RU163590U1 - THERMOSTATING SYSTEM OF LIQUID MISSION FUEL COMPONENTS - Google Patents

Abstract

The temperature control system for liquid propellant components, containing thermally insulated containers for liquid propellant components and for a coolant with instrumentation installed on them, interconnected by pipelines with shut-off and safety valves and having drain pipelines, a pump, a bypass line, a fan, an air heat exchanger , a liquid nitrogen gasifier connected through a flexible conduit and a pressure line for supplying nitrogen to a coolant tank, In this case, a liquid nitrogen atomizer and tubular electric heaters are located at the bottom of the coolant tank, characterized in that a glass is concentrically installed in the heat-insulated tank for the coolant, outside of which there is a coil connected to a thermally insulated tank for liquid rocket fuel components.

Description

The utility model relates to devices of thermostatic control systems for liquid rocket fuel components and can be used in space rocket technology, aviation, etc.

A known temperature control system for the liquid component of rocket fuel (see patent Ru 2291088, C1, IPC B64G 1/50, F25B 21/02, published January 10, 2007) [1], in which the temperature of the product is controlled by heat exchange processes with a coolant temperature-supported thermoelectric batteries, radiator-cooler and supercharger.

The disadvantages of such a system are:

- high energy costs due to the use of thermoelectric elements;

- the need to divert side heat dissipation of thermoelectric elements;

- limiting the heat exchange area of the heat exchanger.

There is a known temperature control system with a built-in heat exchanger (see the book by V. Khlybov. Fundamentals of the theory and development of refueling equipment and temperature control systems. Textbook. M .: RVSN, 1994. 276 p. Fig. 5.1) [2], in which it is heated or cold the intermediate coolant is pumped by a centrifugal pump in a closed circuit from the refrigeration center to the heat exchanger and vice versa until the temperature of the liquid in the tank reaches a predetermined value.

The disadvantages of such a system are:

- the need for a refrigeration center;

- limiting the heat exchange area of the heat exchanger;

- the complexity of carrying out scheduled and unscheduled repair work due to the harmfulness and aggressiveness of the components of liquid rocket fuel.

There is a known temperature control system with an external heat exchanger (see the book by V. Khlybov. Fundamentals of the theory and development of refueling equipment and temperature control systems. Textbook. M.: Strategic Rocket Forces, 1994. 276 p. Fig. 5.3) [2], in which one or two heat exchangers connected in parallel (depending on the required heat and cooling capacity) are alternately connected to each tank, and the product is fed by a centrifugal pump to a recuperative heat exchanger, in which heat is exchanged.

The disadvantages of such a system are:

- the need for a refrigeration center;

- the need for a centrifugal pump, pumping the prepared coolant through a recuperative heat exchanger.

Known stationary temperature control system with an external heat exchanger (shell-and-tube) and an intermediate heat carrier (see the book HF VF Fundamentals of the theory and development of refueling equipment and temperature control systems. Textbook. M .: RVSN, 1994. 276 p. Fig. 5.4) [2 ], in which the temperature preparation of the components of liquid rocket fuel is carried out through recuperative heat transfer with a coolant. If it is necessary to carry out the operation of heating the components of liquid rocket fuel, water is heated in the boiler room, then through the heat exchanger built into the tank with an intermediate heat medium, the intermediate heat medium is heated. If it is necessary to carry out the cooling of components of liquid rocket fuel, the intermediate coolant is cooled by circulating the latter through working vapor compression refrigeration machines.

The disadvantages of such a system are:

- the need for a boiler room;

- the need for vapor compression refrigeration machines;

- the need for four pumps;

- the inability to use this system as a mobile due to the large required number of components and the corresponding mass-dimensional characteristics.

There is a known system for cooling a product with liquid nitrogen (see the book by V. Khlybov. Fundamentals of the theory and development of refueling equipment and temperature control systems. Textbook. M.: Strategic Rocket Forces, 1994. 276 p. Fig. 5.9) [2], in which the components are cooled liquid rocket fuel through a regenerative heat exchanger made in the form of a coil. When the pump is turned on, the components of liquid rocket fuel are circulated through pipelines and a coil located in a container with liquid nitrogen, due to heat exchange in which the components of liquid rocket fuel are cooled to the required temperature.

The disadvantages of such a system are:

- the inability to use this system to heat the components of liquid rocket fuel;

- limiting the types of components of liquid rocket fuel due to the low boiling point of liquid nitrogen;

- icing of liquid rocket fuel components on the inner surface of the heat exchanger;

- possible penetration of crystals of the components of liquid rocket fuel into the pump, into filters of refueling systems, into the product, etc.

