Updated: 12-Jan-2019
Sometimes written as Glouchko. It is the surname of Valentin P. Glushko, who had started in GDL designing rocket engines like the ORM-2, and in a more perfected form the ORM-12C that gave 400 Kgf of thrust, in the year 1935. See Energomash (NPO)
-All the information that appears here, in the Glushko chapter, is complemented with that of Energomash and Energia.
-It is clear that Glushko was surrounded by important teams of high level technical personnel. After him, at the head of Energomash there was chief of design (1974-1991) Vitaly Radovsky and from then until today Boris Katorgin.
-Let's say that the "parents" of Russian astronautics were H.N. Tijomirov and K. Tziolkovsky (or vice versa), who inspired many other people to continue with the studies they left behind.
-In the initial Glushko group we can highlight Head of GDL, N.Y. Ilin. RNII director, I.T. Kleimenov. The RNII chief's assistant and senior engineer G.E. Languemak, and at that time GLD Section Chief, V.P. Glushko himself.
“Ilin and Kleimenov”
“Languemak and a young Glushko”
-Reviewing the origin of all Glushko's work, his biographical data and those obtained at the NPO Energomash Museum, he appears as the main designer of the range of rocket engines in the USSR, continuing with the Russian Confederation and now Russia.
-We already saw the ORM series and a good part of the first RDs. Add that during WWII (or Patriotic War for the Russians), the RD-1 was already installed on the Yak-3RD at the end of the tail of the fuselage. Between 1941 and 1946, the RD-1Khz engine was mounted on fighters This engine had chemical ignition regarding the RD-1.
“Glushko RD-1 on fighter”
-The RD-1Khz was installed on a Lavotchkin La-5 to perform engine tests. It consumed kerosene and nitric acid, in a mixture of 1 and 2 parts of each.
-The engines were known as Zh-RD-1 "from" Zhidkostniyi Rekativnyi Dvigatel "or liquid fuel rocket.
-They were engines for take-off and combat.
“RD-1Khz”
-The RD-1CH2s had chemical starters. The full denomination was RD-1CH2-X3 and they were practically known as RD-1X3.
-The RD-2s delivered 652 Kgf for 200 seconds and were based on the RD-1, like the -3 and -4.
-There was an RKDS-100 that was destined to power bombers in 1946. It ran on Lox and kerosene.
-It is known that in the 50's there was an RD-3 that was the assembly of 3 RD-1 engines with common turbo-pump and external ignition.
-The engines for lifting military loads or satellites start with the RD-100. They were developed with technicians and material from the V-2 brought from Germany.
-The R-100 worked like the German original one that used alcohol and Lox. It was developed between 1946 and 1950 and delivered 31,000 Kgf in vacuum.
-The R-101 was increased to 41000 Kgf of thrust in vacuum, but with little intervention from the Germans, for safety.
-The RD-102 and RD-103 running on Lox and alcohol increased their powers, but with the same substantial measures like the diameter of 1.65 m, varying the accessory elements.
-The RD-105 already used Lox and kerosene with one combustor giving 64,000 Kgf. The RD-106 was installed on the two-stage ICBM R-7. It was an RD-105 but with a larger and higher nozzle.
“RD-107 with correction combustors” (PiP)
-The RD-107s, were seen in R-7 missiles on Vostok and Soyuz carriers.
-There were many variations and despite being a design from the late 1950's, there were still releases in the 1990's.
-The RD-108, on the R-7, Vostok and Soyuz, delivering 102,000 Kgf in vacuum has done almost 700 launches. it is similar to the RD-107.
-The RD-109 was active between 1958 and 1960, using Lox and UDMH. It delivered a moderate thrust of 10,300 Kgf. It was installed on the second stage of the R-7 missile.
-The relatively short time of using the RD-109 was due to Korolev's refusal to use toxic fuels.
-However, they were repeated in the RD-119, widely used in the Cosmos programs.
“RD-119, photo Mark Wade” (PiP)
-The RD-120 used between 1976 and 1985 was mounted on the second stage of the Zenith. It had a thrust of 85,000 Kgf.
-The RD-134 consisted of four gimballing chambers, in +-3° with a thrust of 35,000 Kgf.
-The RD-135 was experimental using LOX / LH2.
--On the Angara vehicle, the RD-146 was used in the second stage, running on Lox / kerosene. It was a variant of the RD-120.
