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Control systems for intercontinental ballistic missiles and launch vehicles

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

ICOS that incorporates multicomputer processing system implements:

• 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

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• booster ( two stages ) is a part of 15A18 missile withdrawn from action;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:

• 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• booster ( two stages ) is a part of 15A35 missile withdrawn from action;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:

• 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:

• 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.