Device and method for simulating supersonic flight environment

Abstract

To simulate a supersonic flight environment that enables evaluation of plasma under hypersonic conditions, by using a compact device.SOLUTION: The device includes: an acceleration chamber 3 with a dielectric container 31 having an acceleration space 3s communicating with a measurement space 2s of a measurement chamber 2 and a coil 32 provided around the outer periphery of the dielectric container 31, the coil 32 having an axis X extending within the acceleration space 3s toward the measurement space 2s; and a power supply for applying a current to the coil 32. When a current is applied from the power supply to the coil 32, a magnetic pressure gradient is formed in the acceleration space 3s such that a side closer to the measurement space 2s along the axis X has a lower magnetic pressure, thereby accelerating plasma P within the acceleration space 3s toward the measurement space 2s.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present disclosure relates to a supersonic flight environment simulator and a supersonic flight environment simulator. [Background technology]

[0002] In the development of various fluid machines, airplanes, space rockets, etc., a device that simulates the environment in which an object to be measured flies at supersonic speed, i.e., a supersonic flight environment simulator, is needed. As such a device, a supersonic wind tunnel device having an arc discharge unit that accelerates a high-enthalpy airflow to hypersonic speed and injects it toward the object to be measured has been disclosed (see, for example, Patent Document 1). [Prior art documents] [Patent documents]

[0003] [Patent Document 1] JP 08-271373 (paragraph 0003, figure 3) Summary of the Invention [Problem to be solved by the invention]

[0004] However, when attempting to evaluate the effect of plasma formed on the surface of a test object due to a thermal equilibrium normal shock wave at supersonic speeds, problems arise such as the need for very large equipment, or the difficulty of measurement due to limitations on the strength of the wind tunnel or the model used as the test object.

[0005] The present disclosure is intended to solve the above-mentioned problems, and aims to make it possible to simulate a hypersonic flight environment using a small device, which makes it possible to evaluate the effects of plasma at hypersonic speeds. [Means for solving the problem]

[0006] The supersonic flight environment simulator disclosed herein comprises a measurement chamber having a measurement space in which an object to be measured is placed, a dielectric container having an acceleration space communicating with the measurement space, and an acceleration chamber having a coil provided on the outer periphery of the dielectric container and having an axis extending within the acceleration space toward the measurement space, and a power supply that applies current to the coil, and is characterized in that when current is applied to the coil from the power supply, a magnetic pressure gradient is formed in the acceleration space along the axis that is lower on the side closer to the measurement space, and plasma in the acceleration space is accelerated toward the measurement space.

[0007] The supersonic flight environment simulation method disclosed herein is characterized by forming a magnetic pressure gradient in an acceleration space communicating with a measurement space in which an object to be measured is placed, with the magnetic pressure gradient being lower on the side closer to the measurement space, and accelerating plasma in the acceleration space toward the measurement space. [Effects of the Invention]

[0008] According to the supersonic flight environment simulation device or supersonic flight environment simulation method disclosed herein, plasma is accelerated by a magnetic pressure gradient, making it possible to simulate a supersonic flight environment that allows evaluation of the effects of plasma at hypersonic speeds using a small device. [Brief explanation of the drawings]

