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Delta IV

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This article is about the rocket. For other uses, see Delta 4 (disambiguation).

Delta IV is a group of five expendable launch systems in the Delta rocket family introduced in the early 2000s. Originally designed by Boeing's Defense, Space & Security division for the Evolved Expendable Launch Vehicle (EELV) program, the Delta IV became a United Launch Alliance (ULA) product in 2006. The Delta IV was and is primarily a launch vehicle for United States Air Force military payloads, but has also been used to launch a number of U.S. government non-military payloads and a single commercial satellite.

Delta IV (Delta 9000)
Delta IV Medium launch carrying DSCS III-B6
FunctionOrbital launch vehicle
ManufacturerUnited Launch Alliance
Country of originUnited States
Cost per launchUS$164+ million[1]
Size
Height63–72 m (207–236 ft)
Diameter5 m (16 ft)
Mass249,500–733,400 kg (550,100–1,616,900 lb)
Stages2
Capacity
Payload to LEO11,470–28,790 kg (25,290–63,470 lb)[2]
Payload to
GTO		4,440–14,220 kg (9,790–31,350 lb)
Associated rockets
FamilyDelta (rocket family)
Comparable
Launch history
StatusDelta IV Heavy is active; Delta IV Medium, M+(4,2), M+(5,2), and M+(5,4) retired.
Launch sitesSLC-37B, Cape Canaveral
SLC-6, Vandenberg AFB
Total launches
40
  • Medium: 3
  • M+ (4,2): 15
  • M+ (5,2): 3
  • M+ (5,4): 8
  • Heavy: 11
Success(es)
39
  • Medium: 3
  • M+ (4,2): 15
  • M+ (5,2): 3
  • M+ (5,4): 8
  • Heavy: 10
Partial failure(s)1 (Heavy)
First flight
Last flight
  • Medium/M+: 22 August 2019 (USA-293/GPS III-2)
  • Heavy: 19 January 2019 (NROL-71)
Type of passengers/cargo
Boosters (Medium+) – GEM 60
No. boostersMedium+ (4,2), Medium+ (5,2): 2
Medium+ (5,4): 4
Gross mass33,638 kg (74,158 lb)
Powered byoff
Maximum thrust826.6 kN (185,800 lbf)
Specific impulse245 s (2.40 km/s) (sea level)
Burn time91 seconds
PropellantHTPB / Aluminum
Boosters (Heavy) – CBC
No. boosters2
Gross mass226,400 kg (499,100 lb)
Powered by1 RS-68A
Maximum thrust3,140 kN (705,000 lbf) (sea level)
Specific impulseSea level: 360 s (3.5 km/s)
Vacuum: 412 s (4.04 km/s)
Burn time242 seconds[2]
PropellantLH2 / LOX
First stage – CBC
Gross mass226,400 kg (499,100 lb)
Powered by1 RS-68A
Maximum thrust3,140 kN (705,000 lbf) (sea level)
Specific impulseSea level: 360 s (3.5 km/s)
Vacuum: 412 s (4.04 km/s)
Burn time245 seconds (328 seconds in Heavy configuration)[2]
PropellantLH2 / LOX
Second stage – DCSS
Gross mass4-m: 24,170 kg (53,290 lb)
5-m: 30,700 kg (67,700 lb)
Powered by1 RL10-B-2
Maximum thrust110 kN (25,000 lbf)
Specific impulse462 s (4.53 km/s)
Burn time850-1,125 seconds
PropellantLH2 / LOX
[edit on Wikidata]

The Delta IV originally had two main versions which allowed the family to cover a range of payload sizes and masses: the retired Medium (which had four configurations) and Heavy. As of 2019, only the Heavy remains active, with payloads that would previously fly on Medium moving to either the existing Atlas V or the forthcoming Vulcan. Retirement of the Delta IV is anticipated in 2024.

Delta IV vehicles are built in the ULA facility in Decatur, Alabama.[3] Final assembly is completed at the launch site by ULA: at the Horizontal Integration Facility for launches from SLC-37B pad at Cape Canaveral and in a similar facility for launches from SLC-6 pad at Vandenberg Air Force Base.

