Soyuz (rocket)
The Soyuz rocket [ sʌjus ] (Russian Союз, Union ',' union ') is one of the developments of the world's first intercontinental ballistic missile, the R -7, which launched on its first flight on 15 May 1957.
- 3.6.1 Jamal
- 3.6.2 Aurora
- 3.6.3 Onega
Overview
Had the first official space mission, the R-7 on October 4, 1957 Sputnik 1 on board. By continuously developing many variants of the R-7, which also becoming more powerful and more reliable have been developed. One of the most well-known variants of the R-7 is the Soyuz. It was created by slight modifications of the Voskhod rocket, with the initial task to launch manned Soyuz spaceships. The differences between the two rockets were so low that some authors also expect the Voskhod to the Soyuz series. The initial launch of the Soyuz was held on November 28, 1966 instead ( the Voskhod flew since 1963 ). Since then, the rocket was used to launch a wide variety of payloads, including have included all manned Soyuz spacecraft, Progress cargo spacecraft, low-flying research and military satellites, and since 1999 with additional Ikar or Fregat upper stages also ESA spacecraft and commercial satellite.
Today, the Soyuz rocket is the most flown orbital rocket in the world with more than 850 flights and one of the most successful with a reliability rate of 97.5%. She is also the only active launcher of the Russian Federation, which is approved for manned space flight. Commercially, the rocket by the company Starsem is marketed, they since October 21, 2011 (First Start: VS -001 with two Galileo satellites Soyuz ST -B ), it can also start from the European Spaceport in Kourou, French Guiana.
Technology
The first stage of the spacecraft consists of four boosters with four combustion chambers, and each combustion chamber, a nozzle (RD- 107). These are each 19.6 meters long, have a maximum diameter of 2.68 meters and weigh empty about 3.5 t and 44.5 t at startup. The second stage is very similar in construction to the booster, but has an elongated tank and a modified, optimized for operation in the engine space (RD- 108). This could avoid a new development of the combustion chamber for higher pressure and higher temperatures. The central block is 27.8 m long and has a maximum diameter of 2.95 m, an empty weight of 6.9 t and a mass at the start of 104.5 t. Since we initially had no experience with exciting in flight stages, both stages were simply started simultaneously, with all five major and twelve control thrusters (two each at the four boosters RD- 107 and RD -108 at four ) light. The engines of the first two stages burn kerosene and liquid oxygen (LOX ). After two minutes, the fuel of the booster is consumed and these are dropped, the fuel supply to the main stage provides them for about another 2.5 minutes. The engines were constantly increased in their performance, and contribute to the current Soyuz -FG, the designations RD- 107A and RD- 108A. The second stage (the central booster) is also known as block A, the four boosters of the first stage as block B, F, G and D (after the first letter of the Cyrillic alphabet: А, Б, В, Г, Д ).
The third stage of the Soyuz is powered by the RD -0110 engine with 298 kN thrust, which burns kerosene and liquid oxygen also (LOX ). The stage is called a block I ( Russian: И ). You (referred to engl. as core ) to the second stage of the rocket, the core block A, connected by a tubular adapter and two seconds ignited before the firing circuit of the block A, which is called the hot stage separation and pushes the main stage of the third stage. A deflecting cone to titanium is installed on the end of the main stage. The third stage has a length of 6.74 m, a diameter of 2.66 m and weighs 2.36 tonnes and empty at the start about 25 t. The burning time is 250 s
For manned missions, the Soyuz additionally carries a rescue system (Russian система аварийного спасения, САС, to German SAS) for cosmonauts with it. The system consists of a complex of solid rocket is mounted on top of the spacecraft. With a false start, they are ignited and bear the cabin with the cosmonauts very fast out of the danger zone. On September 27, 1983, the unprecedented rescue system for use when a Soyuz -U exploded directly on the launching pad. The rescue system saved the crew of the Soyuz T -10-1 spacecraft only seconds before the explosion. This system also includes four distinctive rectangular components along the sides of the fairing. These so-called grid fins fold out upon activation of the rescue system and serve the aerodynamic stabilization. Small solid rocket at the very tip are used for separation of the payload fairing of the spaceship. In a normal course start the rescue system is about 150 s dropped after the start.
