RU2318706C1 - Launching complex for pre-launch preparation and launching of launch vehicle with space nose cone (versions) - Google Patents

Abstract

FIELD: rocketry and space engineering.

SUBSTANCE: proposed launching complex of each design version contains transportation-and-assembly package 3, launch facility 4, launch system 5, umbilical mast 6, upper cable mast 7, service tower 8, service cabin 9, oxidizer filling system 10 and fuel filling system 11, fuel cooling system 12, gas storage equipment 13, cooling center 14 and low air pressure thermostatic control system 15 of nose cone 2. Launching complex is furnished with thermostatic control system including main pipeline 18, receiver 19 and bottles 20 of which are connected with main pipeline 18 through charging panel 21 and pipeline 22 with valves, all connected with gas storage equipment 13. Delivery panel 23 of receiver 19 is connected with air delivery pipeline 24 provided with sampler 25 connected with aerosol particles counter 26, pneumatic control panel 27, temperature and pressure remote control devices and hygrometer 30 according to first design version, high air pressure thermostatic control system is provided in nose cone 2. According to second design version, high air pressure thermostatic control system of launch vehicle compartment is provided. According to third design version, nitrogen high pressure thermostatic control system of launch vehicle compartments is provided.

EFFECT: improved reliability and efficiency of operation of launching complex.

4 cl, 4 dwg

Description

The invention relates to rocket and space technology, and more particularly to launch complexes of space launch vehicles. It can be used under any climatic and meteorological conditions at any time of the year or day to maintain in the compartments of the launch vehicle and the space head part during their prelaunch preparation the specified optimal temperature and humidity conditions and high purity and air conditioning, which have one of the decisive effects on the operability, reliability and efficiency of the equipment, instruments, assemblies, systems, on-board power supplies and other elements installed in thermostatically controlled compartments ah vehicle (LV) and the head part space (CHS), which increases the reliability and efficiency of the starting complex (IC), and HGC RN in general.

The invention can also be used to maintain the specified optimal temperature and humidity conditions in the LV compartments with inert gaseous nitrogen of high pressure, while simultaneously providing explosion and fire safety and high reliability of launches at the launch complex.

Known launch complex flyover type No. 39 of the space center. Kennedy (US) for prelaunch and launch of the Saturn-V rocket with the Apollon spacecraft, containing a launch pad, a wedge-shaped gas deflector, a gas outlet channel, a caterpillar conveyor, with the help of which a launch platform with a missile launcher installed on it is delivered Saturn-V-Apollo space system and a cable-filling tower, a receiver for compressed gases, a mobile service tower, on which equipment and low-pressure air and nitrogen supply lines with temperature and moisture control are located space rocket system, an oxidizer and fuel refueling system, and all other necessary equipment (see the Cosmodrome book. Under the general editorship of Prof. A.P. Volsky. M: Military Publishing House, 1977, p.95-100; 229 -232) [1].

The advantages of the famous launch complex include the fact that it is unique in equipment saturation and technical solution. The Apollo spacecraft launched from this launch complex, delivering American astronauts (astronauts) to the moon, as well as the Apollo spacecraft to meet the Soyuz spacecraft under the EPAS program.

The disadvantages of the launch complex can be attributed, firstly, to the fact that the mobile service tower with air and nitrogen supply lines is diverted to start-up, while thermostating is prematurely interrupted, and secondly, the degree of purity of the air supplied to the rocket with a hardener is not high enough (concentration contaminants aerosol particles of about 3 mg / m ³ or more), may lead to clogging of passage sections with sides pnevmokommunikatsii under certain conditions, as well as contamination of the working surface of the onboard equipment, instruments, Istemi et al., which reduces their reliability.

A known launch complex containing a starting device, a storage of liquid rocket fuels, facilities for refueling and draining components of liquid rocket fuels, a fire extinguishing system with a tank for industrial water, a system for structuring nitrogen-containing liquid rocket fuels, including storage tanks for the structure-forming agent of nitrogen-containing liquid rocket fuels, and a supply system builder in the zone of emergency strait of fuel, having collectors with spray guns builder, concentric located relatively starting device (Ru Patent 2094338, C1, B64G 5/00, 20.06.1994) [2].

