RU2291817C2 - Module-type launch vehicle (versions) - Google Patents

Abstract

FIELD: rocketry and space engineering; multi-module launch vehicles of cluster arrangement at transfer of propellant among modules.

SUBSTANCE: proposed launch vehicle has central and side modules; it may be made in three versions at various modifications. According to first version, propellant for transfer is so distributed that each side two-tank module has excessive amount of only one propellant component. Each of these modules is provided with one inter-module main for transfer of propellant components. Some modifications of first version make use of displacement system for delivery of propellant component from upper tanks of side modules to lower tank of central module. According to second and third versions, use is made of one-tank side modules filled with different propellant components. In some modifications of these versions, modules are combined in clusters and are interconnected by means of simplified inter-module propellant lines. Propellant system of launch vehicle is simplified due to specialization of modules excluding dangerous processes. Efficiency is enhanced at use of kerosene-liquid oxygen propellant and engines of "closed" system employed in Russia.

EFFECT: low cost of manufacture and operation of launch vehicle; enhanced reliability.

11 cl, 18 dwg

Description

The invention relates to rocket and space technology, and in particular to the construction of multi-stage launch vehicles (LV), consisting of rocket modules (blocks) and designed to bring payloads to various near-Earth orbits, both directly and with the help of an additional upper stage - a completion unit constituting together with the payload the head block of the launch vehicle.

Known technical solutions for the use of multi-stage launcher single-tank missile modules (RM). An example of the use of single-tank RMs is the first stage of the Proton launch vehicle [1], in which six single-tank RMs are attached to the central fuel tank (TB). The liquid propellant rocket engine (LRE) of each module receives one component of fuel from the tank of its own unit, the other from the central fuel tank using the inter-module fuel line (TM). The use of such a scheme made it possible to reduce the length of the step and the dimension of the tanks, which in turn made it possible to transport it block by rail. The disadvantage of the launch vehicle is the low energy-mass perfection of the first stage, due to its structural design and the type of fuel used. In order for the launch vehicle to be effective, two more stages are connected to it, connected to the first one according to the tandem scheme. The engines of these stages start in flight, which negatively affects the reliability of the carrier. In addition, the dimension of the upper stages required the installation on them of engines of a different thrust class than on the first, i.e., the carrier turned out to be unified by the LRE. Accident statistics of the Proton rocket show that a significant proportion of them were related to the operation of the upper stage engines.

It is known to use pairs of single-tank units combined in a bundle ([2] - "HAZARD"), in which the rocket was composed of pairs of single-tank blocks having their own engine and a single fuel tank and using a fuel displacement system. Kerosene and concentrated nitric acid were used as fuel. During the flight, the missing fuel components were exchanged between the blocks in pairs. The main drawback of such a scheme is the required high staging to compensate for the low energy-mass characteristics of the rocket (up to 6 steps for carriers "HAG"), which resulted in a large - from several tens to 600 - the number of pairs of blocks. The consequence of this number of elements was the low design reliability of the rocket. In addition, the central missile element was absent in the rocket, while the payload was mounted in tandem with it. The absence of such an element in the design of the launch vehicle contributes to the development of instabilities in flight and leads to increased vibration effects on the payload and the design of the rocket itself.

The project of the technological series of the Angara launch vehicle [3] is known, the first stage of which is based on unified two-tank RM assembled according to the "package" scheme. One of the modules is central, the rest are symmetrically around it. In the Angara launch vehicle family, all modules have a high degree of unification — they use the same fuel components, engines of the same type, and fuel tanks of the same diameter and volume. This allows you to reduce the cost of developing the launch vehicle and creating a production base.

But these media have the following disadvantages. To increase efficiency in the last section of the first stage, throttle the liquid propellant rocket engine of the central Republic of Moldova (TsRM). This allows the end of the lateral PM to have some fuel remaining in the tanks of the CRM. The discharge of the side RMs and the autonomous flight of the central RM increase the carrying capacity of the carrier, but deep throttling of the engine is impossible without a deterioration of its characteristics and a decrease in reliability. Moderate throttling without significant consequences allows you to achieve a relatively small, about 20%, fuel residue in the tanks of the centralized storage. Thus, a bunch of several unified blocks is ineffective for launching artificial satellites. The second stage installed on the launch vehicle - an additional missile unit located coaxially with the CRM, significantly increases the mass of the payload. But this unit introduces two significant drawbacks to the pH. Firstly, it starts the engine in flight, which makes it impossible to stop the start-up if it is not turned on. Secondly, the second stage unit is not unified with the first stage units, which requires the organization of a separate production for it. Another disadvantage of the carrier is that failure to fly the engine of any of the first-stage units throughout its operation, with the exception of the very last seconds, inevitably leads to failure to fulfill the LV mission. This is caused by the unused fuel remaining in the emergency unit, which prevents the carrier from gaining sufficient speed.

Also known is the PH of a packet scheme in which both components from two-tank rocket blocks (modules) are transferred to blocks of subsequent stages in the process of their joint work so as to ensure the maximum filling of the tanks of the modules of the working layout by the time the stages are separated [4]. The carrier consists of several two-tank RM, assembled according to the "package" scheme, and the head part containing the payload. The head part may also contain a missile block - an additional upper stage. A batch layout may contain a different number of PM, which are modules of at least two stages. The last step consists of one block, on which the head is mounted on top. RM of all stages up to the penultimate inclusively equipped with means of separation in flight from the main layout. The LV is equipped with a fuel component overflow system between the modules, consisting of inter-module fuel lines, which connect their own fuel lines of the modules of each previous and subsequent stages. Separate hydraulic connectors and two shut-off valves on both sides of them are installed on the intermodular TM. In addition, on each of its own TM modules, with the exception of modules of the first stage, trigger valves are installed above the junction points with the intermodular TM.

The launch vehicle can be manufactured in several modifications, differing in the number of lateral RM, their location relative to the central RM, and the number of RM in each stage.

According to [4], the scheme of the overflow system of the fuel components is as follows. On the fuel lines of the modules of the next stage, connecting their fuel tanks with the blocks of the rocket engine, starting valves are installed. Between the modules of the preceding and subsequent stages, fuel lines are laid connecting the fuel lines of the modules of the previous stage with the fuel lines of the corresponding component of the modules of the next stage below the starting valves installed on them. Separate hydraulic connectors are installed on the inter-module TM in the inter-module space, and shut-off valves are installed on both sides of them. The last step is the CRM, from which the fuel does not overflow.

In total, the launch vehicle has two intermodular TMs for each lateral block.

Presented PH [4] is the closest to the proposed and selected as a prototype.

The disadvantage of the prototype is the increasing complexity with an increase in the number of component blocks: with each additional PM, starting from the second, the PH receives two fuel tanks with the systems that support them and two intermodular TMs, each of which contains two shut-off valves and one tear-off hydraulic connector. In addition, the PM of the second and subsequent stages contain two starting valves on their own TM module. The presence of these devices adversely affects the reliability of the launch vehicle, since all of them are triggered during the flight, and the failure of most of them causes a launch vehicle accident. At least, an accident will occur when the disconnect hydraulic connectors are not undocked and the shut-off valves are not closed from the side of the working stage.

An increasing number of intermodular TM with detachable hydraulic connectors is reflected in the mass and cost of manufacturing the structure. A large number of tanks also increases the dry weight and the cost of manufacturing pH. This is due not only to the need to install component monitoring systems in each tank, but also to the volume of internal tank work, after which its high purity must be ensured. In the process of production of tanks, cleaning is also required from the inside of their walls. The volume of this work is proportional to the total area of the inner surface of the tanks, which is proportional to the number of PM.

Particularly difficult is the control of the internal state of tanks in reusable modules. An additional complication is the piping of the component located in the upper tank of the unit, usually laid through the lower tank. It is fully or partially suspended in a position close to vertical, and upon return it experiences transverse loads several times higher than the loads during transportation and removal. The production of reusable rocket blocks will require the strengthening of the internal fuel line or laying it along the outer surface of the tank, which will lead to an increase in their dry weight.

The purpose of the proposed technical solution is to increase the reliability of the launch vehicle, reducing production costs and operating costs.

This is achieved by the fact that the fuel intended for overflow into other blocks is distributed component-wise over two-tank PM so that in each of them only one component includes a fraction intended for overflow. In addition, this is achieved by the reverse arrangement of the tanks in the modules of different stages and by the fact that the intermodular TM components of the upper tanks of the previous stage are connected directly to the tanks of the same component of the next stage, which have a lower arrangement in the modules. This will halve the number of intermodular TM, as well as reduce the number of start-up valves and thereby increase reliability and reduce the cost of manufacturing LV.

This is also achieved by the fact that in the PH both two-tank and single-tank RM are used. This will make it possible to reduce the number of tanks with the same number of intermodular TMs and thereby reduce the dry weight of the LV and the number of measuring equipment and, therefore, reduce the cost of manufacturing and launch of the LV. In some modifications of the LV, this is also achieved due to the fact that single-tank RM containing different components located next to each other and exchanging components using intermodular TMs are paired using force connections ensuring their separation from the main layout in bundles, while the fuel lines connecting the fuel systems of these RMs do not contain shut-off valves and have a simplified detachable connection. At the same time, in some modifications of the launch vehicle using fuel components with significantly different volume ratios, in bundles of single-tank RMs in that of them that contains a component with a smaller volume, an additional TB is installed on top, containing another fuel component that connects to the fuel tank of another unit when help intermodular fuel line.

The pH can be performed in three versions:

1. With component-wise placement of all transfused fuel in the side two-tank RM and overfilling it in the central distribution center.

2. With the placement of all transfused fuel in the side single-tank RM.

3. With the addition of single-tank PM to the two-stage layout of two-tank RM, using fuel overflow between units.

Among the options there may be modifications containing a different number of side modules, having a different configuration of component overflow systems, having direct and reverse arrangement of fuel tanks in two-tank RM of different levels, with additional RM with an autonomous fuel system.

The invention is illustrated by the following graphic material:

Figure 1 shows a side view (a) and a bottom view (b) of a four-block modification of the launch vehicle with the component-wise placement of all transfused fuel in three side two-tank RM.