Launch facilities for Soyuz rocket exist on the one hand in Plesetsk (Russia) and Baikonur (Kazakhstan ), since October 2011, Soyuz launch in French Guiana (South America) possible. The Guiana Space Centre is convenient for satellite launches near the equator, giving the Soyuz system allows there a higher payload with the same configuration. Manned space flights are still limited to the Baikonur launch site, as the Soyuz spacecraft so far only mastered emergency landings on the mainland. Starts from French Guiana on the other hand lead across the Atlantic.
Versions of the Soyuz
Over the years, several versions of the Soyuz rocket developed. They differed in the engines, fairings and fuels used. All versions possessed three stages and were for the transport of payloads into low orbits. It was not until the late 1990s a fourth stage was used to reach higher orbits, since the four-stage Molniya previously used for this task was not flexible enough in the Soyuz. The upper stages of the Soyuz will be treated in its own section.
Early versions
- Soyuz - ( GRAU index 11A511 ) - This is the original version of the Soyuz rocket that for the first time on 28 November 1966, a Soyuz - prototypes ( Cosmos 133) flew on board and on 23 April 1967, the manned Soyuz 1 spacecraft into space carried. The rocket used RD -107 engines in the first stage RD -108 in the second and RD -0110 in the third. The starting weight was 308 t, the length of 50.67 m. In addition to the Soyuz spacecraft, it was also used to launch a range of military satellites of the Cosmos series. The last flight took place with the Soyuz -18 spacecraft on 24 May 1975.
- Soyuz -L - ( GRAU index 11A511L, Russian 11A511Л, Л is Лунный - to German lunar ) - A Soyuz with the prototypes of Soviet lunar modules were taken for test purposes into orbit. It differed from the Soyuz by another payload fairing with more than 12 m in length and a structurally reinforced central stage. The starting weight was 305 t, length 44 m. The rocket was launched only three times, the first time on 24 November 1970 and the last time on 12 August 1971. A sketch of the Soyuz -L is available here.
- Soyuz -M - ( GRAU index 11A511M, Russian 11A511М, М is Модифицированный - to German modified) - About the differences from an ordinary Soyuz there are few information (see). As the proposed for transporting military Soyuz 7K- WI was too heavy spaceship but about 300 kg for the payload capacity of normal Soyuz, and the synthetic fuel Sintin were in this version except different weight savings, used instead of kerosene and the best engines ( from the series variance ) was used. The Soyuz -M weighed 310 tons and was 50.670 m high. Although the military Soyuz spacecraft was never used, but the eight -built missiles were used in orbit for the start of military reconnaissance satellites of the type Zenit- 4MT. The first launch took place on December 27, 1971. The last launch of a Soyuz -M on 31 March 1976.
Later versions
- Soyuz -U - ( GRAU index 11A511U, Russian 11A511У, У represents Унифицированный - unified into German, unified ) - The Soyuz - U, which first flew on 18 May 1973, the modifications of the last eight years were a standardized rocket summarized. The modifications concern the engines and the rocket booster, also starting preparations lines were adapted to the new rocket. In addition, the fuel for the main stage has been cooled, which resulted in a higher density and therefore greater mass of fuel. The engines were new terms: RD- 117 for the first stage, and RD -118 for the second. The Soyuz - U is the most widely used version of the Soyuz series, she weighs 313 tonnes and has a height of 51.1 m. The payload capacity of the rocket is at a start from Baikonur up to 6950 kg into a 200 km high orbit and at a start of Plesetsk up to 6700 kg into a 220 km high orbit. This version is the most widely used with over 700 starts execution and is still (as of May 2012) used. However, you will soon be superseded by the more modern Soyuz -FG and Soyuz -2.
