RU71962U1 - GROUND STARTING COMPLEX FOR PRE-START PREPARATION AND STARTING A ROCKER-BOARD WITH A SPACE HEAD (OPTIONS) - Google Patents

Abstract

1. A ground launch complex for prelaunch preparation and launch of a launch vehicle with a space warhead, comprising a transport and installation unit, a launch structure, a single-slope gas deflector with a gas outlet, a launch system, a cable-filling mast, an upper cable-mast, lower cable-masts , service tower, service cabin, oxidizer and fuel refueling systems, fuel cooling system, gas storage equipment, refrigeration center, low-pressure air temperature control system, general technical systems and auxiliary equipment, characterized in that it is additionally equipped with a high-pressure thermostatting system for the space head part with an accelerating unit and a spacecraft, which includes a main pipeline and a receiver of compressed air connected to the gas storage equipment, the cylinders of which through the charging shield and the pipeline with fittings are connected to the main pipeline, and the shield for the delivery of the compressed air receiver is connected to the pipeline for supplying air to the space a head part equipped with a sampling device connected to an aerosol particle counter, a pneumatic shield for monitoring the condition of compressed air, means for remote monitoring of temperature and air pressure parameters, as well as a standard hygrometer for controlling the humidity of the air supplied to the space head part, which is lowered through a pneumatic control box pressure, gas heater and air cooler installed in the ring cooling circuit of the refrigeration center, connected to a detachable connection bl

Description

The utility model relates to rocket and space technology, and more specifically to ground-based launch complexes of space launch vehicles and can be used under any climatic meteorological conditions at any time of the year or day to automatically maintain in the rocket compartments and space head part with a booster unit and spacecraft in the process of their prelaunch preparation of specified optimal temperature and humidity conditions and high purity and air conditioning, providing one of the solutions constituent influences on the performance, reliability and efficiency of the equipment, devices, assemblies, systems, onboard power sources and other elements installed in the thermostatic

the compartments of the launch vehicle (LV) and the space warhead (KGCH), which increases the reliability and efficiency of the launch complex (SC), the LV and KGCH as a whole. The utility model can also be used to automatically maintain the specified optimal temperature and humidity conditions in the LV compartments with high-pressure inert gaseous nitrogen, which at the same time ensures explosion and fire safety and high reliability of LV launches with KGCH at the launch complex.

A ground-based launch complex for prelaunch preparation and launch of a launch vehicle with a manned spacecraft is known, comprising a launch stand, a gas reflector, a gas outlet channel, a caterpillar conveyor, a cable-filling tower, a receiver of compressed gases, a mobile service tower, on which equipment and air supply lines are located and low-pressure nitrogen to the space rocket system, an oxidizer and fuel refueling system, and all other necessary equipment (see the Cosmodrome book. Under the general revision of paragraph Prof. A.P. Volsky. M: Military Publishing House, 1977, p.95-100; 229-232) [1].

The disadvantages of the ground-based launch complex include the fact that the mobile service tower with air and nitrogen supply lines is diverted long before the launch, while thermostating is prematurely interrupted, which leads to a violation of the temperature and humidity conditions in the LV and OGC compartments with negative consequences. In addition, the insufficiently high degree of purity of the air supplied to the spacecraft with a CGF (the concentration of air pollution with aerosol particles is about 2.0 ... 3.0 mg / m ³ or more), under certain conditions, can lead to clogging of the passage sections of the airborne pneumatic communication , as well as contamination of the working surface of on-board equipment, devices, systems, etc., which reduces their reliability.

Known land launch complex containing a launching device, storage of liquid rocket fuels, facilities for refueling and draining components

liquid rocket fuels, a fire extinguishing system with a tank for industrial water, a system for structuring nitrogen-containing liquid rocket fuels, including tanks for storing a structure-forming nitrogen-containing liquid rocket fuel, and a system for supplying a structure-forming agent to the emergency fuel spill area, having collectors with structure-forming sprayers (concentrically arranged Patent Ru 2094338, C1, B64G 5/00, 06/20/1994) [2].

The disadvantages of this starting complex are:

- insufficiency of special technological and general technical equipment for prelaunch preparation and launch of the launch vehicle with KGCH, since using this launch complex only part of the tasks can be solved, namely: to carry out, for example, refueling the launch vehicle with fuel components, while observing the fire and explosion safety requirements and environmental safety;

- low reliability and lack of effectiveness of the launch complex, due to the absence, in particular, of high-pressure air thermostat systems for PH and KGCh, as well as a system for thermostatting of LV compartments with high-pressure nitrogen gas;

- lack of tools for monitoring parameters: temperature, pressure, humidity and purity of thermostatic air.

These shortcomings significantly reduce the reliability and efficiency of the ground launch complex and lead to the inability to ensure high reliability of LV launches with KGCh.

