Thus, all Soviet and subsequently Russian spacecraft TKS, L-1/Zond, artificial satellites, orbital and interplanetary stations (Salyut-DOS, Almaz), Mira modules and the ISS were launched into orbit by Proton series launch vehicles. By the mid-2000s, the Proton-M modification became most widespread. It accounts for the bulk of spacecraft launched into orbit (federal Russian and commercial foreign).

Initially, the UR-500 (universal rocket) was designed and created as an orbital and intercontinental ballistic missile capable of delivering a super-powerful (100 megatons or more) thermonuclear warhead to any point on the planet. However, the option of using it as a launch vehicle for heavy satellites was also envisaged. On July 16, 1965, the first launch of the two-stage LV UR-500 took place. The payload was the N-4 No. 1 Proton-1 spacecraft. A total of four launches were carried out between 1965 and 1966.

As part of the Soviet “lunar program”, since July 1965, a new three-stage launch vehicle UR-500K (8K82K “Proton-K”) has been developed and, in parallel, the design of the fourth stage began. Officially, the birthday of the Proton-K launch vehicle is March 10, 1967, when a three-stage rocket with a block D and KK 7K-L1P (“Cosmos-146”) was launched.

Despite significant successes and a large number of successful design solutions, the number of accidents was too high (in the period from March 1967 to August 1970 - 21 launches, and only 6 completely successful). This delayed the adoption of the Proton-K launch vehicle into service until 1978 (after 61 launches). The last launch of a rocket of this class was carried out on March 30, 2012. It was collected at the State Research and Production Space Center named after. M.V. Khrunichev in the late 2000s and was kept in the arsenal. The purpose of the launch is to launch the last satellite of the US-KMO series into orbit. In this case, the last time the accelerating block version DM-2 was used. Currently, Proton-K is out of production. From 1967 to 2012, launch vehicles of this series were launched 310 times. The three-stage Proton-K version was used to deliver the payload to so-called low orbits, and the four-stage version was used to deliver high-energy orbits. To a height of 200 km, the Proton could lift up to 21 tons of payload, and to GSO (geostationary orbit) - up to 2.6 tons.

In 2001, GKNPTs im. M.V. Khrunichev switched to the production of a new modification 8K82KM, otherwise - “Proton-M”. The modern rocket is superior to previous modifications in terms of environmental friendliness. In addition, new upper stages are installed on it - 14C43 Briz-M, thanks to which it is possible to significantly increase the payload when ascending to geostationary transfer and geostationary orbits. The Proton-M launch vehicle is equipped with a high-precision digital control system based on an on-board digital computer complex. And finally, it became possible to increase the size of the fairings compared to the previous Proton-K launch vehicles.

Layout of the three-stage Proton launch vehicle

The first stage is made in the form of blocks. The central one has a tail compartment, an oxidizer tank and a transition compartment. Six side blocks are symmetrically placed around it. Each of them is divided into a front compartment, a fuel tank and a tail compartment. The latter houses a propulsion liquid rocket engine of the RD-253 type. Thus, we can say that the first stage propulsion system includes six autonomous liquid rocket engines. They are started by breaking through the pyromembranes located at the engine inlet. The RD-253 engine is equipped with a fuel supply system with afterburning of generator gas.

The second stage is made in the shape of a cylinder. Compartments: transition, fuel and tail. The propulsion system consists of three RD-0210 and one 0211 (all autonomous). The task of RD-0211 is to ensure pressurization of the fuel tank. All of them can deviate in tangential directions at an angle of up to 3°15". The total thrust of the propulsion system is equal to 2,352 kN in vacuum. The second stage engines are launched before the first stage liquid rocket engine is turned on, due to which the “hot” principle of stage separation occurs. Namely:

The thrust of the second stage engines becomes greater than the residual thrust of the first stage rocket engine;
- the pyrobolts connecting the stage trusses are undermined;
- the steps begin to diverge;
- combustion products leaving the chambers of the second stage liquid propellant engine act on the heat shield of the first stage and repel it.

The third stage includes three compartments (instrument, fuel and tail) of a cylindrical shape. Equipped with one propulsion rocket engine.

The power plants of all stages of the Proton launch vehicle use the same propellant components. This is an unsymmetrical dimethylhydrazine (otherwise heptyl or UDMH), chemical formula of which - (CH3)2N2H2, as well as nitrogen tetroxide - N2O4. These components are classified as particularly toxic and require the most careful handling. Their use is due to the ability to increase the reliability of the propulsion system and simplify its design due to the self-ignition of the fuel mixture.

All Proton launches take place exclusively from the Baikonur Cosmodrome. There, by the beginning of 1965, launch and technical complexes were built - two workplaces (site 92/1) and two launchers (site 81). An additional launch complex (pad 200) was completed in the late 70s. The cost of one launch of a Proton-type launch vehicle, on average, costs $80 - $100 million or 2.4 billion rubles.

UR-500 Proton – Soviet/Russian heavy-class launch vehicle developed at OKB-52 Chelomeya (now Khrunichev State Research and Production Space Center) in the 1960s.

History of Proton rockets

In the early 1960s, the space race between the USSR and the USA reached its climax. Space exploration and emergence huge amount new technologies and techniques made recently developed missiles obsolete. Already by the beginning of the 1960s, the leadership of the USSR decided to create a new generation of rockets capable of launching both a large payload and heavy super-powerful nuclear charges into space.

