RU82677U1 - FUEL FILLER FOR FILLING AIRCRAFT WITH A COMPONENT OF LIQUID ROCKET FUEL (OPTIONS) - Google Patents

Abstract

1. A gas tanker for refueling aircraft with a liquid rocket fuel component, comprising a tractor unit connected to a semi-trailer and a tank, a pneumatic and hydraulic system including a pump unit, shutoff valves, instrumentation, dispensing fittings with permanently attached hoses and a control system, characterized in that it made in the form of a transport modular container mounted on a container semi-trailer, separated by a sealed partition into two compartments - a technological compartment, in which refueling equipment is located, and a control compartment with electrical equipment and a control system for refueling technological operations associated with both local and remote control panels, the technological compartment is equipped with forced mechanical ventilation system with a filter and ventilation system, and the control compartment is portable air conditioning, a fire warning system is located in both compartments, which gives a signal about a fire to local and remote control panels, The tank installed in the technological compartment is provided with thermal insulation and three supports located along its length, of which the central one is fixed, and the two extreme ones with the possibility of sliding relative to the longitudinal axis of the container, and the constantly connected hoses are located in trays made along the walls of the container, and the receiving hose is equipped with an additional hose of a smaller diameter, one end of which is connected to the pneumatic system, and the other to the receiving hose on the dispensing fitting, while

Description

The utility model relates to devices for refueling aircraft with a component of liquid rocket fuel and can be used in rocket and space technology, aviation, hypersonic aviation, reusable space transport systems with a large carrying capacity, etc. [1, 2, 3].

A well-known automobile semi-trailer for transporting a component of liquid rocket fuel, for example, liquid hydrogen, containing a thermally insulated tank, a compartment for accommodating instrumentation,

safety device, unloading and other necessary equipment (see book: V.N. Zrelov, E.P.Seregin. Liquid rocket fuels. M: Chemistry, 1975, p. 62-65, Fig. 41) [4 ].

The disadvantages of this technical solution include the lack of automation and, consequently, the low reliability of the work, as well as the limited ability associated only with the transportation of a component of liquid rocket fuel.

A known fuel tanker comprising a tractor connected to a tank semi-trailer connected to a filling line equipped with a filling valve connected to a filling indicator (see patent RU No. 2206478, publication date 06/20/2003, IPC 7: B64F 1/28, B60S 5/02, V65D 88/12, V67D 5/04, V60P 3/24) [5].

The disadvantages of the known tanker include low reliability and limited application, since it is intended only for filling the tank, therefore, without significant modifications, it cannot be used for refueling, for example, launch vehicles and spacecraft at launch complexes.

It should be noted that when searching for information, the terms “tanker”, “tanker” and “tanker” are often used. Each of these terms has the same meaning. Therefore, the more correct, modern and concise is the use of the term “gas station”.

A known tanker for refueling aircraft with a liquid propellant component containing a tractor connected to a semitrailer and a tank, a pneumatic system including a pumping unit, shutoff valves, instrumentation, dispensing fittings with permanently attached hoses and a control system (see patent RU No. 22862628 , C2, IPC 7: B64F 1/00, B67D 5/04, B60S 5/02, B60P 3/22, published October 27, 2006) [6].

The analysis of patents and scientific and technical literature [1 ... 14, etc.] showed that, according to the technical nature and the achieved result, a gas tanker according to a patent

Ru 2286289, C2 is the closest to the proposed utility model and we have chosen as a prototype.

The disadvantages of the prototype include the following:

- the lack of thermal insulation on the surface of the tanker tank in the conditions of French Guiana (almost at the equator - 5 ° north latitude) with a tropical climate [1, p. 47 ... 51] does not allow to strictly maintain the temperature regime of filling the launch vehicle within the required limits, which reduces the reliability and efficiency of not only the tanker, but also the launch vehicle, which is unacceptable;

- the inability to fill the tanker tank with a component (for example, kerosene) from its delivery vehicle - the tank container;

- the impossibility of cooling a fuel component, for example, kerosene, in a tanker tanker.

