Usage: in rocket and space technology and, more specifically, as part of upper stages (RB) spacecraft, launched from the base to high-energy working orbits. The essence of the invention: RB contains a cryogenic oxidizer tank, a toroidal tank (TB) of hydrocarbon fuel, a liquid-propellant rocket engine (LPRE) with an engine mount located along the axis of the fuel TB, a rod truss (SF) for interconnecting the oxidizer and fuel tanks, as well as SF for payload attachments and a transition compartment for connection with the previous stage of a space rocket, while the support nodes of the SF and the transition compartment are installed on the outer annular surface of the fuel tank, and the LRE attachment point is installed on the inner annular wall of the fuel tank, in particular, using radial pylons . This makes it possible to reduce the weight of the rocket launcher, using the fuel tank as the main power unit in the design of the rocket launcher and fixing the cryogenic oxidizer tank and the rocket engine mount directly on it. 1 z.p. f-ly, 2 ill.

The invention relates to rocket and space technology and concerns the design of booster rocket blocks (upper blocks) of space vehicles that are part of a space rocket and are intended for launching various space objects of payloads from a base orbit into working high-energy orbits. Known booster block L for the spacecraft "Vostok", containing located on a common axis liquid rocket engine (LRE) and toroidal fuel tanks of cryogenic oxidizer (liquid oxygen) and hydrocarbon fuel (kerosene), interconnected by an inter-tank frame transition compartment and internal power beams , while the LRE is located in the central part of the toroidal fuel tank, limited by its inner annular wall, and is mounted on a power frame mounted on internal power beams, and a rod truss is located on the inner annular wall of the toroidal oxidizer tank for attaching the payload. the presence in it of a frame inter-tank compartment, which increases heat loss to the cryogenic oxidizer tank and worsens the weight characteristics of the block. The implementation of the toroidal cryogenic oxidizer tank is not optimal from the point of view of ensuring the conditions for storing the cryogenic component in space conditions due to the relatively large surface of the tank, and also from the point of view of minimizing the mass of the tank due to the presence of cylindrical inserts in it. Closest to the proposed is upper stage D for the L1 lunar space complex, containing a liquid-propellant rocket engine (LPRE), a toroidal tank of hydrocarbon fuel and a spherical tank of cryogenic oxidizer, connected to each other through a frame inter-tank compartment, to which they are connected using rod trusses, with this LRE is located in the central part of the toroidal fuel tank, limited by its annular wall, and is mounted on its own load-bearing frame, fixed by means of an internal rod truss on the inter-tank compartment, to the upper part of which a rod truss is also connected for attaching a space object and a transition compartment connecting the booster block with the previous stage of the space rocket The disadvantage of this booster block is that the connection between the oxidizer and fuel tanks is carried out using a power element made in the form of a frame inter-tank compartment and two rod trusses fixed at its ends. This leads to the need to strengthen the constituent parts of this power element to ensure sufficient structural rigidity, which is associated with an increase in the mass of the upper stage and, accordingly, leads to a decrease in the mass of the payload launched into orbit. The disadvantage is also the fixing of the power frame of the rocket engine (the mount of the rocket engine) on the frame inter-tank compartment, which is significantly remote from the rocket engine, which leads to an increase in the size and weight of the internal rod farm for attaching the power frame of the rocket engine to the inter-tank compartment. At the same time, in order to achieve the necessary rigidity of this design of the upper stage, additional rod couplers were introduced into it, connecting the power frame of the rocket engine with the toroidal fuel tank covering it. The objective of the invention is to reduce the weight and simplify the design of the upper stage of the spacecraft. The solution of the problem is provided due to the fact that in the upper block containing the cryogenic oxidizer tank, the toroidal hydrocarbon fuel tank, the liquid rocket engine with the engine mount located along the axis of the fuel tank, the power element of the mutual connection of the oxidizer and fuel tanks, as well as the rod truss for fastening the payload and the transition compartment for connection with the previous stage of the space rocket, in accordance with the invention, the power element of the mutual connection of the oxidizer and fuel tanks is made in the form of a rod truss, while the support nodes of the rod trusses and the transition compartment are located on the outer annular wall of the toroidal tank fuel, and the engine mount is fixed on the inner annular wall of the fuel tank. In a particular case of the invention, the mount of the liquid rocket engine can be fixed to the toroidal fuel tank using radial pylons. The placement of the support nodes of the rod trusses and the transition compartment on the outer annular wall of the toroidal fuel tank and the fastening of the LRE attachment point on the inner annular wall of the fuel tank determines the use of this tank as the main power unit in the upper stage design. This makes it possible to simplify the design and reduce the weight of the booster block by fixing the cryogenic oxidizer tank with a rod truss directly on the fuel tank, excluding the frame inter-tank compartment and the additional rod truss from the design of the booster block. The use of a toroidal fuel tank as the main power unit of the upper stage also makes it possible to fix on it the engine mount located in close proximity to the inner annular wall of the fuel tank, using a rod truss or radial pylons mounted on the inner annular wall of the tank as a connecting power element. This allows to simplify the design, reduce the size and reduce the weight of the power element of the fastening in the upper block of the engine mount. Reducing the mass of the upper stage makes it possible to correspondingly increase the mass of the payload of the spacecraft. The use of radial pylons as a power element for securing the engine also makes it possible to additionally increase the rigidity of the toroidal fuel tank, which is very significant in the case of using a propulsion system with turbopump fuel supply to the LRE, in which the thickness of the fuel tank shell is less than in the installation with displacement fuel supply to the LRE . Figure 1 schematically shows a General view of the upper block, in section; in fig. 2 the location of the support nodes of the trusses and radial pylons mounted on the rocket engine on the toroidal fuel tank, view A. The upper stage contains a spherical cryogenic oxidizer tank 1, a toroidal hydrocarbon fuel tank 2 and a propulsion liquid rocket engine 3 with a gimbal assembly 4 engine mounts, sequentially located on a common axis , located in the central part of the toroidal tank 2, limited by the annular wall of the tank. The cryogenic oxidizer tank 1 is rigidly fixed (suspended) on the toroidal fuel tank 2 by means of a rod truss 5 made of a low heat-conducting material, for example, titanium or fiberglass, while the support nodes 6 of the truss 5 on the tank 2 are located, for example, on the annular frame 7 installed on the outer annular wall of the tank in its equatorial plane. The cardan assembly 4 of the engine mount is fixed on the toroidal fuel tank 2 with the help of radial pylons 8, installed by welding on the inner annular wall of the tank 2. compartment 11, made, for example, in the form of a rod truss, for connecting the upper stage with the previous stage 12 of the space rocket. The support nodes 13 of the rod truss 9 and the support nodes 14 of the transition compartment 11, as well as the support nodes 6 of the truss 5 of the oxidizer tank attachment, are located on the frame 7 installed on the outer annular wall of the fuel tank 2. The fuel tanks of the oxidizer 1 and fuel 2 contain in-tank devices, respectively 15 and 16, inside the oxidizer tank 1 there is also a cylinder 17 with pressurized gas. At the lower end of the fuel tank 2 there is also a block of nozzles 18 of the reactive control system of the upper stage. To reduce the weight of the pylons 8, they can be perforated. Since the main engine 3 of the upper stage is fixed on the inner annular wall of the toroidal fuel tank 2, on the outer annular wall of which there are support nodes 6 and 13 of the rod farm 5 for attaching the oxidizer tank and the rod farm 9 for attaching the payload, during the flight of the spacecraft from the base orbit to the working orbit, the fuel tank 2 plays the role of the main power unit of the apparatus. The placement of the support nodes 14 of the transition compartment 11 on the outer annular wall of the fuel tank 2 determines the use of this tank as the main power node when the spacecraft is launched into the base orbit by a space rocket. At the same time, in the case of using a propulsion unit from a displacement unit with displacement fuel supply to the LRE, the strength properties of the fuel tank make it possible to use it as the main power unit of the spacecraft without strengthening its structure. In the case of using a propulsion system with a turbopump fuel supply system, it is necessary to strengthen the shell of the fuel tank in the places where the support units are installed on it. RSC Energia has developed technical proposals for the design of an upper stage made in accordance with the invention. The upper stage is designed to launch a payload into a high-energy orbit after it has been delivered to an intermediate base orbit by a Molniya or Soyuz type space rocket. In the upper stage, a propulsion system with displacement fuel supply to the liquid-propellant rocket engine was used, which leads to increased strength characteristics of the fuel tanks, therefore, the fuel tank structure was not strengthened at the attachment points of the truss support nodes, the transition compartment and the engine mount assembly. In this particular case, the application of the invention made it possible to increase the mass of the payload of the spacecraft by 10% compared with the use of an upper stage made according to a known scheme (prototype).

