 | |
 Delta IV Medium launch carryingDSCS III-B6. | |
| Function | Orbitallaunch vehicle |
|---|---|
| Manufacturer | United Launch Alliance |
| Country of origin | United States |
| Cost per launch | US$164+ million[1] |
| Size | |
| Height | 63.0–70.7 m (206.7–232.0 ft) |
| Diameter | 5.1 m (17 ft) |
| Mass | 249,500–733,400 kg (550,100–1,616,900 lb) |
| Stages | 2 |
| Capacity | |
| Payload toLEO | |
| Mass | 11,470–28,790 kg (25,290–63,470 lb)[2] |
| Payload toGTO | |
| Mass | 4,440–14,220 kg (9,790–31,350 lb) |
| Associated rockets | |
| Family | Delta (rocket family) |
| Comparable | |
| Launch history | |
| Status | Retired |
| Launch sites | |
| Total launches | |
| Success(es) | 44
|
| Partial failure(s) | 1 (Heavy Demo) |
| First flight |
|
| Last flight | |
| Carries passengers or cargo | |
| Boosters (Medium+) –GEM 60 | |
| No. boosters | 2[a] or 4[b] |
| Gross mass | 33,638 kg (74,158 lb) |
| Maximum thrust | 826.6 kN (185,800 lbf) |
| Specific impulse | SL: 245 s (2.40 km/s) |
| Burn time | 91 seconds |
| Propellant | AP /HTPB /Al |
| Boosters (Heavy) –CBC | |
| No. boosters | 2 |
| Gross mass | 226,400 kg (499,100 lb) |
| Powered by | 1 × RS-68A |
| Maximum thrust | 3,140 kN (705,000 lbf) (sea level) |
| Specific impulse | SL: 360 s (3.5 km/s) vac: 412 s (4.04 km/s) |
| Burn time | 242 seconds[2] |
| Propellant | LH2 /LOX |
| First stage –CBC | |
| Gross mass | 226,400 kg (499,100 lb) |
| Powered by | 1 × RS-68A |
| Maximum thrust | 3,140 kN (705,000 lbf) (sea level) |
| Specific impulse | SL: 360 s (3.5 km/s) vac: 412 s (4.04 km/s) |
| Burn time | 245 seconds (328 seconds in Heavy configuration)[2] |
| Propellant | LH2 /LOX |
| Second stage –DCSS | |
| Gross mass | 4-m: 24,170 kg (53,290 lb) 5-m: 30,700 kg (67,700 lb) |
| Powered by | 1 × RL10-B-2 |
| Maximum thrust | 110 kN (25,000 lbf) |
| Specific impulse | 462 s (4.53 km/s) |
| Burn time | 850–1,125 seconds |
| Propellant | LH2 /LOX |
Delta IV was a group of fiveexpendable launch systems in theDelta rocket family. It flew 45 missions from 2002 to 2024. Originally designed byBoeing's Defense, Space and Security division for theEvolved Expendable Launch Vehicle (EELV) program, the Delta IV became aUnited Launch Alliance (ULA) product in 2006. The Delta IV was primarily a launch vehicle forUnited States Air Force (USAF) military payloads, but was also used to launch a number of United States government non-military payloads and a single commercial satellite.
The Delta IV had two main versions which allowed the family to cover a range of payload sizes and masses: the Medium (which had four configurations) andHeavy. The final flight of Medium occurred in 2019. The final flight of Heavy was in April 2024.
Delta IV vehicles were built in the ULA facility inDecatur, Alabama.[5] Final assembly was completed at the launch site by ULA: at thehorizontal integration facility for launches fromSLC-37B pad atCape Canaveral and in a similar facility for launches fromSLC-6 pad atVandenberg Space Force Base.
