Rocket and space complexes. Development of rocket and space launching systems Technological equipment of domestic rocket and space complexes

, controls, design of ballistic missiles, upper stages, rocket and space launch systems, launch vehicles, nozzle blocks, flight trajectories, transport space systems

Based on a large amount of factual material, the main stages of the development of rocket-space launch systems are traced in detail and the directions for their improvement are presented. Detailed comparative analysis characteristics of domestic and foreign long-range ballistic missiles and launch vehicles, including reusable space transport systems. The basics of design and design features of rocket and space launch vehicles are stated.

For students of technical universities studying in rocket and space specialties and areas, as well as for everyone interested in the history of the development of rocket and space technology and the prospects for its improvement.

TABLE OF CONTENTS
Part 1. Fundamentals of rocket and space launch systems
Chapter 1. Ballistic missiles as the basis for the creation of launch vehicles
1.1. Prehistory and initial stages of the creation of the first MRBM
1.2. Basic concepts and terms
1.3. Improvement of the design and layout of single-stage missiles to increase the range and the transition to multi-stage MRBM
Chapter 2. Features of the design of long-range ballistic missiles
2.1. Single stage missiles
2.2. Multistage rockets
2.3. Features of combat missiles
Chapter 3. Influence of trajectory features on missile flight control
3.1. Control system functions
3.2. Governing bodies
3.3. Development of the design of the solid propellant rocket nozzle unit
3.4. The use of a retractable nozzle on a rocket engine
Chapter 4. General task of flight control
4.1. Basic control methods
4.2. Control method along the "rigid" trajectory
4.3. Apparent speed control system
4.4. Synchronous tank emptying system
4.5. Flexible trajectory control method
4.6. Control method with correction on the passive part of the trajectory
Chapter 5. Development of designs of intercontinental ballistic missiles and launch vehicles
5.1. Main directions of development
5.2. Basing of launch vehicles and combat ballistic missiles
5.3. Features of separation of the warhead and separation of stages in rockets with solid propellants
5.4. Launch vehicle "Proton"
5.5. Use of cryogenic propellants in launch vehicles
5.6. Launch vehicle "Saturn-V"
5.7. Launch vehicle N-1
5.8. The use of solid propellants as a "zero" (booster) stage in launch vehicles
5.9. The use of hybrid engines in rocket units
5.10. Upper stages, or interorbital transport vehicles
5.11. Reusable space transport systems
5.12. Submarine ballistic missiles
Chapter 6. State of the art and development trends of launch vehicles
6.1. Development of the design of carrier rockets of the Soyuz family (R-7)
6.2. Launch vehicles of the Rus-M family and a promising new generation manned spacecraft
6.3. Angara launch vehicle family
6.4. Conversion launch vehicles
6.5. General trends in the development of launch systems

Part 2. Fundamentals of the design of long-range ballistic missiles and launch vehicles
Chapter 7. General Design Problem
7.1. Design stages
7.2. Basic tactical and technical requirements
7.3. Optimization criteria and general design problem
Chapter 8. Ballistic and Mass Analysis
8.1. Analysis of the forces acting on the rocket in flight on the active leg of the trajectory
8.2. The equations of motion of the rocket on the active part of the trajectory
8.3. Equations of motion of a rocket in a polar coordinate system
8.4. Changes in the flight characteristics of a rocket during flight
8.5. Approximate determination of the flight range. Tasks of the passive section of the trajectory
8.6. The equations of motion of the rocket on the active section of the trajectory as a function of the main design parameters
8.7. An approximate determination of the speed of a rocket
8.8. Influence of the main design parameters on the rocket flight speed
8.9. Influence of the main design parameters on the missile flight range
8.10. Mass analysis of a single-stage liquid-propellant rocket
Chapter 9. Features of the choice of the main design parameters of a multistage rocket
9.1. Basic terminology
9.2. Determining the speed of a multistage rocket
9.3. Determination of the main design parameters of a multistage rocket
Application. Ballistic design parameters selection programs

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Rocket and space complex (RSC)

A set of rocket or space rockets (ILV) with functionally interconnected technical means and structures, designed to ensure transportation, storage, deployment and maintenance in established readiness, Maintenance, preparation, launch and control of the ILV flight at the launch site. Includes ILV, facilities of the technical complex (TC), facilities of the launch complex (SC), facilities of the measuring complex of the cosmodrome (IKK).

