Analysis of information sources in references of the Wikipedia article "Small Satellite Launch Vehicle" in English language version.
The first static test of SS1 solid motor was conducted and the performance of SS1 ignition system, propellant system and Flex Nozzle Control (FNC) system was evaluated. Various design modifications have been incorporated to resolve the anomalies observed in the first static test (…)
It may be specifically noted that process toolings of composite motor case for 2nd stage of SSLV is interchangeable with composite motor case for 3rd stage of PSLV to maximum extent.
The proposed systems will be used as a part of new commanding requirement for Small Satellite Launch Vehicle (SSLV) Launch Complex (SLC) Site at Kulasekarapatnam, Tamilnadu.
REQUEST FOR PROPOSAL (RFP) FOR SUPPLY, INSTALLATION AND COMMISSIONING OF RAIL TRACK FOR SLC PROJECT
REQUEST FOR PROPOSAL (RFP) FOR PROCUREMENT, MANUFACTURE, SUPPLY, TESTING and COMMISIONING [sic] OF SELF PROPELLED UNITS FOR SLC
RFP document for Supply of Stainless Steel Tanks
By appropriate choice from among the solid propellant stages available with ISRO and DRDO, a launch vehicle could be configured and designated Small Satellite Launch Vehicle (SSLV-1). The performance of SSLV-1 was estimated using the in house developed trajectory-modelling programme QuoVadis. The performance runs show that SSLV-1 is capable of putting a 350 kg satellite in a polar orbit of 511 km x 497 km orbit and a 400 kg satellite in an orbit of 425 x 401 km (higher payloads are possible in equatorial orbit). This payload capability allows the launch of microsatellites with optical imaging and radar imaging payloads as well as individual intelligence satellites. Satellite life for the 400 kg mass satellite may be short in the 400 km orbit.
The development of SSLV is in the final stages and the first developmental flight of SSLV is targeted during the first quarter of 2022. The Government has sanctioned a total cost of Rs.169.07 Crores for the development project including the development & qualification of the vehicle systems and the flight demonstration through three development flights (SSLV-D1, SSLV-D2 & SSLV-D3)
According to a former ISRO scientist, the VTM can correct for a velocity shortfall of up to 172 metres/s. The rocket used for SSLV-D1 was a 34 m tall, 2 m diameter vehicle having a lift-off mass of 120 t.
By appropriate choice from among the solid propellant stages available with ISRO and DRDO, a launch vehicle could be configured and designated Small Satellite Launch Vehicle (SSLV-1). The performance of SSLV-1 was estimated using the in house developed trajectory-modelling programme QuoVadis. The performance runs show that SSLV-1 is capable of putting a 350 kg satellite in a polar orbit of 511 km x 497 km orbit and a 400 kg satellite in an orbit of 425 x 401 km (higher payloads are possible in equatorial orbit). This payload capability allows the launch of microsatellites with optical imaging and radar imaging payloads as well as individual intelligence satellites. Satellite life for the 400 kg mass satellite may be short in the 400 km orbit.
The first static test of SS1 solid motor was conducted and the performance of SS1 ignition system, propellant system and Flex Nozzle Control (FNC) system was evaluated. Various design modifications have been incorporated to resolve the anomalies observed in the first static test (…)
It may be specifically noted that process toolings of composite motor case for 2nd stage of SSLV is interchangeable with composite motor case for 3rd stage of PSLV to maximum extent.
The proposed systems will be used as a part of new commanding requirement for Small Satellite Launch Vehicle (SSLV) Launch Complex (SLC) Site at Kulasekarapatnam, Tamilnadu.
REQUEST FOR PROPOSAL (RFP) FOR SUPPLY, INSTALLATION AND COMMISSIONING OF RAIL TRACK FOR SLC PROJECT
REQUEST FOR PROPOSAL (RFP) FOR PROCUREMENT, MANUFACTURE, SUPPLY, TESTING and COMMISIONING [sic] OF SELF PROPELLED UNITS FOR SLC
RFP document for Supply of Stainless Steel Tanks
Two solid stages are new, fully developed. That is SS1 with 85-90 tonnes and SS3 with 4.5 tonnes whereas SS2 is almost identical to the HPS3 of PSLV.
