Technological features of domestic rocket and space complexes. Basic research. Research results and discussion

1

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

preparedness model

resource intensity of operational processes

supply systems

readiness factor

1. Boyarshinov S.N., Dyakov A.N., Reshetnikov D.V. Simulation of a system for maintaining a working state of complex technical systems// Armament and economy. - M .: Regional social organization"Academy of problems of military economy and finance", 2016. - No. 3 (36). – P. 35–43.

2. Volkov L.I. Management of the operation of aircraft complexes: textbook. allowance for universities. - 2nd ed., revised. and additional - M .: Higher. school, 1987. - 400 p.

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

4. Kokarev A.S., Marchenko M.A., Pachin A.V. Development integrated program improving the maintainability of complex technical systems // Basic Research. - 2016. - No. 4–3. – S. 501–505.

5. Shura-Bura A.E., Topolsky M.V. Methods of organization, calculation and optimization of sets of spare elements of complex technical systems. - M.: Knowledge, 1981. - 540 p.

During the last years in scientific research dedicated to the creation and operation of complex technical systems (CTS), the approach to improve the efficiency of their operation by reducing the cost of life cycle(LC) of these systems. Cost management of the CTC life cycle allows you to gain superiority over competitors by optimizing the cost of purchasing and owning products.

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

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 (TLOB) of rocket and space complexes (RSC) for the intended use. These costs include costs for the purchase of spare parts, tools and accessories, their delivery, storage and maintenance.

The issue of substantiating 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, who propose methods for calculating the optimal structure of POPs, the range and number of spare parts items. At the same time, the frequency (strategy) of replenishment of a specific range of spare parts and accessories, which significantly affects the cost of delivery, storage and maintenance of spare parts, is either considered given or remains outside the scope of research.

S1 - operable state TlOb;

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

S3 - repair, replacement of the SPTA element;

S4 - waiting for the delivery of the SPTA element in the absence of the operation site;

S5 - control technical condition after repair.

Rice. 1. Graph of the availability model

Table 1

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

			p23 = PPackup	p24 = 1 - PAccessZIP

Purpose of the study

In this regard, the task of developing a model for ensuring the readiness of TlOB RKK for the intended use, taking into account the cost of the chosen strategy for replenishing spare parts, becomes especially relevant.

Materials and methods of research

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

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

H is the number of elements.

Let us describe the dependence of the equipment readiness factor on the indicators of reliability, maintainability and persistence of the h-th equipment element by a graph model of the operational processes implemented on this equipment.

Let's make the assumption that the equipment can be simultaneously in only one state i = 1, 2, ..., n from the set of possible E. The state change flow is the simplest. At the initial time t = 0, the equipment is in the operational state S1. After a random time τ1, the equipment instantly switches to a new state j∈E with probability p ij ≥ 0, moreover, 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 build an analytical dependence, the following particular indicators of the system are used Maintenance and repair (MRO):

ω1 - element failure rate;

ω3 - failure recovery flow parameter (Erlang parameter);

ω5 - the parameter of the flow of failures detected during the control of the technical condition of the TLOB after the installation of the SPTA elements (due to the mathematical expectation of the shelf life of the SPTA element);

TPost - the duration of waiting for the delivery of a spare parts and accessories item that is not available at the operation site;

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

T Kts - the duration of the control of the technical condition after the replacement of the SPTA element;

n is the number of SPTA elements of one nomenclature in the composition of TlOB;

m - the number of elements of one nomenclature in the composition of spare parts.

table 2

Dependencies describing the properties of the graph model

Transitions

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

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

, (2)

, (3)

, (4)

, (5)

. (6)

The obtained dependences determine the probabilities of finding the element ТlOB 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, persistence and integral indicator, which is used as KГh.

