JP2003014398A - Shooting device for flying body - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a shooting device for a flying body for safely and assuredly fling the flying body at high speed with a space saved and at low cost without requiring a special skill for a treatment. SOLUTION: In the shooting device for a flying body for shooting the flying body 5 through a burst plate by a medium pressed in a pressure storage device 3, liquid 1 is supplied under pressure to the pressure storage device 3 by a high pressure pump 2. The liquid by which tests are stably performed many times by a simple treatment, is high in its converting efficiency from pressurized energy to kinetic energy and is excellent in its workability, is used as working fluid. The flying body can fly at high speed without requiring a large-scale device or a high output such as explosive chemical. The space-saving device can be realized and the shooting device for the flying body can be obtained at low running cost without a special skill.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a projectile launcher that can be used in impact testers and impact processors, and particularly space debris to an operating artificial satellite that occurs in space or in a satellite orbit. The present invention relates to a projectile launching device that realizes high-speed generation of a projectile, which is effective in elucidating the collision damage mechanism of artificial satellites and fragments of meteorites.

[0002]

2. Description of the Related Art In space, especially in the satellite orbits of the earth,
Space debris called artificial debris and small meteorites are moving at a high speed of several kilometers per second. In recent years, it has been considered a problem that space debris having such enormous kinetic energy collides with an operating artificial satellite, space shuttle, or the like at high speed, and gives various obstacles to their operating performance. Therefore, the need to elucidate the mechanism of collision damage of such space debris to artificial satellites in advance on the ground was exclaimed, and research institutions in Japan and overseas are developing experimental equipment for elucidating the mechanism of collision damage. It is being earnestly pursued. In particular, the emergence of a low-cost projectile launcher that realizes high-speed flight of small pieces assuming space debris is awaited.

Some existing projectile launchers for realizing high-speed flight of small pieces have been adopted, and the most classic and representative is the gunpowder gun. The gunpowder gun accelerates the projectile by the pressure of the combustion gas of the gunpowder, has a simple structure, and the cost required for the experiment is also low. A normal gunpowder gun has a spiral rifle groove engraved on the inner surface of the barrel, but a gunpowder gun in a projectile launcher has a smooth inner surface (smooth bore).
Has been adopted. Other highly practical projectile launchers include two-stage light gas guns, railguns, and plasma accelerators.

The one shown in FIG. 6 is a two-stage light gas gun that is the most popular in Japan for achieving a collision speed higher than that of a gunpowder gun. When the propellant is ignited in the state b from the state a before the propellant ignition, the piston is accelerated by the combustion gas pressure of the explosive and the light gas such as helium gas is compressed. At this time, the pressure of the light gas increases stepwise due to the reflection of the shock wave, and the peak pressure reaches about 1 GPa. When a predetermined compression pressure is generated, the diaphragm interposed between the projectile and the projectile is broken, and the projectile is accelerated by the light gas ejected into the launch tube as in the state c and is launched at high speed.

FIG. 7 shows a projectile launching device called a rail gun. When the switch S is closed, a current I flows from the capacitor in the order of rail → flying body metal part → rail, and the flying body is accelerated by the electromagnetic force F = 1 / 2L _× I ² due to the pressure of the generated magnetic field. It However, L _x is the self-inductance per unit length of the rail. The metal on the surface of the flying object is gasified by the flowing current, and the flying object flies with the force of the magnetic field proportional to the square of the current flowing through the plasma. In principle, the larger the current, the faster the flying object's velocity. Although it increases, a speed of about 15 km / s can be obtained by simulation.

FIG. 8 shows a projectile launching device called a plasma gun. The needle 101 of the gas reservoir 102 is adjusted so that aluminum plasma is blown out from the coaxial tube 107, and the coil 1 is placed here.
When a current is passed through 16, the plasma is compressed by the force of the magnetic field. As a result, the plasma flow is throttled to increase the velocity, and the velocity of the aluminum plasma blown out is 30%.
Reaching ~ 35 Km / s. A high-speed flying body is obtained by placing glass beads 105 as a flying body on this plasma flow. Pyrex (registered trademark) with a diameter of 0.1 mm
The world's highest speed of 20 km / s has been obtained with glass beads.

[0007]

However, in such a conventional projectile launching apparatus as described above, since the explosive gun involves explosive combustion of the explosive powder, skill is required, running costs are high, and stability is high. It was lacking. In addition, with the two-stage light gas gun, explosives are still used, handling is complicated, and know-how to obtain an optimal combination of operating parameters is required.
Since the experiment is limited to about 2 times and a gas which is a compressive fluid is used as the working fluid, enormous energy is required for the pressurization. In addition, in principle, a rail gun can accelerate to a speed close to the speed of light, but in reality, there are problems in rail wear due to a large current, viscosity of plasma, etc., and at present it stops at several Km / s. There is. Further, in the plasma gun, the device is enlarged and the control is inevitably complicated.