Figure 2 shows the fuel scheme of the four-block modification of the launch vehicle with the component-wise placement of all transfused fuel in three lateral two-tank RM and the same arrangement of fuel tanks in all RM.

Figure 3 shows the fuel scheme of the four-block modification of the launch vehicle with the component-wise placement of all the transfused fuel in three lateral two-tank RM and the upper location of the fuel tank containing an additional amount of component.

Figure 4 shows a side view (a) and a bottom view (b) of a seven-block launch vehicle modification with component-wise placement of all transfused fuel in three side two-tank PM and three additional RM with an autonomous fuel system.

Figure 5 shows a side view (a) and a bottom view (b) of a seven-block launch vehicle modification with component-wise placement of all transfused fuel in six side two-tank RM.

Figure 6 shows the fuel scheme of the seven-block modification of the launch vehicle with the component-wise placement of all transfused fuel in six lateral two-tank RM and the same arrangement of fuel tanks in all RM.

Figure 7 shows a side view (a) and a bottom view (b) of a four-block modification of the launch vehicle using three single-sided side PM.

On Fig shows the fuel circuit of the four-block modification of the PH, using three single-sided side PM.

Fig. 9 shows a side view (a) and a bottom view (b) of a seven-block modification of the launch vehicle using three single-tank side PMs and three two-tank side PMs with an autonomous fuel system.

Figure 10 shows a side view (a) and a bottom view (b) of a seven-block modification of the PH using six single-sided side PM.

Figure 11 shows the fuel circuit of a three-stage seven-block modification of the launch vehicle, using six single-tank side RM.

On Fig shows a side view (a) and a bottom view (b) of a five-block modification of the PH, using four single-sided side PM, which are pairwise combined into bundles.

On Fig shows the fuel scheme of the five-block modification of the pH, using four single-sided side PM, which are paired in bundles.

On Fig shows a side view (a) and a bottom view (b) of a five-block modification of the PH, using two single-tank and two two-tank side PM, which are pairwise combined into bundles.

On Fig shows the fuel scheme of the five-block modification of the pH, using two single-tank and two two-tank side PM, which are paired in bundles.

On Fig shows the fuel scheme of the seven-block modification of the pH, using six single-sided side PM, which are combined in two groups of three modules containing bundles of two modules.

On Fig shows a side view (a) and a bottom view (b) of the seven-block modification of the PH, using four single-sided side PM, which are pairwise combined in bundles, and two side two-tank PM.

On Fig shows the fuel scheme of the seven-block modification of the pH, using four single-sided side RM, which are pairwise combined into bundles, and two side two-tank RM.

In all modifications, the pH contains a head part 1 and a central PM 2, as well as side PM. The warhead contains a payload, and may also contain an additional missile unit, which is not taken into account later in the text when determining the phasing.

The four-block modification of the launch vehicle with the component-wise placement of all transfused fuel in three lateral two-tank RM (Figs. 1 (a) and (b)) is based on the DTM 2, in parallel with which the lateral rocket modules 3, 4 and 5 are installed. coaxially mounted with the head part 1.

In most used pairs of components, the fuel and oxidizing agent have different densities. For example, liquid oxygen is approximately 1.35 times denser than kerosene. The component-wise placement of all or part of the fuel in the side modules of the four-module launch vehicle displaces the center of mass relative to the thrust vector. This problem is solved by throttling at the start of engines of heavier side modules with a gradual restoration of their thrust to nominal or by shifting the side modules to completely eliminate thrust eccentricity at the start, followed by gradual throttling of engines of heavier modules.

The fuel circuit of this launch vehicle is constructed as follows (Fig.2, 3). The CRM has a liquid-propellant rocket engine block 6, containing one or several liquid-propellant rocket engines, an oxidizer tank 7, oxidizer TM 8, connecting the tank 7 to the oxidizer inlet pipe of the liquid-propellant rocket engine block 6. The internal path of the liquid-propellant rocket engine block 6 and the volume of TV 7 are separated by a start-up valve 9. Second fuel tank 10, the fuel-containing CRM is connected by the fuel line 11 to the inlet of the fuel block of the liquid fuel engine 6. The internal path of the fuel block of the liquid fuel engine 6 and the volume of the fuel cell 10 are separated by a start trigger valve 12.

The lateral PM 3 contains a rocket engine block 13, an oxidizer tank 14, an oxidizer TM 15, connecting the tank 14 to the oxidizer inlet pipe of the rocket engine block 13. The internal oxidizer path of the rocket engine block 13 and the volume of TB 14 are separated by a start trigger valve 16. The second TB 17 containing fuel, connected to the fuel line 18 with the inlet of the fuel block of the liquid propellant rocket engine 13. The internal path of the fuel block of the liquid propellant rocket engine 13 and the volume of TB 17 are separated by a start trigger valve 19.

Lateral RM 4 contains a rocket engine block 20, an oxidizer tank 21, oxidizer TM 22, connecting the tank 21 to the oxidizer inlet pipe of the rocket engine block 20. The internal oxidizer path of the rocket engine block 20 and the volume of the TB 21 are separated by a start trigger valve 23. The second TB 24 containing fuel, connected to the fuel line 25 with the inlet of the fuel block of the liquid propellant rocket engine 20. The internal path of the fuel block of the liquid propellant rocket engine 20 and the volume of the fuel cell 24 are separated by a start trigger valve 26.

The lateral PM 5 contains a rocket engine block 27, an oxidizer tank 28, an oxidizer TM 29, connecting the tank 28 to the oxidizer inlet pipe of the rocket engine block 27. The internal path of the oxidizer block of the rocket engine 27 and the volume of the fuel cell 28 are separated by a start trigger valve 30. The second fuel cell 31, containing fuel, connected to the fuel line 32 with the inlet of the fuel block of the liquid propellant rocket engine 27. The internal path of the fuel block of the liquid propellant rocket engine 27 and the volume of the fuel cell 31 are separated by a start trigger valve 33.

In PM 3, the fuel tank 17 contains an additional amount of the component in excess of the required remote control for this PM when using the entire oxidizer from tank 14. Between this and the central modules, an intermodular TM 34 is laid connecting their fuel volumes of fuel, including tanks 10 and 17 and their own lines 11 and 18 fuel. A tear-off hydraulic connector 35 is installed in the inter-module space on the inter-module TM. A shut-off valve 36 is installed on the inter-module TM to the hydraulic connector 35 on the inter-module TM, and a shut-off valve 37 is installed on the side of the lateral PM.

The pH can be performed in two versions. In one of them (FIG. 2), the TBs in modules 2 and 3 are located identically (the oxidizer tanks are upper, the fuel tanks are lower). If the intermodular ТМ 34 is connected to the ТМ fuel of fuel 11, then the start valve 38 can be installed at the last connection point above. In another modification (Fig. 3), the fuel tank 17 in РМ 3 is installed above the oxidizer tank 14, the inter-modular ТМ 34 directly connects the tanks fuel 17 and 10 in the PM 3 and the TsRM, and the start valve on the fuel line 11 is missing.

In both versions in PM 4 and 5, the oxidizer tanks 21 and 28 contain an additional amount of the component in excess of the required for the remote control when using all the fuel from the tanks 24 and 31. Intermodular ТМ 39 and 40 are laid between these modules and the CRM, connecting their oxidizer fuel volumes, including tanks 7, 21, 28 and own oxidizer lines 8, 22 and 29. Separate hydraulic connectors 41 and 42 are installed in the inter-module space on the inter-module TMs. Shut-off valves 43 and 44 are installed on the side of the central control valve to the hydraulic connectors 41 and 42 on the inter-module TM and side boko PM's - shut-off valves 45 and 46.

If the intermodular ТМ 39 and 40 are connected to the ТМ of oxidizing agent 8 of ЦРМ, then at the last higher point of connection a controlled starting valve 47 can be installed.

All modifications of the launch vehicle can be performed without starting valves 38 and 47 on the fuel lines of the centralized engine. Then, in order to overcome the pressure of the liquid column without complicating the design of the pH, the components should be overfilled with the difference in boost pressure in the tanks. The differential pressure boost for liquid oxygen at characteristic 4-fold overloads provides a level difference of ~ 1 / (0.45 atm / m). At characteristic boost pressures that do not require a significant thickening of the walls of the tanks, the absence of valve 47 can be justified for a PH of small height, with a CRM length of no more than ~ 10 m. Under the same conditions, it is possible to assume the absence of valve 38 for a CRM up to ~ 35 m long.

Three additional PMs having an autonomous fuel system (PM 48, 49 and 50, in Fig. 4 (a), (b)) can be installed on the launch vehicle.

The three-stage seven-block modification of the launch vehicle with the component-wise placement of all transfused fuel in six lateral two-tank RM (Fig. 5 (a), (b)) is based on the four-block modification of the launch vehicle with the component-wise placement of all transfused fuel in three lateral two-tank RM (figure 1) with the difference that the proportions of the fuel tanks in the side PM were changed and three additional two-tank RM were installed. Module 51 contains an additional amount of fuel; modules 52 and 53 contain an additional amount of oxidizing agent intended for overflow in the central combustion chamber.

The fuel scheme of the seven-block modification of the launch vehicle with the component-wise placement of all transfused fuel in six side two-tank RM and the same arrangement of the fuel tanks in all RMs (Fig. 6) is based on the fuel scheme of the four-block launch vehicle with the component-wise placement of all transfused fuel in three lateral two-tank RM (Fig. .2). The fuel systems of three additional two-tank PM 51, 52, 53, having the same composition 3, 4, 5 and the composition of the fuel tanks and fuel lines, are added to the base.

Lateral RM 51 contains a rocket engine block 54, oxidizer tank 55, oxidizer TM 56, connecting the tank 55 to the oxidizer inlet pipe of the rocket engine block 54. The internal path of the rocket engine block 54 and the volume of TB 55 are separated by a start trigger valve 57. A second TB 58 containing fuel, connected to the fuel line 59 with the inlet of the fuel block of the liquid propellant rocket engine 54. The internal path of the fuel block of the liquid propellant rocket engine 54 and the volume of the fuel cell 58 are separated by a start trigger valve 60.

