RU2035358C1 - Recoverable launch vehicle and multiple configurration transportatioon system - Google Patents

Abstract

FIELD: rocketry; systems provided with power plants together with orbital shuttle-type vehicle or other vehicle carrying payload. SUBSTANCE: recoverable launch vehicle has at least one partially recoverable unmanned unit of first stage which may be used for performing operations involved in injection to orbit by one stage of this unit which carries payloads inside or outside; it may be also used as part of multi-stage orbital injection system for injecting heavier payloads. First-stage unit is detachably secured to other units of first stage, passive units carrying load and/or manned space vehicles. The first-stage unit may be fully expendable after launch. EFFECT: enhanced economical and operational efficiency of system which may be used with many different modules for creation of many launch configurations. 11 cl, 9 dwg

Description

 The invention relates to rocket technology, namely, systems and methods for launching rockets into outer space. In particular, the invention relates to systems having power plants in combination with a shuttle-type orbiter or other payload aircraft.

 The space shuttle [1] is a multilateral aircraft with the basic characteristics of a spacecraft, at the same time in some respects resembling an airplane. The space shuttle is launched into outer space using rocket engines in exactly the same way as a regular space ship does, and returns from outer space like an airplane by planning to descend through the atmosphere and land on the runway. The development of the space shuttle is a significant achievement, as it marks the arrival of an elementary space transport system. A system is foreseen that will enable a person and a cargo to perform elementary shuttle flights into outer space and vice versa, thereby providing the possibility of servicing, repairing and refueling a spacecraft, creating large-sized structures, such as production equipment, and, ultimately, structures in space space settlements.

 Technically, a space shuttle consists of an orbital vehicle containing shuttle marching engines, an external tank containing rocket propellant for lift used by the marching engines, and two solid propellant rocket boosters. The orbital aircraft and rocket boosters are reusable, while the external tank is consumed at each launch. When launched, two solid propellant rocket engines and three liquid propellant rocket engines start and operate simultaneously. The orbital aircraft, together with the crew and payload, remains in orbit to fulfill its mission, usually for about 7 days, but if necessary for a longer period of time, up to 30 days. After completing the mission, the orbiting aircraft returns to Earth and lands like an airplane.

 While the space shuttle was the main step forward in space exploration, there are still a number of problems that prevent the most efficient, economical, and expedient way of operating such a shuttle system. So far, few attempts have been made to improve the space shuttle to ensure its greater flexibility.

 One of the main problems associated with the space shuttle is that the orbital aircraft, a spaceship that looks like a plane with a triangular wing, must be attached to the external tank and systems and also contains three liquid-propellant rocket engines with their associated systems. Fuel tank, residual fuel after engine shutdown, rocket engines add significant weight to the total weight brought into orbit close to it.

 In addition, and even more importantly, engines and fuel delivery devices minimize the amount of space for placing cargo inside an orbital aircraft. This means that there is a need to reduce the volume and weight of the payload. Although an orbital aircraft can deliver up to 25 tons of internal payload into orbit, the weight of this load is only 1/7 of the total weight put into orbit.

 Another problem associated with the space shuttle is the lack of flexibility, since it ensures the fulfillment of only one type of space flight (mission) with a strict restriction on the size and weight of payloads put into orbit. Thus, space flight programs should be developed taking into account the capabilities of the space shuttle and its limitations. Space shuttles contain a cargo compartment and marching engines. Since they are expensive and difficult to manufacture, at any given time, several such shuttles should usually be in operation. Transportation to outer space is limited when orbiting aircraft are inoperative for maintenance or while they are in orbit. Thus, for example, orbital aircraft cannot be used for long-term manned space flights without severely limiting launch capabilities. They must be quickly returned to Earth to support launch operations. This limits the time it takes to conduct in-orbit research and could critically limit the delivery and assembly of a space station or the implementation of other major space flight projects.

 The invention proposes the creation of a launch vehicle with a multi-purpose multi-component space transport reuse system, in which a plurality of modules are provided that can be interconnected to form various possible arrangements according to the requirements of a particular space mission. The main part of the system is the first stage unit, which is selectively used as an independent device, put into orbit by one stage, or as one stage of a multi-stage arrangement. The first stage unit is reusable and has an appropriate device for returning to Earth.