The main design schools participated in the competition: Korolev Design Bureau proposed the N-1 rocket, Yangel Design Bureau the R-56 heavy rocket, and Design Bureau No. 52 under the leadership of Chelomey proposed a family of missiles called UR - Universal Rocket. Chelomey planned to create 4 unified missiles at once: the light ICBM UR-100, the medium ICBM UR-200, the heavy carrier UR-500 and the super-heavy carrier UR-700.

As a result of the competition, it was decided to abandon the light rocket option. OKB No. 52 received an order for a medium ICBM and a heavy launch vehicle. Korolev received the order for the super-heavy carrier with his N-1.

Initially, the UR-500 assumed a “package” design consisting of four parallel-connected UR-200 missiles, with a third stage also created on the basis of the UR-200. Over time, this scheme was abandoned in favor of a tandem one, although the upper stages were still created from UR-200.

The rocket was created both as a civilian rocket, for delivering heavy loads into space, and as a military rocket, as a strategic carrier of super-heavy bombs with a capacity of up to 150 megatons. For this, the rocket had to be very powerful, because, for example, the AN602 hydrogen bomb (the famous Kuzka’s Mother or Tsar Bomb) created in 1961 with a power of 58 megatons weighed 26.5 tons and did not fit in the fuselage of a bomber.

RD-253 engines developed at the Glushko Design Bureau were adapted for the UR-500. At one time, this engine was rejected by Korolev in the N-1 project due to the toxic fuel used in it. It was decided to apply this technology with the UR-500, although the toxicity of the fuel is still the main complaint about Proton rockets.

The project was in serious danger of being closed after the resignation of Khrushchev, who supported it. The UR-200 project was closed as it was already a duplicate current project ICBM R-9. However, after a long confrontation between politicians and engineers, it was decided to keep the UR-500 in a civilian version.

The first launch of the two-stage version of the UR-500 was made in 1965 with a load weighing 8.4 tons. In total, during 1965-1966, 4 launches were carried out, delivering Proton satellites into space. Initially, they planned to call the rocket Hercules, but due to the fact that for the first 2 years the UR-500 was delivering Proton satellites into space, it itself began to be called that.

At the same time, the development of a heavy version of the Proton-K began - already a three-stage one for the possibility of flights to the Moon. This rocket took off in 1967 with a prototype of a future ship to fly around the Moon.

However, the USSR Lunar Program was not crowned with success: out of 11 launches of Proton-K and the lunar ship, only 1 was considered completely successful, and in total, out of 21 launches of Proton-K, only 6 were considered successful. Coupled with the unsuccessful launches of the N-1 rockets and that fact that in 1969 Apollo 11 reached the Moon, the program was curtailed in the USSR.

Due to the high accident rate and the large number of modifications, the Proton-K was put into service only in 1978 after 61 launches.

Proton-K has been used to launch various scientific, military and civilian spacecraft. The rocket was used to launch payloads into low orbits, and the four-stage rocket was used to launch spacecraft into high orbits. Depending on the modification, the rocket was capable of delivering up to 21 tons of payload into an orbit at an altitude of 200 km and up to 2.6 tons into geostationary orbit.

In the first decade of the 21st century, the Proton-K rocket was replaced by a modernized version of the Proton-M, which is successfully operated in Russia.

Proton rocket design

UR-200

The basic UR-500 was a two-stage rocket, in which the first stage, a more powerful one, was specially developed, and the second stage was inherited from the UR-200. The rocket could launch up to 8.4 tons of cargo into low orbit.

The first stage is seven-block: one central, surrounded by six side blocks. The central block includes the tail compartment, transition compartment and oxidizer tank; there are no engines. The side blocks contain tail compartments with RD-253 engines, fuel tanks and front compartments.

The second stage consists of the transition, fuel and tail sections. Equipped with three RD-0210 engines and one RD-0211 (can provide pressurization of fuel tanks).

Proton-K

The appearance of the Proton-K modification required a number of changes to be made to the second stage of the base rocket to make it possible to add a third and fourth stage. This made it possible to increase the payload mass and operate in higher orbits.

The power of the first stage engines was increased by 7.7% (the updated engines received the index RD-275).

In the second stage, the fuel tanks were enlarged and the design of the transition compartment between the first and second stages was changed.

The third stage – new for the UR-500 – consists of the instrument, fuel and tail sections. It was developed on the basis of the second stage, but shortened and installed 1 RD-0212 engine + a small RD-0214 steering engine.

Proton-M

By 2012, the updated version of the Proton-M became the main rocket in Russia. It was created on the basis of the “K” modification, but a number of changes were made to it, primarily to the control system. Thanks to this, the rocket burns fuel more efficiently, spent stages return to Earth more accurately, gains the ability to maneuver in space, and also allows the installation of larger loads. Also, the RD-275 engines were replaced with RD-276, which increased the weight of the cargo thrown at the GPO by 650 kg.

All stages use a propellant composed of unsymmetrical dimethylhydrazine (UDMH or heptyl) and nitrogen tetroxide. This fuel has made it possible to simplify engines, but is considered extremely toxic.

Acceleration blocks

For the final launch of the cargo into orbit and maneuvering in space, the DM and Briz-M upper stages are used.

Block DM (originally Block D) was created at OKB-1 Korolev. After upgrading to the DM version, the unit could operate in space for up to 9 hours with three possible launches. Now new modifications are being created on its basis.

