RU2466056C1 - Nuclear submarine and marine-version rocket engine - Google Patents

Abstract

FIELD: transport. ^ SUBSTANCE: set of invention relates to ship building, particularly, nuclear submarines. Proposed submarine comprises fast hull enveloping light hull, tanks arranged between said hulls, fast con and rescue surfacing chamber arranged inside fast hull under fast con, and, at least, one nuclear reactor connected via circulation circuit pipelines with turbogenerator electrically connected with motor. At least, one streamlined tight pod with fast-detach face plug housing liquid-propellant rocket engine. The latter comprises airframe, combustion chamber suspended to airframe and having cylinder part and nozzle, gas generator and turbo pump unit including, in its turn, turbine, oxidiser and fuel pumps, gas duct communicating turbine outlet with combustion chamber head via suspension assy. Careen nozzles are arranged in pairs on load-bearing ring fitted on light hull outer surface cross-section. Generated gas feed pipeline and fuel feed pipeline are connected via gas and fuel three-way valves to careen nozzles. Opposite end of generated gas feed pipeline is connected with gas bleed pipeline. Careen nozzles are secured on load-bearing ring by means of two inclined tie rods. ^ EFFECT: notably higher speed in attach on surface, better controllability. ^ 5 cl, 11 dwg

Description

The invention relates to shipbuilding, mainly nuclear underwater. A nuclear submarine (NPS) contains a solid 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 controlled submarine, which houses the main control center of the nuclear submarine and which is used to rescue the entire crew in the event of an atomic 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 nuclear submarine 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. In the wake 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 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 (TEGs) working with standard reactors of a nuclear power plant (NPP) NPS ( 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, 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, self-regulation and automatic duplication functions to local maintenance-free computer devices that have been successfully used for a long time, for example, in terrestrial nuclear power and manned vehicles space flights, aviation (see, for example. Minatom's industry workshop "Modern methods and means of diagnosis Nuclear Power Plant Ostomy ". Obninsk, 2001, 98 pp.), as well as experience in 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 p. , p. 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 dramatically reduce the number of submarine crews, leaving only control over the main service posts for specialists. 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 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 in space booster blocks, stages of rocket launchers and as the main engine of spacecraft, includes a combustion chamber with a regenerative cooling path, pumps for supplying components - fuel and an oxidizer with a turbine 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, IPC 7 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. September 10, 2003, 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 connected to the gas generator by means of a gas duct, which in turn contains a turbine, an oxidizer pump, a fuel pump and an additional fuel pump, a gas duct connecting the outlet from turbines with a combustion chamber, and a rocking assembly of a 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. Gimbal bearings, 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 work extremely dangerous, since when the bellows breaks, the fuel and gas-generating gas containing excess oxidizer will come into contact, which 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 improve control of the submarine on which the engine is mounted.

The solution to these problems has been 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 propellers, with a hub mounted on the 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 by an electric cable to the electric motor At the same time, according to the invention, at least one sealed streamlined nacelle with a quick-release end cap and a liquid rocket engine is attached to the sturdy case. Oxidizer and fuel tanks can be installed inside the sturdy case, connected by pipelines to each liquid rocket engine. Thermoelectric generators connected by pipelines of the circulation circuit to a nuclear reactor can be installed inside a robust housing. 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 engine containing a power frame, a combustion chamber mounted on the suspension unit to the power frame, having a head, a cylindrical part and a nozzle, a gas generator and a turbopump assembly, which in turn contains a turbine, an oxidizer pump, a fuel pump, a gas duct connecting the outlet of the turbine to the head of the combustion chamber through the suspension unit, in that according to the invention, the nozzle rolls are grouped into blocks of nozzle rolls in pairs and are mounted on the power ring, setting cross-section on the outer surface of the light body, to the roll nozzles through three-way gas and fuel valves are connected respectively gas supply gas pipelines, the other ends of which are connected first by a gas extraction pipe, and fuel pipelines, while the bank of nozzle blocks are fixed to the power ring when using two inclined rods.

The invention is illustrated in FIG. 1 ... 11, where:

figure 1 shows a diagram of a nuclear submarine,

figure 2 shows a top view

figure 3 shows a second embodiment of a fuel supply system for a nuclear submarine,

figure 4 shows the electrical circuit for the first embodiment,

figure 5 shows a diagram of the electrical equipment for the second option,

Fig.6 shows a section aa, aft of the nuclear submarine,

Fig.7 shows a diagram of the aft submarine,

on Fig shows a diagram of a liquid rocket engine,

figure 9 shows a top view,

figure 10 shows the design of the block nozzle roll,

figure 11 shows a section bB of figure 10.

The nuclear submarine submarine (Fig. 1 ... 11) contains a solid hull 1, covering it with a 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 solid pilothouse 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. At the same time, at least one sealed streamlined engine nacelle 18 with a quick-release end cap 19 and with a marine rocket engine 20. is attached to the durable casing 1 with a streamlined pylon 17 inside the strong case 1 can be tanks of oxidizer 21 and fuel 22 are installed, connected by pipelines of oxidizer 23 and fuel 24 to each liquid-propellant rocket engine of marine design 20. Inside the durable housing 1, a therm electric generators 25, connected by pipelines circulation circuit 26 with a nuclear reactor 11.

