# Delta II

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American space launch system (1989–2018)

This article is about the rocket. For the submarine, see [Delta-class submarine](/source/Delta-class_submarine). For the airplane, see [Fairey Delta 2](/source/Fairey_Delta_2).

Delta II A Delta II rocket launches from Cape Canaveral carrying the Dawn spacecraft. Function Launch vehicle Manufacturer McDonnell Douglas (1989–1997) Boeing Defense, Space & Security (1997–2006) United Launch Alliance (2006–2018) Country of origin United States Cost per launch US$51 million in 1987[a][1] US$137 million in 2018[2] 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 Cape Canaveral, SLC-17 Vandenberg, SLC-2W Total launches 155: Delta 6000: 17 Delta 7000: 132 Delta 7000 Heavy: 6 Success(es) 153: Delta 6000: 17 Delta 7000: 130 Delta 7000 Heavy: 6 Failure 1 (Delta 7000) Partial failure 1 (Delta 7000) First flight Delta 6000: 14 February 1989 (USA-35) Delta 7000: 26 November 1990 (USA-66) Delta 7000 Heavy: 7 July 2003 (Opportunity rover) Last flight Delta 6000: 24 July 1992 (Geotail) Delta 7000: 15 September 2018 (ICESat-2) Delta 7000 Heavy: 10 September 2011 (GRAIL) 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 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 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 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 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 [edit on Wikidata]

**Delta II** was an [expendable launch system](/source/Expendable_launch_system) designed and built by [McDonnell Douglas](/source/McDonnell_Douglas), sometimes known as the Thorad Delta 1. Delta II was part of the [Delta rocket](/source/Delta_rocket) family, derived from the [Delta 3000](/source/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 payloads, including 24 [Global Positioning System](/source/Global_Positioning_System) (GPS) [Block II](/source/GPS_satellite_blocks) satellites, several dozen NASA payloads, and 60 Iridium communication satellites. The rocket flew its final mission, [ICESat-2](/source/ICESat-2), on 15 September 2018, earning a streak of 100 consecutive successful missions, with the last failure being [GPS IIR-1](/source/GPS_IIR-1) in 1997.[3] In the late 1990s, Delta II was developed into the unsuccessful [Delta III](/source/Delta_III), which was in turn developed into the more capable and successful [Delta IV](/source/Delta_IV), though the latter shares little heritage with the original Thor and Delta rockets.

## History

Evolution of the modern Delta rockets

In the early 1980s, all United States [expendable launch vehicles](/source/Expendable_launch_vehicles) were planned to be phased out in favor of the [Space Shuttle](/source/Space_Shuttle), which would be responsible for all government and commercial launches. Production of Delta, [Atlas-Centaur](/source/Atlas-Centaur), and [Titan 34D](/source/Titan_34D) had ended.[7] The [*Challenger* disaster](/source/Space_Shuttle_Challenger_disaster) of 1986 and the subsequent halt of Shuttle operations changed this policy, and President [Ronald Reagan](/source/Ronald_Reagan) announced in December 1986 that the Space Shuttle would no longer launch commercial payloads, and [NASA](/source/NASA) would seek to purchase launches on expendable vehicles for missions that did not require crew or Shuttle support.[8]

McDonnell Douglas, at that time the manufacturer of the Delta family, signed a contract with the [U.S. Air Force](/source/U.S._Air_Force) in 1987 to provide seven Delta II. These were intended to launch a series of [Global Positioning System](/source/Global_Positioning_System) (GPS) [Block II](/source/GPS_satellite_blocks) satellites, which had previously been manifested for the Space Shuttle. The Air Force exercised additional contract options in 1988, expanding this order to 20 vehicles, and NASA purchased its first Delta II in 1990 for the launch of three Earth-observing satellites.[9][10] The first Delta II launch occurred on 14 February 1989, with a Delta 6925 boosting the first GPS Block II satellite ([USA-35](/source/USA-35)) from [Launch Complex 17A](/source/Cape_Canaveral_Space_Launch_Complex_17) (SLC-17A) at [Cape Canaveral](/source/Cape_Canaveral_Space_Force_Station) into a 20,000 km (12,000 mi) high [medium Earth orbit](/source/Medium_Earth_orbit).[11]

The first Delta II 7000-series flew on 26 November 1990, replacing the [RS-27](/source/RS-27) engine of the 6000-series with the more powerful [RS-27A](/source/RS-27A) engine. Additionally, the steel-cased [Castor 4A](/source/Castor_(rocket_stage)) solid boosters of the 6000-series were replaced with the composite-cased [GEM 40](/source/Graphite-Epoxy_Motor). All further Delta II launches except three were of this upgraded configuration, and the 6000-series was retired in 1992 with the last launch being on July 24.[12]

McDonnell Douglas began [Delta III](/source/Delta_III) development in the mid-1990s as increasing satellite mass required more powerful launch vehicles.[9] Delta III, with its liquid hydrogen second stage and more powerful [GEM 46](/source/Graphite-Epoxy_Motor) boosters, could bring twice as much mass as Delta II to [geostationary transfer orbit](/source/Geostationary_transfer_orbit), but a string of two failures and one partial failure, along with the development of the much more powerful [Delta IV](/source/Delta_IV), led to the cancellation of the Delta III program.[13] The upgraded boosters would still find use on the Delta II, leading to the Delta II Heavy.