The technical results of the utility model are:

1) improving the reliability and efficiency of the refueling tanker during the aircraft refueling process with a liquid rocket fuel component by automating the refueling process, achieving stable and cavitation-free pump operation in the refueling mode of the launch vehicle at a low flow rate;

2) ensuring the filling of the insulated tanker tank with a liquid propellant component with a predetermined temperature from a delivery vehicle — a tank container;

3) ensuring the cooling of a component of liquid rocket fuel, for example, kerosene, to the required temperature in a thermally insulated tank of a tanker in order to increase its density before refueling the aircraft.

These technical results are achieved due to the fact that a gas station for refueling aircraft with a liquid propellant component containing a tractor connected to a semitrailer and a tank, a pneumatic and hydraulic system including a pumping unit, shutoff valves, and control

devices, dispensing fittings with permanently docked hoses and a control system, according to a utility model, is made in the form of a transport modular container mounted on a container semi-trailer, separated by a sealed partition into two compartments - the technological compartment in which the filling equipment is located, and the control compartment with installed electrical equipment and a process control system for refueling related to both local and remote control panels, technology The compartment is equipped with a mechanical ventilation system with a filter and ventilation system, and the control compartment is equipped with a portable air conditioner, a fire warning system is located in both compartments, which gives a signal about a fire to the local and remote control panels, the tank installed in the technological compartment is insulated and located along it the length of the three supports, of which the central is made stationary, and the two extreme - with the possibility of sliding relative to the longitudinal axis of the container, and permanently docked hoses are located in trays made along the walls of the container, and the pick-up hose is equipped with an additional hose of a smaller diameter, one end of which is connected to the pneumatic system, and the other with a pick-up hose on the dispensing fitting, while the gas station is equipped with parallel mounted pressure line after the pump and filter by small and high flow solenoid valves, behind which are unregulated throttles ДРН2 and ДРНЗ to ensure the required pump flow, as well as ypasnoy line hydraulically connected to the low flow solenoid valve.

These technical results are also achieved due to the fact that a gas station for refueling aircraft with a liquid propellant component containing a tractor connected to a semitrailer and a tank, a pneumohydrosystem including a pumping unit, shutoff valves, and control

devices, dispensing fittings with permanently docked hoses and a control system, is equipped with a pipeline, including hydraulically locking devices connected in series with each other, a filter, a flexible pipe and a connecting fitting, by means of which the insulated tank is connected to a pipe connected to a delivery vehicle - a tank container filled component of liquid rocket fuel, for example, kerosene, through a suction pipe with fittings and a refrigeration unit made in de two parallel mounted pump units, each of which is connected in series with a cooler located behind it.

The indicated technical results are also achieved due to the fact that the tanker for refueling aircraft with a liquid propellant component containing a tractor connected to a semitrailer and a tank, a pneumohydrosystem including a pump unit, shutoff valves, instrumentation, dispensing fittings with permanently attached hoses and control system, equipped with pipelines connected to a heat-insulated tank with fittings and fittings Ш2, Ш4, connecting the heat-insulated c a stub with a cooling system for a component of liquid rocket fuel, for example, kerosene, made in the form of two pump units connected in parallel and parallel installed after them and connected by pipelines with fittings with two liquid nitrogen tanks, two coolers, which together with pipelines with fittings form a closed cooling circuit of a component of liquid rocket fuel in a thermally insulated tank of a tanker.

The essence of the proposed utility models is illustrated by drawings. Figures 1, 2, 3, 4, and 5 show embodiments of a gas station for refueling aircraft with a liquid propellant component.

Since the prototype is the same for all variants, the figures 1 and 2 are common.

Figure 1, 2 and 3 - relate to option 1;

Figure 1, 2 and 4 - to option 2;

Figure 1, 2 and 5 - to option 3.

Figure 1 - shows a General view of a gas station for refueling aircraft with a component of liquid rocket fuel;

Figure 2 - shows a diagram of the pneumohydrosystem of a gas station;

In Fig.Z is a simplified diagram of refueling the upper stage of an aircraft - a carrier rocket - as a component of liquid rocket fuel using a gas tank;

Figure 4 is a diagram of the filling of a thermally insulated tanker tank with a liquid propellant component from a tank container;

5 is a diagram of a cooling component of a liquid rocket fuel in a gas tank.