The advantages of this launch complex include the safety of certain technological operations of prelaunch preparation and launch of a launch vehicle with a space warhead, and the following are disadvantages:

- insufficiency of special technological and general technical equipment for prelaunch preparation and launch of a booster rocket with KGCH, since using this launch complex you can solve only a part of the tasks, namely: carry out, for example, refueling the booster rocket 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 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 the effect achieved, the closest to the proposed invention is the launch complex for prelaunch preparation and launch of the Vostok launch vehicle with a space warhead 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 - Launch vehicle "East"].

This starting complex contains a transport and installation unit, a starting structure, a single-slope gas deflector with a gas outlet in the form of a tray, a starting system, a cable-filling mast, an upper cable-mast, a service truss (tower), a service cabin, an oxidizer and fuel filling system, a system fuel cooling, gas storage equipment, refrigeration center, low-pressure air temperature control system, general technical systems and auxiliary equipment.

The transport and installation unit is a lifting and transport unit on a railway track, equipped with a hydraulic system for hanging the unit on hydraulic supports and lifting the boom from the LV to a vertical position, as well as electrical equipment for actuating the actuators and monitoring their position. Movement of the transport and installation unit (TUA) between the technical and launch complexes is carried out by a diesel locomotive, and within the zero mark of the launch complex and in the assembly and test building, by an electric drive of the running trolleys.

The transport and installation unit consists of the following main units: platforms, booms, boom lifting hydraulic cylinders, wings, lower support, upper support, middle support, suspension mechanism, lapping mechanism, hydraulic system, electrical equipment and auxiliary equipment.

Ancillary equipment consists of a cargo model, platforms, stairs, etc.

The equipment that is part of the transport and installation unit (except for the cargo model) is located on the boom and platform of the transport and installation unit.

The launch facility is the main structure of the launch complex and is designed to accommodate units and systems that provide for the installation, preparation, refueling and launch of the launch vehicle, to accommodate the necessary test equipment and launch equipment, as well as technical systems that ensure their functioning.

The launch facility consists of two start-up and technological units monolithically interconnected. The first of these includes a launch pad - a "tetrahedron", on which a launch system is installed, a single-slope gas deflector with a gas outlet in the form of a tray, a room for a service cabin and premises for equipment that is connected with direct pH service and wiring communications.

In the central part of the block, an opening with a diameter of 15.0 m is provided for the removal of gases from propulsion systems of the LV to the gas duct.

At around 2 m, an annular platform is provided around the opening onto which the support ring of the launch system is mounted.

The technological unit is 4-storey, designed to accommodate technological equipment that provides refueling of the LV with fuel, oxidizer and other components, fire protection equipment, as well as technical systems (ventilation, water supply, electricity, automation, etc.). There are two entrances, four emergency exits, as well as emergency escape routes leading to shelters at the launch facility.

The launch system is intended for installation of the Vostok launch vehicle in it, verticalization and holding it in the set position during prelaunch preparation for launch and launch, as well as for placement of pneumatic-hydro-electric communications supplied to the launch vehicle. The starting system consists of:

- a support ring and four bases for attaching four support trusses and four load-bearing arrows, on which a launch vehicle with a space head is suspended and fixed; supporting farms have counterweights and sectors of the upper power belt;

- four guiding devices that fix the tail of the launch vehicle while it is on the launch system and at the initial moment of its movement at launch;

- two lower cable masts for supplying and connecting cable communications with electrical connectors to the carrier rocket, providing power to the carrier rocket before it is launched from ground sources;

- hydrobuffers of supporting farms;

- hydraulic drives.

On the starting system, RI with KGCH is suspended by the power nodes on the central block in the place of attachment of the side blocks using four power bearing arrows and four support trusses that are discarded under the action of counterweights after gaining traction. The kinetic energy of the supporting farms is extinguished with the help of hydrobuffers. The trusses and guides are mounted on a platform that provides verticalization and guidance along the azimuth of the LV with the KGCH using a hydraulic system located at the base of the supporting trusses.