[0009] [Figure 1] 1 is a schematic diagram illustrating a configuration of a supersonic flight environment simulator according to a first embodiment. [Figure 2] 2A to 2D are schematic diagrams showing the states of the measurement chamber and the acceleration chamber at each stage, for explaining the operating principle of the supersonic flight environment simulator according to the first embodiment. [Figure 3] 4 is a flowchart illustrating an operation of the supersonic flight environment simulator according to the first embodiment. [Figure 4] FIG. 2 is a block diagram showing the hardware configuration of a control unit of the supersonic flight environment simulator of the present disclosure. [Figure 5] FIG. 10 is a schematic diagram showing the configuration of a supersonic flight environment simulator according to a second embodiment. [Figure 6]10 is a flowchart for explaining the operation of the supersonic flight environment simulator according to the second embodiment. [Figure 7] FIG. 10 is a schematic diagram showing the configuration of a supersonic flight environment simulator according to a modified example of the second embodiment. [Figure 8] FIG. 10 is a schematic diagram showing the configuration of a supersonic flight environment simulator according to a third embodiment. [Figure 9] 10 is a flowchart for explaining the operation of the supersonic flight environment simulator according to the third embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0010] Embodiment 1 1 to 3 are diagrams for explaining the configuration and operation of a supersonic flight environment simulator or a method for simulating a supersonic flight environment according to a first embodiment, and Fig. 1 is a schematic block diagram showing cross sections of a measurement chamber and an acceleration chamber to illustrate the configuration of the supersonic flight environment simulator. Figs. 2A to 2D are schematic cross-sectional views showing the states of the main parts, including the measurement chamber and the acceleration chamber, at each stage to explain the operating principle of the supersonic flight environment simulator, and Fig. 3 is a flowchart for explaining the operation of the supersonic flight environment simulator, i.e., the method for simulating a supersonic flight environment.

[0011] 1, the supersonic flight environment simulator 1 according to the first embodiment includes a measurement chamber 2 in which a measurement space 2s is formed in which a measurement object MO is placed, an acceleration chamber 3 that accelerates plasma P and injects it into the communicating measurement chamber 2, and a pulsed power supply 5 that applies current to a coil 32 in the acceleration chamber 3. The simulator also includes a control unit 8 that controls the operation of each device in the apparatus, including the pulsed power supply 5.

[0012] The measurement chamber 2 and the acceleration chamber 3 are configured so that the measurement space 2s and the acceleration space 3s of the acceleration chamber 3 are in communication with each other and are both airtight, and are connected to a vacuum pump 7. By operating the vacuum pump 7, the pressure inside (the measurement space 2s and the acceleration space 3s) can be adjusted (reduced) to a desired level according to the simulated altitude.

[0013] The acceleration chamber 3 is made of a dielectric material and is formed in a cone shape in which the diameter of at least the outer circumferential surface decreases with increasing distance from the measurement chamber 2 along the axis X, and is composed of a dielectric container 31 with an acceleration space 3s formed on its inner circumferential surface, and a coil 32 wound around the outer circumferential surface of the dielectric container 31. The coil 32 is configured to fit the outer circumferential surface of the dielectric container 31 and to have an inner diameter that decreases with increasing distance from the measurement chamber 2 along the axis X.

[0014] Furthermore, the dielectric container 31 is connected to a gas supply unit 6 that supplies a gas for forming plasma P. In the drawing, the inner peripheral surface side is also cone-shaped, but the inner peripheral surface side does not necessarily have to be cone-shaped.

[0015] The pulsed power supply 5 is a power supply that abruptly changes the current applied to the coil 32 to generate plasma P by electromagnetic induction and that applies a current to form a magnetic pressure gradient necessary for accelerating the plasma P. Therefore, if the current applied to the coil 32 is to be abruptly changed, a pulsed power supply is not necessary. However, since the time required to accelerate the plasma P is short, the current during other periods is wasted, and therefore, from the viewpoint of power efficiency, it is preferable to use a pulsed power supply.

[0016] Next, the operation of the supersonic flight environment simulator 1 under the control of the control unit 8, that is, the method for simulating a supersonic flight environment, will be described using FIGS. 2A to 2D and with reference to the flowchart of FIG.

[0017] First, as shown in FIG. 2A, the air inside the measurement chamber 2 and acceleration chamber 3 (measurement space 2s and acceleration space 3s), in which the object to be measured MO is placed within the measurement space 2s, is evacuated V by driving the vacuum pump 7. For example, to simulate an environment at an altitude of 40 km, the pressure is reduced to approximately 1000 Pa (step S100). Then, gas G is supplied from the gas supply unit 6 to the inside of the dielectric container 31 (acceleration space 3s) (step S200). At this time, unlike the background art, the speed of the gas supplied from the gas supply unit 6 to the acceleration space 3s is less than the speed of sound.

