The names and sites of our company have repeatedly changed, but main subjects - development of powerful liquid propellant rocket engines – were invariable ones.

 

MILESTONES OF HISTORY of NPO ENERGOMASH

   History of NPO ENERGOMASH is inseparably linked with V.P.Glushko's creative biography.

May, 15th 1929 - the creation of group under leadership of V.P.Glushko on development of electric and liquid rocket engines in structure of Gasdynamic laboratory (GDL) in Leningrad.

September 1933 - continuation of works in structure of the Reactive scientific research institute (RNII) in Moscow, created on the basis of GDL and Moscow group of studying of reactive movement (MosGIRD).

1939-1940 - work in group of 4-th Special department of People's Commissariat of Internal Affairs at Tushino' aviaengine-building factory №82.

1940-1944 - work in OKB of 4-th Special department of People's Commissariat of Internal Affairs at the Kazan plant №16.

1944 – the creation of Experimental design bureau of special engines (OKB-SD) in Kazan under leadership of V.P.Glushko.

1946 – the relocation of OKB-SD in Khimky and the creation of  Experimental-design bureau №456 (ОКB-456) on development of powerful LPRE in Khimky, Moscow area, later received the modern name - NPO ENERGOMASH named after academician V.P.Glushko.

Academician Valentin Petrovich Glushko - the founder of domestic liquid rocket engine development was the founder and permanent head of NPO ENERGOMASH till 1974.

Since 1974 he was head of NPO "Energia" into which structure since 1974 till 1990 Design Bureau Energomash and Experimental plant ENERGOMASH have entered.

 

Leningrad university' student engaged degree thesis V.P.Glushko has been invited in GDL for realization of the ideas stated by him in a special part of the degree project under the name "Metal as explosive". As a result of works of group under Glushko leadership the first-ever electrothermal rocket engine has been created, the patent for a design of such rocket engine is received. But from the beginning of 1930 the basic attention has been devoted to development of LPRE.

 In 1930-1931 in GDL under Glushko leadership the first in the USSR liquid rocket engines - ORM (experimental rocket motor), ОRM-1 and ОRM-2 - have been developed and produced. In 1931 47 bench tests of experimental ORM and ORM-1 LPRE are conducted.

There were works not only on development of specific designs, but also ways for advance designs were investigated. For the first time cardan mount of engine with pump units and a number of other ideas have been offered. For the first time nitric acid and a number of other substances are offered and are investigated in the further as rocket propellant by Glushko.

In 1932 designs of experimental LPRE (from ОRM-4 up to ОRМ-22) for research of type of ignition, a method of start and systems of mixture have been developed and tested at test on various components of propellant.

In 1933 a number of engines from ОRM-23 up to ОRM-52 with pyrotechnic and chemical ignition have been developed and tested at the stand, design of TPU with centrifugal pumps also has been developed.

During from 1934 till 1938 the department under leadership of V.P.Glushko has developed and has tested engines from ОRM-53 up to ОRM-102. ORM-65 engine for RP-318-1 rocketglider and a cruise missile 212 was the best domestic engine of this time.

Within the Second World War designs of airplane LPRE - accelerators for fighting aircraft have been created: RD-1, RD-1KhZ with thrust of 300 kg, RD-2 with thrust of 600 kg, experimental three-chamber engine RD-3 with thrust of 900 kg.

 

 

 

These engines have passed about 400 start-ups on airplanes PE-2R, LA-7R and 120R, Як-3, SU-6 and SU-7 of V.M.Petljakov, A.S.Lavochkin, A.S.Yakovlev, P.S.Sukhoy designs. RD-1 and RD-1KhZ engines have passed the state tests, reports on which have been approved by I.V.Stalin. From 1944 RD-1 engine and from 1945 RD-1KhZ engine have been started in a serial production.

In June, 1945 the group of workers of OKB-SD has been directed to Germany for studying of German trophy technics. Acquaintance to German experience of creation of А-4 (V-2) rocket and comprehension of necessity to have similar arms in Red Army promoted that in rather short terms the governmental decree about creation of Special Committee on Reactive technics was accepted. Putting into effect this decision a number of the enterprises, including ОКB-456 on development of powerful LPRE, have organized.

In the end of 1946 ОКB-456 has located in Khimky on a place of a former aviation factory №84 which chief-pilot was V.P.Chkalov. In the beginning of war this factory was evacuated to Tashkent where it exists and till now. On the remained industrial facilities within war a repair aviation enterprise (plant №456) for front aircraft has organized.

