RU2488517C1 - Nuclear submarine and marine-version liquid-propellant rocket engine - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: set of invention relates to ship building and may be used in construction of warships. Proposed atomic submarine comprises strong hull embraced by light hull, cisterns arranged there between, solid deckhouse and rescue float chamber arranged inside strong hull under said deckhouse, stern with propeller screw with hub fitted on propeller shaft coupled with motor and, at least one nuclear reactor communicated via circulation pipelines with turbo generator connected via electric cables with storage batteries and motor. Two streamlined combat modules with screw propellers are attached to aforesaid hull on its both sides while rocket modules is secured atop it and furnished with fast-release end plug and liquid-propellant rocker engine. Said liquid-propellant rocker engine comprises bearing frame, combustion chamber hinged thereto and including head, cylindrical section and nozzle, gas generator and a pump unit, in its turn, comprising turbine, oxidiser and propellant pumps, gas duct communicating turbine outlet with combustion chamber head via suspension assy. Gas generator and turbo pump unit are aligned with combustion chamber. Note here that gas generator and turbo pump unit are integrated into single unit.

EFFECT: higher speed in attack from surface position, better controllability.

5 cl, 10 dwg

Description

The invention relates to shipbuilding, mainly nuclear underwater. A nuclear submarine (NPS) contains a robust hull covering its light hull, tanks between these hulls and a rescue pop-up camera docked to the NPS with the possibility of separation from it. The durable case is made of separate capsules rigidly interconnected with their separation into capsules for crew accommodation and capsules with energy and other potentially dangerous installations and systems. The capsules are attached to a common power keel farm, and the rescue chamber is made in the form of a self-propelled and guided submarine, which houses the main control center of a nuclear submarine and which is used to rescue the entire crew in the event of a nuclear submarine accident. Capsules are interconnected by access hatches with hermetic closures and through a connecting block and a detachable gateway with a rescue chamber for the crew to enter it. Achieved increased safety and noiselessness of nuclear submarines, as well as increasing the ability to save the crew.

A nuclear submarine (NPS) is known, containing a solid hull, covering its light hull, tanks between these hulls and a rescue chamber docked to the NPS with the possibility of separation from it (see Pavlov A.S. Warships of Russia 1997-1998 . Handbook. Yakutsk, Lithographer, 1997 - 151 pp. Pages 17, 18, 23, 24; Bukalov V. M., Narusbaev A. A. Design of nuclear submarines. L., Shipbuilding, 1968, pp. 72-83 )

The existing dismemberment of the habitat in a robust hull through the use of "durable" intersection bulkheads of a submarine is illusory, preserving the interconnection of compartments through numerous gas and liquid pipelines passing through the bulkheads, ventilation ducts, and cable routes (power, control, communications, etc.), which often leads to the inability to localize damage and fires on board, loss of control of compartments and the spread of damage to neighboring compartments. Such situations inevitably end in disasters (see. S. Bukan. Following the traces of underwater disasters. M: Guild of Masters "Rus". - 1992).

The technical means of control, communication, life support, fire fighting and power supply have shown their failure due to poor engineering protection and the lack of a reliable local (cut-off) reserve of these funds, the rational organization of the organization in dealing with accidents, and the dangerous direct contact of energy-intensive equipment with the crew.

These results (ensuring crew safety) are achieved by the fact that in a nuclear submarine containing a robust hull, covering its light hull, tanks between these hulls and a rescue chamber docked to the nuclear submarine, the robust hull is made of separate rigidly interconnected capsules with dividing them into capsules for crew accommodation and capsules with energy and other potentially dangerous installations and systems, the capsules being attached to a common power keel farm, and the rescue chamber made in the form of a self-propelled and guided submarine, in which the main control center of the nuclear submarine is located and which is used to save the entire crew in the event of an atomic submarine accident, while the capsules are interconnected by passage hatches with hermetic closures and through the connecting block and detachable gateway for passage to the rescue chamber.