[0018] Next, as shown in FIG. 2B, a high-voltage pulse is applied to the coil 32 from the pulse power supply 5 as a sudden change in current (step S300). When a magnetic field is formed in the acceleration space 3s due to the sudden change in current caused by the high-voltage pulse, plasma P is generated by electromagnetic induction (event P300). Furthermore, the magnetic pressure gradient of the magnetic field generated by the application of current accelerates the plasma P toward the measurement space 2s (acceleration direction Da) as shown in FIG. 2C (event P310). Then, the plasma P accelerated to a speed faster than supersonic speed is ejected into the measurement space 2s and collides with the object to be measured MO in the measurement space 2s as shown in FIG. 2D, simulating a supersonic flight environment.

[0019] After the gas is supplied, a bias magnetic field may be formed by applying a low-frequency current to the coil 32. By forming a bias magnetic field, it is possible to suppress the diffusion of the plasma P in the initial stage of generation. When the direction of the bias magnetic field is the same as the direction of the magnetic field formed in the coil 32 by the high-voltage pulse, this is called a theta pinch, and when the direction of the bias magnetic field is opposite to the direction of the magnetic field formed in the coil 32 by the high-voltage pulse, this is called a reverse bias theta pinch.

[0020] Furthermore, after the gas is supplied, preionization may be performed by applying a high-frequency alternating current to the coil 32. Preionization facilitates the generation of plasma P by electromagnetic induction and improves the controllability of the plasma P. In addition to using the coil 32, preionization can also be performed by applying a high-frequency alternating electric field to a needle electrode installed in the dielectric container 31, or by irradiating it with a beam or ultraviolet light.

[0021] In the process from steps S200 and S300 to event P310, only the plasma P is accelerated to supersonic speed, and because the speed of the plasma P is sufficiently faster than the speed of the gas G, the plasma P is ejected into the measurement space 2s before the gas G reaches the measurement space 2s. Therefore, compared to the case where a cylinder, a blower, or the like is used as in the background art, it is now possible to simulate a supersonic flight environment that allows evaluation of the effect of the plasma P on the object to be measured MO traveling at hypersonic speeds using a smaller device.

[0022] Although the dielectric container 31 and the coil 32 are formed in a cone shape as an example of a configuration for creating a magnetic pressure gradient, the present invention is not limited to this. For example, even if the dielectric container 31 and the coil 32 are formed in a cylindrical shape whose diameter does not change along the axis X, the number of turns per axial length, i.e., the winding density, may be increased with increasing distance from the measurement chamber 2.

[0023] Furthermore, the coil 32 may be a plurality of different coils arranged along the axis X. By adjusting the size or shape of each coil, or the matching state between the voltage applied to each coil and the pulse power supply 5, it is possible to form a magnetic pressure gradient of the magnetic field with high precision.

[0024] Furthermore, although an example of evaluating the effect of plasma P on the object to be measured MO has been shown, the present invention is not limited to this. For example, as a simulation of a meteorite or a re-entry vehicle, the plasma P itself may be used as the object to be measured without installing the object to be measured MO.

[0025] As shown in FIG. 4, the control unit 8 may be configured by a single piece of hardware 800 including a processor 801 and a storage device 802. Although not shown, the storage device 802 includes a volatile storage device such as a random access memory and a non-volatile auxiliary storage device such as a flash memory. Alternatively, a hard disk auxiliary storage device may be included instead of the flash memory. The processor 801 executes a program input from the storage device 802. In this case, the program is input to the processor 801 from the auxiliary storage device via the volatile storage device. The processor 801 may output data such as calculation results to the volatile storage device of the storage device 802, or may store the data in the auxiliary storage device via the volatile storage device.

[0026] Embodiment 2 In the above-mentioned first embodiment, an example of simulating a supersonic flight environment in a measurement space was described, but no reference was made to a configuration related to measurement in a simulated state. In the second embodiment, a configuration for measuring the state in the measurement space will be described. Fig. 5 is a schematic diagram in the form of a block diagram showing cross sections of a measurement chamber and an acceleration chamber to explain the configuration of a supersonic flight environment simulator according to the second embodiment, and Fig. 6 is a flowchart to explain the operation of the supersonic flight environment simulator, i.e., a method for simulating a supersonic flight environment.