History

The latest evolutionary development of the Delta rocket family, Delta IV was introduced to meet the requirements of the United States Air Force's (USAF's) Evolved Expendable Launch Vehicle (EELV, now national security space launch/NSSL) program. While the Delta IV retains the name of the Delta family of rockets, major changes were incorporated. Perhaps the most significant change was the switch from kerosene to liquid hydrogen fuel, with new tankage and a new engine required.[citation needed]

During the Delta IV's development, a Small variant was considered. This would have featured the Delta II second stage, an optional Thiokol Star 48B third stage, and the Delta II payload fairing, all atop a single CBC.[4] The Small variant was dropped by 1999.[5][6]

In 2002, the Delta IV was first launched, with the RS-68 becoming the first large liquid-propellant rocket engine designed in the U.S. since the Space Shuttle main engine (SSME) in the 1970s.[7] The primary goal for the RS-68 was to reduce cost versus the SSME. Some sacrifice in chamber pressure and specific impulse was made, hurting efficiency; however, development time, part count, total cost, and assembly labor were reduced to a fraction of the SSME, despite the RS-68's significantly larger size.

The L3 Technologies Redundant Inertial Flight Control Assembly (RIFCA) guidance system originally used on the Delta IV was common to that carried on the Delta II, although the software was different because of the differences between the Delta II and Delta IV. The RIFCA featured six ring laser gyroscopes and accelerometers each, to provide a higher degree of reliability.[8]

Boeing initially intended to market Delta IV commercial launch services. However, the Delta IV entered the space launch market when global capacity was already much higher than demand. Furthermore, as an unproven design it had difficulty finding a market in commercial launches, and Delta IV launch costs are higher than comparable vehicles of the same era. In 2003, Boeing pulled the Delta IV from the commercial market, citing low demand and high costs. In 2005, Boeing stated that it sought to return the Delta IV to commercial service.[9]

As of 2009, the USAF funded Delta IV EELV engineering, integration, and infrastructure work through contracts with Boeing Launch Services (BLS). On August 8, 2008 the USAF Space and Missile Systems Center increased the "cost plus award fee" contract with BLS for $1.656 billion to extend the period of performance through the end of FY09. In addition a $557.1 million option was added to cover FY10.[10] However, the Delta IV series was at that time launched by the United Launch Alliance (ULA), a joint venture between Boeing and Lockheed Martin.[citation needed]

In February 2010, Naturalized citizen Dongfan Chung, an engineer working with Boeing, was the first person convicted under the Economic Espionage Act of 1996. Chung passed on classified information on designs including the Delta IV rocket and was sentenced to 15 years.[11]

In March 2015, ULA announced plans to phase out the Delta IV Medium by 2018.[12] The Delta IV will be replaced by the Atlas V in the near term and Vulcan in the far term.[13] The Delta IV Medium was actually retired on 22 August 2019.

With the exception of the first launch, which carried the Eutelsat W5 commercial communications satellite, all Delta IV launches have been paid for by the US government. In 2015, ULA stated that a Delta IV Heavy is sold for nearly $400 million.[14]

RS-68A booster engine upgrade

The possibility of a higher performance Delta IV was first proposed in a 2006 RAND Corporation study of national security launch requirements out to 2020. A single National Reconnaissance Office (NRO) payload required an increase in the lift capability of the Delta IV Heavy.[15] Lift capacity was increased by the development of the higher-performance RS-68A engine,[16] and launched on June 29, 2012.[17] ULA phased out the baseline RS-68 engine with the launch of Delta flight 371 on March 25, 2015. All launches since then have used the RS-68A,[18] and the engine's higher thrust allowed the use of a single standardized CBC design for all Delta IV Medium and M+ versions. This upgrade reduced cost and increased flexibility, since any standardized CBC could be configured for zero, two, or four solid boosters. However, the new CBC led to a slight performance loss for most medium configurations.[19] The Delta IV Heavy still requires non-standard CBCs for the core and boosters.[20]