The latest evolutionary development of theDelta rocket family, Delta IV was introduced to meet the requirements of the United States Air Force's (USAF)Evolved Expendable Launch Vehicle (EELV, nowNational 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 toliquid hydrogen fuel, with new tankage and a new engine required.[6][7]
During the Delta IV's development, a small variant was considered. This would have featured theDelta II second stage, an optionalThiokolStar 48B third stage, and the Delta II payload fairing, all atop a singleCommon Booster Core (CBC).[8] The Small variant was dropped by 1999.[9][10]
In 2002, the Delta IV was first launched, with theRS-68 becoming the first largeliquid-propellant rocket engine designed in the United States since theSpace Shuttle main engine (SSME) in the 1970s.[11]
TheL3 Technologies Redundant Inertial Flight Control Assembly (RIFCA) guidance system originally used on the Delta IV was common to that carried on theDelta II, although the software was different because of the differences between the Delta II and Delta IV. The RIFCA featured sixring laser gyroscopes andaccelerometers each, to provide a higher degree of reliability.[12]
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.[13]
As of 2009, the USAF funded Delta IV EELV engineering, integration, and infrastructure work through contracts with Boeing Launch Services (BLS). On 8 August 2008, the USAFSpace and Missile Systems Center increased the "cost plus award fee" contract with BLS for US$1.656 billion to extend the period of performance through the 30 September 2008 (FY09). In addition, a US$557.1 million option was added to cover FY10.[14]
In February 2010, naturalized citizen Dongfan Chung, an engineer working with Boeing, was the first person convicted under theEconomic Espionage Act of 1996. Chung passed on classified information on designs including the Delta IV rocket to China and was sentenced to 15 years.[15]
In March 2015, ULA announced plans to phase out the Delta IV Medium by 2018.[16]
With the exception of the first launch, which carried theEutelsat W5 commercial communications satellite, all Delta IV launches have been paid for by the US government. In 2015, ULA stated that aDelta IV Heavy is sold for nearly US$400 million.[17]
The possibility of a higher performance Delta IV was first proposed in a 2006RAND Corporation study of national security launch requirements out to 2020. A singleNational Reconnaissance Office (NRO) payload required an increase in the lift capability of the Delta IV Heavy.[18] Lift capacity was increased by developing the higher-performanceRS-68A engine,[19] which first flew on 29 June 2012.[20] ULA phased out the baseline RS-68 engine with the launch of Delta flight 371 on 25 March 2015. All following launches used the RS-68A,[21] 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 foursolid-propellant rocket boosters. However, the new CBC led to a slight performance loss for most medium configurations.[22] The Delta IV Heavy required non-standard CBCs for the core and boosters.[23]
Payload capacities after RS-68A upgrade
| Version | Fairing | CBCs | SRBs | Payload toLEO 407 km x 51.6° | Payload toGTO 1800 m/s residual | Launches |
|---|---|---|---|---|---|---|
| Medium | 4 m | 1 | 0 | 8,510 kg[24] | 4,440 kg[2] | 0 |
| M+ (4,2) | 4 m | 1 | 2 | 12,000 kg[24] | 6,390 kg[2] | 2 |
| M+ (5,2) | 5 m | 1 | 2 | 10,220 kg[24] | 5,490 kg[2] | 2 |
| M+ (5,4) | 5 m | 1 | 4 | 12,820 kg[24] | 7,300 kg[2] | 4 |
| Heavy | 5 m | 3 | 0 | 25,980 kg[24] | 14,220 kg[2] | 9 |
Payload capacities with original RS-68
Version | Fairing | CBCs | SRBs | Payload toLEO 407 km x 51.6° | Payload toGTO 1800 m/s residual | Launches |
|---|---|---|---|---|---|---|
| Medium | 4 m | 1 | 0 | 8,800 kg[24] | 4,540 kg[25] | 3 |
| M+ (4,2) | 4 m | 1 | 2 | 11,920 kg[24] | 6,270 kg[25] | 13 |
| M+ (5,2) | 5 m | 1 | 2 | 10,580 kg[24] | 5,430 kg[25] | 1 |
| M+ (5,4) | 5 m | 1 | 4 | 13,450 kg[24] | 7,430 kg[25] | 4 |
| Heavy | 5 m | 3 | 0 | 22,980 kg[24] | 13,400 kg[25] | 7 |
*Masses include a Payload Attach Fitting (240 kg to 1,221 kg depending on payload).[2]
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 eight) strap-on CBCs, and a cryogenic propellant cross feed from strap on boosters to the common core.[26]
At one point, NASA planned to use Delta IV or Atlas V to launch the proposedOrbital Space Plane,[27] which eventually became theCrew Exploration Vehicle and then theOrion. Orion was intended to fly on theAres I launch vehicle, then theSpace Launch System after Ares I was cancelled.