A space rocket, an assembly of a carrier rocket with a space warhead (CGC), which consists of a spacecraft (SC) together with assembly-protective and upper stages. Space warhead, a set of spacecraft with prefabricated protective and upper stages. Upper stage in individual cases may be absent.

Launch complex, a set of technologically and functionally interconnected mobile and stationary technical means and structures that ensure all types of work with the ILV and (or) it constituent parts from the moment the ILV arrives from the technical position until the completion of the necessary pre-launch operations with the elements of the ILV, and during the tests of the ILV and the failed launch of the ILV until the return of the ILV to the technical position. Located at the starting position. Provides: delivery of the ILV from the technical complex to the launcher (PU), its installation on the launcher, aiming, refueling with propellant components and compressed gases, testing, performance of all operations to prepare the ILV for launch and its launch. The SC includes: one or several launchers, facilities with technical systems that provide ILV preparation and launch, a launch command post.

PU can be implemented in the following versions: stationary ground; stationary underground (mine); mobile ground (ground and rail); mobile underground (trench); mobile marine (on offshore platforms, surface ships and submarines); mobile air (air start).

A technical complex, a set of technical complexes of a launch vehicle, a spacecraft, an upper stage, a space warhead, a space rocket and other technical means common to space rockets. Depending on the purpose of the RKK TC, one of the types of technical complexes may be absent.

Technical position, area with access roads, utilities, buildings and structures.

Rocket and space complex "Soyuz"

The Soyuz rocket and space complex is the oldest at the Baikonur cosmodrome. The most striking events in the history of world cosmonautics are associated with the functioning of this complex. The most significant among them are the launch on October 4, 1957 of the world's first artificial Earth satellite and the flight on April 12, 1961 of the first cosmonaut of the planet, Yuri Alekseevich Gagarin.

The complex was created on the basis of the R-7 intercontinental ballistic missile, the famous royal "seven". Its modifications are widely known throughout the world under the names Sputnik, Vostok, Voskhod, Molniya and Soyuz.

The number of spacecraft launches carried out using the Soyuz rocket and space complex is already approaching a thousand. Only 27 were unsuccessful. The high reliability of the complex allows it to be widely used in the implementation of the Federal Space Program of Russia and in international cooperation programs.

For launches of Soyuz carrier rockets, two launch sites were built at the cosmodrome, one of them was created in 1957, the other - in 1961. The launch sites occupy a vast territory (more than 100 hectares) and have one launcher each of which it is capable of performing up to 24 launches of carrier rockets per year.

Preparation of carrier rockets and spacecraft for launch is carried out in five assembly and test buildings. Special apparatus and equipment provide the necessary temperature, humidity and finishing conditions, a full list of technological operations for the preparation of launch vehicles, booster blocks and spacecraft for launch.

The Soyuz launch vehicle uses environmentally friendly propellants; kerosene and liquid oxygen. During the launch, the rocket weighs about 310 tons, and its engines develop a total thrust of up to 400 tons at the surface of the earth. The technical parameters of the rocket allow launching a payload weighing up to 7 tons into the reference orbit.

Rocket and space complex "Proton"

The Proton rocket and space complex is one of the main ones at the Baikonur cosmodrome. Thanks to the progressive scientific and technical solutions incorporated in it, this complex, in terms of its reliability and many other indicators, is the best in the world among launching systems of a similar class. Flights of automatic interplanetary stations with landings of spacecraft on the Moon, Venus and Mars, as well as launches of long-term orbital stations Salyut and Mir, communications and television broadcasting satellites into geostationary orbit are carried out using the Proton complex.