An embodiment of the nuclear submarine is possible, in which a hydrogen and oxygen catalyst 27 is mounted inside the solid housing 1, connected by a cable 28 to the batteries 15. The hydrogen and oxygen catalyst 27 is connected to the rocket engine 20 by pipelines 29 and 30.

The nuclear submarine contains decks 31, bulkheads 32, dividing the internal cavity of the sturdy hull 1 into compartments 33. Torpedoes 34 are installed in one or two compartments 33. A power belt 35 is mounted on the lightweight casing for mounting the roll nozzles.

The submarine may have containers 37 mounted on pylons 36 with a quick-release plug 38 and a quick-release fairing 39 (for example, using pyro-bolts). Inside the container 37 mounted rockets 40.

The marine liquid propellant rocket engine (Figs. 8 ... 11) comprises a power frame 41, a combustion chamber 42 configured to swing in two planes, a gas generator 43 and a turbopump unit 44, coupled to the gas generator 43 by means of a gas duct 45, comprising, in turn, a turbine 46, an oxidizer pump 47, a fuel pump 48. The turbopump unit 44 may include an additional fuel pump 49.

The outlet of the fuel pump 48 is connected by a pipe 50 to the inlet of the additional fuel pump 49 (if any). The combustion chamber 42 contains a head 51, a cylindrical part 52 and a nozzle 53. The gas generator 43 is mounted on the power frame 41 using a hinge 54, and the TNA 44 with two hinged rods 55. Between the gas duct 45 and the combustion chamber 42, more precisely, its head 51 is installed the suspension assembly 56 of the combustion chamber 42. It provides the swing of the combustion chamber 42 in two planes relative to the point "O" to control the thrust vector R.

For this, a marine-made liquid-rocket engine contains two drives 57 mounted in mutually perpendicular planes of the combustion chamber 42, made, for example, in the form of hydraulic cylinders 58, attached to the power frame 41, and having rods 59. On the combustion chamber 42, for example, on its of the cylindrical part 52, the main power ring 60 is made, to which the rods 59 of the actuators 57 are pivotally attached. The actuators 57 serve to control the nuclear submarines at pitch and yaw angles.

A possible pneumohydraulic scheme of the liquid propellant rocket engine is shown in Fig. 8 and contains a fuel pipe 61 connected at one end to the outlet of the fuel pump 48, containing a start-off valve 62 and a bellows 63, the output of this pipe being connected to the main manifold 64 of the combustion chamber 42. The output from the oxidizer pump 47 the oxidizer pipe 65 containing the start-off valve of the oxidizer 66 is connected to the gas generator 43. Also, the outlet of the additional fuel pump 49 the fuel pipe 67 containing the start-off valve of the fuel 68 is connected to a gas generator 43. At least one ignition device 69 is installed on the gas generator 43 and on the combustion chamber 42.

The engine is equipped with a control unit 70, which is connected by electrical connections 71 to the ignition devices 69 and to the shut-off valves 62, 66 and 68.

A feature of the engine (FIGS. 1 and 2) is that the TNA 44 is rigidly fixed to the power frame 41 using at least three articulated rods 55, and the combustion chamber 42 has the ability to rotate relative to the point “O”.

The suspension assembly 66 of the combustion chamber 42 of the LRE contains two parts: the stationary 72 and the movable 73. The fixed part 72 is rigidly connected to the gas duct 45, and the movable part 73 is rigidly connected to the head 51 of the combustion chamber 42, due to the fact that both parts form a spherical joint 74, made hollow, while the stationary part 72 is inside.

The roll angle control system (FIGS. 9 and 11) contains one block of roll nozzles 75, containing two roll nozzles 76. The blocks of roll nozzles 75 are mounted on the power ring 35. The power ring 35 is mounted and mounted on the lightweight housing 2 (FIG. 2 ) This power ring 35 is used to transmit torque from the nozzles of the roll 76 to the light body 2, for this each block of nozzles of the roll 75 is connected to the power ring 35 by means of brackets 77. Gas supply gas supply pipes 78 are connected to the nozzles of the roll 76, the other ends of which are connected with a gas withdrawal pipe 79 and then with a gas duct 45. In the block 75 of the nozzles of the roll 76, a three-way gas valve 80 is installed between them, which is connected by a gas extraction pipe 79 to the gas supply gas supply pipe 78, and a three-way fuel valve 81, to to which a fuel pipe 82 is connected, coming from the main manifold 64. On three-way valves 80 and 81, a common drive 83 is installed on each block. Thus, every two roll nozzles 76, three-way valves 80 and 81 and the drive 83 form one assembly: a block of nozzles of a roll 75. The nozzles of a roll 76 (FIGS. 10 and 11) are made with two walls 84 and 85 and manifolds 86 for cooling fuel passage . In each nozzle of the roll 85, fuel nozzles 87, oxidizing agent 88 and ignition device 89) are installed.