Payload capacities after RS-68A upgrade

Version Fairing CBCs SRBs Payload to LEO

407 km x 51.6°

Payload to GTO

1800 m/s residual

Launches to date
Medium 4 m 1 0 8,510 kg[21] 4,440 kg[2] 0
M+(4,2) 4 m 1 2 12,000 kg[21] 6,390 kg[2] 2
M+(5,2) 5 m 1 2 10,220 kg[21] 5,490 kg[2] 2
M+(5,4) 5 m 1 4 12,820 kg[21] 7,300 kg[2] 4
Heavy 5 m 3 0 25,980 kg[21] 14,220 kg[2] 4

Payload capacities with original RS-68

Version

Fairing

CBCs

SRBs

Payload to LEO

407 km x 51.6°

Payload to GTO

1800 m/s residual

Launches to date

Medium 4 m 1 0 8,800 kg[21] 4,540 kg[22] 3
M+(4,2) 4 m 1 2 11,920 kg[21] 6,270 kg[22] 13
M+(5,2) 5 m 1 2 10,580 kg[21] 5,430 kg[22] 1
M+(5,4) 5 m 1 4 13,450 kg[21] 7,430 kg[22] 4
Heavy 5 m 3 0 22,980 kg[21] 13,400 kg[22] 7

*Masses include a Payload Attach Fitting (240 kg to 1,221 kg depending on payload).[2]

Proposed upgrades that were not implemented

Possible future upgrades for the Delta IV included adding extra strap-on solid motors, higher-thrust main engines, lighter materials, higher-thrust second stages, more (up to six) strap-on CBCs, and a cryogenic propellant cross feed from strap on boosters to the common core.[23]

At one point NASA planned to use Delta IV or Atlas V to launch the proposed Orbital Space Plane,[24] which eventually became the Crew Exploration Vehicle and then the Orion. Orion was intended to fly on the Ares I launch vehicle, then the Space Launch System after Ares I was cancelled.

In 2009 The Aerospace Corporation reported on NASA results of a study to determine the feasibility of modifying Delta IV to be human-rated for use in NASA human spaceflight missions. According to Aviation Week the study, "found that a Delta IV heavy [...] could meet NASA's requirements for getting humans to low Earth orbit."[25]

A proposed upgrade to the Delta IV family was the addition of extra solid motors. The Medium+(4,4) would have used existing mount points to pair the four GEM-60s of the M+(5,4) with the upper stage and fairing of the (4,2). An M+(4,4) would have had a GTO payload of 7,500 kg (16,600 lb), a LEO payload of 14,800 kg (32,700 lb), and could have been available within 36 months of the first order. It was also considered to add extra GEM-60s to the M+(5,4), which would have required adding extra attachment points, structural changes to cope with the different flight loads, and launch pad and infrastructure changes. The Medium+(5,6) and (5,8) would have flown with six and eight SRBs respectively, for a maximum of up to 9,200 kg/20,200 lb to GTO with the M+(5,8). The Medium+(5,6) and (5,8) could have been available within 48 months of the first order.[26]

Planned successor

The Vulcan rocket is planned to replace the Atlas V and Delta IV rockets. Vulcan is projected to enter service by 2021, using the Blue Origin BE-4 methane-fueled rocket engine.[27] The Delta IV Heavy and Atlas V are expected to stay in service for a few years after Vulcan's inaugural launch, and the Heavy is expected to be discontinued by 2024.[28]

Vehicle description

 
Delta IV evolution

Delta IV Medium

The Delta IV Medium was available in four configurations: Medium, Medium+ (4,2), Medium+ (5,2), and Medium+ (5,4).

