This article is about the rocket. For the submarine, see Delta-class submarine. For the airplane, see Fairey Delta 2.
Delta II
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) [1] US$137 million in 2018 before retirement [2]
Size
Height
38.9 m (128 ft)[3]
Diameter
2.44 m (8 ft 0 in)
Mass
152,000–286,100 kg (335,100–630,700 lb)[3][4]
Capacity
Payload to 185 km (115 mi) low Earth orbit
Orbital inclination
28.7°
Mass
2,776–6,107 kg (6,120–13,464 lb)[4]
Payload to geostationary transfer orbit
Orbital inclination
28.7°
Mass
929–2,180 kg (2,048–4,806 lb)[4]
Payload to 833 km (518 mi) Sun-synchronous orbit
Orbital inclination
98.7°
Mass
1,652–3,182 kg (3,642–7,015 lb)[4]
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
Delta 6000: 14 February 1989 (USA-35)
Delta 7000: 26 November 1990 (USA-66)
Delta 7000H: 7 July 2003 (Opportunity rover)
Last flight
Delta 6000: 24 July 1992 (Geotail)
Delta 7000: 15 September 2018 (ICESat-2)
Delta 7000H: 10 September 2011 (GRAIL)
Stage info
Boosters (6000 Series) – 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 (7000 Series) – 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
Ground-lit: 499.2 kN (112,200 lbf)
Air-lit: 516.2 kN (116,000 lbf)
Specific impulse
Ground-lit: 274.0 s (2.687 km/s)
Air-lit: 283.4 s (2.779 km/s)
Burn time
64 seconds
Propellant
HTPB
Boosters (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
Ground-lit: 608.1 kN (136,700 lbf)
Air-lit: 628.5 kN (141,300 lbf)
Specific impulse
Ground-lit: 224.0 s (2.197 km/s)
Air-lit: 284.0 s (2.785 km/s)
Burn time
76 seconds or 178.03 seconds after liftoff
Propellant
HTPB
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
1xRS-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
1xAJ10-118K
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
Propellant
HTPB
[edit on Wikidata]
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.
^"Delta II 7920H-10". Archived from the original on 14 July 2014. Retrieved 1 July 2014.
^"The Annual Compendium of Commercial Space Transportation: 2018" (PDF). Federal Aviation Administration's Office of Commercial Space Transportation. Bryce Space and Technology. January 2018. This article incorporates text from this source, which is in the public domain.
^ abcKyle, Ed. "Delta II Data Sheet". spacelaunchreport.com. Archived from the original on 28 July 2014. Retrieved 24 July 2014.{{cite web}}: CS1 maint: unfit URL (link)
^ abcdefghIsakowitz, Steven J.; Hopkins, Joshua B.; Hopkins, Joseph R. Jr. (2004). International Reference Guide to Space Launch Systems (Report) (Fourth ed.). American Institute of Aeronautics and Astronautics.
^Cite error: The named reference Castor4A was invoked but never defined (see the help page).
^"Boeing: Integrated Defense Systems - Delta - Delta II Launch Vehicle Family". Archived from the original on 3 November 2006. Retrieved 3 November 2006.
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Global Information
This article incorporates text from this source, which is in the public domain.
