UA126118C2 - Anchor for the railroad trolley - Google Patents

Abstract

The invention belongs to the field of development of railguns (electromagnetic accelerators of macro-bodies), which are designed to accelerate solids to ultra-high speeds, and can be used to solve scientific and applied problems, namely, to study phase transformations of various substances, including supercritical fluids in geology, to study thermodynamic effects, that accompany the hypersonic motion of bodies in dense atmospheric layers, for modeling small meteorites and man-made particles, for studying the destructive effect of high-speed bodies in collision with various targets, for use in high-speed impact physics, for launching small spacecraft, and can also be used in military applications. A railgun anchor contains an airshell, armatures integrated into the airshell near the anchor's center of mass, and flaps attached to the airshell with flaps that extend and retract during flight from and to the airshell to control the anchor's trajectory during flight. The armature allows current to flow from one rail through the armature to the other rail to accelerate the armature. The aeroshell includes openings through which the armature surfaces pass to contact the rails. The anchor includes an insulator that surrounds the armature within the aeroshell to isolate other components of the anchor from current passing through the armature and further includes a guidance, navigation and control system. The aeroshell has an axis of symmetry and comprises a streamlined front portion of a first material in which a ring magnet is housed, the axis of which coincides with the axis of symmetry of the aeroshell, comprises a middle portion with a pointed nose of a second material, and comprises a rear portion of a third material where flaps of the same material are attached and within which balls of the second material are tightly packed. The balls are in tight contact with the rear wall of the middle part, which has the shape of a cone with an internal angle of 120° and is directed in the direction of the armature movement. The first material is ferromagnetic and softer than the second material, the second material is non-magnetic, harder and heavier than the first and third materials, and the third material is non-magnetic and lighter than the second material. The technical result of the invention is to increase the efficiency of armature acceleration (increase the muzzle energy of the armature), increase the intensity of the reactions of interaction between the armature fragments and the target material.

Description

passes through the armature and additionally contains a guidance, navigation and control system.

The airfoil has an axis of symmetry and comprises a streamlined front part of the first material, which houses an annular magnet, the axis of which coincides with the axis of symmetry of the airfoil, a middle part with a pointed nose of a second material, and a rear part of a third material, where flaps of such of the same material, and inside which balls of the second material are placed in a dense package. The balls are in tight contact with the rear wall of the middle part, which is in the shape of a cone, the internal angle of which is 120" and is directed in the direction of movement of the armature. The first material is ferromagnetic and softer than the second material, the second material is non-magnetic, harder and heavier than the first and third materials, and the third material is non-magnetic and lighter than the second material. The technical result of the invention is an increase in the efficiency of anchor acceleration (an increase in the muzzle energy of the anchor), an increase in the intensity of the reactions of the interaction of the anchor fragments and the target material. WHOSE i i she 0000000 sn B g she nn

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The invention belongs to the field of development of reikotrons (electromagnetic macrobody accelerators), which are designed to accelerate solid bodies to ultrahigh speeds, and can be used to solve scientific and applied problems, namely, the study of phase transformations of various substances, including supercritical fluids in geology, to study the thermodynamic effects that accompany the hypersonic movement of bodies in the dense layers of the atmosphere, to model small meteorites and man-made particles, to study the destructive action of high-speed bodies when they collide with various targets, to find use in the physics of high-speed impact, to launch small space vehicles, as well as may find use in military affairs. Raycotrons can be used to destroy asteroids. This is also relevant, since humanity remembers the explosion of the Chelyabinsk meteorite on February 15, 2013, and recently it became known about the explosion of the Kamchatka meteorite on December 18, 2018.

Moreover, the power of the explosion is equivalent, respectively, to the power of 20 or 10 atomic bombs that destroyed the city of Hiroshima. The diameter of meteorites (asteroids) was -20 and -10 m, respectively.

The speed of the Kamchatka meteorite reached 32 km/s.

Reikotrons can be used not only as means of high-speed throwing of solid bodies, but also as innovative transport technologies. The standard design of the railcotron includes two (or an even number) parallel insulated electrodes (rails), to which a powerful source of electrical energy is connected through a switching device. Such sources include: a battery of pulse capacitors of high voltage; explosive magnetic or magnetocumulative generator; chemical fuel generator; unipolar generator with inductive storage.