The complex is based on a three-stage launch vehicle "Proton" with a length of 44.3 meters and a maximum cross-section of 7.4 meters. At the surface of the earth, its engines develop a thrust of 900 tons. The rocket is capable of injecting a payload weighing up to 20 tons into a reference orbit, and, when using an upper stage, a satellite weighing up to 3.5 tons into a geostationary orbit. The first launch of the Proton took place on July 16, 1965. Now the number of launches exceeds 250, of which only 11 failed.

Preparation of launch vehicles, booster blocks and spacecraft for launch is carried out at technical positions, which are located in four assembly and test buildings. Technical positions are equipped with special technological and general technical equipment, access roads and utilities. They are designed to receive launch vehicles and payloads from manufacturing plants, store them, assemble and test them. Here, spacecraft are fueled with propellants and compressed gases, and payloads are docked to launch vehicles.

The assembly and test building of the Proton launch vehicle is a unique structure consisting of an assembly and test hall with an area of ​​more than 1,500 square meters and many office space with control rooms, control rooms, laboratories and other services.

The Proton launch vehicles are launched from two launch sites, each of which has two launch sites, a command post, fuel and oxidizer storage facilities, refrigeration centers, high-voltage substations and other infrastructure facilities.

In 1996, Proton was the first domestic launch vehicle to enter the world market for commercial spacecraft launch services, and International Launch Services is engaged in its marketing.

During its operation, the rocket has been repeatedly improved. Now the next stage of its modernization is coming to an end. The new Proton-M will have an improved control system. The pollution of the environment with fuel residues in the areas of the fall of the spent stages will decrease.

Rocket and space complex "Zenith"

The newest among the rocket and space complexes of the Baikonur cosmodrome is Zenit. Its creation began in 1976 and was carried out in parallel with the development of the Energia-Buran reusable space system. The modified first stages of the Zenit launch vehicle were used as the side blocks of the Energia launch vehicle.

The Zenit launch vehicle has a two-stage design and is capable of injecting a payload weighing up to 13.7 tons into a reference orbit with an altitude of 200 km and an inclination of 51 °. Both stages use environmentally friendly fuel components - liquid oxygen and kerosene.

The launch site, which covers an area of ​​113 hectares, has two launchers, a cryogenic center and more than 50 technological systems. All operations for transportation, installation of the rocket on the launching device, docking of refueling and other communications are performed automatically. The rocket can be launched within an hour and a half after its installation on the launch facility. Even if the launch is canceled, the work to restore the rocket to its original state is performed when remote control from the command post.

The technical position of the Zenit rocket and space complex includes an assembly and test building, storage facilities for launch vehicles and spacecraft, technical buildings and other structures.

In the late 1980s, the country's space programs were seriously curtailed. Many new satellites targeting Zenit have never been created. Therefore, the load on the rocket and space complex was low - a total of 32 launches were carried out. At the same time, the creators of the complex were born new idea to carry out launches of the carrier rocket from the floating platform. Thus, its capabilities are significantly expanded by moving the starting point to the equator. The project was named Sea Launch. Firms from Ukraine participate in it. Russia, USA and Norway. The first successful launch of Zenit-31 from the Odyssey platform took place on March 28, 1999.

Rocket and space complex "Cyclone"

The general direction of work during the creation of the Cyclone rocket and space complex was to improve the safety of the service personnel during the preparation of the launch vehicle at the launch site. The developers of "Cyclone" fully managed to implement the concept of "deserted start". During the prelaunch preparation of the launch vehicle and the spacecraft on the launcher, all equipment of the complex is controlled remotely from the command post.

The Cyclone launch vehicle is based on the R-36 intercontinental ballistic missile developed by the Yuzhnoye design bureau under the leadership of chief designer M.K. Yangel.