- Soyuz -U2 - ( GRAU index 11A511U2, Russian 11A511У2 ) - Soyuz -U2 launched for the first time December 28, 1982 and used in contrast to the Soyuz -U synthetic kerosene ( Sintin ) as fuel for the central level ( Block A). For use, the injection nozzles of the engines had to be modified. With these changes, the payload of the rocket increased by 200 kg compared to the Soyuz -U. The Soyuz -U2 flew a total of 80 times and was mainly to start manned Soyuz ships. However, since the production of Sintin the older production facilities had to be modified and thus the price of petrol would be increased, the production of the Soyuz -U2 mid-1990 has been set and she brought on her last flight on September 3, 1995, the Soyuz TM -22 spacecraft into orbit.
- Soyuz -FG - ( GRAU index 11A511FG, Russian 11A511ФГ ) - Soyuz -FG is a transitional version between the Soyuz -U and the new Soyuz -2. The first and second stages were optimized with new engines injection heads and a changed mixing ratio of fuel and were designated RD- 107A and RD- 108A. In addition, a new air traffic control system has been installed which allows the change of the inclination during the ascent phase, and integrated a new telemetry system. In addition, a larger payload fairing will be used. The rocket is slightly stronger than the Soyuz -U and can thus start the slightly heavier Soyuz TMA spacecraft to the ISS. It also serves as the basis of SojusFG / Fregat. The payload capacity of the rocket is at a start from Baikonur up to 7130 kg into a 200 km high orbit. The first launch took place on 21 May 2001 a Progress cargo spacecraft. Starting with the mission Soyuz TMA -1 are all manned Soyuz flights to the Soyuz -FG carried out (July 2011).
Sojus-2/ST
Since 1992 the project of " Rus" was followed rocket (Russian Русь ) in Russia, which is a further development of the Soyuz -U and a payload capacity of about 7.5 t for the low Earth orbit has. It should not be confused with the new Rus -M, which is a completely new development. The Rus should obtain a digital flight control system that would replace the old one, dating from the 1960s, analog control system. Thus, a more flexible flight planning and more efficient use of fuel would be possible, which would be beneficial to the payload capacity of the rocket. In addition, the rocket should receive a modified third stage (Block I) with a new RD -0124 engine (thrust 30 kN Specific Impulse 3522 Ns / kg and 359 s ) and the first and second stage engines should the improved RD- 107A and RD- 108A to be replaced. Later, the Rus was called Soyuz -2. However, since there was no money in the Russian space checkout, the development of the Soyuz -2 was only very hesitantly in the 1990s.
The turning point came when the company Starsem was founded in cooperation with Arianespace, which offered the Soyuz in the west to the start of commercial satellites. Soon the first launch contracts and therefore money came into the coffers that could be used for further development of the Soyuz. The original plans of Starsem before seen, to offer from 2002, a Soyuz -U, which is equipped with a digital control system and with the RD- 107A and RD- 108A engines in the first and the second stage under the name of Soyuz -ST. In addition, the Soyuz -ST on a larger and more spacious payload fairing (ST- type, diameter 4.11 m, length 11.433 m) should have. The ST payload fairing largely corresponds in size and shape of the payload fairing of the Ariane 4 In addition, it was planned that they can use to reach high orbit a new upper stage, called Fregat should. A Soyuz -ST with the new RD -0124 engine in the third stage should hot Soyuz -ST.
Instead of Soyuz -ST came in 2001, the Soyuz -FG used, which differed from the usual Soyuz -U only by the RD- 107A and RD- 108A engines in the first two stages. It is now used to launch manned spacecraft and cargo spacecraft. In addition, the Fregat stage was tested in conjunction with the Soyuz -U and later also with the Soyuz -FG and used successfully several times. Furthermore, a new fairing (S- type, Ø 3.715 m, length 7.7 m) was introduced for commercial launches, which came into use, for example at the start of the spacecraft Mars Express and Venus Express.
