shape of the heating area as needed.

5. The pulsed radiation-driven test platform according to claim 1 or 2, characterized in that, The magnetohydrodynamic acceleration system is installed inside the expansion section of the nozzle. Through the coupling effect of an external electric field and a magnetic field, it converts the electrical energy of the injected conductive fluid into kinetic energy, thereby accelerating the airflow. The magnetohydrodynamic acceleration system includes an electrode coil coaxially arranged on the inner wall of the nozzle and an electromagnetic coil arranged around the nozzle. The electrode coil is used to generate a strong electric field, and the electromagnetic coil is used to generate a magnetic field. The magnetic field lines are parallel to the airflow direction or the angle between the magnetic field lines and the airflow direction is less than the angle of the maximum axial section of the nozzle when it is at its maximum expansion.

6. The pulsed radiation-driven test platform according to claim 1 or 2, characterized in that, The track support system uses parallel double tracks, which have initial alignment function, fine-tuning calibration function and intelligent automatic reset adjustment function.

7. The pulsed radiation-driven test platform according to claim 2, characterized in that, The membrane breaking mechanism of the main clamping mechanism can be a single membrane breaking or a double membrane breaking. When a double membrane breaking is used, the membrane thicknesses are different. The thickness of the membrane closer to the driving section is 1.1 to 1.5 times that of the membrane closer to the driven section.

8. [Amended according to Rule 26, 14.02.2025] The operating method of the pulsed radiation-driven test platform according to claim 1 is characterized in that, It includes the following two operating modes: a: The radiation source acts on the driven section, the magnetohydrodynamic acceleration system is activated, and the test speed is obtained with a maximum speed of not less than 7km / s; b: The radiation source acts on the driven section, the magnetohydrodynamic acceleration system is not activated, and the test speed is obtained with a maximum speed of not less than 3km / s.

9. The method for operating the pulsed radiation-driven test platform according to claim 2, characterized in that, It includes the following two operating modes: c: The radiation source acts on the drive section, the magnetohydrodynamic acceleration system is activated, and the test speed is obtained with a maximum speed of not less than 12km / s; d: The radiation source acts on the drive section, the magnetohydrodynamic acceleration system is not activated, and the test speed is obtained with a maximum speed of not less than 9 km / s.

10. The method for operating the pulsed radiation-driven test platform according to claim 8 or 9, characterized in that, Operating mode b uses an expansion nozzle, while operating modes a, c, and d use a contraction-expansion nozzle.

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