For short term buildings of engine manufacture have been constructed, stands for fire tests of engines and their main units are built.

The decision to reproduce the engine of a German rocket and then to move further was accepted. RD-100, created for R-1 rocket, is the reproduced copy of the German engine made of domestic materials and on domestic technology.

A little more powerful on thrust RD-101 and RD-103 engines for R-2 and R-5М rockets accordingly are created with modernization of RD-100. By some design improvements on cooling, thermal protection and strenghthening it was possible to increase pressure and temperature in the chamber, having increased thus concentration of fuel. Changes have undergone many systems and elements of LPRE.

The decision on the termination of development on the basis of a design of German engines and speeding up of works, which were conducted in parallel on experimental chamber KS-50 and AD-140 (thrust up to 7 tons) with the purpose of definition of an opportunity of increase of pressure and temperatures of gases in the combustion chamber, was accepted. The new chamber has appeared long efficient at temperatures up to 4400 K of high pressure gas. The opportunity of use in engines of highly effective components of propellant has opened. Such design and technology of its manufacturing began to be applied widely on all subsequent development of NPO ENERGOMASH and in other design bureau of our country.

In 1957 all world has learned about successful flights in the USSR the first intercontinental missile R-7 which have soon put into orbits the first satellites of Earth. At first and second stages of "Vostok" LV by means of which then start of the first satellites and the first manned flight into space have been carried out,  RD-107 and RD-108 four-chamber oxygen-kerosene engines with steering chambers for control of a rocket flight direction are installed. Multichambers has allowed to reduce essentially length of the engine that has led to reduction of weight of a rocket. Besides this decision has allowed to simplify technological development of these combustion chambers, and also to lower dimensions of industrial-process equipment, necessary for their manufacture. The principle of multichambers continues to be used widely in many new LPRE of NPO ENERGOMASH.

 

 

President of the USA D.Kennedy in the special message of May, 25th,61 “About the major goals of the country” wrote to the Congress:“We became witnesses of that the beginning to achievements in space was based by Soviet Union owing to powerful rocket engines available it.

 It has provided to Soviet Union the leading role... ”.

 

                                    

                  KS-50                                                                                                                                                      AD-140

 

                                  

		RD-107 and RD-108 engines have been developed in 1954-57. They and their modernized variants work in structure  of space launch-vehicles which put into orbits artificial satellites of the Earth and the Moon, space vehicles for research of solar system. They reliably provide and today fullfilment of the Russian space program of manned flights.
RD-107	RD-108

    

                                 

                                                                                                                                                           

                                                             

Launch of "Souyz"LV

Souyz LV transportation     In the end of 90th years - the beginning of new century works on modernization of engines for "Souyz" with new mixing head (RD-107А and RD-108А) are conducted. Since May 2001 these engines are used for launches of "Progress" cargo vehicles and since October 2002 - manned "Souyz" LV.

                                                                                                                        

 Now works on introduction of system of chemical ignition instead of pyrotechnic are conducted. 12 fire tests for 2 engines with chemical ignition has conducted, full readiness for carrying out of certification and flight tests of new improved engines.

In parallel with these works NPO ENERGOMASH has conducted development of engines on storable propellant for use in missiles. In 1952-57 nitric acid LPRE RD-214, begun line of powerful LPRE on high-boiling components of propellant, has been developed.

 

RD-214	RD-216
RD-218	RD -219

 

 

 

 

 In 1958-61 RD-216, RD-218 and RD-219 engines have been developed for the first and second stages of missile R-16 and one of variants of "Cosmos" LV, operated on nitric acid and UDMH. In 1961-65 six-chamber engine RD-251, consisting (as well as RD-218) from three two-chamber blocks, has been developed. This engine operated on nitric tetroxide and UDMH. RD-252 for the second stage had one block. As a result the problem of creation during short time of powerful multichamber propulsion units on storable components of propellant has been solved by application of block schemes of engines with the maximal unification of their elements. Engines of last development of this series promoted the maximal readiness of missiles on start which could be in the filled condition for many years.