On 28 March 2003, the Air Force Space Command began the process of deactivating the Delta II launch facilities and infrastructure at Cape Canaveral once the last of the second-generation GPS satellites were launched. However, in 2008, it instead announced that it would transfer all the Delta II facilities and infrastructure to NASA to support the launch of the [Gravity Recovery and Interior Laboratory](/source/GRAIL) (GRAIL) in 2011.[14]

On 14 December 2006, with the launch of [USA-193](/source/USA-193), was the first launch of the Delta II operated by [United Launch Alliance](/source/United_Launch_Alliance).[15]

The last GPS launch aboard a Delta II and the final launch from SLC-17A at Cape Canaveral occurred in 2009. The GRAIL Launch in 2011 marked the last Delta II Heavy launch and the last from Florida. The final five launches would all be from [Vandenberg Air Force Base](/source/Vandenberg_Space_Force_Base) in [California](/source/California).[16]

On 16 July 2012, NASA selected the Delta II to support the [Orbiting Carbon Observatory](/source/Orbiting_Carbon_Observatory) (OCO-2), [Soil Moisture Active Passive](/source/Soil_Moisture_Active_Passive) (SMAP), and [Joint Polar Satellite System](/source/Joint_Polar_Satellite_System) (JPSS-1 – NOAA-20) missions. This marked the final purchase of Delta II. OCO-2 was launched on 2 July 2014, [Soil Moisture Active Passive](/source/Soil_Moisture_Active_Passive) (SMAP) was launched on 31 January 2015, and [JPSS-1](/source/NOAA-20) was launched on 18 November 2017. All three of these launches were placed into orbit from [SLC-2](/source/Vandenberg_Space_Launch_Complex_2) at Vandenberg.[17]

The Delta II family launched 155 times. Its only unsuccessful launches were [Koreasat 1](/source/Koreasat_1) in 1995, and [GPS IIR-1](/source/GPS_IIR-1) in 1997. The Koreasat 1 launch was a partial failure caused by one booster not separating from the first stage, which resulted in the satellite being placed in a lower-than-intended orbit. By using reserve fuel, it was able to achieve its proper [geosynchronous orbit](/source/Geosynchronous_orbit) and operated for 10 years.[18] The GPS IIR-1 was a total loss as the Delta II exploded 13 seconds after launch. The explosion occurred when a damaged [solid rocket booster](/source/Solid_rocket_booster) casing ruptured and triggered the vehicle's flight termination system.[19] No one was injured, and the launch pad itself was not seriously impacted, though several cars were destroyed and a few buildings were damaged.[20]

In 2007, Delta II completed its 75th consecutive successful launch, surpassing the 74 consecutive successful launches of the [Ariane 4](/source/Ariane_4).[21][22] With the launch of [ICESat-2](/source/ICESat-2) in 2018, Delta II reached 100 consecutive successful launches.

During its career, Delta II achieved a peak launch rate of 12 launches in a single year, although its infrastructure was capable of supporting up to 15 launches per year.[4]

While all completed Delta II rockets were launched, many flight-qualified spare parts remained in inventory. These spare parts were assembled, alongside a few structural simulators, to create a nearly complete Delta II for exhibition in its 7320-10C configuration. The rocket is displayed vertically at the [Kennedy Space Center Visitor Complex](/source/Kennedy_Space_Center_Visitor_Complex), and bears its popular "shark teeth" livery on its fairing, which was painted on past Delta II rockets for the GPS launches.[23]

## Vehicle description

Delta II 7425 diagram

A Delta-K stage

### First stage

The first stage of the Delta II was propelled by a Rocketdyne [RS-27](/source/RS-27) or [RS-27A](/source/RS-27A) main engine burning [RP-1](/source/RP-1) and [liquid oxygen](/source/Liquid_oxygen). This stage was technically referred to as the "Extra-Extended Long Tank Thor", a derivative of the [Thor](/source/PGM-17_Thor) ballistic missile [24] as were all Delta rockets until the [Delta IV](/source/Delta_IV). The RS-27 used on the 6000-series Delta II produced 915 kN (206,000 lbf) of thrust,[25] while the upgraded RS-27A used by the 7000-series produced 1,054 kN (237,000 lbf).[26] The stage was 26.1 meters (86 ft) long and 2.44 meters (8.0 ft) wide, had a mass of 101.8 tonnes (224,000 lb) when fueled, and burned for 260 seconds.[3] The main engine, which could not throttle, provided pitch and yaw control for the vehicle during ascent using hydraulic gimballing. In addition, two [Rocketdyne LR-101-NA-11](https://en.wikipedia.org/w/index.php?title=Rocketdyne_LR-101-NA-11&action=edit&redlink=1) vernier engines provided roll control for the first stage during ascent and continued firing after the main engine shut down to stabilize the vehicle before stage separation.[27][4]

