RU2362604C2 - Model rocket engine - Google Patents

Abstract

FIELD: health; games.

SUBSTANCE: invention relates to rocket engines for space-rocket simulation in the field of designing development games for youths and children. The said engine has a body with a nozzle, propellant charge, forward head with a delay device, which realises different operation time delays, and blow-off charge. Proposed are different arrangements of channels (with different amount and length) for coordination of firing the delay device at the bottom, apparatus for uniform opening of the surface of the bottom using "combustion leader", different geometries of the bottom. The given arrangements and devices widen the range and number of discrete time delays realised. Proposed is a design of the delay device with smooth change of operation time delay. The design contains duplicated sections of a circular groove with a delay composition in contact with unarmoured parts of the blow-off charge. The blow-off charge can move (rotate, flip over) on the surface of the bottom adjoining it. Adjoining surfaces of the charge and bottom can be made from magnetic material with the aim of compacting through mutual attraction.

EFFECT: increased degree of unification of the engine and mass scale production due to variety reduction.

9 cl, 18 dwg

Description

The invention relates to the toy industry, namely to model rocket engines (MRJ) for space rocket modeling in technical forms of creativity.

It is well known MRP [3, 4], containing a paper or plastic case in which a nozzle, a charge of solid fuel, a pyrotechnic moderator tracer are burned, which burns out with the emission of color or contrast smoke against a sky background to indicate the flight path of the model after the operation of the MRP, and expelling charge that is triggered by a heat pulse (ray of fire) of the moderator and pushes a payload from the model’s body - the next stage of the rocket model, aircraft, rescue equipment, etc. The delay time of the expelling charge is determined by the class of the model and ranges from 0 to 6 ... 7 seconds. The existing nomenclature of engines produced by the industry according to the operating times of the moderators provides for a discrete — by 2-3 intervals — breakdown of the flight time of the model on the passive section of the trajectory to its upper point, for example, 0, 3, 6 seconds, and scatter at the level of plus or minus 20% of the time slowdowns.

Also known is a miniature MRD, the composition of the pyrotechnic moderator of which is pressed not into the body, but into the axial channel of the front bottom, as shown in Fig.6.6 p.149 source [5].

Separation of the front bottom moderator into a separate unit makes it possible to unify its design, using channel equipment with pyrotechnic compositions burning at different speeds to implement different delay times, to simplify autonomous testing and reduce the dispersion of the total thrust impulse of the engine. At the same time, due to a decrease in the mass of the composition, the trace of the passive portion of the flight path of the model somewhat deteriorates.

A common drawback of the MRP of the considered schemes is the unambiguous adjustment of the moderator for a given delay time of the transfer of the firing beam to the operation of the expelling charge, which leads to a significant - two-, three-fold - increase in the nomenclature of the produced MRPs of one class [3].

Known MRI with a moderator, providing the possibility of implementing two times of delay in the supply of a beam of fire for the operation of the expelling charge. So, the engine moderator of the first stage of the PS A (1) 5-1 brand manufactured by Peter Sarnowski, Poland allows you to start the engine of the next stage both immediately after the fuel charge of the engine, the burner (delay 0 sec), and after burnout of the tracer-moderator (delay 1 sec ) For this, an additional nest with a diameter of 3.5 mm is drilled through the perforated front bottom and the moderator layer to the border with the fuel charge and a plastic tube with an internal diameter of 2 mm protruding 12-13 mm above the surface of the bottom is glued. To start the engine of the second stage without delay, fire communication is used in the form of a hollow channel of a tube transmitting a fire beam when the combustion set reaches the input cut of the tube, and to separate the stages with a delay, a fire beam transmitted through perforation of the front bottom after the moderator is burned out.