A known liquid cooling system (see patent Ru 2323133, C1, IPC B64D 33/10, published April 27, 2008) [3], in which the product is cooled by regenerative heat exchange with air having a temperature lower than the liquid to be cooled.

The disadvantages of such a system are:

- the inability to use this system to heat the liquid;

- lack of ability to control air temperature and, as a consequence, temperature pressure;

- limiting the heat exchange area of the heat exchanger;

- the impossibility of replacing the cooling medium.

A known temperature control system for liquids (see patent Ru 2216655, C1, IPC F15B 21/04, published November 20, 2003) [4], in which the product is temperature-controlled by means of a temperature sensor, heat exchanger, battery, timer and timer.

The disadvantages of such a system are:

- the inability to use this system for cooling the components of liquid rocket fuel;

- the ability to use this temperature control system only for small doses of the product in connection with the features of the selected method of temperature control;

- the long duration of the operation of temperature control of the product.

The known system of temperature control of the oxidizing agent for the Rokot launch vehicle at the launch site of the Plesetsk launch site (see the article Komlev D.E., Soloviev V.I. Naphthyl cooling by cryogenic sparging // Technology news: collection M .: KBTM, 2004. p. 137-141. Fig. 2) [5]. The system contains thermally insulated containers for liquid propellant components and for the coolant with instrumentation installed on them. Thermally insulated containers are interconnected by pipelines with shut-off and safety valves and have drain pipelines. The system also includes refueling system heat exchangers, a pump, a fan, an air heat exchanger, a liquid nitrogen gasifier connected through a flexible pipe and a pressure nitrogen supply line with a heat-insulated coolant tank. At the same time, a liquid nitrogen atomizer and tubular electric heaters are located below in a thermally insulated container for the coolant.

An analysis of patents and scientific and technical literature [1-5] showed that according to the technical nature and the achieved result, the oxidizer thermostat control system for the Rokot launch vehicle at the launch site of the Plesetsk launch site is the closest to the proposed utility model and is selected as a prototype.

The disadvantages of the prototype include the following:

- the presence of heat exchangers in the fueling system;

- the presence of a pumping unit in the temperature control system;

- the impossibility of simultaneously cooling the coolant and the component of liquid rocket fuel;

- the presence of excess coolant;

- the possibility of cavitation mode of the pumping unit of the temperature control system;

- the need for an expensive control system due to the presence of a stepped mode of operation;

- large values of the mass-dimensional characteristics of the temperature control system.

The technical results of the utility model are:

- improving the reliability and efficiency of the temperature control system by eliminating heat exchangers and the pumping system of the fueling system;

- simultaneous cooling of the coolant and the component of liquid rocket fuel by installing the coil in a thermally insulated container for the coolant;

- elimination of the excess amount of coolant due to the placement of the glass in a thermally insulated container for the coolant;

- the exclusion of the cavitation mode of operation of the pumping unit of the thermostating system due to the installation of the coil in a thermally insulated container for the coolant;

- cheaper control system by eliminating the stepped mode of operation;

- achieving lower values of the mass-dimensional characteristics of the temperature control system due to the elimination of structural elements (heat exchangers and the pumping system of the refueling system), as well as by installing the glass in a heat-insulated container for the coolant.

These technical results are achieved due to the fact that the temperature control system of liquid rocket fuel components contains thermally insulated containers for liquid rocket fuel components and for the coolant with instrumentation installed on them. Thermally insulated containers are interconnected by pipelines with shut-off and safety valves and have drain pipelines. The system also includes a pump, a bypass line, a fan, an air heat exchanger, a liquid nitrogen gasifier connected through a flexible pipe and a pressure line for nitrogen supply with a heat-insulated tank for the coolant. At the same time, a liquid nitrogen atomizer and tubular electric heaters are located below in a thermally insulated container for the coolant. In addition, in a thermally insulated container for the coolant, a cup is concentrically installed, outside of which there is a coil connected to a thermally insulated container for components of liquid rocket fuel.

The essence of the proposed utility model is illustrated in the drawing.

The temperature control system of liquid propellant components contains thermally insulated containers for liquid propellant components 1 and for the coolant 2 with instrumentation 3 installed on them. Thermally insulated containers are interconnected by pipelines 4 with shut-off valves 5 and have drain pipelines 6. The system includes also a pump 7, a bypass line 8, a fan 9, an air heat exchanger 10, a liquid nitrogen gasifier 11 connected through a flexible pipe 12 and pressure a nitrogen supply line 13 with a thermally insulated container for the coolant 2. In this case, a liquid nitrogen atomizer 14 and tubular electric heaters 15 are located at the bottom of the thermally insulated container for the coolant 15. In addition, a glass 16 is concentrically installed in the thermally insulated container 2 for the coolant, the coil 17 is located outside connected to a thermally insulated tank for liquid propellant components 1.