Claim

1. An upper stage containing a cryogenic oxidizer tank, a toroidal hydrocarbon fuel tank, a liquid-propellant rocket engine with an engine mount located along the axis of the fuel tank, a power element for interconnecting the oxidizer and fuel tanks, as well as a rod truss for attaching the payload and a transition compartment for connection with the previous stage of the space rocket, characterized in that the power element of the mutual connection of the oxidizer and fuel tanks is made in the form of a rod truss, while the support nodes of the rod trusses and the transition compartment are located on the outer annular wall of the toroidal fuel tank, and the engine mount is fixed on inner annular wall of the fuel tank. 2. Block according to claim. 1, characterized in that the mount of the liquid rocket engine is fixed to the toroidal fuel tank using radial pylons.

The most important component of the system of launch vehicles are upper stages (UR), also called interorbital tugs. Upper stages ensure the movement of payloads to be launched from orbit to orbit or direct them to departure and interplanetary trajectories. To do this, the RB must be able to perform one or more maneuvers associated with a change in flight speed, for which, in each case, the main engine is supposed to be turned on. Between these inclusions follow long (up to several hours) sections of passive flight along transfer orbits or trajectories. Thus, any US must have a sustainer engine of multiple inclusion, as well as an additional reactive system or propulsion system that provides orientation and stabilization of the movement of the US with the spacecraft and the creation of conditions for launching the sustainer engine. At the same time, the operation of its engines can be controlled both from the spacecraft control system and from autonomous system management of the Republic of Belarus. In the latter case, it must have a special instrument compartment for its placement.

Upper stage "DM" is designed for use on the launch vehicle "Proton-K", "Proton-M" and "Zenit-3". In 1974, the upper stage “D”, created in the late 1960s, passed the first flight tests for launching a spacecraft into a geostationary orbit. for a lunar expedition. Subsequently, it was modernized, and since 1976, its modification, the “DM” block, has been used to launch a spacecraft on the GSO.

When launching the spacecraft to the GEO, the launch vehicle can operate according to a two- or three-pulse scheme. At the same time, depending on the longitude of the spacecraft’s stay in the GSO, the time spent by the RB in intermediate orbits changes and, accordingly, total time flight, which can be from 7 to 21 hours. During the flight, the US can operate either completely autonomously, or controlled via radio channels from the Earth.

The upper stage engine of the LRE RD-58M of multiple launch with a turbopump supply system is made according to the scheme with afterburning of oxidizing gas. It runs on fuel components: oxidizer - liquid oxygen, fuel - kerosene (RG-1). The engine is fixed in a cardan suspension on the inner tier of a two-tier truss. This engine setup allows you to control the pitch and yaw channels. Roll control uses a rotating nozzle powered by hot generator gas. The RD-58M liquid-propellant rocket engine also includes a multiple launch unit and pneumatically controlled automation units. In addition, two engines of the launch support system are installed on the RB, which are fixed on the lower bottom of the fuel tank and are designed to create an initial axial overload. They turn on before starting the main rocket engine. To prevent the thermal impact of the outflowing gas jet on structural elements and LRE, bottom protection is used, which is a frame welded from tubes, covered with EVTI.

The instrument compartment is made in the form of a sealed toroidal container and is fixed on the inner and outer tiers top farm. The container is made detachable and contains control system devices, as well as an air-liquid thermal control system. Upper stage "DM" is equipped with conical and cylindrical adapters that connect it with the launch vehicle. When the RB is separated from the third stage of the launch vehicle, the conical adapter is separated along with the stage, and after a while the cylindrical adapter is also dropped. The mass of the dry block without drop elements is 2200 kg, the maximum length is 6.26 m, the maximum diameter is 4.1 m, the mass of the SRT and gases is 15,095 kg.

