(See Kosberg)

Konstruktorskoe Buro Khimavtomatiki, which is also known by the initials KBKhA builds vehicles and rocket engines.

They built the 2nd state engine for the Russian Molniya-M rocket. It is an RD-461 (LOX / RP1) liquid fuel engine.

The RD-461 is also used in the 2nd stage on the Soyuz U.

-The RD-0210 is installed on the Proton-M, but running on N204 / UDMH fuels. As on Proton K, with a cluster of four of them in the 2nd stage and one in the 3rd.

-Before it was the OKB Kosberg (see). Emphasizing:

-The monopropellant D-1 OT.152 (isopropylnitrate) was cancelled when it exploded during the first test.

-The D-7 identical to the previous one and was mounted on the Toropov missile.

-The RD-0109 on Vostok 3rd stage, Blok E-Vostok, etc (RD-448 and 8D719) with LOX/Ker RG1.

-The RD-0110 (RD-461) used Lox/ker T1. It was installed on Soyuz, Molniya, R-9, etc.

-The RD-0212 was installed on the 3rd stage of the Proton. It was a cluster with RD-0213 and RD-0214 engines.

-The RD-0215 ​​was planned for the first stage of the UR-700.

-The RD-0216 (from 1974 to 1991) on the UR-100 /K / RS-10 and SS-11 first stage.

-The RD-0217 is a modified RD-0216.

-The RD-0221 on the upper stage of the Mishin.

-The RD-0225 for maneuvering of the Almaz space station.

-The RD-0228 on the R36M, SS-18, 2nd stages. This engine is composed of 1 x RD-0229 and 4 x RD-0230.

“RD-0225 (11D24)”

-The RD-0229 is the main engine of the RD-0228. The -M version uses LOX / LNG or liquefied natural gas (Methane).

-The RD-0230 is a part of the RD-0228 cluster.

-The RD-0231 has been mounted on the Granit spacecraft.

-The RD-0233 was used on the first stage of the UR 100N (RS-18).

-The RD-0234-Kerosene used LOX / Ker.

-RD-0234-Methan used LOX / LNG instead of N2O4 / UDMH.

-The RD-0235 is a version with high altitude nozzle derived from the RD-0217 for the UR 100N.

-RD-0236 is a vernier thruster for the RS-18 (SS-19) and UR 100N in 2nd stages.

-RD-0237 for the same rockets but in the 3rd stage.

-The RD-0242 uses N2O4/UDMH.

-RD-0242-Kerosene, using LOX/Kerosene.

-RD-0242-M, variant using MMH instead of UDMH with the N2O4.

-The RD-0242-M1 was an export model for the western market.

-The RD-0243 consisted of one RD-0244 and four RD-0245 engines.

-RD-0244 is a part of the RD-0243.

-RD-0245 is a part of the RD-0243.

From Appendix 6: After a visit to the Paris Air Show this year, 2009, we have collected information on some of the engines of this brand, the “Konstruktorskoe Buro Khimavtomatiki”.

“KBKhA logo”

“Poster achieved at the 2009 Paris Air Show”

-KBKhA builds the same engines as Energia, today Energomash.

-It is identified through a “0” added to the same reference in front of the number -and after the normal RD-.

-We start with a review, this time with illustrations that were not published in the main text because they were not available.

-The RD-0105 was used in the third stage of the LV Luna that served to launch terrestrial satellites and also photographed the moon surface, including its hidden face.

“RD-0105”

-For the P-9A intercontinental ballistic missile, they used the RD-0106 open cycle engine with four chambers, a cluster. It was used between 1959 and 1961.

“RD-0106”

-The RD-0107, RD-0108 and RD-0110 engines have been used on the third stages of the Molniya, Voskhod and Soyuz launchers for launching satellites and space vehicles, emphasizing those of the Kosmos, Progress, Mars, Venera series.

“RD-0107”

“RD-0108”

-From the basic RD-0110 came the RD-0110MA, which uses liquefied natural gas (with LOX). It was first tested with methane gas.

“RD-0110MA”

-The RD-0109 was a derivative of the RD-0105.

“RD-0109”

-The RD-0120 mounted on the Energia transport rocket was developed between 1976 and 1990. It was used in the launch of the Buran, in the few cases there were.

-The engine runs on LOX/LH2. It delivers 1962 kN of thrust in a vacuum.

“RD-0120”

-The RD-0124 and RD-0124A were also for the third stage of the Soyuz 2-16, and the first and second stage on the “Angara” LV (Launch Vehicle).

-Both use Kerosene and Liquid Oxygen and 294 kN.

-The RD-0126 has a Laval nozzle and uses liquid oxygen and hydrogen.

“RD-0126”

-The rare RD-0126E surprises with its combustion system, called expansion-deflection, as we see below.

