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Control systems for launch vehicles

Autonomous integrated control system(ICOS) for super heavy-duty Energya launch vehicle

ICOS that incorporates multicomputer processing system implements:

LV 'Energya'
  • precise optimal injection of pay-load ( orbital spacecraft – OS ) into required orbit
  • flight control under condition of critical failure occurrence
    ( i.e. failure with probability value less than 10 -6 ) and specially when one or two main engine packed up parrying of critical failure consequences and, if necessary, return of OS to the basic airdrome through:
  • - one-turn returning maneuver;
    - bringing maneuver;

  • precise bringing of separated parts to the alienated districts;
  • main engines operation control;
  • fuel flow control;
  • ensuring of restrictions on:

    - impact head;
    - overloading;
    - transverse loading of LV Structure due to aerodynamic force;

  • stabilization of the LV that has extremely complex dynamics including:

    - 40 tones of LV body flexible oscillation;
    - fuel oscillaton in 12 tanks;
    - oscillation of 8 main engine’s flexible suspension;
    - dynamic characteristics of 40 steering actuators.


Control system for Dnepr launch vehicle

LV 'Dnepr'

Dnepr LV features:

  • it is a middle-class LV for space vehicle injection into the Earth circular and elliptic orbits;
  • booster ( two stages ) is a part of 15A18 missile withdrawn from action;
  • upper ( the third ) stage is a derivative from warheads delivery stage of 15A18 missile. New features of upper stage:
  • - repeated main engine firing and new scheme of its operation;
    - additional low-powered motive installation for stage stabilization while coasting;

  • launch – from silo launch facilities, Baikonour.

CS Performance:

  • LV mission and motion control at phases of pre-launch preparation, launch and space;
  • vehicle placing into required orbit;
  • it is derived from CS for 15A18 missile by means of modification both HW and SW;
  • combined error of injection comes to:

    - for orbit altitude, km - 4;
    - for angle of orbit inclination, ang. min - 2,5;

  • duration of injection, hours - up to 1,0.


Control system for Strela launch vehicle

Strela LV features:

LV 'Strela'
  • it is a light - class LV for space vehicle injection into the Earth circular and elliptic orbits;
  • booster ( two stages ) is a part of 15A35 missile withdrawn from action;
  • upper ( the third ) stage is a derivative from warheads delivery stage of 15A35 missile.New features of upper stage:

    - new scheme of the main engine operation under single-mode firing;
    - additional low-powered motive installation for stage stabilization while coasting;

  • launch – from silo launch facilities, Svobodny.

CS Performance:

  • LV mission and motion control at phases of pre-launch preparation, launch and space vehicle placing into required orbit;
  • it is derived from CS for 15A35 missile by means of modification both HW and SW;
  • combined error of injection comes to:

    - for orbit altitude, km 4;
    - for angle of orbit inclination, ang. min - 2,5;

    duration of injection, hours - up to 1,0.

Control system for Rokot launch vehicle

Rokot LV features:

LV 'Rokot'
  • it is a light - class LV for space vehicle injection into the Earth circular and elliptic orbits;
  • booster ( two stages ) is a part of 15A35 missile withdrawn from action;
  • upper ( the third ) stage is a specific developed one. It provides repeated main engine firing and controlled coasting flight;
  • launch will be made from launch pad, Plesetsk.

CS Performance:

  • LV mission and motion control at phases of pre-launch preparation, launch and space vehicle placing into required orbit;
  • it is designed for the Rokot LV specially, with up-to-date componeuts use;
  • combined error of injection comes to:

    - for orbit altitude, percentage up to 1,0;
    - for angle of orbit inclination, ang. min up to 2,5;

    duration of injection, hours - up to 7,0.

Control system for Cyclone-4 launch vehicle

Cyclone-4 LV features:

LV 'Cyclone-4'
  • it is a middle - class LV for space vehicle injection into a near-earth circular or elliptic orbits;
  • its booster ( two stages ) is a part of 11K68 LV;
  • its upper, the third, stage is a specific developed one and provides repeated main engine firing and controlled coasting flight;
  • it is intended to be launched from an equatorial launch site.

CS Performance:

  • it provides LV mission and motion control at phases of pre-launch preparation, launch and payload placing into required orbit;
  • it provides stages equipment check at all phases of LV mounting and testing;
  • it is designed with up-to-date components use;
  • to improve injection accuracy it is equipped with INS and GPS based navigation subsystem;
  • combined error of injection comes to:

    - for orbit altitude, km up to 1,5;
    - for angle of orbit inclination, ang. min up to 0,2;

    duration of injection, hours - up to 3,5.
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