Delta-II rocket

This article is about the rocket. For the submarine see Delta class submarine.
Delta II
Dawn spacecraft.
Function Launch vehicle
Manufacturer United Launch Alliance (Boeing IDS)
Country of origin United States
Cost per launch (1987) US$51 million (7920-10 mod.)[1]
Height 38.2 - 39 m (125.3 - 127 ft)
Diameter 2.44 m (8 ft)
Mass 151,700 - 231,870 kg
(334,300 - 511,180 lb)
Stages 2 or 3
Payload to
2,700 - 6,100 kg
(5,960 - 13,440 lb)
Payload to
900 - 2,170 kg
(1,980 - 4,790 lb)
Payload to
1,000 kg (2,200 lb)
Launch history
Status Active
Launch sites Cape Canaveral SLC-17
Vandenberg AFB SLC-2W
Total launches 151
Delta 6000: 17
Delta 7000: 128
Delta 7000H: 6
Successes 149
Delta 6000: 17
Delta 7000: 126
Delta 7000H: 6
Failures 1 (Delta 7000)
Partial failures 1 (Delta 7000)
First flight Delta 6000: 14 February 1989
Delta 7000: 26 November 1990
Delta 7000H: 8 July 2003
Last flight Delta 6000: 24 July 1992
Delta 7000H: 10 September 2011
Boosters (6000 Series) - Castor 4A
No. boosters 9
Engines 1 Solid
Thrust 478.3 kN (107,530 lbf)
Specific impulse 266 sec
Burn time 56 seconds
Fuel Solid
Boosters (7000 Series) - GEM 40
No. boosters 3, 4 or 9
Engines 1 Solid
Thrust 492.9 kN (110,800 lbf)
Specific impulse 274 sec
Burn time 64 seconds
Fuel solid
Boosters (7000 Heavy) - GEM 46
No boosters 9
Engines 1 solid
Thrust 628.3 kN (141,250 lbf)
Specific impulse 278 sec
Burn time 75 seconds
Fuel solid
First stage - Thor/Delta XLT(-C)
Engines 1 RS-27 (6000 series) or RS-27A (7000 series)[2]
Thrust 1,054.2 kN (237,000 lbf)
Specific impulse 302 sec
Burn time 265 seconds
Fuel RP-1/LOX
Second stage - Delta K
Engines 1 AJ-10
Thrust 43.6 kN (9,800 lbf)
Specific impulse 319 sec
Burn time 431 seconds
Fuel Dinitrogen tetroxide/Aerozine
Third stage - PAM-D (optional)
Engines 1 Star 48B
Thrust 66.0 kN (14,837 lbf)
Specific impulse 286 sec
Burn time 87 seconds
Fuel Solid

Delta II is an American space launch system, originally designed and built by McDonnell Douglas. Delta II is part of the Delta rocket family and entered service in 1989. Delta II vehicles included the Delta 6000, the Delta 7000, and two 7000 variants ("Light" and "Heavy").

After McDonnell Douglas merged with Boeing in 1997, Delta II rockets were built by Boeing Integrated Defense Systems, until Delta rocket production became the responsibility of United Launch Alliance (ULA) on December 1, 2006.[3][4] ULA now markets Delta II to U.S. government customers, and Boeing Launch Services (BLS) markets Delta II to commercial companies.[5]


All United States expendable launch vehicles were planned to be phased out in favor of the Space Shuttle. After the Challenger disaster of 1986, President Reagan announced that commercial satellites were to be launched by private industry.[6] A contract to provide 20 launch vehicles for the U. S. Air Force, beginning in 1989, brought Delta back into production with Delta II.[7] Delta II was specifically designed to accommodate the GPS Block II series of positioning satellites. [8] As of October 2011, Delta IIs have successfully launched 149 projects, including several NASA missions to Mars:

Delta II manufacturing, assembly and integration reportedly take place at facilities in Decatur, Alabama; Harlingen, Texas; San Diego, California; and Denver, Colorado.[5]

Vehicle description

Deltas are expendable launch vehicles (ELVs), which means they can only be used once. Each Delta II launch vehicle consists of:

  • Stage I: RP-1 and liquid oxygen tanks that feed the Rocketdyne RS-27 main engine for the ascent. The first stage is technically referred to as the "Extra-Extended Long Tank Thor", a derivative of the Thor ballistic missile[9] as are all Delta rockets until the Delta IV.
  • Solid rocket booster motors: Used to increase thrust during the initial two minutes of flight. The medium-capacity Delta II has nine motors total (six fire on the ground, three in flight); the other models use only three or four.
  • Interstage: A spacer between stage I and stage II. The first friction stir welded interstage module was launched in 1999.
  • Stage II: Fuel and oxidizer tanks feeding a restartable hypergolic Aerojet AJ10-118K engine that fires one or more times to insert the vehicle-spacecraft stack into low Earth orbit. This propellant mixture is highly corrosive, so once loaded the launch must occur within approximately 37 days, or the stage will have to be refurbished or replaced.[10] This stage also contains the vehicle's "brains", a combined inertial platform and guidance system that controls all flight events.
  • Stage III: Optional ATK-Thiokol solid rocket motor provides the majority of the velocity change needed to leave Earth orbit and inject the spacecraft on a trajectory to Mars or other target beyond Earth orbit. It is connected to the spacecraft until it is done firing, and then separates. This stage is spin-stabilized and has no active guidance control; it depends on the second stage for proper orientation prior to Stage II/III separation. It also includes a yo-yo de-spin mechanism to slow the spin before spacecraft release, as many spacecraft cannot handle the high spin rates needed for stability of this stage. Note that some Delta II vehicles are two-stage only, these generally being used for Earth-orbit missions.
  • Payload fairing: Thin metal or composite payload fairing (aka "nose cone") to protect the spacecraft during the ascent through Earth's atmosphere.