The Delta IV Medium (Delta 9040) was the most basic Delta IV. It featured a single CBC and a modified Delta III second stage, with 4-meter liquid hydrogen and liquid oxygen tanks and a 4-meter payload fairing. The Delta IV Medium was capable of launching 4,200 kg to geosynchronous transfer orbit (GTO). From Cape Canaveral, GTO is 1804 m/s away from GEO. The mass of fairing and payload attach fittings have been subtracted from the gross performance.[29] It flew last time on 22 August 2019.[30]

The Delta IV Medium+ (4,2) (Delta 9240) had the same CBC and DCSS as the Medium, but with the addition of two Orbital ATK-built 1.5-m (60-in) diameter solid rocket booster Graphite-Epoxy Motors (GEM-60s) strap-on boosters to increase payload capacity to 6,150 kg to GTO.[29]

The Delta IV Medium+ (5,2) (Delta 9250) was similar to the Medium+ (4,2), but had a 5-m–diameter DCSS and payload fairing for larger payloads. Because of the extra weight of the larger payload fairing and second stage, the Medium+ (5,2) could launch 5,072 kg to GTO.[29]

The Delta IV Medium+ (5,4) (Delta 9450) was similar to the Medium+ (5,2), but used four GEM-60s instead of two, enabling it to lift 6,882 kg to GTO.[29]

To encapsulate the satellite payload, a variety of different payload fairings were available. A stretched Delta III 4 meter diameter composite payload fairing was used on 4 meter Medium versions, while an enlarged, 5 meter diameter composite fairing was used on 5 meter Medium versions.[31]

Delta IV Heavy

 
Delta IV Heavy launching
Main article: Delta IV Heavy

The Delta IV Heavy (Delta 9250H) combines a 5-meter (16 ft) diameter DCSS and payload fairing with two additional CBCs. These are strap-on boosters which are separated earlier in the flight than the center CBC. As of 2007, a longer 5 meter diameter composite fairing was standard on the Delta IV Heavy,[23] with an aluminum isogrid fairing also available. The aluminum trisector (three-part) fairing was built by Boeing and derived from a Titan IV fairing.[31] The trisector fairing was first used on the DSP-23 flight.[32] The Delta IV with the extended fairing is over 62 m (205 ft) tall.

Common Booster Core

Main article: Common Booster Core

Each Delta IV consists of at least one Common Booster Core (CBC). Each CBC is powered by one Aerojet Rocketdyne RS-68 engine, which burns liquid hydrogen and liquid oxygen.

On flights of the Medium, the RS-68 ran at 102% rated thrust for the first few minutes of flight, and then throttled down to 58% rated thrust before main engine cutoff.[33] On the Heavy, the main CBC's engine throttles down to 58% rated thrust around 50 seconds after liftoff, while the strap-on CBCs remain at 102%. This conserves propellant and allows the main CBC to burn after booster separation. After the strap-on CBCs separate, the main CBC's engine throttles back up to 102% before throttling back down to 58% prior to main engine cutoff.[34]

The RS-68 engine is mounted to the lower thrust structure of the CBC by a four-legged (quadrapod) thrust frame and enclosed in a protective composite conical thermal shield. Above the thrust structure is an aluminum isogrid (a grid pattern machined out of the inside of the tank to reduce weight) liquid hydrogen tank, followed by a composite cylinder called the centerbody, an aluminum isogrid liquid oxygen tank, and a forward skirt. Along the back of the CBC is a cable tunnel to hold electrical and signal lines, and a feedline to carry the liquid oxygen to the RS-68 from the tank. The CBC is of a constant, 5-meter (16.4 ft) diameter.[7]

Delta Cryogenic Second Stage

 
Delta IV 4-Meter Second Stage
Main article: Delta Cryogenic Second Stage

The upper stage of the Delta IV is the Delta Cryogenic Second Stage (DCSS). The DCSS is based on the Delta III upper stage but has increased propellant capacity. Two versions have been produced: a 4-meter (13.1 ft) diameter DCSS that was retired with the Delta IV Medium and a 5-meter diameter DCSS that remains in service with the Delta IV Heavy. The 4 m diameter version lengthened both Delta III propellant tanks, while the 5-meter version has an extended diameter liquid hydrogen tank and a further lengthened liquid oxygen tank. Regardless of the diameter, each DCSS is powered by one RL10B2 engine, with an extendable carbon-carbon nozzle to improve specific impulse.[35] Two different interstages are used to mate the first stage and DCSS. A tapering interstage that narrowed down from 5 m to 4 m diameter was used to mate the 4 m DCSS to the CBC, while a cylindrical interstage is used to mate the 5 m DCSS. Both interstages were built from composites and enclosed the liquid oxygen tank, with the larger liquid hydrogen tank making up part of the vehicle's outer mold line.[36][37]