 The closest from a technical point of view both for the launch vehicle and for the multi-component transport system, it is possible to adopt a launch vehicle [2] containing many cylindrical modules, one of which is made in the form of at least partially disposable first-stage unmanned unit with a main propulsion system , and one more in the form of a payload block, attached with the possibility of removal from the outside to the block of the first stage.

 The disadvantages of this launch vehicle are that the launch configuration of the modules is constant and the first stage unit is not able to selectively be used as an independent single-stage rocket, orbited or as a multi-stage configuration with attachment points for the choice of one or more additional identical or different modules .

 The proposed reusable launch vehicle, which differs from the known one in that for the selective transportation of various payloads into outer space, it contains many different modules that can detachably interconnect with each other to form various possible arrangements. The modules include a first stage unit, which is at least partially consumable and contains a propulsion (propulsion) propulsion system to provide sufficient traction to bring payloads up to a predetermined weight in or close to orbit, a payload block to accommodate payloads and at least one second-stage unit or auxiliary unit for selectively connecting to the rest of the system, including a second-stage propulsion system to provide additional traction for outputting orbit payloads with more weight or payloads into deep space. Each of the blocks can be individually attached to any other block, and several blocks of the same type can be used in the selected starting layouts. The payload block may be a simple passive payload container attached externally or internally to the first stage block, or it may include an orbital vehicle for manned orbit flight, including a cargo compartment and orbit maneuvering devices or engines. Both types of payload blocks are preferably implemented as system modules. The second stage blocks are rocket boosters or rockets of much smaller sizes than the first stage blocks, which provide the main thrust.

 Preferably, the first stage unit includes a cargo compartment and is preferably used as an apparatus to be put into orbit in one stage, as well as an integral part of various multi-stage arrangements. The block is fully or at least partially consumed after startup. If desired, the engines and electronic equipment can be separated when the unit returns to Earth and can, for example, be saved using a suitable parachute system. However, in the simplest case, the entire block is expendable and is completely lost after startup. If it is used as a device that is put into orbit in one step, then it usually puts a small payload into orbit, releases the payload and remains in orbit or subsequently falls to Earth.

 The first stage unit in the preferred embodiment of the invention is made in the form of a simple cylindrical fuel tank of a type similar to the outer tank of the present space shuttle and including liquid rocket engines having an additional internal volume for the cargo. The unit has various attachment points for selectively attaching it to a payload container, orbital aircraft, second-stage units or to other first-stage units to provide increased payload. The attachment points in the preferred embodiment should be similar to those currently available in a standard space shuttle launch vehicle. Preferably, the unit also has its own internal compartment for the payload and is intended for the flight of the apparatus without a crew when used as an apparatus put into orbit in one step.

 In a preferred embodiment, the first stage unit has from three to eight engines, which may have a thrust equivalent to the thrust of the currently used space shuttle engines, all of which are located at the rear end of the first stage unit. In the front part there are tanks with liquid rocket fuel. In an alternative embodiment, other fuels may be used to provide the required traction. This relatively simple and expendable main launch vehicle provides a wide variety of launch capabilities and the ability to perform various space exploration tasks at relatively low cost. Two or more of these main launch vehicles can be joined together to increase payload.

 With the help of such a block of the first stage, an orbital aircraft similar to a real shuttle orbital aircraft, but without bulky and heavy marching engines of the space shuttle, can be launched into outer space. The orbital aircraft can be separated from the first stage unit at any time and then the first stage unit can be returned to Earth and reused if necessary. Thus, the orbital aircraft can remain in outer space for a longer time and may have a greater payload, since the marching shuttle engines are removed from the aircraft. The aircraft can have an increased amount of rocket toll for the maneuvering system in orbital flight compared to standard space shuttles and a longer cargo compartment, which makes it possible to transport more voluminous payload into outer space.

 To increase the carrying capacity and provide the possibility of transportation into deep space, a second-stage unit or auxiliary rocket engine can be used. It can be in the form of solid fuel rocket boosters attached to the first stage unit, or in the form of external suspension missiles that can dock either to the first stage unit or to an orbital aircraft launched by the first stage unit. The auxiliary units may be liquid hydrogen and oxygen rockets, or rockets containing any suitable rocket fuel, and preferably also be consumable.

 Thus, one possible layout of the proposed launch vehicle includes one block of the first stage, containing a payload for putting into orbit. In this case, the first stage unit may include either an internal payload compartment or external payload containers attached to the unit.

