TAI – Turkish Aerospace Industries, Inc. 1 UNCLASSIFIED Corporate Information TAI - Space Systems Activities Necessity of Propulsion in Space Functionality of Propulsion System Spacecraft Propulsion Technologies Cold Gas Propulsion Chemical Propulsion Electric Propulsion The Usage of Chemical and Electric Propulsion TAI and Spacecraft Propulsion 2 UNCLASSIFIED 1 CORPORATE INFORMATION Merger of TAI and TUSAŞ Procurement of Lockheed Martin / General Electric shares (%49) by TUSAŞ Establishment of TAI as a joint venture to manufacture F-16 aircraft in Turkey Establishment of TUSAŞ UNCLASSIFIED CORPORATE INFORMATION 3 TAFF 54,49% SSM 45.45% Aerospace Aerostructures Aeroengines Integrated Systems TAI-GE Joint Venture 4 UNCLASSIFIED 2 CEO&President Muharrem DÖRTKAŞLI Strategy & Corporate Governance Bekir Ata YILMAZ Support Departments CORPORATE INFORMATION TAI BOARD Logistics Muammer AKPINAR Facilities and Asset Management İsmail ULUBAYRAM Flight and Flight Tests Cemal Nadir SAYIN Enterprise Management Systems Orhan Veli KAYA Human Resources Oya TANSU Industrialization and Procurement İlhami TANYOLU Finance and Subsidiaries Saadet KORKEM Strategy and Technology Management Bekir Ata YILMAZ (a) Quality and Certification Murat TAŞPINAR (a) Business Units Aerospace CORPORATE INFORMATION 5 Aerostructures Aerostructures Naki POLAT AeroEngine Integrated Systems Aircraft Helicopter Özcan ERTEM Metin SANCAR UAV Systems Serdar ÖLEZ Space Systems Sinan ŞENOL JV with GE UNCLASSIFIED 4269 4515 4633 3951 3541 2406 2995 3046 2008 2009 2689 2044 2005 2006 2007 2010 2011 2012 1800 1600 2013 2014 (budget) ENGINEER DESIGN ENGINEER 1400 1200 1000 800 600 400 200 0 2005 2006 2007 2008 2009 2010 2011 2012 2013 6 UNCLASSIFIED 3 CORPORATE INFORMATION 1.100 1.000 EXPORT 900 DOMESTIC 800 700 600 500 400 300 200 100 0 '05 '06 '07 '08 '09 '10 '11* 12* 13* 14* (E) DEFENSE NEWS TOP 100 : RANK #85th TURKISH EXPORTERS ASSEMBLY ‘s RANKING : # 1 EXPORTER OF THE INDUSTRY * IFRS 7 UNCLASSIFIED 8 UNCLASSIFIED 4 CORPORATE INFORMATION AGUSTA WESTLAND BOEING AIRBUS HELICOPTERS BOMBARDIER AIRBUS D&S LOCKHEED MARTIN AIRBUS LMMFC ALENIA AERMACCHI FOKKER MARVIN ENGINEERING IAMCO NORTHROP GRUMMAN PAG SIKORSKY TELESPAZIO SPIRIT AEROSYSTEMS THALES TAI is accredited to the stringest quality standards in the aerospace business SPACE SYSTEMS 9 10 UNCLASSIFIED Project GÖKTÜRK-1 Project Definition High Resolution Electro-Optic Remote Sensing Satellite and Fixed / Mobile Ground Station Contractor SSM End User Turkish Air Force Contract Schedule 19 July 2010 – December 2015 Prime Contractor TELESPAZIO/THALES ALENIA SPACE (TAS) Content Direct Participation to Engineering Activities Manufacturing of MMS Panels AIT Center Establishment in TAI Facilities Features Resolution: < 1 m Orbit: Sun Synchronous Orbit (SSO) Altitude: ~690 km Mass: ~1000 kg Status Design phase has been completed Integration phase in process UNCLASSIFIED 5 SPACE SYSTEMS TOTAL 58 WP 850 Man-Month 67 Personnel UNCLASSIFIED AIT Center Infrastructure capable to support Assembly, Integration and Test activities at least one LEO satellite up to minimum two tons and one GEO satellite up to minimum five ton simultaneously. AIT Center will be fully operational in 2014. All final tests of GÖKTÜRK-1 Satellite will be performed at this AIT Center. Closed Area: 9.850 m² SPACE SYSTEMS 11 AIT Center Infrastructure Consist of; Thermal Vacuum Chamber Compact Antenna Test Range (CATR) Facility Solar Array Deployment Facility EMI/EMC Test Facility Vibration Test Facility Mass Properties Measurement System Acoustic Test Facility Multi Layer Isolation (MLI) Preparation Room Harness Room Battery Storage & Preparation Room Clean Room Area: 3.880 m² AIT Center will serve national and international all space programs. LEO: Low Earth Orbit GEO: Geo-synchronous Earth Orbit 12 UNCLASSIFIED 6 SPACE SYSTEMS GÖKTÜRK-2 (Turkey’s first High Resolution EO Satellite ) Project Definition Electro-Optic Remote Sensing Satellite and Fixed / Mobile Ground Stations Contractor MoD R&D and Technology Department End User Turkish Air Force Contract Schedule 01 May 2007 – 31 December 2012 Prime Contractor TAI - TÜBİTAK UZAY Cooperation Content Satellite System Development, AIT & Launch Features Resolution: 2.5 m (PAN) / 5 m (MS) Orbit: Sun Synchronous Orbit (SSO) Altitude: ~686 km Mass: 409 kg Status Launched on 18 December 2012 from Jiuquan Satellite Launch Center, China with a LM-2D. 5.344 passes in one year and gathered high resolution images from all around the world. Operated by Turkish Air Forces. UNCLASSIFIED SPACE SYSTEMS 13 Project İstanbul Bosphorus FSM Bridge 14 Çanakkale Vessel Ship Transition Dubai - Palm Jebel Ali BAE UNCLASSIFIED 7 SPACE SYSTEMS Project GÖKTÜRK-3 Project Definition High Resolution SAR Remote Sensing Satellite and Fixed / Mobile Ground Station Contractor SSM End User Turkish Air Forces Contract Schedule 26 November 2013 – 26 May 2016 Prime Contractor TAI Subcontractor ASELSAN and TÜBİTAK Space Content Satellite and Ground Station Preliminary Design (PDR) Status Definition of System Configuration Photo from the Signature Ceremony of GÖKTÜRK-3 Program Trade-off Analysis for the Selection of the SAR Payload Mission Definition is in progress SPACE SYSTEMS 15 UNCLASSIFIED Project TÜRKSAT-6A National Communication Satellite Project Definition Communication Satellite (Ku & X Band) Contractor TÜBİTAK End User TÜRKSAT Duration 60 Months Content Communication Development Mission Life Time 15 years Features Status Proposal has been submitted on 28th February 2014 Proposal Phase is in progress Satellite System TÜRKSAT – 3A 16 Active, 4 Redundant Ku-band 2 Active, 1 Redundant X-band Orbit: GEO, 42º East Deorbiting: ~350 km GEO: Geo-synchronous Earth Orbit 16 UNCLASSIFIED 8 SPACECRAFT PROPULSION TECHNOLOGIES to move the spacecraft to rotate the spacecraft about its center of mass It’s required for the following maneuvers; Launch Transfer orbit Orbit insertion Orbit maintenance Attitude control maneuvers Deorbiting UNCLASSIFIED SPACECRAFT PROPULSION TECHNOLOGIES 17 Propulsion system provides thrust; 18 UNCLASSIFIED 9 SPACECRAFT PROPULSION TECHNOLOGIES What does mission require? Launcher Propulsion Type Launch Spacecraft Transfer Orbit Maneuver SPACECRAFT PROPULSION TECHNOLOGIES 20 Orbit Insertion (Launch Errors) Orbit Maintenance Attitude Control X X X X X X X X X X X Cold Gas Chemical Solid X X X Liquid Monopropellant X Bipropellant X X Electric 19 Decision on the Right Propulsion Types!! Which maneuvers are mandatory? UNCLASSIFIED Cold gas propulsion system uses the pre-stored energy of a compressed gas to develop thrust. Simple and safe Due to the low thrust and Isp values, they are widely used; in low mass satellites (Proba-2, Slosh-Sat, BilSAT-1) for attitude control and minor orbital maneuvers Propulsion Type Isp (s) Thrust Cold Gas Nitrogen (N2) Hydrogen (H2) 60 250 0,1 - 5 N UNCLASSIFIED 10 SPACECRAFT PROPULSION TECHNOLOGIES SPACECRAFT PROPULSION TECHNOLOGIES 21 22 Propulsion Type Chemical Liquid Monopropellant Bipropellant Isp (s) Advantages Thrust Disadvantages - 140 - 235 320 - 460 0,1 N 5 MN - High thrust Extensive heritage - Only moderate Isp Toxic/hazardous material Safety problems Combustion complications Liquid-propellant systems have the most extensive heritage and wide usage. UNCLASSIFIED Monopropellant systems; Thrust is generated by decomposition of the pressurized propellant passing through a catalyst. Used especially for the Low-Earth-Orbit (LEO) satellites to achieve: Orbit insertion Orbit maintanence Attitude control Deorbiting There are many achieved missions such as Göktürk-2, Göktürk-1, Pleiades, GeoEye, Terrasar-X… UNCLASSIFIED 11 SPACECRAFT PROPULSION TECHNOLOGIES SPACECRAFT PROPULSION TECHNOLOGIES 23 24 Bipropellant systems; Thrust is generated by combustion of fuel and oxidiser