Naming system

The Delta II family uses a four-digit system to generate its technical names:[11]

  • The first digit is either 6 or 7, denoting the 6000- or 7000-series Deltas. The 6000-series, last flown in 1992, had an Extra Extended Long Tank first stage with RS-27 main engine, plus Castor IVA solid rocket boosters. The current model 7000-series have an RS-27A engine, with a longer nozzle for higher expansion ratio and better high-altitude performance, and GEM (Graphite-Epoxy Motor) boosters. GEMs are larger, and have a composite casing to reduce mass versus the steel-cased Castors. In addition, two LR101-NA-11 vernier engines provide guidance for the first stage.
  • The second digit indicates the number of boosters, usually 9. In such cases, six are lit at liftoff and three are lit one minute into flight. On vehicles with 3 or 4 boosters, all are ignited at liftoff.
  • The third digit is 2, denoting a second stage with an Aerojet AJ10 engine. This engine is restartable, for complex missions. Only Deltas prior to the 6000-series used a different engine, the TR-201.
  • The last digit denotes the third stage. 0 denotes no third stage, 5 indicates a Payload Assist Module (PAM) stage with Star 48B solid motor, 6 indicates a Star 37FM motor.

For example, a Delta 7925 has the later first stage, nine GEM boosters, and a PAM third stage. A Delta 7320 is a two-stage vehicle with three boosters.

  • A Delta II-Heavy has the larger GEM-46 boosters, originally designed for the Delta III. These are designated 79xxH.

Three payload fairings are available. The original aluminum fairing, seen above, is 9.5 feet in diameter. A 10-foot fairing is made of composite, and can be distinguished by its tapering front and rear. A lengthened 10-foot fairing is used for the largest payloads.

Launch description

Launch vehicle build-up 
A Delta II launch vehicle is assembled vertically on the launch pad. Assembly starts by hoisting the first stage into position. The solid rocket boosters are then hoisted into position and mated with the first stage. Launch vehicle build-up then continues with the second stage being hoisted atop the first stage.[12]
It takes approximately 20 minutes to load the first stage with 37,900 litres (10,000 US gal) of fuel.[13]

Delta II launches

The Delta II system has been used for 151 launches. On September 18, 2007, Delta II completed its 75th consecutive successful launch.[14] This is a record for modern launch vehicles.[15] As of 2012, it is the most reliable launch vehicle in service, which it has been since the presumed retirement of the Tsyklon 2 in 2006.[16] Eight launches took place in 2007.

However, the Delta II system does not have a perfect success record. One mission, the launch of Koreasat-1 in 1995, was a partial failure in which the satellite payload was able to compensate when the launch system placed the vehicle in an incorrect orbit.[17]

Another failure, this time complete, occurred on January 17, 1997, when a Delta II 7925 carrying the first GPS Block IIR satellite, GPS IIR-1, exploded only 13 seconds after liftoff, raining flaming debris all over Launch Complex 17 at Cape Canaveral Air Force Station. No one was injured, and the launchpad itself was not seriously damaged, though several cars were destroyed and a few buildings were damaged.[18] It was later determined that a "17-foot crack" in the rocket booster had caused the failure.[19]

Notable payloads

Furthermore, between May 1997 and November 1998, Delta II vehicles placed 55 Iridium satellites into orbit.[20]

Post MLV-3

A 2007 article published by the Wall Street Journal speculated about the fate of the Delta II launch system after the U.S. Air Force discontinues its use of the Delta II.[21] Thomas Young, who was director of Goddard Space Flight Center from 1980 to 1982, is quoted as saying, "It's definitely an item people are quite worried about."

As of February 2013, four further Delta II launches are scheduled; carrying the SMAP and OCO 2 satellites in 2014, and the JPSS-1 and ICESat-2 satellites in 2016.[22][23] ULA had previously indicated that it had "around half a dozen" unsold Delta II rockets on hand.[24] A spokesperson indicated that ULA will change some aspects of the Delta II system once the current Medium Launch Vehicle 3 contract with the Air Force ends and requirements imposed by the contract are lifted. The Air Force contract required that Delta II be kept ready to launch within 40 days of call up, which led ULA to maintain two launch pads at Cape Canaveral. ULA indicated it would not continue to operate two launch pads.[24]

In August 2009, the NASA assistant associate administrator for the Launch Services Program stated that NASA might purchase additional Delta II launches beyond those it had planned at that time.[25] However on September 30, 2011, NASA modified the NASA Launch Services II (NLS-II) contract[26] to allow for the continuing order of Delta II launchers in agreement with ULA. Components for five additional Delta II vehicles had been built and two now remain unassigned to planned flights.[27] Under the terms of the revised NLS-II contract, only three Delta II configurations are available – the 7320-10, 7420-10 and 7920-10 – and launches are only available from SLC-2W at Vandenberg Air Force Base.[28] ULA has continued to update its product website[29] and continues to state that the vehicle is available for order for commercial or government offices.[30]

On July 16, 2012 NASA selected the Delta II for the launch of Soil Moisture Active Passive (SMAP), Orbiting Carbon Observatory-2 (OCO-2) and Joint Polar Satellite System-1 (JPSS-1) spacecraft. The spacecraft will launch in October 2014, July 2014 and November 2016, respectively, aboard Delta II rockets from Complex 2 at Vandenberg Air Force Base in California.[31]

Comparable rockets

See also


External links

  • Delta II page at
  • Delta I, II und III launch data at
  • History of the Delta launch vehicle