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”.
To launch a significant volume of payload into low-Earth orbit, and then into outer space, a powerful launch vehicle (LV), the so-called heavy class, is needed. In the USSR, work on the creation of such a device was carried out by the OKB-23 division - currently the State Research and Production Space Center named after. M. V. Khrunicheva. The result of the research was the creation of a two-stage launch vehicle UR-500 (the first in the Proton line). He belonged to the medium-heavy class RN. On its basis, Proton-K and Proton-M (heavy class) were subsequently created. In the USA, such rockets are abbreviated “Saturn-1B”.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.
Power plants All stages of the Proton launch vehicle use the same propellant components. This is an unsymmetrical dimethylhydrazine (otherwise heptyl or UDMH), the chemical formula of which is (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.
"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 the means of launching all Soviet and Russian orbital stations Salyut-DOS and Almaz, modules of the Mir and ISS stations, planned manned spacecraft 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 a new version of 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), which ensures high accuracy of launching the launch vehicle 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 rotation with a rectangular 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; instruments 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
With the standard launch scheme, 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 on 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 houses the technical complexes for assembling and testing 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 work first three stages of the launch vehicle and the first activation of the Briz-M upper stage, the orbital block (OB) as part of the Briz-M upper stage, the transition system and 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 motors 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 during 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 of the descending 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 onset of the global 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.
Specifications Proton launch vehicleOn July 2, the Proton-M launch vehicle, launched from the Baikonur Cosmodrome, fell in the first minute of launch. For information about what a Proton launch vehicle is and what function the device performs in orbit, see the infographic.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. It helps to deploy satellite system"Glonass", satellites of the "Express" series are launched, which provide satellite communications 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
The Proton launch vehicle is a direct successor to the Soviet two-stage intercontinental ballistic missile UR-500, designed at the design bureau headed by Vladimir Chelomey. Its development began in 1961, and it soon became clear that it would not go into service due to its excess power, although it was capable of delivering the famous thermonuclear bomb, conventionally called “Kuzka’s mother,” to enemy territory. The rocket was supposed to be based in mines; once Khrushchev, who came to Baikonur, having learned how much money was needed for this, said:
“So what will we build - communism or silos for the UR-500?”
The rocket lost its combat purpose, but was repurposed for launching satellites. The first launch took place on July 16, 1965 with the Proton laboratory for the study of cosmic particles. A total of four launches of the two-stage version were carried out, three of them were successful. On the basis of this rocket, Chelomey proposed a program for a manned flight around the Moon, and another third stage and a small upper stage were installed on the rocket. However, the developers did not have time to implement the program, because spaceship and the upper stage was entrusted to the design bureau of Sergei Korolev. Chelomey actually had only the rocket left. In total, 11 unmanned spacecraft were launched under the program, 4 of them did not enter Earth orbit due to launch vehicle failures, 4 spaceships flew around the Moon.
One ship was not launched in July 1968 due to an upper stage failure during preparation for launch. In January 1970, the program was closed due to the fact that the Soviet Union lost priority in the first manned flight to the Moon (in December 1968, American astronauts on the Apollo 8 spacecraft were the first in the world to fly around the Moon and enter lunar orbit, and in July 1969 Apollo 11 landed on the lunar surface). After the completion of the flyby program, the rocket, which eventually received the name “Proton,” was used in three-stage and four-stage versions to launch spacecraft.
Alexander Shlyadinsky
In the 1970s, the first Soviet orbital stations Salyut and Almaz, as well as interplanetary probes to the Moon, Mars and Venus, began to be launched on the rocket. Proton was the only Soviet rocket capable of launching geostationary satellites hovering above one point of the equator at an altitude of 36 thousand km. With a total mass of 700 tons, the rocket delivers 21 tons to low-Earth orbit or up to 3.5 tons to geostationary orbit. Launch complexes for Proton were and remain only at Baikonur. In 1993, American and Russian enterprises established the company Lockheed-Khrunichev-Energia International (LKEI), transformed in 1995 into International Launch Services (ILS), which since 1996 has launched foreign satellites on the Proton rocket on a commercial basis.
One step, two steps...
The military past of this missile determined one of its main differences - all three stages use asymmetrical dimethylhydrazaine (heptyl) as fuel and nitrogen tetroxide as an oxidizer. This is due to the fact that a ballistic missile must be in a combat-ready state long before launch. In contrast, previously developed royal rockets used liquid oxygen as an oxidizer, which evaporates and does not allow long-term storage. The disadvantage of long-storing fuel is the toxicity of both of its components; the advantage is that it does not require an ignition system, since the fuel ignites itself upon contact with an oxidizer.
Unlike the Soyuz, in which at launch both the “sides” of the first stage and the central second stage begin to operate simultaneously, the Proton is made according to an optimal design with a sequential division of stages.
Currently, the most advanced modification of the rocket, Proton-M, is used, equipped with uprated engines, lightweight design and a digital control system.
In total, the rocket has 11 sustainer single-chamber engines: six of the first stage, four of the second stage and one of the third stage. The third stage also has a four-chamber steering engine.
The first stage consists of one central oxidizer tank and six fuel tanks surrounding it. Six oscillating RD-276 engines (developed by NPO Energomash and produced by the Perm plant Proton-PM) provide thrust and control of the rocket during the first stage operation (approximately 120 seconds).