-From 1993 the RD-160 is being used with the new Lox / LCH4 (methane) fuel. Oscillating +-6° and being the head of the RD-161 family. This engine is mounted on the Soyuz M3
-A variant of RD-134 is RD-167 that runs on Lox and methane.
-The RD-169 is again derived from the RD-120 delivering 17,000 kgf.
-The RD-170 and RD-171 were "clusters" of 4 chambers, a common turbo-pump and two gas generators.
-The main difference was that the former could gimbal their engines in one plane, the latter could do it in two planes.
-The RD-172 was more powerful than the RD-171. The RD-173 with four chambers had a turbo-pump and two gas generators, and was destined for the Zenith 3.
“Proton, Cyclon, Zenith and Energia-Buran”
-All vehicles shown in the illustration have engines whose main design is attributed to Glusko. Something amazing.
-The RD-174 of 1995 had 4 chambers running on Lox/ker, and was installed in the first stage of the Angara.
-Now we come to the important RD-180, winner of the American competition to power the Lockheed-Martin Atlas III. This engine was developed between 1993 and 1999. It is built in Russia and the USA. It runs on Lox and kerosene.
-It has hypergolic ignition that is, chemical. The engine is controllable between 50% and 100% of its power. 80% of the components are the same as the RD-170.
-The RD-182 is an RD-120M using Lox and methane, with a gimbal of +-6° delivering 92,000 Kgf. "M" means with LNG and Lox.
-The RD-183 is a small apogee engine with a thrust of 1,000 kgf running on Lox/LCH4 gimballing +-10° in two planes. This engine dates from 1996. The RD-184 is the same project as the RD-183 but with +-20° of gimballing.
“RD-180” (PeT)
-The RD-185 is a larger version of the RD-169
-With six engines from the RD-169 giving 102,000 Kgf, the RD-190 was made. It ran on Lox and LCH4, gimballing +-8° in two planes. It was a 1996 project.
-For the Angara vehicle there was the RD-191 that ran on Lox and kerosene with a thrust of 208,000 Kgf. It was based on the RD-170 and RD-171.
-The methane variant of the RD-191 was the RD-192 with a thrust of 218,000 Kgf.
-The RD-200s were made for sounding rockets. They had a thrust of 1,000 Kgf.
-The RD-210 was used in sounding rockets with 3000 Kgf.
-The RD-211 for long distance witgh a thrust of 65,000 Kgf was replaced by the RD-214.
-Both the RD-212 and the RD-213 were used between 1952 and 1957 on the Buran M40/41 winged missiles.
-The RD-214, widely used in the Cosmos, ran on nitric acid and kerosene, and had a thrust of almost 75,000 Kgf. It was used very much between 1961 and 1977.
-With a thrust of 85,000 Kgf, the RD-215 from 1958 to 1960 ran on nitric acid and UDMH.
-The RD-216 consisted of two RD-215s together in the first stage of the Cosmos. From these years is the RD-217. With three RD-217 engines arises the RD-218, delivering 226,000 Kgf.
“RD-214”
-The RD-219 that was used during 1958-1961 was the impeller of the R-16 missile. It ran on nitric acid and UDMH. The RD-220 was from 1960, and had a thrust of 109,000 Kgf. The RD-221 had a thrust of 114,000 Kgf.
-The RD-222 was the predecessor of the RD-253 and the RD-223, a variant of the -222 that delivered 173,000 Kgf.
-The RD-224 is a cluster of two RD-225s. The RD-225 gives 90,000 Kgf on the R-26 missile.
-The RD-226 was also used on the R-26 in its second stage. This engine was based on the RD-224.
“RD-251” (PiP)
-Between 1960-1965, the RD-250 engines that ran on N2O4 / UDMH were mounted on the R-36 and Tsyklon 2 (Cyclon) vehicles.
-The RD-251 was a cluster of 3 RD-250 engines.
-We have a photograph of this engine, made by Dietrich Haeseler at the NPO Energomash Museum.
-The RD-252 with a thrust of 96,000 Kgf, had two combustors, and was used on the R-36 and Tsyklon 2. It ran on N2O4 and UDMH.
-They are used in the vehicle's upper stages for high altitudes, therefore they have a much larger, longer and wider nozzle.
-The RD-253 gave way to the RD-175, and the RD-254 was the high-elevation version with a thrust of 175,000 Kgf.