An anchor is placed between the electrodes - a macrobody that accelerates and a metal conductor. When the electric circuit is closed, a pulsed current passes through the electrodes (rails) and the armature and the Lorentz force arises, which pushes the armature out. At the same time, two situations are possible, on which two methods of pushing out are justified. If the macrobody and the metal conductor are one solid metal body, then the current passes through it, and the Lorentz force acts directly on the macrobody. If the metal conductor is made separately, then it turns into a plasma, on which the Lorentz force acts. This plasma pushes the accelerating macrobody |see Pat. 131727

Ukraine, IPC (2006) BA1E 7/00, 418 6/00, НО2К 41/00. Electromagnetic accelerator of macrobodies with a ferromagnetic part / Dzenzerskyi V.O., Burylov S.V., Tarasov S.V., Skosar V.Yu., Buryak

From O.A. The applicant and patent owner is the Institute of Transport Systems and Technologies of the National Academy of Sciences of Ukraine "Transmag" (USA). - MO and 201808407; statement 01.08.2018; published 25.01.2019, Bull. May 21.

As a rule, before entering the acceleration channel in reikotrons, preliminary acceleration of the body being thrown is used. Because it significantly reduces the erosion of the rails and increases the overall efficiency of the device

Yisemkin N.D. Methods and means of accelerating particles of natural and man-made origin/ N.D. Semkin, K.M. Sukhachev, A.S. Dorofeev // Electronics, measurement technology, radio technology and communication, vol. 14, Mo. 4, 2015. - p. 171-191). Common methods of pre-excitation are technologies that use magnetic forces acting on a ferromagnetic, for example, steel armature. Therefore, at least part of the anchor in such cases should be made of ferromagnetic material I (see Pat. 131727 Ukraine...|.

A well-known anchor for a raycotron (electromagnetic macrobody accelerator), which includes a throwing body as its integral part, for which it is rigidly attached in front in the direction of movement, the body itself is made in an oblong shape with a streamlined frontal part, which is determined by the development research problem, and has a length that is 2/3-3/4 of the total length of the anchor, while the maximum diameter of the body in its rear part is less than the uniform cross-section of the accelerator barrel, the throwing body has a complex structure and consists of an outer shell made of heat-resistant plastic material and a set core made of heavy and hard material, the body core has a complex structure and is assembled from four identical longitudinal segments, fitted to each other, each of which is set from no less than five fragments, and the dividing planes of the segments are inclined in

BO side of throwing at angles increasing from the bow part с154-5"7, d2y8-107, оз»12-157, осаз16-207, о5й20-307, the core material fills the entire volume limited by the shell on the upper and lower planes, perpendicular to them, two flat flaps are rigidly fixed, in order to increase the stabilizing function, they have a long length, which is increased due to the transition to part of the surface of the macrobody, and for the passage of the flaps during throwing on the upper and lower planes of the barrel, protrusions with slotted channels are made, connected with volume of the barrel, through which flaps are passed in the assembly (Pat. 131378 Ukraine, IPC (2006) НО2К 41/00, БАТ1Е 7/00. Anchor for an electromagnetic accelerator of macrobodies/ Dzenzersky V.O., Burylov S.V.,

Tarasov S.V., Skosar V.Yu., Buryak O.A.; The applicant and patent owner is the Institute of Transport Systems and Technologies of the National Academy of Sciences of Ukraine "Transmag" (OA). - MO and 201808028; application. 19.07.2018; published 10.01.2019, 60 Bull. Mo 11.

The advantage of the analogue is that it improves the aerodynamic parameters of the hypersonic movement of the anchor, increases the effectiveness of the interaction reactions between the fragments of the macrobody and the target material. And this leads to the expansion of the spectrum of practical use of raycotrons, the opening of the opportunity to conduct research on the destructive action of high-speed bodies in cases of interaction with targets made of various materials, the reduction of the energy consumption of experiments, and the increase of the profitability of projects.

The disadvantage of the analogue is the possibility of skewing of the anchor in the channel for acceleration, which can lead to a significant increase in the resistance of the movement of the armature and rapid technical wear of the channel for acceleration (accelerator barrel).

A known armature for a reycotron (body for a reycotron that is thrown), which contains a main part, a tail part and a plasma-generating insert between them, the main part is connected to the tail part by means of a jumper, the plasma-generating insert is made in the form of a ring and fixed on the jumper. Moreover, the ratio of the diameter of the jumper to the diameter of the body being thrown is a function of the plasma pressure and the structural parameters of the anchor (A.s. 1809285 USSR,

IPC? 428 6/00. A throwing body for a railtron/ Bakhtin B.I., Belyakov Yu.Y., Ivashov A.I.,

Turenko A.A. The applicant and patent owner is the Scientific Research Institute of Thermal Processes (ZM). - MO 4899056/23; statement 02.10.1990; published 15.04.1993, Bull. Mo 14).

The advantage of the analog is that it achieves an increase in the acceleration of the anchor. But this result could only satisfy the needs of the 90s of the 20th century, and is already insufficient for modern reikotrons. In addition, the tail part is not used as a throwing body, but is destroyed in the raycotron channel after the plasma explosion. This significantly reduces the useful mass of the anchor and can lead to damage to the entire reikotron. These are the disadvantages of the analogue.

A known anchor for a reikotron (shell for an electromagnetic reikotron), according to IRaiepi 7,526,988 05, C1. BROTHER 1/00 (2006.01). Eiesitotadpeiis gaidyp rgoiiestsye/ Juoidiav 9. EIDeg (05);

Te Voipd Sotrapu (05).-11/432,575, 11.05.2006; 05.05.20091, which we take as a prototype.

In the analogy, the anchor for the radiotron contains an aeroshell; armature integrated into the airfoil near the center of mass of the anchor; flaps attached to the airfoil with valves, the flaps being moved and retracted in flight to and from the airfoil to control the armature trajectory in flight, the armature passing current from one

From the electromagnetic rail through the armature to another electromagnetic rail to start the armature, the airfoil is defined by holes, and the armature surfaces pass through the holes to contact the rails. In addition, the armature includes an insulator surrounding the armature within the air jacket to isolate other components of the armature from the current flowing through the armature when that armature is started; the anchor has a mass in the range of 6-20 kg; the anchor additionally contains a guidance, navigation and control system. Armatures can be made of aluminum, copper, silver-impregnated tungsten, or copper-impregnated tungsten. The insulator may contain high-strength, high-temperature plastic.

The advantage of the analog is that it allows you to increase the useful mass of the armature, since the parasitic mass can be converted into useful mass, because the armature is not thrown away, as in traditional reikotrons. The advantage of the prototype is also the fact that it allows you to control the trajectory of the anchor during flight.

The drawback of the analog is that it is not effective enough: in the prototype, the reaction intensity of the interaction between the anchor fragments and the target material is insufficient; in the prototype, it is difficult to provide a quick preliminary acceleration of the anchor to the entrance to the railcotron channel, which leads not only to increased erosion of the rails, but also to a decrease in the efficiency of the acceleration of the next anchor.

The invention is based on the task of increasing the effectiveness of the anchor by increasing the acceleration efficiency of the anchor (increasing the muzzle energy of the anchor) and by increasing the intensity of reactions of the interaction of the anchor fragments and the target material.

The problem is solved by the fact that in an anchor for a radiotron, which contains an aeroshell, fittings integrated into the aeroshell near the center of mass of the anchor, as well as flaps attached to the aeroshell with valves, while the valves are pushed and extended during flight from and to the aeroshell for controlling the armature's trajectory in flight, with the armature passing current from one rail through the armature to the other rail to accelerate the armature, the air jacket includes holes through which the armature surfaces pass to contact the rails, the armature includes an insulator that surrounds the armature inside the air jacket to isolate other components of the armature from the current that passes through the armature, the armature additionally contains a guidance, navigation and control system, according to the invention, the airfoil has an axis of symmetry and contains a front part of a streamlined shape made of a relatively soft, ferromagnetic material, in which a ring magnet is placed, the axis of which coincides with the axis of symmetry of the airfoil, contains 60 the middle part with a pointed nose, of a relatively hard, heavy and non-magnetic material, and containing a rear part of a relatively light non-magnetic material, to which flaps of the same material are attached, and within which are closely packed balls of the same material as the middle part of the airfoil, and the balls are in tight contact with the rear wall of the middle part, which has the shape of a cone, the internal angle of which is equal to 120" and is directed in the direction of movement of the anchor.

The symmetrical shape of the airfoil - with the axis of symmetry - ensures the balance of aerodynamic forces during the flight of the anchor and a stable flight trajectory. This ensures that the anchor hits the target.

The front part of the airfoil is designed to minimize aerodynamic drag, so it has a streamlined shape. This increases the speed of the anchor and the collision energy. Secondly, the front part of the airfoil is designed for the first contact with the target, so it is made of a relatively soft material. When the anchor collides with various targets, the front part contributes to anchor engagement with the target not only in the case of a frontal impact, but even in the case of a tangential, sliding collision, reducing the possibility of ricochet. Thirdly, the front part of the aerofoil is designed for preliminary magnetic acceleration of the armature, therefore it is also made of ferromagnetic material. Thus, the front part of the airfoil is made of a relatively soft ferromagnetic material, for example, of mild steel, or electrical steel, or technically pure iron. A ring magnet is placed inside the front part, the axis of which coincides with the axis of symmetry of the airfoil. This ensures symmetrical magnetization of the front part and effective pre-excitation of the entire armature, since the magnetic field of the pre-excitation device will interact with the powerful magnetic field of the front part.

Obviously, the magnetic orientation of the pre-acceleration device must be matched with the magnetic orientation of the ring magnet to ensure the desired direction of armature movement, but this is very easy. It is rational to use a powerful ring magnet of the following options: rare earth magnet (Ma-Re-B, 5t-Co) or magnetoplast (based on Ma-Re-

B), or magnets based on BRe-Si-So (|Magnets and magnetic fields. Access mode: perz/Lymly.Kakgtav.pi/dos/tadpeiv-apa-tadpeiis-tivi|av5. piti).

Further. The middle part of the airfoil has a pointed nose, and is made of a relatively hard, heavy material, because when the anchor collides with various targets, it is designed to penetrate the internal volume of the target. In addition, the middle part should be with

From a non-magnetic material (diamagnetic or paramagnetic) so as not to transfer magnetization to the back of the aerosphere and thus not block flaps and valves. Therefore, the middle part is made of a relatively hard, heavy and non-magnetic material, for example, tungsten alloys or uranium-238 alloys. When the anchor collides with very hard and strong targets, the middle part of the airfoil penetrates into the internal volume of the target and generates a large volume of supercritical fluids and plasma, which is carried out as a result of the kinetic impact and subsequent penetrating penetration of the flying fragments into the target material. This contributes to the overall destruction of the target. When the anchor collides with weak targets, the middle part may not have time to generate the necessary volume of supercritical fluids and plasma, because it will pass through the target on departure. But, in this case, the middle part will sharply reduce the flight speed due to contact with the target. And then the rear part of the airfoil will work, since the rear wall of the middle part has the shape of a cone, the inner corner of which is directed in the direction of the anchor's movement; this is needed to spread the balls of the rear part.

The rear part of the airfoil is made of a relatively light non-magnetic material, where the flaps and valves of the same material are attached. A light non-magnetic material is most effective for performing the functions of the rear part. Namely, for the operation of valves and flaps that control the trajectory of the anchor during flight. The non-magnetic material (diamagnetic or paramagnetic) of the rear part prevents magnetization and sticky blocking of flaps and valves. In addition, the light material does not overload the anchor. Therefore, the rear part is made, for example, of titanium or aluminum alloys, or of a composite material. The rear part of the airfoil is activated when the anchor collides with weak targets, because inside the rear part there are densely packed balls of the same material as the middle part of the airfoil - a relatively hard, heavy and non-magnetic material (tungsten alloys or uranium-238 alloys ). Since the balls are in tight contact with the rear wall of the middle part, which has the shape of a cone, the inner corner of which is directed in the direction of the anchor's movement, then upon collision and a sharp decrease in the anchor's flight speed, the balls will fly into the internal volume of the target. This becomes possible because the middle part of the airfoil will already make a through hole in the target. It is obvious that the walls of the rear part must be made thin enough so that they are easily destroyed when they collide with the target and do not interfere with the flight of the balls. These balls will generate the necessary volume of supercritical fluids and plasma in the internal volume of the target and contribute to the overall destruction of the target. Dense packing of balls allows rational use of the volume of the anchor, because it reduces the volume of voids. If the inside back wall cone angle of the middle part is 120", then the balls will fit tightly to it. Also, according to our estimates, with this back wall cone angle (ie 120") the balls will fly in all directions into the interior volume of the target , destroying Her as much as possible.

The invention can be used to study phase transformations of various substances, including supercritical fluids in geology (when shelling mining rocks and drilling wells), to destroy asteroids both in outer space and in the atmosphere, to study the destructive action of high-speed macrobodies upon collision with various targets (including, in cases of penetrating penetration into the target and generating at the same time a significant volume of supercritical fluids and plasma), and may also find use in military affairs.

The conducted comparative analysis shows that the patented device has significant distinctive features compared to the prototype, and the set of features contributes to the solution of the task.

Analogously, the airfoil is made of a composite material or metal such as steel, tungsten, titanium, or other suitable alloys, and has a variety of shapes. This is done to generate a small lifting force. In the claimed invention, the aerofoil has a symmetrical shape - with an axis of symmetry - to ensure the balance of aerodynamic forces during acceleration and flight of the anchor, and the stability of the flight path, as well as for a guaranteed hit on the target. This is more important in conditions of such high speeds, reaching 2-3 km/s and more.

The presence of the front, middle and rear parts in the airfoil allows to increase the effectiveness of the anchor when encountering various targets, as indicated above. | on the contrary, such efficiency cannot be achieved in the prototype. For example, if the prototype airfoil is made of a relatively light composite material, then the anchor will not be able to destroy a strong target at a long distance, or make a hole in it. Or, if the prototype airfoil is made of tungsten, then the anchor will not be able to destroy a weak target, but will only pass through the target on departure. In many cases, this is not enough. Moreover, in the case of a tangential, sliding collision, the anchor can create a ricochet, which is also unsatisfactory.

Analogously, a steel anchor can be pre-accelerated using magnetic acceleration.

But the ferromagnetic material (steel) of the anchor when the magnetic field of the device is turned on

From the previous acceleration, the magnetization gradually increases with a phase delay. This leads to a delay in the acceleration of the armature. In the claimed invention, the ferromagnetic front part of the airfoil is already magnetized by a powerful magnetic field due to the action of a powerful ring magnet. Therefore, there is no delay in the acceleration of the anchor, which leads to an increase in flight speed and collision energy. It is obvious to a person skilled in the art that the magnetic orientation of the pre-acceleration device must be coordinated with the magnetic orientation of the ring magnet to ensure the desired direction of movement of the armature, but this requirement is very easy to satisfy.

The drawings explain the essence of the invention.

In fig. 1 shows the general view of the anchor.

In fig. 2 shows how the front part of the armature with the ring magnet inside interacts with the magnetic field of the pre-acceleration device.

In fig. C shows the process of anchor collision with a strong iron asteroid.

In fig. 4 shows the process of anchor collision with a weak stone-ice body.

Fig. 1 shows the general construction of the anchor (side view and rear view). The anchor contains a front part 1 made of mild steel, in which is placed a ring magnet 2 of the Ma-Re-B type, the axis of which coincides with the axis of symmetry Z of the aerosphere. The anchor contains a middle part 4 with a pointed nose, made of tungsten, and the back wall of the middle part has the shape of a cone, the internal angle of which is equal to 1207 and is directed in the direction of movement of the anchor. The anchor also contains a rear part 5 made of aluminum, where flaps 6 are attached, and inside which tungsten balls 7 are placed in a dense package, and the balls are in tight contact with the back wall of the middle part. The diameter of the balls 7 can be 5-25 mm, and the thickness of the aluminum wall of the rear part, as a rule, does not exceed 2-3 mm. As in the analogue, the anchor can additionally contain a guidance, navigation and control system 8. As in the analogue, in the claimed invention, the flaps 6 can be equipped with valves (not shown in the figure), while the valves are pushed and extended during flight to control the trajectory of the anchor during flight. In the analog, flaps with valves are made of composite material or of steel, tungsten, titanium or other alloys. In the claimed invention, flaps with valves are made of diamagnets or paramagnets to prevent magnetization and blocking of flaps and valves. Therefore, flaps, valves and the rear part are made, for example, of aluminum. Flaps, valves and the rear part can be made of a diamagnetic composite material (for example, graphite-glass/epoxy, as in the prototype). As in the prototype armature 9 can be made of aluminum, copper, silver-impregnated tungsten or copper-impregnated tungsten |Tungsten. Access mode: por//teiaP speskKim-ropai.gi/taiKki teiaPom/my|. The insulator 10 surrounding the armature 9, also, as in the prototype, can contain a high-strength high-temperature plastic, for example, MM ATCOMF og GEHAMO (see |Muiaygop. Egot UMmiKiredia, (Shee yieeee epsusioredia)|, or |Lexan. Material from

Wikipedia - the free encyclopedia|). In the side view, it is possible to see the side surface of the armature 9, which is in contact with the reikotron rail (the reikotron is not shown in the figure). In the rear view, it is possible to see how flaps 6 work.

Consider the process of preliminary acceleration of the anchor (Fig. 2). The ferromagnetic front part 1 together with the powerful ring magnet 2 generate a powerful magnetic field Vi, the orientation of which is indicated by the arrows in Fig. 2. The orientation of the magnetic field B" of the pre-acceleration device 11 is coordinated with the orientation of the magnetic field Vi (Fig. 2). Therefore, the armature is pulled in the direction of the pre-acceleration device 11 and into the acceleration channel in the reikotron (not shown in the figure).

Let's consider the process of the interaction of the anchor when it collides with an asteroid or the nucleus of a comet (Fig. 3-4).

In fig. From the anchors along the trajectory 12 plunges into the solid iron asteroid 13. The main direction of impact 14 provides a well in the asteroid, and fragments of the middle part 4 ensure the destruction of the asteroid (large black arrows). In addition, when balls 7 fly apart, the part of the asteroid that is located near the point of collision with the anchor is destroyed (small black arrows). In fig. 4 anchor along the trajectory 12 is thrust into a weak rock-ice asteroid or into the core of a comet 13. In many cases, this will lead to the passage of the main fragments of the anchor 14 on departure through the target, but the balls 7 will destroy the asteroid or the comet core due to flight (black arrows).

According to preliminary calculations, such a technical solution will be effective, and the required technical result will be achieved.

Claims (1)

DISCLOSURE OF THE INVENTION An anchor for a radiotron comprising an aerofoil, fittings integrated into the aerofoil near the center of mass of the anchor, and flaps attached to the aerofoil with valves, wherein the valves are designed to move apart and extend in flight from and to the aerofoil for control the flight path of the armature, while the armature is made with the possibility of passing current from one rail through the armature to another rail to accelerate the armature, the air jacket includes holes through which the surfaces of the armature pass for contact with the rails, the armature contains an insulator that surrounds the armature inside the air jacket, for insulation of other components 35 of the armature from the current that passes through the armature, the armature additionally includes a guidance, navigation and control system, which is distinguished by the fact that the airfoil has an axis of symmetry and contains a front part of the streamlined form of the first material, which houses an annular magnet, the axis of which coincides with with the axis of symmetry of the airfoil, contains the middle part of pointed nose of the second material, contains a rear part of a third material, to which flaps of 40 of the same material are attached, and inside which are placed in a dense package balls of the second material, and the balls are in tight contact with the back wall of the middle part, which is in the shape of a cone, the inner whose angle is 1207 and is directed in the direction of motion of the armature, while the first material is ferromagnetic and softer than the second material, the second material is non-magnetic, harder and heavier than the first and third materials, and the third material is 45 non-magnetic and lighter than the second material . om: SHIN M IN what - is PO about MK Sho nn 7 a Fig. 1. 14 uk shi Ne v u dit nn V u i v. Goryaetnknnosya yy Fig. 2 1 Z She oo an y Sho vi Kai z Z i x - i same Z dnk spra a E still she she i se; 18 m she men dok I eat and ee tutu rn i and 7 ee kA AAAT Ak olyachan i "y E MAO in; sha: 7 In ky zn Y hron o Fig.Z 15. -- ka ra a M «o 14 sho NE . Z tya OT i ih Z ek g y ih kh as sho vi She it re and re M things t a o kA and shk Fig. 4