Dr. Celal Sami Tüfekci Erdem Demircioğlu Turksat AS...• GEO Communication Satellite • Launch at 2015 • Maneuver life time ‐15 years • Payload • 16 transponders –Ku

Copyright © 2008 Türksat AŞ

Dr. Celal Sami Tüfekci &Erdem Demircioğlu

Turksat AS

10 September 2008Prague, Czech Republic

http://www.dlr.de/


AgendaShort company introductionTurksat’s satellite design and R&D goalsOutline Turksat’s satellite design activitiesCooperation and partnership opportunities via FP7

210 Sep 2008 ‐ Prague


Company: Turksat AS“Turksat Satellite Communication Cable TV and Operation AS”Publicly owned satellite operator since 1994Divisions

Satellite OperationsCable TV & Internete‐GovernmentSatellite Design and R&DImaging (Turksat Globe)

Over 500 employees



Satellite OperationsSatellite Location Launch EOL

Türksat‐1C 42 1996 2008

Eurasiasat 42 2001 2016

Türksat‐3A 42 2008 2028



Cable TV & InternetOver 1.200.000 subscribersHigh‐speed internetDigital TV I/F ready



e‐Government

6

ee--GovernmentGovernmentGatewayGateway

Mobile PlatformsMobile Platforms

InternetInternet

Call CenterCall Center

Digital Cable TVDigital Cable TV

CitizensCitizensCompaniesCompanies

BanksBanks

FirmsFirms

Government InstitutesGovernment Institutes

ServiceService

InformationInformation

PaymentPaymentOutside WorldOutside World



Partnering with Digital Globe (USA)

Quick Bird 2

World Viev 1

World Viev 2

QuickBird 2

World View 1World View 2

Turksat Globe: Current & Future Satellites


GEO Communication Satellite Design



Satellite Design and R&D Goals


Short Term Goals Organizational and Infrastructure Goals• Establish a strong systems engineering

capability in communication satellite systems design

• Establish application software development capability in communication satellite systems design

• Gain satellite system assembly, integration, and test (AIT) capability through certification

Intermediate Term Goals• Establish capability in communication

satellite subsystems integrated‐design• Participate in R&D projects

Long Term Goals• Develop a prime contractor capability in

communication satellite systems design and manufacture

• Establish the organizational structureo Managemento Processo Technical

• Recruit a Project Managers• Identify and obtaining required consulting

services• Identify and acquiring required resources

(human/financial)• Develop R&D infrastructure• Plan and build necessary facilities

o Office spaceo Labso Clean rooms


AIT Center

Turksat is cooperating with other agencies in Turkey to build a satellite AIT CenterIt will be used for assembly, integration, and testing of communication, observation, and scientific satellites



Design TeamGroup of Turksat engineers trained by Thales Alenia Space in Cannes and Toulouse

Specialized in:Data‐Handling, OBSW and AOCSMission and System AnalysisThermal ControlElectrical Power Payload and TCRStructure and Propulsion



Satellite DesignPDR‐A level satellite design is performed by TAS supportBased on Spacebus 4000 architectureSuccessfully completed in May 2008



General Specs• GEO Communication Satellite

• Launch at 2015

• Maneuver life time ‐ 15 years

• Payload• 16 transponders – Ku band

• 4 transponders – C Band

• Structure• Central tube based

• Max. launch mass: 2700 kg

• Propulsion• Chemical unified propulsion sys.

• LAE & 16 reaction control thrusters



General Specs (contd.)