The Cyclone launch vehicle was launched in 1967. The launch mass of this two-stage rocket (excluding the mass of the spacecraft) is 178.6 tons. The Cyclone rocket provides spacecraft with a mass of 3.2 and 2.7 tons, respectively, into circular orbits with an altitude of 200 km and an inclination of 65 ° and 90 °. At present, this rocket is used only for launching spacecraft of the Cosmos series.

Elements of the ground infrastructure of the Cyclone rocket and space complex are compactly located on the left flank of the cosmodrome. The launch site is equipped with two launchers, one of which is now mothballed. The preparation of the launch vehicle and payloads is carried out in one assembly and test building.

The disadvantage of the Cyclone rocket and space complex is the high toxicity of the propellant components, which creates a danger of environmental pollution in the event of an accident. However, this disadvantage is largely compensated for by the high reliability of the complex. To date, more than a hundred launches of the Cyclone carrier rocket have already been carried out, among which there is not a single emergency one.

Rocket and space complex "Energia-Buran"

The Energia-Buran rocket and space complex includes the Energia universal super-heavy launch vehicle, the Buran orbital spacecraft, as well as the ground space infrastructure facilities of the launch vehicle and orbital vehicle.

The Energia launch vehicle is a two-stage rocket made according to the “package” scheme with lateral placement of the withdrawn payload. Its first stage consists of four side blocks 40 m high and 4 m in diameter. Side blocks are placed around the central block, its height is 60 m, diameter is 8 m. The engines of the first stage run on oxygen-kerosene fuel, the second stage - on oxygen-hydrogen fuel. The launch weight of the launch vehicle is 2,400 tons. Energia is capable of launching a payload weighing more than 100 tons into near-earth space. Many enterprises of the country, headed by the Rocket and Space Corporation Energia named after V.I. S.P. Queen. The creation of the rocket and space complex has become an outstanding achievement of domestic designers of rocket and space technology.

Orbital spacecraft "Buran" is a reusable spacecraft capable of long-term flights, orbital maneuvering, controlled descent and aircraft landing at a specially equipped airfield.

With the help of "Buran" it is possible to deliver cosmonauts and payloads weighing up to 30 tons into space and return to Earth, as well as carry out repair and maintenance of spacecraft directly in orbit. The length of the orbital ship is 36.4 m, the height is 16.45 m, the maximum launch weight is 105 tons.

The technical complex of the reusable space system (ISS) "Energia-Buran" is located 5 km from the launch site. It includes structures of truly grandiose dimensions. These include the assembly and test building of the Energia launch vehicle, where the launch vehicle is assembled and undergoes the entire test cycle. It is the largest building of the cosmodrome, has five spans, its length is 240 m, width is 190 m and height is 47 m. On the most intense days, up to 2,000 people worked here at the same time. The assembly and test building of the orbital spacecraft "Buran" is somewhat smaller, it has a length of 224 m, a width of 122 m and a height of 34 m. In its premises, preparation of three orbital ships can be carried out simultaneously.

The ISS Energia-Buran Launch Complex is a huge ground-based complex covering an area of ​​over 1000 hectares. It consists of several dozen structures that house more than 50 technological and 200 technical systems.

The launch facility of the ISS Energia-Buran is a reinforced concrete structure buried in five floors with control and testing equipment and other equipment. Two railway tracks, spaced 18 m apart, lead from the assembly and refueling building to the launch facility. Four diesel locomotives use these tracks to take out the transport assembly unit with the Energia launch vehicle and the Buran orbital vehicle attached to it.

The launch complex includes a universal "stand-start" complex, which not only provides preparation and launch of the launch vehicle, but also with its help, dynamic and firing tests will be carried out, and the technology for refueling the Energia launch vehicle is being worked out.

All launch systems are controlled by modern suspicious technology from the command post. A high degree of automation of control processes provides the ability to detect and eliminate more than 500 emergency situations provided for by the program.

