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N2O4/UDMH

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8K84 back
Credit: © Mark Wade

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Specific impulse: 333 s. Specific impulse sea level: 285 s. Location: 1720.

Optimum Oxidizer to Fuel Ratio: 2.61. Temperature of Combustion: 3,415 deg K. Ratio of Specific Heats: 1.25. Density: 1.18 g/cc. Characteristic velocity c: 1,720 m/s (5,640 ft/sec). Isp Shifting: 285 sec. Isp Frozen: 273 sec. Oxidizer Density: 1.450 g/cc. Oxidizer Freezing Point: -11 deg C. Oxidizer Boiling Point: 21 deg C. Fuel Density: 0.793 g/cc. Fuel Freezing Point: -57 deg C. Fuel Boiling Point: 63 deg C.

37K-Mir Russian manned space station. Cancelled 1983. The basic 37K design consisted of a 4.2 m diameter pressurized cylinder with a docking port at the forward end. It was not equipped with its own propulsion system.

8D43 Kosberg N2O4/UDMH rocket engine. UR-500 stage 1 original concept. Hardware. In early Proton design would be clustered with 4 x Glushko 11D43. Abandoned in favor of 6 x Glushko 11D48, but later developed into the RD-0208 and RD-0210.

8S816 N2O4/UDMH propellant rocket stage. Orevo has sectioned hardware. Total mass, sea level thrust accurate; Isp, empty mass and burn time estimated. Source: Placard, Orevo.

Almaz APOS Russian manned space station. Cancelled 1966. The initial Almaz phase 1 configuration as conceived in 1965 included a single-launch station with its own VA crew return re-entry module.

Almaz OPS Russian manned space station. Vladimir Chelomei's Almaz OPS was the only manned military space station ever actually flown.

Almaz OPS-2 Russian manned space station. Configuration with two docking ports, one at each end of the station. Cancelled 1979. The initial Almaz military space station program planned in 1965 consisted of two phases. In the second phase sustained operations would be conducted with Almaz dual-docking port stations serviced by TKS manned resupply vehicles.

Almaz-1B Russian civilian surveillance radar satellite. Study 1993.

Almaz-2 Russian civilian surveillance radar satellite. Study 1995. Plans for an even more sophisticated and capable civilian Almaz 2 spacecraft were made in the early 1990's. Almaz 2's payload mass of 6.

Almaz-T Russian civilian surveillance radar satellite. The results of the manned Almaz flights showed that manned reconnaissance from space was not worth the expense. Radar satellite (modified manned spacecraft) satellite for NPO Machinostroenye, USSR. Launched 1986-1991.

Apollo CSM The Apollo Command Service Module was the spacecraft developed by NASA in the 1960's as a standard spacecraft for earth and lunar orbit missions. Manned spacecraft for earth orbit and lunar orbit satellite operated by NASA, USA. Launched 1967 - 1975.

Apollo CSM Block I American manned spacecraft. The Apollo Command Service Module was the spacecraft developed by NASA in the 1960's as a standard spacecraft for earth and lunar orbit missions.

Apollo RM American logistics spacecraft. Study 1967. In 1967 it was planned that Saturn IB-launched Orbital Workshops would be supplied by Apollo CSM spacecraft and Resupply Modules (RM) with up to three metric tons of supplies and instruments.

Fregat N2O4/UDMH propellant rocket stage. Upper stage developed from propulsion bus for Lavochkin lunar and planetary probes (Luna Ye-8, Mars M1, Fobos 1F). 20 restarts.

Gemini - Double Transtage American manned lunar orbiter. Study 1965. In June 1965 astronaut Pete Conrad conspired with the Martin and McDonnell corporations to advocate an early circumlunar flight using Gemini.

Gemini LORV American manned lunar orbiter. Study 1967. This version of Gemini was studied as a means of rescuing an Apollo CSM crew stranded in lunar orbit. The Gemini would be launched unmanned on a translunar trajectory by a Saturn V.