In addition, reactors are installed on a nuclear submarine having branches of the first circuit to thermoelectric generators with natural coolant circulation.

In addition, each capsule is equipped with autonomous fire extinguishing and survivability systems, and habitable capsules also have autonomous life support and communication systems.

In addition to improving the safety of the crew in capsules spaced from the capsules with energy and other hazardous installations and systems, a significant functional effect of the proposed nuclear submarine (NPS) is provided by the use of additional thermoelectric generators (TEG) working with standard reactors of a nuclear power plant (NPP) ALL ( see the description of patent RU 2151083 C1). This allows you to abandon emergency diesel generators and reduce the capacity of the battery (backup). The power of the TEG is approximately two orders of magnitude lower than that of a standard turbo-generator, and is selected from the conditions for ensuring silent submarine navigation at low speeds (3-7 knots) in an underwater flight with simultaneous economical supply of electricity to the main onboard control systems, life support, survivability and communication of the nuclear submarine, in including during repairs and / or accidents on board without limitation on the time spent in the underwater position.

The reality of the proposal is confirmed by the currently achieved reliability indicators and the capabilities of remote control of complex technical systems from a remote center with the transfer of active safety functions, self-regulation and automatic duplication to local maintenance-free computer devices that have been successfully used for a long time, for example, in terrestrial nuclear power and in manned space technology flights, aviation (see, for example, the Minatom Industry Seminar "Modern methods and means of diagnosis sticks of nuclear power plants, Obninsk, 2001, 98 pp., as well as the experience of creating and operating an automated nuclear submarine of project 705 developed by SKB-142, see Ilyin V.E. Submarines of Russia.M.: Astral, 2002 - 287 pp., pg. 62-71).

The proposed encapsulation and remote control of self-regulating submarine installations from the main control center (GPU), located in the rescue chamber, can drastically reduce the number of submarine crew, leaving specialists with only control over the main service posts. With a three-shift shift, 15 people are obtained on board.

A number of auxiliary functions, such as nutrition, cleaning, medicine, leisure activities, etc., will be provided by a shift shift. The reality of this expansion of functions is confirmed by the practice of long (more than 1 year!) Space manned flights. With a set of experience in swimming in such conditions, we can expect further integration of the functions of crew members and a decrease in their numbers.

Known American nuclear submarine "Triton" (SSRN-586), having a stern end (KO) containing a sturdy hull, propeller shafts with propellers, as well as the main thrust bearings and deadwood in the aft compartment. (Bykhovsky I.A. Nuclear ships. Leningrad, 1961, p. 121-128, 144, table 13/3 line from the top).

The disadvantage of this submarine is that its KO is not adapted to accommodate additional equipment for monitoring and protecting the aft hemisphere, both because of the lack of the necessary space for placement and the inability to provide conditions for the operation of detection equipment.

Also known is the Russian diesel submarine of project 877 (Class "Kilo" - "Varshavyanka") (see the Handbook "Warships of the USSR and Russia", Yakutsk, ed. 1995, p. 44), which has a KO with a stern compartment, through which the shaft line passes through, and the propeller is located aft in relation to the aft steering wheels - a prototype.

The disadvantage of the KO of this submarine is its structural inability to place additional acoustic and non-acoustic means of monitoring the most vulnerable aft hemisphere of space behind the submarine, underwater radio communication systems with the produced antenna, and means of active and passive protection from enemy telecommand and homing weapons.

The technical essence of the present invention is the protection of the aft end of the submarine as its most vulnerable part.

