RU2270792C1 - Launch complex for preparation and launching of launch vehicles with spacecraft - Google Patents

Abstract

FIELD: ground facilities for spacecraft.

SUBSTANCE: proposed launch complex includes launch control center, transportation and mounting package, launch structure, launch system with launch deflector, service tower and searchlight tower. Launch complex is provided with oxidizer and fuel filling systems, compressor station, gas supply systems, refrigerating center and other systems. Launch complex is provided with system for filling and replenishing onboard sphere balloons mounted in cryogenic tanks with high-purity compressed helium. System is provided with helium and nitrogen receivers connected with compressor station and equipped with required fittings. Each helium receiver is connected with onboard sphere balloons of launch vehicle and spacecraft by means of pipe lines equipped with required fittings. Joint includes gas reducer, cryostats, heater, collector and vertical pipe line. Cryostats are connected with liquid nitrogen storage reservoir. Nitrogen receiver is connected with each cryostats by means of pipe line through gas reducer and heater.

EFFECT: extended functional capabilities; enhanced efficiency and reliability.

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Description

The invention relates to rocket and space technology, and more particularly, to launch complexes of space launch vehicles, and can be used to expand technological capabilities, ensure high efficiency and reliability of the launch complex, launch vehicles and spacecraft by providing refueling and refueling with compressed high-purity helium on-board charballs installed in cryogenic tanks of launch vehicles and spacecraft.

Known launch complexes 36A, 36B for the preparation and launch of the Atlas-Centaur launcher (US), containing a launch control center, transport and installation equipment, a flyover type launch structure, a launch system in the form of a rotary launch table with a trough gas reflector, a service tower , refueling systems with fuel components and compressed gases, a compressor station, onboard balloon batteries with helium for pressurizing the fuel tank and purging the propulsion system of the first stage, placed in a casing with liquid nitrogen, to which merges into the ground system just before the launch of the launch vehicle, and all other necessary equipment (see the book "Cosmodrome" under the general editorship of Professor A.P. Volsky. M: Military Publishing House, 1977, p. 81, 141) [8] .

The advantages of the famous launch complex include the possibility of successfully launching a space launch vehicle, and the disadvantages are the following:

- the difficulty of ensuring high reliability and operational efficiency of the launch complex and launch vehicle due to the complexity of the assembly and installation of the launch vehicle on the launch system by the service tower mechanisms;

- the forced transportation of the ballast casing into space reduces the efficiency of the launch vehicle and cannot be considered technically and economically justified;

- insufficiently high helium purity in on-board balloon batteries (pollution concentration according to experimental data is about 3-7 mg / m) leads to clogging of the pneumatic communication cross-sections [24], fuel pollution and deterioration of characteristics and disruption of the propulsion system and, ultimately, to failure to fulfill the tasks assigned to the space rocket system - the launch vehicle and the spacecraft.

Famous launch complex number 39 of the Space Center. Kennedy, designed for the preparation and launch of the Saturn-V launch vehicle with the Apollon spacecraft, containing a launch control center, a tracked conveyor, a flyover type launch pad with a launch pad and a wedge-shaped gas reflector, a service tower, a launch platform with an installation on it space rocket system and cable-filling tower, refueling systems with cryogenic fuel components, refrigeration center, compressor station, compressed gas refueling systems, air conditioning systems for odachi air and nitrogen at a controlled temperature and humidity to the rocket-space system, four on-board container (volume of 0.88 m ³ each) with helium to pressurize the fuel tank installed inside of the oxygen tank of the first stage of the launch vehicle "Saturn-V» and other necessary equipment [8, p. 82; 141; 177-179; 200-201].