“RD-0126E”

-It also uses liquid oxygen and hydrogen. The RD-0146 was to be used in the upper stages of the Angara, Soyuz 2-3 and Proton.

“RD-0146”

-Since 2006, work is being done on the RD-0162, known as the "Volga", with 250 tf of thrust and these engines were used in the first stages of Russian MTKS.

“The Volga (RD-0162)”

-The Booster engine for the AA 5B11 guided missile with 59 kN of thrust is the RD-0200.

-And the RD-0203 and the RD-0204 are for YP-200 intercontinental ballistic missiles. For the 2nd stages there is the RD-0205 system, which consists of a RD-0206 main engine and several small gimballing RD-0207s.

“RD-0203, RD-0204”

“The RD-0206 and the small RD-0207 engines”

-The RD-0208 and RD-0209 are the main engines for the Proton launch vehicle.

-The RD-0208 and RD-0209 give 570 kN of vacuum thrust running on N²O⁴ and NDMH.

“RD-0208, RD-0209”

-The RD-0210, RD-0211, and RD-0213 deliver similar power, together with the RD-0214, of only 31 kN, for the upper stages.

“RD-0210, RD-0211”

“RD-0212”

-The RD-0212 is an engine assembly consisting of a RD-0213 main engine and 4 of the so-called steering ones for the RD-0214 model.

The RD-0216 and RD-0217 were used for the intercontinental ballistic missile PC-10. They were developed between 1963 and 1966.

“RD-0216, RD-0217”

The RD-0225, with small size and thrust - almost 4 kN - was made for the Proton launcher that carried the Almaz space station.

“RD-0225”

-For the PC-20 missile series there are two groups of composite engines such as RD-0228 and RD-0255. The former is composed of the RD-0229 main engine and the small RD-0230 vernier engines.

“RD-0228”

“RD-0255”

-The PC-18 missiles were powered by the RD-0233 and RD-0234.

“RD-0233 y RD-0234”

-The RD-0233, RD-0234 engines operate in a closed cycle and were mounted in the first stage of the missile.

-The RD-0235 as the main engine and the gimballing RD-0236 verniers were in the second stage.

-The RD-0236 and the RD-0237 operate with an open cycle. The latter is used in the third stage.

“RD-0235 y RD-0236”

“RD-0237”

-For the "Sea-Launch" joint-project with the West, Khimavtomakivy built their RD-0242 for the 3M25 vehicle.

-In the photo below we see it with a trimmed nozzle. The first launch was made in May 1980.

“RD-0242”

-The RD-0243 is a cluster composed of a main RD-0244 and the gimballing RD-0245. They were intended for the PCM-54 missile.

“RD-0243”

-We now have the nuclear rocket engine project for advanced launch vehicles and deep space travel.

-It is the RD-0410 that is based on the development of the physical characteristics of Neutrons and uses gaseous hydrogen.

-It has a thrust of 35 kN, giving the jet a thermal energy of 196 MW. The assembly has a height of 3.5 meters.

“RD-0410”

-The GDL RD-0600 is a test engine using lasers and dynamic gases such as oxidizer air, carbon oxide in the gaseous state as fuel and nitrogen gas as ballast. The radiant power is 100 kW.

“RD-0600”

-Returning to the more classic rocket engines, there is the RD-0750 for advanced launch vehicles (although its first test was made in 1993). In fact it is a development based on the RD-0120.

-It could run in two modes, considering it a three-fuel. The first mode with liquid oxygen, kerosene and 6% hydrogen. In the second mode only liquid oxygen and hydrogen.

“RD-0750”

-KBKhA has tested Scramjet (see) type rocket engines, such as the GPVRD-58L. This was done in cooperation with CIAM (TsIAM) and P.I. Baranov. For more than 6 Mach.

“Scramjet and test rocket”

-Another model under experimentation is the engine with a adjustable nozzle or "throat" (like German WWII turbines). They run on liquid oxygen and hydrogen and were designed with an attempt to regulate the thrust, between 939 kN in Ha mode and 922 kN in HT mode. The maximum vacuum thrust is 1,864 kN.

-Below we show a schematic drawing for the principle of the central adjustable needle in the chamber that, as we see, moves to decrease the throat section of the Laval type nozzle.

"Scheme showing the displacement of the needle"

-Now a plasma rocket engine started by laser and known as LRD. It is made in collaboration with Kheldish and NII NI, since 2002 and identified as LRD.

“LRD laser engine”

-And below an interesting poster describing a part of the RD-170 family.

“RD-170 family and derivatives”

-On the left the RD-170 and its similar RD-171. From them comes the RD-171M, the upper one.

-At the bottom is the RD-180 and to the right of the RD-191.