EOS-07
EOS-07 satellite in deployed configuration, rendering
NamesMicrosat-2B, EOS-07
Mission typeEarth observation
OperatorISRO
COSPAR ID2023-019A
SATCAT no.55562
Websitehttps://www.isro.gov.in/
Mission duration≈1 year (planned)
Spacecraft properties
SpacecraftEOS-07
ManufacturerIndian Space Research Organisation
Launch mass157 kg (346 lb)
Power357 watts
Start of mission
Launch date10 February 2023 03:48 UTC
RocketSmall Satellite Launch Vehicle, (SSLV-D2)
Launch siteSatish Dhawan Space Centre, First Launch Pad (FLP)
ContractorIndian Space Research Organisation
Entered service10 February 2023
Orbital parameters
Reference systemGeocentric orbit
RegimePolar orbit
Perigee altitude450 km (280 mi)
Apogee altitude450 km (280 mi)
Inclination37.2°
Periodminutes
Instruments
mmWave Humidity Sounder (MHS), Spectrum Monitoring Payload (SMP)
 


EOS–07 or Microsat-2B is an Earth observation satellite developed by the Indian Space Research Organisation (ISRO) and launched during the SSLV-D2 mission, the first successful mission of the SSLV rocket.[1] It's a minisatellite designed to accommodate new technology payloads in a quick turn-around time.[2][1]

Structure and Payloads

It has a cubical structure consisting of six Honeycomb structures.[3] Top and Bottom decks are connected with 4 staggered cross ribs and 4 closing vertical decks. The structure includes a Starsensor (mSS), 4π Sunsensor (4πSS), micro-Inertial Reference Unit (mIRU), and a Magnetometer. It has a passive thermal control system with Optical Solar Reflector, Multi-Layer Insulation, Thermal interface material, etc.[3] It has 1N Thrusters (1Nms), 0.02Nm Reaction Wheels, and 20 A.m2 Magnetic Torquers powered by 5 kg of hydrazine fuel. The altitude and orbital control system (AOCS) has a pointing accuracy of – 0.1° (3σ) and a drift rate of – 7.5e-4°/s. For power generation, it has solar panels which will be deployed using Frangi bolt actuators. The panels have a power generation of 357 watts. It also has a Li-ion battery of 27.2 Ah capacity. The onboard computer has a MIL STD 1553B protocol for interfacing with other sub-systems. It has a data storage capacity of 32Gb. The RF system uses S-Band Telemetry Transmitters, S-Band Telecommand Receiver, 12 channel SPS. It has a 15m location accuracy, 0.15 m/s velocity accuracy and an X-Band Data Transmitter.

Payloads

It has two payloads; mmWave Humidity Sounder (MHS) and a Spectrum Monitoring Payload. MHS has 6 water vapor sounding channels with 50rpm scan rate. It weighs 26 kg and requires 55 watt power. The Spectrum Monitoring Payload weighs 13 kg, requires a power~ of 35W, and has a data rate of 2Mbit/s.

References

  1. 1 2 "Successful flight of Small Satellite Launch Vehicle (SSLV)". Press Information Bureau. 10 February 2023. Archived from the original on 13 February 2023. Retrieved 14 February 2023.
  2. ↑ "SSLV D2, EOS 07 MISSION" (PDF). isro.gov.in. February 2023. Archived (PDF) from the original on 2023-10-15. Retrieved 2023-11-09.
  3. 1 2 "SSLV-D2/EOS-07 MISSION". www.isro.gov.in. Archived from the original on 2023-08-24. Retrieved 2023-08-24.
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