| Manufacturer | Khrunichev |
|---|---|
| Country of origin | Russia |
| Used on | Angara stage 1 and boosters |
| General characteristics | |
| Height | 25.7 m (84 ft) |
| Diameter | 2.9 m (9 ft 6 in) |
| Gross mass | 142,400 kg (313,900 lb) |
| Propellant mass | 132,600 kg (292,300 lb) |
| URM-1 | |
| Powered by | 1 RD-191 |
| Maximum thrust | 1,920 kN (430,000 lbf) (sea level) |
| Specific impulse | 311 seconds (3.05 km/s) (sea level) |
| Burn time | Angara 1.2: 214 s Angara A5 Booster: 214 s Angara A5 Core: 325 s |
| Propellant | LOX/Kerosene |
| Manufacturer | Khrunichev |
|---|---|
| Country of origin | Russia |
| Used on | Angara A5 stage 2 |
| General characteristics | |
| Height | 6.9 m (23 ft) |
| Diameter | 3.6 m (12 ft) |
| Propellant mass | 36,000 kg (79,000 lb) |
| URM-2 | |
| Powered by | 1 RD-0124A |
| Maximum thrust | 294 kN (66,000 lbf) |
| Specific impulse | 359 seconds (3.52 km/s) |
| Burn time | 424 s |
| Propellant | LOX/Kerosene |
Universal Rocket Module (URM) is the name of the modular liquid fuelled first and second stage of the Angara expendable launch system. The first stage and booster variant is referred to as URM-1, while the second stage is referred to as URM-2. The URM-2 is derived from the Soyuz-2 Block I second stage. [1]
URM-1 is a unitary structure 2.9 meters in diameter and 25 meters in length that includes an oxidizer tank, a fuel tank (both tanks being coupled by a spacer) and an RD-191 engine burning RP-1 fuel with liquid oxygen producing a thrust of 1.92 MN. [2] URM-1 was first flown in 2014 on the Angara 1.2PP suborbital test flight. Angara can fly with either one URM-1 in the case of Angara 1.2 and Angara 1.2PP, or one URM-1 as a sustainer core with four additional URM-1s as boosters for Angara A5. [1]
URM-2 is a modified Block I stage, 3.6 meters in diameter and 6.9 meters in length. It is powered by a single RD-0124A producing 294 kilonewtons, derived from Block I's RD-0124. URM-2 was first flight tested on Angara 1.2PP, but will fly in operation only on the Angara A5. The operational Angara 1.2 will also use a modified Block I powered by the RD-0124A as a second stage, though this stage will have a diameter of no more than 2.9 meters. [3]
The Naro-1 launch vehicle was based on the URM-1 with a reduced thrust RD-191, called RD-151, combined with a solid-fueled second stage built by Republic of Korea KARI.
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Energia was a 1980s super-heavy lift launch vehicle. It was designed by NPO Energia of the Soviet Union as part of the Buran programme for a variety of payloads including the Buran spacecraft. Control system main developer enterprise was the Khartron NPO "Electropribor". The Energia used four strap-on boosters each powered by a four-chamber RD-170 engine burning kerosene/LOX, and a central core stage with four single-chamber RD-0120 (11D122) engines fueled by liquid hydrogen/LOX.
A solid-propellant rocket or solid rocket is a rocket with a rocket engine that uses solid propellants (fuel/oxidizer). The earliest rockets were solid-fuel rockets powered by gunpowder; they were used in warfare by the Chinese, Persians, Mongols, and Indians as early as the 13th century.
Soyuz is a family of expendable Russian and Soviet carrier rockets developed by OKB-1 and manufactured by Progress Rocket Space Centre in Samara, Russia. With over 1,900 flights since its debut in 1966, the Soyuz is the most frequently used launch vehicle in the world as of 2021.
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Delta IV is a group of five expendable launch systems in the Delta rocket family introduced in the early 2000s. Originally designed by Boeing's Defense, Space and Security division for the Evolved Expendable Launch Vehicle (EELV) program, the Delta IV became a United Launch Alliance (ULA) product in 2006. The Delta IV is primarily a launch vehicle for United States Air Force (USAF) military payloads, but has also been used to launch a number of United States government non-military payloads and a single commercial satellite.
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The Angara rocket family is a family of launch vehicles being developed by the Moscow-based Khrunichev State Research and Production Space Center. The launch vehicles are to put between 3,800 kg (8,400 lb) and 24,500 kg (54,000 lb) into low Earth orbit and are intended, along with Soyuz-2 variants, to replace several existing launch vehicles.