Lateral RM 52 contains a rocket engine block 61, an oxidizer tank 62, oxidizer TM 63, which connects the tank 62 to the oxidizer inlet pipe of the rocket engine block 61. The internal path of the oxidizer block of the rocket engine 61 and the volume of TB 62 are separated by a start trigger valve 64. The second TB 65 containing fuel, connected to the fuel line 66 with the inlet of the fuel block of the liquid propellant rocket engine 61. The internal path of the fuel block of the liquid propellant rocket engine 61 and the volume of the fuel cell 65 are separated by a start trigger valve 67.

Lateral RM 53 contains a rocket engine block 68, an oxidizer tank 69, an oxidizer TM 70, connecting the tank 69 to the inlet pipe of the oxidizer rocket engine block 68. The internal path of the oxidizer block of the liquid rocket engine 68 and the volume of TB 69 are separated by a start trigger valve 71. A second TB 72 containing fuel, connected to the fuel line 73 with the inlet of the fuel block of the liquid propellant rocket engine 68. The internal path of the fuel block of the liquid propellant rocket engine 68 and the volume of TB 72 are separated by a start trigger valve 74.

In the PM 51, the fuel tank 58 contains an additional amount of component intended for overflow in the DPC. Between these modules, an intermodular TM 75 was laid, connecting the fuel volume of the PM 51 fuel with the fuel line 11 of the intake cylinder below the start valve 38. A shut-off hydraulic connector 76 was installed in the inter-module space on the inter-module TM. A shut-off valve 77 was installed on the side of the central distribution module to the hydraulic connector 76, and the intermodular TM 76 from the side of the side РМ - shut-off valve 78.

In PM 52 and 53, the oxidizer tanks 62 and 69 contain an additional amount of component intended for overflow in the central combustion chamber. Between these and the central modules there are interblock ТМ 79 and 80 connecting their oxidizer lines 63 and 70 with the oxidizer line 8 of the TsRM below the start valve 47. Separate hydraulic sockets 81 and 82 are installed in the inter-module space on these inter-module TMs. From the TsRM to the hydraulic sockets 81 and 82 shut-off valves 83 and 84 are installed on the intermodular TM, and shut-off valves 85 and 86 are installed on the side of the lateral PM.

On the TM 18 PM 3 above the junction with the intermodular fuel line 34, a start valve 87 is installed. On the TM 22 PM 4 and on the TM 29 PM 5, the start valves 88 and 89, respectively, are installed above the junction with the oxidizing lines 39 and 40.

The four-block modification of the launch vehicle, using three single-tank lateral PMs (Fig. 7 (a), (b)), is based on the CRM 2, in parallel with which the lateral rocket modules 3, 4, 5 are installed, each of which has a single fuel tank. PM 3 contains fuel, modules 4 and 5 - an oxidizing agent. On top of the CRM and coaxially mounted with it is the head part 1.

The fuel system of the four-block modification of the PH using three single-tank PM (Fig. 8) differs from the fuel system of the PH with the component-wise placement of all transfused fuel in the three side two-tank RM (Fig. 2) with the elemental composition of the side modules and the presence of additional intermodular TM.

Lateral RM 3 contains a rocket engine block 13, TV 17, containing fuel and connected to the fuel line 18 with the inlet pipe of the fuel block rocket engine 13. The internal path of the fuel block rocket engine 13 and the volume of the TV 17 are separated by a start trigger valve 19.

Lateral RM 4 contains a rocket engine block 20, an oxidizer tank 21, oxidizer TM 22, connecting the tank 21 to the oxidizer inlet pipe of the rocket engine block 20. The internal oxidizer path of the rocket engine block 20 and the volume of the TV 21 are separated by a start trigger valve 23.

Lateral RM 5 contains a rocket engine block 27, oxidizer tank 28, oxidizer TM 29, connecting the tank 28 to the oxidizer inlet pipe of the rocket engine block 27. The internal oxidizer path of the rocket engine block 27 and the volume of the TV 28 are separated by a start trigger valve 30.

An additional intermodular oxidizer line 90 was laid between the CRM and RM 3, which has a tear-off hydraulic connector 91 in the intermodular space and shut-off valves 92 and 93 on both sides of it.

Between TsRM and RM 4 an additional intermodular fuel line 94 has been laid, having a tear-off hydraulic connector 95 in the inter-module space and shut-off valves 96 and 97 on both sides of it.

Between TsRM and RM 5 an intermodular fuel line 98 was laid, having a tear-off hydraulic connector 99 in the intermodular space and shut-off valves 100 and 101 on both sides of it.

Intermodular TMs are connected to the central distribution center, forming a common collector of the intermodular fuel lines and a common collector of the intermodular oxidizer lines.

The common manifold of the intermodular fuel lines connects the fuel volume PM 3, including the fuel tank 17 and the fuel pipe 18, with the fuel pipe 11 of the central control module and with the fuel inlet pipes of engines 20 and 27. The internal paths of the fuel blocks of the LPRE 20 and 27 are separated from the volume of the fuel manifold by the starting launchers valves 26 and 33.

The common collector of the intermodular oxidizer lines connects the fuel volumes РМ 4 and 5, including the oxidizer tanks 21 and 28 and the oxidizer lines 22 and 29 corresponding to them, with the oxidizer line 8 of the central combustion engine and with the oxidizer inlet pipe of the engine rocket engine 13 РМ 3. The internal path of the oxidizer of the engine rocket engine 13 is separated from the volume of the collector of the oxidizer starting start valve 16.

On the fuel TM 11 of the central fuel injection system, a controlled start valve 38 can be installed above the junction with the common collector of the intermodular fuel mains.

On the oxidizer TM 8 of the central combustion engine, a controlled start-up valve 47 can be installed above the junction with the common collector of the intermodular oxidizer lines.

Three additional PMs having an autonomous fuel system (PM 48, 49 and 50 in Fig. 9 (a), (b)) can be installed on the launch vehicle.

The seven-block PH modification using six single-sided side RMs (Fig. 10 (a), (b)) is based on a four-block PH with single-sided side RMs (Fig. 7), to which three additional PM 51, 52 and 53 are added. made one-tank. PM 51 contains fuel, modules 52 and 53 - an oxidizing agent.

The fuel system of the seven-block modification of the pH using six one-sided side PM (Fig. 11) is based on the fuel system of the four-block modification of the PH using three side one-sided PM (Fig. 8). Fuel systems PM 51, 52, 53, fuel lines connecting these modules with a four-block layout, as well as start valves installed in RM 3, 4 and 5 are added to it.

Lateral RM 51 contains a rocket engine block 54, TV 58 containing fuel and is connected by a fuel line 59 to the inlet of the fuel block of the rocket engine 54. The internal path of the fuel block of the rocket engine 54 and the volume of the TV 58 are separated by a start trigger valve 60.

Lateral RM 52 contains a rocket engine block 61, an oxidizer tank 62, oxidizer TM 63, connecting the tank 62 to the oxidizer inlet pipe of the rocket engine block 61. The internal oxidizer path of the rocket engine block 61 and the volume of TV 62 are separated by a start trigger valve 64.

Lateral RM 53 contains a rocket engine block 68, an oxidizer tank 69, an oxidizer TM 70, connecting the tank 69 to the oxidizer inlet pipe of the rocket engine block 68. The internal oxidizer path of the rocket engine block 68 and the volume of TV 69 are separated by a start trigger valve 71.

Between TsRM and RM 51 are laid:

- an intermodular fuel line 75, having a tear-off hydraulic connector 76 in the inter-module space and shut-off valves 77 and 78 on both sides of it;

- an intermodular oxidizer line 102 having a tear-off hydraulic connector 103 in the intermodular space and shut-off valves 104 and 105 on both sides of it.

Between TsRM and RM 52 laid:

- an intermodular fuel line 106 having a tear-off hydraulic connector 107 in the inter-module space and shut-off valves 108 and 109 on both sides of it;

- an intermodular oxidizer line 79, having a tear-off hydraulic connector 81 in the inter-module space and shut-off valves 83 and 85 on both sides of it.

Between TsRM and RM 53 laid:

- an intermodular fuel line 110 having a tear-off hydraulic connector 111 in the inter-module space and shut-off valves 112 and 113 on both sides of it;

- the intermodular line of the oxidizing agent 80, which has a tear-off hydraulic connector 82 in the inter-modular space and shut-off valves 84 and 86 on both sides of it.

In PM 3, on the fuel line 18 above the junction with the intermodular TM 34, a start valve 87 is installed.

In PM 4 and 5, on the oxidizer lines 22 and 29 above the junction with the intermodular TM 39 and 40, trigger valves 88 and 89 are installed.

Intermodular TMs are connected to the central distribution center, forming a common collector of the intermodular fuel lines and a common collector of the intermodular oxidizer lines.

A common manifold of the intermodular fuel lines connects the fuel volumes РМ 3 and РМ 51, including fuel tanks 17 and 58, fuel lines 18 and 59 corresponding to them, to the fuel line 11 of the central combustion engine and to the fuel inlet pipes of engines 20, 27, 61 and 68. Internal paths fuel blocks of the rocket engine 20, 27, 61 and 68 are separated from the volume of the fuel manifold by starting trigger valves 26, 33, 67, 74.

The common collector of the intermodular oxidizer lines connects the fuel volumes РМ 4, 5, 52 and 53, including the oxidizer tanks 21, 28, 62 and 69, the corresponding oxidizer lines 22, 29, 63 and 70, with the oxidizer line 8 of the central combustion engine and with the oxidizer inlets engines 13 and 54. The internal paths of the oxidizer of the rocket engine blocks 13 and 54 are separated from the volume of the oxidizer collector by starting trigger valves 16 and 57.

On the fuel line 11 of the TsRM above the point of connection with the collector of the intermodular fuel lines, a start valve 38 can be installed.

A start valve 47 may be installed on the oxidizer line 8 of the central combustion engine above the junction with the collector of the intermodular oxidizer lines.