The two first-stage tanks were constructed from aluminum isogrid panels, providing high strength at a lower mass. Nitrogen gas was used to pressurize the tanks. These tanks were stretched a total of 148 inches (3.8 m) from those of the Extended Long Tank Thor that flew on older Delta rockets, providing more propellant. Between the two tanks was the "center body", where first-stage avionics and communications equipment were housed. The solid rocket booster attachment points were located on the outside of the liquid oxygen tank and the aft skirt, the latter of which also contained a [gyroscope](/source/Gyroscope) for vehicle stability.[4]

### Solid rocket boosters

For additional thrust during launch, the Delta II used solid boosters. For the 6000-series, Delta II used Castor 4A boosters (sometimes stylized as "Castor IVA"), while the 7000-series used GEM 40 [Graphite-Epoxy Motors](/source/Graphite-Epoxy_Motor) manufactured by [Alliant Techsystems](/source/Alliant_Techsystems) (ATK). Like its predecessors, the Delta II 6000-series was only offered in nine-booster configurations. However, with the arrival of the 7000-series, variants with three and four boosters were introduced to allow Delta II to fly small payloads for cheaper.[4] When three or four boosters were used, all ignited on the ground at launch, while models that used nine boosters would ignite six on the ground, then the remaining three would ignite in flight after the burnout and jettison of the first six.[3]

The Castor 4A boosters were an improvement over the Castor 4 motors flown on the earlier [Delta 3000](/source/Delta_3000) rocket, replacing the propellant with more modern [HTPB](/source/Hydroxyl-terminated_polybutadiene)-based propellant and providing an 11% increase in performance.[5] The GEM 40 boosters on the 7000-series further improved Delta II's performance by each featuring 2.5 tonnes (5,500 lb) of extra propellant than the Castor 4A thanks to a lengthening of 3 meters (9.8 ft). In addition, the GEM boosters also boasted a lower dry mass than the Castors due to the former's carbon composite construction.[28]

In 2003, the Delta II Heavy debuted, featuring larger GEM 46 motors from the abandoned [Delta III](/source/Delta_III) program. These new motors allowed the vehicle to carry over 1,000 kg (2,200 lb) of extra payload into low-Earth orbit. Only Cape Canaveral Space Launch Complex 17B was capable of flying the Heavy configuration, as it was previously reinforced to handle the Delta III.[4]

The Castor motor nozzles were angled 11° from vertical to aim their thrust into the vehicle's center of gravity, while the GEM motors had a slightly lower 10° tilt.[5] On the nine-engine configuration, the three air-lit motors featured longer nozzles to allow the boosters to perform better in the upper atmosphere.[27] All solid motors that flew on the Delta II featured fixed nozzles, meaning the first stage was solely responsible for vehicle control during the initial portions of the flight.[4]

### Delta-K second stage

The second stage of Delta II was the [Delta-K](/source/Delta-K), powered by a restartable (up to six restarts) [Aerojet](/source/Aerojet) [AJ10](/source/AJ10)-118K engine burning [hypergolic](/source/Hypergolic) [Aerozine-50](/source/Aerozine-50) and [N2O4](/source/Dinitrogen_tetroxide). These propellants are highly toxic and corrosive, and once loaded the launch had to occur within approximately 37 days or the stage would have to be refurbished or replaced.[29] This stage also contained a combined [inertial platform](/source/Inertial_platform) and [guidance system](/source/Guidance_system) that controlled all flight events.[3]

The Delta-K consisted of stainless steel tanks and a lightweight aluminum structure. The tanks were pressurized with helium gas, and the stage featured nitrogen thrusters for roll control during burns and for complete attitude control during coasts. The stage had a mass of 950 kg (2,090 lb) when empty, and 6,954 kg (15,331 lb) when fully fueled.[4]

### Third stage

For low Earth orbit missions, Delta II was not equipped with a third stage. Payloads bound for higher energy orbits such as [GTO](/source/Geostationary_transfer_orbit) or to reach Earth escape velocity for [trans-Mars injection](/source/Trans-Mars_injection) or other destinations beyond Earth used an [HTPB](/source/HTPB) solid propellant third stage, situated inside the fairing during launch. This stage was [spin-stabilized](/source/Spin-stabilized) and depended on the second stage for proper orientation prior to stage separation, but was sometimes equipped with a hydrazine nutation control system to maintain proper spin axis.[27] The third stage would be spun up using small rocket motors and then released by the second stage to perform its burn. The third stage also included a yo-weight system to induce tumbling in the stage after payload separation to prevent recontact, or a [yo-yo de-spin](/source/Yo-yo_de-spin) mechanism to slow the rotation before payload release.[27] The stage would also contain an S-band transmitter, batteries, and a sequencer to command the stage events.

