DISTRIBUTION AMONG INDUSTRIES

Space industry

Power industry

Rail transportation

Different industries

PJS HartronPJS Hartron

RPERPE Hartron-AscondHartron-Ascond

LLCLLC WestronWestronRPERPE

Hartron-InkorHartron-Inkor

RPERPE Hartron-ExpressHartron-Express

RPERPE Hartron-PlantHartron-Plant

RPERPE Hartron-ArkosHartron-Arkos

RPERPE Hartron-EnergoHartron-Energo

LLCLLC Hartron-Hartron-

ElektrosvyazElektrosvyaz

LLC RPELLC RPE Hartron-ViolisHartron-Violis

ISC KosmotrasISC Kosmotras

RPERPE Hartron-UkomHartron-Ukom

M. VakhnoM. Vakhno

CONTROL SYSTEMS FOR INTERCONTINTAL BALLISTIC MISSILES

CONTROL SYSTEMS FOR LAUNCH VEHICLES

GNC SYSTEM FOR LV TO LAUNCH SATELLITES AND SPACECRAFTS

GNC SYSTEM FOR LV TO LAUNCH

SATELLITES AND SPACECRAFTS

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withdrawn from action;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:

- one-time 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, Yasniy.

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 – 1,5;

- for angle of orbit inclination, ang. min – 1,0;

duration of injection, min – up to 20.

CONTROL SYSTEM FOR ROKOT LAUNCH VEHICLE

ROKOT LV features:

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withdrawn from action;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 ROCOT LV specially, with up-to-

date componeuts use;

combined error of injection comes to:

− for orbit altitude, percentage – up to 1,5;

− for angle of orbit inclination, ang. min – 1...3;

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

CONTROL SYSTEMS FOR SPACECRAFTS

TSELINA family

Their orbit altitude were of 500 - 900 km. 84 ones were launched. Some of them operate up to the present.

1967 - 2005

OCEAN family

Their circular orbits had an altitude about 500 km. 5 spacecrafts were launched. Some of them operate up to the present.

1970 – 1984

KOSMOS family

They were placed into geostationary orbits and allowed the imaging of the Earth surface. System «Oko».

1991 - 2008

CONTROL SYSTEMS FOR SPACECRAFTS

ARKON

Spacecraft for Earth remote sensing.Apogee - 2700 - 2900 km.Perigee - 1400 - 1600 km.

1997, 2002 - 2003

KORONAS

Automatically guided orbital station for study of solar activity. It operates up to the present.

1994 - 2001

COUPON

The first component of space segment for satellite intercommunications and data communications system BANKER.(geostationary orbit).

1997

CONTROL SYSTEMS FOR MODULES OF STATION «MIR»

«Kvant», «Kvant-2», «Kristall», «Spectr», «Priroda»

Docking with station «Mir»

Delivery of the scientific apparatus, PLs and propellant

Control of the station «Mir» motion

Orbits: Circular 250 - 550 km

PERFORMANCE DATA OF CONTROL SYSTEM (CS) FOR SUPPLY

SPACECRAFT-MODULE (SSM) AND FUNCTIONAL AND CARGO UNIT (FCU)Peculiarity:

CS is installed in power unit FCU that is the first component of the ISS ALPHA;

FCU CS is a modification of basal control system which was qualified completely during preparation and mission of modules QUANTUM-2, CRYSTAL, SPECTRUM and NATURE. Development chronology-1994…1997.

Performance data of the CS for FCU is in accordance of those for the SSM. In addition the FCU CS will provide the specified spatial orientation during docking to FCU of the rendez -vous module NODE1 Unity delivered by re-used spacecraft SHUTTLE as well as the orientation of joint structure FCU+NODE1 during direct docking of SHUTTLE the next time;

This CS can be used to construct other components of the ISS ALPHA. To expand the CS functionality and to upgrade its performance it can be supplemented with additional HW and SW. Such modification will provide combined operation of FCU CS and CS of other ISS components as well as the operation of ISS different configurations during its assembling and operation.

ISS: Final configuration

The 1st phase of the ISS assembling: FCB "Zarya" + NODE-1 in autonomous flight during

~ 600 days

Phase of the ISS assembling: FCB

"Zarya" + NODE-1 perform docking to

service module «Zvesda»

ISS «ALPHA»

ANOTHER ACTIVITIES AREASANOTHER ACTIVITIES AREAS

The basic technology stages of control system projection and experimental development

Development of engineering

documentation, models and algorithms

Development of engineering

documentation, models and algorithms

Tests of CS in complex stand

Tests of CS in complex stand

Tests of CS in checking stationTests of CS in checking station

Tests in technical and

starting positions

Tests in technical and

starting positions

Flight testsFlight tests

Development of algorithms in mathematical

stand

Development of algorithms in mathematical

stand

Development of equipment

Development of equipment

Development of SW in research

stand

Development of SW in research

stand

Autonomousdevelopment of

equipment

Autonomousdevelopment of

equipment

The stand of physical modelling

Tasks to be solved:

- validation of mathematical models of control system units for

adequacy;

- test for control system operationability in dynamic modes;

- support during flight tests.

Main principles of physical simulation:

- simulation of SC angular motion;

- simulation of emission of celestial reference bodies;

- simulation of operation of control system actuators.

Simulators of emission

Sun simulator

Earth simulatorStars simulators

TEST & CERTIFICATION CENTER

Tracking of spacecrafts in flight

During tracking of spacecraft in flight it is solved the following tasks:

- distribution of control functions

between GNC system and

Mission Control Center;

- planning of mission;

- computation of mission data in

Mission Control Center;

- providing SC control using single

commands from ground stations;

- processing of TLM information

for operative analysis.

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.

CONTROL SYSTEM FOR CYCLONE-4 LAUNCH VEHICLE

Strap-down inertial navigation system

Purpose:

- initial alignment of inertial system;

- definition of LV navigating movement parametres.

Weight ………………32 kg

Autonomous initial alignment:

azimuth ……………5-7 ang. min

horizon ……………10-15 ang. sec

Accuracy of insertion into a

solnechno-synchronous orbit:

height ………………9,5 km

inclination …………12 ang. min

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© PJSC HARTRON, 2014