Gemini Lunar Surface Rescue Spacecraft American manned lunar lander. Study 1966. This version of Gemini would allow a direct manned lunar landing mission to be undertaken in a single Saturn V flight, although it was only proposed as an Apollo rescue vehicle.

Gemini Lunar Surface Survival Shelter American manned lunar habitat. Study 1967. Prior to an Apollo moon landing attempt, the shelter would be landed, unmanned, near the landing site of a stranded Apollo Lunar Module.

LEAP lunar flyer American manned lunar flyer. Study 1961. LEAP was an early 1960's British design for getting disabled astronauts on the lunar surface quickly to lunar orbit for ferrying home.

LK Russian manned lunar lander. The LK ('Lunniy korabl' - lunar craft) was the Soviet lunar lander - the Russian counterpart of the American LM Lunar Module. Manned Lunar lander test satellite, Russia. Launched 1970 - 1971.

LK-1 Russian manned lunar flyby spacecraft. Cancelled 1965. The LK-1 was the spacecraft designed by Chelomei for the original Soviet manned lunar flyby project. The re-entry vehicle and propulsion systems would continue in development for the LK-700 lunar lander and TKS space station resupply vehicle.

LK-3 Russian manned lunar lander. Reached mock-up stage, 1972. The LK-3 was Chelomei's preliminary design for a direct-landing alternative to Korolev's L3 manned lunar landing design.

LK-700 Russian manned lunar lander. Chelomei's direct-landing alternative to Korolev's L3 manned lunar landing design. Developed at a low level 1964 to 1974, reaching mockup and component test stage.

LM Langley Light American manned lunar lander. Study 1961. This early open-cab single-crew Langley lunar lander design used storable propellants, resulting in an all-up mass of 4,372 kg.

Mir The Mir space station was the last remnant of the once mighty Soviet space program. The core module was launched on 1986-02-20. It was built to last only five years, and consisted of a station core derived from the Salyut space station, with docking ports to accomodate additional modules for specialized research. As the Soviet Union collapsed Mir stayed in orbit, but the final modules were were delivered years late and could only be completed with American financial assistance. The Mir complex in the end consisting of 7 modules with 11.5 metric tons of scientific equipment. It cost $220 to $240 million per year to keep in operation. Kept flying over a decade beyond its rated life, Mir proved a source of pride to the Russian people and proved the ability of their cosmonauts and engineers to improvise and keep operations going despite all manner of challenges and mishaps.

MTKVA Russian manned spaceplane. Study 1974, competitor with Buran. Manned lifting body spaceplane, designed by Soviet engineers as a recoverable spacecraft in the early 1970's.

OK-M Russian manned spaceplane. Study 1984. 1980's design for a spaceplane, smaller than Buran, to replace Soyuz and Progress spacecraft for space station crew rotation/replenishment tasks.

OK-M1 Russian manned spaceplane. Study 1984. The OK-M1 manned spaceplane was designed by NPO Molniya as a follow-on to the OK-M of NPO Energia. The OK-M1 was an integrated part of a unique launch vehicle, the MMKS reusable multi-module space system.

OK-M2 Russian manned spaceplane. Study 1984. The OK-M2 was a manned spaceplane, a straight delta wing joined to a broad fuselage with an upturned nose.

Polyblock UR-500-1P N2O4/UDMH propellant rocket stage. Original 'Polyblock' design for Proton first stage. This was selected configuration; although somewhat greater in dry mass, it had the advantages of shorter length.

Progress M Russian logistics spacecraft. Progress M was an upgraded version of the original Progress. New service module and rendezvous and docking systems were adopted from Soyuz T. Cargo satellite operated by RKK > RAKA, Russia. Launched 1989 - 2009.

Proton The Proton launch vehicle has been the medium-lift workhorse of the Soviet and Russian space programs for over fifty years. Although constantly criticized within Russia for its use of toxic and ecologically-damaging storable liquid propellants, it has out-lasted all challengers. The latest potential replacement, the Angara, may not be operational until the 2020's.

R-56 Block A N2O4/UDMH propellant rocket stage. .