The five-block pH modification using four single-sided lateral RMs, which are pairwise combined into bundles (Fig. 12 (a), (b)), differs from the seven-block modification of the LV using six single-sided lateral RMs (Fig. 10 (a), (b) ), the absence of two side modules - 5 and 53. Of the remaining side modules, PM 3 and 51 contain fuel, PM 4 and 52 - an oxidizing agent. Lateral RM are grouped in two. Modules 3 and 4 comprise one group, modules 51 and 52 form another. In each group, the modules are mated laterally with each other and with the DTM.

The fuel system of the five-block modification of the PH using four single-tank side RMs, which are paired into bundles (Fig. 13), differs from the fuel system of the seven-block modification of the PH using six side single-tank RMs (Fig. 11), by the absence of two modules in the system (5 and 53) and the configuration of intermodular TM. Of the TMs laid between the central and side PM, there are oxidizer lines 39 and 79 and fuel lines 34 and 75, the device and the purpose of which are similar to the corresponding TMs in the seven-block modification of the LV with six single-sided lateral RMs (Fig. 11). In addition, between modules 3 and 4 are laid:

- an intermodular fuel line 114 having a connector 115 in the intermodular space;

- an intermodular oxidizer line 116 having a connector 117 in the intermodular space;

and between modules 51 and 52:

- an inter-module fuel line 118, having a connector 119 in the inter-module space;

- an intermodular oxidizer line 120 having a connector 121 in the intermodular space.

The inter-module fuel line 114 connects the fuel volume PM 3, including the fuel tank 17 and the fuel line 18, with the inlet pipe of the engine block 20. The internal path of the fuel block of the liquid propellant rocket engine 20 is separated from the fuel volume by a start trigger valve 26.

The intermodular fuel line 118 connects the fuel volume PM 51, including the fuel tank 58 and the fuel line 59, with the inlet pipe of the engine block 61. The internal path of the fuel block of the LRE 61 is separated from the fuel volume by a start trigger valve 67.

The inter-module oxidizer line 116 connects the fuel volume PM 4, including the fuel tank 21 and the fuel line 22, with the inlet pipe of the engine block 13 PM 3. The internal path of the fuel block of the rocket engine 13 is separated from the volume of the fuel by a start trigger valve 16.

The intermodular oxidizer line 120 connects the fuel volume PM 52, including the fuel tank 62 and the fuel line 63, with the inlet pipe of the engine block 54 PM 51. The internal path of the fuel block of the rocket engine 54 is separated from the fuel volume by a start trigger valve 57.

On the fuel ТМ 11 of the TsRM, a controlled start valve 38 is installed above the junction with the common fuel manifold.

On the oxidizer TM 8 of the central combustion engine, a controlled starting valve 47 is installed above the junction with the common oxidizer collector.

There are no start valves on the own fuel lines of the side RM.

The five-block modification of the PH using two single-tank and two two-tank lateral RMs, which are pairwise combined into bundles (Fig. 14 (a), (b)), differs from the five-block modification of the PH using four single-sided RMs (Fig. 12 (a), (b)), in that the PM 3 and 51 contain additional oxidizer tanks.

The fuel modification system of the PH using two single-tank and two two-tank side RMs that are paired together in bundles (Fig. 15) differs from the fuel modification system of the PH using four single-tank side RMs that are pairwise combined into bundles (Fig. 13) as follows.

In PM 3, an oxidizer tank 14 is installed above the fuel tank 17 and is connected to the oxidizer tank 21 in the PM 4 intermodular TM 122, on which the connector 123 is mounted.

In the PM 51, an oxidizer tank 55 is mounted on top of the fuel tank 58, which is connected to the oxidizer tank 62 in the PM 52 intermodular TM 124, on which the connector 125 is mounted.

The seven-block modification of the PH using six single-sided lateral RMs, which are combined into two groups of three modules containing bundles of two modules (Fig. 10 (a), (b)), differs from the five-block modification of the PH using four single-sided lateral RMs pairwise combined into bundles (Fig.12 (a), (b)), two additional single-tank modules 5 and 53 containing an oxidizing agent.

The fuel system of the seven-block modification of the PH using six single-sided lateral PMs, which are combined into two groups of three modules containing bundles of two modules (Fig. 16), differs from the fuel system of the five-block modification of the PH using four single-sided lateral RMs, which are pairwise combined in ligaments (Fig.13), as follows.

The additional lateral PM 5 contains a rocket engine block 27, an oxidizer tank 28, an oxidizer TM 29, connecting the tank 28 to the oxidizer inlet pipe of the rocket engine block 27. The internal path of the oxidizer block of the rocket engine 27 and the volume of the cylinder assembly 28 are separated by a start trigger valve 30.

An additional lateral PM 53 contains a rocket engine block 68, an oxidizer tank 69, an oxidizer TM 70, connecting the tank 69 to the inlet pipe of the oxidizer rocket engine block 68. The internal path of the oxidizer block of the liquid rocket engine 68 and the volume of fuel cell 69 are separated by a start trigger valve 71.

Between modules 4 and 5 are laid:

- a fuel line 126 having a tear-off hydraulic connector 127 in the intermodular space, shut-off valves 128 and 129 on both sides of it, and connecting the inlet pipe of the fuel block of the LRE 27 in RM 5 with the collector of the inter-module fuel lines;

- oxidizer line 130, having a tear-off hydraulic connector 131 in the intermodular space, shut-off valves 132 and 133 on both sides of it, and connecting TM 29 in PM 5 with the collector of the intermodular oxidizer lines.

Between modules 52 and 53 are laid:

- a fuel line 134 having a tear-off hydraulic connector 135 in the intermodular space, on both sides of it there are shut-off valves 136 and 137, and connecting the inlet pipe of the fuel block of the liquid propellant rocket engine in РМ 53 with the collector of the inter-module fuel lines;

- oxidizer line 138, having a tear-off hydraulic connector 139 in the intermodular space, shut-off valves 140 and 141 on both sides of it, and connecting ТМ 70 in РМ 53 with the collector of the inter-modular oxidizer lines.

In PM 4, on the oxidizer line 22 above the junction with the collector of the intermodular oxidizer lines, a start valve 88 is installed.

In PM 52, on the oxidizer line 63 above the junction with the collector of the intermodular oxidizer lines, a start valve 142 is installed.

The seven-block modification of the PH using four single-sided side RMs, which are pairwise combined into bundles, and two two-sided side RMs (Fig. 17 (a), (b)), differs from the five-block modification of the PH using four single-sided side RMs, which are pairwise combined into ligaments (Fig.12 (a), (b)), in that two additional two-tank modules 5 and 53 are installed on it.

The fuel modification system of the PH using four single-sided side PMs, which are pairwise combined into bundles, and two two-sided side RMs (Fig. 18), differs from the fuel system of the five-block modification of the PH using four single-sided side PMs, which are pairwise combined into bundles (Fig. 13) as follows.

Lateral RM 5 contains a rocket engine block 27, an oxidizer tank 28, oxidizer TM 29, connecting the tank 28 to the inlet pipe of the oxidizer rocket engine block 27. The internal path of the oxidizer block of the rocket engine 27 and the volume of TB 28 are separated by a start trigger valve 30. In addition, RM 5 contains a tank fuel 31, fuel TM 32, connecting the tank 31 to the inlet pipe of the oxidizer of the rocket engine block 27. The internal path of the fuel block of the rocket engine 27 and the volume of the fuel tank 31 are separated by a start trigger valve 33.

Lateral RM 53 contains a rocket engine block 68, an oxidizer 69 tank, and TM oxidizer 70 connecting the tank 69 to the oxidizer inlet pipe of the rocket engine block 68. The internal path of the oxidizer block of the liquid rocket engine 68 and the volume of TB 69 are separated by a start trigger valve 71. In addition, RM 53 contains a tank fuel 72, fuel TM 73, connecting the tank 72 with the inlet pipe of the oxidizer of the rocket engine block 68. The internal path of the fuel block of the rocket engine 68 and the volume of TB 72 are separated by a start trigger valve 74.

The intermodular oxidizer line 39, which has a tear-off hydraulic connector 41 in the inter-modular space and has shut-off valves 43 and 45 on both sides of it, is laid between the PM 5 and the bundle PM 3, 4.

The inter-module fuel line 34, having a tear-off hydraulic connector 35 in the inter-module space and with shut-off valves 36 and 37 on both sides of it, is laid between the PM 53 and the bundle PM 3, 4.

The inter-module oxidizer line 79, which has a tear-off hydraulic connector 81 in the inter-module space and has shut-off valves 83 and 85 on both sides of it, is laid between the PM 53 and the bundle PM 51, 52.

The intermodular fuel line 75, which has a detachable hydraulic connector 76 in the intermodular space and has shut-off valves 77 and 78 on both sides of it, is laid between the PM 5 and the bundle PM 51, 52.

The intermodular line of oxidizer 40, which has a tear-off hydraulic connector 42 in the inter-module space and has shut-off valves 44 and 46 on both sides of it, connects ТМ 8 ЦРМ with ТМ 29 РМ 5;

The intermodular fuel line 98, which has a tear-off hydraulic connector 99 in the inter-module space and has shut-off valves 100 and 101 on both sides of it, connects ТМ 11 ЦРМ with ТМ 32 РМ 5.

In PM 5, on the oxidizer line 29 above the junction with the intermodular TM 39 and 40, a start valve 143 is installed; on the fuel line 32 above the junction with the intermodular TM 75 and 98, a start valve 144 is installed.

The inter-module oxidizer line 80, which has a detachable hydraulic connector 82 in the inter-module space and has shut-off valves 84 and 86 on both sides of it, connects ТМ 8 ЦРМ with ТМ 70 РМ 53;

The intermodular fuel line 110, which has a tear-off hydraulic connector 111 in the inter-module space and has shut-off valves 112 and 113 on both sides of it, connects ТМ 11 ЦРМ with ТМ 73 РМ 53.

In PM 53, on the oxidizer line 70 above the junction with the intermodular TM 79 and 80, a start valve 145 is installed; on the fuel line 73 above the junction with the intermodular TM 34 and 110, a start valve 146 is installed.