The advantages of this starting complex can be attributed to its uniqueness both in terms of its dimensions, and in terms of equipment saturation and technical solution, and the following are the disadvantages:

- the difficulty of ensuring high reliability and efficiency of work at the launch complex due to the complexity, the long preparation time (14 days) and the complexity of operations;

- low purity of helium in the onboard cylinders (the concentration of pollution according to experimental data is 5-7 mg / m ³ ), the possibility of clogging of the on-board pneumocommunication [24] and fuel pollution in the tank, which can lead to a change in the operating mode of the propulsion system with undesirable consequences;

- when refueling airborne cylinders cooled to cryogenic temperatures with high-pressure compressed helium, heat shock may occur that can destroy the walls of airborne cylinders and cause a cryo-shock (like a hydro-shock) in an oxygen tank, which will lead to failure of the launch vehicle and the spacecraft.

These shortcomings do not allow to use the launch complex No. 39 neither for the prototype, nor for improvement.

A further analysis of patents and scientific and technical literature [1-26, etc.] showed that in terms of technical nature and the effect achieved, the closest to the invention is the launch complex for the preparation and launch of launch vehicles with spacecraft, described in the book "Cosmodrome" [8].

This launch complex contains: a launch control center, a transport and installation unit, a launch facility, a launch system with a gas reflector, a service tower, a searchlight mast with television and movie cameras installed on it, and installations in the refueling system of the oxidizer (liquid oxygen) and fuel, compressor station, gas supply systems, refrigeration center, air systems for ensuring the temperature and humidity conditions of the compartments and blocks of the launch vehicle and spacecraft, guidance system, electric power lovoe equipment, control and test equipment, test-starting equipment, technical systems and accessories.

Technical systems include: a water supply system, a reverse water supply system for cooling refrigeration machines and other units, an industrial waste water system, a fire protection system, ventilation systems, a heating system, a gas analysis system for rooms, lightning protection devices and lightning rods (divertors) and communication equipment.

Auxiliary equipment includes: mobile and stationary systems of water, gas and foam fire extinguishing, systems of neutralization of fuel components and others.

This starting complex most fully meets modern requirements and we have chosen as a prototype of the invention.

The advantages of the prototype include the possibility of ensuring the safety of work during the preparation and launch of launch vehicles with spacecraft, and the disadvantages are the inability to ensure refueling and recharge of high-purity compressed helium on-board balloons installed in cryogenic tanks of the upper stage of the booster head unit of the launch vehicle and spacecraft.

The technical result of the invention is the expansion of technological capabilities, ensuring high efficiency and reliability of the launch complex, launch vehicle and spacecraft.

Let us briefly describe the technical result.

One of the most important technological operations for prelaunching a launch vehicle and a spacecraft at the launch complex is to refuel with high-purity compressed helium airborne charballs installed inside the cryogenic tanks of the space-rocket system filled with liquid fuel cryocomponents.

On board the space rocket system, compressed helium is used to:

- pressurization of cryogenic tanks in order to ensure normal cavitation-free operation of turbopump units;

- purging tanks of liquid hydrogen (if any);

- sparging (mixing) of liquid oxygen in the cryogenic tanks of the space rocket system in order to prevent temperature separation, which negatively affects the operation of propulsion systems, etc.

To carry out these works, it is necessary to expand the technological capabilities of both the space-rocket system and the launch complex, providing the latter with a refueling and recharge system with high-purity compressed helium on-board balloons, which allows cool compressed helium to cryogenic temperatures and clean it of mechanical impurities, moisture, compressor oil , carbon dioxide and other undesirable impurities, the presence of which in refueling compressed helium is unacceptable. Ensuring high efficiency and reliability of the space-rocket system is possible only with the failure-free operation of the launch complex, launch vehicle and spacecraft, therefore, the resulting positive effect cannot be divided into parts associated with the launch complex, launch vehicle and spacecraft, since they closely interconnected, inextricable from the point of view of achieving the objectives of the invention, which does not contradict the requirements of the unity of the invention.