 

                                                                      

     

 

 

 

 

 

 

 

 

 

 

 

 

 

 

                     RD-251                                                   RD-252

 

 The further increase of a specific impulse of engines demanded growth of working pressure in combustion chamber that was limited to losses on a drive of turbopump unit. Final decision of a problem have found in new scheme of LPRE: preburner' gas exhausted from turbine has afterburned in the main combustion chamber at mixture with missing component of propellant. Achievement in the combustion chamber the pressure in some hundreds atmospheres has allowed to create also engines of the big thrust with essentially reduced, in comparison with former, dimensions.

        RD-253  

 

 

In 1961-65 creation of RD-253 engine for "Proton" LV was big practical achievement. It is the most powerful single-chamber LPRE, operating on storable components of propellant. For the first time in the world so powerful engine has been produced under the scheme with afterburning of oxidizer-rich gas that has considerably increased efficiency of the engine. Pressure in the combustion chamber was 150 atm. Six  RD-253 engines reliably work in structure of first stage of "Proton" LV, providing successful flights of space vehicles "Moon", "Venus", "Mars" and others, and also orbital space stations " Salut " and "Mir", elements of ISS.

In the middle of 90th years modernization of this engine for use in structure of "Proton-M" LV has conducted. New updating engine has designation RD-275 (14D14). Thrust of the engine has been increased by 7,7 % owing to increase in pressure in the combustion chamber that allows to increase weight of a payload by 600 kg. First launch of "Proton" LV with RD-275 engines took place in October 1995.

       

 

         

"Proton" LV transportation	Launch of "Proton" LV

 

Kamsky branch in 2001 has started development of RD-275M (14D14M) engine - forced on 5,2 % on thrust updating of serial engine RD-275. Such increase of thrust of the engine allows to increase weight of the payload put into a stationary orbit by 150 kg. In 2002-2003 the design and technological documentation on RD-275M engine was issued, 4 fire tests of 3 development RD-275M engines with an running time 735 sec had conducted. On May, 4th 2005 the program of interdepartmental tests of 3 engines RD-275M has been successfully completed. First launch of "Proton-M" LV with new updated engines RD-275M (14D14M) took place July 7th, 2007.

                    

RD-264	RD-268

         In next years the further development was received with propulsion units with the closed cycle on storable components of propellant which have been created for military missiles. RD-264 and RD-268 engines have been developed and installed on modern perfect missiles (including RS-20 or R-36М, designation of NATO - SS-18 or Satan). Pressure in the combustion chamber of RD-268 makes 230 atm.

                               

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

                                  

                                             RD-120                                                         Launch of "Zenit 3SL"

 

 In 1985 creation of the single-chamber RD-120 engine intended for second stage of "Zenit" LV, capable to put into a near Earth orbit a payload at weight up to 12 tons, has been completed. Significant reserves of working capacity of the basic units and the engine as a whole have allowed to create on its basis forced on 10 % on thrust modification with thrust 93 tons and with guarantee reserve in 5 % and to receive its resource on an operating time of one engine up to 4260 sec, and on number of start ups - up to 19, that allows to consider RD-120 engine and as a basis for creation of the reusable engine. These works on modernization of the engine have been conducted in 2001-2003. 4 engines have passed 28 fire tests with running time 8135 sec. The first launch of "Zenit" LV with forced engine RD-120 under the «Sea Launch» program is successfully conducted in June 2003.

 

Modifications of this engine with shortened nozzle and cardan mount or with use of steering chambers for thrust vector control can be used at the first stages at modernization of existing LV and also at creation of new LV of small and middle classes.   

                                                                                   

Qualitatively new step in creation LPRE for new generation of LV became development of RD-170 engine and its updating RD-171 for the first stages of rocket - space complex “Energia - Buran” and  "Zenit" LV accordingly. The most powerful in the world four-chamber RD-170 LPRE possesses the highest level of parameters and characteristics for engines of the given class, operates on ecologically clean components of propellant: liquid oxygen and kerosene. The engine is intended for reusable operation and has certified for 10 times uses. One of engines has been tested on fire stand up to 20 times. The engine is characterized by high reliability of functioning at all operation phases, repairability and controlability and has the big reserve on a resource (not less than 5). The special system of diagnosing of afterflight conditions of the engine hardware is developed. The special technology of interflight processing of the engine for preparation of the engine for new flight or test is mastered. Thrust vector control of the engine is carried out owing to creation of unique bellows unit of chamber gimballing, working in a zone of high-temperature gas flow. On set of the power and operational characteristics this engine has no domestic and foreign analogues.