The disadvantages of the known design include its high complexity, the presence of hazardous manual operations of increased accuracy, such as drilling a nest in a pyrotechnic composition and gluing tubes into it, limiting the diameter of the engine due to the difficulty of placing several holes on the surfaces of the bottoms of small engines (diameter MPA PS A (1) 5-1 is 15 mm, while the largest massjet engine in Russia of the same class has a diameter of 10 mm), as well as slightly worse energy-mass indicators due to incomplete use of energy tracer at zero delay time of the moderator.

From the above MRI analogues, a Polish-made PS A (1) 5-1 engine is selected as a prototype, comprising a housing with a nozzle, a fuel charge sequentially mounted in the housing cavity, a front bottom with a moderator in the form of one or more fire communication channels, and an expelling charge, which is the closest in essence of the invention as providing the ability to select different delay times for the operation of fire communication moderator.

The aim of the invention is to increase the manufacturability and expansion of the functionality of the engine by means of unification of the design of the moderator, expanding the time range and improving the accuracy of operation of fire communication moderator.

The goal in an engine with a nozzle and a fuel charge sequentially mounted in the cavity of the housing, a front bottom with a moderator in the form of one or more fire connection ditches and a discharge charge, is achieved by the fact that the discharge charge along the mating surface of the outputs of the front underbody communication channels is made with the ability to move and partially armored.

The proposed solution can be implemented according to several design schemes.

In the simplest version, the front bottom of the MRP is made with a group of fire communication channels with low-gas slow-burning compositions located in them having different burning speeds. In this case, fire communication with zero delay time can be a channel open at both ends or equipped with a fast-burning train like stopin. At the end of the MRP, the high-temperature products of the combustion of the fuel charge ignite the compositions in the fire communication channels and, as they burn out, through the calculated time intervals, the fire rays reach the outlet openings of the channels on the outer surface of the bottom. When one of these channels comes into contact with an unarmored portion of the expelling charge, a fire beam of fire fire ignites the expelling charge, the combustion products of which perform the work necessary for the functioning of the rocket model — they separate the rocket stages, push out the rescue equipment, etc. When placing fire-retardant communication channels of the moderator and the unarmored portion of the knockout charge on the periphery of the bottom and the knockout charge along circles of equal diameter, the required delay time is achieved by rotating the knockout charge until its unarmored portion is aligned with the corresponding fire connection outlet.

Thus, the proposed solution fundamentally provides the possibility of discrete, in terms of the number of channels, selection of the delay time of the expelling charge. Separation of the moderator bottom into a separate, autonomously developed assembly allows the engine to be unified as a whole, reducing the range of produced engines and engines by 2-3 times and, accordingly, increasing their seriality. The attractiveness of the unified MRP is also increasing for consumers, since there is no need to purchase different models of aircraft with different delay times of the detonating charge of the flight propeller.

The technical implementation of the proposed solution on small-sized MRP with housing diameters of the order of 10 ... 13 mm is fraught with a number of limitations. Thus, stable combustion of small-gas compositions in the channels without extinguishing from heat loss is provided in channels with minimum diameters of the order of 2-3 mm, which limits the number of fire links placed on the bottom to 2 ... 3. The use of more energetic compositions in the moderator instead of small-gas ones leads to the need for thorough sealing of the mating surfaces of the bottom and the knockout charge to prevent flame penetration from the previously opened fire connection, which complicates the design and reduces the accuracy and reliability of the moderator, increases the complexity and cost of manufacturing the mrd.

The above schematic diagram of the implementation of the MRD moderator in the form of fire communication channels of the same length with compositions burning at different speeds is not the only solution to ensure a discrete change in the delay time. Given the high cost of the compositions of pyrotechnic moderators, which are 1-2 orders of magnitude higher than the cost of structural materials used in MRP - cardboard, plastics, ceramics, the solution of the problem of ensuring the simultaneous supply of a fire beam to the surface of the front bottom can be performed by other, less expensive means than using one igniter of several pyrotechnic compositions. In particular, the difference in the opening times of the fire holes of the fire channels or their length, including filling the channel not to the full length, can be used, which makes it possible to reduce the range of retarder compositions to one common for equipping all fire channels.