The specified technical result is achieved due to the fact that the launch complex for the preparation and launch of launch vehicles with spacecraft, containing a launch control center, a transport and installation unit, a launch facility, a launch system with a gas reflector, a service tower, a searchlight mast with a television set mounted on it and movie cameras located in the facilities of the oxidizer (liquid oxygen) and fuel refueling system, compressor station, gas supply systems, refrigeration center, air conditioning systems the temperature and humidity regimes of the compartments and blocks of the launch vehicle and the spacecraft, the guidance system, electric power equipment, test equipment, test and start-up equipment, technical systems and auxiliary equipment, according to the invention is equipped with a high-purity compressed helium refueling and recharge system for onboard balloons installed in the cryogenic tanks of the booster, for example the third, stage of the head block of the launch vehicle and the spacecraft, consisting of a helium receiver press station, each of which is connected via valves to a valve via a gas reducer, cryostats connected to a liquid nitrogen storage, a heater, a collector and a vertical pipeline with airborne charballoons of a launch vehicle and spacecraft, as well as a nitrogen receiver with valves, which using a pipeline through a gas reducer and a heater connected to each of the cryostats.

The authors of the invention are not aware of similar technical solutions, and therefore, according to the authors, the claimed combination of inextricably linked essential features set forth in the claims meets the criteria of the invention “significant differences” and “novelty”.

The invention is illustrated by drawings, where Fig. 1 shows a structural diagram of a launch complex for preparing and launching launch vehicles with spacecraft at the time after installation of a launch vehicle with a spacecraft on the launch system and bringing the service unit (tower) to them, in Fig. .2 - diagram of a high-purity compressed helium refueling and feeding system for onboard charballs installed in cryogenic tanks of the upper stage upper stage launcher cryogenic tanks and spacecraft (on-board charballs in spacecraft conditionally not shown), and Fig. 3 is an exemplary graph of cooling gaseous helium to the required refueling and recharge temperatures.

The launch complex (figure 1) contains a launch vehicle 1 with side blocks (conical shape), a spacecraft 2, a launch control center 3, a transport and installation unit 4, a launch facility 5, a launch system 6 with a gas reflector 7, a service tower 8, floodlight mast 9 with television and movie cameras installed on it, located in the facilities of the oxidizer (liquid oxygen) refueling system 10 and fuel 11, compressor station 12, gas supply systems 13, refrigeration center 14, air temperature and humidity systems Modes compartments 15 and booster units 1 and 2 of the spacecraft, the guidance system 16, electric power equipment 17, control the test apparatus 18, test equipment 19, the starter-technical systems 20 and accessory 21.

The launch complex for the preparation and launch of launch vehicles with spacecraft is equipped with a high-purity compressed helium fueling and recharging system 22 of high-purity side balloons 23 (Fig. 1) installed in the cryogenic tanks 24 of the upper stage booster stage 1 of the launch vehicle 1 and spacecraft 2.

The system for refueling and recharging with compressed helium 22 consists (Fig. 2) of helium receivers 25, 26 connected to the compressor station, each of which, through pipelines 27, 28 with pneumatic valves, including angle valves 29, 30, a throttle 31, electro-pneumatic valves 32, 33 and check valves 34, 35, connected through a gas reducer 36, cryostats 37, 38 connected to a liquid nitrogen storage 39, a heater 40 with three coils, a manifold 41 and a vertical pipe 42 (FIG. 1) with onboard charballoons 23. The filling system and compressed helium recharge 22 (figure 1) also consists e from a nitrogen receiver 43 with shutoff valves 44 (FIG. 2), which is connected via a pipeline 45 through a gas reducer 46 and a heater 40 to each of the cryostats 37, 38.

The liquid nitrogen storage 39 is equipped with means for supplying liquid nitrogen with a temperature of 77K (-196 ° C) and through pipelines 47, 48 with valves 49, 50 is connected to cryostats 37, 38 (Fig. 2).

The preparation and launch of the launch vehicle 1 with the spacecraft 2 at the proposed launch complex is carried out from the launch control center 3, designed to control all prelaunch and launch operations, according to the launch vehicle launch sequence diagram, which shows a table-graphical representation of the sequence of preparation operations to launch and launch a launch vehicle with a spacecraft indicating the time spent on each operation.