A unique structure is the landing complex of the orbital spacecraft "Buran", which previously included the main Yubileiny airfield (Baikonur) and two spare ones (Simferopol and Khorol). It is designed to deliver the ship from the manufacturing plant, to ensure its landing upon return to Earth, as well as post-flight service. In addition to its main purpose, the landing complex can be used as an airfield and receive aircraft of any class. The runway of the landing complex is 4.5 km long and 84 m wide.

The launches of the Energia carrier rocket, carried out on May 15, 1987 with a mock-up of the Polyus spacecraft and on November 15, 1988, with the Buran orbiter in an unmanned version, are a huge step in Russian science and technology in creating new means of development and space exploration.

The creation of the ISS Energia-Buran could become a new stage in the rapid development of Russian rocket and space technology. However, due to economic problems, further work on the Energia-Buran rocket and space complex was suspended.

The scientific and technical groundwork accumulated in the process of creating the Energia-Buran rocket and space complex is a valuable national treasure and is currently widely used in many areas. human activity.
Photos from RSC Energia-Buran

This article is devoted to the description of a model for ensuring the readiness of technological equipment of rocket and space complexes for target use, taking into account the cost of the chosen strategy for replenishing spare parts. The problem of determining the set of optimal strategies for replenishing the elements of spare parts and accessories of each nomenclature according to the criterion "readiness - cost" is substantiated, taking into account the parameters of reliability, maintainability and preservation. To solve the optimization problem, the well-known models for justifying the requirements for inventory supply systems are analyzed, which are based on methods for calculating their optimal structure, nomenclature and number of spare parts, as well as the frequency of replenishment of a specific range of spare parts. The proposed model allows you to determine the amount of costs for the implementation of the strategy of replenishing the elements of spare parts of the same range during the assigned service life of the equipment based on the use of the criterion "readiness - cost" and takes into account the parameters of reliability, maintainability and preservation of this equipment. The article provides an example of the use of models for choosing the optimal strategies for replenishing the set of spare parts for a filling unit.

preparedness model

resource intensity of operational processes

supply systems

availability factor

1. Boyarshinov S.N., Dyakov A.N., Reshetnikov D.V. Modeling of the system for maintaining the operational state of complex technical systems // Vooruzhenie i ekonomika. - M .: Regional public organization"Academy of Problems of Military Economy and Finance", 2016. - No. 3 (36). - S. 35–43.

2. Volkov L.I. Management of the operation of aircraft complexes: textbook. manual for technical colleges. - 2nd ed., Rev. and add. - M .: Higher. shk., 1987 .-- 400 p.

3. Dyakov A.N. Model of the process of maintaining the readiness of technological equipment with service after failure. Proceedings of the A.F. Mozhaisky. Issue 651. Under total. ed. Yu.V. Kuleshova. - SPb .: VKA named after A.F. Mozhaisky, 2016 .-- 272 p.

4. Kokarev A.S., Marchenko M.A., Pachin A.V. Development of a comprehensive program for improving the maintainability of complex technical complexes // Basic research... - 2016. - No. 4–3. - S. 501-505.

5. Shura-Bura A.E., Topolsky M.V. Methods for organizing, calculating and optimizing sets of spare elements for complex technical systems. - M .: Knowledge, 1981 .-- 540 p.

During recent years in scientific research devoted to the creation and operation of complex technical systems (STS), the approach of increasing the efficiency of their functioning by reducing the cost has been significantly developed life cycle(Life cycle) of these systems. Cost management of the life cycle of the CTC allows you to gain superiority over competitors by optimizing the costs of purchasing and owning products.

This concept is also relevant for rocket and space technology. So, in the Federal Space Program of the Russian Federation for 2016-2025. the task of increasing the competitiveness of existing and prospective launch vehicles is postulated as one of the priority tasks.

A significant contribution to the cost of services for launching payloads into orbit is made by the costs of ensuring the readiness of technological equipment (Tb) of rocket and space complexes (RSC) for target use. These costs include the costs of purchasing sets of spare parts (spare parts, tools and accessories), their delivery, storage and maintenance.