Launch sites

 
First Delta IV Heavy with three CBCs prior to launch

Delta IV launches occur from either of two rocket launch complexes. Launches on the East coast of the United States use Space Launch Complex 37 (SLC-37) at the Cape Canaveral Air Force Station. On the West coast, polar-orbit and high-inclination launches use Vandenberg Air Force Base's Space Launch Complex 6 (SLC-6).[38]

Launch facilities at both sites are similar. A Horizontal Integration Facility (HIF) is situated some distance from the pad. Delta IV CBCs and second stages to be mated and tested in the HIF before they are moved to the pad.[38] The partial horizontal rocket assembly of the Delta IV is somewhat similar to the Soyuz launch vehicle, which is completely assembled horizontally. The Space Shuttles, the past Saturn launch vehicles, and the upcoming Space Launch System are assembled and rolled out to the launch pad entirely vertically.[citation needed]

Movement of the Delta IVs among the various facilities at the pad is facilitated by rubber-tired Elevating Platform Transporters (EPTs) and various transport jigs. Diesel engine EPTs are used for moving the vehicles from the HIF to the pad, while electric EPTs are used in the HIF, where precision of movement is important.[38]

The basic launchpad structure includes a flame trench to direct the engine plume away from the rocket, lightning protection, and propellant storage. In the case of Delta IV, the vehicle is assembled inside a building that is moved to the launch pad on rails. This Mobile Service Tower (MST) provides service access to the rocket and protection from the weather. A crane at the top of the MST lifts the encapsulated payload to the vehicle and also attached the GEM-60 solid motors for Delta IV Medium launches. The MST is rolled away from the rocket several hours before launch. At Vandenberg, the launch pad also has a Mobile Assembly Shelter (MAS), which completely encloses the vehicle; at CCAFS, the vehicle is partly exposed near its bottom.[38]

Beside the vehicle is a Fixed Umbilical Tower (FUT), which has two (VAFB) or three (CCAFS) swing arms. These arms carry telemetry signals, electrical power, hydraulic fluid, environmental control air flow, and other support functions to the vehicle through umbilical lines. The swing arms retract at T-0 seconds once the vehicle is committed to launch.[38]

Under the vehicle is a Launch Table, with six Tail Service Masts (TSMs), two for each CBC. The Launch Table supports the vehicle on the pad, and the TSMs provide further support and fueling functions for the CBCs. The vehicle is mounted to the Launch Table by a Launch Mate Unit (LMU), which is attached to the vehicle by bolts that sever at launch. Behind the Launch Table is a Fixed Pad Erector (FPE), which uses two long-stroke hydraulic pistons to raise the vehicle to the vertical position after being rolled to the pad from the Horizontal Integration Facility (HIF). Beneath the Launch Table is a flame duct, which deflects the rocket's exhaust away from the rocket or facilities.[38]

Vehicle processing

Delta IV CBCs and DCSSs are assembled at ULA's factory in Decatur, Alabama. They are then loaded onto the M/V Delta Mariner, a roll-on/roll-off cargo vessel, and shipped to either launch pad. There, they are offloaded and rolled into a Horizontal Integration Facility (HIF). For Delta IV Medium launches, the CBC and DCSS were mated in the HIF. For Delta IV Heavy launches, the port and starboard strap-on CBCs are also mated in the HIF.[39]