Substituting into expression (2) the expressions for the operational and technical characteristics of the equipment from Table. 2, we obtain an expression that allows us to evaluate 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 recovery time;

t4h - mathematical expectation of the waiting time for the delivery of the h-th element of spare parts and accessories that are not available at the operation site;

t5h - mathematical expectation of the shelf life of the h-th SPTA element;

T7h - mathematical expectation of the duration of the technical condition control;

T10h - period of replenishment of the h-th element of the SPTA.

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

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

where - the cost of storing an item of spare parts and accessories of one nomenclature during the appointed service life of TlOb;

Costs for the supply of spare parts and accessories of the same nomenclature to replace those used up during the assigned service life of TlOB;

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

The number of SPTA elements of one nomenclature required to ensure the required level of TLOB readiness during the replenishment period.

Research results and discussion

Let us consider the use of models to select the optimal strategies for replenishing the set of spare parts and accessories for the filling unit, ensuring the value of the unit availability factor is not lower than 0.99 for 10 years of operation.

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

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

Bookmark for the entire service life;

Periodic replenishment (with a period of 1 year);

Continuous replenishment.

In table. Figure 3 shows the results of calculations for the spare parts kit of the 11G101 unit, obtained using the models described above.

Table 3

Calculation results

Spare parts kit nomenclature	Replenishment strategy	Required quantity h-th elements nomenclature of spare parts and accessories to ensure the required KG	Strategy Lifetime Cost
Nomenclature 1	Lifetime bookmark		2 675 den. units
	Periodic replenishment		2 150 den. units
	Continuous replenishment		2 600 den. units
Nomenclature 2	Lifetime bookmark		2 390 den. units
	Periodic replenishment		1 720 den. units
	Continuous replenishment		1 700 den. units
The end of the table. 3
Nomenclature 3	Lifetime bookmark		2 735 den. units
	Periodic replenishment		3 150 den. units
	Continuous replenishment		2 100 den. units
Nomenclature 4	Lifetime bookmark		2 455 den. units
	Periodic replenishment		1 800 den. units
	Continuous replenishment		3 000 den. units
Nomenclature 5	Lifetime bookmark		2 700 den. units
	Periodic replenishment		2 050 den. units
	Continuous replenishment		1 300 den. units

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

A new model for ensuring the readiness of TLOB RKK is proposed, which can be applied to solve the problem of determining the set of optimal strategies for replenishing the elements of spare parts and accessories of each nomenclature according to the "availability - cost" criterion, taking into account the parameters of reliability, maintainability and persistence.

Bibliographic link

Bogdan A.N., Boyarshinov S.N., Klepov A.V., Polyakov A.P. MODEL OF READINESS OF TECHNOLOGICAL EQUIPMENT OF ROCKET AND SPACE COMPLEX // Fundamental research. - 2017. - No. 11-2. – S. 272-277;
URL: http://fundamental-research.ru/ru/article/view?id=41934 (date of access: 10/17/2019). We bring to your attention the journals published by the publishing house "Academy of Natural History"

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

Based on a large amount of factual material, the main stages in the development of space-rocket launch systems are traced in detail and 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 fundamentals of designing and design features of space-rocket launch vehicles are outlined.

For students technical universities students in rocket and space specialties and directions, as well as for all those 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 the design of rocket and space launch systems
Chapter 1. Ballistic missiles as the basis for the creation of launch vehicles
1.1. Background and initial stages of the creation of the first BRDD
1.2. Basic concepts and terms
1.3. Improvement of the design and layout scheme of single-stage missiles to increase the range and transition to multi-stage BRDD
Chapter 2. Design features of long-range ballistic missiles
2.1. single stage rockets
2.2. Multi-stage rockets
2.3. Features of combat missiles
Chapter 3
3.1. Control system functions
3.2. Governing bodies
3.3. Development of the design of the solid propellant rocket engine nozzle block
3.4. The use of a retractable nozzle on a rocket engine
Chapter 4. The General Task of Flight Control
4.1. Basic control methods
4.2. Method of control along a "hard" trajectory
4.3. Apparent velocity control system
4.4. Synchronous tank emptying system
4.5. Method of control along the "flexible" trajectory
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 propellant rocket motors
5.4. Launch vehicle "Proton"
5.5. Use of cryogenic propellant components in launch vehicles
5.6. Launch vehicle "Saturn-V"
5.7. Launch vehicle H-1
5.8. The use of solid propellant rocket engines as a "zero" (booster) stage in launch vehicles
5.9. Use of hybrid engines in rocket pods
5.10. Upper stages, or interorbital transport vehicles
5.11. Reusable transport space systems
5.12. Submarine ballistic missiles
Chapter 6 Current state and trends in the development of launch vehicles
6.1. Development of the design of launch vehicles of the Soyuz family (R-7)
6.2. Launch vehicles of the "Rus-M" family and a promising manned spacecraft of a new generation
6.3. Angara launch vehicle family
6.4. Conversion launch vehicles
6.5. General trends in the development of hatching systems

Part 2. Fundamentals of designing long-range ballistic missiles and launch vehicles
Chapter 7
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 part of the trajectory
8.2. Equations of rocket motion on the active part of the trajectory
8.3. Rocket motion equations in polar coordinate system
8.4. Changing the flight characteristics of a rocket during flight
8.5. Approximate determination of flight range. Tasks of the passive section of the trajectory
8.6. Equations of rocket motion on the active part of the trajectory as a function of the main design parameters
8.7. Approximate definition of rocket speed
8.8. Influence of the main design parameters on the rocket flight speed
8.9. Influence of the main design parameters on the range of the rocket
8.10. Bulk analysis of a single stage liquid propellant rocket
Chapter 9. Features of the choice of the main design parameters of a multi-stage rocket
9.1. Basic terminology
9.2. Determining the speed of a multi-stage rocket
9.3. Determination of the main design parameters of a multi-stage rocket
Application. Programs for selecting design and ballistic parameters

Rocket and space systems in their development have come a long way from the first German rockets V-1 and V-2 to modern launch vehicles "Proton-M", "Energy" and "Angara" of Soviet and Russian production, "TitanIIIC", "Shuttle" of US production , "Ariane" made in France and many others. In the history of cosmonautics, the achievements of Soviet and Russian science and technology remained important milestones: the launch of the first Earth satellite; launching the first man into space; the first human spacewalk; the first automatic flight of the Buran reusable spacecraft, etc. At present, the intensive development of rocket and space systems and space exploration are carried out by such countries as Russia, the USA, England, France, Japan, and China.

Let us consider the general provisions and principles of constructive and technological division of rocket and space systems.

Rocket and Space Complex (RKK) represents With the totality of the rocket and space system, flight control system and launch equipment located at the cosmodrome . Rocket and Space Systems (RSS) - these are transport systems designed for the removal (delivery) payload weight m pg from several tens of kilograms to hundreds of tons to a given point in near-Earth or near-solar space with a certain velocity vector.

The mass of the rocket-space system consumed for acceleration is called active mass (fuel mass) and denote m t. The active mass is divided into two parts: the first part provides acceleration of the space-rocket system to a given flight speed, the second - control of the space-rocket system and compensation of various disturbances in flight.

Passive mass (structure mass) rocket-space system (m k) is also divided into two parts. The first includes passive masses that ensure the functioning of the rocket and space system during the entire flight time, the second includes a part of the passive mass that provides storage of the active mass. The active mass makes up a large part (up to 90%) of the rocket-space system and is used to accelerate the payload and passive mass.

The most effective way to accelerate a rocket at the present time is the outflow from nozzles rocket engines of combustion products rocket propellants in.

The sum of the masses of the payload m pg, active mass m t, passive mass m k, is starting weight rocket and space system m Art. For a given payload mass m pg launch weight m st depends on the following factors:

- from the coordinates of a point in space and the final speed of the rocket-space system on the active part of the trajectory;

- from the forces of resistance to the movement of the rocket-space system along the trajectory;

- from the loads acting on the rocket-space system when it moves along the trajectory;

- from the need to adjust the passive section of the trajectory.