-The RD-261 was based on the RD-251 that was mounted on the Tsyklon 3. It delivered 310,000 kgf with 6 chambers. The RD-262 was based on the RD-252.
-With 4 RD-263 engines they made the RD-264 for the R-36M and RS-20A missiles.
-The RD-268 is a modified RD-263. Now we arrive at the largest engine developed in the USSR, the RD-270 with almost 700,000 Kgf of thrust.
-Some information indicates that it runs on N2O4 and UDMH and other that it uses pentaborane.
“RD-270, photo Dietrich Haeseler” (PiP)
-In a certain way, it is the answer to the American F-1, destined to the Chelomei UR-700 lunar vehicle, mounting six of them.
-The RD-273 is an improved RD-263, giving 126,000 Kgf, as well as the RD-274 it is from the RD-264 with 505,000 Kgf (it consists of 4 RD-273 engines).
-As already said, the RD-275 is an improvement of the RD-253 from the 1980's.
-The RD-280 is an experiment with N2O4 and Aerozine 50 (50% of UDMH + 50% of hydrazine). It was produced between 1963 and 1965 for the R-56 missile.
-The first of the RD-301 family (see Energomash) used exotic fuels such as LF2 / Ammonia giving 9,860 Kgf. The RD-302 was similar to the previous one, just like the RD-303. They were built between 1960 and 1969.
-The RD-350 that ran on LF2 / LH2 was made for the study of high-energy fuels.
-The RD-410 was very special. In the 1960s, this engine was tested with nuclear energy and liquid hydrogen. It delivered only 7,000 Kgf. The RD-400 series (such as -401, -403, used U-235 with either ammonia or hydrogen).
“Schematic diagram”
-The RD-500 series used rare storable fuels, and was to be used in higher stages.
-For example, RD-502 for the Protons, used H2O2 and Pentaborane. Its development was between 1960 and 1966. It was experimental and the program was canceled due to the toxicity of the fuels.
-The RD-510 and RD-511 were built between 1965 and 1975, and used H2O2 / CxHy.
-Up to RD-550, the engines were experimental, running on LOX / Beryllium + Pentaborane with 70% hydrazine. They were developed between the years 1963 and 1970. They had only one chamber. The fuel was exotic and very toxic.
“RD-502” (PiP)
-An RD-513 (cluster of 4 engines) was the one that was mounted on the Zenith in its second stage, being an RD-123 the one of the first stage.
“Zenith and two engines”
-The 600 series was to be nuclear again, using hydrogen. The same as the OKB-456's YarD design, nuclear with ammonia and with a thrust of 140,000 Kgf for 500 seconds for the ICBM. The propellant heated in the reactor was ejected by four nozzles.
-The tripropellant RD-701 used LOX / kerosene / LH2, with a thrust of just over 400,000 Kgf. It was intended for the MAKS program, a space vehicle that was to be launched by an Antonov An-225 "Mriya" at an altitude of 8 km. Its development began around 1988 .
“Launching from an airplane”
-The RD-704 was developed in the 1990's, and was a tripropellant as well. It used LOX / Ker. / LH2 with 1 combustor and it delivered 200,000 Kgf.
-These tripropellant engines use two fuels at the same time: first Lox with the dense kerosene in the initial operation, then changing to a more modest thrust but with a greater specific impulse with Lox and the low-density hydrogen.
-Another family of Glushko's hallmark engines was the RLA.
-The RLA-1200 wasdeveloped between 1972 and 1975, and it used Lox / Ker. and had a thrust of 130,000 Kgf with 4 combustors.
-The RLA-300 delivered 325,000 Kgf and the RLA-600 gave 650,000 Kgf.
-A continuación se añade lo aparecido en la revisión número 4 de ésta publicación de fecha 2006/8 “Super” y todavia no integrada. Como un nuevo resumen.
From Appendix 4: A new summery is added.
-Valentin Petrovich Glushko has been, perhaps, the most important designer of liquid fuel rocket engines in the USSR.
“V.P. Glushko”
-Initiator of GDL, which engine range today is included in Energomash.
“Four of the initial engines”
-During the WWII they test rocket engines such as RD-1, RD-2, etc. installed in fighters to increase their speed. (see main text)
-After WWII, they receive German material, documentation and even technical personnel. They start to build the same V-2 engines as RD-100.
-Developments from the RD-100 followed as RD-101, RD-102 and RD-103. They were very similar but increasing in thrust continuously.