On the fuel ТМ 11 of the TsRM, a controlled start valve 38 is installed above the junction with the intermodular ТМ 98 and 110.

On the oxidizer TM 8 of the central combustion engine, a controlled start valve 47 is installed above the junction with the intermodular TM 40 and 80.

The work of the launch vehicle begins with refueling operations, during which the fuel tanks of the modules, their own and intermodular fuel lines are filled with fuel components. Strait through drainage holes from the lines remove all combined-gas inclusions.

The operation of the four-block modification of the PH variant with the component-wise placement of all transfused fuel in three lateral two-tank RM and the same arrangement of fuel tanks in all RMs is explained below using FIG. 2.

During refueling, the starting trigger valves 9, 12, 16, 19, 23, 26, 30 and 33 are closed. Their opening corresponds to the beginning of engine start.

During pre-launch operations and in the initial phase of the flight, fuel valves 36 and 37, oxidizer valves 43, 44, 45, 46 are open, valves 38 and 47 on their own CRM highways are closed.

In the initial phase of the flight, the excess fuel components located in the accelerators 3, 4, and 5 is poured into the CRM 2 along the intermodular highways 34, 39, 40, where it is used in the rocket engine 6. At this time, there is no significant fuel consumption from the CRM tanks. But a small flow rate is possible to compensate for the external impact on the fuel in the pipelines in order to avoid the loss of its conditioning. In this case, the start valves 38 and 47 in the closed position should have an appropriate throughput. All starting valves on all LV modifications can have the same property.

At time moments determined by the carrier measurement system and corresponding to the exhaustion of the excess of the corresponding fuel component in each accelerator, at the command of the control system, the intermodular ТМ 34, 39, and 40 are closed and the fuel overflow stops.

The overlapping of the intermodular fuel line 34 occurs when one of the valves 36 or 37 is triggered, synchronized with the opening of the valve 38 on its own fuel line 11 of the TsRM, as a result of which the engine’s liquid propellant block switches to fuel from the tanks of its own module.

Overlapping of the intermodular oxidizer lines 39 and 40 occurs when one of the valves 43 or 45, 44, or 46 is triggered on each of them. Synchronously with the last of the intermodular oxidizer lines 39 and 40 overlapping, valve 47 completely opens on the oxidizer 8 own CRM and LRE of the latter goes to the oxidizer from the tanks of its own module.

By the time of separation of the lateral PM, all shut-off valves on the intermodular lines 34, 39 and 40 are closed. After the exhaustion of fuel reserves to the technological residue, the lateral PM are separated. The disconnection of the connectors 35, 41 and 42 occurs in the interval between the closing of the shut-off valves installed on their respective inter-module TMs and the separation of the modules.

Valve 47 can be three-position and partially open synchronously with the closure of the first of the intermodular oxidizer lines 39 and 40.

Further flight of the CRM is autonomous. After the exhaustion of fuel reserves in the tanks of the CRM or at the moment of reaching the required speed, its engines stop and the flight task is considered completed.

Compared with the prototype of the pH of the given scheme has the following advantages. The number of intermodular fuel lines and related elements is halved - from 6 to 3, which positively affects the reliability of the carrier. Simplification of the design creates the prerequisites for reducing the cost of manufacturing LV blocks and operating costs. Due to the reduction of intermodular TM, the dry mass of the RM, especially the central mass, is also reduced, which increases the carrying capacity of the LV.

In the four-block modification of the launch vehicle with the component-wise placement of all the transfused fuel in the three side two-tank RM and the upper location of the fuel tank containing an additional amount of fuel, the fuel tanks 14 and 17 in the PM 3 are in the opposite position relative to the tanks of the CRM. The flight diagram of modifications with direct and reverse fuel tanks is the same. The operation of the fuel system (figure 3) of this modification is similar to that shown in figure 2 with the exception of the following. In the initial phase of the flight, the excess fuel from the tank 17 by gravity is poured into the tank 10 via the intermodular TM 34, where it is mixed with the fuel available in the tank. CRM engines 6 receive fuel from tank 10 along line 11. The differential pressure of the liquid column caused by the difference in liquid levels in the system of tanks 17 and 10 allows dispensing with a system for regulating the overflow process, limiting the amount of overflowing liquid with a TM 34 cut-off time using valves 36 or 37 .

The advantage of the scheme with the reverse arrangement of tanks in the module 3 (figure 3) over the scheme with their direct location (figure 2) - in the absence of a start valve on the TM 11 CRM.

It is convenient to apply the two given schemes to LV using engines of the “closed” scheme operating on oxygen-kerosene fuel, for which the volume ratio of the components used is close to 2: 1. Then all three lateral PM will have the same length between each other and with the prototype modules.

The above modifications can be equipped with three autonomous PM (Fig. 4 (a), (b)). Additional RM will not affect the operation of the fuel system of the main layout. If the total capacity of all side blocks is the same, then in the first division there will be three RMs involved in the overflow of components, in the second - three autonomous RMs. Thus, the stepped pH, which favorably affects its effectiveness.

The installation of three additional autonomous PM significantly increases the load capacity of the launch vehicle, while the system does not complicate the overflow of components and does not deteriorate the symmetry of the layout.

The work of the seven-block modification of the launch vehicle with the component-wise placement of all transfused fuel in six side two-tank RM (Figs. 5, 6) is carried out as follows.

During refueling, the starting start valves 9, 12, 16, 19, 23, 26, 30, 33, 57, 60, 64, 67, 71, 74 are closed. Their opening corresponds to the beginning of engine start.

During pre-launch operations and in the initial phase of the flight, fuel valves 36, 37, 77, 78, oxidizer valves 43, 44, 45, 46, 83, 84, 85, 86 are open, valves 38 and 47 on their own CRM highways, and valve 87 on its own fuel line 18 PM 3 and valves 88 and 89 on its own oxidizer lines 22 PM 4 and 29 PM 5 are closed.

In the initial phase of the flight, the excess fuel located in the PM 51 is transferred to the central control center via the intermodular line 75, where it is used in the engine rocket engine block 6, and then to the accelerator 3 along the intermodular highway 34, where it is used in the liquid fuel engine block 13. At the same time, the excess oxidizer placed in accelerators 52 and 53 it is poured into the central combustion engine along the intermodular highways 79 and 80, where it is used in the engine rocket engine block 6, and then into the accelerators 4 and 5 along the intermodular highways 39 and 40. At this time, the fuel from the centralized fuel tanks, fuel from the tank 17 RM 3, the oxidizing agent from tanks 21 and 28 PM 4 and 5 are not used; or Use in small quantities. At time moments determined by the carrier measurement system and corresponding to the exhaustion of the excess of the corresponding fuel component in each accelerator, at the command of the control system, lines 75, 79 and 80 are closed and fuel overflow stops through them.

Synchronously with the overlapping of the intermodular fuel line 75, the valve 87 opens on the own fuel line 18 of the RM 3, and the fuel from the tank 17 begins to flow into the rocket engine block 13 and is transmitted to the CRM via the intermodular highway 34 for use in the rocket engine block 6. Synchronously with the last of the intermodular blocking oxidizer lines 79 and 80 fully open valves 88 and 89 on their own oxidizer lines 22 and 29 PM 4 and 5, and the oxidizer from tanks 21 and 28 begins to flow into the rocket engine blocks 20 and 27, and is also transmitted to the CRM via intermodular lines 39 and 40 for use in the rocket engine block 6. By the time of separation of the side PM 51, 52 and 53, the shut-off valves 77, 78, 83, 84, 85, and 86 located on the intermodular lines 75, 79, and 80 are closed. After the exhaustion of fuel reserves in accelerators 51, 52 and 53 to the technological residue, these lateral PMs are separated. The disconnection of the connectors 76, 81 and 82 takes place in the interval between the closing of the controlled shut-off valves installed on their respective inter-module TMs and the separation of the blocks.

The further work of the launch vehicle exactly corresponds to the work of the four-block modification of the launch vehicle with the component-wise placement of all the transfused fuel in three lateral two-tank RM and the upper location of the fuel tank containing an additional amount of component (Figs.

Compared with the prototype of the pH of the given scheme has the following advantages. The number of intermodular fuel lines and related elements is halved - from 12 to 6, which positively affects the reliability of the carrier, and 3 start valves installed on the side RM allow for a three-stage output circuit, which increases the mass of the load. Simplification of the design creates the prerequisites for reducing the cost of manufacturing LV blocks and operating costs. Due to the reduction of intermodular TM, the dry mass of the RM, especially the central mass, is also reduced, which increases the carrying capacity of the LV.

The above scheme is more convenient to apply to the LV using closed-circuit engines operating on oxygen-kerosene fuel, for which the volume ratio of the components used is close to 2: 1. Then all three side RMs will have the same length between themselves and with the prototype modules.

Four-block modification of the PH, using three single-sided side PM (Fig.7, 8), works as follows.

During refueling, the pre-start starting valves 9, 12, 16, 19, 23, 26, 30 and 33 are closed. Their opening corresponds to the beginning of engine start.

During pre-launch operations and in the initial phase of the flight, the fuel valves 36, 37, 96, 97, 100 and 101, the oxidizer valves 43, 44, 45, 46, 92 and 93 are open, the valves 38 and 47 on their own CRM highways are closed.

At the initial stage of the flight, a part of the fuel component located in RM 3, 4, and 5 is used in its own rocket engine modules, the other part enters the common collector of the corresponding component. From the common collector of the oxidizer lines, fuel is supplied to the oxidizer’s own highway 8 of the central combustion engine and to PM 3 to the oxidizer inlet pipe of the engine rocket unit 13 through intermodular ТМ 90. From the general collector of the fuel mains, fuel is supplied to the own fuel highway of 11 CRMs and to modules 4 and 5 to the input fuel nozzles of LRE blocks 20 and 27 according to intermodular ТМ 94 and 98.

When a certain amount of fuel residue in the tank PM 3 is reached, the intermodular TM 34 is shut off and the fuel supply from the PM 3 to the common collector of the intermodular fuel lines is stopped. Synchronously with this action, the valve 38 opens, and fuel from the tank 10 of the CRM begins to be supplied to its own engine block 6 of the CRM and to the PM 4 and 5.

