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Changzheng 7
The Changzheng 7 (CZ-7, or " Long March 7") [1] is the medium-lift variant in China’s new-generation orbital launch vehicle family, using the 3.35m-diameter module as its core vehicle. The rocket is intended as a successor to all Changzheng 2, 3 and 4 series launch vehicles currently in use, with much improved reliability, flexibility, and adaptability. The primary contractor of the launch vehicle is CALT, and the first launch of the rocket is expected to take place in 2014~2015.
The core vehicle of the CZ-7 is a two-stage rocket 3.35m in diameter. The first-stage uses a K3-1 module powered by two YF-100 engines burning the LOX/Kerosene propellant. The stage has a gross mass of 147t and a lift-off thrust of 2,680kN. The second-stage uses a K3-2 module powered by four YF-115 engines that also burn the LOX/Kerosene propellant. The vehicle can be attached with two or four 2.25m-diameter K2-1 modules as strap-on boosters, each powered by a single YF-100 engine.
The CZ-7 is expected to succeed the CZ-2F for the launch of Shenzhou spacecraft and the unmanned cargo resupply ship to the space station. It is also likely going to replace all existing medium-lift launch vehicles such as CZ-2C, CZ-2D, CZ-3A/B/C, and CZ-4B/C for LEO, GTO and SSO launch missions.
The launch vehicle will be available in both man-rated and cargo versions. The man-rated version will be capable of delivering 12,500kg payload to LEO. The cargo version will be capable of delivering 13,500kg payload to a 400X200km LEO inclined at 42°, or 5,500kg payload to a 700km SSO. By adding a LOX/LH2 third-stage (two YF-75 engines), the rocket will also be able to support the launch of GEO satellites and lunar probes.
CZ-7 (three-stage configuration)
Specifications
First-stage ( K3-1) |
Booster (K2-1) |
Second-stage (K3-2) |
Third-stage (H3-3) |
|
| Diameter | 3.35 m | 2.25 m | 3.35 m | 5 m |
| Length | 26.28 m | 25.04 m | ||
| Gross mass | 147,000 kg | 69,000 kg | ||
| Propellant mass | 97,500 kg (LOX) 37,500 kg (Kerosene) |
45,500 kg (LOX) 17,500 kg (Kerosene) |
||
| Empty mass | 12,000 kg | 6,000 kg | ||
| Engine | 2X YF-100 | 1X YF-100 | 4X YF-115 | 2X YF-75 |
| Propellant | LOX/Kerosene | LOX/Kerosene | LOX/Kerosene | LOX/LH2 |
| Thrust, vac | 2,680 kN | 1,340 kN | ||
| Isp | ||||
| Burn time |
Notes
- The rocket was originally designated CZ-2F/H.
Last updated: 23 February 2012