stored at different tanks. These systems are used especially for Geosynchronous Orbit (GEO) and Medium Earth Orbit (MEO) satellites to achieve: Transfer orbit Orbit insertion Orbit maintanence Attitude control Deorbiting Some examples: TÜRKSAT 2A-3A, HotBird 7A, Chinasat-9, Eutelsat W3A… UNCLASSIFIED Propulsion Type Electric Electro-thermal Electro-magnetic Electro-static Isp (s) Thrust 500 - 1000 1000 - 7000 2000 - 10000 0,1 mN 20 N Advantages - High Isp Disadvantages - Limited heritage Low thrust High power consumption Expensive Electric propulsion is a technology aimed at achieving thrust with high exhaust velocities, which results in a reduction in the amount of propellant required compared to other conventional propulsion methods. Reduced propellant mass can significantly decrease the launch mass of a spacecraft or satellite, leading to lower costs from the use of smaller launch vehicles to deliver a desired mass into a given orbit or to a deepspace target. UNCLASSIFIED 12 SPACECRAFT PROPULSION TECHNOLOGIES Electric Propulsion Electro-thermal SPACECRAFT PROPULSION TECHNOLOGIES • Used to heat a fluid or gas, which is vented out an exhaust nozzle to produce thrust. • Hydrazine is the common propellant. • Resistojet and Arcjet motors • Works by creating ions out of a stable gas (generally by electron bombardment). • Xenon is the common propellant. • Ion and Hall effect thrusters LMC7000, A2100, AMSATPhase 3-D, Intelsat-5 F-2… GOCE, AEHV-SV2, SMART1, MEASAT 3.. Electro-magnetic • Works by accelerating charged fluid by utilization of a flowing electrical current and magnetic fields. • Pulsed plasma (PPT) Magnetoplasmadynamic thrusters (MPDT) FalconSat-3, EO-1.. UNCLASSIFIED 25 26 Electro-static Example scenario: GTO-GSO maneuver of TURKSAT-4A (Launch Vehicle: Proton M-Breeze) Launch Mass 4850 kg GTO Parameters Perigee (Hp) 9673 km Apogee (Ha) 35786 km Inclination (i) dV-to-GSO Parameter Chemical Propulsion Electric Propulsion Specific Impulse (Isp) 320 s 1500 s Thrust 400 N 90 mN Propellant Mass 1300 kg 315 kg Thrust Duration 170 minutes 600 days 12.7º 985 m/s Electric propulsion is NOT desirable for GTO-GSO maneuvers. UNCLASSIFIED 13 SPACECRAFT PROPULSION TECHNOLOGIES Example scenario: Calculation of the maximum satellite launch mass with Direct-GEO (Launch Vehicle: Proton M-Breeze) SPACECRAFT Launch Type 3250 kg Service Lifetime 15 years Delta-V Budget 850 m/s Parameter Electric Propulsion 280 s 1500 s Thrust 20 N 90 mN 3250 kg 3250 kg Propellant Mass Dry Mass 683 kg 173 kg 2567 kg 3077 kg Electric propulsion makes spacecraft to win 510 kg more dry mass. UNCLASSIFIED 27 SPACECRAFT PROPULSION TECHNOLOGIES Chemical Propulsion Specific Impulse (Isp) Launch Mass Example scenario: GTO-launch type GEO spacecraft propulsion sizing GTO Parameters Perigee (Hp) 9673 km Apogee (Ha) 35786 km 12.7º Inclination (i) Propulsion Type Only Chemical GTO-GSO Orbit Maintanence Specific Impulse (Isp) 320 s Thrust 400 N 1300 kg Maneuver Propellant Mass 28 Direct-GEO Launch Mass Limit (Proton M-Breeze) dV-to-GSO 985 m/s Service lifetime 15 years dV-Orbit maintanence 850 m/s Chemical + Electric GTO-GSO Orbit Maintanence 280 s 320 s 1500 s 20 N 400 N 90 mN 945 kg 1300 kg 200 kg Launch Mass 4850 kg 4850 kg Dry Mass 2605 kg 3350 kg Chemical + Electrical option makes spacecraft to win 745 kg more dry mass. UNCLASSIFIED 14 TAI has been experienced in chemical propulsion systems during GOKTURK satellites development programs. Advantages of electric propulsion are undeniable. TAI encourages and follows the technological developments on electric propulsion. TAI aims to support the national plasma propulsion system development programs as being the prime user of those systems. TAI greatly appreciates the technical opportunities technologies for the future satellite programs. 29 UNCLASSIFIED 30 UNCLASSIFIED of plasma 30 15
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