On the technical complex of launch vehicles (according to the old terminology of the technical position), the fully assembled and tested (in horizontal position) launch vehicle 1 with the help of cranes and traverses is transferred to the transport and installation unit 4, after which it is carefully assembled, tested and refueled (at the filling station) technical complex stations) with fuel components and compressed gases, the spacecraft 2 is docked to the launch vehicle 1. After checking the correct docking and cable connections of the launch vehicle 1 with the spacecraft atom 2 they are fixed on the transport and installation unit 4 using grippers and attachment points and transported from the technical complex to the launch complex. Next, the launch vehicle 1 with the spacecraft 2 is raised to a vertical position and installed on the launch system 6, verticalization is carried out, after which the transport and installation unit 4 is diverted from the launch complex to a safe place.

For servicing the space-rocket system - the launch vehicle 1 and spacecraft 2 and for connecting the airborne communications connectors to the communications communications connectors of the ground systems (that is, for connecting Earth-to-board communications) to the rocket-space system, a service tower 8, which has stationary, retractable and rotary service platforms connected by high-speed elevators (not shown conditionally).

For thermostating of the launch vehicle 1 and spacecraft 2 from the moment of their installation on the launch system 6, air systems for providing temperature and humidity conditions of 15 compartments and units of the launch vehicle 1 and spacecraft 2, including fans for supplying air with the required parameters (pressure, flow, temperature), filters that clean the air from dust and mechanical impurities associated with the refrigeration center 14 air coolers that cool the air to a given temperature and precipitate water Agu from the air, and electric heaters that provide air heating to the required temperature.

Before refueling the launch vehicle 1 with liquid propellant components, refueling systems 10, 11 are alerted, the oxidizer and fuel in the refueling tanks are cooled to a certain temperature and thermostated.

To increase the reliability of the pumps and to prevent cavitation, gas pads of refueling containers are pressurized with gas from gas supply systems 13 to optimal pressures.

The carrier rocket 1 dock fueling communications. Before refueling the launch vehicle 1 with cryogenic fuel components, ground-based refueling communications, on-board communications and cryogenic tanks 24 of the launch vehicle 1 with the on-board charballs 23 installed in them are cooled with cryogenic liquid, for example liquid oxygen, to the required refueling temperature with a minimum flow rate that excludes thermal shock.

The vapors generated during cooling are discharged through the drainage safety valve (DPK) of the launch vehicle 1 into the atmosphere.

After cooling, the cryogenic tanks 24 are charged with supercooled or boiling liquid oxygen with a temperature of 90K (-183 ° C).

Non-cryogenic tanks are refueled like chilled kerosene.

Oxygen-kerosene fuel is most mastered in rocket and space technology, inexpensive to manufacture, and convenient to operate.

Cooling and refueling with deeply cooled oxygen of thermally insulated cryogenic tanks of the spacecraft 2, in which airborne charballoons are installed, at the technical complex carry out the same cooling and refueling of cryogenic tanks 24 of the launch vehicle 1 at the launch complex.

Before refueling on-board charballs 23 (Fig. 1), compressed helium must undergo special training, including cleaning from mechanical impurities, moisture, compressor oil, carbon dioxide and other undesirable impurities by freezing them in cryostats and retaining fine filters installed in cryostats on the filter elements.

The presence of these impurities in compressed helium is unacceptable, since it leads to clogging of the cross-sections of the on-board pneumocommunication of the space-rocket system, contamination of the cryogenic fuel components during their sparging in flight and pressurization of cryogenic tanks and, as a result, to a deterioration in the characteristics and operating modes of rocket propulsion carrier 1 and spacecraft 2.

Previously, cryostats 37, 38 (Fig. 2) are filled through pipelines 47, 48 with valves 49, 50 with liquid nitrogen with a temperature of 77K (-196 ° C) from the liquid nitrogen storage 39. Then, compressed helium from helium receivers 25, 26 is fed into cryostats 37, 38, where it, being cooled in liquid nitrogen to a temperature that ensures freezing of harmful impurities, is purified, and the impurities are retained on the filter elements of the cryostat.

