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The YF-75 is a liquid cryogenic rocket engine burning liquid hydrogen and liquid oxygen in a gas generator cycle. It is China's second generation of cryogenic propellant engine, after the YF-73, which it replaced. It is used in a dual engine mount in the H-18 third stage of the Long March 3A, Long March 3B and Long March 3C launch vehicles. Within the…
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engine hydrogen propellant long march yf-73 3b cryogenic oxygen stage gas generator 3a 3c chamber cycle mixture ratio dual mount
| Subject | Predicate | Object | Confidence | Src |
|---|---|---|---|---|
| YF-75 | Associated LV | Long March 3A, Long March 3B and Long March 3C | 1.00 | infobox |
| YF-75 | Burn time | 470 seconds (7.8 min) | 1.00 | infobox |
| YF-75 | Chamber | 1 | 1.00 | infobox |
| YF-75 | Chamber pressure | 3.76 MPa (37.6 bar) | 1.00 | infobox |
| YF-75 | Country of origin | China | 1.00 | infobox |
| YF-75 | Cycle | Gas-generator | 1.00 | infobox |
| YF-75 | Designer | Beijing Aerospace Propulsion Institute | 1.00 | infobox |
| YF-75 | Diameter | 1.5 metres (4 ft 11 in) | 1.00 | infobox |
| YF-75 | Dry mass | 550 kilograms (1,210 lb) | 1.00 | infobox |
| YF-75 | First flight | 1994-02-08 | 1.00 | infobox |
| YF-75 | Length | 2.8 metres (9 ft 2 in) | 1.00 | infobox |
| YF-75 | Manufacturer | China Academy of Launch Vehicle Technology (CALT) | 1.00 | infobox |
| YF-75 | Mixture ratio | 5.1 (adjustable) | 1.00 | infobox |
| YF-75 | Nozzle ratio | 80 | 1.00 | infobox |
| YF-75 | Predecessor | YF-73 | 1.00 | infobox |
| YF-75 | Propellant | Liquid oxygen / Liquid hydrogen | 1.00 | infobox |
| YF-75 | Specific impulse, vacuum | 438 seconds (4.30 km/s) | 1.00 | infobox |
| YF-75 | Status | In service | 1.00 | infobox |
| YF-75 | Successor | YF-75D | 1.00 | infobox |
| YF-75 | Thrust, vacuum | 78.45 kilonewtons (17,640 lbf) | 1.00 | infobox |
| YF-75 | is a | liquid cryogenic rocket engine burning liquid hydrogen and liquid oxygen in a gas generator cycle | 0.90 | text |
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