When a certain amount of oxidant residue is reached in the tanks of modules 4 and 5, the intermodular lines 39 and 40 are shut off and the supply of oxidizing agent from modules 4 and 5 to the common collector of the intermodular lines of the oxidizer is stopped. In synchronism with these actions, valve 47 opens and the oxidizer from the tank 7 of the central combustion engine begins to be supplied to its own engine block 6 of the central combustion engine and to the PM 3.

After the fuel is exhausted in the tanks of the side PM to the technological residue, the intermodular fuel lines 90, 94 and 98 are simultaneously blocked. By the time of separation of the side PM 3, 4 and 5, shut-off valves 36, 37, 43, 44, 45, 46, 92, 93, 96 , 97, 100 and 101, located on the intermodular highways 34, 39, 40, 90, 94 and 98 are closed. The overlapping of intermodular TM is accompanied by a stop of the engines of the side RM, after which the hydraulic sockets 35, 41, 42, 91, 95 and 99 open and the RM 3, 4 and 5 are separated from the CRM.

Further flight of the CRM is autonomous. After the exhaustion of fuel reserves in the tanks of the CRM or the achievement of the required speed, its engines stop and the flight task is considered completed.

Compared with the prototype of the pH of the given scheme has the following advantages. In lateral PM, the number of tanks and associated systems is halved; in total, four PM in the carrier contain five fuel tanks. As a result, the complexity of manufacturing side modules and their dry weight were reduced, mainly due to the absence of an inter-tank compartment, one upper and one lower bottoms, and an internal tank pipeline. The absence of an inter-tank compartment leads to a certain decrease in the length of the PM. The absence of an internal tank fuel line simplifies the production and preparation of PM, and for reusable blocks - the technology of after-flight maintenance, and also removes the problem of its resistance to transverse loads at the return site.

The above scheme is more convenient to apply to oxygen-kerosene fuel vehicles using "closed" circuit engines for which the volume ratio of the components used is close to 2: 1. Then all three lateral PMs will have the same length and a high degree of unification, and the additional elements ensuring their rescue for the purpose of reuse will not differ between the fuel and oxidizing modules.

The four-block modification of the pH, using three single-sided side RM, can be retrofitted with three autonomous RM (Fig.9 (a), (b)). Additional RM will not affect the operation of the fuel system of the main layout. If the total capacity of all side blocks is the same, then three single-tank RMs will participate in the first division, and three autonomous RMs in the second. Thus, the stepped pH, which favorably affects its effectiveness.

The installation of three additional autonomous PM significantly increases the load capacity of the launch vehicle, while the system does not complicate the overflow of components and does not deteriorate the symmetry of the layout.

Three-stage seven-block modification of the pH, using six single-sided side PM (figure 10, 11), works as follows.

During refueling, the starting start valves 9, 12, 16, 19, 23, 26, 30, 33, 57, 60, 64, 67, 71 and 74 are closed. Their opening corresponds to the beginning of engine start.

During pre-launch operations and in the initial phase of the flight, fuel valves 36, 37, 77, 78, 96, 97, 100, 101, 108, 109, 112 and 113, oxidizer valves 43, 44, 45, 46, 83, 84, 85, 86, 92, 93, 104 and 105 are open, valves 38 and 47 on their own main circuits are closed.

The flight of the LV takes place in three stages. At the stage of operation of the first stage, valves 87, 88, and 89 are closed, fuel from blocks 3, 4, and 5 is not used or its minimum technological consumption is maintained. Some of the fuel components located in RM 51, 52 and 53 are used in their own rocket engine modules, the other part enters the common collector of the corresponding component. From a common collector of oxidizer highways, fuel is supplied to its own oxidizer 8 high-pressure fuel line, and also to PM 3 and 51 to inlet pipes of the oxidizer of LRE blocks 13 and 54 via intermodular ТМ 90 and 102. From a common collector of fuel highways, fuel is supplied to its own fuel main as well as modules 4, 5, 52 and 53 to the inlet pipes of the fuel blocks of the liquid propellant rocket engine 20, 27, 61 and 68 according to the intermodular ТМ 94, 98, 106 and 110.

When a certain amount of fuel residue is reached in the PM 51 tank, determined by the pH measurement system, the intermodular TM 75 is shut off and the fuel supply from the PM 51 to the common collector of the intermodular fuel lines is stopped. Synchronously with this action, valve 87 opens, and fuel from tank 17 PM 3 begins to flow into the common manifold of the intermodular fuel lines.

When a certain amount of oxidant residue is reached in the tanks of modules 52 and 53, the intermodular lines 79 and 80 are shut off and the supply of oxidant from the modules 52 and 53 to the common collector of the intermodular oxidizer lines is stopped. In parallel with these actions, valves 88 and 89 open, as a result of which the oxidizer from the tanks 21 and 28 begins to be supplied to the common collector of the intermodular oxidizer lines.

After the exhaustion of fuel in the tanks of the side PM 51, 52 and 53 to the technological residue, the intermodular fuel lines 102, 106 and 110 are simultaneously blocked. By the time of the separation of the side PM 51, 52 and 53, shut-off valves 77, 78, 83, 84, 85, 86, 104, 105, 108, 109, 112 and 113, located on the intermodular highways 75, 79, 80, 102, 106 and 110 are closed. The overlapping of the intermodular TM 102, 106 and 110 is accompanied by a stop of the engines of the side PM 51, 52 and 53, after which the hydraulic sockets 76, 81, 82, 103, 107 and 111 are opened and the PM 51, 52 and 53 are separated from the main PH arrangement.

In the future, the launch vehicle works as a four-block modification of the launch vehicle, using three single-sided lateral launch vehicles.

Compared with the prototype of the pH of the given scheme has the following advantages. In lateral PM, the number of tanks and associated systems is halved; in total, seven PM in the carrier contain eight fuel tanks. As a result, the complexity of manufacturing the modules and their dry weight were reduced, mainly due to the lack of an inter-tank compartment, one upper and one lower bottoms, and an internal tank pipeline.

The absence of an inter-tank compartment leads to a certain decrease in the length of the PM. The absence of an internal tank fuel line simplifies the production and preparation of PM, and for reusable blocks - the technology of after-flight maintenance, and also removes the problem of its resistance to transverse loads at the return site.

The above scheme is more convenient to apply to oxygen-kerosene fuel vehicles using "closed" circuit engines for which the volume ratio of the components used is close to 2: 1. Then all six lateral PMs will have the same length and a high degree of unification, and additional elements ensuring their rescue for reuse in combustible and oxidizing modules will be the same for each group of simultaneously detachable modules.

The five-block modification of the pH, using four single-sided lateral RM, which are pairwise combined into bundles (Fig.12, 13), works as follows.

During refueling, the starting start valves 9, 12, 16, 19, 23, 26, 57, 60, 64 and 67 are closed. Their opening corresponds to the beginning of engine start.

During pre-launch operations and in the initial phase of the flight, the fuel valves 36, 37, 77 and 78, the oxidizer valves 43, 45, 83 and 85 are open, valves 38 and 47 are closed on their own CRM highways.

At the initial stage of the launch of the launch vehicle, some of the fuel components located in the RM 3, 4, 51 and 52 are used in their own rocket engine modules, the other part enters the common collector of the corresponding component. From the common collector of the oxidizer lines, fuel is supplied to the CRM oxidizer's own line, and also to PM 3 and 51 to the oxidizer inlet pipes of the LRE blocks 13 and 54 via the intermodular ТМ 116 and 120. From the general collector of the fuel lines, the fuel is supplied to the own line of the 11 ЦРМ fuel, as well as modules 4 and 52 to the inlet nozzles of the fuel blocks of the liquid propellant rocket engines 20 and 61 according to the intermodular ТМ 114 and 118.

When a certain amount of fuel is reached in the tanks 17 and 58 of the modules 3 and 51, the inter-module lines 34 and 75 are closed and the fuel supply from the modules 3 and 51 to the CRM is stopped. Synchronously with these actions, the valve 38 opens and the fuel from the tank 10 of the TsRM begins to be supplied to the block of the liquid propellant rocket engine 6 of the TsRM.

Upon reaching a certain amount of oxidant residue in the tanks 21 and 62 of modules 4 and 52, the intermodular lines 39 and 79 are closed and the supply of oxidizing agent from modules 4 and 52 to the CRM is stopped. Synchronously with these actions, valve 47 opens and the oxidizing agent from the tank 7 of the TsRM starts to be supplied to the block of the liquid fuel engine 6 of the TsRM.

Until the moment of fuel production in the tanks of the side RM, the valves 36, 37, 43, 45, 77, 78, 83, 85 are closed, after which the hydraulic connectors 35, 41, 76, 81 are disconnected.

After the exhaustion of fuel in the tanks of the side RM to the technological residue, the bundles of blocks 3 and 4, 51 and 52 are separated from the main layout of the pH.

Further flight of the CRM is autonomous. After the fuel is exhausted in the tanks of the CRM or when the required speed is reached, its remote control is stopped, and the LV flight task is considered completed.

Compared with the prototype of the pH of the given scheme has the following advantages. In lateral PM, the number of tanks and associated systems is halved; in total, five PM in the carrier contain six fuel tanks. In addition, the number of tear-off hydraulic sockets is reduced by four, and shut-off valves - by eight units. As a result, the complexity of manufacturing the modules and their dry weight were reduced, mainly due to the lack of an inter-tank compartment, one upper and one lower bottoms, an internal tank pipeline; increased reliability of the process of separation of steps. The absence of an inter-tank compartment leads to a certain decrease in the length of the PM. The absence of an internal tank fuel line simplifies the production and preparation of PM, and for reusable blocks - the technology of after-flight maintenance, and also removes the problem of its resistance to transverse loads at the return site.

Despite the fact that the total number of intermodular highways has not decreased, some of them were redistributed to the side modules. As a result, the number of intermodular TMs passing through the CRM decreased from eight to four. This difference means the redistribution of part of the dry mass from the central to the lateral PM and, as a consequence, an increase in the mass of the payload.