The compressed helium refueling and recharging system for airborne charballoons operates in two modes. In the first mode I (Fig. 3), cooled to cryogenic temperatures and purified compressed helium through pipelines 41, 42 with valves 32, 33, 34, 35 (when the electric heater 40 is not turned on), they are fed into the onboard charballoons 23 to rinse them in order to clean them from possible contaminants, after which the side charballs 23 are filled with helium to a predetermined working pressure (for example, not more than 22 MPa).

In this case, the pressure and temperature of helium gas are monitored at the inlet and outlet of the cryostats 37, 38 (Fig. 2) and at the inlet of the launch vehicle 1 (Fig. 1). When the pressure difference at the inlet and outlet of the cryostat is more than 1 MPa, one cryostat is switched off and the other is connected.

In the second mode II (Fig. 3), the compressed and cooled helium purified in a cryostat enters the electric heater 40 for subsequent heating to the required temperature at the inlet of the launch vehicle 1 (for example, from minus 40 ° C to plus 50 ° C).

At the end of the refueling and replenishment with compressed helium of the onboard charballoons, they issue a command to close the electro-pneumatic valves 32, 33 and turn off the cryostats 37, 38 for frostbite and regeneration.

Refueling on-board cylinders with nitrogen and air (if necessary) is done from gas supply systems 13, which are receiver tanks with high-pressure cylinders, necessary control and shut-off valves, as well as a system of gas pressure reducers to reduce the pressure of compressed gases supplied to consumers.

In the process of pre-launch preparation using gas supply systems 13, purges are carried out for highways, tail compartments, propulsion systems, pressurization of the launch vehicle tanks 1, etc.

Compressor station 12 operates in non-technological time (that is, before the start of pre-launch work), ensuring that the cylinders of the gas supply systems 13 are filled with conditioned (clean and dried) compressed gases (air, nitrogen, helium) with a pressure of up to 40 MPa with a dew point of no higher than minus 55 ° C.

The refrigeration center 14, including refrigerators, brine tanks for the coolant, pumps and other equipment, works when thermostatting (cooling) the fuel components in refueling systems 10, 11, cooling thermostatic air, nitrogen, etc.

The guidance system 16 as part of the launch system 6 is to give the rocket and space system 1, 2 located on the launch system 6, a strictly vertical position using the supports or jacks of the launch system 6 and azimuthal guidance - combining the stabilization plane of the space rocket system 1, 2 with the launch plane by turning the rocket and space system in the horizontal plane using the turntable of the launch system 6.

To guidance the space-rocket system 1, 2 perform geodetic preparation of the launch and determine the coordinates of the launch system 6 and reference directions. Then include electric power equipment 17 for powering the launch vehicle 1, spacecraft 2, electric motors of the fueling system pumps 10, 11, equipment and systems of remote and automatic control, as well as other systems and units with special currents and direct current voltage of 27-30 V.

Using test equipment 18 carry out test tests of devices, assemblies and systems of the launch vehicle 1, as well as docked launch vehicle 1 and spacecraft 2. Next, using the test and launch equipment 19, pre-launch checks of the equipment and systems of the rocket- carrier 1 and spacecraft 2, as well as the issuance of commands to launch the rocket and space system 1, 2.

In accordance with the training schedule, technical systems 20 are included for water supply to the launch complex, maintenance of the space-rocket system 1, 2 and special technological equipment in constant readiness for work and the creation of normal conditions necessary for the successful work of maintenance personnel.

As necessary, auxiliary equipment 21 is activated to carry out auxiliary operations that arise during the prelaunch process.

All work on the prelaunch preparation and launch of the launch vehicle 1 with the spacecraft 2 is carried out from the launch control center 3 by the commands of the remote control system for technological operations and test and launch equipment 19 and is fixed on the launch console with a set of preparedness banners.

After the completion of all prelaunch operations, the launch vehicle 1 is launched with the spacecraft 2.

The gas jet of the propulsion systems when launching the launch vehicle 1 is discharged using the gas deflector 7 through the gas outlet channels of the launch structure 5 (Fig. 1).