The Briz-M block is designed for Proton-M rockets and is a universal and most actively used system. The block allows you to increase the load weight to 3.5 tons per GSO. It was first launched in 2001.

Video of the launch of the Proton-M launch vehicle

Operation of Proton rockets

The development of a launch vehicle was one of the main programs in Soviet cosmonautics. Despite a series of failures in the first years of its existence, along with the “seven” (LV Vostok, LV Soyuz, etc.), the Proton rocket became one of the most used launch vehicles in the Soviet and later Russian cosmonautics. Over time, the initial design errors were worked out, and currently the Proton is one of the most reliable launch vehicles ever created.

The Proton rocket is manufactured at the State Research and Production Space Center named after. Khrunicheva. The assembled rocket elements are delivered to cosmodromes via railway. The final assembly of the rocket and preparation for launch is carried out at the cosmodrome on site 92A-50.

Launches are carried out from the Baikonur Cosmodrome. Of the four launch pads built for the rocket during the Soviet period, three are in operation: pads 81L, 81P and 200L.

It was established specifically to promote commercial launches international company International Launch Services (ILS). As of 2011, 72 launches were carried out under the auspices of ILS.

Since 1965, the Proton launch vehicle in its three modifications has been launched 409 times (2015), of which 27 launches were unsuccessful and 20 were partially unsuccessful.

It is planned that by 2020 the rocket will give way to the new, more advanced and environmentally friendly Angara rocket.

Design of modifications of Proton rockets

Proton is one of the largest car manufacturers in Malaysia, which specializes in the production of vehicles under Mitsubishi license.

For the first time, the production of vehicles in Malaysia began back in 1983 in connection with the signing of an interstate agreement between the local Malaysian auto company Heavy Industry of Malaysia and the Japanese concern Mitsubishi Motor Corporation. The first representatives of the Proton Saga were rolled off the assembly line in 1985. The car of the Saga model (Iswara, Magma) with a hatchback or sedan body was a kind of externally modernized Lancer of the 1983 model. The car was equipped with a more reinforced suspension, which ensured efficient operation of the vehicle in local conditions.

In 1991, the so-called transformation took place common enterprise into the Public Limited Company (PLC), which was freed from the influence of Mitsubishi Motor Corp. In 1995, the company became one of the constituent elements of the DRB-HICOM group.

At the beginning of 1996, the first show of the Proton Perdana middle-class sedan took place; this model was created on the basis of the Mitsubishi Eterna. Towards the end of the year, the Proton company decides to acquire a controlling stake (80%) of the shares of Lotus, a British company.

Proton is quite rapidly expanding the range of its model range, which a few years ago included only models licensed by Mitsubishi.

The 400 series vehicles are quite similar in design to the Mitsubishi Lancer. Cars are produced with sedan bodies, as well as a 5-door hatchback.

The Proton Putra 218 GLXi is a replica of the famous 1991 Mitsubishi Mirage two-door coupe. The car does not have a bright and original “appearance”, however, it looks quite nice and harmonious. The model is equipped with a spoiler located on the roof of the trunk, as well as a chrome tip located on the double-barrel exhaust pipe.

The Wira Cabrio was based on the Satria model. By appearance The models are quite different from each other, mainly due to the use of a different body kit.

So, the largest and most powerful car company in Malaysia, Proton Otomobil Nasional Berhad, produced more than 169 thousand cars during 2000. However, the company is not going to stop there, and in the near future will significantly expand the offered range with its own models that will not be produced under Mitsubishi license.

So, at the beginning of 2000, the world saw the new Waja model, which since the summer of 2001 has been presented in European markets under the sonorous name - Impian, which translated from the native Malaysian language means “a dream comes true.” This model is exclusively a Malaysian development with the help of Lotus engineers.

Since 2003, Malaysia has abolished huge tariffs on imported vehicles, which is why local car manufacturer Proton is making every effort not to be displaced by “import guests”.

"Proton" (UR-500 - Universal rocket, "Proton-K", "Proton-M") is a heavy-class launch vehicle (LV) designed to launch automatic spacecraft into Earth orbit and further into outer space. Developed in 1961-1967 in the OKB-23 division (now the M.V. Khrunichev State Research and Production Space Center), which was part of V.N. Chelomey’s OKB-52. The original two-stage version of the Proton launch vehicle (UR-500) became one of the first medium-heavy class carriers, and the three-stage Proton-K - heavy, along with the American Saturn-1B launch vehicle.

Video of the Proton-M rocket launch

The Proton launch vehicle was a means of launching all Soviet and Russian orbital stations"Salyut-DOS" and "Almaz", modules of the Mir station and the ISS, planned manned spaceships TKS and L-1/Zond (Soviet lunar flyby program), as well as heavy satellites for various purposes and interplanetary stations.

Since the mid-2000s, the main modification of the Proton launch vehicle has been the Proton-M launch vehicle, used to launch both federal Russian and commercial foreign spacecraft.

Design

The first version of the Proton launch vehicle was two-stage. Subsequent modifications of the rocket, Proton-K and Proton-M, were launched either in three-stage (to the reference orbit) or four-stage versions (with an upper stage).

RN UR-500

The UR-500 launch vehicle (Proton, GRAU index 8K82) consisted of two stages, the first of which was developed specifically for this launch vehicle, and the second was inherited from the UR-200 rocket project. In this version, the Proton launch vehicle was capable of launching 8.4 tons of payload into low Earth orbit.