The subsequent versions of the engine are the development of the basic idea of creating a high-tech engine with the possibility of expanding the range and accuracy of the response time of the moderator.

An MPP is proposed in which the fuel charge is bonded or tightly in contact with the inner surface of the front bottom, the shape of which and / or the arrangement of the inputs of the fire communication channels on it and / or the shape of the fuel charge are made with the possibility of simultaneously opening the inputs of the channels of the moderator with a burning fuel arch.

This generalized MRI scheme is easily realized theoretically enough, for example, the inner surface of the lid can be made of any acceptable shape that does not coincide with the shape of the surface of the fuel charge burning at the end of its operation, and the inputs of fire communication channels should be placed in sections with different opening times. With equal channel lengths, fire pulses on the outside of the bottom will be shifted in time by the difference in the opening time of the inputs. In practice, in order to obtain an acceptable difference in the time of opening of the fuel charge of various, also usually axisymmetric, sections of the bottom by an axisymmetric burning arch of the bottom, it is necessary to form a relatively steep front of fuel charge burning at the end of the MRP operation.

For this purpose, it was proposed to install an elongated element from a material with increased thermal diffusivity, for example, copper or aluminum, from which the inputs of the fire retardant communication channels are placed at different distances in the fuel charge from the front bottom side. Intensified heating of the fuel adjacent to the element sharply - up to 3 ... 4 times - increases its local burning rate, and along the element, performing a kind of "leader of combustion", a conical surface of combustion is formed with a semi-corner of the apex up to 15 ... 20 degrees. A definite drawback of this solution is the prolonged pressure drop and the resulting energy loss.

It is proposed to perform the front bottom flat outside, and on the fuel charge side with a central recess, on the periphery of which fire retardant communication channels of the moderator are available, of variable length. This form organically and technologically rationally combines a variety of structural and functional requirements for the unit - its reliable fastening with the engine housing, provided by the maximum thickness of the bottom on the periphery, and the placement on the surface of the lid of fire communication channels of various lengths from the largest along the periphery to the smallest along the axis.

It is proposed to perform the front bottom on the side of the knockout charge at an angle to the longitudinal axis of the engine, and the knockout charge in terms of an elliptical shape with the possibility of installing it on the bottom by turning 180 degrees and / or flipping to the other side. The implementation of the two delay times is ensured by the execution on the inclined outer surface of the bottom of the two fire communication channels of different lengths, symmetrical and maximally spaced along the major axis of the ellipse, and by booking the mating surfaces of the expelling charge except for the contact zone with the channel. By setting the expelling charge to the unarmored portion in one of two positions, fire contact with the fire communication channel of the corresponding length and, correspondingly, a predetermined response delay time is ensured.

To realize three delay times on the bottom along the minor axis of the ellipse, a third fire link is made, and the plate charge on one side has an unarmored portion along the minor axis of the ellipse, for example, in the form of a strip. In this case, the extreme delay times are provided by installing a knock-out charge with a rotation of 180 degrees without turning, and the average time by turning the charge on the other side. The wad, closing the expelling charge, can be performed with an inclined end surface to maintain the axial alignment of the engine.

To smoothly control the delay time, an engine is proposed in which the moderator is capable of continuously moving the contact point along the length of the fire communication channel with the unarmored portion of the expelling charge. This circuit solution allows, depending on the length of the channel and the burnup time of the moderator composition in it to the point of contact with the unarmored surface of the expelling charge, to control the response time in the range of the burnup time of the channel length.

An MRD implementing this circuit design is proposed, in which the final part of the fire communication channel is made in the form of a gutter on the outer surface of the front bottom. The lead-in initial fire communication section can be equipped with a retarder in whole or in part or be completely hollow, duplicated, have a cross section of various shapes, for example, in the form of a through slot on the lateral peripheral surface of the bottom. When combining the unarmored part of the expelling charge with the end surface of the slot, the moderator provides the minimum response delay time after burning out the fuel charge of the engine. The peripheral placement of the engine feed channels of the fire communication channels and their duplication allow to ensure reliable operation of the moderator in a limited space of the bottom of a small engine.