 A multi-component transport system is a combination of a first-stage unit with suitable auxiliary devices, for example rocket boosters similar to those currently used in the space shuttle, or auxiliary external launch vehicle having suitable rocket fuel to enable the first-stage block to put heavier useful ones into orbit load. In a modified arrangement, two or more first stage blocks could be arranged with the formation of cylindrical structures with parallel operation by providing suitable ringing of the rocket fuel supply system, as is done in the present space shuttle system. A system with many first-stage blocks of this type could be used with additional rocket boosters or external suspension blocks to provide additional thrust to it and could work as a multi-stage aircraft designed to launch superheavy payloads into orbit. Payload containers could be attached to first stage units externally or placed inside them in suitable payload compartments. In an alternative embodiment, for launching a large container with a payload into orbit, several blocks of the first stage could be located in a bundle looped over rocket fuel around the container and work in parallel or in multi-stage mode to bring the container into orbit.

 Thus, the proposed modular multicomponent space transport system is relatively simple, flexible and makes it possible to transport payloads of various weights into orbit or deep space by a suitable choice of blocks that must be joined together detachably. Instead of specifically developing the entire new rocket propulsion system for each new payload or solving new space problems, the existing modular system can be used by simply connecting the required modules for launch to each other. The blocks in the preferred embodiment are expendable, with the exception of any orbital aircraft with crew, making launches less difficult and the design of individual aircraft less complex and thus less expensive. Improved orbital aircraft, which do not include marching engines, are less expensive to manufacture and, therefore, can be more affordable, improving the transport coefficient of availability and allowing orbital aircraft to remain in space for a longer time without severely limiting launch capabilities.

 In FIG. 1 shows a main part or block of a first stage of a reusable launch vehicle, side view; in FIG. 2 shows a first stage unit shown in FIG. 1 is a rear view illustrating an arrangement of engines; in FIG. 3 shows a first stage unit attached to an external tank or payload unit, side view; in FIG. 4 shows an alternative nose mount for a payload block; in FIG. 5 shows an alternative starting arrangement with two consumable main parts and a payload block; in FIG. 6 shows another possible system layout using a first stage unit and two rocket boosters, side view; in FIG. 7 shows a multi-layout transport system in which a parallel arrangement of first-stage blocks is used to bring a payload container into outer space, side view; in FIG. 8 shows the starting arrangement of FIG. 7, top view; in FIG. 9 is a perspective view of another possible launch arrangement using one first stage unit, an orbital aircraft and rocket boosters.

 In FIG. 1 and 2 show the base unit of the first stage or the main unit 1 of the preferred embodiment of the proposed reusable launch vehicle. Block 1 is at least partially or completely expendable or of a one-time action (in other words, no means are provided for returning the block to the Earth after launch) and can be used as an apparatus put into orbit in one step, as shown in FIG. 1, or may be selectively attached to various other blocks or modules to form many possible alternative starting arrangements.

 The modular blocks of the launch vehicle include a first-stage unit or main unit 1, auxiliary propulsion systems, including solid-state rocket boosters 2, which are detachably attached to the first-stage unit 1 (Fig. 6 and 7), an orbital aircraft 3 (Fig. 9), another type of auxiliary power plant, including wing tanks or rockets 4 of the external suspension, and cargo containers or blocks 5, 6 without engines of various sizes (Figs. 3-5, 7 and 8). These modular units are used in various possible launch and orbital arrangements according to the required payload and transportation. Payload containers or freight containers 5, 6 are unmanned payload containers that can preferably be detachably attached to a first stage unit and similarly to other units. Payload containers can have various sizes. Thus, each of the modular units can be detachably attached to any other unit according to the desired starting arrangement and payload weight.

 Block 1 of the first stage is a reusable launch vehicle, which is able to operate as a device, put into orbit in one stage. It is similar in appearance to the outer tank of the space shuttle. At the rear end of block 1 are eight engines 7 (Fig. 2). The housing 8 of the block 1 has a generally cylindrical shape, the front end 9 of which has a conical shape. Engines 7 are designed to provide sufficient traction to bring the device into the desired orbit. They are high-thrust engines and can be of a similar or identical type with marching engines of the space shuttle. For increased payload, launch vehicles can have up to eight marching engines. The engine 7 may use any suitable propellant, and unit 1 has suitable fuel tanks mounted in a cylindrical housing 8. The fuel tanks may include separate compartments for liquid oxygen, liquid hydrogen, solid or liquid hydrocarbon fuel, or any other suitable combination of fuel to produce useful loads in outer space. In a preferred embodiment, the mid-flight engines use liquid hydrogen and oxygen as rocket fuel, which are also used in the space shuttle mid-flight engines supplied from an external tank.