Further analysis of patents and scientific and technical literature [1 ... 20 et al.] Showed that, in terms of technical nature and technical result achieved, the closest to the proposed utility model is the ground launch complex for prelaunch preparation and launch of the Vostok launch vehicle with space head part described in the books "Cosmonautics (Encyclopedia)"

[3, p. 44; 67-68; 152; 309-310; 383-384] and “Launch vehicles” [4, p.19-22, Fig. 1. 2 - Vostok launch vehicle]

This ground-based launch complex includes: a railway transportation and installation unit equipped with a hydraulic system and electrical equipment; launching facility, which is the main construction of the launching complex and provides preparation and launch of the LV with KGCh and placement of equipment; a single-slope gas deflector with a gas outlet in the form of a tray; a launch system for installing the Vostok launch vehicle in it, verticalization and holding of the launch vehicle with the KCH in a predetermined position during prelaunch and launch; cable-refueling mast for supplying electric cables, refueling, pneumatic, drainage and other communications to the upper LV blocks and to KGCh; the upper cable-mast, along which electric cables are laid to the upper stages of the launch vehicle; lower cable masts for connecting electric cables to the tail of the launch vehicle; a service farm (tower) for connecting ground-to-board communications to the launch vehicle with the KCH; a service cabin for servicing the tail and bottom parts of the launch vehicle; oxidizer and fuel refueling systems; fuel cooling system; gas storage equipment - receiver of compressed gases (air, nitrogen, helium); a refrigeration center that meets the needs of the launch complex, LV and KGCh in the cold; systems of temperature control by low-pressure air RN and KGCh; general technical systems, including: water supply system; water recycling system for cooling refrigeration machines and other units; system of industrial stocks; gas analysis system of premises; lightning protection devices and lightning conductors; communication facilities and others; auxiliary equipment, including mobile and stationary systems of water, gas and foam fire extinguishing, etc.

We selected this ground-based launch complex as a prototype of the proposed utility model.

The disadvantage of the prototype is that the farm (tower) service is diverted from the LV with KGCH for a considerable time before launch and at the same time undock

connection of thermostatic control systems with low-pressure air from the LV and KGCh. As a result, premature termination of thermostatting of the LV and OGC at the launch complex occurs, which can lead to a violation of the optimal temperature and humidity conditions in the LV and OGC compartments, which are essential for their normal functioning. The maintenance of these modes due to preliminary bringing the temperature of the structure and air in the LV compartments and in the KGCH to higher values does not give the desired optimal results.

The technical result of the utility model when used on rocket and space complexes is to increase the reliability and efficiency of the ground launch complex and to ensure high reliability of launches of launch vehicles with space warheads.

Let us briefly describe the technical result.

Ensuring high reliability of launches of launch vehicles with space warheads is possible only with the failure-free and reliable operation of the ground launch complex, launch vehicle and space head, therefore, the obtained technical result cannot be divided into parts related to the ground launch complex, launch vehicle and the space head part, since they are closely interconnected, are inseparable from the point of view of achieving a technical result and should be considered as a single system. The reliability of such a system depends on the reliability of its components. Therefore, increasing the reliability and efficiency of the ground launch complex will certainly affect the reliability of launches of launch vehicles with space warheads.

Thus, the utility model is aimed at obtaining a single technical result, which does not contradict the requirements of the unity of the invention.

The specified technical result is achieved due to the fact that the ground-based launch complex for prelaunch preparation and launch of the launch vehicle with a space warhead, comprising a transport and installation unit, a launch facility, a single-slope gas deflector with a gas outlet channel,

start-up system, cable-mast, upper cable-mast, lower cable-masts, service tower, service cabin, oxidizer and fuel refueling systems, fuel cooling system, gas storage equipment, refrigeration center, low-pressure thermostat system, general technical systems and auxiliary equipment, according to the utility model, it is additionally equipped with a thermostatic control system for high-pressure air of the space head part with an upper stage and a spacecraft, which The first one includes a main pipeline and a compressed air receiver connected to the gas storage equipment, the cylinders of which are connected to the main pipeline through a charging shield and a pipeline with valves, and the compressed air receiver delivery panel is connected to the air supply pipe to the space head equipped with a sampling device, connected to a counter of aerosol particles, a pneumatic shield for monitoring the conditionality of compressed air, means of remote control of parameters - temperature and air pressure the ear, as well as a standard hygrometer for controlling the humidity of the air supplied to the space head part, which is connected to the detachable connection of the launch vehicle block A through the pneumatic control box, pressure reduction unit, gas heater and air cooler installed in the ring cooling circuit of the refrigeration center through a vertical pipeline on board the launch vehicle is connected to the space head part, while the pipeline for supplying air to the space head part in the section from the gas heater to A well-insulated carrier rocket.