The issue of justifying the requirements for supply systems (POPs) is the subject of many works by such authors as A.E. Shura-Bura, V.P. Grabovetsky, G.N. Cherkesov, in which methods for calculating the optimal structure of POPs, the nomenclature and the number of spare parts items are proposed. At the same time, the frequency (strategy) of replenishing a specific range of spare parts, which significantly affects the cost of delivery, storage and maintenance of spare parts, is either considered specified, or remains outside the scope of research.

S1 - operable state of TlOb;

S2 - failure condition, identification of the cause of failure;

S3 - repair, replacement of a spare parts element;

S4 - waiting for the delivery of the spare parts item if it is not at the operation site;

S5 - control of technical condition after repair.

Rice. 1. Preparedness model graph

Table 1

Laws of transitions from the i-th to the j-th state of the graph

Purpose of the study

In this regard, the task of developing a model for ensuring the readiness of the RSC TOT for target use, taking into account the cost of the chosen strategy for replenishing spare parts, becomes especially urgent.

Materials and research methods

To determine the readiness factor of TlOb RKK, we will use the following expression:

where K Гh is the availability factor of the h-th element, depending on the indicators of reliability, maintainability and preservation;

H is the number of elements.

Let us describe the dependence of the equipment availability factor on the indicators of reliability, maintainability and preservation of the h-th item of equipment with a graph model of the operational processes implemented on this equipment.

Let us make the assumption that the equipment can be simultaneously in only one state i = 1, 2,…, n from the set of possible E. The flow of state change is the simplest. At the initial moment of time t = 0, the equipment is in a working state S1. After a random time τ1, the equipment instantly switches to a new state j∈E with probability p ij ≥ 0, and for any i∈E. The equipment stays in state j for a random time before moving to the next state. In this case, the laws of transitions from the i-th to the j-th state of the graph can be represented in the following form (Table 1).

To construct an analytical relationship, the following particular indicators of the maintenance and repair (MRO) system are used:

ω1 is the rate of failure of the element;

ω3 - parameter of the flow of recovery of failures (Erlang parameter);

ω5 is the parameter of the flow of failures detected during the control of the technical condition of the technical condition after the installation of the spare parts and accessories (due to the mathematical expectation of the shelf life of the spare parts);

TPost - the duration of waiting for the delivery of a spare parts item that is absent at the operation facility;

T d - the duration of diagnostics, identifying the cause of the failure, searching for the failed element;

Т Ктс - duration of technical condition monitoring after replacement of a spare parts element;

n is the number of spare parts and accessories of one nomenclature in the Tlob;

m is the number of items of one item in the SPTA.

table 2

Dependencies that describe the properties of the graph model

To obtain analytical dependencies that characterize the model, a well-known approach was used, given in. In order to avoid repetition of the known provisions, we omit the derivation and present the final expressions characterizing the states of the graph model (Table 2).

Then the probabilities of the states of the investigated semi-Markov process:

, (2)

, (3)

, (4)

, (5)

. (6)

The obtained dependencies determine the probabilities of finding the TlOb element in the states of the investigated operational process. So, for example, the indicator P1 is a complex indicator of reliability - the availability factor, and expression (2) models the relationship between the parameters of reliability, maintainability, preservation and the integral indicator, which is used as KГh.

Substituting into expression (2) the expressions for the operational and technical characteristics of the equipment from the table. 2, we obtain an expression that allows us to assess the influence of elements of one nomenclature on the equipment availability factor:

(7)

where λ h is the failure rate of the h-th element;

t2h - mathematical expectation of the duration of the technical condition control;

t3h - mathematical expectation of the recovery time;

t4h is the mathematical expectation of the waiting time for the delivery of the h-th item of spare parts, which are absent at the operating facility;

t5h - mathematical expectation of the shelf life of the h-th element of the spare parts and accessories;

Т7h - mathematical expectation of the duration of the technical condition monitoring;

Т10h - period of replenishment of the h-th element of spare parts.

The proposed model differs from the known ones in that it allows calculating the value of KG TlOb RCC, depending on the parameters of its reliability, maintainability and preservation.