 In the embodiment shown in FIG. 2, engines 7 are used in two different types, including an outer ring of four small rocket boosters 10, which are stationary engines used from the moment of launch to reaching a height of 5-6 km, and two large central main engines 11 with thrust vector control for operation in space. Smaller engines can be marching engines of the space shuttle or equivalent, while larger engines can be standard marching engines of the space shuttle or equivalent types of engines. Alternatively, the outer ring may include six starting motors for increased payload or a plurality of smaller thrusters, such as RL-10 or equivalent engines, which replace the motors 7 shown in FIG. 2, for example, eight or more RL-10 engines can provide the ability to enter into orbit in one step.

 Preferably, the first stage unit also includes a suitable cargo compartment designed to accommodate the payload. Preferably, the first stage unit 1 is compatible with existing space shuttle attachment points (zones), solid rocket boosters and launch pad. Around the lower end of block 1, locking posts 12 of the launch pad are provided, as in a shuttle system. The attachment point or the mating surface 13 serves to connect the block 1 with the block 5 payload, orbital aircraft or other modular blocks in alternative layouts. Two or more such attachment points are provided in order to enable the main unit 1 to be connected to one or more additional devices. Preferably, a fastening device is also provided to enable, for example, selective attachment of the payload block to one side of the block 1, as shown in FIG. 3, or to its bow, as shown in FIG. 4. Nasal fixation provides higher payload.

 Preferably, the mounting location is set to provide the required interchangeable detachable mechanical connection, as well as two-way communication (exchange of information) and to provide the ability to supply fuel from one device to another. An electrical or power connection may also be provided.

 The exchange of information between the device can be provided through a physical connection or remotely via radio signals. At an appropriate height, unit 1 of the first stage is separated from the orbital aircraft or other modular unit and usually falls to Earth. Other attachment zones of a similar nature (not shown in the figures) are used for releasably attaching solid rocket boosters, wing tanks or payload containers around unit 1 of the first stage in various possible starting arrangements. A suitable nose attachment area is provided for selectively detachably attaching the payload block to the nose of the device, as shown in FIG. 4. This nasal attachment area should be of the standard type with all the necessary mechanical, electrical and fluid connections, but should be modified similarly to the lateral attachment area to allow two-way transmission of information, rather than one-way.

 A consumable first stage unit is the main part of the proposed reusable launch vehicle.

 Solid propellant rocket boosters 2 (Fig. 6) are detachably attached to one or more blocks of the first stage through mounts 14 to enable the launch of heavier payloads into outer space. The same attachment zones can be used to selectively attach either accelerators 2 or payload blocks. Accelerators 2 may be of the same type used in the space shuttle. Each of the accelerators mainly includes a cylindrical housing 15 having a conical part 16 at the front end and a motor 17 at the rear end. The engine 17 is a suitable solid-state motor and serves to provide accelerator traction during the start-up process. The conical portion 16 of the housing 15 facilitates passage through the atmosphere of the Earth and can serve as a container for accommodating a landing parachute for returning the accelerator to Earth. Alternatively, accelerators 2 may be disposable. External surfaces may be coated with suitable material to provide thermal protection when entering dense atmospheric layers.

 Accelerators 2 are detachably attached to the first stage unit 1 in the same manner as is done in the existing shuttle system. For example, they can be used when it becomes necessary to launch goods having too large dimensions or weight. During the development of solid rocket fuel, accelerators 2 are separated from block 1 and returned to Earth, where they are lost if they are expendable blocks, or can be saved and refilled with fuel for later use.

 In alternative embodiments, solid rocket boosters can be grounded by rockets with suitable liquid propellants of equivalent thrust, for example, using liquid hydrocarbons, liquid oxygen and liquid hydrogen, or other suitable liquid fuel.

 The orbital aircraft 3 shown in FIG. 9 is similar to an orbiting spacecraft such as a space shuttle, but it lacks three main engines and a rocket fuel compartment is provided at the rear of the shuttle. The thrust of the three main engines is provided in the proposed launch vehicle in the first stage unit, and the removal of these engines from the orbital aircraft significantly reduces its weight and provides a larger volume for placing additional cargo. The orbital aircraft includes an orbital flight maneuvering system 18, similar to that used in the space shuttle, but with an excess of rocket fuel to bring the aircraft into orbit.