First stage

The first stage consists of a central and six side blocks located symmetrically around the central one. The central block includes a transition compartment, an oxidizer tank and a tail compartment, while each of the side blocks of the first stage booster consists of a forward compartment, a fuel tank and a tail compartment in which the engine is mounted. Thus, the first stage propulsion system consists of six autonomous propulsion liquid rocket engines(LPRE) RD-253. The engines have a turbopump fuel supply system with afterburning of generator gas. The engine is started by breaking through the pyromembrane at the engine inlet.

Second stage

The second stage has a cylindrical shape and consists of a transition, fuel and tail compartments. The second stage propulsion system includes four autonomous propulsion rocket engines designed by S. A. Kosberg: three RD-0210 and one RD-0211. The RD-0211 engine is a modification of the RD-0210 engine to provide pressurization of the fuel tank. Each of the engines can deviate by an angle of up to 3° 15" in tangential directions. The second stage engines also have a turbopump fuel supply system and are designed according to the afterburning of generator gas. The total thrust of the second stage propulsion system is 2352 kN in vacuum. The second stage engines are started earlier than the start of shutdown of the first stage propulsion rocket engines, which ensures the “hot" principle of stage separation. As soon as the thrust of the second stage engines exceeds the residual thrust of the first stage rocket engine, the pyrobolts connecting the stage trusses are undermined, the stages diverge, and combustion products from the chambers of the second stage rocket engine, acting on the heat shield, they slow down and push away the first stage.

Proton-K LV

The Proton-K launch vehicle was developed on the basis of the two-stage UR-500 launch vehicle with some changes to the second stage and the addition of third and fourth stages. This made it possible to increase the mass of the payload in low Earth orbit, as well as to launch spacecraft into higher orbits.

First stage

In the initial version, the Proton-K launch vehicle inherited the first stage of the UR-500 launch vehicle. Later, in the early 1990s, the thrust of the RD-253 first stage engines was increased by 7.7%, and new option The engine was named RD-275.

Second stage

The second stage of the Proton-K launch vehicle was developed on the basis of the second stage of the UR-500 launch vehicle. To increase the mass of the PN in orbit, the volumes of the fuel tanks were increased and the design of the truss transition compartment connecting it to the first stage was changed.

Third stage

The third stage of the Proton-K launch vehicle is cylindrical in shape and consists of instrument, fuel and tail sections. Like the second stage, the third stage of the Proton-K launch vehicle was also developed on the basis of the second stage of the UR-500 launch vehicle. For this purpose, the original version of the second stage of the UR-500 LV was shortened, and one propulsion rocket engine was installed on it instead of four. Therefore, the RD-0212 main engine (designed by S. A. Kosberg) is similar in design and operation to the second stage RD-0210 engine and is its modification. This engine consists of a single-chamber propulsion engine RD-0213 and a four-chamber steering engine RD-0214. The thrust of the main engine is 588 kN in a vacuum, and the thrust of the steering engine is 32 kN in a vacuum. The separation of the second stage occurs due to the thrust of the steering rocket engine of the third stage, which is launched before the main rocket engines of the second stage are turned off, and braking of the detachable part of the second stage by the six 8D84 solid propellant engines on it. The payload is separated after turning off the RD-0214 steering engine. In this case, the third stage is braked by four solid fuel engines.

Control system for Proton-K launch vehicle

The Proton-K launch vehicle is equipped with an autonomous inertial control system (CS), providing high accuracy launching PN into various orbits. The control system was designed under the leadership of N. A. Pilyugin and used a number of original solutions based on gyroscopes, the development of which began earlier on the R-5 and R-7 rockets.
The control system instruments are located in the instrument compartment located on the third stage accelerator. The riveted, unsealed instrument compartment is made in the form of a torus shell of rectangular rotation cross section. The main instruments of the control system, made according to a triple scheme (with triple redundancy), are located in the torus compartments. In addition, the instrument compartment contains devices for the apparent speed control system; devices that determine the parameters of the end of the active section of the trajectory, and three gyrostabilizers. Command and control signals are also constructed using the triple principle. This solution increases the reliability and accuracy of spacecraft launches.

Fuel used

The propellant components used in all rocket stages are unsymmetrical dimethylhydrazine (UDMH, also known as heptyl) (CH3)2N2H2 and nitrogen tetroxide N2O4. The self-igniting fuel mixture made it possible to simplify the propulsion system and increase its reliability. At the same time, fuel components are highly toxic and require extreme care when handling.

Improvements to the Proton-M launch vehicle

From 2001 to 2012, the Proton-K launch vehicle was gradually replaced by a new modernized version of the launch vehicle, the Proton-M launch vehicle. Although the design of the Proton-M launch vehicle is mainly based on the Proton-K launch vehicle, serious changes were made to the control system (CS) of the launch vehicle, which was completely replaced by a new advanced control system based on the on-board digital computer complex (ONDCC). Using the new control system on the Proton-M launch vehicle, the following improvements are achieved:

• more complete depletion of the on-board fuel reserve, which increases the mass of the SG in orbit and reduces the remains of harmful components in the places where the spent first stages of the launch vehicle fall;
• reducing the size of the fields allocated for the fall of spent first stages of the launch vehicle;
• the possibility of spatial maneuver during the active phase of the flight expands the range of possible inclinations of the reference orbits;
• simplifying the design and increasing the reliability of many systems, whose functions are now performed by the BTsVK;
• the ability to install large head fairings (up to 5 m in diameter), which allows you to more than double the volume for accommodating the payload and use a number of promising upper stages on the Proton-M launch vehicle;
• quick change of flight mission.