A variant of the engine with a trough partially passing through the center of the bottom and with an expelling charge made with the possibility of its overturning to the other side is proposed. Such a design of an invertible expelling charge with an unarmoured central portion on the invertible side provides smooth and uniform control of the delay time of the moderator in the entire - from zero to maximum - time range of combustion of the retarder.

The creation of a powerjet engine with continuous control of the moderator response time according to the schemes discussed above opens up fundamentally new opportunities for improving sports models of aircraft and unifying the propulsion system itself. Compared with an engine with a discrete breakdown of the time range of the operation delay, such an engine makes it possible to compensate for variations in the energy characteristics of the engine, wind and temperature start conditions.

An engine is proposed in which at least a part of the mating surfaces of the front bottom and the knockout charge are made of mutually attracting magnetic materials. Such a solution, providing mutual attraction and sealing of the contact between the movable elements of the engine, reduces the possibility of a breakthrough of a fire beam from a previously opened fire link through the seal, increases the accuracy of the moderator, the reliability and safety of the engine.

Creation of hard magnetic polymer materials, including for coatings and bookings, refers to well-established technological processes and is widely used in the production of elastic permanent magnets. Such materials have a sufficiently high coercive force and residual induction, a wide loop of magnetic hysteresis. As magnetically solid powdered fillers, ferrites of strontium, barium, iron oxides, etc. with a high specific surface and various degrees of filling of polymers are used - up to 90% wt. After manufacturing, magnetic materials or profile products from them are pulled through a magnetizing unit and used in the form of elastic and solid magnetic plates and coatings for various devices and toys.

In technology, in particular in anti-aircraft artillery, remote powder fuses with a similar principle of action are known [2]. In the remote tubes of such fuses, between the igniter capsule and the detonator capsule, a powder composition is placed, pressed into the troughs of three distance rings placed in layers and interconnected by transfer openings for the passage of the flame. The distance rings are arranged so that they can be rotated using a special key and thereby shorten or increase the length of the powder path. The burning speed of the powder is constant, therefore, by changing the length of the powder path, it is possible to change the burning time of the powder and, thus, provide the projectile with the ability to fly a given distance and explode at the desired point on the trajectory. During operation of the moderator, the powder compositions of the upper, middle, and then lower rings are sequentially ignited and burned out. After burning out the powder composition corresponding to a given installation, a beam of fire enters the detonator igniter capsule. A scale is marked on the lower distance ring with the divisions corresponding to the burning times of the powder composition, and on the side surface of the casing is the installation risk, relative to which the fuse is installed.

Given the similarity of the techniques used, the proposed design of the MRI moderator is characterized by a number of significant differences from the described analogue, the aircraft projectile moderator. The retarder MRI is at the same time part of its body, which performs the function of a power element loaded with pressure from the front bottom and structurally combined with it. In the proposed moderator, the number of links of the fire chain is reduced from five to three, the mutual displacement of the expelling charge and the bottom is carried out not only by turning, but also by reversing the expelling charge to the other side, which is due to accessibility to the node from the front end of the engine, which is absent in military products and space rocket technology. The MRI moderator implements a “zero” delay of the response time, which is objectively absent from the projectile moderator analogue and the simplicity of the fire communication channel in the form of slots on the side surfaces of the bottom, which is completely unacceptable to military equipment. The fixation of the position of mutually moving elements and the sealing of mating surfaces with the help of magnetic materials and duplication have been introduced, which provides the required level of MRP reliability with more affordable means compared to highly reliable expensive systems of rocket and space technology [1].

