RU197089U1 - Steam, with hot water and steam generation by a laser heat source, Romanova rocket - Google Patents

Abstract

The utility model relates to missiles that use water as a working fluid and to generate superheated steam a laser heat source (LIT), and can be used as a medium-sized vehicle moving in water, the atmosphere and in airless space, for combat torpedoes, rockets, rocket and space technology for the delivery of spacecraft into space. In the steam engine of the apparatus, only water and an engine are used to generate steam and create a force driving the apparatus, comprising a hemispherical nozzle chamber. Water from the tank into the nozzle chamber is displaced by a small excess pressure of saturated steam, for the generation of which a laser heat source is installed in the tank. To generate superheated steam, a laser heat source (LIT) of increased power is also installed in the nozzle chamber. A rocket containing water and the simplest small-sized laser source of thermal energy (LIT) as a working fluid is characterized by a simple design, 100% environmental safety for humans and the environment, low volume and cost of designing a design documentation, and short production time. 4 s.p. f-ly, 2 ill.

Description

The utility model relates to missiles that use water as a working medium and to generate a superheated steam laser heat source (LIT), and can be used as a medium-sized vehicle moving in water, the atmosphere and in airless space, for combat torpedoes, rockets, rocket and space technology for the delivery of spacecraft into space.

It is known that water is the most gas-generating substance, and, therefore, the most efficient working fluid not only for steam turbines, but also as a power amplifier for all types of heat engines using the heat of high-temperature gases in rocket engines, and in pulsed single-action (powder and detonation explosives )

When one kilogram of smoke powder is burned, 300 l of gaseous products are formed, with the explosion of 1 kg of TNT, 700 l are formed, with the explosion of 1 kg of hexogen, 908 l / kg is formed, and with the evaporation of water - 1650 l.

The water placed in the ampoule inside the charge of any known explosive when it is exposed to the pressure of high-temperature explosion products explodes, increasing the pressure of the resulting gas-vapor mixture by more than 2 times and, accordingly, the specific power of the explosion.

The more gases are formed during the explosion of an explosive, and the higher their temperature, the greater part of the charge can be replaced by water, providing a higher specific power of the explosion.

Known rocket engine containing as a source of heat a nuclear reactor, as an additional working fluid, water and a supersonic nozzle to expand the working fluid is a gas-vapor mixture (RF Patent No. 2380563).

A gas-vapor rocket engine is known, which contains a nozzle-free cylindrical combustion chamber for fuel components with a nozzle head and a cylindrical evaporation chamber for evaporating water, which, passing through the cooling system of the combustion chamber and then through cylindrical channels washed by high-temperature combustion products, enters the surface of the evaporator and is used as the main working fluid in the vapor-gas mixture generated in the evaporator creating traction (RF Patent No. 187155).

A direct-flow steam power plant of an unmanned underwater vehicle is known, which generates saturated steam and contains fuel assemblies and a fission reaction, stop and power control equipment as a heat source (RF Patent No. 185128).

A direct-flow steam engine with a nuclear heat source TVEL for ships is known that uses outside water as a working fluid to generate saturated steam and create propulsive power for the propulsion vessel (Newspaper "Energy and Industry of Russia" \ No. 09 (365) May 2019).

When creating a useful model, the tasks were:

- simplify the thermodynamic cycle of the engine,

- to simplify the working fluid and the costs of not generating it in flight,

- use a more efficient, compact source of thermal energy to generate a gaseous body,

- to provide increased specific power of the engine,

- dramatically simplify the design of the engine and rockets,

- ensure its versatility when used in various types of missiles.

The tasks are solved in that:

- water is used as a substance for generating a gaseous working fluid in the apparatus engine,

- to displace water from the tank to the nozzle chamber, it contains a heat source installed in the laser, which, unlike a nuclear one, linear, which generates heat from the axis into the surrounding space, compresses thermal energy to a narrow beam.

- to reduce energy costs after launch and in flight, the water in the tank, before starting, is heated to a boiling point,

- to exclude cooling of heated water, the tank is covered with thermal insulation,

- to maintain the temperature in flight, the tank contains an electric heater, for example, a heater,

- for generating steam contains a chamber - a hemispherical nozzle,

- as a source of thermal energy generating water vapor, contains a laser heat source (LIT) installed in the nozzle.

- to increase the take-off speed and speed gain in the atmosphere, the launch is made from a barrel similar to an gun mounted vertically on the surface of the earth,

- during launches in water, (torpedo, rocket), for example from a submarine, launch from a torpedo tube or mine is made by starting the engine.

- for flight control, it contains flat rudders, with drives mounted on the nozzle exit, providing a change in steam flow and trajectories in 2 perpendicular planes or an all-angle nozzle that provides a change in the flight path in any direction.

In fig. 1 shows a schematic diagram of a rocket, where 1 is a compartment for PN, 2 is LIT for displacing water, 3 is tank insulation, 4 heating elements, 5 is an evaporator, 6 is a nozzle chamber, 7 are rudders, Fig. 2 is a schematic diagram of a rocket installed in a launch barrel, where 1 is a launch barrel, 2 are rocket supports, 3 are support rollers.

The operation of the steam engine is as follows.

When the laser installed in the tank is turned on, a small volume of saturated steam of low pressure is generated and displaces water through the channel into the chamber cavity - nozzle onto the heated surface of the evaporator heated by the heat of the laser beam, while the detonation generation of superheated steam is continuous and its expansion is continuous with continuous generation of propulsive force pushing and accelerating a rocket.

For a military rocket or launched into near-Earth orbit to launch the spacecraft, either the simplest launch pad is used - a flat platform, or a ground launching barrel, or a trunk (mine) installed in the ground.

When starting in a confined space between the launch pad and the chamber - nozzle, high pressure vapor accumulates and a short-term increase in propulsive force, and a quick rise and acceleration, and when starting from an airtight barrel in its volume, a greater accumulation of steam is provided from detachment to going beyond the barrel. with greater pressure and faster rise, and acceleration of the rocket.

Flight control can be carried out by flat rudders, with drives mounted on the nozzle exit and providing a change in steam flow and trajectories in 2 perpendicular planes or an all-angle nozzle that provides trajectory changes in any direction.

At negative air temperatures, the tank of a steam rocket covered with thermal insulation and water heated by a ground source of heat, which is turned off before launch, provide the highest starting readiness and instant launch, which is important for tactical combat missiles.

For powering LITs and rudder drives or turning the nozzle, an on-board source of electrical energy of small power is required.

A rocket containing water and the simplest small-sized laser source of thermal energy (LIT) as a working fluid is characterized by a simple design, 100% environmental safety for humans and the environment, low volume and cost of designing a design documentation, and short production time.

Claims (5)

1. A rocket containing a water tank, an engine containing a steam generation chamber, a water supply source to the steam generation chamber and a heat energy source for generating steam, characterized in that the engine as a steam generation chamber comprises a hemispherical nozzle chamber to displace water from the tank to the nozzle chamber, it contains a laser heat source installed in the tank, while a laser heat source (LIT) is installed in the nozzle chamber. 2. The rocket according to claim 1, characterized in that the water tank contains a water heater TEN. 3. A rocket according to claim 1 or 2, characterized in that the tank contains a thermal insulation coating. 4. The rocket according to any one of paragraphs. 1, 2, 3, characterized in that it contains flat rudders with drives mounted on the nozzle exit, providing a change in the steam flow in perpendicular planes. 5. The rocket according to any one of paragraphs. 1, 2, 3, characterized in that it contains an all-angle nozzle with a drive, providing a change in the flight path in any direction.

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