Using television and movie cameras installed on the projector mast 9, pre-launch preparation and launch vehicle launch processes 1 with the spacecraft 2 are shot.

The proposed launch complex for the preparation and launch of launch vehicles with spacecraft allows refueling and fueling with high-purity compressed helium airborne charballs installed in the cryogenic tanks of the upper stage booster of the head block of the launch vehicle 1 and spacecraft 2 (Fig. 1) with any given temperature: both cryogenic (below 120K) and high (for example, in the range from 233 to 323K).

High purity of compressed helium (the concentration of contaminants according to experimental data is 0.5-1.0 mg / m ³ ) supplied to airborne charballoons installed in cryogenic tanks is achieved by the fact that:

- firstly, the compressor unit, with which helium receivers 25, 26 are refueled (Fig. 2), has a drying and cleaning unit to remove mechanical impurities, dust, oil and moisture;

- secondly, all undesirable impurities are frozen out at cryogenic temperatures in cryostats and their retention on fine filter elements.

In addition, the cooling of compressed helium on the one hand and the location of the side charballs 23 in the cryogenic tanks 24 on the other hand allow:

- increase the density of refilled compressed helium. So, at a pressure of 22 MPa and a temperature of 90 K, the density of helium is approximately 112 kg / m ³ , while at the same pressure and temperature 293 K, the density is about 33.8 kg / m ³ , that is, with a decrease in temperature from 293 to 90 K, the density of compressed helium increases by 3.3 times;

- increase the amount of refilled compressed helium, since M = ρV,

where M is the amount of refueling helium, kg;

ρ is the density of helium, kg / m ³ ;

V is the volume of onboard charballoons, m ³ .

When V = 3,52 m ³ we have M = 112 · 3,52 = 394,24 kg;

- reduce the volume of onboard charballs by increasing the density of compressed helium at cryogenic temperatures;

- to reduce the mass of the construction of charballs by reducing their wall thicknesses as a result of significant hardening of the material (stainless steel) at cryogenic temperatures [21-23].

These advantages, along with the high purity of refueling compressed helium (the concentration of pollution according to experimental data is not more than 0.5-1.0 mg / m ³ ), not only expand technological capabilities, but also provide high efficiency and reliability of the rocket-space system and launch complex generally.

A comparative analysis of the proposed and well-known launch complexes showed that in terms of technical level and the achieved effect, the proposed launch complex for the preparation and launch of launch vehicles with spacecraft exceeds the current world level and meets the criteria of the invention “Technical Level” and “Positive Effect”.

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 expand technological capabilities, to ensure high efficiency and reliability of the launch vehicle, spacecraft and launch complex generally.

The invention will be used in full at the launch complexes of Soyuz-2 launch vehicles.

Information sources

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3. Patent US 4932607, B 64 G 5/00, 08/02/1989 - analogue.

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Claims (1)

Launch complex for the preparation and launch of launch vehicles with spacecraft, containing a launch control center, a transport and installation unit, a launch facility, a launch system with a gas reflector, a service tower, a searchlight mast with television and movie cameras installed on it, located in the refueling system oxidizing agent and fuel, a compressor station, gas supply systems, a refrigeration center, air systems for ensuring the temperature and humidity conditions of the compartments and blocks of the launch vehicle and space apparatus, guidance system, electric power equipment, test equipment, test and start-up equipment, technical systems and auxiliary equipment, characterized in that it is equipped with a high-purity compressed helium refueling and recharge system for airborne balloons installed in cryogenic tanks of the upper stage the head block of the launch vehicle and the spacecraft, consisting of helium receivers connected to the compressor station, each of which is through pipelines with fittings connected through a gas reducer, cryostats associated with a liquid nitrogen storage, a heater, a collector and a vertical pipeline with airborne balloons of a launch vehicle and a spacecraft, as well as a nitrogen receiver with armature, which is connected through a pipeline through a gas reducer and a heater to each from cryostats.

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