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The LR87 is an American liquid-propellant rocket engine that was used on the first stages of Titan intercontinental ballistic missiles and launch vehicles. Composed of twin motors with separate combustion chambers and turbopump machinery, it is considered a single unit and was never flown as a single combustion chamber engine or designed for this. The…
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titan lr87 engine used liquid fuel first chamber thrust rp-1 ii oxygen space use aerojet aerozine 50 lr87-3 launch engines
| Subject | Predicate | Object | Confidence | Src |
|---|---|---|---|---|
| Aerojet LR87 | Application | Main engine | 1.00 | infobox |
| Aerojet LR87 | Associated LV | Titan | 1.00 | infobox |
| Aerojet LR87 | Chamber pressure | 40–59 bar (4,000–5,900 kPa) | 1.00 | infobox |
| Aerojet LR87 | Country of origin | United States | 1.00 | infobox |
| Aerojet LR87 | Cycle | Gas-generator | 1.00 | infobox |
| Aerojet LR87 | Diameter | 1.14 m (3 ft 9 in) | 1.00 | infobox |
| Aerojet LR87 | Dry mass | 839 kg (1,850 lb) | 1.00 | infobox |
| Aerojet LR87 | First flight | 1959 (1959) | 1.00 | infobox |
| Aerojet LR87 | Last flight | 2005 (2005) | 1.00 | infobox |
| Aerojet LR87 | Length | 3.13–3.84 m (10.3–12.6 ft) | 1.00 | infobox |
| Aerojet LR87 | Length | LR87 LH2: 4 m (13 ft) | 1.00 | infobox |
| Aerojet LR87 | Manufacturer | Aerojet | 1.00 | infobox |
| Aerojet LR87 | Propellant | LR87-3: RP-1 / LOX | 1.00 | infobox |
| Aerojet LR87 | Propellant | LR87-5, LR87-7, LR87-9, LR87-11: Aerozine 50 / .mw-parser-output .template-chem2-su{display:inline-block;font-size:80%;line-height:1;vertical-align:-0.35em}.mw-parser-output .te… | 1.00 | infobox |
| Aerojet LR87 | Propellant | LR87 LH2: LH2 / LOX | 1.00 | infobox |
| Aerojet LR87 | Specific impulse, sea-level | 256 s (2.51 km/s) | 1.00 | infobox |
| Aerojet LR87 | Specific impulse, vacuum | 290 s (2.8 km/s) | 1.00 | infobox |
| Aerojet LR87 | Successor | D LR-91 | 1.00 | infobox |
| Aerojet LR87 | Thrust, sea-level | LR87-11: 1,900 kN (430,000 lbf) | 1.00 | infobox |
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