 The outer casing of the orbital aircraft 3 is very similar to a space shuttle, including a nose section 19 at the front end, in which control panels and a pilot cabin are located, a cargo compartment 20 where experiments are performed, various power sources are stored, tools are stored, and fixed wings 21. Cargo the compartment is much longer than the compartment used in this aircraft, due to the lack of mid-flight engines and associated control devices and fuel systems. Thus, the cargo compartment extends to the rear loading hatches. The cargo compartment has an upper hatch for access to outer space, as is the case in the space shuttle. The wings 21 have a sharp external shape and extend tangentially from the cylindrical part of the body of the apparatus 3. The front edge 22 of the wings is covered with a layer of carbon. In the rear of the apparatus 3 extends up the steering wheel 23, almost perpendicular to the plane of the wings 21.

 The orbital aircraft may be provided with a rotary wing instead of the fixed wings 21, which may be equivalent to a rotary wing mounted on the block of the first stage. Shot nasal rudders may also be provided. The maneuvering system 18 includes a suitable rocket engine or engines located at the rear end of the orbital aircraft, which communicate with the nozzle or nozzles 24. The system 18 serves as a small thrust maneuvering engine for the orbital aircraft 3 when it is in or near orbit . There is no need to use this system in all cases with a certain initial range of active flight, although in some cases this can be done. The maneuvering system 18 may have any suitable propellant stored in tanks at the rear end of the orbital aircraft, such as liquid hydrogen and oxygen. In a preferred arrangement, the maneuvering system is equivalent to the system available on the space shuttle, but having a larger fuel supply.

 Another type of modular block shown in FIG. 9 is an auxiliary unit including a wing tank or an external suspension rocket 4. In the device shown in FIG. 1, two such missiles 4 are shown for detachable attachment to the wings of an orbital aircraft 3. However, alternatively, they can similarly attach to a first stage unit. Preferably, the rockets 4 are rockets with a liquid hydrogen and oxygen engine, which are primarily intended to be attached to the payload, but may have looped power systems with a first stage unit 1.

 Rocket 4 resembles in appearance a solid fuel rocket accelerator 2, but shorter and much lighter. In a preferred arrangement, its weight is 1/20 of the dry weight of the accelerator 2, and it is designed to operate at high altitude up to outer space or as an accelerator for long-distance space flights or supply aircraft. After full fuel consumption rockets 4 are separated and lost.

 The rocket 4 has an almost cylindrical main body part 25 with a conical nose 26 at the front end and an engine nozzle or nozzles 27 protruding from its rear end. In cross section, rocket 4 is almost the same as block 1. Inside rocket 4 there is one or more tanks for rocket fuel.

 Another selectable modular block of the launch vehicle shown in FIG. 3, 4, 5, 7, and 8, is a payload unit or container 5, 6, which is a simple passive container for accommodating a cargo brought into orbit or delivered to an orbital aircraft or space station. Such a unit is detachably attached to a first stage unit, and also similarly to an orbital aircraft 3. Blocks 5, 6 may have different sizes depending on the weight of the payloads. In FIG. 3, 4 and 5 show a smaller block 5, in FIG. 7 and 8, a block 6 is shown for a larger payload having increased dimensions.

 Various blocks of a reusable modular launch vehicle can be selectively attached to each other with the formation of various launch arrangements according to the weight of the payload and the need to solve particular problems of space flight, i.e. launching into orbit, launching into deep space, making long flights, constructing a space station, etc. Some of the various possible layouts of the proposed launch vehicle are presented below. Estimated load ratings for various layouts are given.

Примерая грузоподъемность/ т

1. Блок 1 (шесть маршевых двигате-

лей) с боковым закреплением

блока 5 (фиг. 3)

12 2. Блок 1 (шесть маршевых двигате-

лей) с носовым закреплением

блока 5 (фиг. 4)

24 3. Связка из двух блоков 1 (шесть

маршевых двигателей в кажом)

(фиг. 5)

100 (полная) 4. Блок 1 (восемь маршевых двига-

телей) с боковым закреплением

полезной нагрузки

30 5. Блок 1 (восемь маршевых двига-

телей) с носовым закреплением

полезной нагрузки

40 6. Своенный блок 1 (восемь мар-

шевых вигателей)

150 (полная) 7. Блок 1 с полуторной ступенью

(т.е. двумя вспомогательными

ракетами 4)