This is achieved by the fact that in KO, containing a strong and lightweight hull, propeller and shaft, a propeller motor, main thrust and thrust bearings, deadwood and stern rudders with drives, the propeller is movably mounted on a sturdy hull, for example, in the area of the aft compartment, and has a hub of large diameter that coincides along the contour with the generatrix of the light submarine housing at the installation site of the hot water. At the same time, to accommodate the GV, the lightweight submarine housing has a gap, and the screw stop is transferred to the housing structures of the durable housing directly from the GV through ring surfaces on the screw hub and the sturdy housing (located in the frame plane) provided with an antifriction coating, and lubrication and cooling of the rubbing surfaces is provided self-flow of the surrounding sea water.

The number of blades of this hot water in connection with a sharp increase in the diameter of the hub increases several times in comparison with the hot water of a traditional design, and their height is reduced based on the creation of the required stop of the hot water at a significantly reduced rotational speed to ultra-low revolutions.

The drive of the hot water is carried out, for example, by several radially mounted electric motors, on the output shaft of each of which there are gears that engage with a large diameter gear wheel, which is part of the design of the hot water supply hub.

The following is an overview of the schemes of the most modern rocket engines and an analysis is made of their adaptation to marine conditions.

Known liquid rocket engine according to the patent of the Russian Federation for invention No. 2095607, intended for use as part of space booster blocks, stages of rocket launchers and, as the main engine of space vehicles, includes a combustion chamber with a regenerative cooling path, pumps for supplying components - fuel and an oxidizer with a turbine on one shaft into which the capacitor is inserted. The condenser outlet through the refrigerant line is connected to the entrance to the combustion chamber and to the entrance to the regenerative cooling path of the combustion chamber.

The disadvantage of this engine is the lack of thrust vector control.

Known liquid rocket engine according to the patent of the Russian Federation for the invention No. 2187684. The method of operation of a liquid-propellant rocket engine is to supply fuel components to the combustion chamber of the engine, gasify one of the components in the cooling path of the combustion chamber, supply it to the turbine of the turbopump unit, and then discharge it into the nozzle head of the combustion chamber. Part of the flow rate of one of the fuel components is directed to the combustion chamber, and the remaining part is gasified and directed to turbines of turbopump units. The gaseous component spent on the turbines is mixed with the liquid component entering the engine at a pressure higher than the saturated vapor pressure of the resulting mixture.

The disadvantage of this scheme is that the thermal energy removed during cooling of the combustion chamber may not be enough to drive a turbopump engine unit of very high power.

Known LRE according to the patent of the Russian Federation for the invention No. 2190114, IPC7 F02K 9/48, publ. 09/27/2002 This LPRE includes a combustion chamber with a regenerative cooling path, a TNA turbopump unit with oxidizer and fuel pumps, the output lines of which are connected to the head of the combustion chamber, the main turbine and the drive circuit of the main turbine. The main turbine drive circuit includes a fuel pump and a regenerative cooling path of the combustion chamber connected in series with each other and connected to the main turbine inlet. The exit from the turbine TNA is connected to the input of the second stage of the fuel pump.

This engine has a significant drawback. Bypassing the fuel combustion chamber heated in the regenerative cooling path to the entrance to the second stage of the fuel pump will lead to cavitation. Most LREs use fuel components such that the oxidizer consumption is almost always greater than the fuel consumption. Therefore, for powerful rocket engines with great thrust and high pressure in the combustion chamber, this scheme is not acceptable, because fuel consumption will not be enough to cool the combustion chamber and drive the main turbine. In addition, the LRE launch system, the ignition system of the fuel components and the LRE shutdown system and its cleaning of fuel residues in the regenerative cooling path of the combustion chamber have not been developed.

Known liquid rocket engine according to the patent of the Russian Federation for the invention No. 2232915, publ. 09/10/2003 g, which contains a turbo pump unit, a gas generator, a launch system, means for igniting fuel components and fuel lines. The output of the oxidizer pump is connected to the inlet of the gas generator. The output of the first stage of the fuel pump is connected to the channels of regenerative cooling of the chamber and to the mixing head. The output of the second stage of the fuel pump is connected to an electric flow regulator.