In view of the above, the present invention solves the problems of the conventional projectile launching device described above, saves space, costs low, does not require special skill in handling, and is capable of achieving safe and reliable high-speed flight. An object of the present invention is to provide a flying object launching device.

[0009]

Therefore, according to the present invention, in a projectile launching device for launching a projectile through a rupture plate by a medium pressurized in a pressure accumulator, liquid is pressurized in the pressure accumulator. It is characterized in that it is configured as follows. Further, the present invention is a projectile launching device for launching a projectile through a rupture plate by a medium pressurized in a pressure accumulator, wherein a fluid is pressurized in the pressure accumulator to cause a supercritical fluid state or a subcritical fluid state. It is characterized in that it is configured to. Further, the present invention is characterized in that a heater is arranged around or inside or around and inside the pressure accumulator so that the temperature of the fluid can be raised to a supercritical fluid state or a subcritical fluid state. Further, the present invention is characterized in that a pressure gauge and a thermometer are installed in the pressure accumulator, and the burst pressure and temperature at the time of burst of the burst plate can be stored. Further, the present invention is characterized in that the pressure gauge is installed by branching from an exhaust pipe connected to a pressure accumulator, and these are means for solving the problems.

[0010]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of a projectile launching device according to the present invention will be described below in detail with reference to the drawings. 1 and 2 show a first embodiment of the present invention, and FIG. 1 is a schematic view of an experimental apparatus for realizing the projectile launching apparatus of the present invention,
FIG. 2 shows the experimental result. As shown in FIG. 1, the present invention relates to a projectile launching device for launching a projectile 5 through a rupture plate by a medium pressurized in a pressure accumulator 3, wherein a high pressure pump for liquid 1 is stored in the pressure accumulator 3. It is characterized in that it is configured so as to be pressurized and supplied in 2.

Explaining in detail below, the experimental apparatus mainly consists of
A high pressure pump 2 for introducing and pressurizing a liquid 1 (which may be tap water), a pressure accumulator 3 for storing the pressurized fluid from the high pressure pump 2,
The pressure accumulator 3 is composed of a run-up tube 6 which is arranged on the front surface of the pressure accumulator 3 with a rupture plate (not shown) interposed therebetween.
The pressure accumulator 3 is connected to an exhaust pipe that discharges air when a pressurized fluid is introduced, and an opening / closing valve 7 is installed in the exhaust pipe.
A pressure gauge 4 is installed branching to the exhaust pipe. The projectile 5 is inserted into the run-up tube 6 from the front.

An experiment was conducted under the following conditions by using such an experimental apparatus. The flow rate range of the high-pressure pump 2 is 0.1
At 10 ml / min, the maximum working pressure is 80 MPa. The pressure gauge 4 is a digital type and has an upper limiter and a peak hold function, and the measurement capacity is 0 in 0.1 MPa units.
-100 MPa can be measured. Accumulator 3 has a total length of 300 m
The pressure resistance is 30 MPa and the volume is 500 ml. The rupture plate uses SUS316L and aluminum foil. The thickness of SUS316L is 0.03, 0.04, 0.
05 and 0.06 mm, set the burst pressure to 1
A material having a pressure of 2, 14, 16, 18 MPa is used. The thickness of aluminum foil is 15 μm, and it is 2, 4, 8, 1
It is used by stacking 6 sheets, and the set pressure is 0.8, 1.5,
It is 3.5 and 8.0 MPa. Inner diameter of run-up tube 6 is 3/8
In, the length is 30 mm. The piping of each part is 1 / inner diameter
It is 8 inches. The opening / closing valve 7 is manually opened / closed using a needle valve. The flying body 5 has a diameter of 6 mm and a density of 3.
Use 9 kg / m ³ alumina spheres. Tap water is used as the working fluid, and a rubber hose is connected to the tap water to supply it directly to the high pressure pump 2.

First, the on-off valve 7 is opened to allow the tap water to flow into the system so that the tap water 1 is stored in the pressure accumulator 3.
Filled within. Next, the opening / closing valve 7 is closed and the high pressure pump 2 is operated to pressurize the tap water in the pressure accumulator 3. The pressure in the pressure accumulator 3 at that time is detected by the pressure gauge 4. The limiter function of the pressure gauge 4 sets the set pressure to the maximum pressure of the pressure accumulator 3 of 30 MPa. When the set pressure is reached, the high pressure pump 2 is turned off and the pressurization is stopped. Accumulator 3
The rupture plate ruptures due to the pressure of the tap water therein, and the projectile 5 inserted into the run-up tube 6 is launched and accelerated by the opening of the tap water. At this time, the pressure gauge 4 is peak-held to detect the maximum pressure when the rupture plate ruptures.

