EOS-07 satellite in deployed configuration, rendering
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| Names | EOS-07 / Microsat-2B |
|---|---|
| Mission type | Earth observation |
| Operator | ISRO |
| COSPAR ID | 2023-019A |
| SATCAT no. | 55562 |
| Website | https://www.isro.gov.in/ |
| Mission duration | Planned: ≈1 year Elapsed: 1 year, 5 months, 2 days |
| Spacecraft properties | |
| Spacecraft | EOS-07 |
| Manufacturer | Indian Space Research Organisation |
| Launch mass | 157 kg (346 lb) |
| Power | 357 watts |
| Start of mission | |
| Launch date | 10 February 2023 03:48 UTC |
| Rocket | Small Satellite Launch Vehicle, (SSLV-D2) |
| Launch site | Satish Dhawan Space Centre, First Launch Pad (FLP) |
| Contractor | Indian Space Research Organisation |
| Entered service | 10 February 2023 |
| Orbital parameters | |
| Reference system | Geocentric orbit |
| Regime | Polar orbit |
| Perigee altitude | 450 km (280 mi) |
| Apogee altitude | 450 km (280 mi) |
| Inclination | 37.2° |
| Period | minutes |
| Instruments | |
| mmWave Humidity Sounder (MHS), Spectrum Monitoring Payload (SMP) | |
EOS–07 (formerly known as 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]
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 32 Gb. 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.
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 2 Mbit/s.
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