DEVELOPMENTS OF LRE FOR LAUNCHERS

For the first time at Keldysh Research Center the high efficiency of LRE working on generator gas staged combustion cycle was substantiated and experimentally demonstrated. Further in the branch the engines of such configuration with high parameters were developed for sustainer and booster stages. They have no analoga in the world practice (engines for launchers: "Proton", "Zenit", "Energia" and others).

Currently the works on creation of the new-generation engines, meeting the requirements to the future launch systems are expanded together with update of engines for promising launchers ("Proton-M", "Angara", "Rus" and others) at Keldysh Research Center.

Basic requirements are:

• reliability close to that of aviation systems;

• low cost of payload injected;

• maximum level of ecological safety.

In particular, the engines working on tripropellant fuel (oxygen + hydrogen + hydrocarbon fuel) as well as on LOX/Liquid methane are related to the engines\line of a new generation.

The combustion chamber for sustainer LRE

The injector head is used in the chamber, which provides an expansion
of the region of high-frequency oscillations resistance.
It is protected by RF patent # 2126905 dated 12.03.1998.

Liquefied air cycle engine (LACE)

The investigations are under way within the framework of the joint programme of the Russian Space Agency and the European Space Agency.