[0027] In the second embodiment, the basic configuration and operation for generating and accelerating plasma are the same as those in the first embodiment, so a description of the similar parts will be omitted and FIGS. 2A to 2D of the first embodiment will be used.

[0028] 5, the supersonic flight environment simulator 1 according to the second embodiment includes, in addition to the configuration described in FIG. 1 of the first embodiment, an antenna 9 connected to a high-frequency transceiver 10 provided in the measurement space 2s as a device for measuring the state within the measurement space 2s. Furthermore, the supersonic flight environment simulator 1 includes a trigger signal generator 11 connected to the high-frequency transceiver 10 and the pulsed power supply 5 and transmitting a trigger signal to the high-frequency transceiver 10 and the pulsed power supply 5.

[0029] The pulse power supply 5 outputs a high voltage pulse to the coil 32 in response to a trigger signal, and the high frequency transceiver 10 emits electromagnetic waves to the object to be measured MO via the antenna 9 in response to the trigger signal, and receives the electromagnetic waves reflected by the object to be measured MO. Also, a radio wave absorber 12 is provided so as to surround the outside of the measurement chamber 2.

[0030] Next, the operation of the supersonic flight environment simulator 1 under the control of the control unit 8, i.e., the supersonic flight environment simulation method, will be described with reference to the flowchart in Figure 6. Note that the processes from steps S100 to S200 and the process of executing step S300 to generate events P300 to P310 are the same as those described in Figure 3 of the first embodiment, and therefore will not be described again.

[0031] In step S200, when the gas G is supplied from the gas supply unit 6 to the inside (acceleration space 3s) of the dielectric container 31, the control unit 8 instructs the trigger signal generator 11 to send a trigger signal. When the pulsed power supply 5 receives the trigger signal ("Yes" in step S250), the pulsed power supply 5 applies a high-voltage pulse as a sudden-change current to the coil 32 (step S300).

[0032] Then, as event P300 progresses to event P310, plasma P accelerated to supersonic speed or faster is emitted into measurement space 2s. Upon receiving the trigger signal, high-frequency transceiver 10 irradiates electromagnetic waves from antenna 9 and receives reflected waves to measure the state of object to be measured MO in a supersonic flight environment.

[0033] As long as measurements can be taken at a timing that simulates the supersonic flight environment, the trigger signals may be sent to the pulsed power supply 5 and the high-frequency transceiver 10 at the same or different times. In particular, by changing the timing of the trigger signal, it is possible to accurately evaluate the change in state before and after the plasma P collides with the object to be measured MO.

[0034] Variant. In the above example, an example in which the antenna is provided inside the measurement space has been described, but this is not limiting. In this modified example, an example in which the antenna is provided outside the measurement space will be described. Figure 7 is a schematic block diagram showing cross sections of the measurement chamber and acceleration chamber to explain the configuration of a supersonic flight environment simulator according to this modified example.

[0035] In the supersonic flight environment simulator 1 according to this modification, as shown in Fig. 7, the wall material of the measurement chamber 2 is made of a dielectric material that transmits electromagnetic waves, and the antenna 9 is provided outside the measurement chamber 2. The rest of the configuration and operation are as described in Fig. 5 and Fig. 6. Since the antenna 9 is provided outside the measurement space 2s, it is possible to eliminate disturbance of the plasma P by the antenna 9.

[0036] Embodiment 3 In the above-described first and second embodiments, examples have been described in which plasma is generated by electromagnetic induction in an acceleration chamber, but the present invention is not limited to this. In a supersonic flight environment simulator and a flight environment simulation method according to a third embodiment, an example will be described in which plasma generated by a plasma gun is supplied to an acceleration chamber. Fig. 8 is a schematic block diagram showing cross sections of the measurement chamber and acceleration chamber to explain the configuration of the supersonic flight environment simulator according to the third embodiment, and Fig. 9 is a flowchart to explain the operation of the supersonic flight environment simulator, i.e., the supersonic flight environment simulation method.