“RD-100 and RD-101”
-Below, several motors are inserted whose illustrations have been obtained recently, and whose description is in the main text.
“RD-105/106”
“RD-107”
“RD-108”
“RD-110”
“RD-111”
“RD-119”
“RD-120 and RD-120K”
“RD-120 with frame”
“RD-161 and RD-161P”
“RD-170”
“RD-171M”
“RD-180”
“RD-191”
“RD-214”
“RD-216”
“RD-218”
“RD-219”
“RD-251”
“RD-252”
“RD-253”
“Another RD-253 from Energia”
“RD-264”
“RD-270” (PiP)
“RD-301”
“RD-700”
“RD-701”
“RD-704”
-All engines in this revision are not related in size.
-Glushko died in 1989, so many of those represented here are no longer of his design, but with much to do.
-Energomash follows his style as we can see by the cylindrical-circular combustors, etc., adding its experiences to the previous ones.
-Finally, we can show the Vulkan heavy carrier rocket. As a sample of the Russian philosophy of obtaining great powers based on large engine clusters.
“Energia Vulkan”
-The four central engines of the Vulkan are RD-120s and those that carry the Boosters are RD-179s with 937 tons of thrust in vacuum for more than 300 seconds.
"RD-180 and the impressive turbo-pump"
-We see the turbo-pump installed in the middle of the two engines. It is the closed circuit system, as we see in the following diagram of the fuel system.
“Closed combustion circuit”
Author's note: The information in this summary is from NPO Energomash.
From Appendix 9: Review of a list of engines built by this brand to contrast with the main text.
-11D119 (RD-264), 11D130F (RD-302 LF2), 11D14 (RD-303 LF2), 11D26 (RD-219), 11D43, 11D48 (RD-253), 11D511 (RD-107), 11D511P y PF (RD-107 y RD-117PF), 11D512 y P (RD-108), 11D520 (RD-170), 11D521 (RD-171), 11D614 (RD-216), 14D14 (RD-253).
“RD-219, 11D26” (PiP)
“RD-107, 11D511” (PiP=mw)
“RD-170, 11D520” (PiP=mw)
-Another group of Glushko engines is the 8D: 8D21 (RD-301LF2), RD-420 (RD-270), 8D420M (RD-270M), 8D515 (RD-217), 8D52 (RD-103), 8D52M (RD-103M), 8D71 (RD-103), 8D710 (RD-119), 8D711 (RD-109), 8D712 (RD-218), 8D713 (RD-219), RD-716 (RD-111), 8D720 (RD-106), 8D721 (RD-224), 8D723 (RD-250 y RD-251), 8D727 -K y -P (RD-108), 8D728 (RD-107-), 8D74 -1958, -1959 (RD-107-), 8D74K y PS (RD-107-), 8D75 (RD-108-), 8D75 -1958 y -1959 (RD-108-), 8D75K y PS (RD-108-), 8D76 (RD-107-), 8D77 (RD-108-).
“RD-301, 8D21” (PiP=dh)
“RD-270, 8D420” (PiP=dh)
-Glushko engines with unusual references: ED-140, GDU-10 (RD-109), Glushko C, KS-50 (Lilliput), U102-000, Yard OKB-456, RLA-600, RLA-300, RLA-1200.
-And with official references: RD-1, RD-100, RD-101, RD-102A (RD-3A), RD-103 y -M, RD-105, RD-106, RD-107 y -D, RD-108, RD-109, RD-110, RD-111, RD-112, RD-113, RD-114, RD-115, RD-117 y PF, RD-118, RD-119, RD-120, -M y -K (RD-182), RD-120.01 y .03, RD-123 (RD-134R, RD-146 y RD-120K), RD-134 y R, RD-135, RD-146, RD-160, RD-161, -1 y -2, RD-161-P
“RD-252” (PiP=dh)
“RD-502” (PiP=dh)
Del apéndice 10: Directamente de una publicación rusa el desarrollo de las cámaras de combustión para motores cohetes.
From appendix 10: Directly from a Russian publication, the development of combustion chambers for rocket engines.
“First Russian native design combustors”
-Initially they made the operational German V-2 (A-4) missile engines, which were exact copies in the beginning, and were increased in size, until making the totally spherical chamber of the above illustration.
“ED-140 engine”
-Parallel studies were made with cylindrical combustion chambers that turned out to be of better performance. The ED-140 engine is an example. Since then they are like this, RD-170, RD-180, etc.
