Lox/Kerosene propellant rocket stage. Loaded/empty mass 25,400/2,400 kg. Thrust 298.10 kN. Vacuum specific impulse 330 seconds.
Cost $ : 3.000 million.
Status: Retired 2007.
More... - Chronology...
Gross mass: 25,400 kg (55,900 lb).
Unfuelled mass: 2,400 kg (5,200 lb).
Height: 6.74 m (22.11 ft).
Diameter: 2.66 m (8.72 ft).
Span: 2.66 m (8.72 ft).
Thrust: 298.10 kN (67,016 lbf).
Specific impulse: 330 s.
Burn time: 250 s.
Number: 1171 .
RD-0110 Kosberg Lox/Kerosene rocket engine. 297.9 kN. Soyuz 11A511, Molniya-M 8K78M. Precursor RD-0107 used in 11A57 Voskhod stage 2. Modified to increase reliability. Isp=326s. First flight 1964. More...
Associated Launch Vehicles
Molniya 8K78M Russian orbital launch vehicle. Improved Molniya, in variants with Blocks ML, 2BL, or SO-L third stages according to payload. More...
Molniya 8K78M ML Russian orbital launch vehicle. Improved Molniya variant with Blok-ML upper stage for placement of communications satellites into Molniya-class orbits with apogees of 38,500 km. More...
Soyuz 11A511L Russian orbital launch vehicle. 11A511 with reinforced second stage, large fairing for earth orbit test of LK lunar lander. More...
Soyuz 11A511M Russian orbital launch vehicle. Development of the Soyuz-M began in 1967 to launch the 6.6 metric ton Soyuz 7K-VI manned military spacecraft into a 65-degree inclination earth orbit. The spacecraft was cancelled, but development continued, and eight were Soyuz-M's were built and used to launch Zenit-4MT reconnaissance satellites in 1971-1976. The differences compared to the Soyuz-U are not known, and what (if anything) differentiated these Zenit-4MT missions from others is also a mystery. More...
Soyuz 11A511U Russian standardised man-rated orbital launch vehicle derived from the original R-7 ICBM of 1957. It has been launched in greater numbers than any orbital launch vehicle in history. Not coincidentally, it has been the most reliable as well. After over 40 years service in Russia, ESA built a new launch pad at Kourou which will keep it in service from three launch sites in three countries well into the mid-21st Century. More...
Soyuz 11A511U2 Russian orbital launch vehicle. Soyuz 11A511U2 used synthetic kerosene ('Sintin') in first stage for launch of premium reconnaisance satellite and manned payloads requiring just a bit more payload than the standard 11A511 could offer. Further use of the 11A511U2 abandoned in 1996 due to Sintin production stoppage. Later Soyuz spacecraft launched on standard Soyuz, with reduced payload and rendezvous with Mir in lower orbit accepted. More...
Molniya 8K78M SOL Russian orbital launch vehicle. Improved Molniya variant with Blok SO-L upper stage for placement of Prognoz-class satellites in orbits with apogees of 200,000 km. More...
Lox/Kerosene Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...
Home - Browse - Contact
© / Conditions for Use