On 8 November 2004 successfully launched the Soyuz - 2.1a, which was the next stage of development on the way to Soyuz -2. They now had the digital flight control system and adapted to the RD -0124 third stage, which was, however, still driven by an older RD -0110. Another Soyuz - 2.1a launch took place on 19 October 2006, when the European weather satellite MetOp -A was launched into space using a Fregat stage and an ST -type payload fairing. The Soyuz - 2.1b, which corresponds to the former plans of the Soyuz -2, launched on 27 December 2006 for the first time in Baikonur with the COROT space telescope. From 2010 Soyuz - 2.1b should stand together with the Soyuz - 2.1a in Kourou for commercial launches are available.
The payload capacity of the Soyuz - 2.1a is at a start from Baikonur up to 7020 kg into a 200 km high orbit and at a start of Plesetsk up to 6830 kg into a 220 km high orbit. Soyuz - 2.1b can carry from Baikonur up to 8250 kg into a 200 km high in orbit and from Plesetsk of up to 7020 kg into a 220 km high orbit. The payload capacity of the Soyuz -ST at a start from Kourou is likely to be considerably higher.
Soyuz with upper stage
In order to bring commercial satellites and space probes on high orbits, the Soyuz rocket stage a fourth was added. The fourth stage is enclosed together with the payload from the payload fairing.
Soyuz - Ikar
The Ikar stage was derived and used to launch the Soyuz -U Globalstar satellites of the drive module of the Russian Kometa or Jantar -1 reconnaissance satellites. Here were brought in 1999 six flights 24 Globalstar satellites into space, four piece per flight. Sojus-U/Ikar is 308 t and 47.285 m high. As of 2000, the Ikar was replaced by the new and more powerful Fregat.
Soyuz - Fregat
The Fregat stage was derived from the propulsion module of the spacecraft Phobos and Mars 96 and is equipped with a modern digital control system. They will be built by Russia's Lavochkin. Fregat can be up to twenty times again be ignited, making it ideal for launching multiple satellites in different orbits. This fact was used by the ESA, as she was looking for a launcher for their Cluster satellites. The first launch of a Sojus-U/Fregat took place on 8 February 2000. After another test flight four Cluster satellites were successfully launched into space at two Sojus-U/Fregat-Flügen. This Fregat was able to prove their efficiency and reliability, when she took over in time for a premature shutdown of the third stage of the Soyuz control of the flight and the mission still was able to save by their excess fuel charge. Since then, the Soyuz with Fregat stage for launching spacecraft (Mars Express) and commercial payloads will be used. Since 2003 Fregat is also used on the Soyuz FG and from 2006 also the new Soyuz - 2 rocket. In addition to Soyuz - Fregat replace the already outdated Molniya rocket, which also has four stages and high-flying satellite launches. The Sojus-U/Fregat 308 tons in weight, 46.645 meters high and can bring from Baikonur up to 2100 kg in the Geotransferorbit or up to 1260 kg on a transfer orbit to Mars.
Soyuz 2.3
Since 2006 there are talks about a development of the Soyuz -2 rocket, the first, was called Soyuz Soyuz 1 later than 2.3. This is used in the central stage, a Kuznetsov NK -33 engines and is thus similar to the Jamal / Aurora concept ( see the relevant section of this article ). This engine comes from the Russian rocket N1 which was originally planned for moon flights. The LEO payload capacity of the Soyuz is 2.3 with 11 tonnes from Baikonur / Plesetsk and from 12.7 t from Kourou specified. Through the use of a hydrogen-powered third-party and / or advanced the payload capacity of the rocket can be increased even further.