The cable-filling mast (KZM), which is a mast-type metal structure, is designed to supply electrical cables, fueling, pneumatic, drainage and other communications to the upper LV blocks and to the KGCH, which are undocked immediately before the LV launch. At KZM are placed devices, equipment, cables, communications, as well as their means of protection. KZM consists of a fixed part (two bases) and a rotary part, which is a shaped structure, pivotally connected to the base, and can be rotated in a vertical plane at an angle of 40 °.

The extreme upper position of the KZM is defined as working, and the lowermost one is defined as the initial one.

The angle between the truss in the working position and the vertical leaves 17 °. The movement of the KZM from the working position to the initial one occurs under the influence of the counterweight. Braking and stopping the KZM in the initial position is carried out by two hydrobuffers installed on the basis of the KZM.

The KZM is raised to its working position by two hydraulic jacks. In the working position, the rotary part of the KZM is held either by two mechanical locks or by a special lock. The time of removal of the rotary part from the working position to its original position is not more than 12 s. KZM provides work at any time of the year or day under any meteorological conditions at an ambient temperature of minus 40 ° C to plus 50 ° C at a maximum wind speed in gust of up to 15 m / s.

Electric cables to the PH are laid along the upper cable mast.

The upper cable mast (VKM) includes a truss, a base, a VKM head, cable fastening and protection means, a hydraulic drive, a hydraulic buffer, electrical equipment and grounding equipment.

For servicing the LV and KGCH and docking the onboard communications connectors with the mating connectors of the ground systems (ie, for connecting ground-to-board communications), a service farm (tower) that has service platforms is brought to the LV with the KCH. Inside the service farms are located elevators that deliver maintenance personnel to the site.

To service the tail and bottom parts of the launch vehicle during prelaunch preparation, a retractable service cabin with its multi-tiered service platforms is used.

The service cabin includes a telescopic column, upper platforms, accessories, middle and lower platforms, a platform, a movement mechanism, a rail, vessels and drain pipes, a bridge, a hydraulic system, electrical equipment and a nitrogen installation.

Refueling facilities of the launch complex consist of a complex of stationary systems and mobile units and include:

- systems for refueling and feeding the pH with an oxidizing agent - liquid oxygen and liquid nitrogen;

- refueling system with kerosene T-1 PH from a railway refueling machine;

- pH filling systems with hydrogen peroxide from a railway tanker.

Before refueling, T-1 kerosene is cooled to the required temperature, for example, to minus 25 ° С, to increase its density, using a fuel cooling system for this.

The gas storage equipment provides prelaunch technological operations using air, nitrogen and helium and consists of storage tanks under a pressure of 40 MPa, pneumatic panels for charging and dispensing nitrogen and air, pneumatic panels for charging and dispensing helium, pneumatic panels for reducing pressure, pneumatic panels for monitoring the gas pressure consumers, pneumatic control panel for gas quality control and trunk pipelines with fittings.

The refrigeration center, including refrigerators, pumps, coolant tanks, pipelines with shut-off and control valves, control panels and other equipment, is used to ensure the normal operation of gas coolers (air and nitrogen) in thermostatic control systems of the LV and KGCh during their pre-launch preparation.

Thermostatic control system with low pressure air provides the specified temperature and humidity conditions of the LV and KGCh during their prelaunch preparation at the launch complex.

General technical systems include a water supply system, a circulating water supply system for cooling refrigeration machines and other units, a system of industrial drains, a gas analysis system for rooms, lightning protection devices, lightning rods, communication equipment and others.

The auxiliary equipment includes mobile and stationary systems of water, gas and foam fire extinguishing, etc.

This starting complex is selected by us as a prototype of the invention.

The advantages of the prototype include its high reliability and safety in operation, as well as the uniqueness of the launch system, which has no analogues in the world.