Two third-stage options were available, both consisting of a single solid rocket motor. The most common by far was [Star 48](/source/Star_48), flying on over 70 missions. The Star 48, also referred to as the Payload Assist Module-Delta (PAM-D, PAM-Delta), was the more, powerful of the two options, producing an average thrust of about 66.4 kN (14,900 lbf) during its 87.1 seconds of burn time. The stage would end up flying primarily on the more powerful Delta variants and never flew on the three-booster configuration.

The other third-stage option was [Star 37FM](/source/Star_37FM). This stage flew four times, and only on three- and four-booster configurations of Delta. Star 37FM produced about 45.8 kN (10,300 lbf) of thrust during its 66.4-second burn.[4]

## Naming system

The Delta II family used a four-digit system to generate its technical names:[30]

- The **first digit** was either 6 or 7, denoting the 6000- or 7000-series Delta;

- The **second digit** indicated the number of boosters. Most Delta II rockets flew with 9 boosters, but some flew with 3 or 4;

- The **third digit** was always 2, denoting a second stage with an Aerojet AJ10 engine. Only Deltas prior to the 6000-series used a different engine, the [TR-201](/source/TR-201);

- The **last digit** denoted the third stage. 0 denoted no third stage, 5 indicated a [Payload Assist Module](/source/Payload_Assist_Module) (PAM) stage with Star 48B being used, and 6 indicated it used the Star 37FM motor for a [PAM](/source/Payload_Assist_Module).

- An **H** following the four digits denoted that the vehicle used larger [Delta III](/source/Delta_III) [GEM 46](/source/GEM_46) boosters. The [Heavy](/source/Delta_IV_Heavy) variant could be launched only from [Cape Canaveral](/source/Cape_Canaveral) (as [Vandenberg](/source/Vandenberg_Space_Force_Base)'s pad wasn't modified to handle the larger SRBs) and was retired with the closure of that launch site in 2011;[31]

- Numbers and letters following those indicate the type of fairing. -9.5 means that the vehicle had a 9.5 ft (2.9 m) diameter fairing, -10 means an aluminum 10 ft (3.0 m) diameter fairing, -10C means a composite 10 ft (3.0 m) diameter fairing, and -10L indicates a lengthened 10 ft (3.0 m) diameter composite fairing. In some early Delta II flights, a fairing, about 8-feet in diameter (from older Delta rockets) was flown, and those vehicles had the -8 designation.

For example, a Delta 7925H-10L used the RS-27A, nine [GEM 46](/source/GEM_46) boosters, a [PAM](/source/Payload_Assist_Module) third stage, and a lengthened 10 ft (3.0 m) diameter fairing. A Delta 6320–9.5 is a two-stage vehicle with an RS-27 first-stage engine, three Castor 4A boosters, a 9.5 ft (2.9 m) diameter fairing, and no third stage.

## Launch profile

**Launch vehicle build-up**
- A Delta II [launch vehicle](/source/Launch_vehicle) was assembled vertically on the launch pad. Assembly started by hoisting the first stage into position. The solid rocket boosters were then hoisted into position and mated with the first stage. Launch vehicle build-up then continued with the second stage being hoisted atop the first stage.[32]

**Fueling**
- It took approximately 20 minutes to load the first stage with 37,900 L (10,000 U.S. gal) of fuel.[33]

- At T-45 minutes, fueling completion was confirmed. At T-20 minutes, the [FTS](/source/Flight_termination) pyros were armed. At T-20 minutes and T-4 minutes, two built-in holds occurred. During these holds, final launch checkouts were performed. At T-11 seconds SRB igniters were armed. Ignition of the main engine was at T-0.4 seconds. The ascent profile varies between missions.

**SRB staging**
- If nine solid rocket boosters were used, only six were ignited at launch. After about a minute, once the first six were depleted, three air-start motors would ignite for another minute and the ground-start motors would separate.[34] The air-start motors had nozzles optimized for high-altitude as they operated mostly in a near-vacuum during the flight.

- If only three or four boosters were used, all were ignited on the ground and jettisoned at the same time.