The disadvantage is that the engine does not have a thrust vector control system and roll control.

Known liquid rocket engine and TNA according to the patent of the Russian Federation for the invention №2161263, prototype rocket engine.

This engine contains a power frame, a combustion chamber made with the possibility of swinging in two planes, a gas generator and a turbopump unit, coupled to the gas generator by means of a gas duct, containing, in turn, a turbine, an oxidizer pump, a fuel pump and an additional fuel pump, a gas duct connecting the outlet from a turbine with a combustion chamber, and a rocking unit of the rocket engine combustion chamber installed between the gas duct and the combustion chamber, more precisely, the head of the combustion chamber. This unit is made in the form of a bellows and a universal joint, which together provide the swing of the combustion chamber and sealing the supply of gas-generating gas, which has high pressure and temperature. In addition, a bellows cooling system is provided, since its performance under such extreme conditions is in doubt.

The turbopump assembly comprises a turbine with an impeller and oxidizer pumps, fuel pumps and an additional fuel pump installed coaxially with the pump.

The disadvantages of this engine and the suspension unit of the combustion chamber included in its composition: low unreliability of the suspension unit of the combustion chamber of the rocket engine due to the presence of a large number of parts, low strength of thin-walled bellows operating at high pressure and temperature. The bearings of the gimbal, transmitting the thrust of the combustion chamber, reaching 200 ... 1000 tf, also work at high temperatures (from 500 to 800 ° C), while the grease burns out, the bearings are destroyed, the thrust vector control is difficult.

The use for cooling this unit of fuel, intended for feeding into the combustion chamber, not only complicates the design of this unit and the engine as a whole, but also makes its operation extremely dangerous, since when the bellows breaks, the fuel and gas-generating gas containing excess oxidizer will come into contact that will inevitably lead to a fire in the engine compartment of the rocket and the cessation of fuel supply to the combustion chamber.

The thrust vector control of the rocket engine is unreliable, and there is no control over the roll angles (according to rocket terminology).

The tasks of creating a group of inventions are a significant increase in the speed of movement of the submarine in the attack mode from the surface and the improvement of the submarine on which the engine is mounted.

The solution of these problems was achieved in an atomic submarine containing a robust hull, covering its light hull, tanks between these hulls, a robust wheelhouse and a rescue pop-up camera installed inside the robust hull under a robust pilothouse, aft tip with a propeller, with a hub mounted on a propeller a shaft connected to an electric motor and at least one nuclear reactor connected by pipelines of the circulation circuit to a turbogenerator, which is connected to the batteries by an electric cable and with an electric motor, in accordance with the invention, two streamlined combat modules with propellers are attached to the robust casing on both sides, and a rocket module with a quick-release end cap and a marine rocket engine is attached on top. Inside the rocket module, oxidizer and fuel tanks can be installed, connected by pipelines to a marine rocket engine. Combat modules can be divided into compartments in which rockets, torpedoes, nuclear reactors and propeller drives are installed. A hydrogen and oxygen catalyst can be installed inside the rugged case, connected by a cable to the batteries.

The solution of these problems was achieved in a marine liquid-propellant rocket engine containing a power frame, a combustion chamber fixed to the suspension unit to the power frame, having a head, a cylindrical part and a nozzle, a gas generator and a turbopump, which in turn contains a turbine, oxidizer pumps, and fuel, a gas duct connecting the outlet of the turbine to the head of the combustion chamber through the suspension unit, characterized in that the gas generator and the turbopump are installed coaxially with the combustion chamber, while the gas generator and the tour the pumping unit is designed as a single unit.