These changes, in turn, led to an improvement in the mass characteristics of the Proton-M launch vehicle. In addition, the modernization of the Proton-M launch vehicle with the Briz-M upper stage (UR) was carried out even after the start of their use. Since 2001, the launch vehicle and upper stage have undergone four stages of modernization (Phase I, Phase II, Phase III and Phase IV), the purpose of which was to lighten the design of various rocket blocks and upper stage, increase the power of the first stage engines of the launch vehicle (replacing the RD-275 with the RD -276), as well as other improvements.

LV "Proton-M" 4th stage

A typical version of the Proton-M launch vehicle currently in operation is called “Phase III Proton Breeze M” (Proton-M launch vehicle - Breeze-M launch vehicle of the third phase). This option is capable of launching into a geotransfer orbit (GTO) a PG weighing up to 6150 kg using a conventional launch path (with an inclination of 51.6°) and a PG weighing up to 6300 kg using an optimized path with an inclination of 48° (with a residual ΔV up to GSO 1500 m /With).

However, due to the constant increase in the mass of telecommunication satellites and the inability to use the optimized route with an inclination of 48° (since this route is not specified in the “Lease Agreement of the Baikonur Cosmodrome”, and every time, launching Proton at this inclination, this is necessary additionally coordinated with Kazakhstan), the carrying capacity of the Proton-M launch vehicle was increased. In 2016, GKNPTs im. M.V. Khrunicheva completed the 4th stage of modernization of the Proton-M launch vehicle - Breeze-M (“Phase IV Proton Breeze M”). As a result of the improvements, the mass of the system payload launched to the GPO was increased to 6300-6350 kg on a standard route (inclination 51.6°, residual ΔV to GSO 1500 m/s) and to 6500 kg when launched into a super synchronous orbit (orbit with height at apogee up to 65,000 km). The first launch of the improved carrier took place on June 9, 2016 with the Intelsat 31 satellite.

Further improvements to the Proton-M launch vehicle

• Increased thrust of first stage engines.
• The use of high-energy molecular complexes dissolved in both components of high-boiling fuel.
• Reducing energy and hydraulic losses in the paths of engine turbopump units by using special additives from polymer materials, high molecular weight polyisobutylene (PIB). The use of fuel with a PIB additive will increase the mass of the payload launched into the geostationary transfer orbit by 1.8%.

Acceleration blocks

To launch the payload into high, geostationary transfer, geostationary and departure orbits, an additional stage called an upper stage (UB) is used. Upper stages allow multiple activations of their propulsion engine and reorientation in space to achieve a given orbit. The first upper stages for the Proton-K launch vehicle were made on the basis of the rocket block D of the N-1 carrier (its fifth stage). At the end of the 1990s, GKNPTs im. M. V. Khrunichev developed a new upper stage “Briz-M”, used in the Proton-M launch vehicle along with the D-family booster.

Block DM

The development of block D was carried out at OKB-1 (now RSC Energia named after S.P. Korolev). As part of the Proton-K launch vehicle, block D has undergone several modifications since the mid-60s. After a modification aimed at increasing the load capacity and reducing the cost of block D, the RB began to be called “Blok-DM”. The modified upper stage had an active lifetime of 9 hours, and the number of engine starts was limited to three. Currently, upper stages of the DM-2, DM-2M and DM-03 models produced by RSC Energia are used, in which the number of inclusions has been increased to 5.

Block Briz-M

"Breeze-M" is an upper stage for the Proton-M and Angara launch vehicles. "Briz-M" ensures the launch of spacecraft into low, medium, high orbits and geostationary orbits. The use of the Briz-M upper stage as part of the Proton-M launch vehicle makes it possible to increase the mass of the payload launched into geostationary orbit to 3.5 tons, and into a transfer orbit to more than 6 tons. First launch of the Proton complex -M" - "Breeze-M" took place on April 7, 2001.

Transition systems

At standard scheme extraction, the mechanical and electrical connection of the spacecraft with the Breeze-M RB is carried out through a transition system consisting of an isogrid carbon-fiber or metal adapter and a separation system (SR). For insertion into geostationary orbits, several different transition systems can be used, differing in the diameter of the spacecraft mounting ring: 937, 1194, 1664 and 1666 mm. The specific adapter and separation system are selected depending on the specific spacecraft. The adapters used in the Proton-M launch vehicle are developed and manufactured by the State Research and Production Space Center named after. M.V. Khrunichev, and separation systems are produced by RUAG Space AB, GKNPTs im. M. V. Khrunicheva and EADS CASA Espacio.

As an example, we can cite the 1666V separation system, which consists of a locking tape connecting the spacecraft and the adapter to each other. The tape consists of two parts, tightened using connecting bolts. At the moment of separation of the RB and spacecraft, the pyroguillotines of the separation system cut the connecting bolts of the locking tape, after which the tape opens, and due to the release of eight spring pushers (the number may vary depending on the type of separation system used) located on the adapter, the spacecraft is separated from the RB.

Electrical and data telemetry systems

In addition to the main mechanical units mentioned above, the Proton-M launch vehicle has a number of electrical systems used throughout the preparation for launch and launch of the launch vehicle. With the help of these systems, the electrical and telemetric connection of the spacecraft and LV systems with the control room 4102 is carried out during preparation for launch, as well as the collection of telemetric data during the flight.