[0037] In the third embodiment, the basic configuration and operation for accelerating plasma are the same as those in the first and second embodiments, so a description of the same parts will be omitted and FIGS. 2C and 2D of the first embodiment will be used.

[0038] 8, the supersonic flight environment simulator 1 according to the third embodiment is configured such that, in addition to the configuration described in FIG. 5 of the second embodiment, a plasma gun 13 for supplying plasma P into the acceleration space 3s is provided on the side of the dielectric container 31 away from the measurement chamber 2. In the first and second embodiments, the current applied to the coil 32 is suddenly changed to generate the plasma P, but in the third embodiment, it is only necessary to form a magnetic pressure gradient, so that the current does not necessarily have to be suddenly changed, and a power supply 5V is provided instead of the pulsed power supply 5.

[0039] The plasma gun 13 comprises an electrode 13a that generates plasma P by applying an electric charge, a plasma generation power supply 13b that applies a DC voltage to the electrode 13a, and a vacuum vessel 13c that houses the electrode 13a in a vacuum atmosphere. The gas supply unit 6 is configured to supply gas to the vacuum vessel 13c. The plasma generation power supply 13b is further connected to a trigger signal generator 11 and is configured to supply the generated plasma P to the acceleration space 3s upon receiving a trigger signal.

[0040] Next, the operation of the supersonic flight environment simulator 1 under the control of the control unit 8, i.e., the supersonic flight environment simulation method, will be described with reference to the flowchart in Figure 9. Note that the process of step S100 and the process of executing step S400 when event P310 occurs are the same as those described in Figure 6 of the second embodiment, and therefore further description will be omitted.

[0041] In step S200V, when gas G is supplied from gas supply unit 6 to vacuum vessel 13c whose pressure has been reduced, control unit 8 instructs trigger signal generator 11 to send a trigger signal. Upon receiving the trigger signal ("Yes" in step S205), plasma generation power supply 13b applies a high voltage to electrode 13a to generate plasma P in vacuum vessel 13c to which gas G has been supplied (step S210), and supplies the generated plasma P into acceleration space 3s.

[0042] Meanwhile, power supply 5V applies current to coil 32 in response to the trigger signal (step S300V). The application of current creates a magnetic pressure gradient in the magnetic field within acceleration space 3s, and plasma P supplied into acceleration space 3s is accelerated toward measurement space 2s (event P310), as described in FIG. 2C. Then, plasma P accelerated to a speed greater than or equal to supersonic speed is ejected into measurement space 2s, and collides with object to be measured MO within measurement space 2s, simulating a supersonic flight environment, as described in FIG. 2D.

[0043] In response to the trigger signal, the high frequency transceiver 10 irradiates electromagnetic waves from the antenna 9 and receives reflected waves, thereby measuring the state of the object to be measured MO in a supersonic flight environment (step S400).

[0044] In this way, by using the plasma gun 13 for plasma generation, the degree of freedom is increased, and it becomes possible to expand the measurement range of electron density, etc. Note that, unlike the first and second embodiments, the power supply 5V does not need to change the current suddenly, but since the time required to accelerate the plasma P is short, a pulse power supply 5 may be used as in the first and second embodiments.

[0045] Although various exemplary embodiments and examples are described in this disclosure, the various features, aspects, and functions described in one or more embodiments are not limited to the application of a particular embodiment, but may be applied to the embodiments alone or in various combinations. Therefore, countless modifications not illustrated are contemplated within the scope of the technology disclosed in this specification. For example, this includes cases where at least one component is modified, added, or omitted, or where at least one component is extracted and combined with components of another embodiment.

[0046] In this disclosure, an example has been described in which the timing for suddenly changing the current flowing through the coil, the timing for performing measurements, and the timing for generating plasma are adjusted using trigger signals from trigger signal generator 11, but the present invention is not limited to this. For example, even without using trigger signal generator 11, the timing may be controlled within control unit 8, and control signals may be sent directly to pulsed power supply 5, high-frequency transceiver 10, or plasma gun 13.