To determine the cost of implementing the strategy for replenishing items of spare parts for one item during the assigned service life of the equipment, you can use the following expression:

where is the cost of storing an item of spare parts for one item during the period of the assigned service life Tlob;

Costs for the supply of spare parts and accessories of the same item instead of those consumed during the assigned service life of the Tlob;

The cost of maintaining an item of spare parts and accessories of one item.

The number of spare parts and accessories of one item required to ensure the required level of readiness of the TOT during the replenishment period.

Research results and their discussion

Let us consider the use of models for choosing the optimal strategies for replenishing the set of spare parts for the filling unit, ensuring the unit availability factor is not less than 0.99 during 10 years of operation.

Let the failure flow be the simplest, the failure flow parameter will be taken equal to the failure rate. Similarly, we take the flow parameters ω3 and ω5 as quantities inversely proportional to mathematical expectations the durations of the corresponding processes.

To carry out calculations, we will consider three options for strategies for replenishing a set of spare parts, which are limiting cases:

Lifetime bookmark;

Periodic replenishment (with a period of 1 year);

Continuous replenishment.

Table 3 shows the results of calculations for a set of spare parts for the 11G101 unit, obtained using the models described above.

Table 3

Calculation results

From the analysis of the table. 3 it follows that for items 1 and 4, the optimal strategy is periodic replenishment of spare parts, and for items 2, 3 and 5 - continuous replenishment.

Proposed new model ensuring the readiness of the RKK TDS, which can be used to solve the problem of determining the set of optimal strategies for replenishing the elements of spare parts for each nomenclature according to the “readiness - cost” criterion, taking into account the parameters of reliability, maintainability and preservation.

Bibliographic reference

The goal of the state policy in the rocket and space sector provides for the formation of an economically stable, competitive, diversified rocket and space industry, ensuring guaranteed access and the necessary presence of Russia in outer space.

Capital investments for reconstruction and technical re-equipment include:

targeted investment support for the introduction of special technological equipment that ensures the implementation of the basic technologies for the production of rocket and space vehicles provided for by the FKPR-2015 and the federal target program "Development of the OPK-2015";

raising the general technical level of enterprises producing rocket-space vehicles through the automation of technological processes that reduce labor intensity, improve the quality and reliability of rocket-space vehicles;

creation of technological conditions for the widespread introduction of information technological processes (IPI technologies).

The main share of these investments is formed within the framework of the FKPR-2015 and the Federal Target Program "Development of the OPK-2015".

The priority directions of state policy in this area are as follows.

The first is the creation of space complexes and systems of a new generation with technical characteristics ensuring their high competitiveness in the world market:

development modern means launching (modernization of existing launch vehicles and development of new launch vehicles and upper stages, creation of a medium-class launch vehicle for launching a new generation of manned spacecraft), space satellites with an extended active life;

preparation for the implementation of breakthrough projects in the field of space technologies and space research.

The second is the completion of the creation and development of the GLONASS system:

deployment of a satellite constellation based on new generation vehicles with a long active life (at least 12 years) and improved technical characteristics;

creation of a ground control complex and creation of equipment for end users, its promotion to the world market, ensuring the interface between GLONASS and GPS equipment.

Third, the development of a satellite constellation, including the creation of a constellation of communication satellites, ensuring the growth of the use of all types of communication - fixed, mobile, personal (throughout Russian Federation); creation of a constellation of meteorological satellites capable of transmitting information in real time.

In the long term, the interests of maintaining high competitiveness in the information transmission market will require a qualitative leap in increasing the interval of "competitive existence" of communication satellites. This can only be achieved by creating a technology for the production of "reusable" communication satellites, i.e. those that will be initially designed and built with the possibility of their maintenance, refueling, repair and modernization directly in orbit. The result of such technological development may be the emergence by 2025 of massive orbital platforms, which will host various target equipment and other equipment, incl. energy, allowing maintenance or replacement. In this case, the satellite production market will undergo significant structural and quantitative changes.