Various tests are performed, and then the vehicle is rolled horizontally to the pad, where the Fixed Pad Erector (FPE) is used to raise the vehicle to the vertical position. At this time, the GEM-60 solid motors, if any are required, are rolled to the pad and attached to the vehicle. After further testing, the payload (which has already been enclosed in its fairing) is transported to the pad, hoisted into the MST by a crane, and attached to the vehicle. Finally, on launch day, the MST is rolled away from the vehicle, and the vehicle is ready for launch.[39]

Delta IV launches in chronological order

Further information: List of Thor and Delta launches (2000–09) and List of Thor and Delta launches (2010–19)
No. Date/Time
(UTC) 		Type Serial no. Start place Payload Payload type Orbit Outcome Remarks
1 2002-11-20
22:39 		Medium+(4,2) 293 CCAFS SLC-37B Eutelsat W5 Commercial communications satellite GTO Success First Delta IV launch
2 2003-03-11
00:59 		Medium 296 CCAFS SLC-37B USA-167 (DSCS-3 A3) Military communications satellite GTO Success First Delta IV Medium launch
First USAF EELV mission
3 2003-08-29
23:13 		Medium 301 CCAFS SLC-37B USA-170 (DSCS-3 B6) Military communications satellite GTO Success
4 2004-12-21
21:50 		Heavy 310 CCAFS SLC-37B DemoSat[40] / 3CS-1 / 3CS-2 Demonstration payload GSO (planned) Partial failure
  • First Delta IV Heavy launch
  • Premature cutoff of CBCs
  • DemoSat reached incorrect orbit, 3CS failed to reach orbit[41][42]
5 2006-05-24
22:11 		Medium+(4,2) 315 CCAFS SLC-37B GOES 13 (GOES-N) Weather satellite GTO Success
6 2006-06-28
03:33 		Medium+(4,2) 317 VAFB SLC-6 USA-184 (NROL-22) Reconnaissance satellite Molniya Success First Delta IV launch from Vandenberg[43]
7 2006-11-04
13:53 		Medium 320 VAFB SLC-6 USA-192 (DMSP F17) Military weather satellite SSO Success First Delta IV launch into a LEO/SSO, last flight of Delta IV Medium
8 2007-11-11
01:50 		Heavy 329 CCAFS SLC-37B USA-197 (DSP-23) Missile warning satellite GSO Success First Delta IV launch contracted by United Launch Alliance
Launch delayed due to damage to launch pad caused by a liquid oxygen leak[44]
9 2009-01-18
02:47[45][46] 		Heavy 337 CCAFS SLC-37B USA-202 (NROL-26) Reconnaissance satellite GSO Success[47]
10 2009-06-27
22:51[48] 		Medium+(4,2) 342 CCAFS SLC-37B GOES 14 (GOES-O) Weather satellite GTO Success[49]
11 2009-12-06
01:47[50] 		Medium+(5,4) 346 CCAFS SLC-37B USA-211 (WGS-3) Military communications satellite GTO Success[50] First Delta IV Medium+ (5,4) launch
12 2010-03-04
23:57 		Medium+(4,2) 348 CCAFS SLC-37B GOES 15 (GOES-P) Weather satellite GTO Success[51]
13 2010-05-28
03:00 		Medium+(4,2) 349 CCAFS SLC-37B USA-213 (GPS IIF-1) Navigation Satellite MEO Success[52]
14 2010-11-21
22:58[45] 		Heavy 351 CCAFS SLC-37B USA-223 (NROL-32) Reconnaissance satellite GSO Success[53]
15 2011-01-20
21:10 		Heavy 352 VAFB SLC-6 USA-224 (NROL-49) Reconnaissance satellite LEO Success[54] First Delta IV Heavy launch from Vandenberg[54]
16 2011-03-11
23:38[45] 		Medium+(4,2) 353 CCAFS SLC-37B USA-227 (NROL-27) Reconnaissance satellite GTO Success[55]
17 2011-07-16
06:41 		Medium+(4,2) 355 CCAFS SLC-37B USA-232 (GPS IIF-2) Navigation Satellite MEO Success[56]