The indicated technical result is also achieved due to the fact that the ground launch complex for prelaunch preparation and launch of the launch vehicle with a space head contains a transport and installation unit, a launch structure, a single-slope gas deflector with a gas outlet channel, a launch system, a cable-filling mast, and an upper

cable mast, lower cable masts, service tower, service cabin, oxidizer and fuel refueling systems, fuel cooling system, gas storage equipment, refrigeration center, low-pressure air temperature control system, general technical systems and auxiliary equipment, according to the utility model is additionally equipped with a system thermostatic control of high-pressure air of the compartments of the launch vehicle, which includes the main pipeline and the receiver compressed into air, consisting of cylinders, the charging board of which is connected via a pipeline with valves to the main pipeline, and the delivery panel is connected to the air supply pipe to the launch vehicle with pressure and temperature sensors installed on it, which through the air supply box, filter, control air box, block a pressure reducing device, a gas heater and an air cooler located in the cooling circuit of the refrigeration center are connected to a detachable connection of the launcher unit A and are connected via on-board communication to the instrument and inter-tank compartments of block A and the inter-tank and tail compartments of block And of the launch vehicle, while the portion of the pipeline for supplying air to the launch vehicle from the gas heater to block A is thermally insulated.

The indicated technical result is also achieved due to the fact that the ground launch complex for prelaunch preparation and launch of a carrier rocket with a space head contains a transport and installation unit, a launch structure, a single-slope gas deflector with a gas outlet channel, a launch system, a refueling mast cable, and an upper cable -mast, lower cable masts, service tower, service cabin, oxidizer and fuel refueling systems, fuel cooling system, gas storage equipment, refrigerated The center, thermostatic control system with low-pressure air, general technical systems and auxiliary equipment, according to the utility model, is equipped with a high-temperature nitrogen control system

the compartments of the launch vehicle compartments, which includes the main pipeline and a high-pressure compressed nitrogen receiver connected to the gas storage equipment, the cylinder charging shield through which is connected to the main pipeline through the pipeline with valves, and the delivery shield is connected to the high-pressure nitrogen supply pipe to the rocket carrier with pressure and temperature sensors installed on it, which through the inlet air shield with an angle valve, filter, control air shield, pressure reduction unit, gas heater and a nitrogen cooler installed in the cooling circuit of the refrigeration center is connected to a detachable connection of the launcher unit A and is connected via the on-board communication to the instrument and inter-tank compartments of the A unit and the inter-tank and tail compartments of the And launcher unit.

The essence of the proposed utility models is illustrated by drawings.

Figure 1, 2, 3 and 4 presents embodiments of a ground-based launch complex for prelaunch preparation and launch of the LV with KGCh.

Since for all variants the prototype is the same, then figure 1 is common.

Figure 1 and 2 - relate to option 1;

Figure 1 and 3 - to option 2;

Figure 1 and 4 - to option 3.

Figure 1 - shows a structural diagram of a ground-based launch complex for prelaunch preparation and launch of a launch vehicle (LV) with a space warhead (CSC) at a point in time after installing the launch vehicle using the transport and installation unit on the launch system, bringing up the service tower, lifting and docking KGCh with the LV.

Figure 1 - positions that could not be shown are enclosed in squares.

Figure 2 - shows a diagram of a temperature control system for high pressure air space head part.

Figure 3 - diagram of a temperature control system for high-pressure air compartments of the launch vehicle.

Figure 4 - diagram of a thermostatic system of high-pressure nitrogen compartments of the launch vehicle.

Option 1

The ground-based launch complex for prelaunch preparation and launch of the launch vehicle with a space warhead (Fig. 1) comprises a launch vehicle 1 (with conical side blocks), a space warhead 2 (including a head fairing, a spacecraft and, if necessary, an acceleration block " Frigate "), transport and installation unit. 3, launching structure 4, single-slope gas deflector 4a with gas outlet channel, launching system 5, cable-filling mast 6, upper cable-mast 7, lower cable-masts 7a, service tower 8, cab 9 from maintenance, refueling system 10 oxidizer and fuel 11, cooling system 12, fuel, gas storage equipment 13, refrigeration center 14, temperature control system low pressure air space 15 the head portion 2, general technical system 16 and accessory 17.