The division of the rocket-space system into its component parts is due to the following reasons:

- the need to separate the spent parts of the structure during the movement of the rocket-space system along the trajectory;

- difference in the functional purpose of adjacent structural elements and their different design (for example, a sealed tank and a truss);

- the complexity of transporting an undivided product from the manufacturer to the launch site;

– requirements for the convenience of maintenance of elements of the rocket-space system during its storage and preparation for launch;

- restrictions imposed on the dimensions and configuration of the processed structural elements, depending on the available production technological processes and technological equipment;

- the need to provide free access to structural elements for assembly and technical control;

- organizational reasons associated with a reduction in the duration of the product manufacturing cycle (expanding the scope of work when assembling complex units).

The division of the rocket-space system into parts makes it possible to carry out the parallel design of these parts by groups of specialists and thus reduce the time for designing a product and improve its quality due to the specialization of the groups.

In production, the division of the rocket-space system into parts predetermines the simultaneity (parallelism) of the processes of manufacturing parts and their assembly, which reduces the duration of the production cycle. The number of components of the rocket-space system has a certain optimum. As assembly units are disaggregated, the cycle of their manufacture is reduced, but the cycle of assembly and technical control of assembly units is increased.

The uniformity of design and technological solutions of the constituent parts allows for the technological specialization of the enterprise's divisions (sites for assembling fuel tanks and dry compartments, blank production, etc.). Technological specialization creates the prerequisites for the mechanization and automation of the work performed, for the rational use production capacity, to improve productivity and product quality.

The constructive and technological completeness of the components makes it possible to manufacture them at specialized enterprises - subcontractors, and contributes to the development of specialization and cooperation in rocket science.

The rocket-space system consists of the following components (Fig. 5).

Fig.5. The structure of the rocket and space system

AT head unit (GB) rocket and space system is located payload , - various kinds of spacecraft (spacecraft, space station, artificial satellite of the planet, telecommunications systems, devices designed for research in outer space or on planets, etc.) .

The composition of the head unit, in addition to the payload, includes a discharged fairing (GO), which protects the payload from the powerful force and thermal effects of the oncoming flow of atmospheric gas in the active phase of the flight of the rocket-space system at supersonic speeds and is separated when it leaves the atmosphere.

launch vehicle (PH), which delivers a payload to a given point in the near-Earth or near-solar space with a speed specified in magnitude and direction. The composition of the launch vehicle includes several rocket blocks (RB). Schemes and examples of typical layouts of rocket blocks are shown in Fig. 6 - 7.

Rice. 6 Schemes of the sequential layout of blocks and stages of rocket and space systems with liquid rocket engines:

a - "tandem" scheme; b - scheme "package"

Rice. 7. Scheme of parallel-sequential arrangement of blocks and stages of rocket and space systems:

a - all rocket blocks are liquid; b - rocket units RB1A and RB1B solid propellant

All blocks of the rocket and space system are combined into steps (C1, C2, etc.), the composition of which changes as the separation occurs during the movement of the rocket-space system along the trajectory.

3. Control system the movement of the space-rocket system along the trajectory (see Fig. 2.5) allows you to control the operation of rocket blocks, the separation of structural elements, and the movement of the space-rocket system along the flight path. It contains sensitive elements : transducers (gyroscopic devices, sensors of accelerations, pressure, fuel consumption, etc.); onboard computer systems for processing measurement results and generating control commands; various executive mechanisms , providing the required parameters of motion and orientation of the space-rocket system in space. The operation of the elements of the control system is provided by a variety of energy sources (electric, pneumohydraulic, charges solid fuel, explosives, etc.). Elements of the control system are dispersed in blocks. Communication between the elements of the control system is carried out using the onboard cable network (BCS).

aim public policy in the rocket and space sphere, it is planned to form 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 provide for:

targeted investment support for the introduction of special technological equipment that ensures the implementation of basic technologies for the production of RCT products, provided for by the FKPR-2015 and the Federal Target Program "Development of the OPK-2015";

increasing the general technical level of enterprises producing RCT by automating technological processes that reduce labor intensity, improve the quality and reliability of RCT products;

creation of technological conditions for the widespread introduction of information technology processes (ITP-technologies).