The invention is illustrated in the drawings, where are schematically shown:

figure 1 - General view of the engine;

figure 2 is a view A of the moderator in figure 1;

figure 3 is a view of B on the expelling charge in figure 1;

figure 4 is an embodiment of the MPP with a charge equipped with a "leader of combustion";

figure 5 - view In the moderator in figure 4;

in Fig.6 is a view of G on the expelling charge in Fig.4;

in Fig.7 is an embodiment of the engine with a conical shape of the front bottom;

in Fig.8 is a view of D on the expelling charge in Fig.7;

figure 9 is an embodiment of the engine with an inclined outer surface of the front bottom;

figure 10 is a view of E on the moderator in figure 9;

figure 11 is a view of G on the expelling charge in figure 9;

in Fig.12 is a view of And on the discharge charge in Fig.9;

in Fig.13 is an embodiment of the engine with smooth control of the deceleration time;

in Fig.14 is a view of K on the moderator in Fig.13;

in Fig.15 is a view of A on the expelling charge in Fig.13;

in Fig.16 is an embodiment of the MPP with an axial fire communication channel;

in Fig.17 is a view of M on the moderator in Fig.16;

in Fig.18 is a view of H in the discharge charge in Fig.16.

The MAJ shown in Fig. 1 contains a housing 1 with a nozzle 2, a solid fuel charge 3 with a bore 4 forming the initial combustion surface, a front retarder 5 with channels 6, equipped with small-gas compositions 7 with different burning speeds, and an expelling charge 8. The channels 6 of the moderator, as shown in figure 2, are located on the periphery of the bottom 5 on the same circumference, and the surface of the bottom, which is conjugated with the expelling charge 8, has a magnetic coating. The knockout charge 8, which is a porous disk plate made of pressed black powder with technological additives, is covered on the mating surface with the bottom, excluding the portion of the hole 10, with a magnetic armor and due to mutual attraction is tightly attached to the bottom 5. In addition, charge 8 has the ability rotation, performed using a key (not shown) installed in the socket 11 to combine the unarmored portion 10 with one of the output channels 6 of the bottom.

Work MRD. Before using the MRP, a key is installed in its housing with protrusions interacting with the slots 11 of the knockout charge 8, and by turning the key, the unarmored portion 10 of the knockout charge 8 is combined with one of the output channels 6 on the bottom 5, which provides the closest to the estimated deceleration time. An electric igniter (not shown) is introduced through the nozzle hole into the cavity of the bore 4, which is an incandescent spiral with a pyrotechnic coating applied to it. When an electric current is supplied to the spiral, the pyrotechnic coating ignites, from the combustion products of which the surface of the bore 4 of the fuel charge 3 ignites. The gases formed during the combustion of the charge 3 flow out of the nozzle 2, creating a reactive thrust. When the charge 3 is burned out, the surface of the front bottom 5 is opened and compositions 7 in the channels 6 of the moderator are set on fire from a high temperature in the body cavity. As the compositions burn at the exit from the channels, fire rays are formed, one of which, in contact with the unarmored portion 10 of the expelling charge 8, ignites it.

Figure 4 shows an embodiment of the engine with a fuel charge 3, fastened to the front bottom 5 and provided with a needle 12 made of a material with high thermal diffusivity. The local burning rate of the fuel along the needle due to intense heating of the adjacent fuel layer is significantly, several times higher than the normal burning rate, as a result of which a cone burning surface 13 is formed in the charge along the needle, after burning part of the arch L, 13. It provides a consistent depending on the distance from the axis, opening of channels 6 and ignition of the moderator compositions and, accordingly, different delay times of the appearance of fire rays at the channel exits when using a slow-burning composition 14 of the same brand. An example of a possible placement of channels on the bottom is shown in Fig. 5, and the corresponding shape of an unarmored portion in the form of a slit 15, the extreme points of which intersect the radii of the centers of the corresponding channels of the moderator, in Fig. 6. The parameters of the fuel charge arch L, protrusion of the needle L1, placement of channels on the bottom, and other parameters of the moderator are closely interrelated with the ballistic characteristics of the engine and are determined during mining. The required delay time for the operation of the moderator is set by turning the knockout charge until the slit 15 is aligned with one of the output channels 6 of the moderator.