The ground-based launch complex for prelaunch preparation and launch of the launch vehicle 1 with the space warhead 2 is additionally equipped with a high-pressure thermostatting system for the space warhead 2 (Fig. 2), which includes a main pipeline 18 and a compressed receiver connected to the gas storage equipment 13 air 19, cylinders 20 of which, through the charging shield 21 and the pipe 22 with fittings, are connected to the main pipe 18, and the delivery board 23 of the compressed air receiver 19 is connected to the air supply pipe 24 ha in the space head part 2,

equipped with a sampling device 25 connected to a counter 26 of aerosol particles, a pneumatic shield 27 for monitoring the condition of compressed air, means for remote control of parameters - temperature 28 and air pressure 29, as well as a standard hygrometer 30 for controlling the humidity of the air supplied to the space head part 2, which a pneumatic control box 31, a pressure reducing unit 32, a gas heater 33 and an air cooler 34 mounted in the ring cooling circuit 35 of the refrigeration center 14, are connected to a detachable connection volume 36 of block A of the launch vehicle 1 and by means of a vertical pipeline (a vertical pipeline not shown conventionally in FIG. 1) on board the launch vehicle 1 is connected to the space head part 2, while the air supply pipe 24 to the space head part 2 is located at a distance from the gas heater 33 to the block A of the launch vehicle 1 is thermally insulated. The sampling device 25 includes a probe connected to the probe installed in the air supply pipe 24, a sampling pipe 37, a shutoff valve 38, an orifice 39, a conical chamber 40, and a sampling pipe 41 connected to an OEAS 26 optical-electronic aerosol counter.

The air supply pipe 24 to the space head part 2 is connected through an angular valve 42 to a control pneumatic board 31, in which a filter 43, a pressure sensor 44, a pressure gauge valve 45, a pressure switch 46, an electro-pneumatic valve 47, and a non-return valve 48 are installed.

In the block of pressure reduction 32 are located: electro-pneumatic valve 47, butterfly valve 49, gas pressure reducer 50, reducing pressure, for example, from 40 MPa to 6 MPa, safety valve 51, check valve 48, throttle 52, angle valve 42.

Option 2

The ground-based launch complex for prelaunch preparation and launch of the launch vehicle with a space warhead (Fig. 1) comprises a launch vehicle 1 (with conical side blocks), a space warhead 2, and a transport and installation

unit 3, start-up structure 4, single-slope gas deflector with gas outlet channel 4a, start-up system 5, cable-filling mast 6, upper cable-mast 7, lower cable-masts 7a, service tower 8, service cab 9, refueling systems 10 with oxidizing agent 10 and fuel 11, a fuel cooling system 12, gas storage equipment 13, a refrigeration center 14, a low pressure air thermostat system 15 PH 1, general technical systems 16 and auxiliary equipment 17.

The ground-based launch complex for prelaunch preparation and launch of a launch vehicle with a space head part (Figs. 1, 3) is additionally equipped with a high-pressure thermostatting system for the PH 1 compartments, including the main pipe 18 and the compressed air receiver 19 with cylinders connected to the gas storage equipment 13 . The charging shield 21 of the cylinders 20 through the pipe 22 with the fittings is connected to the main pipeline 18. The delivery shield 23 is connected to the pipeline 24 for supplying air to the carrier rocket 1, on which pressure sensors 25 and temperature 26 are installed.

The air supply pipe 24 to the PH 1 through the inlet air box 27, the angle valve 28, the filter 29, the air control box 30, the pressure reducing unit 31, the gas heater 32 and the air cooler 33 located in the cooling circuit 34 of the refrigeration center 14 is connected to a detachable connection 35 unit A of the launch vehicle 1 and, through on-board communication, is connected to the instrument and inter-tank compartments of unit A and the inter-tank and tail compartments of the unit And the launch vehicle 1.

In this case, the portion of the pipeline 24 for supplying air to the launch vehicle 1 from the gas heater 32 to the block A is thermally insulated.

The pneumatic control panel 30 (Fig. 3) includes: an angle valve 28, a pressure gauge valve 36, a pressure switch 37, an electro-pneumatic valve 38 and a check valve 39. The pressure reducing unit 31 contains an electro-pneumatic valve 38, a butterfly valve 40, a gas reducer 41, a pressure valve 36 , safety valve 42, pressure switch 37, check valve 39 and throttle 43.

Option 3

The ground-based launch complex for prelaunch preparation and launch of a launch vehicle with a space head part (FIG. 1) comprises a launch vehicle 1, a space head part 2, a transport and installation unit 3, a launch structure 4, a single-stage gas deflector with a gas outlet channel 4a, a launch system 5, cable-filling mast 6, upper cable-mast 7, lower cable-masts 7a, service tower 8, service cabin 9, refueling systems 10 oxidizer and fuel 11, fuel cooling system 12, gas storage equipment 13, refrigerators Center 14, RN 1 thermostating low pressure air system 15, 16 and general technical system auxiliary equipment 17.

The ground-based launch complex for prelaunch preparation and launch of the launch vehicle with the space head part (Figs. 1, 4) is equipped with a high-temperature nitrogen stating system for the launch vehicle compartments 1, which includes the main pipeline 18 and high pressure compressed nitrogen receiver 19

The shield 20 for charging cylinders 21 of the receiver 19 of high-pressure compressed nitrogen through a pipe 22 with valves is connected to the main pipe 18, and the shield 23 of delivery is connected to the pipe 24 for supplying high pressure nitrogen to the launch vehicle 1, on which pressure sensors 25 and temperature 26 are installed. The pipeline 24 for supplying high pressure nitrogen to the launch vehicle 1 through an inlet air shield 27 with an angle valve 28, a filter 29, a pneumatic control board 30, a pressure reduction unit 31, a gas heater 32, and a nitrogen cooler 33 installed in the cooling circuit 34 odilnogo center 14 is connected to a releasable connection unit 35 A booster 1 and through communication board associated with instrumentation and intertank compartments intertank block A and block and caudal compartments and launcher 1.