Option 1 (figures 1, 2, 3)

A gas tanker 1 (FIGS. 1, 2) for refueling an aircraft, for example, a carrier rocket (PH) with a space head part — KGCH (FIG. 3), a component of liquid rocket fuel contains a tractor 2 connected to a semi-trailer 3 and tank 4, pneumohydrosystem 5, including a pumping unit 6, shutoff valves 7 (in Fig. 2 valves ВН1, ВН2, ВНЗ, ВН4 ...), control and measuring devices 8 (DTU1, DTU2 - sensors for monitoring the level and temperature of the component in the tank), 9 (DD1 ... DD4 - pressure monitoring sensors), 10 (MV1, MH1, MH2 - pressure gauges), dispensing fittings 11, 12 with a constant but docked hoses 13, 14 and a control system (not shown conditionally).

A gas station 1 for refueling an aircraft with a liquid propellant component is made in the form of a container ship mounted on a semitrailer

3 transport modular container 15 (with dimensions 1AA according to GOST 18477-79), divided by a sealed partition 16 into two compartments - the technological compartment 17, in which the filling equipment 18 is located (Fig. 1) - insulated tank 4, pump and valve unit, pneumohydraulic a block, pipelines, flexible hoses, sensors and a control compartment 19 with electric equipment 20 installed therein and a process control system for refueling 21 connected to both local 22 and remote 23 control panels.

The technological compartment 17 (FIG. 2) is equipped with a forced mechanical ventilation system 24 with a BHT1 fan, a filter 25 and a ventilation system 25a (FIG. 1), and the control compartment 19 is equipped with a portable air conditioner 26. A fire warning system 27 is located in both compartments 17 and 19, issuing a signal of a fire to local 22 and remote 23 control panels (figure 1).

The tank 4 is equipped with thermal insulation, safety valves KP1 and KP2 (figure 2) and fuses P01 and P02, preventing the explosion of the insulated tank 4 in case of fire, which increases the reliability and safety of the tanker. To optimize the position and stability, the insulated tank 4 is also equipped with three supports 28, 29, 30 (not shown conventionally) located along its length, of which the central 29 is made stationary, and the two extreme 28, 30 are slideable relative to the longitudinal axis of the container. Constantly connected hoses - flexible pipelines 13, 14, 33 (TG1, TG2, TG3, Fig.2) are located in trays 31, 32, made along the walls of the container (not shown conditionally). The receiving-issuing - hose 14 - flexible sleeve ТГЗ (Fig. 2) is equipped with an additional hose 33 (ТГ2) of smaller diameter for blowing, one end of which is connected to the pneumatic system, and the other end with the receiving - delivery hose on the dispensing nipple 11 (Ш4).

For docking with a thermally insulated tank 4 (figure 2), a U31 receiving and issuing device with two metal hoses 33 (TG2) and 14 (TGZ) is provided: sleeve 14 (TGZ) is designed to pump a component of liquid rocket fuel, and sleeve 33 (TG2) is for purging the sleeve 14 (TGZ) after work. Purge control is carried out by the observation device USM1. A bunch of sleeves 33 (TG2) and 14 (TGZ) is used when pouring a component into a thermally insulated tank 4 (Fig. 2), cooling a component, refueling a PH (Fig. 3) and draining a component from the same tank 4.

Before refueling the aircraft through the valve BH4 and the left end fitting Ш1 (Fig.2), the component is sampled for chemical analysis.

Through the fitting 12 (Ш2), the component is supplied to the cooling system (Fig. 5).

The SHZ fitting and the BH5 valve (Fig. 2) are used for introducing into the component, for example, kerosene, ethylcellosolve GOST 8313-88 (С2Н50С2Н40Н), if the set temperature of the component is below 5 ° C. The volume fraction of ethyl cellosolve is approximately 0.3%.

Through the nozzle 11 (W4), the component is fed to the refueling pH (Fig.3).

Union Ш5, valves ВН11 and ВН3 are used to completely remove the component from the tank 4 and extrusion lines.

