• ISRO successfully launched its third and final developmental flight of Small Satellite Launch Vehicle (SSLV-D3) on August 16 whose payloads can be used in applications like satellite-based surveillance, disaster and environmental monitoring, fire detection, volcanic activity among others.

• ISRO had planned for the latest mission to be launched on August 15 at 9.17 am but it was rescheduled for 24 hours later with a 60-minute launch window.

• As the six-hour countdown for the mission concluded, the rocket carrying the primary Earth Observation Satellite EOS-08 lifted off majestically from the first launch pad at the Satish Dhawan Space Centre in Sriharikota, at a pre-fixed time of 9.17 am and later achieved its mission.

• After a flight of about 10-12 minutes, the primary Earth Observation Satellite got separated successfully. Within a few minutes, a SR-O DEMOSAT Satellite developed by Space Kidz India weighing 200 grams also got separated, signalling the mission’s success.

Small Satellite Launch Vehicle (SSLV)

• Small Satellite Launch Vehicle (SSLV) is capable of launching mini, micro or nano satellites (10 to 500 kg mass) into 500 km planar orbit. 

• SSLV is a three-stage launch vehicle with all solid propulsion stages and liquid propulsion based Velocity Trimming Module (VTM) as terminal stage.

• Design drivers of SSLV are low cost, low turn-around time, flexibility in accommodating multiple satellites, launch on demand feasibility, minimal launch infrastructure requirements, etc.

• SSLV-D3 is the third developmental flight of SSLV.

EOS-08 mission

• The primary objectives of the EOS-08 mission include designing and developing a microsatellite, creating payload instruments compatible with the microsatellite bus, and incorporating new technologies required for future operational satellites.

Built on the Microsat/IMS-1 bus, EOS-08 carries three payloads: 

i) Electro Optical Infrared Payload (EOIR)

ii) Global Navigation Satellite System-Reflectometry payload (GNSS-R)

iii) SiC UV Dosimeter.

• The spacecraft has a mission life of one year. It has a mass of  approximately 175.5 kg and generates power of around 420 W. The satellite interfaces with the SSLV-D3/IBL-358 launch vehicle.

• The EOIR payload is designed to capture images in the Mid-Wave IR (MIR) and Long-Wave IR (LWIR) bands, both during the day and night, for applications such as satellite-based surveillance, disaster monitoring, environmental monitoring, fire detection, volcanic activity observation, and industrial and power plant disaster monitoring.

• The GNSS-R payload demonstrates the capability of using GNSS-R-based remote sensing for applications such as ocean surface wind analysis, soil moisture assessment, cryosphere studies over the Himalayan region, flood detection, and inland waterbody detection. 

• The SiC UV Dosimeter monitors UV irradiance at the viewport of the Crew Module in the Gaganyaan Mission and serves as a high-dose alarm sensor for gamma radiation.

• EOS-08 marks a significant advancement in satellite mainframe systems such as an Integrated Avionics system, known as the Communication, Baseband, Storage, and Positioning (CBSP) Package, which combines multiple functions into a single, efficient unit.

• This system is designed with cold redundant systems using commercial off-the-shelf (COTS) components and evaluation boards, supporting up to 400 gb of data storage. 

• Additionally, the satellite includes a structural panel embedded with printed circuit board, an embedded battery, a Micro-DGA (Dual Gimbal Antenna), an M-PAA (Phased Array Antenna), and a flexible solar panel, each serving as key components for onboard technology demonstration.

• Incorporating additional novel schemes, the EOS-08 mission improves satellite technology through X-band data transmission, utilising pulse shaping and Frequency Compensated Modulation (FCM) for X-Band data transmitters.

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