From this launch complex, with the help of the Vostok launch vehicle, the world's first spacecraft with a Soviet man on board was successfully launched into orbit; subsequently, spacecraft Luna-1 - Luna-3, artificial Earth satellites of the Cosmos, Meteor, Electron and others series were launched [3].

One of the disadvantages of the prototype is that the service farm (tower) is diverted from the booster rocket with KGCH for a considerable time before launch and at the same time the connections of thermostatic control systems for low-pressure air of the PH and KGCh are undocked. 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 temperature and humidity conditions in the LV and OGC compartments necessary for their normal functioning. The maintenance of the indicated modes due to preliminary bringing the temperature of the structure and air in the LV and KGCh compartments to higher values does not give the desired optimal results.

The technical result of the invention is to increase the reliability and efficiency of the 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 launch complex, launch vehicle and space head part; therefore, the resulting positive effect cannot be divided into parts associated with the launch complex, launch vehicle and space head part, since they are closely interconnected, inextricable from the point of view of achieving the objectives of the invention 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 launch complex will certainly affect the reliability of launches of launch vehicles with space warheads.

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

We also explain the following: the features of the claims should be indicated in statics, therefore, the use of the term "mobile service tower" contradicts the requirements of the preparation of the claims. For this reason, we use the term “service tower” instead of the term “mobile service tower”.

и ресивер сжатого воздуха, баллоны которого через щит зарядки и трубопровод с арматурой соединены с магистральным трубопроводом, а щит выдачи ресивера сжатого воздуха соединен с трубопроводом подачи воздуха в космическую головную часть, снабженным пробоотборным устройством, соединенным со счетчиком аэрозольных частиц, пневмощитом контроля кондиционности сжатого воздуха, средствами дистанционного контроля параметров - температуры и давления воздуха, а также штатным гигрометром для контроля влажности воздуха, подаваемого в космическую головную часть, который через пневмощит управления, блок понижения давления, нагреватель газов и охладитель воздуха, установленный в кольцевом контуре охлаждения холодильного центра, соединен с разъемным соединением блока А ракеты-носителя и посредством вертикального трубопровода на борту ракеты-носителя связан с космической головной частью, при этом трубопровод подачи воздуха в космическую головную часть на участке от нагревателя газов до блока А ракеты-носителя теплоизолирован.The indicated technical result is achieved due to the fact that the launch complex for prelaunch preparation and launch of the launch vehicle with a space warhead, containing the transport and installation unit, launch structure, launch system, cable-filling mast, upper cable-mast, 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 invention additionally provided with a temperature control system high pressure air space head part which includes the equipment associated with the storage gas main pipeline with a length L to the inner diameter D in the range

and a compressed air receiver, the cylinders of which are connected to the main pipeline through the charging shield and the pipeline with valves, and the compressed air receiver shield is connected to the air supply pipe to the space head part, equipped with a sampling device connected to the aerosol particle counter, and a compressed air conditioning control board , by means of remote control of parameters - temperature and air pressure, as well as a standard hygrometer to control the humidity of the air supplied to the space the head part, which through a pneumatic control board, a pressure reduction unit, a gas heater and an air cooler installed in the ring cooling circuit of the refrigeration center is connected to the detachable connection of the launch vehicle unit A and is connected to the space head part via a vertical pipeline on board the launch vehicle while the pipeline for supplying air to the space head in the area from the gas heater to the block And the launch vehicle is thermally insulated.

и ресивер сжатого воздуха, состоящий из баллонов, щит зарядки которых посредством трубопровода с арматурой связан с магистральным трубопроводом, а щит выдачи соединен с трубопроводом подачи воздуха в ракету-носитель с установленными на нем датчиками давлений и температур, который через входной пневмощит, фильтр, пневмощит управления, блок понижения давления, нагреватель газов и охладитель воздуха, расположенный в контуре охлаждения холодильного центра, соединен с разъемным соединением блока А ракеты-носителя и посредством бортовой коммуникации связан с приборным и межбаковым отсеками блока А и межбаковым и хвостовым отсеками блока И ракеты-носителя, при этом участок трубопровода подачи воздуха в ракету-носитель от нагревателя газов до блока А теплоизолирован.The indicated technical result is also achieved due to the fact that the launch complex for prelaunch preparation and launch of the launch vehicle with a space head includes a transport and installation unit, launch structure, launch system, cable-filling mast, upper cable-mast, service tower, cab services, oxidizer and fuel refueling systems, fuel cooling system, gas storage equipment, refrigeration center, low-pressure air temperature control system, general technical with The systems and auxiliary equipment according to the invention are additionally equipped with a high-pressure thermostatting system of the rocket compartments, which includes a main pipeline connected to the gas storage equipment with a ratio of length L to internal diameter D within