The main share of these investments is formed within the framework of the FKPR-2015 and the Federal Target Program "Development of the MIC-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 specifications that ensure their high competitiveness in the world market:

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

preparation for the implementation of breakthrough projects in the field of space technology and space exploration.

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

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

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

The third is the development of a satellite constellation, including the creation of a constellation of communication satellites that ensure the growth in the use of all types of communications - fixed, mobile, personal (throughout the territory 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 created with the possibility of their maintenance, refueling rocket fuel, repairs and upgrades directly in orbit. The result of such technological development may be the emergence of massive orbital platforms by 2025, which will accommodate 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.

However, despite the fact that currently Russian production As there are practically no satellites on the market of finished products or on the market of individual components, Russia needs to continue its efforts to enter this market segment. At the same time, the goal of these efforts may be not only the conquest of a certain 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 - a technology transfer program for the integration of the module payload between Thales Alenia Space (France) and Federal State Unitary Enterprise NPO Applied Mechanics. M.F. Reshetnev.

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

maintaining leading positions in the traditional markets of space services (commercial launches - up to 30%);

expansion of the presence in 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-based 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 - in the conditions of 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, in the context of a slight increase in the number of manufactured satellites, 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 satellite production, in particular:

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

in the market of "light" carriers from the possibility of transferring remote sensing information to the category of "network goods".

Fifth - carrying out 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 ensure the production of rocket and space technology to solve problems. economic tasks, the tasks of the country's defense capability and security, the effective activity of Russia in international markets.

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

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

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

With the inertial development option, the production of products of the rocket and space industry by 2020 will be 55-60% compared to the level of 2007.

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

state needs in space facilities and services for defense, socio-economic and scientific spheres, the implementation of the GLONASS FTP and the creation of a competitive space transport system with a medium-class launch vehicle with increased payload capacity.

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

Production growth under this option will be ensured by:

• 1. Intensive technical and technological re-equipment since 2008;
• 2. Implementation of a full list of federal and departmental targeted 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 in space facilities and services for defense, socio-economic and scientific spheres, in addition to the inertial scenario, the implementation of the project of a promising manned transport system;

4. Completion of organizational and structural

transformation of enterprises in the industry and the creation of backbone integrated structures connected by a single focus of activity and property relations;

• 5. Ensuring the level of utilization of production capacities by 2020 75 percent;
• 6. Implementation in full of a long-term program of applied research and experiments in various scientific areas with the creation of advanced equipment 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 range of tasks to be solved;
• 8. Decision personnel problems industries.

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

A. S. Nosov

annotation

The theoretical and experimental foundations for creating a drive with an actuator based on a planetary roller screw transmission are outlined to improve the accuracy of reproducing a given law of motion and speed characteristics of the actuating elements of technological equipment and technical systems of rocket and rocket-space complexes and in complex tests of large-mass rockets. A mathematical model of a controlled electromechanical drive for special assembly and docking equipment is presented. Tests have been carried out, on the basis of which it can be concluded that in order to create a high-precision electromechanical drive, it is necessary to use a gear with a smaller gap between the mating elements, high precision and operational reliability. A new design of a planetary roller screw transmission and the advantages of using a stepper motor are described. Mathematical modeling of an electromechanical drive with a planetary roller screw transmission with testing on a layout of an assembly and docking tilter will make it possible to create an electromechanical drive with improved technical and operational characteristics for the tilter of the space warhead of a super-heavy rocket and space launch vehicle.

Key. the words

Mounting and docking equipment; electromechanical drive; roller screw transmission; mathematical model; tests

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