Encyclopedia Astronautica
Zenit-3


Lox/Kerosene propellant rocket stage. Loaded/empty mass 17,300/2,720 kg. Thrust 84.92 kN. Vacuum specific impulse 352 seconds. Adaptation of Block D for Zenit.

Cost $ : 20.000 million.

Status: In production.
Gross mass: 17,300 kg (38,100 lb).
Unfuelled mass: 2,720 kg (5,990 lb).
Height: 5.60 m (18.30 ft).
Diameter: 3.70 m (12.10 ft).
Span: 3.70 m (12.10 ft).
Thrust: 84.92 kN (19,091 lbf).
Specific impulse: 352 s.
Burn time: 650 s.
Number: 25 .

More... - Chronology...


Associated Countries
Associated Engines
  • RD-58Z Korolev Lox/Kerosene rocket engine. 71 kN. Zenit stage 3. Developed 1981-1990. Isp=361s. More...
  • RD-58M Korolev Lox/Kerosene rocket engine. 83.4 kN. Proton 8K824K / 11S824M; 11S824F; 11S86; 11S861; 17S40 stage 4 (block DM). In production. Isp=353s. First flight 1974. More...

Associated Launch Vehicles
  • Kvant Russian orbital launch vehicle. The Kvant was the Soviet third generation light launch vehicle planned to replace the Kosmos and Tsyklon series. Unlike the vehicles it was to replace, the booster used non-toxic 'environmentally friendly' liquid oxygen/kerosene propellants. Although such a light launch vehicle was on Space Forces wish lists since 1972, full scale development was again deferred due to the crash effort on Soviet 'star wars' in the second half of the 1980's. RKK Energia marketed the vehicle design from 1994 to 2001, but could find no source for development funds. More...
  • Zenit-3SL Ukrainian orbital launch vehicle. From the beginning of the program a Zenit-3 version was proposed for geosynchronous launches using the N1/Proton Block D third stage. This had the potential of replacing the Proton in the role of geosynchronous launcher. It was considered for launch from Australia / Cape York in the 1980's. Finally a joint US-Norwegian-Ukraininan-Russian consortium was formed to launch the three stage commercial Zenit from the Odyssey floating launch platform in the Pacific Ocean. More...
  • Zenit-3SLB Ukrainian orbital launch vehicle. Version of the Zenit-3SL modified for launch from existing ground facilities at Baikonur, using the common Zenit-2SB core vehicle with an upper stage Block DM-SLB designed by RSC Energia (Russia) and a new payload fairing designed by NPO Lavochkin (Russia). More...

Associated Propellants
  • 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...

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