and a receiver of compressed air, consisting of cylinders, the charging shield of which is connected via a pipeline with fittings to the main pipeline, and the delivery panel is connected to the pipeline for supplying air to the launch vehicle with pressure and temperature sensors installed on it, which through the input air supply, filter, air support control unit, pressure reducing unit, gas heater and air cooler located in the cooling circuit of the refrigeration center, is connected to the detachable connection of the block And the launch vehicle and through the onboard munikatsii associated with instrumentation and intertank compartments intertank block A and block and caudal compartments and the carrier rocket, wherein the portion of the air supply conduit to the booster from the gases to the heater assembly A thermally insulated.

и ресивер сжатого азота высокого давления, щит зарядки баллонов которого через трубопровод с арматурой связан с магистральным трубопроводом, а щит выдачи соединен с трубопроводом подачи азота высокого давления в ракету-носитель с установленными на нем датчиками давлений и температур, который через входной пневмощит с угловым вентилем, фильтр, пневмощит управления, блок понижения давления, нагреватель газов и охладитель азота, установленный в контуре охлаждения холодильного центра, соединен с разъемным соединением блока А ракеты-носителя и посредством бортовой коммуникации связан с приборным и межбаковым отсеками блока А и межбаковым и хвостовым отсеками блока И ракеты-носителяThe indicated technical result is also achieved due to the fact that the launch complex for prelaunch preparation and launch of the launch vehicle with a space head part, containing the transport and installation unit, launch structure, launch system, cable-filling mast, upper cable-mast, service tower, service cab, oxidizer and fuel refueling systems, fuel cooling system, gas storage equipment, refrigeration center, low-pressure air thermostat system, general technical systems and auxiliary equipment according to the invention is equipped with a high-pressure nitrogen thermostatting system of the rocket compartments, which includes a main pipeline connected to the gas storage equipment with a ratio of length L to internal diameter D in the range

and a receiver of high-pressure compressed nitrogen, the shield of charging cylinders of which through the pipeline with valves is connected to the main pipeline, and the shield of delivery 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 pneumatic shield with an angle valve filter, pneumatic control box, pressure reducing unit, gas heater and nitrogen cooler installed in the cooling circuit of the refrigeration center, connected to a detachable connection of the rocket-carrying unit A la and by means of an onboard communications and instrumentation associated with intertank compartments intertank block A and block and caudal compartments and the carrier rocket

The essence of the invention is illustrated by drawings.

Figure 1, 2, 3 and 4 presents embodiments of the launch complex for prelaunch preparation and launch of the launch vehicle 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 launch complex for prelaunch preparation and launch of a launch vehicle (LV) with a space warhead (KGCH) at a point in time after installing the LV using the transport and installation unit on the launch system, bringing the maintenance tower, lifting and docking KGCH with pH.

In figure 1, the positions that could not be shown are enclosed in squares.

Figure 2 shows a diagram of a temperature control system for high-pressure air of the 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 launch complex for prelaunch preparation and launch of the launch vehicle with a space head part (Fig. 1) contains a launch vehicle 1 (with conical side blocks), a space head part 2 (including a head fairing, a spacecraft and, if necessary, a Frigate booster ), the transport and installation unit 3, the starting structure 4, the starting system 5, the cable-filling mast 6, the upper cable-mast 7, the service tower 8, the service cab 9, the fueling system oxidizer 10 and fuel 11, the fuel cooling system 12 th, 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.