“Cutaway of a Russian engine"
From Appendix 11: The following engines have been found:
-The RD-125 from the 70s with one combustion chamber and a vacuum thrust of 130,200 Kgf. It used LOX / Kerosene.
-The RD-150 from the early 70s that used LOX / Kerosene and had a vacuum thrust of 1,500,000 Kgf.
-The RD-181 that used LOX / Kerosene with a vacuum thrust of 426,000 Kgf.
-The RD-501 from the 60s that used H2O2 / B5H9.
-The RD-560 manufactured between 1965 and 1971 and that used the same fuel as the RD-550.
Engines of GLUSHKO
Model: 11D43
Arquitecture:
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: 8D725
Arquitecture:
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: ED-140 (pre RD-107)
Arquitecture:
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
"ED-140"
Model: Glushko C
Arquitecture:
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: KS-50
Arquitecture:
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: Lilliput
Arquitecture:
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: MD-185
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-1, -X3
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
"RD-1Khz"
Model: RD-100
Arquitecture: Rocket engine
Chambers:
Fuels: Alcohol and Lox
Feed System:
Ignition:
Thrust: 31000 Kgf
Weight:
Based on the German V2 rocket engine.
Model: RD-101
Arquitecture: Rocket engine
Chambers:
Fuels: Alcohol and Lox
Feed System:
Ignition:
Thrust: 41000 Kgf
Weight:
Model: RD-102
Arquitecture: Rocket engine
Chambers:
Fuels: Alcohol and Lox
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-103, -M (8D52, -M), -RD
Arquitecture: Rocket engine
Chambers:
Fuels: Alcohol and Lox
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-105 (8D71)
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 64000 Kgf
Weight:
Model: RD-106 (8D720)
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-107, -K, -PS (11D511, -P) (8D728 y 8D74, -K, -PS) (8D76)
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust:
Weight:
"RD-107"
Model: RD-108, -K (11D512, -P) (8D727, -K, -P) (8D75, -K, -PS) (8D7
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust: 102000 Kgf
Weight:
"RD-108"
Model: RD-109 (8D711) (GDU-10
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and UDMH
Feed System:
Ignition:
Thrust: 10300 Kgf
Weight:
Model: RD-110
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust:
Weight:
"RD-110"
Model: RD-111 (8D716)
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust:
Weight:
"RD-111"
Model: RD-112
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and UDMH
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-113
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and UDMH
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-114
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-115
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and UDMH
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-117, -PF (11D511, -PF)
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-118
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-119 (8D710)
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and UDMH
Feed System:
Ignition:
Thrust:
Weight:
"RD-119"
Model: RD-120, -01, -03, -K , -M
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 85000 Kgf
Weight:
"RD-120 with frame"
Model: RD-123 (RD-134R) (RD-146)(RD-120K)
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-124
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 379500 Kgf
Weight:
Model: RD-125
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 130200 Kgf
Weight:
Model: RD-134, -R
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 35000 Kgf
Weight:
Model: RD-135
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / LH2
Feed System:
Ignition:
Thrust:
Weight:
Experimental engine
Model: RD-146 (base RD-120)
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 90000 Kgf
Weight:
Model: RD-150
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-160
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / LCH4
Feed System:
Ignition:
Thrust: 2000 Kgf
Weight:
Model: RD-161, -1, -2,
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 2000 Kgf
Weight:
"RD-161 and RD-161P"
Model: RD-161P
Arquitecture: Rocket engine
Chambers:
Fuels: H2O2 / kerosene
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-167
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / LCH4
Feed System:
Ignition:
Thrust: 36000 Kgf
Weight:
Model: RD-169
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / LCH4
Feed System:
Ignition:
Thrust: 17000 Kgf
Weight:
Model: RD-170 (11D520)
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 804250 Kgf
Weight:
"RD-170"
Model: RD-171, -M (11D521)
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 806250 Kgf
Weight:
"RD-171M"
Model: RD-172
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 847600 Kgf
Weight:
Model: RD-173
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 918 Kgf
Weight:
Model: RD-174
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 806100 Kgf
Weight:
Model: RD-179
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-180
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and UDMH
Feed System:
Ignition:
Thrust: 423400 Kgf
Weight:
"RD-180" (PeT)
Model: RD-181
Arquitecture: Rocket engine
Chambers:
Fuels: Lox and kerosene
Feed System:
Ignition:
Thrust: 426200 Kgf
Weight:
Model: RD-182, -M
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / LCH4
Feed System:
Ignition:
Thrust: 91000 Kgf
Weight:
Model: RD-183
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / LCH4
Feed System:
Ignition:
Thrust: 1000 Kgf
Weight:
Model: RD-184
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / LCH4
Feed System:
Ignition:
Thrust: 1 Kgf
Weight:
Apogee engine
Model: RD-185
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / LCH4
Feed System:
Ignition:
Thrust: 18000 Kgf
Weight:
Model: RD-190
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / LCH4
Feed System:
Ignition:
Thrust: 102000 Kgf
Weight:
Model: RD-191, -M
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / RG1
Feed System:
Ignition:
Thrust: 201600 Kgf
Weight:
"RD-191"
Model: RD-192, -2, -3, -S
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / LCH4
Feed System:
Ignition:
Thrust: 218000 Kgf
Weight:
Model: RD-1CH2, -X3
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-1Khz
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-2
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust: 652 Kgf
Weight:
652 Kgf. during 200 seconds.
Model: RD-200
Arquitecture: Rocket engine
Chambers:
Fuels: HNO3 / TM114
Feed System:
Ignition:
Thrust: 1000 Kgf
Weight:
Model: RD-210
Arquitecture: Rocket engine
Chambers:
Fuels: HNO3 / TM114
Feed System:
Ignition:
Thrust: 3000 Kgf
Weight:
Model: RD-211
Arquitecture: Rocket engine
Chambers:
Fuels: AK20 / TM185
Feed System:
Ignition:
Thrust: 65500 Kgf
Weight:
Model: RD-212
Arquitecture: Rocket engine
Chambers:
Fuels: AK271 / TM185
Feed System:
Ignition:
Thrust: 63600 Kgf
Weight:
Model: RD-213
Arquitecture: Rocket engine
Chambers:
Fuels: AK271 / TM185
Feed System:
Ignition:
Thrust: 77000 Kgf
Weight:
Model: RD-214 (8D77)
Arquitecture: Rocket engine
Chambers:
Fuels: AK271 / TM185
Feed System:
Ignition:
Thrust: 74500 Kgf
Weight:
"RD-214"
Model: RD-215
Arquitecture: Rocket engine
Chambers:
Fuels: AK271 / UDMH
Feed System:
Ignition:
Thrust: 8500 Kgf
Weight:
Model: RD-216 (11D614), -M
Arquitecture: Rocket engine
Chambers:
Fuels: AK271 / UDMH
Feed System:
Ignition:
Thrust: 176300 Kgf
Weight:
"RD-216"
Model: RD-217 (8D515)
Arquitecture: Rocket engine
Chambers:
Fuels: AK271 / UDMH
Feed System:
Ignition:
Thrust: 88200 Kgf
Weight:
Model: RD-218 (8D712)
Arquitecture: Rocket engine
Chambers:
Fuels: AK271 / UDMH
Feed System:
Ignition:
Thrust: 264500 Kgf
Weight:
"RD-218"
Model: RD-219 (11D26) (8D713)
Arquitecture: Rocket engine
Chambers:
Fuels: AK271 / UDMH
Feed System:
Ignition:
Thrust: 90100 Kgf
Weight:
"RD-219"
Model: RD-220
Arquitecture: Rocket engine
Chambers:
Fuels: AK27P / UDMH
Feed System:
Ignition:
Thrust: 109600 Kgf
Weight:
Model: RD-221
Arquitecture: Rocket engine
Chambers:
Fuels: AK27P / UDMH
Feed System:
Ignition:
Thrust: 114100 Kgf
Weight:
Model: RD-222
Arquitecture: Rocket engine
Chambers:
Fuels: AK27P / UDMH
Feed System:
Ignition:
Thrust: 166700 Kgf
Weight:
Model: RD-223
Arquitecture: Rocket engine
Chambers:
Fuels: AK27P / UDMH
Feed System:
Ignition:
Thrust: 173200 Kgf
Weight:
Model: RD-224 (8D721)
Arquitecture: Rocket engine
Chambers:
Fuels: AK27P / UDMH
Feed System:
Ignition:
Thrust: 181400 Kgf
Weight:
Model: RD-225
Arquitecture: Rocket engine
Chambers:
Fuels: AK27P / UDMH
Feed System:
Ignition:
Thrust: 90700 Kgf
Weight:
Model: RD-226
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-250 (8D723)
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 90000 Kgf
Weight:
Model: RD-251 (8D723)
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 270000 Kgf
Weight:
"RD251"
Model: RD-252
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 92000 Kgf
Weight:
"RD-252"
Model: RD-253 (11D48) (14D14) (UR-700)
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 178100 Kgf
Weight:
"RD-253"
Model: RD-254
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 175000 Kgf
Weight:
Model: RD-261
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 309400 Kgf
Weight:
Model: RD-262
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 96000 Kgf
Weight:
Model: RD-263, -F
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 117800 Kgf
Weight:
Model: RD-264 (11D119)
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 461000 Kgf
Weight:
"RD-264"
Model: RD-268
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 126000 Kgf
Weight:
Model: RD-270, -M (8D420, -M)