Upper stage "Frigate" was created in NPO. S.A. Lavochkin for use as part of the Soyuz-2 launch vehicle. It allows up to 20 main engine starts in flight and has a fuel capacity of up to 5350 kg on board. LRE runs on AT + UDMH fuel components. Fuel is placed in four spherical tanks. Two more similar spherical containers are used as instrument containers. All six spheres are placed around the propulsion engine, the camera of which is installed in a gimbal suspension. The power frame of the cardan is attached to four brackets, each of which is welded to the corresponding fuel tank. On the RB "Fregat" there is also a propulsion system for orientation and ensuring the launch of the main engine. Its work is based on the catalytic decomposition of hydrazine, the supply of which (-85 kg) is placed in two small spherical tanks. The supercharger, which ensures the displacement supply of all fuel components, is carried out with helium. The first launch of the Fregat RB under the flight test program was successfully carried out on February 9, 2000 as part of the Soyuz launch vehicle.

In GKNPTs them. M.V. Khrunichev, the Breeze-M upper stage was created, designed to replace the blocks of the D / DM series and use it as part of the Proton-K and Proton-M launch vehicles. The new upper stage will make it possible to increase the mass of the payload delivered to the geostationary orbit up to 3 tons. Since 1999, the Briz-M launch vehicle has been undergoing flight tests.

RB "Breeze-M" consists of a central unit and a surrounding jettisonable toroidal additional fuel tank. The fuel compartment is cylindrical with a combined bottom with the front placement of the oxidizer tank. The top bottom of the oxidizer tank is spherical, and the bottom has complex shape and forms a hemispherical niche. This niche passes through the fuel tank and is formed by the inner conical shell of the tank. The conical shell is welded at the top to the lower spherical bottom of the oxidizer tank, and at the bottom - to the lower spherical bottom of the fuel tank.

Sustaining LRE, having the possibility of multiple (at least 10) switching on, is installed in a niche, inside the fuel tank of the central unit. Low-thrust rocket engines operating on the same fuel components as the sustainer engine provide orientation and stabilization of the rocket launcher during autonomous flight, as well as fuel compression in the tanks when the sustainer engine is launched. The inertial control system installed in the instrument compartment provides flight control of the Breeze-M rocket launcher and its onboard systems. The RB is also equipped with a power supply system and equipment for collecting telemetric information and for external trajectory measurements. When creating the RB "Breeze-M" great attention focused on improving its performance. So, in particular, refueling of the RB with fuel components is planned to be carried out at the factory, followed by ampulization of the block.

The principal feature of the Breeze-M RB design is the use of many systems and units from the Breeze-KM RB, created for the Rokot launch vehicle. To increase the carrying capacity of the Breeze-M missile launcher, it uses dumped toroidal fuel tanks in addition to the main ones in the central part of the block. The oxygen-hydrogen upper stage (KVRB) is being developed at the GKNPTs im. M.V. Khrunichev for use with the Proton-M launch vehicle, and in the future - with the Angara heavy-class launch vehicle. The creation of the KVRB was required to launch promising Russian spacecraft into high orbits and expand the range of services on the commercial launch market. The prototypes of this block were the unrealized project of the GKNPTs named after. M.V. Khrunichev cryogenic upper stage "Storm" and created for the Indian launch vehicle GSLV oxygen-hydrogen block 12KRB.

During the design of the KVRB, several of its variants were also developed for use as part of the Zenit and Arian-5 launch vehicles, but these variants have not yet found their customers. KVRB is made according to a single-stage scheme and consists of an upper adapter, a tank compartment, an engine compartment and a spacer between the KVRB and the launch vehicle. The KVRB tanks are load-bearing, arranged in series: on top - a tank of liquid oxygen, on the bottom - a tank of liquid hydrogen.

The control system and onboard measuring complex KVRB are created on the basis of similar systems of the Briz-M upper stage. The electronic blocks of these systems are installed on the top adapter. The adapter also has a docking element for installation on the KVRB spacecraft of both Russian and foreign production. Two versions of the KVRB propulsion engine are being considered: RD-0146 developed by KBKhA and KVD-1M developed by KBKhM. The RD-0146 engine is created on the basis of american engine RL10A-4-1 jointly with the Chemical Automation Design Bureau and Pratt & Whitney. The engine will be manufactured in Voronezh. The marching engine has a thrust in the void of about 10 tf. It is mounted in a gimbal to control the direction of the thrust vector in pitch and yaw. For rotation control, two blocks of steering micromotors are installed.

It is possible to start the engine multiple times to bring the payload to a given point. The spacer of the engine compartment allows the unit to dock with the Proton-M, Angara launch vehicles and other carriers with minimal changes. Refueling, compressed gases, supply temperature conditions fire safety, electrical connections are made through detachable on-board connectors located on the unit itself. The number of highways and electrical connections with the launch vehicle is minimal, which simplifies the adaptation of the launch vehicle to various carriers.

The lead manufacturer of KVRB will be the Rocket and Space Plant (RKZ) GKNPTs im. M.V. Khrunichev. Work on the draft design is being carried out in close cooperation with the technological services of the plant and KB Salyut, since part of the necessary technologies has already been mastered by the pilot production of KB Salyut in the manufacture of the Indian unit 12KRB. The tanks and part of the block structure are covered with combined thermal insulation, and the entire block is located under the head fairing. The space between the KVRB and the fairing is divided by diaphragms into several zones to ensure fire safety and the necessary temperature conditions.

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MINISTRY OF EDUCATION AND SCIENCE OF THE RUSSIAN FEDERATION

FEDERAL STATE BUDGET EDUCATIONAL INSTITUTION OF HIGHER EDUCATION

"MOSCOW AVIATION INSTITUTE

(National research university)" (MAI)

Branch "VOSHOD"

on term paper

on the topic: "Types of accelerating blocks"

discipline: "Introduction to the specialty"

Completed:

student of group VL2-48 Zhientaev A.B.

Baikonur 2016

List of abbreviations

RN - launch vehicle

KA - spacecraft

KRT - propellant component

RKN - space rocket

RKK - rocket and space complex

KAZ - oxygen-nitrogen plant

RB - upper stage

GSO - geostationary orbit

DU - propulsion system

K-k. c - structural layout diagram

Content

• List of abbreviations
• Introduction
• 1. Upper stage "Frigate"
• 1.1 Modifications of the upper stage "Frigate"
• 1.2 Launches
• 2. Upper stage "Breeze"
• 2.2 accidents
• 3. Upper stage "Agena"
• 4. Upper stage "Volga"
• 4.1 Exploitation
• 5.1 Application
• 5.2 Modifications
• 5.3 Development
• Annex A

Introduction

The upper stage, as well as the interorbital tug, is a means of launching a spacecraft designed to move payloads from the reference orbit to the target orbit or direct them to departure and interplanetary trajectories.

To accomplish this, upper stages must be able to perform one or more maneuvers associated with a change in flight speed, for which, in each case, the main engine is supposed to be turned on. Between these inclusions follow long (up to several hours) sections of passive flight along transfer orbits or trajectories. Thus, any upper stage must have a multiple-switch main engine, as well as an additional propulsion system or propulsion system that provides orientation and stabilization of the movement of the upper stage with the spacecraft and the creation of conditions for launching the main engine. At the same time, the operation of its engines can be controlled both from the control system of the spacecraft and from the autonomous control system of the upper stage itself. In the latter case, it must have a special instrument compartment for its placement.

1. Upper stage "Frigate"

"Fregat" is a universal booster block that can be used as part of a medium and heavy class launch vehicle. Designed and produced by NPO Lavochkin.

Drawing1 - Overclockingblock " Frigate"

The RB uses an engine similar to that used in the Breeze-M and Breeze-KM RBs. The thrust of this engine is 2 tons, which is close to the optimum for medium-class missiles, but not enough for the Breeze-M missile launcher, which is why the insertion into the geotransitional and departure trajectories has to be carried out in several pulses.

RB "Fregat" is used to launch a spacecraft into the reference, geostationary and geotransfer orbits of an artificial Earth satellite, as well as to orient and stabilize the head unit in the passive and active phase of the flight.

1.1 Modifications of upper stage "Frigate"

1) Basic, the so-called "Frigate"

upper stage interorbital tug

Designed for lower middle class missiles such as Soyuz-2, etc. It went through 3 stages of modernization, including one of the most significant - the replacement of BVK Biser-3 with Biser-6. The first launch of the Fregat upper stage took place in 2000 from the Baikonur cosmodrome.

2) "Frigate-SB" and "Frigate-SBU"

These "Frigates" with drop tanks. The mass of working fuel in a simple and improved block of tanks is 3100 and 4800 kg, respectively. This modification is intended for missiles of the upper medium and heavy classes, primarily for the Zenit-3SLBF ILV. Tests of the Fregat-SB modification started in April 2011 at the Baikonur Cosmodrome during the launch of the Elektro-L spacecraft.

3) "Fregat-M"

This is a frigate with a number of improvements to lighten the design, including a new layout of PO1 and with an increased carrying capacity (from 12 t x m to 16 t x m).

4) "Frigate-MT"

A specialized modification of the Frigate designed for launches from the Kourou cosmodrome. Increased refueling due to the installation of additional tanks, modified PO1, lightweight PxO. The rotation of the Earth allows a larger payload to be launched from the equatorial region than when starting from higher latitudes using the same launch vehicle. Also, wet equatorial climate Guiana differs significantly from the climate of Plesetsk and Baikonur. This required the refinement of the basic models of the block for use in new conditions. The first launch of this modification took place on October 21, 2011. The Soyuz-STB launch vehicle with the Fregat-MT upper stage launched 2 satellites of the European navigation system Gallileo into orbit.

1.2 Launches

The Soyuz-FG launch vehicle with the Fregat upper stage was used to launch the Mars-Express interplanetary station in 2003, and in 2005, a similar Venera-Express station.

Most of the launches of the Soyuz-2 launch vehicle were carried out using the Fregat missile launcher, in particular, all Glonass-K satellites, third-generation GLONASS satellites, will be launched with just such a bundle.

On December 19, 2013, the Fregat-MT upper stage launched the European telescope Gaia into orbit.

The Soyuz-ST-B launch vehicle with the Fregat-MT upper stage and two European Galileo satellites, launched from the equatorial Kourou cosmodrome on August 22, 2014, did not put the satellites into the estimated orbit due to abnormal operation of the Fregat-MT RB ", presumably as a result of an error in software placed on board and containing an incorrect flight assignment.

Starting from 2000 and until August 2016, 58 Fregat upper stages were launched (of which 1 was launched in an emergency due to the fault of the upper stage on August 22, 2014). More than 100 Russian and foreign-made spacecraft have been launched into calculated orbits. Launches are carried out from three cosmodromes: Plesetsk, Baikonur, Kourou (French Guiana).

RB "Fregat" has exceptional characteristics: long (up to 2 days) time of active existence, control algorithms that allow to overcome emergency situations, multiple (up to 7 times) switching on of the marching propulsion system, the highest reliability and, practically, ideal launch accuracy due to the use GLONASS/GPS equipment.

2. Upper stage "Breeze"

"Breeze" is a family of Russian upper stages used as part of a light and heavy class launch vehicle.

Developed at the State Space Research and Production Center. M.V. Khrunichev. Blocks of the "Breeze" family are distinguished by a very dense layout. It uses "heptyl" and "amyl" as fuel. First flight May 16, 2000.

Figure 2. Breeze-M

2.1 Modifications of the upper stage "Breeze"

1) RB "Breeze-M" can be used with launch vehicles Angara, Proton-M. The unit provides payload launch into low, medium, high orbits and GSO. The use of the Breeze-M launch vehicle together with the Proton-M launch vehicle makes it possible to increase the mass of the payload launched into the geostationary orbit up to 3.7 tons, and over 6 tons into the transfer orbit. The first launch of the Briz-M RB took place on July 5, 1999. LV "Proton-K" (emergency launch). The first successful launch took place on June 6, 2000 with the Proton-K launch vehicle and the Gorizont spacecraft. The first launch of the Proton-M - Breeze-M complex took place on April 7, 2001. At the beginning of 2013, more than 55 launches of Proton rockets from the Breeze-M rocket launcher were carried out.

2) RB Breeze-KM is used as the third stage of the Rokot light class launch vehicle. The propulsion engine of the block has the possibility of repeated inclusion, which allows the use of various schemes for launching spacecraft, including the group launch of spacecraft into one or several different orbits. The first launch of the Breeze-KM RB took place on May 16, 2000. The Rokot ILV with payload equivalents (EPL) SimSat-1 and SimSat-2.

2.2 Accidents

Breeze-M was the cause of a number of accidents involving the Proton launch vehicle from 2008 to 2013. According to statistics, since 2008, 48 launches of the Proton rocket have been carried out (31 commercial launches and 17 within the framework of the federal space program), of which four ended in accidents due to the fault of the Breeze-M upper stages.

3. Upper stage "Agena"

RM-81 Agena RM-81 Agena) is an American upper stage and satellite support platform, originally developed by Lockheed in the interests of the WS-117L reconnaissance satellite program. After splitting WS-117L into the SAMOS and CORONA photo reconnaissance satellite development programs and the MIDAS missile early warning satellite development program.

Figure 3. Agena VIII as a target for docking with the Gemini 8 manned spacecraft as part of the Gemini program, March 1966.

Agena began to be used as an upper stage and one of the main components in several programs, including when launching CORONA photo reconnaissance satellites into orbit and as a target for rendezvous and docking in space with manned spacecraft under the Gemini program. It was used as an upper stage as part of the Atlas-Agena, Tor-Agena, Torad-Agena and Titan-3B launch vehicles, and the possibility of its use in the Space Shuttle and Atlas-5 programs was also studied.

In total, starting from February 28, 1959, the Agena was launched 365 times, the last launch took place in February 1987 (in the version Agena D).

The RM-81 "Agena" is adapted for a long stay in outer space with repeated launches of the propulsion system for orbit correction and descent of the spacecraft. The mass of the stage with fuel is about 7 tons, the thrust of the liquid rocket engine is 72 kN.

3.1 Variants of the "Agena" stage

4. Upper stage "Volga"

"Volga" - spacecraft launch unit developed by TsSKB-Progress, designed to work together with the Soyuz-2 launch vehicle.

Figure 4. Upper stage "Volga"

The energy characteristics of the unit allow, when launched from the Plesetsk cosmodrome, to put a payload weighing up to 1700 kg into a circular orbit with a height of 1000 km (inclination 62.8°), for an orbit with a height of 1500 km (inclination 82.4°) the maximum payload mass will be 1400 kg. When launched into a sun-synchronous orbit with an altitude of 835 km and an inclination of 98.7 °, the payload will also be 1400 kg.

Work on the creation of the launch unit began in 2008. The need for this block arose due to the fact that the existing upper stages of the Soyuz-2 launch vehicle make it possible to implement only a single-pulse launch scheme. This does not allow implementing an energetically optimal launch scheme, especially for circular orbits with a height of more than 250-300 km.

The draft design was defended in 2010, and the design documentation was issued the same year.

The main part of the onboard equipment of the unit was taken from other products of TsSKB-Progress with the appropriate modification.

4.1 Operation

1) December 28, 2013 at 16:30 Moscow time, the Soyuz-2.1v carrier rocket with the Volga launcher was launched, the payload was the AIST No. 1 spacecraft and two SKRL-756 calibration spheres. At 18:10 the spacecraft successfully separated from the launcher in the target orbit.

2) On December 5, 2015 at 16:30 Moscow time, the Soyuz-2.1v carrier rocket was launched with the Cosmos-2511 and Cosmos-2512 spacecraft of the RF Ministry of Defense. Perhaps one of the two military satellites did not separate from the upper stage "Volga".

3) On April 28, 2016, the Soyuz-2.1a carrier rocket with the Lomonosov, Aist-2D and SamSat-218 spacecraft was launched from the Vostochny cosmodrome.

5. Family of accelerating blocks "D"

A family of upper stages (upper stages) derived from the upper stage Block "D" - the fifth stage of the space missile system N1-L3, intended for the flight to the moon of Soviet cosmonauts.

A pair of liquid oxygen - kerosene is used as fuel, while refueling with synthine is allowed without altering the structure.

Figure 5. Engine 11D58M

As part of the standard complex, block "D" was responsible for transferring the LK-LOK link from the flight trajectory to the lunar orbit, for transferring the LK from the lunar orbit to the landing trajectory, as well as for corrections during the flight (blocks A, B and C - the first three stages of the rocket H-1, which put the complex into low Earth orbit, block "G" accelerated the expedition to the Moon). Therefore, the maximum number of engine starts of block D (it has the index 11D58, or RD-58 in some sources) was seven, and the lifetime of block D was equal to 7 days. To do this, the oxygen tank had the shape of a sphere and was equipped with thermal insulation. In addition, it was filled with oxygen cooled to? 200 ° C (boiling point? 183 ° C), which made it possible to further reduce evaporation losses, and, in addition, increased the density of liquid oxygen, saving the required tank volume. The kerosene tank had a toroidal shape and was tilted 3 degrees to simplify the design of the fuel intake. The thrust of the 11D58 engine was 8.5 tons.

5.1 Application

In connection with the unavailability of the N-1 rocket, it was decided to launch a program to fly around the moon without landing using the UR-500K rocket. For this, it was developed spaceship 7K-L1, which borrowed part of the systems from the 7K-OK orbiter, known as the Soyuz. To give the ship the necessary speed, the three-stage UR-500K was equipped with a fourth stage - block D, borrowed from the N-1 rocket.

Under the names "Zond-5" - "Zond-8", the 7K-L1 spacecraft circled the Moon four times, but without astronauts ("Zond-4" was launched in the opposite direction from the Moon into a highly elliptical orbit with an apogee height of about 330,000 km).

The requirements for block D as part of the lunar complex did not quite correspond to what was needed for AMS and communication satellites.

As a result, a modification was undertaken aimed at increasing the carrying capacity and reducing the cost of block D. The modified upper stage, called DM, had an active life of only 9 hours, and the number of engine starts was limited to three. This made it possible to get rid of the thermal insulation on the oxygen tank, and part of the blocks of the POP launch support system.

In connection with the different requirements for a variety of payloads, other modifications were developed - DM-2, DM-3. To work as part of the Zenit-3SL complex, a modification of the DM-SL was developed. In addition to kerosene, the DM block can use the synthetic hydrocarbon sintin as fuel, which increases the specific impulse of its engine from 358 to 361 units.

