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![]() A Delta II rocket launches from Cape Canaveral carrying the Dawn spacecraft. | |
Function | Launch vehicle |
---|---|
Manufacturer |
|
Country of origin | United States |
Cost per launch | |
Size | |
Height | 38.9 m (128 ft)[3] |
Diameter | 2.44 m (8 ft) |
Mass | 152,000–286,100 kg (335,100–630,700 lb)[3][4] |
Capacity | |
Payload to LEO | |
Orbital inclination | 28.7° |
Mass | 2,776–6,107 kg (6,120–13,464 lb)[4] |
Payload to GTO | |
Orbital inclination | 28.7° |
Mass | 929–2,180 kg (2,048–4,806 lb)[4] |
Payload to SSO | |
Orbital inclination | 98.7° |
Mass | 1,652–3,182 kg (3,642–7,015 lb)[4] |
Launch history | |
Status | Retired |
Launch sites | |
Total launches |
|
Success(es) |
|
Failure(s) | 1 (Delta 7000) |
Partial failure(s) | 1 (Delta 7000) |
First flight |
|
Last flight | |
Boosters (Delta 6000) – Castor 4A | |
No. boosters | 9 |
Height | 9.2 m (30 ft)[5] |
Diameter | 1.02 m (3 ft 4 in) |
Empty mass | 1,457 kg (3,212 lb) |
Gross mass | 11,578 kg (25,525 lb) |
Powered by | Solid |
Maximum thrust | 478.3 kN (107,500 lbf) |
Specific impulse | 266 s (2.61 km/s) |
Burn time | 56 seconds |
Propellant | HTPB |
Boosters (Delta 7000) – GEM 40 | |
No. boosters | 3, 4, or 9 |
Height | 13.0 m (42.7 ft)[4] |
Diameter | 1.02 m (3 ft 4 in) |
Empty mass | 1,315 kg (2,899 lb) |
Gross mass | 13,080 kg (28,840 lb) |
Powered by | Solid |
Maximum thrust |
|
Specific impulse |
|
Burn time | 64 seconds |
Propellant | AP / HTPB / Al |
Boosters (Delta 7000 Heavy) – GEM 46 | |
No. boosters | 9 |
Height | 14.7 m (48 ft)[4] |
Diameter | 1.17 m (3 ft 10 in) |
Empty mass | 2,035 kg (4,486 lb) |
Gross mass | 19,040 kg (41,980 lb) |
Powered by | Solid |
Maximum thrust |
|
Specific impulse |
|
Burn time | 76 seconds or 178.03 seconds after liftoff |
Propellant | APCP / HTPB / Al |
First stage – Thor/Delta XLT(-C) | |
Height | 26.1 m (86 ft)[4] |
Diameter | 2.44 m (8 ft 0 in) |
Empty mass | 5,680 kg (12,520 lb) |
Gross mass | 101,800 kg (224,400 lb) |
Powered by | 1 × RS-27 (6000 series) or RS-27A (7000 series) [6] |
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 | |
Height | 6 m (20 ft)[4] |
Diameter | 2.44 m (8 ft 0 in) |
Empty mass | 950 kg (2,090 lb) |
Gross mass | 6,954 kg (15,331 lb) |
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 | 1 × Star 48B |
Maximum thrust | 66 kN (15,000 lbf) |
Specific impulse | 286 s (2.80 km/s) |
Burn time | 87 seconds |
Propellant | HTPB |
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, derived directly from the Delta 3000, and entered service in 1989. There were two main variants, the Delta 6000 and Delta 7000, with the latter also having "Light" and "Heavy" subvariants. During its career, Delta II flew several notable payloads, including 24 Global Positioning System (GPS) Block II satellites, several dozen NASA payloads, and 60 Iridium communication satellites. 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.[3] In the late 1990s, Delta II was developed further into the unsuccessful Delta III, which was in turn developed into the more capable and successful Delta IV, though the latter shares little heritage with the original Thor and Delta rockets.
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