The pneumatic control 30 (Fig. 4) includes: a pressure sensor 25, an angle valve 28, a pressure gauge valve 36, a pressure switch 37, an electro-pneumatic valve 38, and a check valve 39.

In the pressure lowering unit 31 are located: electro-pneumatic valve 38, throttle valve 40, gas reducer 41, reducing the inlet pressure, for example, from 40 MPa to a predetermined value (9 ± 1 MPa), pressure gauge valve 36, safety valve 42, pressure switch 37, reverse valve 39, angle valve 28 and throttle 43.

At the proposed ground-based launch complex (with the participation of all variants of the utility model), prelaunch preparation and launch of the launch vehicle with a space head are carried out according to the cyclogram (program) of launching the launch vehicle from the operator’s console using the automated control system for technological equipment of the launch complex - ACS TO SK .

ACS TO SK provides: automatic and manual remote control of executive elements of technological systems and assemblies; automatic and manual remote control of electric drives and electric heaters of technological systems and assemblies through low-voltage complete devices (NKU), which are part of ACS TO SK; remote control and display at the operator’s workplace of information on the state of executive elements of technological systems and assemblies; measurement of the current values of the parameters and the alarm about the disconnection of their values; the functioning of security locks; remote power on (off); exchange of information with related systems, etc.

The proposed utility model (taking into account all its options) can be used both at Russian launch complexes and at the Soyuz-ST launch complex in the Guiana Space Center.

There are two known options for the assembly and installation of LV with KGCH on the launch system. The first option is used at Russian launch complexes, and the second - at the launch complex of the Soyuz-ST launch vehicle in the Guiana space center.

According to the first option, at the technical complex, the fully launched and launched horizontally tested launch vehicle 1 with the help of cranes and traverses is transferred to the transport and installation unit 3. Then carefully assembled, tested and filled (at the filling station of the technical complex) with space components of fuel and compressed gases apparatus 2 and the Frigate booster unit installed in the space head part (CSC) are docked to the launch vehicle 1, fixed to the transport and installation unit 3 and transported t to the launch complex, where the LV with KGCh using the transport and installation unit installed on the launch system in the starting position. Next, connect the connection "Earth - board." A rotary service farm is used to service LVs in Russian SKs.

According to the second option, in a technical complex, a carefully assembled launch vehicle 1 without a space head is installed on the transport and installation unit 3, fixed and transported in a horizontal position to the launch complex, where it is raised to a vertical position using the transport and installation unit 3 and installed on starting system 5. Then, a mobile service tower is brought to the launch vehicle.

At a technical complex gas station, the spacecraft 2 and the Frigate upper stage installed in the space head part are filled with fuel components and compressed gases.

Then the space head part is delivered in an upright position to the launch vehicle to the launch complex, where it is lifted along the rails with the help of a mobile service tower crane and mounted on a stand at a platform at a level of 27 m to remove the transport cover and connect the thermostatic control system with low-pressure air.

After that, the cosmic warhead is docked to the launch vehicle, checked and, using the turntable and hydraulic jacks of the suspensions, the pH is calibrated with KGCh.

Then, ground electrical, pneumatic and hydraulic communications are connected to the onboard detachable connections of the launch vehicle, that is, all ground-to-board communications are connected using the lower cable masts, the upper cable mast, the cable-filling mast, the service tower and service cab.

After servicing the tail and bottom parts of the launch vehicle before launching the launch vehicle with KGCH, the service cabin is diverted to the niche of the launch facility along the rail track and is protected by a heat-shielding curtain from the effects of gas jets of rocket engines.

After assembling the launcher with the OGC on the starting system and setting it to the start position, the low-pressure air is used to operate the thermostat systems of the launcher and OGC compartments.

The KGC thermostatic control system with low pressure air includes blowers (fans), an air supply pipe with fittings, filters, air coolers, electric heaters and other necessary equipment.

Temperature and purity control of thermostatic air supplied to the KGCH is carried out near the KGH hatches.

The thermostatic control system of the KGCH by low-pressure air is turned off when the service tower is withdrawn and the thermostatic control system of high-pressure air of the space head part is turned on (FIGS. 1, 2, option 1). The latter is switched off by a ground-to-board command immediately before the lift contact command.

In the process of temperature control by high pressure air KGCh control the cleanliness, conditioning, humidity, temperature and pressure of the air supplied to the KGCh.

The LV thermostatic control system with low-pressure air includes fans for supplying air with the necessary parameters (pressure, flow, temperature), air filters that clean the atmospheric air of mechanical impurities, dust particles and corrosive agents with cleanliness

filtration of at least 20 microns, refrigerators, air coolers, electric heaters and other necessary equipment. Monitoring and recording the temperature of thermostatic air is carried out near the LV hatches. 3.5 hours before the “Contact lift” command, the thermostatic control system of the LV by low-pressure air is turned off and the thermostatic control system of high-pressure air of the rocket compartments is turned on (Figs. 1, 3, option 2).

15 minutes before the command "Contact lift" include in the system thermostatic control of high-pressure nitrogen compartments of the launch vehicle (Fig.1, 4, option 3). The mass flow rate of nitrogen supplied to the temperature control of the compartments of blocks A and I of the launch vehicle at a temperature of from 20 to 50 ° C is, for example, 0.33 ± 0.02 kg / s; the nitrogen pressure at the inlet to the pH is 9 ± 1 MPa.

Before filling the pH with liquid oxygen, the communications of the filling system and the pH tanks are cooled. Refueling and replenishment of blocks A, B, C, D, D and stage III of the launch vehicle with liquid oxygen is carried out by displacing liquid oxygen from the storage tanks with gaseous oxygen obtained using a liquid oxygen evaporator.

The temperature of liquid oxygen at the inlet to the tanks of the pH blocks is not more than 92 K.

The boost pressure of the storage tanks is, for example, in the range of 0.8-1.0 MPa.

Before filling the vehicle with fuel - T-1 kerosene - the refueling system is alerted. Using a cooling system, T-1 kerosene is cooled to the desired temperature.

The refueling system of blocks A, B, C, D, D of a carrier rocket with fuel - kerosene T-1 consists of a movable and a fixed (stationary) part. The moving part is a railway tanker, which includes a pumping unit, tanks, pipelines with fittings and all necessary equipment.

The stationary part is located in the launch pad. The gas station is installed at the zero mark of the launch facility, and the communication

for the removal of vapors from the drainage safety valve (WPC) of block A of the launch vehicle - on the service tower.

A railway tanker is connected to a gas station.

A filter with a filter fineness of 70 microns is installed in the fueling system.

The block And the launch vehicle is refueled with T-1 kerosene using a gas station through a filter with a filter fineness of 20 microns.

In two compartments of the gas tanker, all the necessary equipment is installed.

The gas storage equipment in the process of prelaunch preparation for the launch of the launch vehicle with KGCH provides compressed gases - air, nitrogen and helium - to all consumers at the launch complex; compressed gases are used to control valves, charge and recharge onboard cylinders of a booster rocket with KGCH, pressurize oxidizer and fuel tanks before start-up, temperature control KGCh high-pressure air (option 1) and LV (option 2), and temperature-control high-pressure nitrogen of the booster compartments (option 3), as well as for the operation of the ejection system, etc.

The gas storage equipment consists of: cylinders with compressed gases, pneumatic panels for charging and dispensing nitrogen and air, pneumatic panels for charging and dispensing helium, pneumatic panels for monitoring gas pressure, gas quality control, gas pipelines with fittings, etc.

The refrigeration center ensures the normal operation of gas coolers (air, nitrogen) in the process of temperature control of KGCh and LV.

General technical systems in the process of pre-launch preparation of the launch vehicle with KGCH for launch are constantly included in the work for the water supply of the launch complex and the creation of normal conditions for the work of maintenance personnel.

Ancillary equipment is used to carry out auxiliary operations arising during the prelaunch.

Complex tests and checks of the launch vehicle and the space head are carried out before launch, and a flight mission is introduced into the control system equipment.

After completing all the technological operations of the pre-launch preparation, the launch command is given by the launch manager in accordance with the established launch program and on the basis of information about the status and availability of all systems and units of the launch complex.

They include a multi-channel system for recording and recording the controlled parameters of all onboard LV systems and the launch complex. The fuel lines of the launch vehicle are purged with nitrogen, the drainage lines of the oxidizer and fuel tanks of all stages of the launch vehicle are closed, the tanks are replenished with liquid oxygen, and the launch tanks are pre-pressurized with compressed gases.

Onboard control systems and power supplies are included. The cable-filling mast is retracted, and then the upper cable-mast. All communication with the LV side is terminated. The latter is in autonomous control mode; all systems are powered from the LV. The ignition turns on, the TNA starts to work. In chambers create a torch of flame.

The exit of rocket engines to the mode and the moment of separation of the launcher with the KGCh from the launch system is controlled.

The progress of operations is displayed on the launch console and is accompanied by the commands "Charge", "Contact", "Earth-board", "Ignition", etc.

A command is issued to undock and discard the quick couplers.

