Pulse type radiation driving test platform and operation method thereof

Abstract

The invention provides a pulse type radiation driving test platform and an operation method thereof, and relates to the technical field of wind tunnel tests. The test platform at least comprises a track supporting system, a driven section, an auxiliary film clamping mechanism, a spray pipe and a test section, the driven section, the auxiliary film clamping mechanism, the spray pipe and the test section are coaxially and sequentially connected and can move along the surface of the track supporting system, a magnetofluid power acceleration system is arranged in the spray pipe, the interior of the test section is communicated with a vacuum system, and the interior of the driven section is communicated with an air supply system. The main film clamping mechanism and the driving section are installed on the upstream of the driven section, and the radiation source can act on one side of the top of the driving section or the driven section. The test platform considers reproduction of ultra-high-speed incoming flow or local high-enthalpy flow field, relatively pure incoming flow, available effective time and wide-working-condition wind tunnel simulation capability, the test platform has multiple operation modes, and the flight envelope of wind tunnel simulation is expanded by the multiple operation modes, so that the test platform has a wide-working-condition flight environment, and the test platform has wide-working-condition wind tunnel simulation performance. And the simulation capability of the wind tunnel is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of wind tunnel testing, and in particular to a pulsed radiation driven testing platform and an operating method thereof, which can simulate the extreme aerodynamic environment encountered by a high-speed aircraft when re-entering the atmosphere. Background Art

[0002] With the development of advanced high-speed aircraft, there is still a big gap in the current level of understanding and research and solution capabilities for the aerodynamic problems encountered by high-speed aircraft when entering the atmosphere. This is particularly evident in the lack of basic models of high-temperature gases, inaccurate simulation of high-temperature flows, and unclear understanding of the mechanism of action. There is an urgent need for a ground test platform that can simulate high speed.

[0003] From the perspective of reproducing ultra-high-speed incoming flow or local high-enthalpy flow field, relatively pure incoming flow, and available effective time, the simulation capabilities of shock tunnels and expansion wind tunnels are not perfect, and a ground simulation platform capable of carrying out high-temperature rarefied flow, thermal radiation environment, and high-temperature non-equilibrium flow is needed. The ground simulation platform can establish relevant data sets, support the research of high-temperature gas chemical reaction models, and verify high-temperature flow prediction methods.

[0004] In view of the above reasons, the present invention proposes a pulsed radiation driven test platform and an operation method thereof, which can simulate the extreme aerodynamic environment encountered by a high-speed aircraft when re-entering the atmosphere. Summary of the invention

[0005] The object of the present invention is to provide a pulsed radiation-driven test platform and an operating method thereof, wherein the test platform takes into account the reproduction of ultra-high-speed incoming flow or local high-enthalpy flow field, relatively pure incoming flow, and available effective time and wide-condition wind tunnel simulation capabilities, and the test platform has multiple operating modes, which expand the flight envelope of wind tunnel simulation, enable it to have a wide-condition flight environment, and improve the simulation capability of the wind tunnel.

[0006] On the one hand, the present invention provides a pulsed radiation-driven test platform, comprising: a track support system and a driven section, a sub-clamping mechanism, a nozzle and a test section which are coaxially connected in sequence and can move along the surface thereof, wherein a magnetohydrodynamic acceleration system is arranged in the nozzle, the interior of the test section is connected to a vacuum system, the interior of the driven section is connected to an air supply system, and a radiation source is arranged on one side of the top of the driven section, and the radiation source acts on the driven section.

[0007] Preferably, the driven section is provided with a main clamping mechanism and a driving section coaxially connected thereto on one side away from the auxiliary clamping mechanism in sequence, the interior of the driving section is connected to the air supply system, the radiation source is provided on the top side of the driving section, and the radiation source acts on the driving section.

[0008] 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.

[0009] Preferably, the radiation source is equipped with a focusing and orientation system, which is used to accurately focus the radiation energy to 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.

[0010] Preferably, the magnetohydrodynamic acceleration system is installed in the expansion section of the nozzle, and converts the electrical energy injected into the conductive fluid into kinetic energy through the coupling of an external electric field and a magnetic field, thereby accelerating the airflow; the magnetohydrodynamic acceleration system includes a coaxial electrode coil 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 cross-section of the nozzle when the nozzle has the maximum expansion degree.