The use of the DM block on the Proton rocket is coming to an end - it is being replaced by the Briz-M block, but in the Sea Launch program the DM-SL block (and in the Land Launch program the DM-SLB is used) will continue to be used. This is due to the fact that Breeze-M uses the same propellant components as the Proton rocket, while Blok DM, on the contrary, corresponds to the Zenit rocket. It is interesting, however, that for launching GLONASS-M satellites (Uragan-M) into circular orbits with an altitude of about 20,000 km, the DM block provides a higher launch accuracy than Breeze-M, and therefore its use on the Proton-M rocket will apparently stop , only after the final replacement of the Uragan-M (GLONASS-M) satellites with new non-pressurized GLONASS-K devices, flight tests of which began in February 2011. Nevertheless, on December 5, 2010, the first launch of a new modification of the DM block (11С861-03) was carried out with increased refueling and a higher carrying capacity. The DM-03 block was used to launch a trio of GLONASS-M satellites, but the launch into orbit ended unsuccessfully.

The attitude towards the decommissioning of the DM block changed somewhat after the Breeze-M accidents in 2006 during the launch of Arabsat-4A and in 2008 during the launch of AMS-14, and, perhaps, the DM block will remain in operation for insurance and as option for commercial customers.

On August 19, 2012, the DM-SL upper stage set a record for launch accuracy. At present (as of August 20, 2012) it is the only block of the D family permitted for use.

5.2 Modifications

1) Block D (11S824) - the prototype of this block is block D, developed by OKB-1, as the fifth stage of the N1-L3 complex, part of the Soviet lunar landing manned program. On block "D" of the L3 complex, the 11D58 engine developed by OKB-1 was installed. The 11D58 engine, made according to a closed circuit, was for the first time supposed to provide multiple launches in outer space and weightlessness by spinning up the booster tank turbopump unit of the oxidizer with compressed gas from the autonomous gas-balloon section of the pneumohydraulic start-up system of the "D" block. During the pneumatic start-up, the oxidizer pump created a significant pressure (about 10 kg/cm2), which ensured reliable filling of the uncooled oxidizer path with liquid oxygen and First level gas generator gas flow through the turbine of the main HP, necessary for the engine to enter normal mode. Such a scheme ensured minimal oxygen losses for cooling down the PS. To reduce the heat inflow to the oxidizer (supercooled oxygen with a temperature of up to −193°C), the spherical shape of the oxidizer tank with screen-vacuum thermal insulation was adopted, and all connections were made using thermal bridges. The fuel tank, inside which the engine was located, had the shape of a torus. On the block were first applied technical solutions, which later became classic in rocket technology (for example, the use of tank pre-pumps that are part of the engine, and the storage of helium in cylinders immersed in liquid oxygen).

2) DM (11S86) - a modification of block "D", designed to launch communication and television satellites into geostationary orbit, developed by Design Bureau PM (Chief Designer M.F. Reshetnev). The communication satellites did not have rocket unit control equipment, so the "D" unit was equipped with an independent control system located in a sealed toroidal instrument compartment, which also housed telemetry equipment and a command radio link. The instrument compartment was installed on a special truss above the oxidizer tank and had a thermal control system. On block "D" was installed the engine 11D58M, developed at NPO Energia under the leadership of B.A. Sokolov. This engine is mass-produced at the Voronezh Mechanical Plant. The modified accelerating unit had an active lifetime of 9 hours, and the number of engine starts was limited to three. Currently, upper stages of models DM-2, DM-2M and DM-03 manufactured by RSC Energia are used, in which the number of inclusions has been increased to 5.

5.3 Development

The development of the DM block began in 1969. The block of this modification from August 3, 1973 to July 30, 1975 passed six fire tests, during which the block was refueled two or three times, and the engine was turned on 4-5 times. It has been operated with the Proton launch vehicle since 1974.

Characteristics:

- Dry weight of the booster block "DM" - 3420 kg,

- The mass of elements separated in flight - 1090 kg;

- The mass of the spacecraft, displayed on the GSO, - up to 2600 kg;

- Refillable stock of fuel components - 15050 kg;

- Length - 6280 mm

- Width (diameter) - 3700-4100 mm

- Engine thrust 11D58M in the void - 8550 kgf

- Specific thrust (in the void) - 361 s

Block "DM" consists of: main engine; two propulsion systems for stabilization and orientation; spherical oxidizer tank; toroidal fuel tank; instrument compartment; equipment of the command-measuring complex; detachable in flight lower and middle adapters. Proven engine reliability 0.997 with a confidence level of 0.9. Each engine passes control tests without overhaul using progressive means of diagnosing a technical condition.

List of sources used

1. Gudilin V.E., Slabkiy L.I. Accelerating blocks. Nuclear power plants of space vehicles. Nuclear rocket engines. // Rocket and space systems (History. Development. Prospects). - M., 1996. - 326 p.

2. Gudilin V.E., Slabkiy L.I. Design studies of promising upper stages // Rocket and space systems (History. Development. Prospects). - M., 1996. - 326 p.

3. http://space. skyrocket. de/doc_stage/fregat. htm

4. http://www.laspace.ru/rus/fregat_construction. php

5. Kurenkov V.I., Design and design of products of rocket and space technology. Part 2. Fundamentals of designing launch vehicles. - Samara, 2012.

Annex A

Structural and layout diagram of the RB "Fregat"

Notation

1 - head fairing

2 - upper tank RN

3 - adapter

4 - payload - small satellites

5 - upper stage

6 - farm to install the payload

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One of the stages of the launch vehicle. With the help of the upper stage, the spacecraft is transferred from an orbit called the reference one to other near-Earth orbits or is put on a departure trajectory to other planets.

Block "L" was the first of the Soviet accelerating blocks, which allowed launching in zero gravity. The first flight was supposed to take place in 1960, but due to computer flaws, the launch was not made. On February 12, 1961, the first successful launch took place as part of the Venera-1 automatic interplanetary station. The upper stage "L" was created to launch the first interplanetary stations of the "Venus", "Mars" series and the lunar stations "Luna-4", "Luna-13". The booster block "DM", running on a fuel mixture, which includes liquid oxygen and kerosene, is a modification of block "D" of the N1-LZ space rocket complex, which was intended for flights to the moon. Block "D" was the fourth stage in the complex. The first three took the apparatus into low orbit, and the fifth accelerated the expedition to the Moon. The oxygen tank was made in the form of a sphere and equipped with thermal insulation. The tank was filled with oxygen, the temperature of which was about -200 °C. Such a low temperature of oxygen is necessary to reduce losses due to evaporation, because the boiling point of liquid oxygen is -183 ° C. With a decrease in temperature, the density of oxygen increases and, accordingly, the occupied volume decreases. The Proton rocket with upper stage D was used to launch the interplanetary stations of the Venera series from No. 9 to No. 16, the Vega and Phobos stations, and the Luna lunar stations from No. 15 to No. 24. Later, in 1974, the launch of the Gorizont and Ekran satellites into stationary orbits began using upper stages D.

All the new requirements imposed by interplanetary stations and communication satellites led to the fact that a number of changes were made. The time of active existence increased to 9 hours, and at the same time, the number of engine starts was reduced. This made it possible to remove the thermal insulation of the engine tank and a number of blocks of the launch support system.

At present, the use of the D upper stage as part of the Proton complex is coming to an end, but the DM-SL modification remains part of the Zenit complex. The Proton rocket will use the Breeze-M block, since it uses the same fuel components, for the same reason the DM-SL block remains in service as part of Zenit. The Breeze-M upper stage, the first launch of which as part of the Proton-M rocket complex took place on April 7, 2001, ensures the launch of the payload into low, medium, high orbits, including geostationary orbits.

When using the Briz-M block, the mass of the payload launched into the Earth's geostationary orbit increases to 3.3 tons. The modification, the Breeze-KM upper stage, thanks to the possibility of repeatedly turning on its main engine, allows the use of various schemes for launching spacecraft into space, including the implementation of a group launch into several different orbits. NPO Lavochkin developed a new-generation Fregat upper stage. Scope of application - as part of launch vehicles of medium and heavy classes. It can carry out insertion into reference orbits, geostationary and geotransfer orbits, is used in various areas for stabilization and orientation. In 2000, the first launch of the Frigate took place. In 2005, Fregat, as part of the Soyuz-FG launch vehicle, made it possible to launch the Venera Express interplanetary station.

As for the development prospects, at the present time in the GKNPTs them. Khrunichev, together with NPO Molniya, is developing reusable accelerators of the Baikal type instead of universal disposable upper stages. To implement this project, the upper stage of the new model must be equipped with a rescue system based on the concept of an unmanned aerial vehicle, which must return in subsonic cruising flight to the launch site. It is necessary to equip the upper stage with an auxiliary air-jet engine and plumage, the layout is carried out according to the aerodynamic scheme.

To orient the spent upper stage before entering the dense layers of the atmosphere, the blocks are equipped with a reactive control system; after entry into the atmosphere, control is carried out by aerodynamic controls. Gliding turns into a motor flight, implemented by air-jet engines, which can be installed in the bow of the reusable booster. For landing, the block can be equipped with an aircraft-type wheeled landing gear. It is necessary to equip the upper stage with an onboard measuring complex, which will collect and transmit to the cosmodrome information on the state and functioning of onboard systems.

The first tests of reusable launch vehicle boosters of the Angara family on scale models have already been carried out by the developers. The technology of reusable upper stages is simple enough to be implemented and used during the launch of launch vehicles in the coming years. With the optimization of structural and ballistic characteristics and various control programs, the losses caused by the use of the rescue system will not exceed 50% of the mass of the payload launched into a low circular orbit. The introduction of such reusable upper stages, in addition to reducing the unit cost, will reduce the impact fields of spent parts of launch vehicles and unload production lines for the subsequent implementation of other projects.

Upper stages (UR), often referred to as interorbital tugs, ensure the movement of payloads to be launched from orbit to orbit or direct them to "takeoff" and interplanetary trajectories. To do this, the RB must be able to perform one or more maneuvers associated with a change (as a rule, an increment) of the flight speed, for which, in each case, its main engine is supposed to be turned on. Between these inclusions, long (up to several hours or more) sections of passive (due to inertia) flight along transfer orbits or trajectories follow. Thus, any US must have a sustainer engine of multiple inclusion (most often, LRE), as well as an additional reactive system or propulsion system that provides orientation and stabilization of the movement of the US with the spacecraft, as well as the creation of conditions for launching the sustainer engine. At the same time, the operation of its engines can be controlled both from the spacecraft control system and from the autonomous control system of the US itself. In the latter case, it must have a special instrument compartment for its placement.

The world's first RB - block "E" for the Soyuz launch vehicle was created in OKB-1 under the leadership of S.P. Korolev to ensure the flight of the Luna-1 spacecraft, which launched on January 2, 1959. Subsequently, this block began to be used as the third stage of the Vostok-type launch vehicle. The marching oxygen-kerosene rocket engine RD-7, which is part of it, was created in record time (6 months) on the basis of the development chamber of M.V. Melnikov and the turbopump unit of S.A. Kosberg.

Later, in the Central Design Bureau of Experimental Engineering (as OKB-1 became known), under the leadership of M.V. Melnikov, an oxygen-kerosene LRE S1-5400 was also created and for the second domestic RB - block "L". This engine, being the first liquid-propellant rocket engine in the world with generator gas afterburning on these components, had a high specific impulse and a long service life, which ensured its successful and long-term operation as part of the Molniya launch vehicle. Block "L" was widely used for flights of interplanetary spacecraft of the "Luna", "Venus" and "Mars" types, and was also often used to launch the Prognoz solar observatories and satellites

Molniya communications to highly elliptical orbits.

However, the main breakthrough in the creation of multipurpose RBs took place at the end of the 60s and was associated with the implementation of the N1-LZ project, which was intended to carry out a lunar expedition. Then two sufficiently powerful RBs were created at once - blocks "G" and "D", which were part of the head block of the LZ. Both blocks also used liquid oxygen and kerosene as propellant components, and their engines were created at the Central Design Bureau of EM by upgrading and forcing the LRE S1-5400 of the "L" block. Unfortunately, block "G" after the termination of work on the N1-LZ program did not find application, but block "D", at the suggestion of S.P. Korolev, was installed on the Proton-K launch vehicle for the implementation of the UR-500K- L 1 - the first stage of the manned lunar program. After the closure of this program, block "D" was actively used for flights of automatic stations to the Moon, Venus and Mars. At present, its use is in the plans of the next interplanetary expeditions.