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 685000 Kgf
Weight:
Model: RD-273
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 126300 Kgf
Weight:
Model: RD-274
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 505300 Kgf
Weight:
Model: RD-275 (RD-253)
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / UDMH
Feed System:
Ignition:
Thrust: 178000 Kgf
Weight:
Model: RD-280
Arquitecture: Rocket engine
Chambers:
Fuels: N2O4 / AZ50
Feed System:
Ignition:
Thrust: 12000 Kgf
Weight:
Model: RD-3, -3A (RD-102)
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Assembly of 3 RD-1 engines with common turbo-pump and external ignition.
Model: RD-301 (8D21)
Arquitecture: Rocket engine
Chambers:
Fuels: LF2 / NH3
Feed System:
Ignition:
Thrust: 9800 Kgf
Weight:
"RD-301"
Model: RD-302 (11D130F)
Arquitecture: Rocket engine
Chambers:
Fuels: LF2 / NH3
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-303 (11D14)
Arquitecture: Rocket engine
Chambers:
Fuels: LF2 / NH3
Feed System:
Ignition:
Thrust: 10000 Kgf
Weight:
Model: RD-350
Arquitecture: Rocket engine
Chambers:
Fuels: LF2 / LH2
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-4
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-401
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-403
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-410
Arquitecture: Rocket engine
Chambers:
Fuels: Nuclear
Feed System:
Ignition:
Thrust: 7000 Kgf
Weight:
Model: RD-501
Arquitecture: Rocket engine
Chambers:
Fuels: H2O2 / B5H9
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-502
Arquitecture: Rocket engine
Chambers:
Fuels: H2O2 / B5H9
Feed System:
Ignition:
Thrust: 10000 Kgf
Weight:
Model: RD-510, -T
Arquitecture: Rocket engine
Chambers:
Fuels: H2O2 / CxHy
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-511
Arquitecture: Rocket engine
Chambers:
Fuels: H2O2 / CxHy
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-513
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-550
Arquitecture: Rocket engine
Chambers:
Fuels: H2O2 / 70% N2H4 + 30% beryllium
Feed System:
Ignition:
Thrust: 10000 Kgf
Weight:
Model: RD-560
Arquitecture: Rocket engine
Chambers:
Fuels: H2O2 / 70% N2H4 + 30% beryllium
Feed System:
Ignition:
Thrust:
Weight:
Model: RD-600
Arquitecture: Rocket engine
Chambers:
Fuels: Nuclear
Feed System:
Ignition:
Thrust: 140000 Kgf
Weight:
Model: RD-700
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
"RD-700"
Model: RD-701
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / queroseno / LH2
Feed System:
Ignition:
Thrust: 408500 Kgf
Weight:
"RD-701"
Model: RD-704
Arquitecture: Rocket engine
Chambers:
Fuels: Lox / queroseno / LH2
Feed System:
Ignition:
Thrust: 200000 Kgf
Weight:
"RD-704"
Model: RKDS-100
Arquitecture:
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: RLA-1200
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust: 130000 Kgf
Weight:
Model: RLA-300
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust: 325000 Kgf
Weight:
Model: RLA-600
Arquitecture: Rocket engine
Chambers:
Fuels:
Feed System:
Ignition:
Thrust: 650000 Kgf
Weight:
Model: U102-000
Arquitecture:
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight:
Model: YaRD OKB-456 (nuclear)
Arquitecture:
Chambers:
Fuels:
Feed System:
Ignition:
Thrust:
Weight: