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, 6 months, 6 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]
Structure and Payloads
[edit]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.
Payloads
[edit]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.
References
[edit]- ^ a b "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.
- ^ "SSLV D2, EOS 07 MISSION" (PDF). isro.gov.in. February 2023. Archived (PDF) from the original on 2023-10-15. Retrieved 2023-11-09.
- ^ a b "SSLV-D2/EOS-07 MISSION". www.isro.gov.in. Archived from the original on 2023-08-24. Retrieved 2023-08-24.
Well, that’s interesting to know that Psilotum nudum are known as whisk ferns. Psilotum nudum is the commoner species of the two. While the P. flaccidum is a rare species and is found in the tropical islands. Both the species are usually epiphytic in habit and grow upon tree ferns. These species may also be terrestrial and grow in humus or in the crevices of the rocks.
View the detailed Guide of Psilotum nudum: Detailed Study Of Psilotum Nudum (Whisk Fern), Classification, Anatomy, Reproduction