R-56 Block B N2O4/UDMH propellant rocket stage. .

R-56 Block O N2O4/UDMH propellant rocket stage. Empty mass estimated (rounded figures given in source material indicates impossible 31 metric tons gross with 30 metric tons propellant).

RD-0203 Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Hardware. DU consisting of 4 RD-0204 gimbaled motors. Staged combustion cycle. First flight 1964.

RD-0205 Kosberg N2O4/UDMH rocket engine. UR-200 stage 2. Engine unit consisting of 1 RD-0206 main engine and 4 RD-0207 vernier/steering engines. Version of 8D44 and 8D45 with extended nozzle. Developed 1961. First flight 1963.

RD-0208 Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Developed 1961-65. Stage 1 had three RD-0208 plus one RD-0209. Further developed into RD-0210.

RD-0210 Kosberg N2O4/UDMH rocket engine. Cluster of four similar engines used in second stage of Proton - one providing tank pressurization (8D412K/RD-0211) and three (8D411K/RD-0210). Staged combustion cycle. First flight 1965.

RD-0212 Kosberg N2O4/UDMH rocket engine. Proton stage 3. Engine unit consisting of 1 RD-0213 main engine and 4 RD-0214 vernier/steering engines. 8D48 essentially similar to 8D411 and 8D412 and has the same combustion chamber. First flight 1967.

RD-0216 Kosberg N2O4/UDMH rocket engine. UR-100 stage 1. Staged combustion cycle. Includes tank pressurization system (RD-0217 without tank press.). First launch November 1963, manufactured until 1974, operational until 1991. First flight 1965.

RD-0221 Kosberg N2O4/UDMH rocket engine. upper stage of unnamed missile by Mishin. Developed 1965-70.

RD-0225 Kosberg N2O4/UDMH rocket engine. Almaz space station orbital maneuvering. Hardware. Originally designed for UR-100 follow-on spaceships. Two engines used on Almaz space station for orbital maneuvering, Pressure fed. First flight 1974.

RD-0228 Kosberg N2O4/UDMH rocket engine. R-36M / RS-20A (SS-18 mod-1) stage 2. Out of Production. Comprises single-chamber main engine RD-0229 plus four-chamber steering engine RD-0230. Further developed to RD-0255.

RD-0233 Kosberg N2O4/UDMH rocket engine. UR-100N / RS-18 (SS-19) stage 1. Out of Production. Staged combustion cycle. First flight 1974.

RD-0235 Kosberg N2O4/UDMH rocket engine. UR-100N / RS-18 (SS-19) stage 2. Main engine based on RD-0217 with larger nozzle for altitude operation. Staged combustion cycle. First flight 1972.

RD-0237 Kosberg N2O4/UDMH rocket engine. UR-100N / RS-18 (SS-19) stage 3. MIRV service block. Open cycle. Analogous to RD-0225, pressure fed. Steering engine for space vehicles gimbaling +/- 45 degree. First flight 1972.

RD-0242 Kosberg N2O4/UDMH rocket engine. sea-based missile booster stage developed 1977-83 (Burlak). First concept planned N2O4/kerosene as propellant, but changed to N2O4/UDMH. Single ignition, 297 development tests. 50 engines for sale.

RD-0243 Kosberg N2O4/UDMH rocket engine. R-29RM stage 1. Out of Production. Consisted of single-chamber main engine RD-0244 plus four-chamber steering engines RD-0245 driven by turbine exhaust gas. Engine submerged in propellant tank.

RD-0244 Kosberg N2O4/UDMH rocket engine. R-29RM / RSM-54 (SS-N-23) stage 1. Out of Production. Main engine in system RD-0243. Staged combustion cycle. Submerged in propellant tank. First flight 1985.

RD-0255 Kosberg N2O4/UDMH rocket engine. R-36M2 / RS-20V (SS-18 Mod-4) stage 2. Comprises of single-chamber main engine RD-0256 plus four-chamber steering engines RD-0257. Development based on RD-0228 with thrust increase by 11%. First flight 1986.