To ensure cavitation-free operation of the pump in the gas cushion of a thermally insulated tank 4 tankers 1 create a boost - overpressure equal to 0.04 MPa.

To do this, into the insulated tank 4 through the rightmost fitting Ш6 (Fig. 2), a filter ФЗ, valves ВН12, ВН13, a gas reducer КР1, a check valve К02, and an electrovalve ЕК7 supply nitrogen gas from the nitrogen system.

Through valves BH14 and BH15, nitrogen pressure is released from the line into the atmosphere.

The solenoid valve EK1 is opened remotely during sparging, and the solenoid valve EK2 is used to turn on the bypass line while refueling at low flow rate through the solenoid valve 35 (EKZ, Fig. 2).

The gas station 1 is equipped with parallel installed in the pressure line 34 (figure 3) after the pump 6 and filter F2 solenoid valves small 35 (EKZ) and large 36 (EK4) costs, behind which are unregulated throttles DRN2 and DRNZ to ensure the required flow of pump 6, and also a bypass line (EK2) hydraulically connected to a small-flow solenoid valve 35 (EKZ). This design provides reliable, stable and cavitation-free pump operation when refueling at low flow rates.

Non-adjustable DRN chokes are very widely used in modern technology, they are calculated and selected according to GOST8 563.1-97 and OST 92.92.69-80. They are described, for example, in books:

- Cosmonautics. Encyclopedia, ed. “Owls. Encyclopedia ", 1985. Section throttling.

- V.F. Kovalevsky, N.T.Zheleznyakov, Yu.E. Beilin. Handbook of hydraulic drives of mining machines. "Bowels", M., 1967. p. 207.

- V.I. Turk, A.V. Minaev, V.A. Karelin. Pumps and pumping stations. Stroyizdat, 1977, p. 68.

- P.V. Koval. Hydraulic drive of mining machines ed. "Nedra", M., 1967, p. 208 and in other sources.

Non-adjustable chokes can be structurally made in the form of a disk with a central hole, for example, in the form of a washer.

Unregulated chokes DRN2 and DRN3 are identical in design, differ only in the diameter of the through holes:

d _dr3 > d _dr2 , since a large flow rate passes through DRN3 and a small flow through DRN2, where d is the diameter of the hole.

The refueling system of the launch vehicle with a component, for example, kerosene, consists of two parts - mobile and motionless (stationary). The movable part is (Fig.2, 3) the gas station to the connecting fitting 11 (W4).

The stationary part is located in the launching structure and on the mobile maintenance tower of MBO (not shown conditionally).

The gas station is located at zero mark (fitting 11 (W4) in Fig.2, 3). Pressure line 34 partially passes through the loss-closed channel [1, p. 37], and then it can be laid along the mobile service tower or cable refueling mast KZM (FIG. 3), on which a filling connection is installed (not shown conditionally) filter and filling valve.

The launch vehicle is preceded by: transportation of the launch vehicle to the launch complex; its installation in the launch system, fixing, docking of the space head part of the KGCH to the LV, verticalization, aiming, docking of ground-to-board communications, thermostating of the LV and KGCH. Therefore, the circuit shown in FIG. 3 is simplified, since the RN with KGCh for conventional purposes is conditionally shown not in the starting system.

When filling the vehicle with a liquid propellant component, for example, kerosene, the refueling tanker can operate automatically, both from the local control panel 22 and remotely from an external automated control system (ACS) 23.

To do this, through the rightmost fitting Ш6 (Fig. 2), a thermally insulated tank 4 is pressurized with nitrogen to an overpressure of 0.04 MPa.

The fitting 11 (W4) is connected to the fuel column (Fig.Z). Open valve 7 (BH2), while the valve BH1 is closed. Then remotely open the solenoid valve 36 (EC4) high flow rate and turn on the pump 6 (Fig.2, 3). In this case, the pressure line 34 is filled with kerosene T-1 to the filling valve on the KZM (Fig. 3), after which the filling valve is opened and the kerosene T-1 enters the tank of the I block of the launch vehicle with a flow rate (4.5 ... 5 ) · 10 ^-3 m ³ / s.