Moving elements of the launch system (supporting trusses, bearing booms and guiding devices) are retracted from the launch vehicle during its movement.

At the moment of launching the launch vehicle from the supports of the launch system, the lift contact sensor (“KP”) is activated and the “Start” banner lights up on the launch console.

The thrust of the engines increases, and the launch vehicle with the space head part leaves the zone of possible collision with elements of the launch system.

The gas stream during the launch of the launch vehicle is discharged through a single-slope gas deflector and a gas channel channel type.

The proposed ground-based launch complex for prelaunch preparation and launch of a launch vehicle with a space warhead allows:

- carry out (unlike analogs and prototype) thermostatic control of high-pressure air of the space head part (option 1) and the rocket compartments (option 2) in automatic mode almost until the start-up (the thermostatic control system of high-pressure air is switched off by the command “Earth- board "about 42 seconds before the command" Contact lift "(" KP "), and the thermostatic control system for high-pressure air of the rocket compartments is turned off by the command" Supercharging "about 2.5 minutes before the command" KP "), which increases reliability and effectively the operation of the equipment, instruments, aggregates and systems installed onboard the LV and KGCH, both at the launch complex and in space, ensuring the implementation of space programs;

- automatically maintain the specified optimal temperature and humidity conditions in the rocket compartments with high-pressure inert gaseous nitrogen, which increases the reliability and efficiency of the on-board equipment and LV systems and at the same time ensures explosion and fire safety, high reliability and safety of the LV launcher launches at the launch pad complex.

The experiments carried out on a similar launch complex 17P32-6 showed [20] that the purity of the high-pressure thermostatic air supplied to the space head was (1 ... 2) • 10 ^-8 g / cm ² in terms of the degree of contamination with organic substances, which an order of magnitude better than compared with the requirements of the specifications of the European Space Agency (ESA pss-01-201, ESA pss-01-705), according to which the pollution should not exceed 2 • 10 ^-7 g / cm ² [20].

Aerosol contamination of thermostatic air was also tested. The purity of thermostatic air was compared with the data of the Federal

US standard (FED.STD-209E) and amounted to 250 particles in one liter, particle size 0.5 μm, and according to US Federal Standard 3530 particles in one liter, that is, according to the proposed utility model, the air supplied to the PSG is 14 times cleaner and ultra-high frequency.

This is extremely important, since the ingress of such air, for example, onto the surface of solar panels will not cause negative consequences, while the ingress of polluted air will lead to the fact that solar cells in space cannot reach the calculated power mode with all the ensuing negative consequences.

Another advantage of the proposed launch complex (in comparison with analogues and prototype) is that it will be built in the Guiana space center, located closer to the equator (5 ° north latitude), which will allow to put more payload into orbit (instead, for example, one spacecraft, several spacecraft), which increases the efficiency of the launch vehicle and the launch complex as a whole.

A comparative analysis of the proposed utility model with known launch complexes showed that the proposed launch complex surpasses all known domestic and foreign launch complexes of space launch vehicles in technical level.

Thus, the set of inextricably interconnected essential features set forth in the utility model formula,

allows you to get a significant technical result,

namely, to increase the reliability and efficiency of the launch complex and to ensure high reliability of launches of launch vehicles with space warheads.

The proposed utility models will be used in full at the launch complex of the Soyuz-ST launch vehicle in the Guiana Space Center, as well as at Russian launch complexes for Soyuz-2 launch vehicles.

INFORMATION SOURCES

1. The spaceport. Under the general editorship of prof. A.P. Volsky. M .: Military Publishing House, 1977, p. 81, table 3.1; p. 92-100; 229-232 - analogue

2. RU 2094338, C1, B64G 5/00, 06/20/1994 - analogue.

3. Cosmonautics. Encyclopedia. M .: Soviet Encyclopedia, 1985, p. 44; 67-68; 152; 309-310; 383-384 - Ground-based launch complex for prelaunch preparation and launch of the Vostok launch vehicle with KGCh - a prototype.

4. Rocket and space complex. Launch vehicles. Under the general editorship of prof. S.O. Osipova. M .: Military Publishing House, 1981, p.19-20 - launch vehicle "Vostok"

5. Actual problems of Russian cosmonautics. Materials of XXX academic readings in space. (Moscow, January 2006), p.235 - analogue.