18 2012-01-20
00:38 		Medium+(5,4) 358 CCAFS SLC-37B USA-233 (WGS-4) Military communications satellite GTO Success
19 2012-04-03
23:12 		Medium+(5,2) 359 VAFB SLC-6 USA-234 (NROL-25) Reconnaissance satellite LEO Success First flight in the Medium+(5,2) version
20 2012-06-29
13:15 		Heavy 360 CCAFS SLC-37B USA-237 (NROL-15) Reconnaissance satellite GSO Success[17] First flight of the RS-68A engine[17]
21 2012-10-04
12:10 		Medium+(4,2) 361 CCAFS SLC-37B USA-239 (GPS IIF-3) Navigation Satellite MEO Success[57] Upper stage (DCSS) anomaly caused by fuel leak, payload still reached planned orbit[58]
22 2013-05-25
00:27 		Medium+(5,4) 362 CCAFS SLC-37B USA-243 (WGS-5) Military communications satellite GTO Success[59]
23 2013-08-08
00:29 		Medium+(5,4) 363 CCAFS SLC-37B USA-244 (WGS-6) Military communications satellite GTO Success[60]
24 2013-08-28
18:03 		Heavy 364 VAFB SLC-6 USA-245 (NROL-65) Reconnaissance satellite LEO Success[61]
25 2014-02-21
01:59 		Medium+(4,2) 365 CCAFS SLC-37B USA-248 (GPS IIF-5) Navigation Satellite MEO Success[62]
26 2014-05-17
00:03 		Medium+(4,2) 366 CCAFS SLC-37B USA-251 (GPS IIF-6) Navigation Satellite MEO Success[63]
27 2014-07-28
23:28 		Medium+(4,2) 368 CCAFS SLC-37B AFSPC-4 (GSSAP #1/2 & ANGELS) (USA-253/4/5) Space surveillance and technology demonstrator GEO Success[64] First use of secondary payload adapter on a Delta rocket
28 2014-12-05
12:05 		Heavy 369 CCAFS SLC-37B EFT-1 Orion Test Flight MEO Success[65]
29 2015-03-25
18:36 		Medium+(4,2) 371 CCAFS SLC-37B USA-260 (GPS IIF-9) Navigation Satellite MEO Success[66] Final launch with baseline RS-68 engine[18]
30 2015-07-24
00:07 		Medium+(5,4) 372 CCAFS SLC-37B USA-263 (WGS-7) Military communications satellite GTO Success[67]
31 2016-02-10
11:40 		Medium+(5,2) 373 VAFB SLC-6 USA-267 (NROL-45) Reconnaissance satellite LEO Success[68]
32 2016-06-11
17:51 		Heavy 374 CCAFS SLC-37B USA-268 (NROL-37) Reconnaissance satellite GSO Success[69][70]
33 2016-08-19
04:52 		Medium+(4,2) 375 CCAFS SLC-37B AFSPC-6 (GSSAP #3/4) (USA-270/1) Space surveillance GEO Success[71]
34 2016-12-07
23:53 		Medium+(5,4) 376 CCAFS SLC-37B USA-272 (WGS-8) Military communications satellite GTO Success[72]
35 2017-03-19
00:18 		Medium+(5,4) 377 CCAFS SLC-37B USA-275 (WGS-9) Military communications satellite GTO Success[73]
36 2018-01-12
22:11 		Medium+(5,2) 379 VAFB SLC-6 USA-281 (NROL-47) Reconnaissance satellite LEO Success[74] Final flight of Delta IV M+(5,2) variant
37 2018-08-12
07:31 		Heavy 380 CCAFS SLC-37B Parker Solar Probe Solar Probe Heliocentric Success First use of Delta IV Heavy with Star 48BV third stage (9255H)
38 2019-01-19
19:10 		Heavy 382 VAFB SLC-6 USA-290 (NROL-71) Reconnaissance satellite LEO Success
39 2019-03-16
00:26 		Medium+(5,4) 383 CCAFS SLC-37B USA-291 (WGS-10) Military communications satellite GTO Success Final flight of Delta IV M+(5,4) variant
40 2019-08-22
13:06 		Medium+(4,2) 384 CCAFS SLC-37B USA-293 (GPS III-2) Navigation Satellite MEO Success[75] Final flight of the Delta IV Medium and the Delta IV M+(4,2) variant[75]

This list was last updated on August 22, 2019. For future launches, see List of Thor and Delta launches (2010–2019).