In 2009,The Aerospace Corporation reported onNASA results of a study to determine the feasibility of modifying Delta IV to becrew-rated for use in NASAhuman spaceflight missions. According toAviation Week & Space Technology the study, "found that a Delta IV heavy [...] could meet NASA's requirements for getting humans to low Earth orbit".[28]
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 (16,500 lb), a LEO payload of 14,800 kg (32,600 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 (20,300 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.[29]
TheVulcan Centaur is planned to replace theAtlas V and Delta IV rockets. Vulcan Centaur had been projected to enter service by 2023, using theBE-4methane-fueled rocket engine,[30][31] but the first Vulcan launched on 8 January 2024.[32] The Atlas V is expected to stay in service for a few years after Vulcan's inaugural launch, and the Delta IV Heavy was discontinued in April 2024.[33]
The Delta IV Medium (also referred to as 'single stick'[34][35]) was available in four configurations: Medium, Medium+ (4,2), Medium+ (5,2), and Medium+ (5,4).[36]
The Delta IV Medium (Delta 9040) was the most basic Delta IV. It featured a single CBC and a modifiedDelta III second stage, with 4-meter liquid hydrogen and liquid oxygen tanks (called aDelta Cryogenic Second Stage (DCSS)) and a 4-meter payload fairing. The Delta IV Medium was capable of launching 4,200 kg togeostationary 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.[7]
The Delta IV Medium+ (4,2) (Delta 9240) had the same CBC and DCSS as the Medium, but with the addition of twoOrbital ATK-built 1.5-m (60-in) diametersolid rocket boosterGraphite-Epoxy Motors (GEM 60s)strap-on boosters to increase payload capacity to 6,150 kg to GTO.[7]
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.[7]
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.[7]
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.[37]
The Medium (4,2) version last flew on 22 August 2019, marking the retirement of the Delta IV Medium variants.[36][38]
The Delta IV Heavy (Delta 9250H) combines a 5 m (16 ft) diameter DCSS and payload fairing with two additional CBCs. These are strap-on boosters which areseparated 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,[26] with an aluminum isogrid fairing also available. The aluminum trisector (three-part) fairing was built byBoeing and derived from aTitan IV fairing.[37] The trisector fairing was first used on theDSP-23 flight.[39] The Delta IV with the extended fairing is over 62 m (203 ft) tall. The last launch took place on 9 April 2024, carrying the NROL-70 satellite, marking the conclusion of the Delta rocket family.
Each Delta IV consists of at least oneCommon Booster Core (CBC). Each CBC is powered by oneAerojet RocketdyneRS-68 engine, which burnsliquid hydrogen andliquid 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.[40] 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 again throttles up to 102% before throttling back down to 58% prior to main engine cutoff.[41]
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 analuminumisogrid (a grid pattern machined out of the inside of the tank to reduce weight) liquid hydrogen tank, followed by acomposite 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 m (16 ft) diameter.[11]
The upper stage of the Delta IV was theDelta Cryogenic Second Stage (DCSS). The DCSS was based on theDelta III upper stage but has increased propellant capacity. Two versions have been produced: a 4 m (13 ft) diameter DCSS that was retired with the Delta IV Medium and a 5 m (16 ft) 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 oneRL10B-2 engine, with an extendable carbon-carbon nozzle to improve specific impulse.[42] 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.[43][44]
Delta IV launched from either of two rocketlaunch complexes. Launches on the East coast of the United States usedSpace Launch Complex 37 (SLC-37) at theCape Canaveral Air Force Station. On the West coast, polar-orbit and high-inclination launches usedVandenberg Space Force Base'sSpace Launch Complex 6 (SLC-6).[45]
Launch facilities at both sites are similar. AHorizontal 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.[45] The partial horizontal rocket assembly of the Delta IV is somewhat similar to theSoyuz launch vehicle, which is completely assembled horizontally. TheSpace Shuttles, the pastSaturn launch vehicles, and theSpace 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 was 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.[45]
