NPO ENERGOMASH named after academician V.P.Glushko - leading enterprise on development of powerful liquid propellant rocket engines.

            In an initial phase of the activity (1929-1938) the first in our country liquid propellant rocket engines of ORM (experimental rocket motors) series were developed here, data about which are presented in the first part of the table.

               In the second and third parts of the table data on oxygen engines and engines on storable components of propellant (nitric acid, nitric tetroxide) are presented. The basic engines from the second and third parts of the table are the main propulsion units reliably operated and continuing to serve in structure of space launch-vehicles and military ballistic missiles. Practically all space objects of our country have been put into space by engines of NPO ENERGOMASH development.

               In the fourth part of the table data on engines on various components of propellant (fluorine, nuclear, hydrogen peroxide, tri-propellant) are presented. They show breadth of search at a choice of new ways of development of advanced engines.

            Following abbreviations are applied here: ОИ - fire tests, сер. - serial production, ОСИ - fire stand test (in structure of a stage), г. – fuel, гидравл. – hydraulic, гос. – state, зем. – sea level, испыт. – tests, КР – wing rocket, не изгот. – not produced, не испыт. – not tested, о. – oxidizer, пр-во – production, пуст. – vacuum, расчет. – analysis value, р-р – solution, ст. – stage, уд. – specific, экспер. – experimental.

            In NPO ENERGOMASH it is accepted and it is used following symbols of LPRE: oxygen LPRE - class RD-1ХХ; storable (nitric acid, nitric tetroxide) LPRE - class RD-2ХХ; fluorine LPRE - class RD-3ХХ; nuclear rocket engines - class RD-4ХХ; hydrogen peroxide LPRE - class RD-5ХХ; nuclear powerplants - class RD-6ХХ; tri-propellant LPRE - class RD-7ХХ. About 60 powerful LPRE of NPO ENERGOMASH development have been passed in a serial production and operated or continue to be operated in structure of ICBM and space LV.

               Part 1. Engine of ORM family. First column – designation of engine, second column – propellant (oxidizer/fuel), third column – thrust (sea level, kgf), fourth column – specific impulse, sec, fifth column – pressure in combustion chamber, kgf/cm², sixth column – mass, kg, seventh column – time of development, last column – destination and status.

               Part 2. Oxygen engines. Part 3. Storable propellant engines (nitrogen acid, nitrogen tetroxide). Part 4. Engines on different propellant (fluorine, nuclear, hydrogen peroxide, tri-propellant). First column – designation and index of engine, second column – propellant (oxidizer/fuel), third column – thrust (sea level/vacuum, tf), fourth column – specific impulse, sea level/vacuum, sec, fifth column – pressure in combustion chamber, kgf/cm², sixth column – mass, dry/filled, kg, seventh column – dimensions, height/diameter, mm, eighth column - time of development, last column – destination and status.

The basic engines of NPO ENERGOMASH development (tables present in Russian now)