At the same time, despite the fact that currently Russian production satellites are practically not represented either on the market of finished products or on the market of individual components, Russia needs to continue its efforts to enter this market segment. Moreover, the goal of these efforts may not only be the conquest of some market share but the interests of technological development as well as national security.

From this point of view, the most interesting is the international project Blinis - the technology transfer program for the integration of the payload module between Thales Alenia Space (France) and the Federal State Unitary Enterprise NPO Applied Mechanics. M.F. Reshetneva.

Fourth, expanding Russia's presence in the global space market:

maintaining a leading position in the traditional markets for space services (commercial launches - up to 30%);

expanding the presence on the market for the production of commercial spacecraft, expanding the promotion of individual components of rocket and space technology and related technologies to foreign markets;

access to high-tech sectors of the world market (production of ground equipment for satellite communications and navigation, remote sensing of the earth);

creation and modernization of the system of the Russian segment of the international space station (ISS).

All segments of the market for the production of carriers are currently characterized by an excess of supply over demand and, accordingly, a high level of internal competition - amid stagnation in the satellite production market in the early 2000s. this has already led to a significant drop in prices in the launch market.

In the medium term, amid a slight increase in the number of satellites produced, the level of market competition in all segments will increase even more when “heavy” and “light” carriers from countries such as Japan, China, and India enter the market.

In the long term, the volume and structure of the carrier market will directly depend on the situation in the "leading" markets in relation to it: information and production of satellites, in particular:

on the market of "heavy" and "medium" carriers from the transition to "reusable" communication satellites, the development of markets for space production and space tourism;

on the market of "light" carriers from the possibility of transferring ERS information to the category of "network goods".

Fifth, organizational changes in the rocket and space industry.

By 2015, three or four large Russian rocket and space corporations will be formed, which by 2020 will enter independent development and will fully provide the release of rocket and space technology for solving economic challenges, tasks of defense and security of the country, effective activities of Russia in international markets.

Sixth - modernization of ground-based space infrastructure and technological level of the rocket and space industry:

technical and technological re-equipment of industry enterprises, introduction of new technologies, optimization technological structure industry;

development of the cosmodrome system, equipping ground control facilities with new equipment, communication systems, experimental and production base of the rocket and space industry.

With an inertial version of development, production rocket and space industry by 2020 - by 55-60% to the level of 2007.

• 1. Partial technical and technological re-equipment of the industry;
• 2. Implementation of interagency and departmental targeted programs;

state needs in space assets and services for defense, socio-economic and scientific spheres, the implementation of the federal target program "GLONASS" and the creation of a competitive space transport system with a medium-class launch vehicle of increased carrying capacity.

With an innovative development option, the production of products of the rocket and space industry will grow by 2020 - 2.6 times compared to the 2007 level.

Production growth under this option will be ensured by:

• 1. Intensive technical and technological re-equipment since 2008;
• 2. Implementation of a complete list of federal and departmental target programs that ensure the development of the rocket and space industry and the possibility of creating a new generation of rocket and space technology from 2012;
• 3. Providing unconditional satisfaction

state needs for space vehicles and services for defense, socio-economic and scientific spheres, in addition to the inertial scenario by the implementation of the project of a promising manned transport system;

4. Completion of organizational and structural

transformations of enterprises in the industry and the creation of backbone integrated structures linked by a single direction of activity and property relations;

• 5. Ensuring the level of utilization of production capacities by 2020 75 percent;
• 6. Full implementation of a long-term program of scientific and applied research and experiments in various scientific areas with the creation of an advanced hardware reserve for the rocket and space industry;
• 7. Construction of the Vostochny cosmodrome in order to provide the Russian Federation with independent access to space in the entire spectrum of tasks to be solved;
• 8. By solving the personnel problems of the industry.

An additional increase in the production of products of the rocket and space industry according to the innovative version in relation to the inertial one will amount to 115-117 billion rubles in 2020.