TAI Turkish Aerospace Industries, Inc.

Transcription

1 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

2 CORPORATE INFORMATION 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 3 UNCLASSIFIED TAFF 54,49% SSM 45.45% Aerostructures Aerospace Integrated Systems Aeroengines TAI-GE Joint Venture 4 UNCLASSIFIED 2

3 CORPORATE INFORMATION Business Units CORPORATE INFORMATION Support Departments TAI BOARD CEO&President Muharrem DÖRTKAŞLI Strategy & Corporate Governance Bekir Ata YILMAZ Facilities and Asset Management İsmail ULUBAYRAM Enterprise Management Systems Orhan Veli KAYA Industrialization and Procurement İlhami TANYOLU Strategy and Technology Management Bekir Ata YILMAZ (a) Quality and Certification Murat TAŞPINAR (a) Logistics Muammer AKPINAR Flight and Flight Tests Cemal Nadir SAYIN Human Resources Oya TANSU Finance and Subsidiaries Saadet KORKEM Aerostructures Aerospace Integrated Systems AeroEngine Aerostructures Naki POLAT Aircraft Özcan ERTEM Helicopter Metin SANCAR UAV Systems Serdar ÖLEZ Space Systems Sinan ŞENOL JV with GE 5 UNCLASSIFIED (budget) ENGINEER DESIGN ENGINEER UNCLASSIFIED 3

4 CORPORATE INFORMATION EXPORT DOMESTIC '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

5 SPACE SYSTEMS CORPORATE INFORMATION BOEING BOMBARDIER LOCKHEED MARTIN LMMFC MARVIN ENGINEERING NORTHROP GRUMMAN SIKORSKY SPIRIT AEROSYSTEMS AGUSTA WESTLAND AIRBUS HELICOPTERS AIRBUS D&S AIRBUS ALENIA AERMACCHI FOKKER IAMCO PAG TELESPAZIO THALES TAI is accredited to the stringest quality standards in the aerospace business 9 UNCLASSIFIED Project Project Definition Contractor End User GÖKTÜRK-1 High Resolution Electro-Optic Remote Sensing Satellite and Fixed / Mobile Ground Station SSM Turkish Air Force Contract Schedule 19 July 2010 December 2015 Prime Contractor Content Features Status TELESPAZIO/THALES ALENIA SPACE (TAS) Direct Participation to Engineering Activities Manufacturing of MMS Panels AIT Center Establishment in TAI Facilities Resolution: < 1 m Orbit: Sun Synchronous Orbit (SSO) Altitude: ~690 km Mass: ~1000 kg Design phase has been completed Integration phase in process 10 UNCLASSIFIED 5

6 SPACE SYSTEMS SPACE SYSTEMS TOTAL 58 WP 850 Man-Month 67 Personnel 11 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 Infrastructure Consist of; 12 UNCLASSIFIED 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 LEO: Low Earth Orbit GEO: Geo-synchronous Earth Orbit AIT Center will be fully operational in All final tests of GÖKTÜRK-1 Satellite will be performed at this AIT Center. Clean Room Area: m² Closed Area: m² AIT Center will serve national and international all space programs. 6

7 SPACE SYSTEMS SPACE SYSTEMS Project GÖKTÜRK-2 (Turkey s first High Resolution EO Satellite ) Project Definition Contractor End User Electro-Optic Remote Sensing Satellite and Fixed / Mobile Ground Stations MoD R&D and Technology Department Turkish Air Force Contract Schedule 01 May December 2012 Prime Contractor Content Features Status TAI - TÜBİTAK UZAY Cooperation Satellite System Development, AIT & Launch Resolution: 2.5 m (PAN) / 5 m (MS) Orbit: Sun Synchronous Orbit (SSO) Altitude: ~686 km Mass: 409 kg Launched on 18 December 2012 from Jiuquan Satellite Launch Center, China with a LM-2D passes in one year and gathered high resolution images from all around the world. Operated by Turkish Air Forces. 13 UNCLASSIFIED İstanbul Bosphorus FSM Bridge Çanakkale Vessel Ship Transition Dubai - Palm Jebel Ali BAE 14 UNCLASSIFIED 7

8 SPACE SYSTEMS SPACE SYSTEMS Project GÖKTÜRK-3 Project Definition High Resolution SAR Remote Sensing Satellite and Fixed / Mobile Ground Station Contractor End User SSM Turkish Air Forces Contract Schedule 26 November May 2016 Prime Contractor Subcontractor Content TAI ASELSAN and TÜBİTAK Space Satellite and Ground Station Preliminary Design (PDR) Status Definition of System Configuration Trade-off Analysis for the Selection of the SAR Payload Mission Definition is in progress Photo from the Signature Ceremony of GÖKTÜRK-3 Program 15 UNCLASSIFIED Project Project Definition Contractor End User Duration TÜRKSAT-6A National Communication Satellite Communication Satellite (Ku & X Band) TÜBİTAK TÜRKSAT 60 Months Content Communication Satellite System Development Mission Life Time Features Status 15 years 16 Active, 4 Redundant Ku-band 2 Active, 1 Redundant X-band Orbit: GEO, 42º East Deorbiting: ~350 km Proposal has been submitted on 28 th February 2014 Proposal Phase is in progress GEO: Geo-synchronous Earth Orbit TÜRKSAT 3A 16 UNCLASSIFIED 8