14

• Thermal Control• Surface Mount Heat Pipes

• Conductive TWTA

• Attitude Control• Zero‐momentum Reaction Wheel

approach

• StarTracker & Gyro based AOCS

• Power Management• Li‐Ion Battery

• 4 solar panels

• Data Handling & OBSW• Leon or ERC32

• 1553B

• RTOS (COTS)



Coverage Area

15

WEST

EAST

TURKEY

SA

TSO

FT

-4.00 -3.00 -2.00 -1.00 0.00 1.00 2.00 3.00 4.00Theta*cos(phi) in Degrees

3.00

4.00

5.00

6.00

7.00

8.00

Thet

a*si

n(ph

i) in

Deg

rees



Payload Performance RequirementsEIRP Performance Requirements for BSS band:

50.5 dBW (West R1 coverage) 52.8 dBW (Turkey coverage)

EIRP Performance Requirement for C band:45 dBW (Turkey coverage)

G/T Performance Requirement for BSS band:3.6 dB/K (West R1 coverage) 1.8 dB/K (East R1 coverage)

G/T Performance Requirements for C band:1 dB/K (Turkey coverage)



Payload Block Diagram

17

Ku-band Payload

C-band Payload



TCR Block Diagram



Structure Overview

19

SB like structure approach

Primary structureCentral tube w/adaptor ringShear webs

Main structurePanels and webs to carry internal equipment

Secondary structureSupport structure for the external equipment



GTO Configuration



Main Dimensions



Launcher Envelope



CM North Panel Layout

23

EPC and CAMP

Shear web

SADM

Ku band TWT

8 Ch Ku band OMUX



CM South Panel Layout

24

C band TWT

4 Ch C band OMUX

TCR

Switches

Heat pipe network



SM South and North Panels

25

Li-Ion Battery

PCU

PFLDIU

BCRB

PCU

SMU

GYRO

Heat Pipe Network



EPS Block Diagram

26

AOCSP = Attitude and Orbit Control System PcbSADM = Solar Array and Drive MechanismBCR = Battery Charge RegulatorBCRB = Battery Connection Relay BoxBDR = Battery Discharge RegulatorCVICP = power ConVerter data bus Insulation and Core PcbDHP = Distribution and Heater PcbFSMP = Full Step Motor PcbHPDP = High Power Distribution PcbLMU = Li-Ion Management Unit (Li-Ion batteries)MAP = Matrix Acquisition and Command PcbPCU = Power conditionning UnitP/F = PlatformP/L = PayloadPFLDIU = P/F and P/L Distribution and Interface UnitPROP = PROpulsion electronic PcbPYP = Pyrotechnic PcbSMU = Satellite Management UnitSTE = Satellite Test Equipment



Tanks Layout

27

Main Engine

Pressurant (He) Tank

MMH Tank

MON Tank



Data Handling Hardware Block Diagram



OBSW Architecture

29

PROCESSOR(ERC32 or LEON)

HARDWARE INTERFACES(OBDH, 1553B Data Bus Interfaces)

HW DRIVERS

REAL TIME OPERATING SYSTEM(COTS, OUTSOURCED or IN-HOUSE solutions)

PLATFORM SERVICES(Telecommand, Telemetry, Failure Detection and etc.)

AOCS SW Battery Management SW

Thermal Management SW

ON BOARD SOFTWARE ARCHITECTURE

APP

LIC

ATI

ON

SW

OPE

RA

TIN

GSY

STEM



AOCS Harware Block Diagram

30

STR1 STR2 GYRO1 GYRO2

CCUPROPPCB

CSS2CSS1

UPS RW1 RW3RW2 RW4

AOCSPPCB

CSS Electronics

1553

SODERN: 3 axis meas. in inertial frame.

1 Nominal+1 Redundant

TNO/TPD: 4 cells 2 axes.Internally Redundant


HONEYWELL: 3 axis meas. in inertial frame.


TELDIX: 12 Nms each.3 Nominal+1 Redundant



System Level Design Work PerformedMission analysisPropellant budgetMechanical layoutThermal analysisLink budget analysisPower budgetBattery sizingSolar array sizingPointing Budget...



Cooperation and Partnership via FP7We are in the process of establishing:

A strong infrastructure with satellite AITR&D infrastructure: labs & clean rooms

We are capable of communication satellite designA strong technical teamPlans for growth

Ideas for potential projects:General: Ready to offer engineering workGMES ComSat applicationsElectric propulsion projects


Thank You


Documents

Dr. Celal Sami Tüfekci Erdem Demircioğlu Turksat AS...• GEO Communication Satellite • Launch at 2015 • Maneuver life time ‐15 years • Payload • 16 transponders –Ku