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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space vehicle injection into the Earth circular and elliptic orbits; booster ( two stages ) is a part of 15A18 missile withdrawn from action; upper ( the third ) stage is a derivative from warheads delivery stage of 15A18 missile.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: - 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CONTROL SYSTEM FOR ROKOT LAUNCH VEHICLE ROKOT LV features: booster ( two stages ) is a part of 15A35 missile withdrawn from action; upper ( the third ) stage is a specific developed one.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 1,0; − for angle of orbit inclination, ang. min up to 2,5; duration of injection, hours - up to 7,0.

CYCLONE-4 LV features: it is a middle - class LV for space vehicle injection into a near- earth circular or elliptic orbits; 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, 2..3 ang. Min; duration of injection, hours - up to 3,5. CONTROL SYSTEM FOR CYCLONE-4 LAUNCH VEHICLE

CONTROL SYSTEMS FOR SPACECRAFTS TSELINA family Their orbit altitude were of km. 84 ones were launched. Some of them operate up to the present OCEAN family Their circular orbits had an altitude about 500 km. 5 spacecrafts were launched. Some of them operate up to the present – 1984 KOSMOS family They were placed into geostationary orbits and allowed the imaging of the Earth surface. System «Oko»

CONTROL SYSTEMS FOR SPACECRAFTS ARKON Spacecraft for Earth remote sensing. Apogee km. Perigee km. 1997, KORONAS Automatically guided orbital station for study of solar activity. It operates up to the present 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 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 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»

SC name, date of launch Egyptsat-1, МS-2-8, МS-2-8М, 2013 Purpose Remote sensing of Earth. Remote sensing of Earth. Scientific data acquisition for investigation of space plasma characteristics. Remote sensing of Earth. Testing of ammoniac propulsion system. Tasks for control system Building of orbital orientation. Turns of SC into required direction. Control of SC sub-systems hardware and PL. Processing of command information. Building of orbital orientation. Turns of SC into required direction. Control of SC sub-systems hardware and PL. Processing of command information. Building of orbital orientation. Turns of SC into required direction with accuracy, which provides operation of PL having high resolution. Control of SC sub-systems hardware and PL. Processing of command information. Control system units OBC, angular rate meter based on fibre-optic gyroscopes, astro-measurement system, magnetometer, electromagnetic actuator, fly-wheeled actuator. OBC, set of angular rate meters based on fibre-optic gyroscopes, astro- measurement system, magnetometer, multi-unit attitude sensor, electromagnetic actuator, fly-wheeled actuator. OBC, set of angular rate meters based on fibre-optic gyroscopes, astro-system with 2 optical blocks, magnetometer, electromagnetic actuator, fly-wheeled actuator. Control systems of spacecrafts for remote sensing of Earth

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

Strap-down astroinertial block The strap-down astroinertial block is intended for measurement of spacecraft angular movement parametres and calculation of instrument system co-ordinates orientation parametres in inertial system co- ordinates. Error of a absolute angular speed vector projection determination: - without calibration in orbital flight – 5,0 · deg/sec; - after calibration in orbital flight – 1,0 · deg/sec. Error of a attitude determination – 15 ang. sec; Innovative aspects and main advantages: Astrocorrection allows to use rough fiber-optical gyroscope as a angular speed measuring instrument in strap-down astroinertial block. The gyroscope zero deviation estimation in flight mode and adjustment mode is provided for strap-down astroinertial block accuracy increase. Areas of Application: The strap-down astroinertial block is used as a structure of a spacecraft orientation and stabilisation control system. Stage of development: The device is at a pre-production model stage of development.

HARTRON MAIN ACHIEVEMENTS IN SPACE ACTIVITIES DURING YEARS OF INDEPENDENCE 1994 – SC injection in the frame of program «Koronas»; 1998 – launch of functional cargo module «Zarya» - Russian segment of the «Alpha» ISS; 1998 – docking of «Zarya» with Shuttle. Formation of cluster – «Zarya» «NODE-1», 600 days of flight with «NODE-1»; 1999 – start of commercial launches of the «Dnepr» launch vehicle; 2000 – automatic docking of the «Zarya» module with the «Zvezda» module ; 2000 – start of commercial launches of the «Rockot» launch vehicle; 2003 – launch of the «Strela» launch vehicle; 2007 – injection of the «Egyptsat-1» satellite for Earth remote sensing; 2008 – injection of the KOSMOS-2440 SC for Earth remote sensing; 2009 – launch of the «Cyclone-3», «Dnepr», «Rockot» launch vehicles; 2010 – first flight testing Strap-down inertial navigation system «Ros-1»; 2011 – second flight testing Strap-down inertial navigation system «Ros-1», launch of SC MS-2-8 (Sich-2).

Hartron offers of cooperation options in space sphere 1. Earth remote sensing from space: - design of remote sounding of the Earth satellites orientation and stabilisation control system; - design of satellite onboard data acquisition subscribers software. 2. Satellite navigation: - design of SC navigation software. 3. Satellite communication: - design of communication satellites orientation and stabilisation control system; 4. Ground infrastructure: - design of telemetry information processing software; - design of software for the operative control and the analysis SC flight in command center. 5. Scientific-technical researches: - increase reliability and autonomy functioning of SC control system methods; - design high-precision strapdown stellar-inertial SC control system; - high-speed SC with elastic elements control methods.

6. Education of experts: - construction of theoretical principles of SC control systems; - automated technology design and testing onboard computers of SC control systems software; - technology of optimisation of SC control systems on test stands; - onboard and land computer complexes operational systems; - principles of SC control in flight. Hartron offers of cooperation options in space sphere

Thanks for attention! © RPE Hartron-Arkos, 2011

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