## Delta II launches

Main article: [List of Delta II launches](/source/List_of_Delta_II_launches)

Delta II lifting off with MER-A on 10 June 2003

Delta II Heavy (7925H-9.5) lifting off from pad 17-B carrying [MER-B](/source/Opportunity_(rover))

### Notable payloads

Earth-orbiting

- [GLAST](/source/Fermi_Gamma-ray_Space_Telescope)

- [Gravity Probe B](/source/Gravity_Probe_B)

- 24 GPS satellites

- 60 [Iridium](/source/Iridium_satellite_constellation) satellites

- [ICESat-2](/source/ICESat-2)

- [Kepler space telescope](/source/Kepler_space_telescope)

- [OSTM/Jason-2](/source/OSTM%2FJason-2)

- [Radarsat-1](/source/Radarsat-1)

- [ELFIN](/source/ELFIN)

- [Polar (satellite)](/source/Polar_(satellite))

- [ROSAT](/source/ROSAT)

- [STSS-ATRR](/source/USA_205)

- [Swift](/source/Swift_Gamma-Ray_Burst_Mission)

- [THEMIS](/source/THEMIS)

- [USA 193 (NROL-21)](/source/USA_193)

- [WIND](/source/WIND_(spacecraft))

- [WISE](/source/Wide-field_Infrared_Survey_Explorer)

- [WMAP](/source/Wilkinson_Microwave_Anisotropy_Probe)

- [Geotail](/source/Geotail)

Interplanetary

- [2001 Mars Odyssey](/source/2001_Mars_Odyssey)

- [CONTOUR](/source/CONTOUR)

- [Dawn](/source/Dawn_(spacecraft))

- *[Deep Impact](/source/Deep_Impact_(spacecraft))*

- [Deep Space 1](/source/Deep_Space_1)

- [Genesis](/source/Genesis_(spacecraft))

- [GRAIL](/source/GRAIL)

- [Mars Climate Orbiter](/source/Mars_Climate_Orbiter)

- [Mars Exploration Rovers](/source/Mars_Exploration_Rover)

- [Mars Global Surveyor](/source/Mars_Global_Surveyor)

- [Mars Pathfinder](/source/Mars_Pathfinder)

- [Mars Phoenix](/source/Phoenix_(spacecraft))

- [Mars Polar Lander](/source/Mars_Polar_Lander)

- [MESSENGER](/source/MESSENGER)

- [NEAR](/source/NEAR_Shoemaker)

- [Spitzer Space Telescope (SIRTF)](/source/Spitzer_Space_Telescope)

- [STEREO](/source/STEREO)

The last Delta II launch was the [ICESat-2](/source/ICESat-2) satellite in September 2018.[31][35][36]

In 2008, ULA indicated that it had "around half a dozen" unsold Delta II rockets on hand,[37] and by October 2017, ULA CEO [Tory Bruno](/source/Tory_Bruno) stated that there were no complete Delta II rockets left in ULA inventory.

There were some unused Delta II components, but not enough to build another vehicle.[38] A Delta II, made of these leftover parts alongside some [simulated](/source/Simulation) parts, is located at the [Kennedy Space Center rocket garden](/source/Rocket_garden).[39]

## Comparable rockets

- [Antares](/source/Antares_(rocket))

- [Ariane 4](/source/Ariane_4) (retired)

- [GSLV](/source/Geosynchronous_Satellite_Launch_Vehicle) – Class of Indian medium-lift expendable launch vehicles, developed by ISRO

- [Long March 4B](/source/Long_March_4B)

- [PSLV](/source/Polar_Satellite_Launch_Vehicle) – Indian expendable launch vehicle

- [Soyuz](/source/Soyuz_(rocket_family))

- [Tsyklon-3](/source/Tsyklon-3) – Soviet / Russian launch vehicle (retired)

- [Vega](/source/Vega_(rocket)) – European Space Agency launch system

## Space debris

The only person on record ever hit by [space debris](/source/Space_debris), Lottie Williams, was hit by a small, light piece of a Delta II rocket. Williams was exercising in a park in [Tulsa, Oklahoma](/source/Tulsa%2C_Oklahoma) on 22 January 1997 when she was hit in the shoulder by a 15-centimeter (6 in) piece of blackened metallic material. The [U.S. Space Command](/source/United_States_Space_Command) confirmed that a used Delta II rocket from the April 1996 launch of the [Midcourse Space Experiment](/source/Midcourse_Space_Experiment) had crashed into the [atmosphere](/source/Atmosphere) 30 minutes earlier. The object tapped her on the shoulder and fell off harmlessly onto the ground. Williams collected the item and [NASA](/source/NASA) tests later showed that the fragment was consistent with the materials of the [rocket](/source/Rocket), and Nicholas Johnson, the agency's chief scientist for [orbital debris](/source/Orbital_debris), believes that she was, indeed hit by a piece of a recently launched Delta II.[40][41]

