2. DISTRIBUTION AMONG INDUSTRIES Space industry Power industry Rail transportation Different industries

3. PJS Hartron RPEHartron-Ascond LLC Westron RPE Hartron-Inkor Hartron-Inkor RPE Hartron-Express Hartron-Express RPE Hartron-Plant Hartron-Plant RPE Hartron-Arkos Hartron-Arkos RPE Hartron-Energo Hartron-Energo LLC Hartron- Elektrosvyaz Hartron- Elektrosvyaz LLC RPE Hartron-Violis Hartron-Violis ISC Kosmotras RPE Hartron-Ukom Hartron-Ukom M. Vakhno

4. CONTROL SYSTEMS FOR INTERCONTINTAL BALLISTIC MISSILES

5. CONTROL SYSTEMS FOR LAUNCH VEHICLES

6. GNC SYSTEM FOR LV TO LAUNCH SATELLITES AND SPACECRAFTS

7. GNC SYSTEM FOR LV TO LAUNCH SATELLITES AND SPACECRAFTS

8. 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space vehicle injection into the Earth circular and elliptic orbits; booster ( two stages ) is a part of 15A18 missile withdrawn from action; upper ( the third ) stage is a derivative from warheads delivery stage of 15A18 missile.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.

9. CONTROL SYSTEM FOR ROKOT LAUNCH VEHICLE ROKOT LV features: booster ( two stages ) is a part of 15A35 missile withdrawn from action; upper ( the third ) stage is a specific developed one.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.

10. 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

11. 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

12. 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

13. 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.

14. ISS: Final configuration The 1 st 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»

15. ANOTHER ACTIVITIES AREAS

16. The basic technology stages of control system projection and experimental development Development of engineering documentation, models and algorithms Tests of CS in complex stand Tests of CS in checking station Tests in technical and starting positions Flight tests Development of algorithms in mathematical stand Development of equipment Development of SW in research stand Autonomous development of equipment Autonomous development of equipment

17. The stand of physical modelling

18. 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.

19. Simulators of emission Sun simulator Earth simulator Stars simulators

20. TEST & CERTIFICATION CENTER

21. 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.

22. 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

23. 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

25. Thanks for attention! © PJSC HARTRON, 2014