The first step in this direction is the Soyuz 2.1W ( Союз - 2.1в ). It is a developed on the basis of the central block of the Soyuz new launcher for smaller payloads up to 2.8 tons. It consists of only two stages, the first one is compared to the second step of traditional Sojus extended and enlarged in diameter, and a NK -33 used as an engine. The second stage was taken over by the Soyuz 2.1b. As a senior, the newly developed Volga is used that is optimized for smaller payloads for which a Fregat upper stage would be oversized. She works with UDMH and N2O2 as, depending on Treibstoffzuladung weighs up to 1740 kg, a diameter of 3.2 m and a height of 1.025 m.
The first flight of the Soyuz was 2.1W moved for months several times and was finally held on 28 December 2013.
Developments
Based on the Soyuz several projects of new more powerful missiles have emerged. Because of financing problems and / or lack of application areas, these projects have not been realized. Here the best known of which are described.
Jamal
Jamal (Russian Ямал, English Yamal, named after the Yamal Peninsula in northwestern Siberia ) the project is a largely based on the Soyuz carrier rocket, which was proposed in 1996 by RKK Energia to implementation. The developers set the target to increase the payload capacity dramatically, but without changing the external shape ratios of the rocket in order to continue to use as the starting units of the Soyuz can. In addition, should for the production of Jamal as possible can be returned reefs to existing production facilities. It was named rocket from the Yamal communications satellites of the Russian gas company Gazprom, which should be started with the new rocket ( launch took place in 1999 with a proton).
The first stage of Jamal (booster) is largely unchanged from the Soyuz -U. The second stage ( center stage ) is driven with a single NK -33 engine. NK -33 is an engine of the Soviet N1 moon rocket, the same number of started it. The engines are no longer produced, but there are still about 30 pieces of the N1 program remained. For the re-use the stored engines have been tested and also received some modifications: Thus, for example, the internal pressure increases and the engine is pivotally mounted. In addition to the installation of the NK -33, the diameter of the central block of the missile to a maximum of 3.44 m was increased ( in the spacecraft - 2.66 m ) and the Treibstoffzuladung up to 141 tonnes ( 50 tons more than the spacecraft ) is raised. The third stage diameter was also increased, resulting in a Treibstoffzuladung of 30 t allowed. Stage should be driven by an RD -0124, which is also used in the spacecraft 2. In addition, the missile should be a fourth stage named Taimyr (Russian Таймыр ) obtained, which is derived from the Blok - D of the Proton rocket. At the same time, the rocket should get a new and bigger payload fairing.
The take-off mass of Jamal should be 374 t, so they could be launched from the launch facilities in Baikonur and Plesetsk the Soyuz, the missile can carry at the maximum mass of 400 t. The payload capacity is 11.8 t into a 200 km high orbit from Baikonur, 11.3 t in a 200 km high orbit from Plesetsk and from 1.36 t in the GEO specified.
Although the rocket could be developed with relatively minor modifications and already finished, the N1 leftover NK -33 engines, lacked the money for it, so that Jamal has not been realized in this configuration. Already in 1999, was also the project of Aurora, an export variant of Jamal.
Aurora
Aurora ( Аврора, dawn ') is a variant of Jamal, which was presented for the first time in 1999. Aurora should start from a new launch facility on the belonging to Australia Christmas Island in the Indian Ocean, previously should be made from Baikonur test flights. The cost of building the plant and infrastructure were estimated at about 500 million U.S. dollars and should be borne by private investors. Aurora should be primarily used to launch commercial communications satellites in average mass segment. After some preparatory work to finance the project, however, was reinstated. Due to the decline of the satellite launch market, it is now unlikely that Aurora will ever called back to life.