Notable launches

 
GOES-N launch on a Medium+ (4,2)
 
A unique aerial view of NROL-22 launch from SLC-6

The first payload launched with a Delta IV was the Eutelsat W5 communications satellite. A Medium+ (4,2) from Cape Canaveral carried the communications satellite into geostationary transfer orbit (GTO) on 20 November 2002.[citation needed]

Heavy Demo was the first launch of the Delta IV Heavy in December 2004 after significant delays due to bad weather. Due to cavitation in the propellant lines, sensors on all three CBCs registered depletion of propellant. The strap-on CBCs and then core CBC engines shut down prematurely, even though sufficient propellant remained to continue the burn as scheduled. The second stage attempted to compensate for the shutdown and burned until it ran out of propellant. This flight was a test launch carrying a payload of:

  • DemoSat – 6020 kg; an aluminum cylinder filled with 60 brass rods – planned to be carried to GEO; however due to the sensor faults, the satellite did not reach this orbit.
  • NanoSat-2, carried to low Earth orbit (LEO) – a set of two very small satellites of 24 and 21 kg, nicknamed Sparky and Ralphie – planned to orbit for one day. Given the under-burn, the two most likely did not reach a stable orbit.[76]

NROL-22 was the first Delta IV launched from SLC-6 at Vandenberg Air Force Base (VAFB). It was launched aboard a Medium+ (4,2) in June 2006 carrying a classified satellite for the U.S. National Reconnaissance Office (NRO).[citation needed]

DSP-23 was the first launch of a valuable payload aboard a Delta IV Heavy. This was also the first Delta IV launch contracted by the United Launch Alliance, a joint venture between Boeing and Lockheed Martin. The main payload was the 23rd and final Defense Support Program missile-warning satellite, DSP-23. Launch from Cape Canaveral occurred on November 10, 2007.[77]

NROL-26 was the first Delta IV Heavy EELV launch for the NRO. USA 202, a classified reconnaissance satellite, lifted off 18 January 2009.[78]

NROL-32 was a Delta IV Heavy launch, carrying a satellite for NRO. The payload is speculated to be the largest satellite sent into space. After a delay from 19 October 2010, the rocket lifted off on 21 November 2010.[79]

NROL-49 lifted off from Vandenberg AFB on January 20, 2011.[45] It was the first Delta IV Heavy mission to be launched out of Vandenberg. This mission was for the NRO and its details are classified.[80]

On October 4, 2012, a Delta IV M+ (4,2) experienced an anomaly in the upper stage's RL10-B-2 engine which resulted in lower than expected thrust. While the vehicle had sufficient fuel margins to successfully place the payload, a GPS Block IIF satellite, into its targeted orbit, investigation into the glitch delayed subsequent Delta IV launches and the next Atlas V launch (AV-034) due to commonality between the engines used on both vehicles' upper stages.[81] By December 2012, ULA had determined the cause of the anomaly to be a fuel leak, and Delta IV launches resumed in May 2013. After two more successful launches, further investigation led to the delay of Delta flight 365 with the GPS IIF-5 satellite.[82] Originally scheduled to launch in October 2013, the vehicle lifted off on February 21, 2014.[83]

A Delta IV Heavy launched the Orion spacecraft on an uncrewed test flight, EFT-1, on December 5, 2014.[84] The launch was originally planned for December 4, but high winds and valve issues caused the launch to be rescheduled for December 5.[85]

The second GPS Block III satellite was launched with the final Delta IV Medium in the +(4,2) configuration on 22 August 2019.[75]

See also

References

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