Head fairings

Over the entire period of operation of the Proton launch vehicle, a large number of different head fairings (HF) were used with it. The type of fairing depends on the type of payload, the modification of the launch vehicle and the upper stage used. The GO reset is carried out during the initial period of operation of the third stage accelerator. The cylindrical spacer is reset after the space head is separated. The classic standard fairings of the Proton-K and Proton-M launch vehicles for launching spacecraft into low orbits without a rocket launcher have an internal diameter of 4.1 m (external 4.35 m) and a length of 12.65 m and 14.56 m, respectively. For example, a fairing of this type was used during the launch of the Proton-K launch vehicle with the Zarya module for the ISS on November 20, 1998.
For commercial launches, head fairings with a length of 10 m and an outer diameter of 4.35 m are used in conjunction with the DM block (the maximum width of the launch pad should be no more than 3.8 m). In the case of using the Briz-M RB, the standard fairing for single commercial launches has a length of 11.6 m and for double commercial launches - 13.2 m. In both cases, the outer diameter of the fairing is 4.35 m.

Head fairings are produced by Federal State Unitary Enterprise ONPP "Technology" in the city of Obninsk Kaluga region. GO is made of several shells, which are three-layer structures with aluminum honeycomb core and carbon fiber skins, containing reinforcements and cutouts for hatches. The use of materials of this type makes it possible to achieve a weight reduction compared to analogues made of metals and fiberglass by no less than 28-35%, increase structural rigidity by 15% and improve acoustic characteristics by 2 times.
In the case of commercial launches through the ILS company, which markets the launch services of the Proton launch vehicle on the international market, larger alternative GOs are used: 13.3 m and 15.25 m long and 4.35 m in diameter. In addition, to increase the capabilities The Proton-M launch vehicle is actively studying the possibility of using a 5-meter diameter booster. This will make it possible to launch larger satellites and increase the competitiveness of the Proton-M launch vehicle against its main competitor, Ariane-5, which is already used with a 5 m diameter launch vehicle.

Configuration options

The Proton launch vehicle (UR-500) existed in only one configuration - 8K82. The Proton-K and Proton-M LVs have used various types of upper stages over many years of operation. In addition, RKK, the manufacturer of the RB DM, optimized its products for specific payloads and assigned a new name to each new configuration. So, for example, different configurations of RB 11S861-01 could have different names depending on the payload: Block-DM-2M, Block-DM3, Block-DM4, etc.

Assembly of the Proton-M launch vehicle

Assembly and preparation for launch of the Proton-M launch vehicle take place in assembly and testing buildings (MIK) 92-1 and 92A-50 on the territory of “site 92”.
Currently, the MIK 92-A50 is mainly used, which was completed and improved in 1997-1998. In addition, a unified fiber optic system was put into operation in 2001 remote control and control of spacecraft (SC), which allows customers to prepare spacecraft at the technical and launch complexes directly from the control room located in MIK 92A-50.

Assembly of the launch vehicle in MIK 92-A50 takes place in the following order:

• Proton LV blocks are delivered to MIK 92-A50, where each block is checked autonomously. After this, the launch vehicle is assembled. The assembly of the first stage is carried out in a special “revolving” type slipway, which significantly reduces labor costs and increases the reliability of the assembly. Next, the fully assembled package of three stages is subjected to comprehensive tests, after which a conclusion is given about its readiness for docking with the space warhead;
• The container with the spacecraft is delivered to hall 102 of MIK 92-A50, where work is carried out to clean its external surfaces and preparatory operations for unloading;
• Next, the spacecraft is removed from the container, prepared and refueled with propellant components in finishing room 103A. The spacecraft is also checked there, after which it is transported to the adjacent hall 101 for assembly with the upper stage;
• In finishing room 101 (technical complex for assembling and testing the CGC), the spacecraft is docked with the Briz-M RB;
• The CCG is transported to finishing room 111, where the Proton-M space rocket (ROV) is assembled and tested;
• A few days after the completion of electrical tests, the fully assembled rocket launcher is transported from the MIK to a fuel filling station to refuel the low-pressure tanks of the Briz-M upper stage. This operation lasts two days;
• Upon completion of the refueling, a meeting of the State Commission is held on the results of the work performed at the technical and launch complexes of the Proton launch vehicle. The commission decides on the readiness of the rocket launcher for installation at the launch site;
• The rocket launcher is installed on the launch pad.

The Proton-K launch vehicle is assembled at MIK 92-1. This MIC was the main one before the commissioning of MIK 92-A50. It contains technical complexes assembly and testing of the Proton-K launch vehicle and the KGCh, where the docking of the KGCh with the Proton-K launch vehicle is also carried out.