 

 

 

                              

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

  

                            RD-170                                                                     RD-171М

 

First launch of "Zenit" LV with RD-171 engine has been carried out in April, 1985. In 1987 and 1988 launches of "Energia" LV with RD-170 engines took place. Since 1999 operation of RD-171 engines proceeds and in structure of «Zenit 3SL» LV under  «Sea Launch» program.

Works on modernization of engine RD-171 for use in «Sea Launch» program have been continued per 2003-2004. Certification of RD-171M engine was completed on July, 5th 2004 - 8 tests at duration 1093,6 sec, and last test (over the plan) - on a mode of 105 % had conducted on the certified engine. First serial production RD-171M engine has delivered to Ukraine on March, 25th 2004 after check-technological test at duration 140 sec.

First launch of “Zenit3SL” LV with RD-171M engine took place February 15, 2006. Now RD-171M engines are used in Land Launch program and Federal Space program also.

 

RD-180	Fire test of RD-180 in USA	RD-180 in a stage

                                                     

 

 

 

 

 

 

 

 

 

 

 

 

Engines which are developed on the basis of four-chamber RD-170 engine have a plenty of attractive features and advantages as they are based on well proven designs of units and elements of the existing engine. The project of two-chamber RD-180 engine became in January, 1996 the winner of competition on development and delivery of engines for modernized “Atlas III” LV of Lockheed Martin (USA). Development of RD-180 was conducted in cooperation with Pratt&Whitney (USA) with which NPO ENERGOMASH in 1992 has signed the Agreement on joint marketing and licensing of engines of NPO ENERGOMASH in USA, and in 1997 has created joint venture RD AMROSS on marketing and realizations of RD-180. Fire tests of RD-180 engine are begun in November, 1996. The first launch of US “Atlas 3А” LV took place on May, 24th, 2000.

First launch of “Atlas 5” LV with RD-180 engine took place August 21, 2002. More 50 serial production RD-180 engines have delivered in USA (at June, 2011), 32 launches of “Atlas 3” and “Atlas 5” have conducted (at June, 2011).

 

 

                         

Near "Atlas" LV                  Launch of "Atlas 3" LV                                 Launch of "Atlas 5" LV

 

In NPO ENERGOMASH development of single-chamber RD-191 LPRE for family of new Russian "Angara" LV is conducted. The engine is based also on a design of RD-170 engine. RD-191 engine represents single-chamber LPRE with vertically located TPU. Within 1999 the design documentation has been issued, in 2000 there is begun autonomous development of units of RD-191 engine, preparation to manufacture was completed. In May 2001 first development engine RD-191 was assembled. The first fire test of RD-191 engine has conducted in July 2001.

3 fire stand tests of RD-191 engine in composition of first stage (URM-1) have conducted successfully in 2009. Interbranch tests of RD-191 engine were completed successfully in May, 2011. Serial production engines delivery has began.

 

Baikal     Angara" LV

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

                

 

 

     

 

 

            RD-191                                                  RD-191 at the stand

 

Projects of three-propellant two-mode LPRE of RD-700 family stimulate special interest among experts of the space industry of all world. Such engines provide consecutive work: first on I mode - on three components (oxygen - kerosene - hydrogen) with the maximal thrust, and then on II mode - on two components (oxygen - hydrogen) with the maximal specific impulse. It is provided reusable (up to 15 times) operation of the engine. Two-chamber RD-701 engine has been intended for aerospace system MAKS, and single-chamber RD-704 engine can be a basis for realization of the perspective concept of an single-stage LV with vertical launch and landing.

NPO ENERGOMASH has conducted tests of experimental three-propellant LPRE which mixing head contains 19 injectors developed for chamber of basic RD-704 engine. For the first time in history of liquid rocket engine development an opportunity of combustion of three components in one fire space with achievement of high efficiency of burning had been confirmed by experimental researches that proves a principal opportunity of creation of new generation of LPRE.

 

 

 

 

                  

          

                                      

                                            

 

 

                                        

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

    

 

                            RD-701                                                                    RD-701 in a tail section of the orbital plane

 

 

         In NPO ENERGOMASH works on research of the concept of the engine of a new direction - with the closed contour of a drive of the turbine - are conducted. Realization of such scheme of LPRE can lead to reception of significant benefits in comparison with existing LPRE of the open or closed schemes.

NPO ENERGOMASH is also leading enterprise in the field of development of continuous chemical lasers.