RU2325614C2 - Construction of hypersonic projectile with self-pressurizing compressive detonation jet engine having high working pressure and using high explosive charge for propulsion - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: projectile comprises engine having an open-ended detonation chamber with a rear exhaust nozzle and annular exhaust windows that rise above the outer surface of said chamber at its front end face and are double-layer at the inlet and single-layer at the outlet. In the centre of the detonation chamber there is a double-layer cylindrical propulsion charge with semispherical end faces. Said propulsion charge consists of explosives having a higher brisance in the top layer and fourteen electric detonators that are mounted being diametrally opposed and equally spaced one to another in three planes perpendicular to the axis in the top layer and at the end faces. At the front end face of the propulsion charge over a hole in the centre of the interior end cover of the detonation chamber housing over there is a semispherical detonation wave baffle turned with its concave side towards the propulsion charge. The engine is connected via a welded coupling sleeve to the charge housing that is tightly inserted into the border of said sleeve. Walls of the coupling sleeve are provided with air vents, and inside the sleeve there are from 4 to 8 pyrovalves for discharging pressure from the cavity of the detonation chamber. Ejectable obturators are mounted on the surface of the charge housing.

EFFECT: increasing the flight velocity and destructive capacity of the projectile.

1 dwg

Description

1. The technical field to which the invention relates.

The invention, depending on the dimensions of a self-compressing compression detonation rocket engine / RD / high working pressure with a fuel charge of a blasting explosive and the implementation of an uncontrolled or controllable version of a projectile, relates to hypersonic ultra-long-range rocket artillery and hypersonic combat rocket technology with a flight range depending on flatness or ballistic trajectory, in a single-stage design - up to about one hundred kilometers, in two - three-stage design - up to several As many as thousands or more kilometers with the possibility of hitting targets not only on the ground, water surface and under water / when using detonation taxiway data in torpedo missiles /, but also in near-earth orbit for a short flight time unattainable for any modern rocket technology.

These self-compressing compression detonation taxiways can be widely used as very effective / ten times higher than the capabilities of the solid propellant rocket propulsion / launch accelerators currently used for these purposes for some types of modern rocket and aerospace equipment that can withstand the huge overloads occurring in the Earth’s atmosphere during the operation of such accelerators .

These self-compressing compression detonation RDs, due to the high working pressure in the detonation chambers and the presence of powerful ether generation-disintegration / or fracture fracture / large corpuscular particles of the working fluid / fuel charge detonation products / to the size of ether particles (ether particles in any substance and any medium fill the space between larger corpuscular particles enter the internal structure of corpuscular particles and are two to three orders of magnitude smaller in size than particles, and the fundamental atomic model of constructing matter invented in the 20th century is false), will have high speed and traction characteristics not only in the Earth’s atmosphere, but also in space due to the strong magnetic properties of ether particles in a free disintegrated state and in large quantities Detonation RD data contained in the jet, which will dramatically increase the magnetic support ability of such a highly disintegrated jet. Also, since the overloads created by these detonation taxiways in space are not so significant, they can also be successfully used as very efficient accelerators or accelerating stages of modern low-speed spacecraft.

2. The level of technology

Analogues of the present invention according to the fundamental process of energy release and construction of a self-compressing compression detonation taxiway, which causes this process to appear, does not exist, since in this detonation RD in addition to the energy release from detonation of the fuel charge of blasting explosives, Fig. 1, pos.6, 7, generated by the usual disintegration of corpuscular and ether particles of explosives usual for this process, an additional compression disintegration will also be carried out I of corpuscular and ethereal particles of the detonation products of this charge as a result of their strong compression inside the detonation chamber A of Fig. 1 by an external annular flow around the detonation products themselves, forming a continuous closed dynamic contour of the external self-compression of this detonation RD, leaving the front end of this chamber through the ring outlet windows With figure 1 and flowing around it but the outer surface towards the rear exhaust nozzle of figure 1, item 9, causing additional compression / from strong compression / energy a phenomenon accompanied by unusual usual detonation by plasma generation and powerful ether generation. At the same time, the detonation wave (detonation products) exiting through the annular outlet windows C of FIG. 1 will align and maintain equal pressure on the outer surface of the housing of FIG. 1 almost immediately from the beginning of detonation. 5 of the detonation chamber A of FIG. 1 and inside this chamber, and due to the powerful magnetic properties of the highly disintegrated detonation products, the annular stream / external self-compression loop / detonation products that flows around the outside of the detonation chamber will have / due to the strong magnetic attraction of the particles inside the specified stream and its attraction to a detonation chamber with a large array of particles with strong magnetism / high stiffness, a fixed shape and position in space, which will exclude for the reasons indicated explosion chamber when activated detonation of the detonation RD, if properly selected its basic design parameters specified in Section 5 of this description.

The powerful ether generation that occurs during additional compression energy generation, which is unusual for ordinary detonation, will very strongly / ten times / increase the traction characteristics of these self-compressing compression taxiways, and the high working pressure in the detonation chamber A of Fig. 1 will create a very high flow rate at the exit nozzle and outlet windows giving hypersonic flight speed to rockets, war missiles and high flight dynamics to accelerated objects, the detonation of which will work amb order of 10 seconds or more due to an additional compression energy.

Compression disintegration of the working fluid and compression energy release in a much weaker and faster variant of manifestation takes place in diesel engines in compression strokes until the working mixture ignites, which then merge with disintegration and energy release from the combustion process. Moreover, these processes, due to weakness and transience, are practically indistinguishable separately, modern science does not yet understand this, as well as the fact that all energy release processes that occur with increasing pressure and plasma generation in any substances and in any medium are always generated by the disintegration of their corpuscular and ether particles.

In addition, due to the presence of strong ether generation when the detonation taxiway data is triggered, which will be accompanied by the nozzle of FIGS. 1, 9 and windows C of FIG. 1, directed fundamental ether radiation, capable of causing a noticeable ether transformation of the substance at a certain distance / fast the conversion of chemical elements / objects that fall into the band of this radiation, it will be necessary to observe some radiation measures during the testing and operation of rockets, war missiles and accelerators with such detonation taxiways constant security in the place of start-up and protection of calculation of the launcher from the etheric radiation.

3. Disclosure of invention

The essence of the invention lies in a special open from two ends design of the detonation chamber A of FIG. 1 of this taxiway, freely releasing a detonation wave / detonation products / explosive charge of FIGS. 1, 6, 7 not only from its rear end into the surrounding space / as in all modern taxiways / through the rear outlet nozzle of Fig. 1, item 9, but also from the front end to its outer surface with an external annular flowing stream - through the annular gap between the end face of the housing of Fig. 1, item 5 of chamber A of Fig. 1 and the inner end cap figure 1, pos. 18 camera And figure 1 also through a large outlet in the center of this cover and the gap between the inner and outer end caps of FIGS. 1, 18, 19 of chamber A of FIG. 1 of the input two-layer part of the annular exhaust windows C of FIG. 1, which are directed with their single-layer output part into the side of the rear exhaust nozzle of figure 1, item 9, while summing up its supporting reactive channels, which dramatically increases the thrust. In addition, the essential features of the invention are the design of threaded joints F, G dynamically sealed by a passing detonation wave / detonation products /, the shape and arrangement of a two-layer fuel charge of blasting explosives of FIGS. 1, 6, 7, the number and location of electric detonators in it, FIG. 1 , pos.8, as well as the presence of gaps between the fuel charge of Fig.1, pos.6, 7 and the casing wall of Fig.1, pos.5, between the inner and outer covers of Fig.1, pos.18, 19 of the front end of the detonation chamber And figure 1 and the presence in it of a concave deflector det Nazioni wave 1, item 12. The indicated gaps and deflector will have a significant damping effect on the body, pos. 5 and end caps, pos. 18, 19 of the detonation chamber A of Fig. 1, as well as on the annular exhaust windows C of Fig. 1 during the initial detonation period upon the exit of the annular flow of detonation products on the outer surface of the detonation chamber, which will help maintain the integrity of this taxiway when triggered.

The device diagram of a hypersonic missile with a self-compressing compression detonation RD of high working pressure is shown in Fig. 1 and includes the following notation:

A — self-compressing externally by the detonation wave — detonation products exiting through the annular outlet windows of the detonation chamber, in which compression disintegration of the detonation products of the fuel charge is performed, items 6, 7;

B - ventilation windows / in the amount of the order of 10 ... 15 /, cut in the wall of the docking cup, pos.3;

C - towering above the outer surface of the body, pos. 5, chamber A, two-layer in the entrance part and single-layer at the exit ring outlet windows / having parallel coaxial walls in section / with welded dividing ribs pos. 14, 15 and ring caps pos. 16, 17, providing exit detonation wave / detonation products / to the outer surface of the housing, pos. 5 from the front end of chamber A with a turn towards the rear exhaust nozzle, pos. 9, flow around the housing of pos. 5 with an external annular flow / external self-compression contour / p oduktov detonation and the formation of part E of the reference channel jet;

D is the inner linear part of the reference reactive channel, which is formed upon the exit of the detonation products of the fuel charge pos.6, 7 through the rear exhaust nozzle pos.9 and summed with its part E;

E is the outer annular part of the reference reactive channel, formed by the detonation products of the fuel charge pos.6, 7, emerging through the annular outlet window C, and summed with its part D;

F - threaded connection / with any large special thread / outer end cap pos.19 of the front end of chamber A with an outer ring cap pos.16 two-layer in the input part of the annular exhaust windows C with one-sided dynamic sealing preload by the detonation wave / detonation products / through an inclined annular conical surface "a";

G - threaded connection / with any large special thread / inner end cap pos. 18 of the front end of chamber A with an inner ring cap pos. 17 two-layer in the inlet part of the annular exhaust windows C with two-way dynamic sealing preload by the detonation wave / detonation products / through inclined annular conical surfaces "a", "b";

pos.1 - missile shell docked through the glass pos.3 and the cover pos.19 with the housing pos.5 of the chamber A of this detonation taxiway, which contains the warhead and elements that provide stabilization and change of the projectile trajectory in flight / including a retractable small plumage from the hull and retractable deflectors changing the flight path at hypersonic speed /;

pos.2 - one or several / depending on the length of the projectile / installed on the housing pos.1 and abutting against its protrusions of split plastic obturators with front ends cut at an angle to the conical surface, which are discharged from the housing pos.1 of the projectile by an incoming air stream after exit a projectile from an open barrel from both ends of the launch barrel or from a launch container with a knock-out bottom and an opening or knock-out top cover / which is more suitable for military missiles with such detonation taxiways /;

pos.3 - a steel docking cup with a bottom facing the body pos.1 of the projectile, welded by the end of its wall to the cover pos.19, in which, on the back of the bottom, the housing pos. 1 shell;

pos.4 - screws securing the body pos.1 shell to the annular side of the bottom of the glass pos.3;

pos.5 - heat-resistant steel case of the detonation chamber A cylindrical from the side of its front end streamlined tapering towards the nozzle pos.9 shape;

pos.6, 7 - a two-layer cylindrical fuel charge with hemispherical ends, consisting of explosives with different brisance / pos.7 - the outer layer with a thickness of 5 ... 10% of the total diameter of a higher blast explosive than the main charge - pos.6 of explosives with not very high brisance /, mounted in the center of chamber A on the supporting ribs pos. 10, 11 with filling the support points and the free interlayer space of this charge when assembling with some adhesive composition and installing special shock-absorbing belts on the outer side surface of the charge, at the ends s aryad - covers with a thick inner shock-absorbing layer and a rigid outer surface;

pos. 8 - triggered synchronously diametrically oppositely installed at equal distances from each other in three planes perpendicular to the axis and at the ends of the fourteen electric detonators of the fuel charge pos. 6, 7 / Fig. 1 shows only eight of them / located in the outer layer pos. 7 high-explosive explosives and activated by an electric signal to launch a rocket through pos. 9 removed from the nozzle and thinned insulated wires ejected from it at start-up;

Pos. 9 - a heat-resistant steel rear nozzle welded to the rear end of chamber A / round profiled /, providing exit from the chamber A of the detonation wave / detonation products / and the formation of part D of the reference reaction channel;

pos.10 - 6 ... 8 heat-resistant steel longitudinal support ribs of the fuel charge pos.6, 7 located along the axis of chamber A and welded to the inner surface of the housing pos.5 of this chamber;

pos.11 - 2 ... 4 heat-resistant steel end support ribs of the fuel charge pos.6, 7 located parallel to the axis of the chamber A and welded to the inner concave surface of the detonation wave deflector pos.12;

pos.12 - heat-resistant steel concave hemispherical detonation wave deflector, which has a damping effect on the walls of the end caps pos.18, 19 of the chamber A and the cap pos.16, 17 of the annular outlet windows C when the detonation wave exits the chamber A through these windows installed through welded support ribs pos. 13 on the inner surface of the end cap pos. 18, with support ribs welded to its inner concave surface pos. 11 fuel charge pos.6, 7;

pos.13 - 4 ... 6 heat-resistant steel support ribs located parallel to the axis of the chamber A and welded to the inner surface of the end cap pos.18 of the chamber A and the outer surface of the deflector pos.12;

Pos. 14, 15 - heat-resistant steel dividing ribs having the minimum allowable thickness / Pos. 14 - single-layer output part, Pos. 15 - two-layer inlet part / annular outlet windows C, parallel to the axis of the chamber A, welded to the annular caps pos. 16, 17 of these windows and the outer surface of the body, pos. 5 of chamber A, dividing windows C into annular sectors and which are welded supporting elements of their structure;

pos.16, 17 - heat-resistant steel ring covers of windows C / pos.16 - outer cover, covering the entire outside of the single-layer and two-layer part of windows C; pos.17 - inner cover located in the two-layer inlet part of windows C and dividing this part of these windows into two layers / with dividing ribs pos. 14, 15 welded to them and end caps fixed to them with dynamically tightening threaded joints F, G Pos. 19, 18 of chamber A;