Standard flight pattern of the Proton-M launch vehicle with the Briz-M launch vehicle

To launch spacecraft into geostationary orbit, the Proton-M launch vehicle follows a standard launch scheme using a standard flight path to ensure the accuracy of the fall of the detachable parts of the launch vehicle in specified areas. As a result, after the operation of the first three stages of the launch vehicle and the first activation of the Briz-M upper stage, the orbital unit (OB) consisting of the Briz-M upper stage, the transition system and the spacecraft (SC) is launched into a reference orbit with an altitude of 170 × 230 km , providing an inclination of 51.5°. Next, the Briz-M RB performs 3 more inclusions, as a result of which a transfer orbit is formed with an apogee close to the apogee of the target orbit. After the fifth activation, the RB launches the spacecraft into the target orbit and separates from the spacecraft. The total flight time from the submission of the “Ascent Contact” (KP) signal to the separation of the spacecraft from the Briz-M RB is usually about 9.3 hours.
The following description shows the approximate times for turning on and off the engines of all stages, the time for resetting the GO and the spatial orientation of the launch vehicle to ensure a given trajectory. Exact times are determined specifically for each launch depending on the specific payload and final orbit.

Operation area of ​​the Proton-M launch vehicle

1.75 s (T −1.75 s) before launch, six engines of the first stage RD-276 are turned on, whose thrust at this moment is 40% of the nominal value, and gain 107% of thrust at the moment the control gear signal is given. Confirmation of the CP signal arrives at the moment T +0.5 s. After 6 seconds of flight (T +6 s), the thrust increases to 112% of the nominal value. The step-by-step sequence of engine activation allows confirmation of their normal operation before the thrust is increased to maximum. After an initial vertical section lasting about 10 s, the ILV performs a roll maneuver to establish the required flight azimuth. With an orbital inclination of 51.5°, as in the case of geostationary insertion, the azimuth is 61.3°. For other orbital inclinations, different azimuths are used: for orbits with an inclination of 72.6°, the azimuth is 22.5°, and for orbits with an inclination of 64.8°, the azimuth is 35.0°.
Three RD-0210 and one RD-0211 of the second stage are turned on at the 119th second of flight and switch to full thrust mode at the moment of separation of the first stage at the 123rd second. The third stage steering engines turn on at the 332nd second of flight, after which the second stage engines turn off at the 334th second of flight. The separation of the second stage is carried out after six braking solid propellant rocket motors are activated at the 335th second and it is withdrawn.

The RD-0213 engine of the third stage is turned on at 338 seconds, after which the nose fairing (GO) is reset at approximately 347 seconds from the control gear signal. As for the stages, the moment of GO release is selected to ensure guaranteed entry of the booster of the second stage of the launch vehicle into the specified area of ​​impact, as well as to meet the thermal requirements of the spacecraft. After the third stage propulsion engine is turned off at the 576th second, the four steering engines operate for another 12 seconds to calibrate the estimated injection speed.
After reaching the specified parameters, approximately at the 588th second of flight, the control system issues a command to turn off the steering engine, after which the third stage is separated from the orbital block and removed using braking solid propellant rocket engines. The moment of separation from the third stage is taken as the beginning of the autonomous flight of the OB. Further deployment of the spacecraft is carried out using the Breeze-M RB.

Work area of ​​RB "Briz-M"

The launch of the object into the geotransfer orbit is carried out according to a scheme with five activations of the main engine (MD) of the Briz-M RB. As with launch vehicles, the exact firing times and orbital parameters depend on the specific mission. Immediately after the separation of the third stage of the launch vehicle, the booster stabilization engines are turned on, which ensure orientation and stabilization of the launch vehicle in the passive flight section along the suborbital trajectory until the first start of the booster engine. Approximately one and a half minutes after separation from the launch vehicle (depending on the specific spacecraft), the first activation of the MD is performed for a duration of 4.5 minutes, as a result of which a reference orbit is formed with an altitude of 170 × 230 km and an inclination of 51.5°.

The second switching on of the MD, lasting about 18 minutes, is carried out in the area of ​​the first ascending node of the reference orbit after 50 minutes of passive flight (with the engines turned off), as a result of which the first intermediate orbit is formed with an apogee at an altitude of 5000-7000 km. After the OB reaches the perigee of the first intermediate orbit within 2-2.5 hours of passive flight, the third switching on of the propulsion engine is performed in the area of ​​the ascending node until the fuel from the additional fuel tank is completely exhausted (DTB, about 12 minutes). After approximately two minutes, during which the DTB is reset, the fourth switching on of the MD is performed. As a result of the third and fourth inclusions, a transfer orbit is formed with an apogee close to the apogee of the target geotransfer orbit (35,786 km). In this orbit, the spacecraft spends approximately 5.2 hours in passive flight. The last, fifth switching on of the MD is performed at the apogee of the transfer orbit in the region downstream node to raise the perigee and change the inclination to a given one, as a result of which the RB launches the spacecraft into the target orbit. Approximately 12-40 minutes after the fifth switching on of the MD, the OB is oriented in the direction of the spacecraft separation, followed by the separation of the spacecraft.
In the intervals between MD activations, the RB control system performs turns of the orbital unit to ensure the maintenance of optimal temperature on board, issue thrust pulses, conduct radio monitoring sessions, and also to separate the spacecraft after the fifth activation.

Exploitation

Since 1993, the marketing of launch services for the Proton launch vehicle on the international market has been carried out by the joint venture International Launch Services (ILS) (from 1993 to 1995: Lockheed-Khrunichev-Energy). ILS has the exclusive right to marketing and commercial operation of the Proton launch vehicle and the promising Angara rocket and space complex. Although the ILS company is registered in the USA, its controlling interest belongs to the Russian State Research and Production Space Center named after. M. V. Khrunicheva. As of October 2011, within the framework of the ILS company, 72 spacecraft launches were carried out using the Proton-K and Proton-M launch vehicles.