[0011] Preferably, the track support system uses parallel double tracks, which have initial alignment function, fine fine-tuning calibration function and intelligent automatic reset adjustment function.

[0012] Preferably, the main membrane-breaking mechanism uses single diaphragm breaking or double diaphragm breaking. When double diaphragm breaking is used, the diaphragms have different thicknesses, and the thickness of the diaphragm close to the driving section is 1.1 to 1.5 times the thickness of the diaphragm close to the driven section.

[0013] On the other hand, the present invention provides an operation method based on the above-mentioned pulse radiation driven test platform, including the following operation modes:

[0014] a: The radiation source acts on the driven section, the magnetohydrodynamic acceleration system is started, and the maximum test speed is not less than 7 km / s;

[0015] b: The radiation source acts on the driven section, the magnetohydrodynamic acceleration system is not started, and the maximum test speed is not less than 3 km / s;

[0016] c: The radiation source acts on the driving section, the magnetohydrodynamic acceleration system is started, and the maximum test speed is not less than 12 km / s;

[0017] d: The radiation source acts on the driving section, the magnetohydrodynamic acceleration system is not started, and the maximum test speed is not less than 9 km / s.

[0018] Preferably, the nozzle used in operation mode b is an expansion type nozzle, and the nozzle used in operation modes a, c, and d is a convergence-expansion type nozzle.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] 1. The present invention arranges a driven section, a sub-film clamping mechanism, a nozzle and a test section on the test platform, wherein the interior of the test section is connected to a vacuum system, and the vacuum system can evacuate the interior of the test section, the driven section and the nozzle, and the gas supply system is connected to the interior of the driven section for supplying gas thereto, and a magnetohydrodynamic acceleration system is arranged in the nozzle, and a radiation source is arranged on one side of the top of the driven section for heating the gas therein, and the gas is heated to generate high-temperature plasma, and the magnetohydrodynamic acceleration system accelerates the high-temperature plasma flow of the nozzle; the present invention obtains different modes of operation by using different ways of the radiation source acting on the driving section and the driven section, and whether the magnetohydrodynamic acceleration system is started, so that the pulsed radiation driven test platform has the simulation capability of different speed domains and different flow domains;

[0021] 2. The present invention utilizes pulse radiation to generate high temperature gas in milliseconds or even microseconds to simulate the extreme aerodynamic environment encountered by aircraft in the atmosphere;

[0022] 3. The test platform of the present invention takes into account the reproduction of ultra-high-speed incoming flow or local high-enthalpy flow field, relatively pure incoming flow, and available effective time and wide-condition wind tunnel simulation capabilities, and the test platform has multiple operating modes. The multiple operating modes expand the flight envelope of wind tunnel simulation, enabling it to have a wide-condition flight environment and improve the simulation capability of the wind tunnel. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0024] Figure 1 This is a schematic diagram of the structure of the test platform of Example 1 of the present invention;

[0025] Figure 2 It is a schematic diagram of the structure of the test platform of Example 2 of the present invention;

[0026] Figure 3 It is a schematic diagram of the double-track structure of the track support system of the present invention;

[0027] Description of reference numerals:

[0028] 1: Radiation source; 2: Driving section; 3: Main clamping mechanism; 4: Driven section; 5: Auxiliary clamping mechanism; 6: Nozzle; 7: Magnetohydrodynamic acceleration system; 8: Test section; 9: Vacuum system; 10: Track support system; 11: Air supply system. DETAILED DESCRIPTION

[0029] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0030] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0031] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined. In addition, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0032] Example 1

[0033] like Figure 1 , 3As shown, this embodiment provides a pulsed radiation driven test platform, including: a track support system 10 and a driven section 4, a secondary clamping mechanism 5, a nozzle 6 and a test section 8 which are coaxially connected in sequence and can move along the surface thereof, wherein the interior of the test section 8 is connected to a vacuum system 9, and the vacuum system 9 is used to evacuate the connected driven section 4, the nozzle 6, the test section 8 and other components, the interior of the driven section 4 is connected to a gas supply system 11, and the gas supply system 11 is used to supply gas to the interior of the driven section 4, and a radiation source 1 is arranged on one side of the top of the driven section 4, and the radiation source 1 acts on the driven section 4 to heat the gas therein, and the gas is heated to generate high-temperature plasma, and a magnetohydrodynamic acceleration system 7 is arranged in the nozzle 6, and the magnetohydrodynamic acceleration system 7 is used to accelerate the high-temperature plasma flow in the nozzle 6.