Upon reaching the "Preliminary level" [12] in the tank according to the command signal from the control system sensor (level control system) on board the LV, the high-flow solenoid valve 36 (EK4) automatically closes and the solenoid valve 35 (EKZ) low flow automatically opens (Fig. 2, 3) . The low flow rate in this case is (0.65 ... 0.85) · 10 ^-3 m ³ / s. When refueling at a low flow rate, the bypass line is simultaneously activated, for which the solenoid valve automatically opens

EC2 (figure 2) and part of the kerosene T-1 from the pressure line 34 after the pump 6 flows into the insulated tank 4 of the tanker.

As studies have shown, this ensures stable, cavitation-free and reliable operation of the pump [13, 14], prevents overheating of the housing and parts of the pump, which, moreover, increases the durability and safety of its operation.

When the “Nominal level” is reached by the command signal of the SKU sensor on board the LV, the low-flow solenoid valve 35 (EKZ) automatically closes and the filling process stops. The time of delivery of kerosene T-1 at a high flow rate is 1730 s (28.9 min), and the time of delivery at a low flow rate is 529 s (8.8 min).

Full refueling time 38 min.

Thus, the set of essential features set forth in the formula of the utility model of option 1, allows to obtain the required technical result, namely: to increase the reliability and efficiency of the gas station during refueling of the aircraft with a liquid propellant component by automating the process of refueling, achieving stable and cavitation-free pump operation in the refueling mode of the launch vehicle with a low flow rate (0.65 ... 0.85) · 10 ^-3 m ³ / s.

After refueling, the following operations are foreseen for cleaning the tanker: purging the filling hoses with gaseous nitrogen before joining them at the kerosene overflow and cooling site and at the zero mark of the launch facility; overflowing the remaining kerosene into the tank container; purging the insulated tank 4 of the tanker with nitrogen after the kerosene has been completely drained from the tanker.

Maintenance of the tanker is carried out with ventilation turned on, open doors and an open ventilation system 25a (Fig. 1).

The atmosphere inside the tanker is controlled by individual gas analyzers.

Option 2 (figures 1, 2, 4)

A gas station 1 for refueling aircraft with a liquid propellant component contains (FIGS. 1, 2): a tractor 2 connected to a semi-trailer 3 and a tank 4, a pneumohydrosystem 5 including a pumping unit 6, shutoff valves 7, instrumentation 8, 9, 10, dispensing fittings 11, 12 with permanently attached hoses 13, 14 and a control system.

In the second embodiment, it is envisaged to fill the insulated tank 4 of the tanker 1 with a liquid propellant component, for example, T-1 kerosene with a predetermined temperature from the tank container 39 (Fig. 4).

For this, the tanker 1 is equipped with a pipeline 37, including hydraulically locking devices connected in series with each other, for example, valves BH1, BH2, filter ФЗ, flexible pipe (hose) 13 and connecting fitting 12 (Ш2).

The container is a tank 39 (Fig. 4) through a suction pipe 40, a refrigeration unit 41, made in the form of two parallel installed pump units 6 (P10, P20), each of which is connected in series with a cooler 42 located behind the pump unit 6, and a pipeline 38 is connected to the nozzle 12 (SH2) of the tanker 1.

Filling the insulated tank 4 of the tanker 1 with a component, for example, T-1 kerosene, is carried out as follows: open the valves BH1, BH2 (figure 4) and the valve on the suction pipe 40. Turn on the refrigeration unit 41: coolers 42 and pumps 6 (P10 , P20). In this case, kerosene from the container-tank 39 (Fig. 4) through the pumps 6 through coolers 42 and pipelines 37 and 38 enters the insulated tank 4 of the tanker 1.

Upon reaching the specified level of the component in the insulated tank 4 by the signals of the temperature sensors - level 8, 9 (DTU1, DTU2) and pressure sensor 9 (DDZ) (figure 2), the valves BH1, BH2 and the valve on the suction pipe 40 are closed. Pipelines 37 and 38 disconnect and purge equipment

nitrogen.

Thus, the set of essential features set forth in the formula of the utility model of option 2, allows to obtain the required technical result, namely: to fill the insulated tanker tank with a liquid propellant component with a given temperature from the delivery vehicle - container - tank.