RD-251 Glushko N2O4/UDMH rocket engine. R-36-0 stage 1, Tsyklon 2 stage 1. In production. Assembly of 3 RD-250-type units. First flight 1965.

RD-252 Glushko N2O4/UDMH rocket engine. R-36-0 stage 2; Tsyklon 2 stage 2. In production. Used modified chamber from RD-219, nozzle is conventional, so performance is higher. First flight 1965.

RD-253 Glushko N2O4/UDMH rocket engine. In Production. Version of RD-253 with thrust increased by 7%. Included an additional gas generator for tank pressurization. First flight 1986.

RD-253-11D48 Glushko N2O4/UDMH rocket engine. Six gimbaled single chamber RD-253s provide the first stage power for the UR-500 Proton launch vehicle and the third stage of the planned UR-700 moon launcher. First flown in 1965.

RD-253-14D14 Glushko N2O4/UDMH rocket engine. Proton KM-1. In production. Developed in 1990s. First flight 1999.

RD-270 Glushko N2O4/UDMH rocket engine. UR-700, R-56 stage 1. Development ended 1968. Developed 1962-1971, largest rocket engine ever built in the Soviet Union, answer to F-1. Tested but cancelled before combustion instability problems solved.

RD-854 Yuzhnoye N2O4/UDMH rocket engine. R-36orb (SS-X-10) orbital stage. Out of Production. Thrust vector control by 4 nozzles fed from gas generator.

RD-855 Yuzhnoye N2O4/UDMH rocket engine. Tsyklon stage 1 attitude control engine. Out of Production. Four-chamber pump-fed single-run engine burned hypergolic propellants in a gas generator scheme.

RD-856 Yuzhnoye N2O4/UDMH rocket engine. Tsyklon stage 2 attitude control engine. Out of Production. Autonomous four-chamber pump-fed single-run engine burned hypergolic propellants in a gas generator scheme.

RD-857 Yuzhnoye N2O4/UDMH rocket engine. RT-20P missile stage 2. Out of production. Designed for second stage of mixed propulsion missile, only flight tests. Thrust vector control by secondary gas injection into nozzle. First flight 1967.

RD-858 Yuzhnoye N2O4/UDMH rocket engine. Primary engine for LK manned lunar lander. Propulsion cluster provided the variable thrust needed for a soft landing onto the lunar surface, then restarted for injection into lunar orbit. Flown 1970.

RD-859 Yuzhnoye N2O4/UDMH rocket engine. LK lunar lander reserve engine. Hardware. Backup engine for the LK manned lunar lander in the event the primary RD-858 engine failed. Restart within three seconds after shut down. Flight tests 1970.

RD-860 Yuzhnoye N2O4/UDMH rocket engine. Upper stages. Developed 1972. Engine used a novel scheme combining an existing proven combustion chamber but using a pneumatic pump for propellant supply.

RD-861 Yuzhnoye N2O4/UDMH rocket engine. Tsyklon 2 and 3 stage 3; Ikar. In production. Based on RD-854. Thrust vector control by 4 nozzles (thrust 98 N each) fed from a gas generator. First flight 1965.

RD-861K Yuzhnoye N2O4/UDMH rocket engine. Tsyklon 2 and 3 stage 3; Ikar. Developed 2005. High pressure fuel was used to gimbal the engine in two planes, replacing four thrust vector engines on the basic RD-861.

RD-862 Yuzhnoye N2O4/UDMH rocket engine. MR-UR-100 / RS-16 (SS-17) stage 2. Out of Production. Based on RD-857. Thrust vector control by secondary gas injection into nozzle. Roll control via special small jet nozzles.

RD-866 Yuzhnoye N2O4/UDMH rocket engine. RT-23 MIRV-bus. Out of Production. Engine consisted of two turbopumps with gas generators and two feeders; a single chamber main engine; and 16 liquid thrusters for attitude control and translation.

RD-868 Yuzhnoye N2O4/UDMH rocket engine. Apogee stage. Developed 1983-. In development in 1996. One main and an unknown number of control thrusters. 23.25 + 0.03 kN. Chamber pressure 91.5 / 6.9 bar. Specific impulse 325 / 230 sec.