Block "D" proved to be very successful for launching payloads into geostationary orbit. In 1974, it passed the first flight tests in this capacity, was modernized, and since 1976, its modification, the "DM" block, has been used to launch a spacecraft into geostationary orbit. The "DM" block, unlike the "D" block, has an autonomous instrument compartment with its own control system. Over the past years, the RD-58 LPRE of the "D" block has also undergone modernization. Currently, blocks "D" and "DM" are equipped with the RD-58M engine, developed already at NPO Energia under the leadership of B.A. Sokolov, who replaced M.V. Melnikov as Chief Designer. LRE RD-58M, unlike the previous modification, can run on synthine instead of kerosene, which gives a significant increase in specific impulse. In addition, the number of engine starts has been increased to 7.

Note also that S.P. Korolev, even when preparing the N1-LZ project, made plans to replace the oxygen-kerosene RB (blocks "G" and "D") on the upper stages of the H1 launch vehicle with one oxygen-hydrogen one. Therefore, in OKB-1, in parallel with the development of blocks "G" and "D", work was carried out to create a perfect oxygen-hydrogen rocket engine (under the leadership of M.V. Melnikov) and a powerful upper stage based on it. These works did not stop completely even after the death of S.P. Korolev. They went as part of the development under the leadership of V.P. Mishin of a new, more advanced program for an expedition to the moon. Work on the powerful oxygen-hydrogen RB was brought to the stage of issuing design documentation for the flight product. Moreover, the block itself was developed in the OKB-1 department, which previously carried out work on the H1 launch vehicle, and the RD-56 engine for it was created by 1974 at the OKB A.M. Isaev. It was the world's first oxygen-hydrogen rocket engine with generator gas afterburning. At that time, he held a leading position in the field of economy, resource and reliability. Moreover, work in the Isaev Design Bureau on the RD-56 reached the stage of final bench tests of the rocket engine.

In May 1974, TsKB EM became part of the newly created NPO Energia, whose General Designer was V.P. Glushko. The new General Designer then did not fully understand the prospects for hydrogen fuels, moreover, from the very beginning he was an ardent opponent of the N1-LZ project. Under his "hot" hand, the project of a powerful oxygen-hydrogen RB fell, work on which was stopped. And only relatively recently this project was revived, and on the basis of the RD-56 LPRE, it is planned to create a new oxygen-hydrogen upper stage (KVRB), which is supposed to be used on promising launch vehicles. In particular, it is planned to install the KVRB instead of the DM block on the Proton-M launch vehicle as part of its modernization,

In other design bureaus, work on the creation of RB was limited to the use of high-boiling MCTs. So, in NPO "Yuzhnoye" for the launch vehicle "Cyclone" was developed RB S5M on nitrogen tetroxide and UDMH. It is used as the third stage of the Cyclone-3 launch vehicle.

Recently, two more promising RBs have been developed for the same fuel components. One of them - RB "Frigate"- created in NPO them. S.A. Lavochkin. It allows up to 20 inclusions of a sustainer rocket engine in flight and has a fuel reserve on board of up to 5350 kg. It is placed in four spherical tanks. Two more similar spherical containers were used as instrument containers. All six spheres are placed around the mid-flight rocket engine, the camera of which is installed in a gimbal suspension. The power frame of this gimbal is attached to four brackets, each of which is welded to the corresponding fuel tank. The RB "Fregat" also has a propulsion system for orientation and launch of a sustainer rocket engine. It works on the catalytic decomposition of hydrazine, the stock of which (about 85 kg) is placed in two small spherical tanks. Each of the micromotors of this remote control has a thrust of 50 N with a specific impulse of 2250 N * s / kg. The pressurization of the tanks, which ensures the displacement supply of all fuel components, is carried out with helium.

The second promising RB for AT and UDMH "Breeze" was developed in the Salyut Design Bureau. It provides up to 25 inclusions of a sustainer rocket engine and has a working fuel reserve of up to 5150 kg. The fuel compartment is cylindrical with a combined bottom with the front placement of the oxidizer tank. The top bottom of the oxidizer tank is spherical, while the bottom bottom has a complex shape and forms a hemispherical niche. This niche passes through the fuel tank and is formed by the internal conical shell of the tank.

The conical shell is welded at the top to the lower bottom of the oxidizer tank, and at the bottom - to the lower spherical bottom of the fuel tank. In the niche of the fuel compartment there is a mid-flight rocket engine.

Unlike Frigate, which has a large diameter and small longitudinal dimensions, Breeze, on the contrary, has a small diameter and a significantly greater length. This allows, with other almost identical performance characteristics (see Table B.1), to use one or another RB on the launch vehicle, depending on the conditions of its layout on the launch vehicle and the size of the spacecraft. When creating the Breeze US, much attention was paid to improving its operational properties. Thus, in particular, the filling of the block with rocket fuel components is planned to be carried out at the factory, followed by the ampoule of the block. Similar technology is used for SLBMs.

The main performance data of the existing and developed upper stages are presented in Table 1.

The refueling of the RB with high-boiling components of rocket fuels and compressed gases is carried out at the spacecraft refueling stations of the cosmodrome, low-boiling

components - at the RKK launch complex.

Refueling of the promising RB "Fregat" is planned to be carried out at the plant

children's conditions with subsequent ampulization of fuel tanks (compartments).

Under ampulization refers to the complete isolation of the fuel tank from the environment through gas and hydraulic channels.

To prevent mechanical damage to fuel tanks due to changes in ambient temperature before refueling components rocket propellants they are saturated with gas (for AT and UDMH, saturation is carried out with nitrogen).

Table 1. Main tactical and technical data of the Republic of Belarus

Name of the Republic of Belarus	Components RT (O + G)	DU thrust,	Remote control operating time, s	Number of inclusions	PH on which RB is used
BREEZE	AT + UDMH				"Rokot", "Angara", "Proton-M"
KVRB	Oxygen+hydrogen				"Proton-M", "Angara"
	Oxygen+kerosene				"Proton-K" "Zenith-3"

change in ambient temperature, before filling the components of rocket fuels, they are saturated with gas (for AT and UDMH, saturation is carried out with nitrogen).

The use of an oxygen-hydrogen upper stage (KVRB), engine

The power plant of which, in terms of specific impulse (i.e., in terms of energy perfection), by 18-28% exceeds the propulsion systems of the RB on other SRTs, will allow the Proton-M and Angara A5 launch vehicles to launch a payload weighing 4.2 into geostationary orbit t (for comparison, the Proton-K launch vehicle with the DM RB displays 2.4t on the GSO).