Aurora differs only slightly from Jamal: the main differences are an improved NK -33- 1 powered plant in the central level as well as a more spacious payload fairing. NK -33- 1 is a variant of the NK -33, which has a retractable nozzle. The nozzle is extended to about 10 km altitude, allowing the engine to better adapt to different phases of flight. The fact the payload capacity of the rocket is increased by about 2%. In addition to NK -33 -1 equipped with four combustion chambers RD- 0124R engine to control the rocket should be installed in the central stage. This is one of the RD -0124 third stage of the rocket Sojus-2/Jamal variant. Since this type of control as proved technically difficult to achieve, it was decided not to develop RD- 0124R, and instead pivoted to use the NK 33-1 engine, for which they used the universal joint of the RD -0120 engine of the Energia rocket. In the first stage (booster) RD- 107A engines of the Soyuz -FG should be used and the third stage should be driven by an RD -0154. RD -0154 is a variant of the RD -0124 with a combustion chamber, the engine is hinged and has a retractable nozzle. The fourth stage was with Korwet (Russian Корвет, English Corvet, Corvette ') similar to that of Jamal one planned by the block D of the Proton rocket derived stage, which should be driven by a 11D58MF engine. Unladen mass of Korwet level is 1649 kg, Treibstoffzuladung 10 t. The rocket should fly both in three-stage (low orbits ) and in four-stage configuration (high orbits ). The take-off mass of the four -stage variant should be 379 t.
Due to the improvements to the rocket and the laying of the launch site closer to the equator the payload capacity of Aurora rises to 11,860 kg in a 200 km orbit with an inclination of 11.3 °, 4350 kg in the Geotransferorbit and 2600 kg into geostationary orbit.
Onega
Onega (Russian Онега, named after the river Onega ) was proposed in 2004 by RKK Energia as the future support for the new manned spacecraft Kliper. Your payload capacity is about 14.5 tonnes for the near-Earth orbit and 1.6 tons for GEO (other sources give 2.3 t to ) at a start of Plesetsk from specified. The first stage ( booster) is driven by a newly developed RD -0155 engine which has a combustion chamber and burn the liquid fuel with oxygen. According to other data, the booster could also RD 120.10F ( 11D123 ) engines, which can also be found in the second stage of the Zenit use, are driven. The central level should not be a NK -33, but with a RD -191, the main engine of the Angara, driven as opposed to Jamal / Aurora. However, both engines are quite similar in their performance. The missile has a highly energetic with liquid oxygen and liquid hydrogen ( LOX/LH2 ) powered third stage RD -0146 engine. The fourth stage called Jastreb (Russian Ястреб, hawk ', English Yastreb ) for use in high orbits is powered by LOX/LH2. This stage uses a RD -0126 or RD- 0126E ( a variant of the RD -0126 with a modified nozzle) powerplant. The take-off mass of the Onega should be 376 t. For a start the Onega with a three Kliper version would be used without payload fairing, which Kliper is placed on the top of the rocket. As Onega would be the first launching in Plesetsk rocket that uses liquid hydrogen as a fuel, is called upon realization as one of the biggest problems the lack of infrastructure for the production / processing of liquid hydrogen in Plesetsk.
Since in the course of 2004, the Russian space agency preferred a Angara rocket or in cooperation with Ukraine a Zenit rocket for transporting Kliper, the project of Onega was placed on ice until further notice. After the European Space Agency in mid-2005 expressed their interest in Kliper was Onega or a similar rocket with a NK -33- 1 in the central stage, RD 120.10F in the boosters and RD- 0146E in the third stage under the name of Soyuz -3 as the carrier back in the news, because it would allow a start of the spaceship from the European Spaceport in Kourou, where both are currently being built launch facilities for Soyuz - 2 rocket and already a LH2 infrastructure for the Ariane 5 exists. The necessary funding for Kliper were approved at the meeting of the European Space Council in December 2005.