30-60 8. Блок 1 с восемью двигателями

RL-10

приблизительно 3-5 9. Сдвоенный блок 1 с восемью

двигателями RL-10 в каждом

приблизительно 8.Starting lineups

Approximate lifting capacity / t

1. Block 1 (six marching engines

lei) with lateral fastening

block 5 (Fig. 3)

12 2. Block 1 (six marching engines

lei) with nasal fixation

block 5 (Fig. 4)

24 3. A bunch of two blocks 1 (six

marching engines in each)

(Fig. 5)

100 (full) 4. Block 1 (eight marching engines

tel) with lateral fastening

payload

30 5. Block 1 (eight marching engines

calves) with nasal fastening

payload

40 6. Own block 1 (eight mar-

neck wiggers)

150 (full) 7. Block 1 with one and a half step

(i.e., two auxiliary

rockets 4)

30-60 8. Block 1 with eight engines

RL-10

approximately 3-5 9. Double unit 1 with eight

RL-10 engines in each

about 8.

 These and other possible arrangements are described in more detail below.

 In FIG. Figures 1 and 2 show the use of one main unit 1 as an apparatus put into orbit in one step. This makes it possible to launch a payload located inside, for example, a satellite, which must be launched into outer space, while the weight of the payload depends on the thrust of the engine of block 1. With an increase in the number of engines in this block, the weight of the payload put into orbit with it can increase .

 In FIG. 3 shows one payload block or container 5 with lateral fastening on block 1. This makes it possible to put into orbit payloads having a weight in the range of 10-30 tons depending on the thrust of the engines of block 1. With the nose fastening of container 5 on block 1, as shown in FIG. 4, the carrying capacity is increased to a weight in the range of 20-40 tons due to the reduced weight of the container and its supporting structures.

 In FIG. Figure 5 shows an alternative starting arrangement for launching very heavy payloads, in which two blocks 1 are connected together in parallel with the container 5 securing between them. This increases the maximum full payload to 100-150 tons depending on the number of engines in blocks 1. For To obtain the maximum net payload, it is necessary to subtract the weight of the supporting structure of the container 5 from the full payload. Preferably, in the interval between the two blocks 1, the power system is ringed fuel unit of the first stage (not visible in Fig. 5) to increase capacity. This arrangement provides a significant gain in capacity.

 In FIG. Figure 6 shows another potential launching arrangement using block 1 and two auxiliary rockets 4. With this arrangement, block 1, carrying a heavier payload, can be launched into a low orbit around the Earth. This is equivalent to the so-called one and a half stage.

 In FIG. Figures 7 and 8 show an arrangement for putting relatively large and heavy payloads into orbit. This arrangement uses a bunch of four parallel blocks 1 to launch one massive container 6 with a payload. This type of arrangement can be used as a multi-stage launch vehicle to launch very large payloads into orbit. In the interval between the blocks of the first stage, a ringing of the fuel supply system 28 can be provided and the layout can include two or more auxiliary rocket engines 2. All of these engines are detachably attached to the container 6 with the payload by means of fasteners 29. The container 6 is similar in shape to the smaller container 5 and has a cylindrical body with a usually conical nose.

 In FIG. 9 shows a launch arrangement including a unit 1, an orbital aircraft 3 and two wing missiles with external suspension detachably attached to the lower surfaces of the wings 21 of the orbital aircraft 3.

 In the embodiment shown in FIG. 9, block 1 is designed to supply rocket fuel to the auxiliary units during the launch process by means of suitable fuel pipelines (not shown) and is separated from the orbital aircraft and auxiliary units upon reaching a speed of several hundred meters per second near the orbit. After separation, the first-stage block falls to the Earth. Then, the orbital aircraft and wing missiles enter a low orbit around the Earth. Calculations show that an orbital aircraft and two wing rockets could reach an orbit with a payload of 50 tons and a total weight of about 20 tons of rocket fuel in two wing rockets. Fuel could be transferred from one winged missile to another. Wing missiles could generate fuel and be returned to Earth after emptying to prepare for their reuse.

 In all possible layouts, the first-stage unit and its marching engines continue to provide traction up to the full consumption of rocket fuel. Alternatively, the motors can be divided into steps. Propellant is supplied from suitable tanks located inside the unit to the engines during the launch and the launch vehicle reaches a speed close to orbital. Excess fuel can be transmitted to wing missiles 4, for example, during or after launch.