Delta rockets have been involved in multiple fragmentation events as they were routinely left in orbit with enough fuel to explode. A large amount of current "[space junk](/source/Space_debris)" is Delta rocket debris.[42]

## See also

- [Comparison of orbital launchers families](/source/Comparison_of_orbital_launchers_families)

- [Comparison of orbital launch systems](/source/Comparison_of_orbital_launch_systems)

## Notes

1. **[^](#cite_ref-1)** (7920-10 model)

## References

1. **[^](#cite_ref-2)** ["Delta II 7920H-10"](https://web.archive.org/web/20140714122955/http://www.spaceflight101.com/delta-ii-7920h-10.html). Archived from [the original](http://www.spaceflight101.com/delta-ii-7920h-10.html) on 14 July 2014. Retrieved 13 August 2024.

1. **[^](#cite_ref-3)** ["The Annual Compendium of Commercial Space Transportation: 2018"](https://www.faa.gov/about/office_org/headquarters_offices/ast/media/2018_ast_compendium.pdf) (PDF). *Federal Aviation Administration's Office of Commercial Space Transportation*. Bryce Space and Technology. January 2018. Retrieved 13 August 2024. This article incorporates text from this source, which is in the [public domain](/source/Public_domain).

1. ^ [***a***](#cite_ref-data_sheet_4-0) [***b***](#cite_ref-data_sheet_4-1) [***c***](#cite_ref-data_sheet_4-2) [***d***](#cite_ref-data_sheet_4-3) [***e***](#cite_ref-data_sheet_4-4) [***f***](#cite_ref-data_sheet_4-5) Kyle, Ed. ["Delta II Data Sheet"](https://web.archive.org/web/20140728024436/http://www.spacelaunchreport.com/delta2.html). *spacelaunchreport.com*. Archived from [the original](http://www.spacelaunchreport.com/delta2.html) on 28 July 2014. Retrieved 28 July 2014.

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## External links

Media related to [Delta II](https://commons.wikimedia.org/wiki/Category:Delta_II) at Wikimedia Commons

- [Delta II page](https://web.archive.org/web/20061103194958/http://www.boeing.com/defense-space/space/delta/delta2/delta2.htm) at Boeing.com

- [Delta I, II und III launch data](https://web.archive.org/web/20110718145330/http://space.skyrocket.de/doc_lau/delta.htm) at Skyrocket.de

- [History of the Delta launch vehicle](http://kevinforsyth.net/delta/)

- [Delta II Launch Weather Commit Criteria](https://www.nasa.gov/sites/default/files/633163main_delta-2-weather.pdf)