The invention is illustrated in figure 1 ... 10, where:

- figure 1 shows a diagram of a nuclear submarine, a section along the horizontal plane,

- figure 2 shows a top view of a nuclear submarine in section,

- figure 3 shows ALL, a section along a vertical plane,

- figure 4 shows a diagram of a rocket block in section,

- figure 4 shows a diagram of the electrical equipment for the first embodiment,

- figure 5 shows the electrical circuit for the second option,

- figure 6 shows a section aa aft submarine,

- figure 7 shows a variant of the power plant with a generator of hydrogen and oxygen,

- Fig.8 shows a diagram of the aft submarine,

- figure 9 shows a diagram of a liquid rocket engine,

- figure 10 shows a top view,

The nuclear submarine submarine (figure 1 ... 10) contains a solid hull 1, covering its light hull 2, tanks 3 between these hulls 1 and 2, a robust wheelhouse 4 and a rescue pop-up camera 5, mounted inside a robust hull 1 under a robust wheelhouse 4, the aft end 6 with a propeller 7 with a hub 8 mounted on a propeller shaft 9 connected to an electric motor 10 and at least one nuclear reactor 11 connected by pipelines of the circulation circuit 12 to a turbogenerator 13, which is connected by an electric cable 14 to the batteries 15, to which are connected by an electric cable 16 to the electric motor 10. In this case, a streamlined pylon 17, a streamlined rocket module 18 with a quick-release end cap 19 and with a marine rocket engine 20. is attached to the solid housing 1, and oxidizer tanks 21 and 22 are installed inside the rocket module 18. connected by an oxidizer pipe 23 with a rocket valve 24 and a fuel pipe 25 with a fuel rocket valve 26 with a marine rocket engine 20.

Inside the durable housing 1, thermoelectric generators 27 can be installed, connected by pipelines of the circulation circuit 28 (Fig. 1) with a nuclear reactor 11.

An embodiment of the nuclear submarine is possible, in which a hydrogen and oxygen catalyst 29 (Fig. 7) is installed inside the solid housing 1, connected by a cable 30 to the batteries 15. The hydrogen and oxygen catalyst 29 by pipelines 31 and 32 can be connected to a marine rocket engine 20.

The submarine contains decks 33, bulkheads 34, dividing the internal cavity of the solid hull 1 into compartments 35.

The nuclear submarines are equipped with combat modules 36 (FIG. 2) containing a streamlined body 37. The attachment of the combat modules to the robust housing 1 is made using attachment units 38 made with the possibility of quick connector (for example, using pyro-bolts).

Combat models 36 each contain a torpedo compartment 39 with torpedoes 40, a missile compartment 41 with missiles 42, an energy compartment 43 with a nuclear reactor 44. In addition, each combat module 36 is equipped with a hydraulic screw 45 and an electric motor 46.

The marine liquid-propellant rocket engine 20 (FIGS. 8 ... 10) comprises a power frame 47, a combustion chamber 48 that can swing in two planes, a gas generator 49 and a turbopump unit 50, coupled to the gas generator 49 by means of a gas duct 51 or directly containing, in in turn, a turbine 52, an oxidizer pump 53, a fuel pump 54. The turbopump assembly 50 may include an additional fuel pump 55.

The output of the fuel pump 54 is connected by a pipe 56 to the inlet of the additional fuel pump 55 (if any). The combustion chamber 48 contains a head 57, a cylindrical part 58 and a nozzle 59. The gas generator 49 and the TNA 50 are fixed using a hinge 60 and two articulated rods 61. Between the gas duct 51 and the combustion chamber 48, more precisely, its head 57 has a suspension assembly 62 of the combustion chamber 48. It provides the swing of the combustion chamber 48 in two planes relative to the point "O", to control the thrust vector R.

For this, a marine-made liquid-rocket engine contains two actuators 63 mounted in mutually perpendicular planes of the combustion chamber 48, made, for example, in the form of hydraulic cylinders 64, attached by rods 65 to the power frame 47, and having rods 65. On the combustion chamber 48, for example, on its cylindrical part 58, the main power ring 66 is made, to which the rods 65 of the actuators 63 are pivotally attached. The actuators 63 serve to control the nuclear submarines at pitch and yaw angles.