 Block 1 of the first stage is separated from the orbital aircraft at a lower inertial speed than when performing the corresponding operation of separating the external tank from the orbital aircraft in the space shuttle. Block 1 is separated when it reaches a sufficiently close orbital speed and altitude to allow wing missiles 4 or an enhanced maneuvering system in orbital flight of an orbital aircraft to put it into orbit.

 After separating the orbital aircraft and wing missiles from block 1, the latter provide traction for launching the orbital aircraft into orbit. Upon reaching the final or transitional trajectory, the wing missile engines are turned off.

 Wing rockets are used not only in the process of launching into orbit, but additionally for transporting small cargoes and / or fuel from the Earth to consumers in space or for moving cargo or fuel from one object to another (for example, from a space station in low orbit around Earth, to the geodetic satellite). For this purpose, cargo compartments may be provided in the wing missile body part. Missiles 4 can be designed to carry out the operation of pulling cargo from the container of the orbital aircraft, for example, by pulling it to their bow and transporting it to another place. This, in particular, can be useful in the case of the construction of space stations, etc.

 In addition, fully loaded wing missiles can be provided in orbit around the Earth for attachment to an orbital aircraft after launch. One, two, three, or four such missiles can be attached to one orbital aircraft in outer space to ensure that a fully loaded orbital aircraft reaches speeds of about 12, 24 or 36 km / s to exit from a low orbit around the Earth. Thus, an orbital aircraft combined with various reusable winged missiles can provide cost-effective access to deep space. The time spent on most critical consumables on an orbital aircraft can be extended by using propellant from attached winged missiles or by using the increased payload of the orbital aircraft as a result of the removal of the main engines. Thus, much longer space flights or deep space flights can be performed. The auxiliary unit or wing missile may, in alternative embodiments, comprise a simple fuel tank of an external suspension without an engine for supplying fuel to a maneuvering system in orbital flight of an orbital vehicle or other internal systems.

 Although in the embodiment shown, the first stage unit has six main engines having suitable propellant, such as liquid hydrogen and oxygen, any alternative engines and fuel can be used to communicate the required thrust, and more or fewer engines can be used. In general, a first stage unit may have from three to ten engines. The fuel for the engines is contained in the respective tanks inside the housing 8 of the block 1. Thus, instead of the main engines, many small engines can be used.

 Block 1, which forms the basis of a reusable modular launch vehicle, is preferably used both as an apparatus put into orbit in one step, and as a single-stage accelerator for putting other payloads into orbit around the Earth or close to it. Alternatively, a smaller main unit can be designed, designed only to reach the Earth’s orbit and used with small launch vehicles, which are detached immediately after launch. Two or more smaller main blocks of this type can be connected together to bring payloads into orbit.

 The base unit can be used alone or in combination with two or more additional units of the first stage, with or without rocket engines to provide a wide range of load capacities. It can be used in multi-stage mode, uniting in a bunch around the carrier or manned spacecraft. It can be combined with traction boosters or upper stages, or it can be used as an orbital transport rocket. The modified orbital aircraft for manned flights puts into orbit less weight of an unbearable load than a space shuttle and has a longer cargo container. The orbital aircraft has an upper hatch in the cargo container that can open to allow experiments during orbital flight and to extract and place payloads in the cargo container, and may have an additional hatch in the rear section of the cargo container to provide access without opening the upper hatch container. A cargo container could hold a payload 4–9 m longer than the load accommodated by a space shuttle. The shuttle body could be fully tubular to provide increased strength. Since the dry weight of the orbital aircraft is much less and the elongated rear of the cargo container creates an aerodynamic profile of low resistance, an orbital aircraft without payload could be a pretty good aircraft. Separate rocket engines running on hydrocarbon or hydrogen fuel stored in tanks in the cargo compartment could be fixed on the wings to ensure the operation of the orbital aircraft as an aircraft. This greatly simplifies the relocation of orbital aircraft from one launch site to another.

 If necessary, auxiliary units in the form of winged missiles can be attached to provide additional traction for the purposes of acceleration and maneuvering of either an orbital aircraft or a first-stage unit, while at the same time not occupying a certain volume in the cargo container. They introduce fewer dangers than if they were located inside an orbital aircraft. Solid propellant rocket boosters can be used at launch to provide additional traction.

