Agnibaan
| Function | Launch Vehicle |
|---|---|
| Manufacturer | AgniKul Cosmos |
| Country of origin | India |
| Size | |
| Height | 18 m (59 ft) |
| Diameter | 1.3 m (4 ft 3 in) |
| Mass | 14,000 kg (31,000 lb) |
| Stages | 2-3 |
| Capacity | |
| Payload to LEO | Altitude 700 km (430 mi)
Orbital inclination 45.0° Mass 100 kg (220 lb) |
| Launch history | |
| Status | Under Development |
| First stage | |
| Engines | 4/5/6/7 × Agnilet (Customizable) |
| Thrust | 140 kN (sea level) |
| Burn time | 285 sec |
| Propellant | LOX/ RP-1 |
| Second stage | |
| Engines | 1 × Agnilet |
| Thrust | 25 kN (sea level) |
| Burn time | 355 sec |
| Propellant | LOX / RP-1 |
| Third stage | |
| Engines | 1 × Agnilet |
| Propellant | LOX / RP-1 |
Agnibaan (Sanskrit, ISO: Agni 'Fire', Bāṇa 'Arrow', lit. 'Arrow of Fire') is a three-stage small-lift launch system currently under development, produced by AgniKul Cosmos in Chennai, Tamil Nadu, India. It is capable of placing a 100 kg (220 lb) satellite into a 700 km (430 mi) orbit. The rocket will be 18 meters long with a diameter of 1.3 meters and a lift-off mass of 14,000 kg (31,000 lb). The first stage is powered by seven Agnilet engines. The second stage is powered by the same Agnilet engine which will have a larger nozzle than the sea level nozzle to optimize it for vacuum.