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 was completed on the launch pad inside a building. ThisMobile Service Tower (MST) provides service access to the rocket and protection from the weather and is rolled away from the rocket on launch day. 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.[45]
Beside the vehicle is a Fixed Umbilical Tower (FUT), which has two (VSFB) 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.[45]
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 used two long-stroke hydraulic pistons to raise the vehicle to the vertical position after being rolled to the pad from the HIF. Beneath the Launch Table is a flame duct, which deflects the rocket's exhaust away from the rocket or facilities.[45]
Delta IV CBCs and DCSSs are assembled at ULA's factory inDecatur, Alabama. They are then loaded onto theR/SRocketShip, aroll-on/roll-off cargovessel, and shipped to either launch pad. There, they are offloaded and rolled into a 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.[46]
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.[46]
| No. | Date/Time (UTC) | Type | Serial no. | Start place | Payload | Payload type | Orbit | Outcome | Remarks |
|---|---|---|---|---|---|---|---|---|---|
| 1 | 20 November 2002 22:39 | Medium+ (4,2) | 293 | CCAFS,SLC-37B | Eutelsat W5 | Commercialcommunications 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[47] /3CS-1 /3CS-2 | Demonstration payload | GSO (planned) | Partial failure |
|
| 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.[50] |
| 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 aLEO/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.[51] |
| 9 | 2009-01-18 02:47[52][53] | Heavy | 337 | CCAFS,SLC-37B | USA-202 (NROL-26) | Reconnaissance satellite | GSO | Success[54] | |
| 10 | 2009-06-27 22:51[55] | Medium+ (4,2) | 342 | CCAFS,SLC-37B | GOES 14 (GOES-O) | Weather satellite | GTO | Success[56] | |
| 11 | 2009-12-06 01:47[57] | Medium+ (5,4) | 346 | CCAFS,SLC-37B | USA-211 (WGS-3) | Military communications satellite | GTO | Success[57] | 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[58] | |
| 13 | 2010-05-28 03:00 | Medium+ (4,2) | 349 | CCAFS,SLC-37B | USA-213 (GPS IIF-1) | Navigation Satellite | MEO | Success[59] | |
| 14 | 2010-11-21 22:58[52] | Heavy | 351 | CCAFS,SLC-37B | USA-223 (NROL-32) | Reconnaissance satellite | GSO | Success[60] | |
| 15 | 2011-01-20 21:10 | Heavy | 352 | VAFB,SLC-6 | USA-224 (NROL-49) | Reconnaissance satellite | LEO | Success[61] | First Delta IV Heavy launch from Vandenberg.[61] |
| 16 | 2011-03-11 23:38[52] | Medium+ (4,2) | 353 | CCAFS,SLC-37B | USA-227 (NROL-27) | Reconnaissance satellite | GTO | Success[62] | |
| 17 | 2011-07-16 06:41 | Medium+ (4,2) | 355 | CCAFS,SLC-37B | USA-232 (GPS IIF-2) | Navigation Satellite | MEO | Success[63] | |
| 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 | First flight of the RS-68A engine.[20] |
| 21 | 2012-10-04 12:10 | Medium+ (4,2) | 361 | CCAFS,SLC-37B | USA-239 (GPS IIF-3) | Navigation Satellite | MEO | Success[64] | Upper stage (DCSS) anomaly caused by fuel leak, payload still reached planned orbit.[65] |
| 22 | 2013-05-25 00:27 | Medium+ (5,4) | 362 | CCAFS,SLC-37B | USA-243 (WGS-5) | Military communications satellite | GTO | Success[66] | |
| 23 | 2013-08-08 00:29 | Medium+ (5,4) | 363 | CCAFS,SLC-37B | USA-244 (WGS-6) | Military communications satellite | GTO | Success[67] | |
| 24 | 2013-08-28 18:03 | Heavy | 364 | VAFB,SLC-6 | USA-245 (NROL-65) | Reconnaissance satellite | LEO | Success[68] | |
| 25 | 2014-02-21 01:59 | Medium+ (4,2) | 365 | CCAFS,SLC-37B | USA-248 (GPS IIF-5) | Navigation Satellite | MEO | Success[69] | |
| 26 | 2014-05-17 00:03 | Medium+ (4,2) | 366 | CCAFS,SLC-37B | USA-251 (GPS IIF-6) | Navigation Satellite | MEO | Success[70] | |
| 27 | 2014-07-28 23:28 | Medium+ (4,2) | 368 | CCAFS,SLC-37B | AFSPC-4 (GSSAP #1/2 andANGELS) (USA-253/254/255) | Space surveillance and technology demonstrator | GEO | Success[71] | First use of secondary payload adapter on a Delta rocket. |
| 28 | 2014-12-05 12:05 | Heavy | 369 | CCAFS,SLC-37B | Orion MPCVEFT-1 | Uncrewed Capsule Test Flight | MEO | Success[72] | |
| 29 | 2015-03-25 18:36 | Medium+ (4,2) | 371 | CCAFS,SLC-37B | USA-260 (GPS IIF-9) | Navigation Satellite | MEO | Success[73] | Final launch with baselineRS-68 engine.[21] |
| 30 | 2015-07-24 00:07 | Medium+ (5,4) | 372 | CCAFS,SLC-37B | USA-263 (WGS-7) | Military communications satellite | GTO | Success[74] | |
| 31 | 2016-02-10 11:40 | Medium+ (5,2) | 373 | VAFB,SLC-6 | USA-267 (NROL-45) | Reconnaissance satellite | LEO | Success[75] | |