A possible pneumohydraulic circuit of the liquid propellant rocket engine is shown in Fig. 8 and contains a fuel pipe 67 connected at one end to the outlet of the fuel pump 54, containing a start-off valve 68 and a bellows 69, the output of this pipe is connected to the main manifold 70 of the combustion chamber 48. The output from the oxidizer pump 53 the oxidizer pipe 71 containing the start-off valve of the oxidizer 72 is connected to the gas generator 49. Also, the output of the additional fuel pump 55 by the fuel pipe 73 containing the flow controller 74 and the start-off valve g ryuchego 75 is connected to the gas generator 49. In gasifier 49 and combustion chamber 48 are installed, at least one ignition device 76.

A feature of the engine (Fig. 10) is that the TNA 50 and the combustion chamber 48 in the upper part are attached to the frames 77 each with at least three hinges 78 and articulated rods 79, and the combustion chamber 48 can rotate relative to the suspension unit 62 .

The suspension assembly 62 of the combustion chamber 48 of the rocket engine 20 contains two parts: the stationary 80 and the movable 81. The fixed part 80 is rigidly connected to the gas duct 51, and the movable part 81 is rigidly connected to the head 57 of the combustion chamber 48, due to the fact that both parts form a spherical articulated the connection 82 made hollow inside, while the stationary part 80 is fixed inside the rocket module 18 using the hinges of the rods 78 and the hinged rods 79.

The missile module 18 comprises a pressurization balloon 83, an oxidizer pressurization pipe 84, an oxidizer pressurization valve 85, a fuel pressurization pipe 86, and a fuel pressurization valve 87.

The nuclear submarine is equipped with an on-board computer 88, which is connected by electrical connections 89 to the ignition devices 76 and to the shut-off valves 68, 72 and 75.

Roll angle control system not provided

The submarine of the first embodiment works as follows (Figs. 1, 2, and 4). The nuclear reactor 11 is started, and the coolant is circulated through the circulation pipes 12 to the turbogenerator 13. The turbogenerator 13 generates an electric current, which is supplied via the electric cable 14 to the battery 15, from which the electric cable 16 is supplied to the electric motor 10. The electric motor 10 leads through the propeller shaft 9 in rotation, the hub 8 with propellers 7. The submarine moves in an underwater position. At the same time, part of the coolant through circulation pipelines 25 enters thermoelectric generators 27, which additionally generate electric energy, for example, in the “flight” mode of a nuclear submarine or in case of a failure of a turbogenerator 13.

To significantly accelerate the movement of the submarine in attack mode, it is transferred to the surface position. Then launch the LRE of marine use 20. LRE of the marine use 20 is launched as follows.

In the initial position, all engine valves are closed. When starting a liquid propellant liquid propellant rocket engine from a control unit 88, an electric communication channel 89 sends a command to the boost valves 85 and 87 and to the oxidizer and fuel rocket valves 24 and 26. After filling the oxidizer pumps 53 and fuel 54, the shut-off valves 68, 72 and 75 are opened. installed behind the oxidizer pump 53, after the fuel pump 54 and after the additional fuel pump 55. The oxidizer and fuel enter the gas generator 49, where they are ignited using the igniter 76. The gas generator gas and fuel are fed into the combustion chamber 48. The fuel cools the chambers at the combustion 48, passing through the gap, between the shells of its nozzle 59 and the cylindrical part 58 forming the regenerative cooling path (Fig. 1), it enters the internal cavity of the combustion chamber 48 for afterburning the gas-generating gas coming from the gas-generator 49. Ignition of these components is also carried out the ignition device 76 mounted on the combustion chamber 48.

After the start of the turbopump unit 50, the gas-generating gas is supplied from the gas-generator 49 to the turbine 52, the TNA rotor is untwisted (not shown in FIGS. 8 ... 10), the pressure at the pump outlets 53, 54 and 55 increases. Further along the gas duct 51 and through the suspension assembly 62, the gas-generating gas is supplied to the head 57 of the combustion chamber 48.