[0047] As described above, the hypersonic flight environment simulator 1 of the present disclosure includes the measurement chamber 2 having the measurement space 2s in which the object to be measured MO is placed, the dielectric container 31 having the acceleration space 3s communicating with the measurement space 2s, and the acceleration chamber 3 having the coil 32 disposed on the outer periphery of the dielectric container 31 and having an axis X extending toward the measurement space 2s within the acceleration space 3s, and a power supply (pulse power supply 5, power supply 5V) that applies current to the coil 32, and is configured such that when current is applied from the power supply to the coil 32, a magnetic pressure gradient is formed in the acceleration space 3s along the axis X such that the side closer to the measurement space 2s is lower, and the plasma P in the acceleration space 3s is accelerated toward the measurement space 2s. This makes it possible to simulate a hypersonic flight environment in which the plasma P at hypersonic speeds can be evaluated using a compact device.

[0048] If the coil 32 is configured so that the diameter increases as it approaches the measurement space 2s along the axis X, a magnetic pressure gradient can be easily generated.

[0049] Alternatively, the coil 32 may be configured so that the winding density decreases as it approaches the measurement space 2s along the axis X, which also makes it possible to easily generate a magnetic pressure gradient.

[0050] The power supply (pulse power supply 5, power supply 5V) has a function of suddenly changing the current applied to the coil 32 (for example, by applying a pulse), and by generating plasma P from the gas supplied to the acceleration space 3s through electromagnetic induction when the current applied to the coil 32 changes, plasma P can be generated and accelerated with a single application.

[0051] Alternatively, if a plasma supply unit (plasma gun 13) that supplies plasma P to the acceleration space 3s is provided, the degree of freedom of measurement is improved.

[0052] By providing a high-frequency transceiver 10 that operates in response to the timing at which current is applied to the coil 32 (for example, by a trigger signal from the trigger signal generator 11 or a control signal from the control unit 8), and an antenna 9 that is connected to the high-frequency transceiver 10 and that emits electromagnetic waves toward the measurement space 2s and receives reflected waves, it is possible to accurately evaluate the state changes before and after the plasma P collides with the object to be measured MO.

[0053] If the measurement chamber 2 is formed with a dielectric wall material and the antenna 9 is provided outside the measurement space 2s, the antenna 9 can be prevented from disturbing the plasma P.

[0054] As described above, according to the hypersonic flight environment simulation method of the present disclosure, in the acceleration space 3s communicating with the measurement space 2s in which the object to be measured MO is placed, a magnetic pressure gradient is formed that is lower on the side closer to the measurement space 2s, and the plasma P in the acceleration space 3s is accelerated toward the measurement space 2s. This makes it possible to simulate a hypersonic flight environment that allows evaluation of the plasma P at hypersonic speeds using a small device.

[0055] Alternatively, if plasma P is generated from gas G supplied to acceleration space 3s by electromagnetic induction, the degree of freedom in measurement is improved.

[0056] Various aspects of the present disclosure are summarized below as appendices.

[0057] (Appendix 1) a measurement chamber having a measurement space in which an object to be measured is placed; an acceleration chamber including a dielectric container having an acceleration space communicating with the measurement space, and a coil provided on the outer periphery of the dielectric container, the coil having an axis extending within the acceleration space toward the measurement space; a power source that applies a current to the coil; A supersonic flight environment simulator characterized in that, when a current is applied to the coil from the power supply, a magnetic pressure gradient is formed in the acceleration space along the axis such that the side closer to the measurement space is lower, and plasma in the acceleration space is accelerated toward the measurement space.

[0058] (Appendix 2) 2. The supersonic flight environment simulator according to claim 1, wherein the diameter of the coil increases as it approaches the measurement space along the axis.

[0059] (Appendix 3) 2. The supersonic flight environment simulator according to claim 1, wherein the coil has a winding density that decreases as it approaches the measurement space along the axis.