 All the modular blocks of the launch vehicle described above, with the exception of the orbital aircraft, are themselves preferably completely or partially expendable and, thus, have a relatively simple design. Blocks can be selected for a specific flight and suitably detachably attached to each other to form the desired layout using the attachment zones provided for this purpose on different blocks. Due to the flexibility of this launch vehicle, only a limited number of different types of modular units are required to provide a wide range of various possible operations, including launching payloads from 20-30 to 100 tons, unmanned and manned flights, transportation in outer space from one place to another, deep space flights, the construction of space stations and many other potential space flights. In the proposed launch vehicle, the connection between space flight projects and rocket design is effectively destroyed. In other words, neither a flight nor a number of planned flights (i.e., a flight model) should be determined by a specific launch vehicle with a fixed carrying capacity.

 Thus, instead of changing the design of the spacecraft to perform the tasks of each new flight, the corresponding modular blocks are simply selected from the existing set and connected to each other with the formation of the desired launch arrangement. Thanks to this, the cost of space flights is significantly reduced. Each unit of a modular system may have a different application. For example, a first-stage unit can be used as an apparatus put into orbit by one stage, or as part of a multi-stage system for launching aircraft into orbit with arbitrarily large payloads. Auxiliary power units, for example, can be used as accelerators in the process of launching, transporting in space, or maneuvering aircraft or external suspension engines on orbital aircraft. Since orbital aircraft are much simpler and less expensive than existing orbital aircraft, an increase in their number is possible. Their work can be supported by fewer first-stage blocks that can return to Earth after each launch to prepare for the launch of another orbital aircraft or other types of payload.

 The launch vehicle can be arranged in the form of an apparatus put into orbit by the first stage, a two-stage launch vehicle (a first stage unit in combination with auxiliary units or solid rocket boosters), a three-stage launch vehicle (a first stage unit in combination with an auxiliary unit and solid fuel rocket accelerator), etc. The cost of launching into orbit using the proposed launch vehicle is reduced due to its modular design. For different types of flights, aircraft with various design features should not be used. Instead, the main modules are selected from the available set to solve a wide range of space flight problems.

Claims (11)

 1. A reusable launch vehicle containing a plurality of cylindrical modules, one of which is made in the form of at least partially disposable first-stage unmanned unit with a main propulsion system, and another one in the form of a payload unit, which is removably mounted externally to the first unit stages, characterized in that the modules are arranged to fasten them together in the form of many possible starting configurations, while the main propulsion system of the first stage unit is made and with means of accelerating one block of the first stage to enter orbit, and the block of the first stage is made in the form of an independent single-stage rocket, which is launched into orbit, while the block of the first stage is equipped with fastening devices to one or more additional identical or different launch vehicle modules with the possibility of formation of a multi-stage configuration.  2. The launch vehicle according to claim 1, characterized in that the first stage unit is equipped with means for attaching the payload unit to the side surface or front end of the first stage unit.  3. The launch vehicle according to claim 1, characterized in that the main propulsion system of the first stage unit is equipped with at least three engines mounted on the rear end of the first stage unit.  4. The launch vehicle according to claim 3, characterized in that the main propulsion system of the first stage unit is equipped with at least eight engines.  5. The launch vehicle according to claim 1, characterized in that the block of the first stage is made completely disposable.  6. The launch vehicle according to claim 1, characterized in that the first stage unit is made with an internal cargo compartment.  7. The launch vehicle according to claim 1, characterized in that the first stage unit is fastened to one or more additional blocks of the first stage.  8. The launch vehicle according to claim 7, characterized in that the two blocks of the first stage are interconnected by pipelines for the supply of rocket fuel.  9. The launch vehicle according to claim 7, characterized in that it is equipped with payload blocks of various sizes, each of which is made with the possibility of connection with the block of the first stage.  10. The launch vehicle according to claim 1, characterized in that it is equipped with two different first stage blocks with different load capacities, while the blocks are respectively equipped with a different number of engines mounted on their rear end.  11. A multi-component transport system comprising a plurality of cylindrical modules, one of which is made in the form of at least partially disposable first stage unit with main propulsion systems, characterized in that the modules are removably fastened together in a variety of different launch and orbital configurations, while the system is equipped with at least one auxiliary engine mounted with the possibility of bonding with other modules in the system, and the auxiliary engine is equipped with additional an additional engine for putting into payload orbit more than a predetermined mass and at least one non-motorized cargo container installed with the possibility of removal from the outside of the first stage unit, while the container is made with an internal cargo compartment.

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