The temperature control system of the components of liquid rocket fuel operates as follows.

Before the operation of temperature control of liquid rocket fuel, a thermally insulated tank for components of liquid rocket fuel 1 and a thermally insulated tank for coolant 2 are refilled.

To carry out the operation of cooling liquid rocket fuel in a liquid nitrogen gasifier 11, excessive pressure is created by supplying nitrogen gas to the gas space of the liquid nitrogen gasifier 11. Then, liquid nitrogen is extruded from the liquid nitrogen gasifier 11 into the pressure head nitrogen supply line 13 through a flexible pipe 12 with cooling them, which undergoes a phase transition and enters the environment using shut-off and safety valves 5. Pressure control in the flexible pipe 12 and pressure shutoff line 13 is carried out by instrumentation 3. To prevent possible damage to the flexible pipe 12 and the pressure line of the nitrogen supply 13 due to exceeding the permissible pressure caused by boiling of nitrogen, shut-off valves 5 are provided. Upon completion of cooling of the flexible pipe 12 and pressure the nitrogen supply line 13 liquid nitrogen enters the heat-insulated container for the coolant 2, in which the glass 16 is installed, through the liquid atomizer nitrogen 14. This leads to boiling of nitrogen and cooling of the coolant, the temperature of which is fixed by instrumentation 3. Boiled nitrogen enters the environment using shut-off valves 5. When the pump 7 is turned on, liquid rocket fuel is circulated through pipelines 4 and the coil 17 located in a thermally insulated container for the coolant 2, due to heat exchange in which the liquid rocket fuel is cooled to the required temperature, fixed control eritelnymi devices 3.

To conduct the operation of heating liquid rocket fuel, tubular electric heaters 15 are turned on, which heat the coolant in a thermally insulated tank for coolant 2. When the pump 7 is turned on, liquid rocket fuel is circulated through pipelines 4 and a coil 17 located in a thermally insulated tank for coolant 2, due to heat exchange in which is used to heat liquid propellant to the required temperature, recorded by instrumentation 3.

The throttle flow rate of liquid rocket fuel is carried out using the bypass line 8, as well as shut-off and safety valves 5. The flow rate of liquid rocket fuel is controlled by instrumentation 3. Upon completion of the thermostating operation of liquid rocket fuel, it is dispensed to the consumer, as well as the coolant is drained through the appropriate drain pipes 6.

By means of an air heat exchanger 10 and a fan 9, the ambient temperature of the system of temperature control of the components of liquid rocket fuel is maintained.

A comparative analysis of the proposed utility model with known thermostatic control systems showed that the proposed utility model surpasses all known thermostatic systems of liquid propellant components in terms of technical level and achieved results.

The proposed utility model meets the criteria of patentability "substantial novelty", "inventive step" and "industrial applicability".

The proposed utility model can be used as part of the launch and technical complexes of rockets and spacecraft.

INFORMATION SOURCES

1. Patent Ru 2291088, C1, IPC B64G 1/50, F25B 21/02, published January 10, 2007 - analogue.

2. Khlybov V.F. Fundamentals of the theory and development of refueling equipment and temperature control systems. Textbook. M.: Strategic Missile Forces, 1994.276 s. - analogues.

3. Patent Ru 2323133, C1, IPC B64D 33/10, published April 27, 2008 - analogue.

4. Patent Ru 2216655, C1, IPC F15B 21/04, published November 20, 2003 - analogue.

5. Komlev D.E., Soloviev V.I. Naphthyl cooling by cryogenic sparging // Technology News: Sat. M .: KBTM, 2004.S. 137-141. - prototype.

Claims (1)

The temperature control system for liquid propellant components, containing thermally insulated containers for liquid propellant components and for a coolant with instrumentation installed on them, interconnected by pipelines with shut-off and safety valves and having drain pipelines, a pump, a bypass line, a fan, an air heat exchanger , a liquid nitrogen gasifier connected through a flexible conduit and a pressure line for supplying nitrogen to a coolant tank, In this case, a liquid nitrogen atomizer and tubular electric heaters are located at the bottom of the coolant tank, characterized in that a glass is concentrically installed in the heat-insulated tank for the coolant, outside of which there is a coil connected to a thermally insulated tank for liquid rocket fuel components.

Images