6. Mikhailov V.P., Nazarov G.A. Space launch complexes. M .: 1979, pp. 10-20 - analogues.

7. Ru 2242411, C2, B64G 5/00, 03/18/2003 - analog.

8. Ru 2270792, C1, B64G 5/00, 08/05/2004 - analog.

9. US 4932607, B64G 5/00, 02/02/1989 - analogue.

10. FR 2635500, A1, B64G 5/00, 02.23.1990 - analogue.

11. Austr. 631804, B64G 5/00, 1990 - analogue.

12. Ru 2099255, C1. B64G 5/00, 12.20.1997 - analogue.

13. Ru 2158421, C2, B64G 5/00, 10.27.2000 - analogue.

14. US PCT (US-98) 15899, B64G 5/00, 07/27/1998 - analogue.

15. US 5042358, 5B63B 35/40, F41F 3/042 - no analogue was found.

16. FR 2595318, B64G 5/00, 03/02/1987 - no analogue was found.

17. Ru 2094337, C1. B64G 5/00, 10.27.1997 - analog.

18. On the earth and in space. FSUE KBOM named after V.P. Barmin. Under the general editorship of Doctor of Technical Sciences, prof. I.V. Barmina. M .: KBOM, 2001, p. 141-143; 158-160 - analogues.

19. Voronin B.P., Stolyarov N.A. Preparing to launch and launch rockets. M: Military Publishing House, 1972, pp. 41-74 - analogues.

20. Program and methodology for conducting experimental work to determine the degree of air purity of thermostatic control systems on SK 17P32-6. M .: 2002, KBOM.

Claims (3)

1. A ground launch complex for prelaunch preparation and launch of a launch vehicle with a space warhead, comprising a transport and installation unit, a launch structure, a single-slope gas deflector with a gas outlet, a launch system, a cable-filling mast, an upper cable-mast, lower cable-masts , service tower, service cabin, oxidizer and fuel refueling systems, fuel cooling system, gas storage equipment, refrigeration center, low-pressure air temperature control system, general technical systems and auxiliary equipment, characterized in that it is additionally equipped with a high-pressure thermostatting system for the space head part with an accelerating unit and a spacecraft, which includes a main pipeline and a receiver of compressed air connected to the gas storage equipment, the cylinders of which through the charging shield and the pipeline with fittings are connected to the main pipeline, and the shield for the delivery of the compressed air receiver is connected to the pipeline for supplying air to the space a head part equipped with a sampling device connected to an aerosol particle counter, a pneumatic shield for monitoring compressed air conditioning, means for remote control of temperature and air pressure parameters, as well as a standard hygrometer for controlling the humidity of the air supplied to the space head part, which is lowered through a pneumatic control box pressure, gas heater and air cooler installed in the ring cooling circuit of the refrigeration center, connected to a detachable connection bl A Single-booster and by a vertical conduit on board the launcher is connected with the head part space, wherein the air supply pipe into a space portion on the head portion from the heater to the block A gas-insulated rocket. 2. A ground launch complex for prelaunch preparation and launch of a launch vehicle with a space warhead, comprising a transport and installation unit, a launch structure, a single-slope gas deflector with a gas outlet, a launch system, a cable-filling mast, an upper cable-mast, lower cable-masts , service tower, service cabin, oxidizer and fuel refueling systems, fuel cooling system, gas storage equipment, refrigeration center, low-pressure air temperature control system, general technical systems and auxiliary equipment, characterized in that it is additionally equipped with a thermostatic control system for high-pressure air of the rocket compartments, including a main pipeline and a compressed air receiver connected to the gas storage equipment, consisting of cylinders, the charging shield of which is connected to the main through a pipeline with valves pipeline, and the dispensing shield is connected to the pipeline for supplying air to the launch vehicle with pressure and temperature sensors installed on it, which th through the inlet air shield, angle valve, filter, air control board, pressure reduction unit, gas heater and air cooler located in the cooling circuit of the refrigeration center, connected to the detachable connection of the rocket A block and through on-board communication connected to the instrument and inter-tank compartments of the block A and the inter-tank and tail compartments of the block And the launch vehicle, while the portion of the pipeline for supplying air to the launch vehicle from the gas heater to block A is thermally insulated. 3. A ground launch complex for prelaunch preparation and launch of a launch vehicle with a space head part, comprising a transport and installation unit, a launch structure, a single-slope gas deflector with a gas outlet channel, a launch system, a cable-filling mast, an upper cable-mast, lower cable-masts , service tower, service cabin, oxidizer and fuel refueling systems, fuel cooling system, gas storage equipment, refrigeration center, low-pressure air temperature control system, general technical systems and auxiliary equipment, characterized in that it is equipped with a high-pressure nitrogen thermostatting system of the rocket compartments, which includes a main pipeline and a high-pressure compressed nitrogen receiver connected to the gas storage equipment, the cylinder charging board through which is connected to the valve with a valve the main pipeline, and the delivery shield is connected to the pipeline for supplying high pressure nitrogen to the launch vehicle, with pressure and temperature sensors installed on it which, through the inlet air box with an angular valve, a filter, a pneumatic control box, a pressure reduction unit, a gas heater and a nitrogen cooler installed in the cooling circuit of the refrigeration center, is connected to the detachable connection of the launcher unit A and is connected via the on-board communication to the instrument and inter-tank compartments block A and the inter-tank and tail compartments of the block And the launch vehicle.