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

[0035] In this embodiment, the 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. The radiation source 1 stores energy through a capacitor bank, and converts electrical energy into radiation energy through rapid discharge when needed. When the 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, generating a high-temperature plasma flow.

[0036] In this embodiment, the radiation source 1 is equipped with a focusing and directing system, which is used to accurately focus the radiation energy to a specific area of ​​the test platform. The focusing and directing 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 in the expansion section of the nozzle 6. It converts the electrical energy injected into the conductive fluid into kinetic energy through the coupling effect of the external electric field and the magnetic field, thereby accelerating the airflow; the magnetohydrodynamic acceleration system 7 includes a coaxial electrode coil 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, and a high voltage is applied between the electrodes to generate a strong electric field between the electrodes. The electromagnetic coil is used to generate a magnetic field, and the magnetic field lines are parallel to the airflow direction or the angle between the magnetic field lines and the airflow direction is smaller than the angle of the maximum axial cross-section of the nozzle when the nozzle has the maximum expansion degree.

[0038] The operation method of the pulse radiation driven test platform includes the following operation modes:

[0039] a: The radiation source 1 acts on the driven section 4, and the magnetohydrodynamic acceleration system 7 is started to obtain a test speed with a maximum speed of not less than 7 km / s;

[0040] b: The radiation source 1 acts on the driven section 4, the magnetohydrodynamic acceleration system 7 is not started, and the maximum test speed is not less than 3 km / s;

[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 material of the nozzle 6 is low-carbon steel or an aluminum alloy that does not contain iron elements, and when performing radiation tests, the driven section 4 is made of aluminum alloy.

[0042] Example 2

[0043] like Figure 2 , 3 As shown, this embodiment provides a pulsed radiation driven test platform, including: a track support system 10 and a driving section 2, a main film clamping mechanism 3, a driven section 4, a secondary film clamping mechanism 5, a nozzle 6 and a test section 8 which are coaxially connected from left to right and can move along the surface thereof, wherein the interior of the test section 8 is connected to a vacuum system 9, and the vacuum system 9 is used to evacuate the connected driving section 2, the main film clamping mechanism 3, the driven section 4, the nozzle 6, the test section 8 and other components, and the interiors of the driving section 2 and the driven section 4 are both connected to a gas supply system 11, and the gas supply system 11 is used to supply gas to the interiors of the driving section 2 and the driven section 4, and a radiation source 1 is arranged on one side of the top of the driving section 2, and the radiation source 1 acts on the driving section 2 to heat the gas inside the driving section 2, and the gas is heated to generate high-temperature plasma, and a magnetohydrodynamic acceleration system 7 is arranged in the nozzle 6, and the magnetohydrodynamic acceleration system 7 is used to accelerate the high-temperature plasma flow in the nozzle 6.

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

[0045] In this embodiment, the 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. The radiation source 1 stores energy through a capacitor bank, and converts electrical energy into radiation energy through rapid discharge when needed. When the 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, generating a high-temperature plasma flow.

[0046] In this embodiment, the radiation source 1 is equipped with a focusing and directing system, which is used to accurately focus the radiation energy to a specific area of ​​the test platform. The focusing and directing 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 in the expansion section of the nozzle 6. It converts the electrical energy injected into the conductive fluid into kinetic energy through the coupling effect of the external electric field and the magnetic field, thereby accelerating the airflow; the magnetohydrodynamic acceleration system 7 includes a coaxial electrode coil 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, and a high voltage is applied between the electrodes to generate a strong electric field between the electrodes. The electromagnetic coil is used to generate a magnetic field, and the magnetic field lines are parallel to the airflow direction or the angle between the magnetic field lines and the airflow direction is smaller than the angle of the maximum axial cross-section of the nozzle when the nozzle has the maximum expansion degree.