The above scheme is more convenient to apply to the LV on fuel, the volume ratio of the components of which is close to 1: 1. Then all four lateral PM will have a close length with a high degree of unification.

A five-block modification of the PH using two single-tank and two two-tank lateral RMs, which are pairwise combined into bundles (Figs. 14, 15), works similarly to the five-block modification of the pH variant using four single-sided lateral RMs that are pairwise combined into bundles. A feature of the pH is the consistent emptying of the oxidizer tanks in each bundle. This is achieved by synchronous operation of the pressurization systems of tanks or by using a common system of pressurization of the oxidizer tanks in each bundle of lateral PM.

Compared with the prototype of the pH of the given scheme has the following advantages. In lateral PM, the number of tanks and associated systems is reduced. In total, five PMs in the carrier contain eight fuel tanks, for which six systems related to their operation are necessary, since the oxidizer tanks in the bundle can be served by unified systems. In addition, the number of tear-off hydraulic sockets is reduced by four, and shut-off valves - by eight units. As a result, the complexity of manufacturing the modules and their dry weight were reduced, mainly due to the absence of an inter-tank compartment, one upper and one lower bottoms in two of them, and in-tank pipeline in four; increased reliability of the process of separation of steps. The absence of an internal tank fuel line simplifies the production and preparation of PM, and for reusable blocks - the technology of after-flight maintenance, and also removes the problem of its resistance to transverse loads at the return site.

Despite the fact that the total number of inter-module lines increased by two, a significant part of them was redistributed to the side modules. As a result, the number of intermodular TMs passing through the CRM decreased from eight to four. This difference means the redistribution of part of the dry mass from the central to the lateral PM and, as a consequence, an increase in the mass of the payload.

The above scheme is more convenient to apply to the LV, the volume ratio of the fuel components of which is significantly different from 1 towards a larger volume of oxidizer. The installation of additional tanks with an oxidizing agent in modules containing tanks with fuel makes it possible to align the length of the lateral PM.

The seven-block modification of the pH using six single-sided lateral RMs, which are combined in two groups of three modules containing bundles of two modules (FIGS. 10, 16), works as follows.

During refueling, the starting start valves 9, 12, 16, 19, 23, 26, 30, 33, 57, 60, 64, 67, 71 and 74 are closed. Their opening corresponds to the beginning of engine start.

During pre-launch operations and in the initial phase of the flight, fuel valves 36, 37, 77, 78, 128, 129, 136 and 137, oxidizer valves 43, 45, 83, 85, 132, 133, 140 and 141 are open, valves 38 and 47 are closed on their own highways

At the stage of operation of the first stage, the valves 88 and 142 are closed, the oxidizing agent from blocks 4 and 52 is not used or is used in small quantities. Some of the fuel components located in RM 3, 5, 51 and 53 are used in their own LRE modules, the other part enters the common collector of the corresponding component. From a common collector of oxidizer lines, fuel is supplied to its own oxidizer line 8 of the central combustion engine, to its own oxidizer lines 22 and 63 of PM 4 and 52, and also to PM 3 and 51 to the oxidizer inlet pipes of the LRE 13 and 54 blocks of intermodular TM 116 and 120. From of the common collector of the fuel mains, fuel is supplied to the own fuel main of 11 ЦРМ, as well as to modules 4, 5, 52 and 53 to the inlet nozzles of the fuel blocks of the liquid propellant rocket engine 20, 27, 61 and 68 according to the intermodular ТМ 114, 118, 126 and 134.

When a certain amount of oxidant residue is reached in the tanks of modules 5 and 53, the intermodular lines 130 and 138 are shut off and the supply of oxidizing agent from modules 5 and 53 to the common collector of the intermodular lines of the oxidizer is stopped. In parallel with these actions, valves 88 and 142 open, as a result of which the oxidizer from the tanks 21 and 62 begins to be supplied to the common collector of the intermodular oxidizer lines.

By the time of fuel production in the side RM tanks 5 and 53, the valves 132, 133, 140 and 141 are closed, the hydraulic connectors 131 and 139 are disconnected.

After the fuel in the lateral tanks PM 5 and 53 has been exhausted to the technological residue, the valves 128, 129, 136 and 137 are closed, the connectors 127 and 135 are disconnected, and these modules are separated from the main PH assembly.

Further work of the PH arrangement does not differ from the work of the five-block modification of the PH variant, using four single-sided lateral RMs, which are pairwise combined into bundles (Figs. 12, 13).

Compared with the prototype of the pH of the given scheme has the following advantages. In lateral PM, the number of tanks and associated systems is halved; in total, seven PM in the carrier contain eight fuel tanks. In addition, the number of tear-off hydraulic sockets is reduced by four, and shut-off valves - by eight units. As a result, the complexity of manufacturing the modules and their dry weight were reduced, mainly due to the lack of an inter-tank compartment, one upper and one lower bottoms, an internal tank pipeline; increased reliability of the process of separation of steps. The absence of an inter-tank compartment leads to a certain decrease in the length of the PM. The absence of an internal tank fuel line simplifies the production and preparation of PM, and for reusable blocks - the technology of after-flight maintenance, and also removes the problem of its resistance to transverse loads at the return site.

Despite the fact that the total number of intermodular highways has not decreased, some of them were redistributed to the side modules. As a result, the number of intermodular TMs passing through the CRM decreased from twelve to four. This difference means the redistribution of part of the dry mass from the central to the lateral PM and, as a consequence, an increase in the mass of the payload.

The above scheme is more convenient to apply to oxygen-kerosene fuel vehicles using "closed" circuit engines for which the volume ratio of the components used is close to 2: 1. Then all six lateral PMs will have the same length and a high degree of unification, and additional elements ensuring their rescue for reuse in combustible and oxidizing modules will be the same for each group of simultaneously detachable modules.

A seven-block modification of the pH using four single-sided side RMs, which are pairwise combined into bundles, and two two-sided side RMs (Figs. 17, 18), works as follows.

During refueling, the starting start valves 9, 12, 16, 19, 23, 26, 30, 33, 57, 60, 64, 67, 71, and 74 are closed. Their opening corresponds to the beginning of engine start.

During pre-launch operations and in the initial phase of the flight, fuel valves 36, 37, 77, 78, 100, 101, 112 and 113, oxidizer valves 43, 45, 83, 85, 44, 46, 84, and 86 are open, valves 38 and 47 are closed on their own highways

At the stage of operation of the first stage, the valves 143, 144, 145 and 146 are closed, fuel from the TsRM, PM 5 and 53 is not used. A part of the fuel component located in RM 3, 4, 51 and 52 is used in the proprietary LRE modules, another part enters the common collector of the corresponding component. From a common collector of oxidizer lines, fuel is supplied to the oxidizer’s own line 8 of the central combustion engine, to the oxidizer’s own lines 29 and 70 of RM 5 and 53, and also to PM 3 and 51 to the oxidizer inlet branch pipes of the liquid-propellant rocket engines 13 and 54 via intermodular TM 116 and 120. From of the common collector of the fuel mains, fuel is supplied to the own fuel main 11 of the central combustion engine, to the own fuel mains 32 and 73 of the PM 5 and 53, as well as to the PM 4 and 52 to the fuel inlet nozzles of the LRE blocks 20 and 61 on the intermodular TM 114 and 118.

When a certain amount of oxidant residue is reached in the tanks of modules 4 and 52, the intermodular lines 39 and 79 are shut off and the supply of oxidant from these modules to the common collector of the intermodular oxidizer lines is stopped. In parallel with these actions, valves 143 and 145 open, as a result of which the oxidizer from the tanks 28 and 69 begins to be supplied to the common collector of the intermodular oxidizer lines.

When a certain amount of fuel residue is reached in the tanks of modules 3 and 51, the inter-module lines 34 and 75 are closed and the fuel supply from these modules to the common collector of the inter-module fuel lines is stopped. In parallel with these actions, valves 144 and 146 open, as a result of which the fuel from the tanks 31 and 72 begins to flow into the common manifold of the intermodular fuel lines.

By the time the hydraulic connectors are undocked, the shut-off valves 36, 37, 43, 45, 77, 78, 83, 85 are closing. After the fuel is exhausted in the lateral tanks PM 3, 4, 51 and 52, the tear-off hydraulic connectors 35, 41, 76, 81 are opened and the bundles of blocks 3 and 4, 51 and 52 are synchronously separated from the main PH assembly.

Further flight takes place with the use of fuel from two-tank side blocks, fuel from the tanks of the CRM is not used, or only its minimal technological consumption is ensured. When a certain amount of fuel remains in the tank 31 PM 5, the intermodular TM 98 is shut off and the fuel supply from the PM 5 to the central combustion engine stops. When a certain amount of fuel remains in the tank 72 PM 53, the intermodular TM 110 is shut off and the fuel supply from the PM 53 to the central combustion engine stops. Synchronously with these actions, the valve 38 opens, and fuel from the tank 10 of the CRM begins to be supplied to the engine block 6 of the CRM.

When a certain amount of oxidant residue in the tank 28 PM 5 is reached, the intermodular TM 40 is shut off and the supply of the oxidizer from PM 5 to the CRM is stopped. Upon reaching a certain amount of oxidant residue in the tank 69 PM 53 intermodular TM 80 is blocked and the supply of oxidant from PM 53 to the CPM stops. Synchronously with these actions, valve 47 opens, and the oxidizer from the tank 7 of the CRM begins to be supplied to the engine block 6 of the CRM.

By the time of fuel production in the lateral tanks PM 5 and 53, valves 44, 46, 84, 86, 100, 101, 112, 113 are closed.

After the exhaustion of fuel in the tanks side RM 5 and 53, the hydraulic connectors 42, 99, 82, 111 are disconnected and the blocks 5 and 53 are separated from the main layout of the pH. Further flight of the CRM is autonomous.

After the fuel is exhausted in the tanks of the CRM or the required speed is reached, the remote control of the CRM is stopped and the flight task is considered completed.

