Delta II

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This article contains information regarding a rocket that may imminently be scheduled to launch, or currently be in the process of doing so.

Details may change as the countdown and ascent progress. Launch details: ULA will use a Delta II 7920H to launch GLAST for NASA. Launch will occur from LC-17B at CCAFS. • Live countdown clock • Webcast

Launch is scheduled for 11 June 2008 at 16:05 UTC. See 2008 in spaceflight and the Spaceflight Portal for further details.

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This article is about the rocket. For the submarine see Delta class submarine.

Fact sheet
Delta II
A Delta II rocket launches from Cape Canaveral carrying the Dawn spacecraft.
Function	Launch vehicle
Manufacturer	United Launch Alliance (Boeing IDS)
Country of origin	United States
Cost per launch (1987)	$36.7m (USD)
Size
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
Capacity
Payload to LEO	2,700 - 6,100 kg (5,960 - 13,440 lb)
Payload to GTO	900 - 2,170 kg (1,980 - 4,790 lb)
Launch History
Status	Active
Launch sites	Cape Canaveral LC-17 Vandenberg AFB SLC-2W
Total launches	135 Delta 6000: 17 Delta 7000: 114 Delta 7000H: 4
Successes	133 Delta 6000: 17 Delta 7000: 112 Delta 7000H: 4
Failures	1 (Delta 7000)
Partial failures	1 (Delta 7000)
Maiden flight	Delta 6000: 14 February 1989 Delta 7000: 26 November 1990 Delta 7000H: 8 July 2003
Last flight	Delta 6000: 24 July 1992
Boosters (6000 Series) - Castor 4A
N^o boosters	3, 4 or 9
Engines	1 Solid
Thrust	478.3 kN (107,530 lb_f)
Specific impulse	266 sec
Burn time	56 seconds
Fuel	Solid
Boosters (7000 Series) - GEM 40
N^o boosters	3, 4 or 9
Engines	1 Solid
Thrust	492.9 kN (110,800 lb_f)
Specific impulse	274 sec
Burn time	64 seconds
Fuel	solid
Boosters (7000 Heavy) - GEM 46
N^o boosters	9
Engines	1 solid
Thrust	628.3 kN (141,250 lb_f)
Specific impulse	278 sec
Burn time	75 seconds
Fuel	solid
First Stage - Thor/Delta XLT-C
Engines	1 RS-27A [1]
Thrust	1,054.2 kN (237,000 lb_f)
Specific impulse	302 sec
Burn time	265 seconds
Fuel	Kerosene/LOX
Second Stage - Delta K
Engines	1 AJ-10
Thrust	43.6 kN (9,800 lb_f)
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 lb_f)
Specific impulse	286 sec
Burn time	87 seconds
Fuel	Solid

Delta II is a space launch system originally designed and built by McDonnell Douglas. The Delta II is part of the Delta rocket family and has been in service since 1989. The Delta II includes the retired Delta 6000, the active Delta 7000, and two 7000 variants (light and heavy). The Delta II rocket was later built by Boeing Integrated Defense Systems until the Delta programs became the responsibility of United Launch Alliance on December 1, 2006.^[1]

1 History
2 Vehicle description
3 Launch description
4 Delta II launches
- 4.1 Notable payloads
5 Retirement of system
6 Future applications
7 References
8 External links

[edit] History

All United States expendable launch vehicles were to be phased out for the Space Shuttle, but in 1986 the Challenger accident restarted Delta development. The Delta II, specifically, was designed to accommodate the GPS Block II series of satellites. Delta IIs have successfully launched 125 projects (through August 2007), including several NASA missions to Mars:

Mars Global Surveyor in 1996
Mars Pathfinder in 1996
Mars Climate Orbiter in 1998
Mars Polar Lander in 1999
Mars Odyssey in 2001
Mars Exploration Rovers (MER-A, Spirit and MER-B, Opportunity) in 2003
Mars Phoenix lander in 2007

[edit] Vehicle description

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

Stage I: Kerosene and liquid oxygen tanks that feed the Rocketdyne RS-27 main engine for the ascent.
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.
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 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 (some Delta II vehicles are two-stage only, and generally used for Earth-orbit missions) 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.
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 is more technically named by a four-digit system:^[2]

Comparison of standard vs. heavy Delta II

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-case 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.

[edit] 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.^[3]

Fueling

It takes approximately 20 minutes to load the first stage with 10,000 US gallons (37,900 L) of fuel.^[4]

[edit] Delta II launches

See also: List of Delta II launches

The Delta II system has been used for 135 launches. On September 18, 2007, Delta II completed its 75th consecutive successful launch.^[5] This is a record for modern launch vehicles.^[6] It is the second most reliable launch vehicle currently in service, behind the Tsyklon 2.^[7] 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, was a partial failure in which the satellite payload was able to compensate when the launch system placed the vehicle in an incorrect orbit.^[8]

Another failure, this time complete, occurred on January 17, 1997, when a Delta II 7925 carrying the first GPS Block IIR satellite 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.^[9]

[edit] Notable payloads

Between May 1997 and November 1998 Delta II vehicles placed 55 Iridium satellites into orbit.^[10]

[edit] Retirement of system

An article published by the Wall Street Journal speculates about the fate of the Delta II launch system after U.S. Air Force discontinues its use of the Delta II.^[11] 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."

The final payload of the Delta II is scheduled to be a NASA moon mission in 2011.^[12]

[edit] Future applications

The Aerojet-built second-stage engine has been chosen by NASA to be used as the main propulsion engine for the Orion spacecraft that will replace the Space Shuttle after 2010. The engine was chosen due to its restart capabilities along with a switch from the original liquid oxygen/liquid methane (LOX/LCH₄) application to hypergolic fuel and oxidizer similar to that in use on the Shuttle's OMS and RCS systems.