Option 3 (figures 1, 2, 5)

A gas station 1 for refueling an aircraft with a liquid propellant component contains (FIGS. 1, 2): a tractor 2 connected to a semi-trailer 3 and a tank 4, a pneumohydrosystem 5 including a pumping unit 6, stop valves 7, control and measuring devices 8, 9, 10, dispensing fittings 11, 12 with permanently attached hoses 13, 14 and a control system.

In the third embodiment, it is provided that the component of liquid rocket fuel, for example, T-1 kerosene, is cooled to the required temperature in the insulated tank 4 of the tanker 1 (Fig. 5) in order to increase its density before refueling.

For this, the tanker 1 through the fittings 11, 12 (Ш4 and Ш2, Fig.2) is connected to the cooling system 43, which consists of two pumps 6 connected in parallel, two coolers 42 and two liquid nitrogen tanks.

The refueling tank 1 together with the cooling system 43 forms a closed circulation cooling circuit for a component of liquid rocket fuel, for example, kerosene, in a thermally insulated tank 4 of the refueling tank (Fig. 5).

During operation, the valves BH1, BH2 and BH6 are opened. Coolers 42, tanks 44 and pumps 6 are included in the operation. In this case, the pumps 6 suck the fuel component from the insulated tank 4 of the tanker 1 and return them to the same tank 4 through the coolers 42. The pumps 6 work until the temperature of the component in the insulated tank 4 will not reach the required value,

then, according to the signals of temperature-level sensors 8, 9 (DTU1 and DTU2), the valves ВН1, ВН2, ВН6 are closed and the cooling system is turned off.

Thus, the set of essential features set forth in the formula of the utility model of option 3 allows us to obtain the required technical result, namely: to provide cooling of the component of liquid rocket fuel, for example, kerosene, to the required temperature in the insulated tank of the refueling tank in order to increase its density before refueling the aircraft apparatus.

The proposed utility model (including all three options), unlike the analogs and prototype, provides:

1) increasing the reliability and efficiency of the gas tanker during the process of filling the launch vehicle (LV) with a component of liquid rocket fuel with the specified parameters (temperature, pressure and flow rate) by automating the refueling process;

2) the achievement of stable and cavitation-free pump operation in the mode of refueling with low flow rate;

3) filling a thermally insulated tanker tank with a liquid propellant component with a predetermined temperature from a delivery vehicle - container - tank;

4) cooling a component of liquid rocket fuel, for example, kerosene (according to GOST 10227-86), to the required temperature in a thermally insulated tanker tank to increase its density before refueling.

A comparative analysis of the proposed utility model with well-known gas stations showed that the proposed utility model surpasses all known domestic and foreign gas stations for refueling aircraft with a liquid propellant component in terms of technical level and achieved results.

All three options of the proposed utility model will be used in full as part of the ground-based launch complex of the Soyuz-ST launch vehicle

at the Guiana Space Center.

The proposed utility model can also be used as part of Russian launch complexes.

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

INFORMATION SOURCES

1. Rocket and space complex, Cosmodrome. Under the general editorship of prof. A.P. Volsky. Military Publishing House, M., 1977, 309 pp. S.185-187 - analogues.

2. Rocket and space complex, Launch vehicles. Under the general editorship of prof. CO. Osipova Military Publishing House, Moscow: 1981, 315 pp. 12-18 - analogues

3. Actual problems of the Russian cosmonautics. Materials of XXX academic readings in space. M., January 2006 p. 330-331 hypersonic aviation - another possible area of application.

