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Long March 1D is the improved version of Long March 1, mainly for the thrustor of stage 1, from 1020 kilonewtons to 1101.2 kilonewtons, also improved the performance for stage 2 and stage 3. The improved Long March 1D can launch variant of LEO satellite, the 卫星入轨姿态既可以是自旋、也可以是三轴稳定状态。 (to be translated...) The first flight in November 1997 was successful.
[edit] Technical specifications
| The rocket |
Stage 1 |
Stage 2 |
Stage 3 |
*Stages: 3
- Length 28.220 m
- 翼展 3.810 m
- Liftoff mass 81,075 kg
- Liftoff thrust 1101.2 kN
- Thrust-to-mass 13.6 N/kg
- Payload
- 930 kg (自旋)
- 750 kg(三轴稳定)
(300 km circular, inclination 57 deg)
- Orbit insertion accuracy
- diff of ecc 0.001 to 0.005
- diff of inc < 0.3度
(300～1000 km circular orbit)
|
- Length 19.735 m
- Diameter 2.250 m
- Mass of the stage 65,040 kg
- Mass of the structure 4,080 kg
- Mass of the fuel 60,860 kg
- Booster YF-2A
- Fuel HNO3-27S/UDMH
- Liftoff thrust (sealevel) 1101.2 kN
- Specific impulse: 2378 N·s/kg
- Burn time ~132 s
|
- Length 6.037 m
- Diameter 2.250 m
- Stage mass 13,490 kg
- Structure mass 1,100 kg
- Fuel mass 12,380 kg
- Booster YF-40 (two boosters)
- Fuel N2O4/UDMH
- Thrust in vacuum 100.86 kN
- Specific impulse 2981.2 N·s/kg
- Burn time 360 s
|
- Length: 1.696 m
- Diameter: 2.054 m
- Stage mass 1,315 kg
- Structure mass 523 kg
- Fuel mass 792 kg
-
- liquid 147 kg
- solid 645 kg
- Solid rocket booster: FG-36
|
[edit] Reference
- Data from Aerospace China magazine
[edit] External links