и ресивер сжатого воздуха 19, баллоны 20 которого через щит зарядки 21 и трубопровод 22 с арматурой соединены с магистральным трубопроводом 18, а щит выдачи 23 ресивера сжатого воздуха 19 соединен с трубопроводом подачи воздуха 24 в космическую головную часть 2, снабженным пробоотборным устройством 25, соединенным со счетчиком 26 аэрозольных частиц, пневмощитом 27 контроля кондиционности сжатого воздуха, средствами дистанционного контроля параметров - температуры 28 и давления 29 воздуха, а также штатным гигрометром 30 для контроля влажности воздуха, подаваемого в космическую головную часть 2, который через пневмощит управления 31, блок понижения давления 32, нагреватель 33 газов и охладитель 34 воздуха, установленный в кольцевом контуре 35 охлаждения холодильного центра 14, соединен с разъемным соединением 36 блока А ракеты-носителя 1 и посредством вертикального трубопровода (на фиг.1 вертикальный трубопровод условно не показан) на борту ракеты-носителя 1 связан с космической головной частью 2, при этом трубопровод подачи воздуха 24 в космическую головную часть 2 на участке от нагревателя 33 газов до блока А ракеты-носителя 1 теплоизолирован. Пробоотборное устройство 25 включает в себя связанный с зондом, установленным в трубопроводе подачи воздуха 24, пробоотборный трубопровод 37, запорный вентиль 38, дроссель 39, коническую камеру 40 и пробозаборный патрубок 41, связанный с оптико-электронным аэрозольным счетчиком ОЭАС 26.The launch complex for prelaunch preparation and launch of the launch vehicle 1 with the space head part 2 is additionally equipped with a high-pressure thermostatting system for the space head part 2 (Fig. 2), which includes the main pipeline 18 connected to the gas storage equipment 13 with a length ratio L to the inner diameter D in the range

and a compressed air receiver 19, the cylinders 20 of which are connected to the main pipe 18 through a charging shield 21 and a pipe 22 with fittings, and a delivery board 23 of the compressed air receiver 19 is connected to the air supply pipe 24 to the space head part 2 equipped with a sampling device 25 connected with a counter 26 of aerosol particles, a pneumatic shield 27 for monitoring the conditionality of compressed air, means for remote control of parameters - temperature 28 and air pressure 29, as well as a standard hygrometer 30 for monitoring air humidity, supplied to the space warhead 2, which through a pneumatic control panel 31, a pressure reduction unit 32, a gas heater 33 and an air cooler 34 installed in the cooling ring ring 35 of the refrigeration center 14 is connected to the detachable connection 36 of the launch vehicle unit 1 and by means of a vertical the pipeline (in Fig. 1, a vertical pipeline is not conventionally shown) on board the launch vehicle 1 is connected to the space head part 2, while the pipeline for supplying air 24 to the space head part 2 on the site from the heater 33 gas in block A to the launcher 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 pressure reducing unit 32, an electro-pneumatic valve 47, a butterfly valve 49, a gas pressure reducer 50, reducing the pressure from 40 MPa to 6 MPa, a safety valve 51, a check valve 48, a butterfly valve 52, an angle valve 42 are located.

Option 2

The launch complex for prelaunch preparation and launch of the launch vehicle with a space head part (Fig. 1) comprises a launch vehicle 1 (with conical side blocks), a space head part 2, a transport and installation unit 3, a launch structure 4, a launch system 5 , cable-filling mast 6, upper cable-mast 7, service tower 8, service cabin 9, refueling systems 10 and fuel 11, fuel cooling system 12, gas storage equipment 13, refrigeration center 14, low temperature air conditioning system pressure 15 PH 1, general technical systems 16 and auxiliary equipment 17.