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 to rotation of the hub 8 with propellers 7. The submarine moves in an underwater position. At the same time, part of the coolant through the pipelines of the circulation circuit 26 enters thermoelectric generators 25, 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 70, an instruction is sent to the oxidizer and fuel rocket valves via electric communication channels 71 (rocket valves are not shown in FIG. 1). After filling the oxidizer pumps 47 and fuel 48, the start-off valves 62, 66 and 56 are installed, installed behind the oxidizer pump 47, after the fuel pump 48 and after the additional fuel pump 49. The oxidizing agent and fuel enter the gas generator 43, where they are ignited using the ignitor 69. Gas generator gas and fuel is supplied to the combustion chamber 42. The fuel cools the combustion chamber 42, passing through the gap, between the shells of its nozzle 53 and the cylindrical part 52 forming the regenerative cooling path (Fig. 1), enters the internal cavity amers combustion gas generator 42 for post-combustion gas coming from the gasifier 43. The ignition of these components is also carried ignition device 69 mounted on the combustion chamber 42.

After starting the turbopump unit 44, the gas-generating gas is supplied from the gas-generator 43 to the turbine 46, the TNA rotor is untwisted (not shown in FIGS. 8 ... 11), and the pressure at the pump outlets 47, 48 and 49 increases. Further, through the gas duct 45 and through the suspension unit 56, the gas-generating gas is supplied to the head 51 of the combustion chamber 42. A part of the gas-generating gas is taken through the gas sampling pipe 79 and then through the pipelines 78 and through three-way valves it enters the nozzle blocks of the bank 75.

To control the thrust vector R using the drive 57, acting on the rod 59 of the power ring 60, rotate the combustion chamber 42 relative to the point "O" at an angle of 5 ... 7 °. In this case, the direction of the thrust vector R1 deviates relative to the initial position R1 of the longitudinal axis of symmetry of the combustion chamber 42 and relative to the atomic submarine on which this engine is mounted.

To control a nuclear submarine on which a liquid-propellant rocket engine 20 is mounted, a command is sent from the control unit 70 to the common drives 83, while one roll nozzle 75 from each pair is turned on and their jet thrust generates a torque that through the power ring 76 and through four inclined thrusts 77 it is transmitted first to the nozzle 53, then to the power frame 41 and then to the solid hull 1 of the nuclear submarine.

The operation of the submarine of the second embodiment in flight mode is as follows (Fig.3 and 5). A hydrogen and oxygen catalyst 27 is included, which begins to decompose water into oxygen and hydrogen. Oxygen and hydrogen are supplied through pipelines 29 and 30 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 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 34 and 40 missiles from the surface. Given that torpedoes 34 already have an initial velocity of M = 0.5 ... 1.0, it is impossible to avoid a torpedo attack. Missiles 40 can be used not only for solving operational-tactical tasks, but also for solving strategic tasks, that is, 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 nuclear submarine 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 34 and 20 nuclear submarines goes underwater. Repeated attack is possible.

The application of the invention allowed the following.

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. To ensure reliable thrust vector control of the rocket engine and the control of the atomic submarine according to the roll angle (according to rocket terminology) through the use of two blocks of roll nozzles containing two opposite mounted roll nozzles, and their rational mounting on the engine on the annular manifold and the use of four inclined rods providing transmission of torque to the engine nozzle and further to the power frame with a minimum weight of structural elements transmitting the torque.

3. Significantly increase the reliability of the rocket control system by roll through the use of two three-way valves: gas and fuel and a common drive for them. This design prevents the inclusion of one of the nozzles of the roll, for example, due to a failure of the start-off fuel valve.

Claims (5)

1. Nuclear submarine containing a sturdy hull, covering its light hull, tanks between these hulls, a robust wheelhouse and a rescue pop-up camera installed inside a robust hull under a robust pilothouse, aft end with propellers, 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 in that at least one sealed streamlined nacelle with a quick-release end cap and a liquid rocket engine is attached to the sturdy case. 2. The nuclear submarine according to claim 1, characterized in that oxidizer and fuel tanks are installed inside the durable hull, connected by pipelines to each liquid rocket engine. 3. The nuclear submarine according to claim 1, characterized in that thermoelectric generators are installed inside the solid hull, connected by pipelines of the circulation circuit to a nuclear reactor. 4. The nuclear submarine according to claim 1, characterized in that a hydrogen and oxygen catalyst is mounted inside the sturdy hull, connected by a cable to the batteries. 5. A marine liquid propellant rocket engine comprising a power frame, a combustion chamber fixed to a suspension unit to a power frame, having a head, a cylindrical part and a nozzle, a gas generator and a turbopump unit, comprising, in turn, a turbine, an oxidizer pump, a fuel pump, a gas duct connecting the exit of the turbine to the head of the combustion chamber through the suspension unit, characterized in that the nozzle rolls are grouped into blocks of nozzle rolls in pairs and are mounted on a power ring mounted on the outer surface of the light body a whisker in its cross section, to the roll nozzles through three-way gas and fuel valves, respectively, are a gas supply gas supply pipe, the other end of which is connected first to a gas extraction pipe, and a fuel pipe, while the bank nozzle blocks are fixed to the power ring with two inclined rods.

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