To control the thrust vector R by means of the actuator 63, acting on the power ring 66 by the rod 65, the combustion chamber 48 is rotated relative to the point “O” by an angle of 5 ... 7 °. The direction of the thrust vector R1 deviates relative to the initial position R1 of the longitudinal axis of symmetry of the combustion chamber 48 and relative to the nuclear submarine on which this engine is mounted.

The operation of the submarine of the second embodiment in flight mode is as follows (Fig.3 and 5). A hydrogen and oxygen catalyst 29 is included, which begins to decompose water into oxygen and hydrogen. Oxygen and hydrogen are supplied through pipelines 31 and 32 to the marine rocket engine 20. The advantage of this option is the absence of oxidizer and fuel tanks and the need to constantly transport a large supply of these rocket fuel components underwater.

The submarine attacks targets in the surface position in the movement of the submarine in the "rocket" mode, with a speed of M = 0.5 ... 1.0, which makes it invulnerable and allows the launch of torpedoes 40 and rockets 42 from the surface position. Given that torpedoes 40 already have an initial velocity of M = 0.5 ... 1.0, it is impossible to avoid a torpedo attack. Missiles 42 can be used not only for solving operational-tactical tasks, but also for solving strategic tasks, i.e. firing from neutral waters at a distance of 3000 ... 5000 km. At the same time, the nuclear submarine remains invulnerable and if its location is detected, then due to the high speed of the ALL in the surface position and the short period of time in the surface position from 10 to 60 seconds, it cannot be hit. After the release of torpedoes 40 and 42 nuclear submarines, it goes into submerged position. Repeated attack is possible.

The application of the invention allowed:

1. To provide a short-term significant increase in the speed of the nuclear submarine in the above-water position and even its flight at a speed of M = 0.5 ... 1.0 in the attack mode to launch torpedoes and missiles in the above-water position to ensure reliable launch and accuracy when the submarine is invulnerable to weapons enemy defense.

2. Provide reliable thrust vector control for rocket engine and nuclear submarine control.

3. Ensure crew safety.

4. Use nuclear submarines for peaceful purposes.

Claims (5)

1. Nuclear submarine containing a sturdy hull, covering its light hull, tanks between these hulls, a robust pilothouse and a rescue pop-up camera mounted inside a robust hull under a robust pilothouse, aft tip with a propeller, with a hub mounted on a propeller shaft connected with an electric motor, and at least one nuclear reactor connected by pipelines of the circulation circuit to a turbogenerator, which is connected by electrical cable to the batteries and to the electric motor, characterized the fact that a robust housing on both sides of the module attached to two combat streamlined with propellers, and the top is attached to the rocket module bystrosbrasyvaemoy of the end cap and liquid-propellant rocket engine marine applications. 2. The nuclear submarine according to claim 1, characterized in that oxidizer and fuel tanks are installed inside the rocket module, connected by pipelines to a marine rocket engine. 3. The nuclear submarine according to claim 1 or 2, characterized in that the combat modules are divided into compartments in which rockets, torpedoes, nuclear reactors and propeller drives are installed. 4. The nuclear submarine according to claim 1 or 2, characterized in that a hydrogen and oxygen catalyst is installed inside the sturdy hull, connected by a cable to the batteries. 5. A marine-style liquid propellant rocket engine containing a power frame, a combustion chamber mounted on a suspension unit to a power frame, having a head, a cylindrical part and a nozzle, a gas generator and a turbopump, containing, in turn, a turbine, oxidizer and fuel pumps, a gas duct connecting the outlet of the turbine with the head of the combustion chamber through a suspension unit, characterized in that the gas generator and the turbopump are installed coaxially with the combustion chamber, while the gas generator and the turbopump are made in the form single unit.

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