LAUNCH TIME | June 30, 2022 - 14:30 |
LAUNCH PROVIDER | Indian Space Research Organization (ISRO) |
CUSTOMER | - |
ROCKET | PSLV-CA |
LAUNCH SITE | Second Launch Pad, Satish Dhawan Space Centre, Republic of India |
PAYLOAD MASS | 523 Kg |
DESTINATION | Low Earth Orbit |
LANDING SITE | It will crash into the Indian Ocean |
WEATHER | - |
The Indian Space Research Organization's Polar Satellite Launch Vehicle (PSLV) will launch the DS-EO mission and other missions from the second launch pad at the Satish Dhawan Space Center. The rocket will carry the Earth observation satellite DS-EO into orbit, along with two secondary payloads: the NeuSAR and SCOOB-I satellites.
What are DS-EO, NeuSAR and SCOOB-I?
The DS-EO is an electro-optical and multispectral satellite for Earth observation. The satellite has a mass of 365 kg and aims to provide color images with a resolution of 0.5 m for land classification. It will help with humanitarian assistance and disaster relief.
NeuSAR has a mass of 155 kg and has a SAR instrument, capable of providing images of the earth 24 hours a day in all weather conditions.
SCOOB-I has a mass of 2.8 kg and was developed by Nanyang Technological University. It is the first satellite built as part of a Student Satellite Series (S3-I) student training program.
PSLV-CA
For this mission ISRO will use the Core Alone variant of the PSLV.
The first stage The first stage is 20m high and 2.8m wide. It uses an S139 solid rocket engine powered by a hydroxyl terminated polybutadiene (HTPB) propellant. It has a maximum thrust of 4800 kN.
The second stage The second stage is 12.8m high and 2.8m wide. It uses a Vikas engine powered by asymmetric dimethylhydrazine (UDMH) as fuel and N 2 O 4 as oxidant.
The third stage The third stage is 3.6m high and 2m wide. It uses solid HTPB propellant, similar to the first stage, with an S-7 engine. The maximum thrust in this stage is 240 kN.
The fourth stage The last stage is 3m high and 1.3m wide. This is a liquid-powered stage, using monomethylhydrazine (MMH) for the fuel and mixed nitrogen oxides (MON) for the oxidizer with two PS-4 engines, each producing 6.6 kN of thrust.