The staged combustion cycle is a power cycle of a bipropellant rocket engine. In the staged combustion cycle, propellant flows through multiple combustion chambers, and is thus combusted in stages. The main advantage relative to other rocket engine power cycles is high fuel efficiency, measured through specific impulse, while its main disadvantage is engineering complexity.
The RD-170 is the world's most powerful and heavy liquid-fuel rocket engine. It was designed and produced in the Soviet Union by NPO Energomash for use with the Energia launch vehicle. The engine burns the Russian equivalent of RP-1 fuel and LOX oxidizer in four combustion chambers, all supplied by one single-shaft, single-turbine turbopump rated at 170 MW (230,000 hp) in a staged combustion cycle.
Blok D is an upper stage used on Soviet and later Russian expendable launch systems, including the N1, Proton-K and Zenit.
A modular rocket is a kind of multistage rocket which has components that can interchanged for different missions. Several such rockets use similar concepts such as unified modules to minimize expenses on manufacturing, transportation and for optimization of support infrastructure for flight preparations.
Atlas is a family of US missiles and space launch vehicles that originated with the SM-65 Atlas. The Atlas intercontinental ballistic missile (ICBM) program was initiated in the late 1950s under the Convair Division of General Dynamics. Atlas was a liquid propellant rocket burning RP-1 fuel with liquid oxygen in three engines configured in an unusual "stage-and-a-half" or "parallel staging" design: two outboard booster engines were jettisoned along with supporting structures during ascent, while the center sustainer engine, propellant tanks and other structural elements remained connected through propellant depletion and engine shutdown.
The RD-191 is a high-performance single-combustion chamber rocket engine, developed in Russia. It is derived from the RD-180 dual-combustion chamber engine, which itself was derived in turn from the four-chamber RD-170 originally used in the Energia launcher.
The RD-0124 is a rocket engine burning liquid oxygen and kerosene in a staged combustion cycle. RD-0124 engines are used on the Soyuz-2.1b and Soyuz-2-1v. A slight variation of the engine, the RD-0124A, is used on the Angara rocket family URM-2 upper stage. RD-0124 is developed by Chemical Automatics Design Bureau in Voronezh.
The Baikal booster was a proposed reusable flyback booster for the Angara rocket family based on the Angara Universal Rocket Module in 2001. It was designed by the Molniya Research and Industrial Corporation for the Khrunichev Space centre, reusing the flyback and control system for the reusable Buran orbiter.
The Delta Cryogenic Second Stage (DCSS) is a family of cryogenic rocket stages used on the Delta III and Delta IV rockets, and which is planned to be used on the Space Launch System Block 1. The stage consists of a cylindrical liquid hydrogen (LH2) tank structurally separated from an oblate spheroid liquid oxygen (LOX) tank. The LH2 tank cylinder carries payload launch loads, while the LOX tank and engine are suspended below within the rocket's inter-stage. The stage is powered by a single Aerojet Rocketdyne-Pratt & Whitney RL10B-2 engine, which features an extendable carbon-carbon nozzle to improve specific impulse.
The flight of Angara-1.2pp was the maiden flight of Russia's Angara series of rockets. This flight was conducted successfully on 9 July 2014. A unique configuration with parts taken from the Angara-1 and Angara-A5 rockets, the suborbital mission served to flight test each of the new stages developed for the rocket ahead of its operational use.
The Soyuz-7 or Amur is a partially-reusable, methane–fueled, orbital launch vehicle currently in the design concept stage of development by the Roscosmos State Corporation in Russia. Design began by 2020, with operational flights planned for no earlier than 2026. Amur is intended to substitute for the existing Soyuz-2, at a much lower per launch cost.
Irtysh, also named Soyuz-5, formerly codenamed Fenix in Russian and Sunkar in Kazakh, is a planned Russian rocket that is being developed by JSC SRC Progress within the "Project Feniks". Initially it will replace the capability of Zenit-2 and Proton Medium, and in the future will serve as the base of a super heavy-lift launch vehicle rocket (Yenisei) to match the Energia/Buran capabilities. As of February 2021, Irtysh is expected to launch from the Baikonur Baiterek, the ex Zenit-2 launch site, in a partnership with the government of Kazakhstan, with a planned debut in late 2023.