A simpler version of the design of the moderator is shown in Fig.7. The difference in the response times of fire links is ensured through the use of channels of different lengths - from the maximum length of channel 6 located on the periphery of the bottom to the minimum length of the axial channel 16. The layout of the peripheral channels on the front bottom, the shape of the unarmored outburst gap do not differ from the above option ( see Figs. 5 and 6), and the implementation of zero delay is ensured by performing the axial zone 17 of the outer surface of the expelling charge without reservation, as shown in Fig. 8, and turning the charge over which side. To accurately set the knockout charge with the desired output channel of the moderator, the scale 18 is plotted on the reverse surface of the knockout charge, and the installation risk is shown on the visible inner surface of the housing 19. The required delay time for the moderator is set by turning the knockout charge until the corresponding scale indicator 18 is aligned with risk 19.

Another embodiment of a moderator with channels of different lengths is shown in FIG. 9. The outer surface of the front bottom is made at an angle, which causes an elliptical shape in terms of both the bottom and the flattened kick charge mating with it 20. The difference in the response times of fire connections is provided due to the different lengths of the peripheral channels - from the maximum length of channel 6, two channels 21 of average length and to the minimum length of the axial channel 16. The layout of the channels on the front bottom is shown in Fig.10, the placement of unarmored zones 10 and 22 on different sides of the expelling charge - in Fig.11 and 12. The maximum of a minimum or minimum delay time of operation of the knockout charge 20 is carried out by removing the charge, turning it 180 degrees and installing it on the bottom 5, which ensures contact of the unarmored portion 10 with the output section of the channel 6 or 16, respectively, and to implement an intermediate delay time, set on the bottom 5 of the knockout charge 8 reverse side. At the same time, the output slices of the duplicated channels 21 are in contact with the unarmored portion of the slot 22 of the knockout charge 20. On the surfaces of the knockout charge, the delay times are marked — 1, 2, and 3 sec, as shown in FIGS. 11 and 12, which facilitates proper charge installation. To compensate for the alignment of the moderator, a wad with an oblique cut along the rear surface can be used.

Below are the versions of the MPP with retarders, providing a smooth (non-discrete) setting of the delay time of the expelling charge.

On the mating with the outfeed charge 8 surface of the front bottom 5 of the small-sized engine, shown in Fig. 13, two duplicate symmetrical half-ring (with jumpers, as shown in Fig. 14) grooves 23 are filled with a low-gas slow-burning composition 14. Two channels supplying a fire pulse to the channel 6 are made in the form of longitudinal slots along the lateral surfaces of the bottom. The knockout charge 8 on the surface mating with the bottom also has two symmetrical unarmored sections 10 (see Fig. 15), the movement of the fire link and, accordingly, the moderator response time change along the gutters during charge rotation.

Work MRD. Before mounting the engine in the rocket model, by turning the expelling charge 8, the necessary delay time of the rescue system is set — from zero, when unarmored sections of the expelling charge 10 are installed opposite the channels 6 supplying a fire pulse (this position is shown in Fig. 13) to the maximum when the sections 10 move to the end of the fire paths formed by composition 14 in the grooves 23. In flight, at the end of the engine’s fuel charge, the entrances to channels 6 are opened, and the fire pulse is transmitted through unbronded These sections 10 are taken out on a charge 8 either directly when setting to zero delay, or through a section of the firing track of a given length, the burn-out time of which is determined by the burning rate of composition 14.

In Fig.16 shows an embodiment of the MAJ with an axial channel 16 supplying a fire pulse from the combustion chamber to the fuel composition 14 of the fire path of the moderator. The radial sections of the firing track at the periphery of the outer surface of the bottom pass into semi-circular arcs, as shown in Fig. 17. The bottom-mating surface of the expelling charge has unarmored portions 10 (see FIG. 15), and the outer surface 18 is provided with a time delay setting scale and a central unarmored portion 17, as shown in FIG. 18. The implementation of the required time delay of operation is provided by turning the knockout charge until the corresponding risks of the scale 18 are combined with the installation risk 19 applied to the MRP case.