9 SPACECRAFT PROPULSION TECHNOLOGIES SPACECRAFT PROPULSION TECHNOLOGIES Propulsion system provides thrust; 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 17 UNCLASSIFIED 18 UNCLASSIFIED 9

10 SPACECRAFT PROPULSION TECHNOLOGIES SPACECRAFT PROPULSION TECHNOLOGIES What does mission require? Which maneuvers are mandatory? Decision on the Right Propulsion Types!! Launcher Spacecraft Propulsion Type Launch Transfer Orbit Maneuver Orbit Insertion (Launch Errors) Orbit Maintenance Attitude Control Cold Gas X X Chemical Solid X X X Liquid Monopropellant X X X X Bipropellant X X X X X Electric X X X 19 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 (N 2 ) Hydrogen (H 2 ) ,1-5 N 20 UNCLASSIFIED 10

11 SPACECRAFT PROPULSION TECHNOLOGIES SPACECRAFT PROPULSION TECHNOLOGIES Propulsion Type Isp (s) Thrust Advantages Disadvantages Chemical Liquid Monopropellant Bipropellant ,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. 21 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 22 UNCLASSIFIED 11

12 SPACECRAFT PROPULSION TECHNOLOGIES SPACECRAFT PROPULSION TECHNOLOGIES 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 23 UNCLASSIFIED Propulsion Type Isp (s) Thrust Advantages Disadvantages Electric Electro-thermal Electro-magnetic Electro-static ,1 mn 20 N - High Isp - 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. 24 UNCLASSIFIED 12

13 SPACECRAFT PROPULSION TECHNOLOGIES SPACECRAFT PROPULSION TECHNOLOGIES Electric Propulsion Electro-thermal Electro-static Electro-magnetic 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 LMC7000, A2100, AMSAT- Phase 3-D, Intelsat-5 F-2 Works by creating ions out of a stable gas (generally by electron bombardment). Xenon is the common propellant. Ion and Hall effect thrusters GOCE, AEHV-SV2, SMART- 1, MEASAT 3.. Works by accelerating charged fluid by utilization of a flowing electrical current and magnetic fields. Pulsed plasma (PPT) Magnetoplasmadynamic thrusters (MPDT) FalconSat-3, EO UNCLASSIFIED Example scenario: GTO-GSO maneuver of TURKSAT-4A (Launch Vehicle: Proton M-Breeze) Launch Mass 4850 kg GTO Parameters Perigee (H p ) Apogee (H a ) 9673 km km Inclination (i) 12.7º dv-to-gso 985 m/s 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 Electric propulsion is NOT desirable for GTO-GSO maneuvers. 26 UNCLASSIFIED 13

14 SPACECRAFT PROPULSION TECHNOLOGIES SPACECRAFT PROPULSION TECHNOLOGIES Example scenario: Calculation of the maximum satellite launch mass with Direct-GEO (Launch Vehicle: Proton M-Breeze) SPACECRAFT Launch Type Launch Mass Limit (Proton M-Breeze) Service Lifetime Delta-V Budget Direct-GEO 3250 kg 15 years 850 m/s Parameter Chemical Propulsion Electric Propulsion Specific Impulse (Isp) 280 s 1500 s Thrust 20 N 90 mn Launch Mass 3250 kg 3250 kg Propellant Mass 683 kg 173 kg Dry Mass 2567 kg 3077 kg Electric propulsion makes spacecraft to win 510 kg more dry mass. 27 UNCLASSIFIED Example scenario: GTO-launch type GEO spacecraft propulsion sizing Perigee (H p ) Apogee (H a ) GTO Parameters 9673 km km Inclination (i) 12.7º dv-to-gso Service lifetime dv-orbit maintanence Propulsion Type Only Chemical Chemical + Electric Maneuver GTO-GSO Orbit Maintanence GTO-GSO Orbit Maintanence Specific Impulse (Isp) 320 s 280 s 320 s 1500 s Thrust 400 N 20 N 400 N 90 mn Propellant Mass 1300 kg 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. 985 m/s 15 years 850 m/s 28 UNCLASSIFIED 14

15 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 of plasma technologies for the future satellite programs. 29 UNCLASSIFIED 30 UNCLASSIFIED 30 15