| 32 | 2016-06-11 17:51 | Heavy | 374 | CCAFS,SLC-37B | USA-268 (NROL-37) | Reconnaissance satellite | GSO | Success[76][77] | |
| 33 | 2016-08-19 04:52 | Medium+ (4,2) | 375 | CCAFS,SLC-37B | AFSPC-6 (GSSAP #3/4) (USA-270/271) | Space surveillance | GEO | Success[78] | |
| 34 | 2016-12-07 23:53 | Medium+ (5,4) | 376 | CCAFS,SLC-37B | USA-272 (WGS-8) | Military communications satellite | GTO | Success[79] | |
| 35 | 2017-03-19 00:18 | Medium+ (5,4) | 377 | CCAFS,SLC-37B | USA-275 (WGS-9) | Military communications satellite | GTO | Success[80] | |
| 36 | 2018-01-12 22:11 | Medium+ (5,2) | 379 | VAFB,SLC-6 | USA-281 (NROL-47) | Reconnaissance satellite | LEO | Success[81] | 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 withStar 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[82] | Final flight of the Delta IV Medium and the Delta IV M+ (4,2) variant.[82] |
| 41 | 2020-12-11 01:09 | Heavy | 385 | CCSFS,SLC-37B | USA-311 (NROL-44) | Reconnaissance satellite | GSO | Success[83] | |
| 42 | 2021-04-26 20:47 | Heavy | 386 | VAFB,SLC-6 | USA 314 (NROL-82) | Reconnaissance satellite | LEO | Success[84] | |
| 43 | 2022-09-24 22:25 | Heavy | 387 | VAFB,SLC-6 | USA 338 (NROL-91) | Reconnaissance satellite | LEO | Success[85] | Final flight of Delta IV fromVSFB |
| 44 | 2023-06-22 09:18 | Heavy | 388 | CCSFS,SLC-37B | USA-345 (NROL-68) | Reconnaissance satellite | GSO | Success[86] | |
| 45 | 2024-04-09 16:53 | Heavy | 389 | CCSFS,SLC-37B | USA-353 (NROL-70) | Reconnaissance satellite | GSO | Success[87] | Final flight of the Delta IV rocket and of the wholeDelta rocket family. |
_NROL-22_launch_1.jpg)
The first payload launched with a Delta IV was theEutelsat W5 communications satellite. A Medium+ (4,2) from Cape Canaveral carried the communications satellite intogeostationary 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 tocavitation 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:
NROL-22 was the first Delta IV launched fromSLC-6 atVandenberg Space Force Base (VSFB). It was launched aboard a Medium+ (4,2) in June 2006 carrying a classified satellite for the U.S.National Reconnaissance Office (NRO).
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 theUnited Launch Alliance, a joint venture between Boeing andLockheed Martin. The main payload was the 23rd and finalDefense Support Program missile-warning satellite,DSP-23. Launch from Cape Canaveral occurred on 10 November 2007.[89]
NROL-26 was the first Delta IV Heavy EELV launch for the NRO.USA 202, a classifiedreconnaissance satellite, lifted off 18 January 2009.[90]
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.[91]
NROL-49 lifted off from Vandenberg AFB on 20 January 2011.[52] 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.[92]
On 4 October 2012, a Delta IV M+ (4,2) experienced an anomaly in the upper stage'sRL10B-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 satelliteUSA-239, 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.[93] By December 2012, ULA had determined the cause of the anomaly to be a fuel leak (into the combustion chamber[94]), and Delta IV launches resumed in May 2013. After two more successful launches, further investigation led to the delay of Delta flight 365 with theGPS IIF-5 satellite.[95] Originally scheduled to launch in October 2013, the vehicle lifted off on 21 February 2014.[96]
A Delta IV Heavy launched theOrion spacecraft on an uncrewed test flight,EFT-1, on 5 December 2014.[97] The launch was originally planned for 4 December 2014, but high winds and valve issues caused the launch to be rescheduled for 5 December 2014.[98]
On August 12, 2018, another Delta IV Heavy launched theParker Solar Probe on a mission to explore or "touch" the outer corona of the Sun.[99]
The secondGPS Block III satellite was launched with the final Delta IV Medium+ (4,2) configuration rocket on 22 August 2019.[82]
The final flight from Vandenberg of the Delta IV Heavy launched theNROL-91 mission in September 2022.
The final flight from Cape Canaveral of the Delta IV Heavy and of the Delta rocket family took place in April 2024 carrying theNROL-70 mission.
"You could launch a smaller human vehicle on a current expendable rocket [...] In fact, before the Columbia disaster NASA teams were working on an Orbital Space Plane (OSP) designed to do just that".
This article incorporates text from this source, which is in thepublic domain. This article incorporates text from this source, which is in thepublic domain.
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