Articles related to Delta II v t e United Launch Alliance Parent companies Boeing Boeing Defense, Space & Security Lockheed Martin Lockheed Martin Space Systems Launch vehicles In service Atlas V Vulcan Centaur Retired Delta II Delta IV Medium Delta IV Heavy Rocket stages Centaur Delta Cryogenic Second Stage Interim Cryogenic Propulsion Stage Launch facilities Current Cape Canaveral Space Launch Complex 41 Vandenberg Space Launch Complex 3E Former Cape Canaveral: SLC-17A, SLC-17B, SLC-37 Vandenberg: SLC-2W, SLC-6 Key people Tory Bruno (CEO) Related Atlas (rocket family) Boeing Starliner Commercial Crew Development Delta (rocket family) Dream Chaser National Security Space Launch Peregrine lander Category Commons v t e Thor and Delta rockets PGM-17 Thor Thor family Delta family Rockets Thor Thor Thor-Able Thor-Ablestar Thor-Agena Thor-Burner Thor-Delta Thor DSV-2 Thor DSV-2U Thorad-Agena Delta Alphabetical Delta A Delta B Delta C Delta D Delta E Delta G Delta J Delta L Delta M Delta N Numerical Delta 0100 Delta 1000 Delta 2000 Delta 3000 Delta 4000 Delta 5000 Delta 6000 Delta 7000 Delta 8000 Delta 9000 Modern Delta II Delta III Delta IV Delta IV Heavy Export N-I N-II H-I Launch sites Canaveral (S)LC-17 LC-18B SLC-37B Johnston LE-1 LE-2 Tanegashima Osaki Vandenberg SLC-1 SLC-2 SLC-3 SLC-6 SLC-10 Bases Bardney Breighton Caistor Carnaby Catfoss Coleby Grange Driffield Feltwell Folkingham Full Sutton Harrington Hemswell Ludford Magna Melton Mowbray Mepal North Luffenham North Pickenham Polebrook Shepherds Grove Tuddenham Components Boosters Castor-1 Castor-1 Castor-4 Castor-4A CBC GEM-40 GEM-46 GEM-60 First stages Common Booster Core Upper Stages Delta Delta-A Delta-D Delta-E Delta-F Delta-K Delta-P DCSS Other Able Ablestar Agena Altair Burner FW-4D IABS PAM-D Star UM-129 Engines AJ10 B-8048 B-8081 B-8096 LE-5 LR-79 R-4D RL10 RS-27 RS-68 TR-201 Manufacturers Rocket Douglas McDonnell Douglas Boeing United Launch Alliance Engines Aerojet Alliant Rocketdyne Thiokol TRW Launches 1957–1959 1960–1969 1970–1979 1980–1989 1990–1999 2000–2009 2010–2019 2020–2024 v t e Orbital launch systems List of orbital launch systems Comparison of orbital launch systems Current Angara 1.2 A5 Ariane 6 Atlas V Ceres 1 1S 2† Chollima-1 Electron Eris† Falcon 9 Block 5 Falcon Heavy Firefly Alpha Gravity-1 GSLV H3 HANBIT-NANO† Hyperbola-1 Jielong 1 3 KAIROS† Kaituozhe 2 Kinetica 1 2 Kuaizhou 1 1A 11 Long March 2C 2D 2F 3A 3B/E 3C 4B 4C 5 5B 6 6A 6C 7 7A 8 11 11H 12 12A 12B LVM3 Minotaur I IV V C New Glenn Nuri OS-M1† Pegasus XL Proton-M PSLV Qaem 100 Qased Shavit 2 Simorgh SLS Block 1 Soyuz-2 2.1a / STA 2.1b / STB Soyuz-5 Spectrum† SSLV Starship Tianlong 2 3† Unha Vega C Vulcan Centaur Zhuque 2E 3 In development Antares 330 Bloostar Blue Whale 1 Cyclone-4M Deca Eclipse Epsilon S Gravity-2 Hyperbola-2 Kinetica 2H 3 KSLV-III Kuaizhou 21 31 Long March 9 10 10A 10B Miura 5 Neutron New Line 1 NGLV Nova OS-M 2 4 Pallas-1 RFA One SLS Block 1B Block 2 Soyuz-7 Terran R VLM Vega E Zero Zuljanah Retired Antares 110 120 130† 230 230+ Ariane 1 2 3 4 5 ASLV Athena I II Atlas B D E/F G H I II III LV-3B SLV-3 Able† Agena Centaur Black Arrow Conestoga† Delta A B C D E G J L M N 0100 1000 2000 3000 4000 5000 II III IV IV Heavy Diamant Dnepr Energia Epsilon Europa I† II† Falcon 1 Falcon 9 v1.0 v1.1 v1.2 "Full Thrust" Feng Bao 1 GSLV Mk I H-I H-II H-IIA H-IIB Juno I Juno II Kaituozhe-1 Kosmos original 1 2/2I 3 3M Lambda 4S LauncherOne Long March 1 1D† 2A 2E 3 3B 4A Mu 4S 3C 3H 3S 3SII V N1† N-I N-II Naro-1 Paektusan† Pilot-2† R-7 Luna Molniya M L Polyot Soyuz original FG L M U U2 2-1v Soyuz/Vostok Sputnik Voskhod Vostok L K 2 2M R-29 Shtil' Volna† Rocket 3 RS1† Safir 1 1A 1B Saturn I IB V Scout X-1 Blue Scout II† X-2† X-2M X-3 X-3M X-4 X-2B† B A B-1 D-1 A-1 E-1 F-1 G-1 Shavit original 1 SLV Space Shuttle SPARK† Sparta SS-520 Start-1 Terran 1† Thor Able Ablestar 1 2 Agena A B D Burner 1 2 Delta DSV-2U Thorad-Agena SLV-2G SLV-2H Titan II GLV IIIA IIIB IIIC IIID IIIE 34D 23G CT-3 IV Tsyklon R-36-O original 2 3 Universal Rocket UR-500 Proton Proton-K Rokot Strela Vanguard Vega original VLS-1† Zenit 2 2M 2FG 3SL 3SLB 3F Zhuque 1† 2 Classes Sounding rocket Small-lift launch vehicle