| Country of origin | China |
|---|---|
| Date | 1958-1969 |
| Designer | Academy of Aerospace Liquid Propulsion Technology, Ren Xinmin, Mo Tso-hsin, Zhang Guitian |
| AssociatedLV | DF-3A,DF-4 andLong March 1 |
| Predecessor | С2.1100 |
| Successor | YF-20 |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | N2O4 /UDMH |
| Cycle | Gas Generator |
| Configuration | |
| Chamber | 1 |
| Nozzle ratio | 10 |
| Performance | |
| Thrust, vacuum | 303.6 kN (68,300 lbf) |
| Thrust, sea-level | 275.3 kN (61,900 lbf) |
| Chamberpressure | 7.1 MPa (1,030 psi) |
| Specific impulse, vacuum | 267.4 seconds (2.622 km/s) |
| Specific impulse, sea-level | 242.5 seconds (2.378 km/s) |
| Burn time | 140s |
| Dimensions | |
| Diameter | 56 centimetres (22 in) |
| Used in | |
| DF-3A,DF-4 andLong March 1 first stage. | |
| References | |
| References | [1][2][3][4][5][6][7][8] |
TheYF-1 was aChineseliquidrocket engine burningN2O4 andUDMH in agas generator cycle. It is a basic engine which when mounted in a four engine module forms theYF-2. It was used as the basis for developing a high altitude version known as theYF-3.[2][9]
Some authors state that it was a direct copy of С.2.1100/С.2.1150La-350 booster engine developed byIsayevOKB-2 (NII-88).[10] What is known is that the engine development had great trouble with combustion instabilities and it took a long time to have a reliable combustion.
The basic engine has been used since theDF-3 rocket and has been the main propulsion of theLong March 1 orbital launch vehicles.[2]
While the basic engine was used multiple times, it was only used as a single engine for booster application. It is usually bundled into modules of multiple engines.
The relevant modules for first stage application are:
| Liquid fuel |
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| Solid fuel |
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