[0048] In this embodiment, the main membrane mechanism 3 has a single diaphragm breaking mode or a double diaphragm breaking mode. When a double diaphragm breaking mode is used, the diaphragm thickness is different. The thickness of the diaphragm close to the driving section is 1.1 to 1.5 times the thickness of the diaphragm close to the driven section.

[0049] The operation method of the pulse radiation driven test platform includes the following operation modes:

[0050] c: The radiation source 1 acts on the driving section 2, and the magnetohydrodynamic acceleration system 7 is started to obtain a test speed with a maximum speed of not less than 12 km / s;

[0051] d: The radiation source 1 acts on the driving section 2, the magnetohydrodynamic acceleration system 7 is not started, and the maximum test speed is not less than 9 km / s;

[0052] In this embodiment, the nozzles 6 used in the operation modes c and d are both contraction-expansion nozzles, and the driven section 4 and the nozzles 6 are made of low-carbon steel or aluminum alloy that does not contain iron elements.

[0053] The present invention achieves different modes of operation by making the radiation source 1 act on the driving section 2 and the driven section 4 in different ways, and whether the magnetohydrodynamic acceleration system 7 is started, so that the pulsed radiation drive test platform has the simulation capabilities of different speed domains and different flow domains, thereby being able to simulate the extreme aerodynamic environment encountered by high-speed aircraft when re-entering the atmosphere, expanding the flight envelope simulated by the wind tunnel, enabling it to have a flight environment with a wide range of working 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, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements 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 test platform, characterized in that: include: A track support system, and a driven section, a secondary clamping mechanism, a nozzle and a test section which are coaxially connected in sequence and can move along the surface thereof, wherein a magnetohydrodynamic acceleration system is arranged in the nozzle, the interior of the test section is connected to a vacuum system, the interior of the driven section is connected to an air supply system, and a radiation source is arranged on one side of the top of the driven section, and the radiation source acts on the driven section.

2. The pulsed radiation driven test platform according to claim 1, characterized in that: The driven section is provided with a main film clamping mechanism and a driving section coaxially connected thereto on one side away from the auxiliary film clamping mechanism in sequence, the interior of the driving section is connected to the air supply system, the radiation source is provided on the top side of the driving section, and the radiation source 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 group 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 to 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 in the expansion section of the nozzle, and converts the electrical energy injected into the conductive fluid into kinetic energy through the coupling effect of an external electric field and a magnetic field, thereby accelerating the airflow; the magnetohydrodynamic acceleration system includes a coaxial electrode coil 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 cross-section of the nozzle when the nozzle has the maximum expansion degree.

6. The pulsed radiation driven test platform according to claim 1 or 2, characterized in that: The track support system adopts parallel double tracks, which have initial alignment function, fine 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 main membrane breaking mechanism has a single diaphragm breaking or a double diaphragm breaking. When the double diaphragm breaking is adopted, the diaphragms have different thicknesses. The thickness of the diaphragm close to the driving section is 1.1 to 1.5 times the thickness of the diaphragm close to the driven section.

8. The operating method of the pulsed radiation driven test platform according to claim 1, characterized in that: There are two operating modes: a: The radiation source acts on the driven section, the magnetohydrodynamic acceleration system is started, and the maximum test speed is not less than 7 km / s; b: The radiation source acts on the driven section, the magnetohydrodynamic acceleration system is not started, and the maximum test speed is not less than 3 km / s.

9. The operating method of the pulsed radiation driven test platform according to claim 2, characterized in that: There are two operating modes: c: The radiation source acts on the driving section, the magnetohydrodynamic acceleration system is started, and the maximum test speed is not less than 12 km / s; d: The radiation source acts on the driving section, the magnetohydrodynamic acceleration system is not started, and the maximum test speed is not less than 9 km / s.

10. The operating method of the pulsed radiation driven test platform according to claim 8 or 9, characterized in that: The nozzle used in operation mode b is an expansion type nozzle, and the nozzles used in operation modes a, c, and d are convergence-expansion type nozzles.

Images