Medium-lift launch vehicle Heavy-lift launch vehicle Super heavy-lift launch vehicle This template lists historical, current, and future space rockets that at least once attempted (but not necessarily succeeded in) an orbital launch or that are planned to attempt such a launch in the future Symbol † indicates past or current rockets that attempted orbital launches but never succeeded (never did or has yet to perform a successful orbital launch) v t e Orbital launch systems developed in the United States Active Atlas V**†† Electron Falcon 9 Block 5 Falcon Heavy Firefly Alpha Minotaur I IV V C New Glenn Pegasus XL SLS Block 1 Vulcan Centaur In development Antares 330 Daytona I Eclipse Neutron Nova SLS Block 1B Block 2 Starship Terran R Retired Antares 110/120/130/230/230+**††† Athena I II Atlas B D E/F G H I II III** LV-3B SLV-3 Able Agena Centaur Conestoga† Delta A B C D E G J L M N 0100 1000 2000 3000 4000 5000 II III IV IV Heavy Falcon 1 Falcon 9 v1.0 v1.1 v1.2 "Full Thrust" H-I* Juno I Juno II LauncherOne N-I* N-II* Pilot† Rocket 3 RS1† Saturn I IB V Scout Space Shuttle SPARK† Sparta Terran 1† Thor Able Ablestar Agena Burner Delta DSV-2U Thorad-Agena Titan II GLV IIIA IIIB IIIC IIID IIIE 34D 23G CT-3 IV Vanguard * - Japanese projects using US rockets or stages ** - uses Russian engines † - never succeeded †† - no new orders accepted and production stopped ††† - used Ukrainian first stage v t e USAF and USSF space vehicle designations (since 1962) SLV series SLV-1 (Scout) SLV-2 (Thor) SLV-3 (Atlas) SLV-4 (Titan II) SLV-5 (Titan) SB series SB-1 SB-2 SB-3 SB-4 SB-5 SB-6 SSB-7 SSB-8 SSB-9 SSB-10 ASB-11 Satellites WS-1 WS-2 LS-3 ES-4 ES-5 LS-6 NS-7 ES-8 LS-9 LS-10 (I) XSS-10 (II) XSS-112 XSS-12 S-131 ES-14 LS-153 LS-163 ES-17 EWS-G1 EWS-G2 1 Not assigned 2 Unofficial designation 3 Designation believed to be this type but unconfirmed v t e Equipment of the United States Air Force Ground systems C2 AN/USQ-163 Falconer AN/GSQ-272 Sentinel Ground vehicle HMMWV LSSV R-5 Refueler R-9 Refueler R-11 Refueler C300 Munitions Bomb Mk-82 Mk-84 GBU-8 GBU-10 Paveway II GBU-12 Paveway II GBU-15 GBU-24 Paveway III GBU-27 Paveway III GBU-28 GBU-31, GB-32, GB-38 JDAM GBU-39 Small Diameter Bomb GBU-43/B MOAB GBU-44/B Viper Strike GBU-53/B Small Diameter Bomb II GBU-54, GB-55, GB-56 Laser JDAM GBU-57 MOP GBU-72 CBU-87 Combined Effects Munition CBU-89 Gator CBU-97 Sensor Fuzed Weapon BLU-109 bomb BLU-116 Bunker Buster B61 nuclear bomb B83 nuclear bomb Gun GAU-8 Avenger M61 Vulcan GAU-12 GAU-13 GAU-19 M240 L/70 Bofors M102 howitzer GAU-23/A M2 Browning M134 Minigun Missile AIM-7 Sparrow AIM-9 Sidewinder LGM-30G Minuteman III AGM-65 Maverick AGM-84 Harpoon AGM-84E Standoff Land Attack Missile AGM-84H/K Standoff Land Attack Missile – Expanded Response AGM-86 ALCM AGM-88 HARM AGM-114 Hellfire AIM-120 AMRAAM AGM-130 Powered Standoff Weapon AGM-154 Joint Standoff Weapon AGM-158 JASSM AGM-176 Griffin Zuni rocket Target BQM-34 Firebee BQM-167 Subscale Aerial Target MQM-107 Streaker QF-16 Aerial Target Small arms Sidearm/PDW M11 Pistol M9 Pistol M17 Pistol MP5 submachine gun USAF Pilot's Survival Knife Rifle/carbine GUU-5/P Carbine M4 carbine M14 Stand-off Munitions Disruptor (SMUD) M16A2 Rifle M24 sniper weapon system M107 Long Range Sniper Rifle Mk 14 Mod 0 Enhanced Battle Rifle Support/CQB M60 machine gun M2HB Browning machine gun M240B Medium Machine Gun M249 light machine gun M1014 shotgun Remington 870 MCS shotgun Ordnance M136 AT4 Light Anti-tank Weapon M18A1 Claymore Mine M18 smoke grenade M67 Fragmentation Grenade M72 Light Anti-tank Weapon (LAW) M79 grenade launcher MK-19 automatic grenade launcher Uniforms and other equipment Airman Battle Uniform Army Combat Uniform Flight Suit Physical Training Uniform Service Dress Uniform Mess dress CMU – 33A/P22P-18

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Adapted from the Wikipedia article [Delta II](https://en.wikipedia.org/wiki/Delta_II) by Wikipedia contributors ([contributor history](https://en.wikipedia.org/wiki/Delta_II?action=history)). Available under [Creative Commons Attribution-ShareAlike 4.0 International](https://creativecommons.org/licenses/by-sa/4.0/). Changes may have been made.