, что находится в диапазоне (1,2-2,5)·10⁵, и ресивер 19 сжатого воздуха с баллонами (емкость каждого баллона 0,4 м³). Щит зарядки 21 баллонов 20 посредством трубопровода 22 с арматурой связан с магистральным трубопроводом 18. Щит выдачи 23 соединен с трубопроводом 24 подачи воздуха в ракету-носитель 1, на котором установлены датчики давлений 25 и температур 26.The launch complex for prelaunch preparation and launch of the launch vehicle with a space warhead (Figs. 1, 3) is additionally equipped with a high-pressure thermostatting system for the PH 1 compartments, including the main pipeline 18 connected to the gas storage equipment 13 with a length ratio of L = 14000 m to inner diameter D = 0.08 m equal to

That is in the range (1.2-2.5) x 10 ⁵ and the receiver 19, compressed air cylinders (each cylinder capacity of 0.4 m ^3). 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 box 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 includes an electro-pneumatic valve 38, a butterfly valve 40, a gas reducer 41, a pressure gauge valve 36, safety valve 42, pressure switch 37, check valve 39 and throttle 43.

Option 3

The launch complex for prelaunch preparation and launch of the 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 launch system 5, a cable-filling mast 6, upper cable mast 7, service tower 8, service cabin 9, refueling systems 10 and fuel 11, fuel cooling system 12, gas storage equipment 13, refrigeration center 14, low-pressure thermostat system 15 PH 1, general technical Istemi 16 and accessory 17.

, что находится в диапазоне (1...4)·10⁵, и ресивер 19 сжатого азота высокого давления (40 МПа).The launch complex for prelaunch preparation and launch of the launch vehicle with a space warhead (Figs. 1, 4) is equipped with a high-pressure nitrogen thermostat system of the launch vehicle compartments 1, which includes a main pipeline 18 connected to the gas storage equipment 13 with a length ratio L = 14000 m to the inner diameter D = 0.05 m equal to

that is in the range (1 ... 4) · 10 ⁵ , and a receiver 19 of high-pressure compressed nitrogen (40 MPa).

The shield 21 for charging cylinders 20 of the receiver 19 of high-pressure compressed nitrogen through a pipe 22 with fittings 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 carrier rocket 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.

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

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

ASUTO 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 ASUTO 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 present invention (taking into account all its variants) 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 Earth-to-board communications. 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 space head part is docked to the launch vehicle, checked and, using the turntable and hydraulic jacks of the suspensions, the launch vehicle is verticalized with a KGCH.

Next, 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, cable-filling mast, 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 air supply with the necessary parameters (pressure, flow, temperature), air filters that purify atmospheric air from mechanical impurities, dust particles and corrosive agents with a filtration purity of at least 20 microns, refrigeration machines, 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 20 to 50 ° C is 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 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 refueling column is installed at the zero mark of the launch facility, and the communication for venting vapors from the drain-safety valve (WPC) of the launch vehicle unit A is located 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 the onboard cylinders of the booster rocket with OGC, pressurize the oxidizer and fuel tanks before start-up, thermostatic control of the high-pressure air OGC (option 1) and the PH (option 2), and thermostatically control the high-pressure nitrogen of the rocket 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 valves, 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.

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 launch complex for prelaunch preparation and launch of a launch vehicle with a space warhead allows:

- carry out (unlike analogues and prototype) thermostatic control of high-pressure air of the space head part (option 1) and the rocket compartments (option 2) almost until the start-up (the thermostatic control system of high-pressure air KGCh shut off by the command "Earth-board" for about 42 s before the “Lift Contact” (“KP”) command, and the high-temperature thermostatic control system of the rocket compartments is turned off by the “Boost” command for about 2.5 minutes before the “KP” command), which increases reliability and efficiency equipment, p PSI, assemblies and systems installed on board the vehicle and AU as at the launch complex, and in space;

- maintain the specified optimal temperature and humidity conditions in the rocket compartments with inert gaseous nitrogen of high pressure, 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 launches at the launch 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 / cm2, which is an order of magnitude better than compared to 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. In this case, the purity of thermostatic air was compared with the data of the US Federal Standard (FED.STD-209E) and amounted to 250 particles in one liter, the particle size was 0.5 μm, and according to the US Federal Standard 3530 particles in one liter, i.e., according to the invention, air supplied to the KGC is 14 times cleaner and has an ultrahigh 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 invention 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.