A high-speed video camera was used as a method for measuring the speed of the flying object 5. A high-speed video camera was installed at the tip of the run-up tube 6, and an image of the moment the projectile 5 was launched from the run-up tube 6 was taken. One frame 1/18000
Seconds are used to calculate the velocity of the flying object 5 based on the captured image. Immediately after the projectile 5 was launched from the approach tube 6, the moving distance of three frames was used for speed calculation.

The result of the experiment conducted in this way is shown in FIG. The flying object 5 is 0.44 g of alumina. From this, the relationship between the breaking pressure of the rupture plate, which is a rupture plate, and the velocity of the flying body was obtained. The velocity of the flying object also increases with the increase in the rupture plate rupture pressure, but the increase in velocity decreases with increasing pressure. This is considered to be the effect of air resistance. Therefore, if a rupture plate with high pressure resistance is prepared to increase the pressure in the accumulator and further reduce the air resistance in the run-up tube, further increase in the flying body speed can be expected.

FIGS. 3 to 5 show a second embodiment of the present invention, and FIG. 3 is a schematic view of an experimental device of a projectile launcher,
FIG. 4 is an explanatory diagram of the supercritical fluid, and FIG. 5 is a result diagram of the experiment. In the present embodiment, as shown in FIG. 3, in a projectile launching device that launches a projectile 5 through a rupture plate by a medium pressurized in the pressure accumulator 3, the fluid 1 is stored in the pressure accumulator 3. It is characterized in that it is pressurized and supplied by the high-pressure pump 2 to be in a supercritical fluid state or a subcritical fluid state. In the present embodiment, a heater 8 is provided around or inside or inside and around the pressure accumulator 3 to heat the fluid in the pressure accumulator 3 to a supercritical fluid state or a subcritical fluid state. It is configured to be possible. Also,
A temperature sensor 10 is arranged in the pressure accumulator 3, and the temperature sensor 10 and the heater 8 are connected to a thermometer 11 outside the pressure accumulator 3 so that the temperature of the fluid in the pressure accumulator 3 can be controlled. . An opening / closing valve 9 is installed between the fluid 1 and the high pressure pump 2. The arrangement of the on-off valve 7, the pressure gauge 4 and the run-up pipe 6 is the same as that of the first embodiment.

In the experiment by the experimental apparatus of this embodiment,
Carbon dioxide was used as the supercritical fluid. Therefore, a liquefied carbon dioxide cylinder is used as the fluid 1. First, the on-off valve 9 and the on-off valve 7 are opened to allow the liquefied carbon dioxide from the liquefied carbon dioxide cylinder to flow into the system to fill the pressure accumulator 3 therein. Next, the opening / closing valve 7 is closed and the high pressure pump 2 is operated to pressurize the liquefied carbon dioxide in the pressure accumulator 3 to a pressure equal to or higher than the critical pressure. The pressure in the pressure accumulator 3 at that time is detected by the pressure gauge 4. After pressurizing to a predetermined pressure, the heater 8 raises the temperature to bring carbon dioxide into a supercritical state. The temperature inside the accumulator 3 at that time is detected by the temperature sensor 10, and the temperature is controlled by the thermometer 11 and the heater 8. As shown in FIG. 4, carbon dioxide has a critical pressure of 7.38 MPa and a critical temperature of 3
At 1.1 ° C, but below those pressures and temperatures, there are subcritical regions. In the present embodiment, subcritical fluids in these subcritical regions are also adopted as incompressible fluids.

The rupture plate is ruptured by the fluid in a supercritical or subcritical state in the pressure accumulator 3, and the pressure of the released carbon dioxide in the supercritical or subcritical state and the volume expansion due to its own vaporization The pressure causes the projectile 5 placed immediately after the rupture plate to accelerate in a certain direction through the run-up tube 6. In addition, the pressure and temperature at the time of rupture of the rupture plate are stored by setting the peak hold by the pressure gauge 4. Therefore, in the present embodiment, in addition to the pressure of the fluid pressurized by the high-pressure pump 2, the volume expansion pressure due to the self-vaporization of the fluid placed in the supercritical or subcritical state is larger. Acceleration is obtained.

FIG. 5 shows the result of the experiment conducted in this way. However, in FIG. 5, the pressure accumulator 3 is not heated but is liquefied carbon dioxide. As the flying vehicle 5, 0.44 g of unsaturated polyester resin was used. Flying body 5
The high speed video camera was used for the speed measurement method as in the above experiment. From this, the relationship between the carbon dioxide pressure (burst disc rupture pressure) and the flying body velocity was obtained. It is understood that the velocity of the projectile also increases as the rupture pressure of the rupture disc increases. Further heating of the pressure accumulator 3 can be expected to increase the velocity of the flying object.