4. Zrelov V.N., Seregin V.N. Liquid rocket fuels. M: Chemistry, 1975, 320 p. 62-65, Fig. 41 - analogue.

5. Patent Ru 2206478 IPC 7 B64F 1/28, B60S 5/02, V65D 88/12, V67D 5/04, V60P 3/24, 06/20/2003 - analogue.

6. Patent Ru 2286289, C2, IPC 7 B64F 1/00, B67D 5/04, B60S 5/02, B60P 3/22, Published October 27, 2006 - prototype.

7. Patent Ru 28347 U1, 03.20.2003 - analogue.

8. Patent GB 1356949A, 06/19/1974 - analogue.

9. JP patent 07-330096A, 12.19.1995 - analogue.

10. Patent US 2707577A, 05/03/1955 - analogue.

11. Patent US 4131214A, 12/26/1978 - analogue.

12. Chelomei V.N., Polukhin D.P., Mirkin N.N. and etc.

Pneumohydraulic systems of propulsion systems with liquid rocket engines. Edited by Academician V.N. Chelomea. M .: Engineering, 1978, 240 s, 87-89 - level control system during refueling - a partial analogue.

13. Cherkassky V.M., Romanova T.M., Kaul R.A. Pumps, compressors, fans. Gosenergoizdat, ML, 1962, 264 s, pp. 65-66 - regulation of the performance of centrifugal machines. Throttle control; p.85-86 - Instability of work. Surge

14. Turk V.I., Minaev A.V., Karelin V.Ya. Pumps and pumping stations. Stroyizdat, M .: 1977, 256 s, pp. 63-64 - transient and transient pump operation; p.68-70 - regulation of the operation of pumps.

Preliminary examination conducted by Ph.D. Zh.R. Rakhmanov on funds of the RSLP at FIPS and FSUE KBOM.

Claims (3)

1. A gas tanker for refueling aircraft with a liquid rocket fuel component, comprising a tractor unit connected to a semi-trailer and a tank, a pneumatic and hydraulic system including a pump unit, shutoff valves, instrumentation, dispensing fittings with permanently attached hoses and a control system, characterized in that it made in the form of a transport modular container mounted on a container semi-trailer, separated by a sealed partition into two compartments - a technological compartment, in which refueling equipment is located, and a control compartment with electrical equipment and a control system for refueling technological operations associated with both local and remote control panels, the technological compartment is equipped with forced mechanical ventilation system with a filter and ventilation system, and the control compartment is portable air conditioning, a fire warning system is located in both compartments, which gives a signal about a fire to local and remote control panels, The tank installed in the technological compartment is provided with thermal insulation and three supports located along its length, of which the central one is fixed, and the two extreme ones with the possibility of sliding relative to the longitudinal axis of the container, and the constantly connected hoses are located in trays made along the walls of the container, and the receiving hose is equipped with an additional hose of a smaller diameter, one end of which is connected to the pneumatic system, and the other to the exhaust hose on the dispensing fitting, while crate is provided with parallel connected in the pressure line after the pump and solenoid filter small and large expenses, which are arranged with fixed throttles DRN2 DRN3 and to provide the required pump capacity, as well as a bypass line fluidly connected with the solenoid valve of small flow rate. 2. A gas tanker for refueling aircraft with a liquid rocket fuel component, comprising a tractor connected to a semitrailer and a tank, a pneumatic and hydraulic system including a pumping unit, shutoff valves, instrumentation, dispensing fittings with permanently attached hoses and a control system, characterized in that it equipped with a pipeline including hydraulically locking devices connected in series with each other, a filter, a flexible pipe and a connecting fitting, by means of which the insulated tank is connected to a pipeline connected to a delivery vehicle — a tank container filled with a liquid rocket fuel component, for example kerosene, through a suction pipe with valves and a refrigeration unit made in the form of two parallel pump units, each of which is connected in series with a cooler, located behind him. 3. A gas tanker for refueling aircraft with a liquid rocket fuel component, comprising a tractor connected to a semi-trailer and a tank, a pneumatic and hydraulic system including a pumping unit, shutoff valves, instrumentation, dispensing fittings with constantly attached hoses and a control system, characterized in that it equipped with pipelines connected to a heat-insulated tank with fittings and fittings Ш2, Ш4, connecting the heat-insulated tank with a cooling system for the liquid component rocket fuel, for example kerosene, made in the form of two pump units connected in parallel and parallel installed after them and connected by pipelines with fittings with two liquid nitrogen tanks, two coolers, which together with pipelines with fittings form a closed circulation cooling circuit of the liquid rocket fuel component in a thermally insulated tanker tank.