Cost of Proton-M

The cost of the Proton launch vehicle varies from year to year and is not the same for federal and commercial customers, although the price order is the same for all consumers.

Commercial launches

In the late 1990s, the cost of a commercial launch of a Proton-K launch vehicle with a DM block ranged from $65 to $80 million. At the beginning of 2004, the launch cost was reduced to $25 million due to a significant increase in competition. Since then, the cost of launches on Protons has constantly increased and at the end of 2008 reached approximately $100 million for GPO using Proton-M with the Briz-M block. However, with the beginning of the world economic crisis in 2008, the ruble-dollar exchange rate decreased by 33%, which led to a reduction in launch costs to approximately $80 million. In July 2015, the cost of launching the Proton-M launch vehicle was reduced to $65 million to allow competition with the Falcon launch vehicle.

Launches under the Russian Federal Space Program

For federal customers, there has been a consistent increase in the cost of the carrier since the beginning of the 2000s: the cost of the Proton-M launch vehicle (without the DM block) increased from 2001 to 2011 by 5.4 times - from 252.1 million to 1356, 5 million rubles. The total cost of Proton-M with the DM or Briz-M block in mid-2011 was about 2.4 billion rubles (about $80 million or €58 million). This price consists of the Proton launch vehicle itself (1.348 billion), the Briz-M launch vehicle (420 million), delivery of components to Baikonur (20 million) and a range of launch services (570 million).
Prices as of 2013: Proton-M itself cost 1.521 billion rubles, 447 million for the Briz-M upper stage, 690 million for launch services, another 20 million rubles for transporting the rocket to the cosmodrome, 170 million rubles - head fairing. In total, one Proton launch cost the Russian budget 2.84 billion rubles.

Performance characteristics of Proton-M

Number of stages........................3 - 4 (hereinafter for “Proton-M” third phase of modification)
Length........................58.2 m
Launch weight........................705 t
Fuel type........................UDMH + AT
Payload weight
-at LEO........................23 tons
-at GPO........................6.35 t (with RB "Breeze-M")
-on GSO........................ up to 3.7 t (with RB "Breeze-M")

Launch history

Launch sites........................Baikonur
Number of launches........................411 (as of 06/09/2016)
-successful........................364
-unsuccessful.........................27
-partially unsuccessful20
First launch........................07/16/1965
Last launch........................9.06.2016
Total produced........................410

First stage (“Proton-M” 3rd phase)

Length........................21.18 m
Diameter........................7.4 m
Dry weight........................30.6 t
Launch weight........................458.9 t
Main engines........................6 × liquid rocket engine RD-276
Thrust........................10026 kN (earth)
Specific impulse........................288 s
Operating time........................121 s

Second stage (“Proton-M” 3rd phase)

Length........................17.05 m
Diameter........................4.1 m
Dry weight........................11 t
Launch weight........................168.3 t
Main engine........................LPRE RD-0210 (3 pcs.) and RD-0211 (1 pc.)
Thrust........................2400 kN
Specific impulse........................320 s
Operating time........................215 s

Third stage (“Proton-M” 3rd phase)

Dry weight........................3.5 t
Launch weight........................46.562 t
Main engine........................LPRE RD-0213
Steering motor........................LPRE RD-0214
Thrust........................583 kN (propulsion) (31 kN (steering))
Specific impulse........................325 s
Operating time........................239 s

Photo Proton-M

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Designed to launch automatic spacecraft into Earth orbit and then into outer space. The rocket was developed by the State Space Research and Production Center (GKNPTs) named after. M.V. Khrunichev and is used to launch Russian federal and foreign commercial spacecraft.

"Proton-M" is a modernized version of the "Proton-K" launch vehicle, has improved energy-mass, operational and environmental characteristics. The first launch of the Proton-M complex with the Briz-M upper stage took place on April 7, 2001.

The use of enlarged nose fairings, including those with a diameter of five meters, as part of the Proton-M launch vehicle makes it possible to more than double the volume for accommodating the payload. The increased volume of the head fairing also allows the carrier to use a number of promising upper stages.

The main task of modernizing the launch vehicle was to replace the control system (CS) created back in the 1960s, which had become outdated both morally and in terms of its elemental base. In addition, the production of this system was established outside of Russia.

The modernized Proton-M carrier is equipped with a control system based on an on-board digital computer complex (ONDC). The Proton-M control system made it possible to solve a number of problems: improve the use of on-board fuel reserves due to its more complete production, which increases the energy characteristics of the launch vehicle and reduces or even eliminates the remains of harmful components; provide spatial maneuver during the active phase of the flight, which expands the range of possible inclinations of the reference orbits; ensure prompt entry or change of flight mission; improve the mass characteristics of the launch vehicle.

After being put into operation in 2001, the Proton-M launch vehicle went through several stages of modernization. The first stage was implemented in 2004 and ended with the launch of the heavy Intelsat-10 spacecraft weighing 5.6 tons into a geostationary transfer orbit. The second stage was completed in 2007 with the launch of the DirekTV-10 device weighing 6 tons. The third stage ended in 2008. The fourth stage of modernization is currently being implemented.

Proton-M forms the basis of the Russian Federal Space Program in the dimension of heavy-class launch vehicles. With its help, the GLONASS satellite system is being deployed and the Express series satellites are being launched, which provide satellite communications to all regions of Russia. In addition, the Proton-M launch vehicle is widely used to launch spacecraft in the interests of the Russian Ministry of Defense