Although the embodiments of the present invention have been described above, the types of fluids, high-pressure pumps, accumulators, open / close valves, pressure gauges, temperature sensors, and
Thermometer, rupture disc, run-up tube, shape and type of projectile, installation form of run-up tube for accumulator, interposition of burst plate between accumulator and projectile, set form of projectile for approach-tube, Type of upper limit limiter and peak hold function in pressure gauge and thermometer, type of temperature control function of thermometer, arrangement of temperature sensor, arrangement of heater and control of temperature rise, flying body velocity measurement method, etc. Can be appropriately selected.

[0021]

As described above in detail, according to the present invention, in the projectile launching device for launching the projectile through the rupture plate by the medium pressurized in the pressure accumulator, the pressure accumulator is provided. Since it is configured to pressurize the liquid, it is easy to handle and stable experiments can be performed any number of times, and the liquid that has high conversion efficiency from pressurizing energy to kinetic energy and excellent pressurizing property is used as a large-scale working fluid. It is possible to obtain a high-speed projectile velocity without requiring a high output of a device, explosives, etc., and to realize a space-saving device and a projectile launching device which requires low running cost without requiring special skill.

Further, in a projectile launching device for launching a projectile through a rupture plate by a medium pressurized in a pressure accumulator, fluid is pressurized in the pressure accumulator to cause a supercritical fluid state or a subcritical fluid state. By configuring to
In addition to the pressure of the pressurized fluid, a larger accelerating force is obtained due to the volume expansion pressure associated with the vaporization of the fluid placed in the supercritical or subcritical state. Further, when a heater is arranged around or inside or around and inside the pressure accumulator so that the fluid in the pressure accumulator can be heated to a supercritical state or a subcritical fluid state, the supercritical fluid Alternatively, the volume expansion pressure due to the vaporization of the subcritical fluid after it is released can be further increased, and a further increase in the velocity of the flying object can be expected.

Furthermore, when a pressure gauge and a thermometer are installed in the pressure accumulator and the burst pressure and temperature at the time of bursting of the burst plate are stored, the pressure and temperature at burst of the burst plate are The speed of the flying object can be controlled by making appropriate settings. When the pressure gauge is installed by branching from the exhaust pipe connected to the pressure accumulator, the pressure gauge is ruptured by using the exhaust pipe for exhausting air and introducing the incompressible fluid into the pressure accumulator. It is possible to easily install a pressure gauge that sets the pressure when the plate bursts. Thus, according to the present invention, there is provided a projectile launching device that saves space, costs low, does not require special skill in handling, and is capable of safe and reliable high-speed flight.

[Brief description of drawings]

FIG. 1 shows a first embodiment of the present invention and is a schematic diagram of an experimental device.

FIG. 2 is a diagram showing the results of the experiment.

FIG. 3 shows a second embodiment of the present invention and is a schematic diagram of an experimental device.

FIG. 4 is an explanatory diagram of a supercritical fluid of the same.

FIG. 5 is a diagram showing the experimental results of the same.

FIG. 6 is a conventional two-stage light gas gun that is most popular in Japan.

FIG. 7 shows a conventional projectile launcher called a rail gun.

FIG. 8 shows a conventional projectile launcher called a plasma gun.

[Explanation of symbols]

1 Incompressible fluid (tap water, liquefied carbon dioxide) 2 high pressure pump 3 accumulator 4 pressure gauge 5 Bursting discs and projectiles 6 Running tube 7 open / close valve 8 heater 9 open / close valve 10 Temperature sensor 11 thermometer

Claims (5)

[Claims] 1. A projectile launching device for launching a projectile through a rupture plate by a medium pressurized in a pressure accumulator, wherein the liquid is pressurized in the pressure accumulator. Body launcher. 2. A projectile launching device for launching a projectile through a rupture plate by a medium pressurized in a pressure accumulator, wherein a fluid is pressurized in the pressure accumulator to be in a supercritical fluid state or a subcritical fluid state. A projectile launching device characterized by being configured as follows. 3. A heater is disposed around or inside or inside and around the pressure accumulator so that the temperature of the fluid can be raised to a supercritical fluid state or a subcritical fluid state. Item 2. The projectile launching device according to item 2. 4. A pressure gauge and a thermometer are installed on the pressure accumulator, and the burst pressure and temperature at the time of burst of the burst plate are configured to be stored. The projectile launcher described in. 5. The projectile launching apparatus according to claim 4, wherein the pressure gauge is installed by branching from an exhaust pipe connected to a pressure accumulator.