The proposed technical solutions (options 1, 2, 3) meet the criteria of the invention "positive effect" and "technical level".

Thus, the set of inextricably interconnected essential features set forth in the claims aimed at achieving a common goal, allows to obtain a significant positive effect, 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 invention will be used in full at the launch complex of the Soyuz-ST launch vehicle in the Guiana Space Center. It can also be used 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 - US launch complexes. Launch complex number 39 of the Space Center. Kennedy (Fig. 3.4) - an 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 - The launch complex of the Vostok launch vehicle - prototype.

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

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; p.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, 5 B63B 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 - analogue.

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. 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 launch system, a cable-filling mast, an upper cable-mast, a service tower, a service cabin, an oxidizer and fuel refueling system , fuel cooling system, gas storage equipment, refrigeration center, low-pressure air temperature control system, general technical systems and auxiliary equipment, characterized in that it It is reliably equipped with a high-pressure thermostatting system for the space head part, which includes a main pipeline connected to the gas storage equipment with a ratio of length L to inner diameter D in the range

and a compressed air receiver, the cylinders of which are connected to the main pipeline through the charging shield and the pipeline with valves, and the compressed air receiver shield is connected to the air supply pipe to the space head part, equipped with a sampling device connected to the aerosol particle counter, and a compressed air conditioning control board , by means of remote control of parameters - temperature and air pressure, as well as a standard hygrometer to control the humidity of the air supplied to the space the head part, which through a pneumatic control board, a pressure reduction unit, a gas heater and an air cooler installed in the ring cooling circuit of the refrigeration center is connected to the detachable connection of the launch vehicle unit A and is connected to the space head part via a vertical pipeline on board the launch vehicle while the pipeline for supplying air to the space head in the area from the gas heater to the block And the launch vehicle is thermally insulated. 2. 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 launch system, a cable-filling mast, an upper cable-mast, a service tower, a service cabin, an oxidizer and fuel refueling system , fuel cooling system, gas storage equipment, refrigeration center, low-pressure air temperature control system, general technical systems and auxiliary equipment, characterized in that it It is reliably equipped with a thermostatic control system for high-pressure air of the rocket compartments, which includes a main pipeline connected with the gas storage equipment with a ratio of length L to internal diameter D within

and a receiver of compressed air, consisting of cylinders, the charging shield of which is connected via a pipeline with fittings to the main pipeline, and the delivery panel is connected to the pipeline for supplying air to the launch vehicle with pressure and temperature sensors installed on it, which through the input air supply, filter, air support control unit, pressure reducing unit, gas heater and air cooler located in the cooling circuit of the refrigeration center, is connected to the detachable connection of the block And the launch vehicle and through the onboard munikatsii associated with instrumentation and intertank compartments intertank block A and block and caudal compartments and the carrier rocket, wherein the portion of the air supply conduit to the booster from the gases to the heater assembly A thermally insulated. 3. 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 launch system, a cable-filling mast, an upper cable-mast, a service tower, a service cabin, an oxidizer and fuel refueling system , fuel cooling system, gas storage equipment, refrigeration center, thermostatic control system of low pressure air, general technical systems and auxiliary equipment, characterized in that it is equipped with It is equipped with a high-pressure nitrogen thermostat system for the launch vehicle compartments, which includes a main pipeline connected to the gas storage equipment with a ratio of length L to internal diameter D in the range

and a receiver of high-pressure compressed nitrogen, the shield of charging cylinders of which through a pipeline with valves is connected to the main pipeline, and the shield of delivery 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 pneumatic input port a valve, a filter, a pneumatic control board, a pressure reduction unit, a gas heater and a nitrogen cooler installed in the cooling circuit of the refrigeration center, are connected to the detachable connection of the rocket-carrying unit A spruce and through on-board communication is connected with the instrument and inter-tank compartments of block A and the inter-tank and tail compartments of block And of the launch vehicle.

Images