Rescue Gemini American manned rescue spacecraft. Study 1966. A version of Gemini was proposed for rescue of crews stranded in Earth orbit. This version, launched by a Titan 3C, used a transtage for maneuvering.

Rokot-3 Briz N2O4/UDMH propellant rocket stage. High performance storable liquid engine. The basic stage can be adapted with 'wrap-around' propellant tanks for Proton booster applications.

S5.51 Isayev N2O4/UDMH rocket engine. Hardware 1969. Complex engine used to maneuver the LOK to a rendezvous with the LK lander in lunar orbit, then propel the LOK out of lunar orbit. Verniers included for midcourse corrections.

Salyut 6 Russian manned space station, launched 1977-09-29. The Salyut 6 space station was the most successful of the DOS series prior to Mir. It was aloft for four years and ten months, completing 27,785 orbits of the earth.

Salyut 7 Russian manned space station, launched 1982-04-19. Salyut 7 was the back-up article for Salyut 6 and very similar in equipment and capabilities. However the crews were able to conduct significant military experiments due to the greatly increased volume and payload of the TKS modules diverted from the cancelled Almaz program that docked with the station.

SE-1, 1-1, -2, and -4 Series Rocketdyne N2O4/UDMH rocket engine. SE-1, 1-1, -2, and -4 Series. Spacecraft Reaction Control. Pressure-fed. Multiple thrust levels. First flight 1959.

SE-5-2/-3 Rocketdyne N2O4/UDMH rocket engine. SE-5-2/-3. Agena Auxiliary. Pressure-fed. SE-5-2 four engines in satellite system. SE-5-3 two engines for Agena auxiliary propulsion. First flight 1963.

Soyuz 7K-LOK Russian manned lunar orbiter. The two-crew LOK lunar orbiting spacecraft was the largest derivative of Soyuz developed. Manned Lunar orbit and return satellite, Russia. Launched 1972.

Soyuz 7K-S Russian manned spacecraft. The Soyuz 7K-S had its genesis in military Soyuz designs of the 1960's. Launched 1974 - 1976.

Soyuz T Russian manned spacecraft. Soyuz T had a long gestation, beginning as the Soyuz VI military orbital complex Soyuz in 1967. Launched 1978 - 1986.

Soyuz TM Russian manned spacecraft. Launched 1986 - 2002.

Soyuz TMA Russian three-crew manned spacecraft. Designed for use as a lifeboat for the International Space Station. After the retirement of the US shuttle in 2011, Soyuz TMA was the only conveying crews to the ISS. Except for the Chinese Shenzhou, it became mankind's sole means of access to space. Launched 2002 - 2011.

TKS Vladimir Chelomei's TKS manned ferry vehicle was designed to provide a reusable resupply and crew return spacecraft much more capable and flexible than either the Soyuz or Apollo designs. Although the TKS completed its development program as part of the military Almaz space station program it was never used for manned spaceflight. However the TKS resupply vehicle provided the basis for the successful FGB space station modules used with the Salyut, Mir, and International Space Station. The original TKS was launched four times, from 1977.07.17 (Cosmos 929) to 1985.09.27 (Cosmos 1686).

Topaze SEP N2O4/UDMH rocket engine. Out of production. Used on Diamant launch vehicle. First flight 1965.

UR-200-2 N2O4/UDMH propellant rocket stage. TsNIIMash has 1:10 structural simulation model. Developed 1960-1965. Orevo has sectioned hardware. All data accurate except empty mass prorated between first and second stages.

UR-700-3 N2O4/UDMH propellant rocket stage. .

Viking 2 SEP N2O4/UDMH rocket engine. In production. Used on Ariane 1, GSLV space launchers. First flight 1979.

YF-20A Beijing Wan Yuan N2O4/UDMH rocket engine. Out of production. Boosted CZ-2A, CZ-2C, CZ-2E(A), CZ-3, FB-1. First flight 1972.