Soyuz in Kourou
End of 2004, the ESA and the Russian space agency Roscosmos agreed to start from 2009 Soyuz rocket from the launch pad ELS neuzubauenden on the European spaceport in Kourou Guiana Space Centre in French Guiana. It should Soyuz -2 with a larger payload fairing (ST type) under the name of Soyuz -ST small payloads for Ariane 5 is too large, carry into space. Both Soyuz - 2.1a as well Soyuz 2.1b versions should be used here. The rocket itself was slightly modified for use in Kourou. For example, the Soyuz will be equipped with a built in Alcatel Alenia Space security system that can shut down in an emergency from the earth, the engines of the rocket. Furthermore, the four boosters were provided with flood valves, so you can quickly sink into the sea after separation. In addition, radar sensors were installed for flight path control. However, the construction of the new Soyuz launch facility in Kourou could not be started with the original forward and were completed by mid- 2011, with ESA bears most of the costs of construction, which are given with € 344 million. The foundation stone of the construction site on 26 February 2007. Here, a plaque was unveiled and walled in a 20 -pound stone from the launch pad at Baikonur, departed from where Yuri Gagarin in April 1961 became the first man into space. The first launch of a Soyuz in Kourou was not yet recognized the end of 2006 for May 2009. Due to technical problems, the first launch on 21 October 2011 entering the service of the smaller Vega rocket in mid-2012, Arianespace is in Kourou offer launch services in all payload categories. For light payloads, the Vega, for medium Soyuz -ST and for heavy Ariane 5
Since Kourou is much closer to the equator than Baikonur, it is energetically cheaper to start from there geostationary satellites, so that a Soyuz in Kourou has a higher payload capacity than Baikonur or Plesetsk. The payload capacity of the Soyuz -ST is given as 2720 kg for a Geotransferorbit, 1360 kg for a geostationary orbit and 4350 kg for a sun-synchronous orbit. At her first start on 21 October 2011, a Soyuz -ST launched the first two satellites of the Galileo satellite navigation system into orbit.
Construction and launch
The Soyuz is marketed by Starsem and built by the Russian producer TsSKB -Progress (Samara Space Center ). The rocket parts supplied by different companies are assembled horizontally in a special assembly and Prüfgebäude. In Kourou erecting already takes place shortly after leaving the Assembly building. The missile is enclosed there until the start for climatic reasons or from an additional mobile service turret up to the launch pad .. After mounting ( fully fueled and equipped ) payload, the rocket moves with a special vehicle by rail for about 2 km from the launch platform. Only there, the rocket is hydraulically placed in its vertical position, aligned with the rotary table to the exact start in the later starting direction (inclination ) and suspended in the starting platform above the 25 m deep pit. The rocket is not at the start of the table, but is connected to the four arms approximately at the level of the ends of Booster mounted, making it possible easily to construct the missile, and thus less stable ( due to the reduced structural mass ). In addition, the two halves of the maintenance and control tower are then placed in position. About eight hours before the start of the final countdown begins. Fueling of the rocket is usually only a few hours before the start. For manned missions the crew meets approximately two and a half hours before the start and takes place in a space ship. An hour before the start of the maintenance storms are folded back and fifteen minutes before the start of the on- board power supply is turned on and the rescue system activated. Six minutes before the start of automatic start is initiated, the cable and mast of the refueling mast be turned away. Two and a half minutes before the start tanks are pressurized with nitrogen gas under pressure and fully switched 45 seconds before starting on the internal power supply. 20 seconds before lifting the start command is then given (point of no return ), three seconds later ignite the engines and three seconds before lift-off the engines reach their full potential. Now the boom open flower shape by its own weight and by the elimination of the weight of the rocket due to its thrust at launch. About 118 seconds later the booster and after 226 seconds are dropped the payload fairing. After 288 s, the second stage has burned out and is discarded after 295 s and the lower part of the third stage panel that continues to operate up to 528 seconds and then separated. For unmanned missions with a fourth stage ignites at about 588 seconds At startup enter accelerations up to 4.3 g just before the separation of the first stage and again just under 3.5 g just before the end of firing the third stage on.
Start list
All scheduled and all starts from 1990 are listed in the start list of the Soyuz rocket.
Specifications
Recycling
The first stage of the Soyuz rocket, the launch from Baikonur booster, go down in the Kasachensteppe where they are salvaged from scrap collectors and recycled.