At the end of engine operation, a fire pulse from the combustion chamber through the channel 16 ignites the radial and then the peripheral semicircular fire tracks. When combining the combustion front of either of the two firing tracks of the moderator with the unarmored portion 10 of the expelling charge, the latter is triggered. Zero delay is provided by turning the expelling charge to the other side, while the central unarmored charge section 17 is combined with the output section of the channel 16, and the fire pulse from the combustion chamber after opening the inlet of the channel 16 ignites the expelling engine charge.

Based on the stated principles, other solutions similar in concept and design to the solution can be implemented, in particular, without duplication of fire communication channels, which improves the accuracy of setting the response time by lengthening the fire communication track. But the operational experience of the MRP shows that it is the failure of the moderators that prevail in the general statistics of the reasons for the failure of the rescue systems of models and damage from their breakdown.

Constructive solutions of the proposed variants of the invention are focused on providing a higher degree of unification and mass production of MRPs than existing ones, using pressing technology in the manufacture of moderator charges. In particular, with a positive result, a number of retarder structures were tested, in the fire bonds of which cord charges were used from ballistic, moisture-resistant compounds formed by extrusion with subsequent gluing into the retarder channels. Extrusion technology is widely used in the manufacture of artillery gunpowders and heat-sensitive elements (cords) for fire extinguishing launch systems.

The applicant is a small business.

USED SOURCES

1. Auxiliary systems of rocket and space technology. - M.: Mir, 1970. Pages 280-340.

2. P.A. Grishuk, K.V. Morozov. Naval anti-aircraft artillery. - M.: DOSAAF, 1981. P. 102.

3. Model rocket engines. Tech. Description and instruction manual. TU 84-795-79.

4. B.C. Rozhkov. Sports models of rockets. - M .: DOSAAF, 1984. pp. 14-15 and p. 153.

5. P. Elstein. The designer of rocket models. Translation from Polish. - M.: Mir, 1978. p. 149.

Claims (9)

1. A model rocket engine containing a housing with a nozzle and a fuel charge sequentially mounted in the cavity of the housing, a front bottom with a moderator in the form of one or more fire communication channels and a blast charge, characterized in that the blast charge along the mating surface of the outputs of the fire communication channels the front bottom is movable and partially armored. 2. The engine according to claim 1, characterized in that the fuel charge is bonded or tightly in contact with the inner surface of the front bottom, the shape of which, and / or the layout of the inputs of the fire channels, and / or the shape of the fuel charge are made with the possibility of simultaneous opening the entrances of the channels of the moderator burning fuel vault. 3. The engine according to claim 2, characterized in that an elongated element with increased thermal diffusivity is installed in the fuel charge from the front bottom side, from which the inputs of the fire retardant communication channels are located at various distances. 4. The engine according to claim 2, characterized in that the front bottom of the fuel charge is made with a Central recess and with channels of a moderator of variable length. 5. The engine according to claim 2, characterized in that the front bottom on the side of the knockout charge is made obliquely to the longitudinal axis of the engine, and the knockout charge in the plan has an elliptical shape and is configured to be mounted on the bottom by turning 180 ° and / or coup on the other side. 6. The engine according to claim 1, characterized in that the moderator is made with the possibility of continuous movement along the length of the fire channel of the point of contact with the unarmored portion of the expelling charge. 7. The engine according to claim 6, characterized in that part of the fire communication channel is made in the form of a gutter on the outer surface of the front bottom. 8. The engine according to claim 7, characterized in that the trough passes through the center of the front bottom, and the discharge charge is configured to flip to the other side and has a central unarmored portion on this side. 9. The engine according to claim 1, characterized in that at least part of the mating surfaces of the front bottom and knockout charge is made of mutually attracting magnetic materials.

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