Third stage with accelerator and load
Alexander ShlyadinskyThe second stage consists of an oxidizer and fuel tank, separated by a partition, as well as four oscillating engines (three RD-0210 and one RD-0211) (developed by the Chemical Automation Design Bureau and produced by the Voronezh Mechanical Plant). In addition to generating thrust, the RD-0211 generates boost gas to create excess pressure in the tanks.
The stages are separated according to the so-called hot circuit: the engines of the upper stage are turned on before the engines of the lower stage are stopped. This is done in order to avoid the problem of turning on the engines in zero gravity, since the rocket overload is involved in creating the necessary pressure when supplying fuel to the turbopump. The stage operates for 200 seconds.
The third stage is designed similarly to the second - the upper tank with the oxidizer, the lower one with fuel, but it has only one fixedly mounted main engine (RD-0213) and one steering engine RD-0214 with four oscillating chambers. They also begin to work until the second stage engines are completely turned off. The steering motor actually pulls the third stage with its payload out of the adapter connecting it to the second stage. The third stage operates for approximately 240 seconds.
It is with the operation of the third stage engines that at least three accidents of Proton rockets are now associated - the recent one, in 2014, which was caused by the destruction of the steering engine turbopump bearing, and in 1988.
“If something in the rocket stops working, an AED command is issued - “emergency engine shutdown.” This goes back to the days of combat missiles, so that in case of failure the missile would fall on our territory. The engines turn off, the rocket falls in the atmosphere and, as a rule, burns out,” explains Igor Afanasyev, editor of the “Cosmonautics News” magazine. Since the rocket costs much less than the launch complex, in emergency cases at the time of launch the main task is, on the contrary, to move the rocket away from the launch. “Therefore, in the event of a failure or even explosion of one of the first stage engines, a command is given to boost the remaining ones, and only then the AED command is given,” the expert explained.
Degraded
How, the May cause of the recent Proton accident lay in the same third-stage steering motor, the failure of which occurred due to “increased vibration loads caused by an increase in the imbalance of the rotor of the turbopump unit associated with the degradation of the properties of its material under the influence of high temperatures and the imperfection of the balancing system.” Moreover, as it turned out, the refusal “is constructive in nature.”
To facilitate separation, powder braking motors are provided at the top of the second stage to help avoid dangerous stage collisions. After this, the third stage with a load and the upper stage enter transfer or low-Earth orbit.
Scheme of insertion into geostationary orbit
The first upper stage, and in fact, the fourth stage of the rocket, appeared during the implementation of the lunar flyby program. It is designed to transfer a spacecraft from low Earth orbit to a flight path to the Moon and other planets or to geostationary orbit. The upper stage operates autonomously for a long time in outer space, functioning in zero gravity, and has its own active orientation and stabilization system.
The Proton uses two types of upper stages (UB). Block “D” is oxygen-kerosene (developed by RSC Energia), used mainly for launching GLONASS devices. "Briz-M" (GKNPTs named after M.V. Khrunichev) - on long-lasting components, for launching geostationary satellites. It itself is essentially two-stage - the central part is surrounded by a toroidal block of drop tanks.
The main difference between the RB (it refers not to the rocket, but to the space head part) from the rocket stages is that it can operate in zero gravity, when fuel can collect in the tanks in the form of balls, gas bubbles can appear in it, due to which the engine may choke. Therefore, small powder engines can be used to create weak overloads.
A common task for Proton is launching geostationary satellites (36 thousand km). To do this, the upper stage must inform the vehicle located in a low circular orbit, extra speed(about 3 km/s) so that it moves from a circular orbit to an elliptical one. And already at the farthest point of this ellipse it is necessary to give the device one more impulse in order to give it the first escape velocity for this altitude. One of the difficulties is that Baikonur is located far from the equator. Therefore, the orbits of the satellites have a high inclination and to launch a geostationary vehicle, additional pulses from the upper stage are required to “straighten” the orbit and force the satellite to hang exactly above the equator.
For the same reason, Proton can send more cargo to the Moon or Mars than to geostationary orbit.
“The Proton design has not changed since 1965, but now new technologies are being used, materials are changing, and engine efficiency has been slightly increased. The possibility of improvement is highly dependent on the rocket design and dimensions. To increase thrust, you need to either increase the pressure in the chambers or increase the nozzle, but this requires changing the dimensions of the rocket and, most importantly, the launch complex,” explained Afanasyev.
From Fili by train
The rocket is assembled in Fili, at the Khrunichev plant, and in the form of a small number of transportable blocks is sent by a special train to the cosmodrome. Initially, the dimensions of the rocket elements were chosen in such a way that its largest part (the first-stage oxidizer tank with a diameter of 4100 mm), placed in a special elongated car, could be transported without causing problems to oncoming trains and overhead power lines, and could pass freely in tunnels and along curved sections of the track . At the same time, in sections with minimal radii of curvature, in order to avoid a collision, it is necessary to stop the movement of trains in the opposite direction. The widest non-separable part of the rockets, with a diameter of up to 5 m, is the head fairing.
To deliver it by railway, it is divided in half lengthwise and transported in an inclined position.
Unlike aviation, where the investigation of most accidents ends with a public and detailed report from the IAC, the results of space accidents in Russia are often made public without proper detail.
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