pos.18 - heat-resistant steel inner end cover of the front end of chamber A of a convex shape, fixed on the inner annular cover of pos.17 of windows C using a dynamically tightening threaded connection G, with a large outlet in the center, guiding the detonation wave / detonation products / in two streams into the two-layer inlet part of the windows C - through the annular gap between the inner surface of this cover and the end of the case, pos. 5 of the chamber A into the lower layer of the inlet part of the windows C, also through the outlet in the center of this yshki the upper layer portion of the input window through the gap C between the covers poz.18, 19;

pos.19 - heat-resistant steel continuous hermetic outer end cover of the front end of chamber A of a convex shape, fixed on the outer annular cover of pos.16 of windows C using dynamically tightening threaded connection F, guiding the detonation wave - detonation products passing through the hole in the center of the inner face cover pos. 18, into the upper layer of the entrance part of windows C through the gap between the covers pos. 18, 19;

pos. 20 - 4 ... 8 heat-resistant steel pairwise diametrically opposite (Fig. 1 shows only two of them) and pairwise synchronously opening pyro-valves for pressure relief from chamber A with pyro-charges removed from the heat-stressed cavity of the docking cup pos. 3, also with 1, the welded pipelines connected to them from two sides, which are welded into the holes on the outer end cover pos.19 of chamber A and not indicated in Fig. 1, and through the perpendicular axis of the projectile, welded nozzles are welded into the holes on the wall of the glass pos.3 / opening is necessary dimogo amount diametrically opposed pairs pyrovalves poz.20 allow stepwise regulate the operation of the detonation RD, reducing its traction and reducing the velocity of the projectile to be braked effectively welded through the nozzle outlet ducts that eliminate hops shells targets and combat rockets such detonation RD /.

5. The implementation of the invention

A description of the design of a hypersonic missile with a self-compressing compression detonation RD of high working pressure and the principle of its operation is sufficient for understanding from sections 2 ... 4 of the present description, as well as from the diagram of FIG. 1, explaining the invention.

Some design parameters of these detonation RDs, significantly affecting their work, due to the falsity of the ideas of modern science of magnetism, the mechanism of energy release and the absence of any previous experimental experience, along with the energy release from normal detonation of blasting explosives, additional compression energy release from the strong compression of detonation products having a place during the operation of detonation taxiway data and accompanied by plasma generation and powerful ether generation, is necessary Dimo will pick up empirically. Such parameters requiring an optimal ratio, which can only be accurately determined by the test results, are the sizes of the layers of the two-layer fuel charge of FIGS. 1, 6, 7 and their brisance; the size of the orifice of the rear nozzle, figure 1, position 9; the size of the outlet in the center of the inner end cap of figure 1, pos. 18 camera A of figure 1; the dimensions of the annular exhaust windows With figure 1 / as the output in a single-layer, and in the input two-layer part /; strength characteristics / wall thickness / of all the main structural elements of this detonation taxiway, experiencing a large load from the effects of detonation products until they exit through the windows C of Fig. 1 to the outer surface of the body, pos. 5 of chamber A of Fig. 1 / when pressure inside the and outside the chamber A / and heat resistance, also the size of the gaps between the fuel charge of Fig. 1, pos. 6, 7 and the body wall of pos. 5 to the chamber A of Fig. 1 / this important and large gap is depicted in Fig. 1 disproportionately with a decrease in 3-4 aza / and between the inner and outer lids 1, poz.18, 19 front end chamber A 1.

Claims (1)

A missile with a self-compressing compression detonation rocket engine having a detonation chamber open from two ends of the type with a rear exhaust nozzle and two-layer inlet in the entrance part and single-exit ring outlet windows directed towards the outlet nozzle rising above the outer surface of this chamber wherein the detonation chamber includes a cylindrical body from the front end and streamlined tapering towards the outlet nozzle shape and the front convex ends e lids - internal with a hole in the center and external solid tight, fastened with dynamically tightening threaded joints from the end to the inner and outer covers of the annular exhaust windows, which are welded through the ribs to the outer surface of the detonation chamber body, in the center of the detonation chamber on the welded support ribs with gaps from its walls is a two-layer cylindrical fuel charge with hemispherical ends, consisting of explosives in the upper layer with a larger br of similarity with diametrically oppositely installed in the upper layer at equal distances from each other in three planes perpendicular to the axis and at the ends fourteen electric detonators, from the front end of the fuel charge above the hole in the center of the inner end cover of the detonation chamber housing, a hemispherical detonation wave deflector is installed on the welded support ribs, facing its concave side to the fuel charge, while the detonation engine through the welded docking cup is connected to the shell of the projectile, which is tightly mounted on the side of this glass and secured with screws, has ventilation windows in the wall of the docking glass and 4 ... 8 pyro-valves for pressure relief from the cavity of the detonation chamber with welded pipelines and nozzles located perpendicular to the axis of the projectile at the same time, on the surface of the shell of the rocket with an emphasis in its protrusions, split plastic shutters discharged by the incoming air flow are installed with a conical surface cut at an angle ited ends.