CZ-11 Space Launch Vehicle
| Development unit | China Academy of Launch Vehicle Technology |
| First flight time | September 25, 2015 |
| Rocket stages | four |
| Propellant | Hydroxyl-terminated polybutadiene ( HTPB ) composite solid propellant |
| Rocket length/m | 20.8 |
| Fairing diameter/m | 1.6/2.0 |
| Maximum diameter/m | 2.0 |
| Takeoff weight/ton | 57.6 |
| Takeoff thrust/ton | 120 |
| 700km SSO carrying capacity | 350kg - 400kg to Sun-synchronous orbit |
| LEO carrying capacity | 700kg to Low Earth orbit |
| Remarks | The Chang 11 project team used the flight data of the first two rockets to find the design margin, Under the premise of ensuring reliability, some products have been cancelled, which has made the rocket carrying capacity Increased by 50 kg. |
| Rocket Stagel 1 parameters | |
| Diameter/m | 2.0 |
| Takeoff mass/ton | 39.8 |
| Propellant mass/ton | 35 |
| Maximum thrust/kN | 1200 |
| Sea level specific impulse/sec | 248 |
| Working time/second | Approximately 72 |
| Shell material | steel |
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