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The Small Satellite launch vehicle is an expendable small-lift capacity launch vehicle designed and built by ISRO.
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| Decade | Successful | Partial success | Failure | Total |
|---|---|---|---|---|
| 2020s | 2 | 0 | 1 | 3 |
| Flight No. | Date and
time (UTC) |
Rocket, configuration |
Launch site | Payload | Payload mass | Orbit | User | Launch
outcome |
|---|---|---|---|---|---|---|---|---|
| D1 | 7 August 2022 03:48 |
SSLV | First |  EOS 02 AzaadiSAT[1] |
143 kg | LEO (intended)
TAO (achieved) |
ISRO | Failure |
| The first developmental flight of SSLV. The mission target was a circular orbit of altitude 356.2 km with 37.2° inclination. The mission carried two satellite payloads. The 135 kg EOS 02, an Earth observation satellite and the 8 kg AzaadiSAT CubeSat.[2][3][4]
Due to sensor failure coupled with shortcomings of onboard software, the stage as well as the two satellite payloads were injected into an unstable transatmospheric Earth orbit measuring 356×76 km and subsequently destroyed upon reentry. According to S. Somanath, an anomaly lasting 2 seconds in one of the accelerometers during second stage separation initiated salvage mode by onboard computer. Guidance, navigation, and control software switched from 'closed loop guidance' where it received real-time feedback from all sensors to an 'open loop guidance' where accelerometer data gets isolated and a predetermined path is followed.[5] This resulted in velocity shortfall from the required 7.3 km/s to 7.2 km/s. Being in salvage mode, Velocity-Trimming Module didn't rectify this shortfall which led to mission failure. | ||||||||
| D2 | 10 February 2023 03:48 [6][7][8] |
SSLV | First | EOS-07 Janus-1 AzaadiSAT-2 |
156.3 kg 11.5 kg 7.3 kg Total = 334 kg |
LEO | ISRO | Success |
| Second developmental flight of the SSLV.[9][10][11] The purpose of SSLV-D2 is to launch EOS-07, Janus-1 and AzaadiSAT-2 into a 450-kilometer circular orbit and showcase the in-flight performance of the SSLV vehicle systems.[12] According to SSLV-D1 fault evaluation study, six onboard accelerometers detected vibrations that were longer in duration and more intense during the second stage of separation. In order to ensure that this problem doesn't occur again, the second stage detachment system in SSLV-D2 was modified to reduce vibrations. Furthermore, the system was redesigned to navigate utilizing NavIC data and readings will now be monitored for a longer time before entering rescue mode.[13] The separation mechanism, the equipment bay, and the on-board system for identifying malfunctioning sensors were further modified and five new pieces of hardware were installed. The electronics in SSLV-D2 worked successfully, as did the launch vehicle's new, affordable guidance and navigation system.[14] | ||||||||
| D3 | 16 August 2024 03:47 [15][16] |
SSLV | First | EOS-08 SR-0 DEMOSAT |
175.5 kg 0.2 kg Total = 175.7 kg |
LEO | ISRO | Success |
| Third developmental flight and completion of SSLV Development Project.[17][18] The development team will continue to search for specific operational activities in the VTM stage before ISRO supplies the industry with SSLV technology for serial production. Any necessary fine-tuning will be finished prior to the technology transfer.[19][20] Repeatable flight performance of the SSLV vehicle systems has also been demonstrated by SSLV-D3.[21] | ||||||||
| Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Orbit | User |
|---|---|---|---|---|---|
| NET 2025[22] | SSLV | SHAR | TBD PARIKSHIT |
ISRO | |
| Flight S1. First serial flight of the SSLV.[16] | |||||
| NET 2025[22] | SSLV | SHAR | TBD Azista60° |
ISRO | |
| Flight S2.[16] | |||||
| 2026[23] | SSLV | SHAR |  Optimus |
LEO | Space Machines Company |
| Space MAITRI (Mission for Australia-India's Technology, Research and Innovation). First dedicated commercial SSLV launch. | |||||
| TBD[24] | SSLV | SHAR | BlackSky Global-5, 6, and two others |
LEO | Spaceflight Industries |
| Manifested on a future SSLV commercial flight, four 56 kg Blacksky Global satellites to ~500 km circular orbit with 50° inclination.[25][26] | |||||
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