Indostar-1, also known as Cakrawarta-1, is the Orbital Science Corporations's first GEO satellite. Originally, it is a STAR-Class bus built by CTA Space Systems.
Mission: Direct Broadcast Satellite
Coverage: Indonesia
MASS & DIMENSIONS
Total mass at launch: 1385 kg
BOL mass in GEO: 802 kg
Dimensions on orbit: W = 16.1 m (solar array tip-to-tip), D = 2.49 m, H = 3.94 m (incl. motor nozzle)
PAYLOAD
Transponder: 5 x 70 W + 2 spares TWTA (Travelling Wave Tube Amplifier)
Bandwidth: 24 MHz each transmitter (center-to-center spacing 30 MHz)
P/L uplink freq. : 8,120 to 8,270 MHz (X-Band)
P/L downlink freq. : 2,520 to 2,670 MHz (S-Band)
EIRP: 44.2 dBW minimum over the coverage area
PROPULSIONS
AKM (Apogee Kick Motor): STAR 30E Solid Rocket Motor
LPS (Liquid Propellans Systems) for station keeping: Monopropellant (Hydrazyne) Blowdown System
ELECTRICAL POWER
Type: Sun-lit regulated (using digital shunt regulator) direct energy transfer system
Bus voltage: Sunlight (36.5 +/- 0.5 Vdc), Eclipse (35-24 Vdc), max overvoltage (39.1 Vdc), min voltage (22 Vdc)
Solar array: Two deployable wings, each with three split panels, with a total surface 9.45 m2)
Batteries: 2 x 22 cells NiH2 batteries, each with 52 AH capacity
ATTITUDE CONTROL
Type: 3-axis pitch bias momentum system
Sensors: Sun sensors, earth sensors, and gyro
Actuators: redundant MWA (Momentum Wheel Assemblies) and redundant MTA (Magnetic Torque Assemblies) along roll and yaw axes
COMMAND AND DATA HANDLING
Data bus: MIL-STD 1553 data bus (redundant)
Flight computer: Honeywell Space Computer (1750 processor) fully redundant and unique RTs (Remote Terminals) for each subsystem which interfae with specific equipments and the 1553 bus
References:
Indostar-1 Control Operations Handbook
Indostar-1 Early Orbit Operations (available on https://www.researchgate.net/publication/298553344_Indostar-1_early_orbit_operations)
Mission: Direct Broadcast Satellite
Coverage: Indonesia
MASS & DIMENSIONS
Total mass at launch: 1385 kg
BOL mass in GEO: 802 kg
Dimensions on orbit: W = 16.1 m (solar array tip-to-tip), D = 2.49 m, H = 3.94 m (incl. motor nozzle)
PAYLOAD
Transponder: 5 x 70 W + 2 spares TWTA (Travelling Wave Tube Amplifier)
Bandwidth: 24 MHz each transmitter (center-to-center spacing 30 MHz)
P/L uplink freq. : 8,120 to 8,270 MHz (X-Band)
P/L downlink freq. : 2,520 to 2,670 MHz (S-Band)
EIRP: 44.2 dBW minimum over the coverage area
PROPULSIONS
AKM (Apogee Kick Motor): STAR 30E Solid Rocket Motor
LPS (Liquid Propellans Systems) for station keeping: Monopropellant (Hydrazyne) Blowdown System
ELECTRICAL POWER
Type: Sun-lit regulated (using digital shunt regulator) direct energy transfer system
Bus voltage: Sunlight (36.5 +/- 0.5 Vdc), Eclipse (35-24 Vdc), max overvoltage (39.1 Vdc), min voltage (22 Vdc)
Solar array: Two deployable wings, each with three split panels, with a total surface 9.45 m2)
Batteries: 2 x 22 cells NiH2 batteries, each with 52 AH capacity
ATTITUDE CONTROL
Type: 3-axis pitch bias momentum system
Sensors: Sun sensors, earth sensors, and gyro
Actuators: redundant MWA (Momentum Wheel Assemblies) and redundant MTA (Magnetic Torque Assemblies) along roll and yaw axes
COMMAND AND DATA HANDLING
Data bus: MIL-STD 1553 data bus (redundant)
Flight computer: Honeywell Space Computer (1750 processor) fully redundant and unique RTs (Remote Terminals) for each subsystem which interfae with specific equipments and the 1553 bus
References:
Indostar-1 Control Operations Handbook
Indostar-1 Early Orbit Operations (available on https://www.researchgate.net/publication/298553344_Indostar-1_early_orbit_operations)
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