Delta II
Delta II was an expendable launch system, originally designed and built by McDonnell Douglas, and sometimes known as the Thorad Delta 1. Delta II was part of the Delta rocket family and entered service in 1989. Delta II vehicles included the Delta 6000, and the two later Delta 7000 variants ("Light" and "Heavy"). The rocket flew its final mission ICESat-2 on 15 September 2018, earning the launch vehicle a streak of 100 successful missions in a row, with the last failure being GPS IIR-1 in 1997.
A Delta II rocket launches from Cape Canaveral carrying the Dawn spacecraft. | |
| Function | Launch vehicle |
|---|---|
| Manufacturer | United Launch Alliance |
| Country of origin | United States |
| Cost per launch | US$51 million in 1987 (7920-10 model) US$137 million in 2018 before retirement |
| Size | |
| Height | 38.9 m (128 ft) |
| Diameter | 2.44 m (8 ft 0 in) |
| Mass | 152,000–286,000 kg (335,000–631,000 lb) |
| Capacity | |
| Payload to low Earth orbit | |
| Mass | 2,800–6,140 kg (6,170–13,540 lb) |
| Payload to geostationary transfer orbit | |
| Mass | 1,140–2,190 kg (2,510–4,830 lb) |
| Payload to heliocentric orbit | |
| Mass | 806–1,519 kg (1,777–3,349 lb) |
| Launch history | |
| Status | Retired |
| Launch sites | Cape Canaveral, SLC-17 Vandenberg Air Force Base, SLC-2W |
| Total launches | 155 Delta 6000: 17 Delta 7000: 132 Delta 7000H: 6 |
| Success(es) | 153 Delta 6000: 17 Delta 7000: 130 Delta 7000H: 6 |
| Failure(s) | 1 (Delta 7000) |
| Partial failure(s) | 1 (Delta 7000) |
| First flight |
|
| Last flight | |
| Boosters (6000 Series) – Castor 4A | |
| No. boosters | 9 |
| Powered by | Solid |
| Maximum thrust | 478 kN (107,000 lbf) |
| Specific impulse | 266 s (2.61 km/s) |
| Burn time | 56 seconds |
| Boosters (7000 Series) – GEM 40 | |
| No. boosters | 3, 4, or 9 |
| Powered by | Solid |
| Maximum thrust | 492.9 kN (110,800 lbf) |
| Specific impulse | 274 s (2.69 km/s) |
| Burn time | 64 seconds |
| Boosters (7000 Heavy) – GEM 46 | |
| No. boosters | 9 |
| Powered by | Solid |
| Maximum thrust | 628.3 kN (141,200 lbf) |
| Specific impulse | 278 s (2.73 km/s) |
| Burn time | 76 seconds or 178.03 seconds after lift off |
| First stage – Thor/Delta XLT(-C) | |
| Powered by | 1 RS-27 (6000 series) or RS-27A (7000 series) |
| Maximum thrust | 1,054 kN (237,000 lbf) |
| Specific impulse | 302 s (2.96 km/s) |
| Burn time | 260.5 seconds |
| Propellant | RP-1 / LOX |
| Second stage – Delta K | |
| Powered by | 1 AJ10-118K |
| Maximum thrust | 43.6 kN (9,800 lbf) |
| Specific impulse | 319 s (3.13 km/s) |
| Burn time | 431 seconds |
| Propellant | N2O4 / Aerozine 50 |
| Third stage – PAM-D (optional) | |
| Powered by | Star 48B |
| Maximum thrust | 66 kN (15,000 lbf) |
| Specific impulse | 286 s (2.80 km/s) |
| Burn time | 87 seconds |
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