Compared with the prototype of the pH of the given scheme has the following advantages. In four lateral RMs, the number of tanks and associated systems is halved; in total, seven RMs contain ten fuel tanks in the carrier. In addition, the number of tear-off hydraulic sockets is reduced by four, and shut-off valves - by eight units. As a result, the laboriousness of manufacturing part of the modules and their dry weight was reduced, mainly due to the lack of an inter-tank compartment, one upper and one lower bottoms, an internal tank pipeline; increased reliability of the process of separation of the blocks of the first stage. The absence of an internal tank fuel line simplifies the production and preparation of PM, and for reusable blocks - the technology of after-flight maintenance, and also removes the problem of its resistance to transverse loads at the return site.

It is advisable to apply the above scheme to a LV using fuel with a volume ratio of components from 1.1 to 1.3 (for example, liquid oxygen - liquid methane). Then the single-tank units will have different lengths, but their axisymmetric arrangement around the DTM in two cases will preserve the aerodynamic symmetry of the layout: when the larger or smaller single-tank modules are the same length as the double-tank. The aerodynamic asymmetry of the layout in other cases will require relatively small additional energy costs, in other cases, adjusting the shape of the fairings of the first-stage modules. The latter will not lead to significant losses in the mass of the output cargo due to its low sensitivity to the weight of the design of the first stage.

The proposed LV arrangement can be used to launch payloads into circular and low perigee elliptical orbits, including geo-transition ones. In this case, no additional upper stage is required; all LV engines will be launched on the ground. A large range of values of the apogee of orbital elimination can be achieved by a simple technological method: lengthening or shortening the tanks of one-tank modules.

As follows from the description of this application, the proposed launch vehicle in all its variants provides increased reliability, reduced production costs and operating costs by reducing the number of structural elements, parts and components of on-board systems. In the first embodiment, the number of fuel lines, including tear-off hydraulic connectors and shut-off valves, as well as the corresponding control and monitoring subsystems, is reduced. In the second and third versions using single-tank modules, the number of fuel tanks, associated boost systems and monitoring of the state of fuel components, inter-tank compartments is reduced, and the total mass of the tank structure is reduced by reducing the number of bottoms and inside tank pipelines. In addition, in LV variants using single-tank modules, a reduction in production costs is achieved by reducing the volume of in-tank work. An additional increase in the reliability of LV modifications using bundles of single-tank units is achieved due to the fact that the fuel lines do not break between the bundle modules, or after they are separated from the CRM and does not affect the performance of the flight task.

All proposed variants of the modular launch vehicle are combined by a single inventive concept and meet the criteria of the invention.

Literature

1. SP Umansky "Launch vehicles. Cosmodromes", Moscow, publishing house "Restart +", 2001

2. "Cosmonautics", encyclopedia, 1985, Moscow, publishing house "SE", - "OTRAG"

3. Journal of Cosmonautics News "No. 3, 1999, p. 48.

4. US Patent No. 5,143,328 of September 1, 1992, B 64 G 1/00, B 64 G 1/40.

Claims (21)

1. A carrier rocket of a modular type on liquid fuel components, including a warhead and at least three rocket modules, each of which contains one fuel tank and one oxidizer tank, which together with the fuel lines connecting these tanks to the module rocket engine block, fuel volumes of the corresponding fuel component, while the central module is located coaxially with the head part, and the remaining modules are interfaced with the central lateral sides, equipped with separation means during flight and containing additional amount of fuel intended for overflow into other modules, a fuel overflow system and an oxidizer overflow system between the modules, including fuel lines laid between the side and central modules and having intermodular tear-off hydraulic connectors, as well as shut-off valves located on both sides of the detachable connections the fact that each of the side modules contains one component of the specified additional amount of fuel - fuel or oxidizer, with at least one m from the modules, the specified component of the additional amount of fuel is different than in the other modules, and the fuel volume of each side module containing fuel for overflow into other modules is connected to the fuel volume of the corresponding component of the central module by one inter-module fuel line. 2. The launch vehicle according to claim 1, characterized in that on the fuel lines of the Central module above the junction with the intermodular fuel lines installed trigger valves. 3. The launcher according to claim 1, characterized in that the tanks of the side modules containing an additional fuel component similar to that located in the lower tank of the central module have a reverse location relative to the location of the tanks of the central module, and the intermodular fuel lines of the component located in the upper the central module tank, connected to the fuel line emerging from this tank, on which a start valve is installed above the connection points. 4. The launch vehicle according to claim 2 or 3, characterized in that on it in the intervals between the side rocket modules additional rocket modules are installed, which are interfaced with the sides of the central module, are equipped with separation means during the flight and have an autonomous fuel system. 5. The launch vehicle according to claim 2 or 3, characterized in that all side modules of different stages containing the specified additional amount of oxidizing agent, except for the first ones to be separated, on their own oxidizer lines above the junction with the intermodular oxidizer lines have start valves. 6. The launch vehicle according to claim 2 or 3, characterized in that all side modules of different stages containing the specified additional amount of fuel, except for the first ones to be separated, have start valves on their own fuel lines above the junction with the inter-module fuel lines. 7. A carrier rocket of a modular type on liquid fuel components, including a warhead, a central missile module located coaxially with it, and at least two lateral missile modules, coupled to the central module on the sides and equipped with separation means during flight, a fuel component overflow system between rocket modules, including fuel lines, laid between the side and central modules and having tear-off hydraulic connectors and shut-off valves located on both sides of the detachable unities, characterized in that at least two side rocket modules are single-tank, of which at least one module contains a different fuel component than the remaining modules, the inter-module fuel lines of each component are combined into a common collector, through which the fuel volumes of single-tank modules including tanks and fuel lines containing one component connecting them to engines, are connected to fuel inlet pipes of engines in single tank modules containing another component, and e to fuel volume corresponding central module component. 8. The launch vehicle according to claim 7, characterized in that the manifold of the inter-module lines of the component located in the upper tank of the central module is connected to the fuel line leaving the tank, on which a start valve is installed above the junction. 9. The launch vehicle according to claim 7, characterized in that the collector of the component located in the lower tank of the central module is connected to the fuel line exiting from this tank, on which a start valve is installed above the junction. 10. A booster rocket according to any one of claims 7 to 9, characterized in that on it in between the one-tank side rocket modules, rocket modules with autonomous fuel systems are additionally mounted, which are mated laterally with the central rocket module and equipped with separation means during flight. 11. A booster rocket according to any one of claims 7 to 9, characterized in that all single-tank rocket modules of different stages containing an oxidizing agent, except for the first ones to be separated, on the fuel lines between their fuel tanks and their engines, above the junctions with the intermodular manifold manifold oxidizer have start valves. 12. A booster rocket according to any one of claims 7 to 9, characterized in that all single-tank rocket modules of different stages, containing fuel, except for the first to be separated, on the fuel lines between their fuel tanks and their engines, above the junction with the intermodule manifold fuel have start valves. 13. A booster rocket according to any one of claims 7 to 9, characterized in that at least two lateral one-tank rocket modules are paired together in bundles in which the rocket modules contain different fuel components, are mated laterally with each other, fastened between power connections with the possibility of simultaneous separation of these modules without breaking the power connections between them, and the fuel volumes of each of the modules are connected to the inlet pipes of the corresponding fuel component of the engine block of the other module using modular fuel lines with connectors in the intermodule space. 14. The launch vehicle according to claim 13, characterized in that in one of the modules of each bundle above the main fuel tank an additional tank is installed with a component different from the main tank, and a fuel line is laid from the additional tank to the tank of the other bundle module, having a connector in the intermodule space. 15. The launch vehicle according to claim 13, characterized in that the power connections in the bundles of the modules, as well as the connectors on the fuel lines laid between the bundle modules, are capable of breaking in flight, on the fuel lines laid between the bundle modules, from both shut-off valves are installed on the sides of the detachable connections, and the modules themselves are equipped with in-flight dilution means and means of ensuring a soft landing. 16. The launch vehicle according to item 13, wherein each bunch of side rocket modules is grouped with an additionally installed single-tank rocket module so that it is mated laterally with one of the bundle modules, and its fuel volume, as well as its block inlet engines of the fuel component not contained therein are connected to the fuel volumes of the respective components of the bundles of modules, including fuel tanks, proprietary and intermodular fuel lines located in the modules, intermodular fuel backbones, inter-module having a tear gidrorazemy and shut-off valves on both sides of the plug connections, the additional installed modules are equipped with means of separation during the flight. 17. The launcher according to clause 16, characterized in that on the own fuel line of each module included in the bundle and containing in the main tank the same fuel component as the additional modules, a start valve is installed above the junction with the inter-module fuel lines. 18. A carrier rocket of a modular type on liquid fuel components, including a warhead, a central missile module located coaxially with it and two lateral two-tank missile modules, interfaced with the central module on the sides and equipped with separation means during flight, a component overflow system between missile modules including fuel lines laid between the side and central modules and having intermodular tear-off hydraulic sockets and shut-off valves located on both sides of the connector volumetric connections, characterized in that in it between the side two-tank modules there are bundles of two single-tank missile modules, conjugated by the sides with each other, containing different fuel components and fastened together by power bonds with the possibility of separating these bundles of modules without breaking power bonds, the fuel volume of each of the bundle modules is connected to the inlet pipe of the corresponding fuel component of the engine block of the other bundle module using the intermodular fuel master it with the connectors into the inter-module space. 19. The launch vehicle according to claim 18, characterized in that the fuel volume of each of the ligament modules is also connected to the fuel volume of the corresponding component of the adjacent two-tank side module using an inter-module fuel line having tear-off hydraulic connectors and shut-off valves on both sides of the detachable connection, wherein the intermodular fuel lines of the fuel component located in the upper tanks of the side two-tank modules are connected to the fuel lines exiting from these tanks, at which there are higher junction points mounted actuating valves. 20. The launch vehicle according to claim 19, characterized in that the fuel lines between the two-tank and one-tank modules of a fuel component located in the lower tanks of the side two-tank modules are connected to the fuel lines leaving these tanks, on which start valves are installed above the junction points. 21. The launch vehicle according to claim 19 or 20, characterized in that the fuel lines between the side and central two-tank modules are connected to their own fuel lines of the central module, on which start valves are installed above the junction points.

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