[0060] (Appendix 4) the power supply has a function of suddenly changing the current applied to the coil, 4. The supersonic flight environment simulator according to any one of claims 1 to 3, characterized in that plasma is generated from the gas supplied to the acceleration space by electromagnetic induction when the current applied to the coil is changed.

[0061] (Appendix 5) 4. The supersonic flight environment simulator according to any one of claims 1 to 3, further comprising a plasma supply unit that supplies plasma to the acceleration space.

[0062] (Appendix 6) a high-frequency transceiver that operates in response to the timing at which a current is applied to the coil; and an antenna connected to the high-frequency transceiver, which emits electromagnetic waves toward the measurement space and receives reflected waves; 6. A supersonic flight environment simulator according to any one of claims 1 to 5, comprising:

[0063] (Appendix 7) 7. The supersonic flight environment simulator according to claim 6, wherein the measurement chamber is formed with a dielectric wall material, and the antenna is provided outside the measurement space.

[0064] (Appendix 8) A method for simulating a supersonic flight environment, comprising: forming a magnetic pressure gradient in an acceleration space communicating with a measurement space in which an object to be measured is placed, the magnetic pressure gradient being lower on the side closer to the measurement space; and accelerating plasma in the acceleration space toward the measurement space.

[0065] (Appendix 9) 9. The method for simulating a supersonic flight environment according to claim 8, wherein plasma is generated from the gas supplied to the acceleration space by electromagnetic induction. [Explanation of symbols]

[0066] 1: Supersonic flight environment simulator, 2: Measurement chamber, 2s: Measurement space, 3: Acceleration chamber, 31: Dielectric container, 32: Coil, 3s: Acceleration space, 5: Pulse power supply, 5V: Power supply, 6: Gas supply unit, 7: Vacuum pump, 8: Control unit, 9: Antenna, 10: High frequency transmitter / receiver, 11: Trigger signal generator, 13: Plasma gun (plasma supply unit), MO: Object to be measured, P: Plasma, X: Axis.

Claims

1. a measurement chamber having a measurement space in which an object to be measured is placed; an acceleration chamber including a dielectric container having an acceleration space communicating with the measurement space, and a coil provided on the outer periphery of the dielectric container, the coil having an axis extending within the acceleration space toward the measurement space; a power source that applies a current to the coil; A supersonic flight environment simulator characterized in that, when a current is applied to the coil from the power supply, a magnetic pressure gradient is formed in the acceleration space along the axis such that the side closer to the measurement space is lower, and plasma in the acceleration space is accelerated toward the measurement space.

2. 2. The supersonic flight environment simulator according to claim 1, wherein the diameter of the coil increases as the coil approaches the measurement space along the axis.

3. 2. The supersonic flight environment simulator according to claim 1, wherein the winding density of the coil decreases as the coil approaches the measurement space along the axis.

4. the power supply has a function of suddenly changing the current applied to the coil, 4. The supersonic flight environment simulator according to claim 1, wherein plasma is generated from the gas supplied to the acceleration space by electromagnetic induction when the current applied to the coil is changed.

5. 4. The supersonic flight environment simulator according to claim 1, further comprising a plasma supply unit for supplying plasma to the acceleration space.

6. a high-frequency transceiver that operates in response to the timing at which a current is applied to the coil; and an antenna connected to the high-frequency transceiver, which emits electromagnetic waves toward the measurement space and receives reflected waves; 4. The supersonic flight environment simulator according to claim 1, further comprising:

7. 7. The supersonic flight environment simulator according to claim 6, wherein the measurement chamber is formed with a dielectric wall material, and the antenna is provided outside the measurement space.

8. A method for simulating a supersonic flight environment, comprising: forming a magnetic pressure gradient in an acceleration space communicating with a measurement space in which an object to be measured is placed, the magnetic pressure gradient being lower on the side closer to the measurement space; and accelerating plasma in the acceleration space toward the measurement space.

9. 9. The method for simulating a supersonic flight environment according to claim 8, wherein plasma is generated from the gas supplied to the acceleration space by electromagnetic induction.

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