DELTA IV
For more than half a century, the Delta family of launch vehicles has achieved unparalleled success in providing access to space for our
Department of Defense (DOD), NASA, and commercial customers. From the earliest Delta rockets to the industry workhorse Delta II,
continual upgrades and improvements have led to the Delta IV, the most advanced Delta yet. Developed with the U.S. Air Force, the Delta IV
offers five configurations for launching all spacecraft types to all orbits. The common booster core (CBC) first stage, the Delta cryogenic
second stage, and a 4-m-diameter or 5-m-diameter payload fairing are common to all configurations. For additional performance at liftoff,
two or four solid rocket motors can be added. For the most demanding missions, the Delta IV Heavy, which launches with two additional
CBCs, provides the most performance of any U.S. launch vehicle available today. With a commitment to mission success, the Delta IV
continues its legacy of launching our nation’s mission-critical national security payloads.
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Product information as of 3/13. For mission-specific information, please refer to the Atlas V and Delta IV User's Guides available at www.ulalaunch.com or contact your ULA representative.
ATLAS V AND DELTA IV
ATLAS V
TECHNICAL SUMMARY
Since 1957, the Atlas rocket has been an integral part of the United States’ space program, supporting national defense missions,
launching Mercury astronauts to orbit, and sending spacecraft to the farthest reaches of the solar system. For nearly six decades, the
Atlas booster has undergone a series of continuous improvements, culminating in the current Atlas V Evolved Expendable Launch Vehicle
(EELV). Designed in partnership with the U.S. Air Force, the Atlas V’s modular design approach allows for multiple configurations to meet
specific customer requirements. All Atlas V launch vehicles consist of a common core booster first stage, a Centaur second stage, and
either a 4-m-diameter or a 5-m-diameter payload fairing. To accommodate larger spacecraft requiring additional thrust at liftoff, one to
three solid rocket boosters (SRB) can be added to the Atlas V 4-m vehicle, while the Atlas V 5-m vehicle can support up to five SRBs.
Flexibility, reliability and 100% mission success are the hallmarks of the Atlas V system, making it the launch vehicle of choice for the full
range of customer requirements.
ATLAS V PAYLOAD FAIRING ENVELOPES
911 dia
35.9
911 dia
35.9
PAYLOAD ADAPTERS
911 dia
35.9
3,708
146.0
dia
5,386
212.1
1,194
dia
47
4,011
157.9
3,750
147.6
dia
Large Payload
Fairing (LPF)
3,750
147.6
dia
4,011
157.9
Extended Payload
Fairing (EPF)
4-m Diameter
5,386
212.1
61.0 m/200 ft
1
914
36.0
1,829
72.0
3,750
147.6
dia
17
53.3 m/175 ft
18
4,011
157.9
6915
D1666
Clampband
Bolted Interface (Four Places)
1,666
dia
66
1,742
dia
69
Extra Extended
Payload Fairing (XEPF)
4-m Diameter
4-m Diameter
19
45.7 m/150 ft
2
38.1 m/125 ft
3
4
5
4,293
169.0
1,448
57.0
dia
1,448
57.0
dia
4,572
180.0
dia
C-Adapter
Bolted Interface (120/121 Places)
5,296
208.5
EELV Secondary
Payload Adapter (ESPA)
1,575
dia
62
1,575
dia
62
4,572
180.0
dia
8
24
25
22.9 m/75 ft
9
5,296
208.5
4,888
192.5
22
23
30.5 m/100 ft
Bolted Interface (120/121 Places)
16.
17.
18.
19.
20.
21.
22.
23.
24.
25.
26.
27.
28.
29.
30.
21
7
7,631
300.5
4,572
180.0
dia
12,192
480.0
All dimensions are mm
in
15.2 m/50 ft
10
7.6 m/25 ft
11
Payload Fairing (5-m Diameter)
Spacecraft
Payload Adapter
Centaur Forward Adapter
Centaur Forward Load Reactor Deck
Centaur Second-Stage
Centaur Second-Stage Fuel (LH2) Tank
Centaur Second-Stage Oxidizer (LO2) Tank
Centaur Second-Stage Engine (RL10)
First-Stage Oxidizer (LO2) Tank
Common Core Booster
Solid Rocket Booster (0-5)
First-Stage Fuel (RP-1) Tank
First-Stage Oxidizer (LO2) Feedline
First-Stage Engine (RD-180)
DELTA IV
20
6
1,448
57.0
dia
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16
Clampband
937
dia
37
3,708
146.0
dia
68.6 m/225 ft
B1194
A937
Clampband
5,386
212.1
ATLAS V
71.6 m/235 ft
Payload Fairing (5-m Diameter)
Spacecraft
Payload Attach Fitting (PAF)
Second-Stage Fuel (LH2) Tank
Second-Stage Oxidizer (LO2) Tank
Second-Stage Equipment Shelf
Second-Stage Engine (RL10B-2)
Interstage Adapter
First-Stage Oxidizer (LO2) Tank
Common Booster Core (CBC)
First-Stage Oxidizer (LO2) Feedline
First-Stage Fuel (LH2) Tank
Solid Rocket Motors
Thermal Shield
First-Stage Engine (RS-68A)
26
Short
Medium
5-m Diameter
27
Long
5-m Diameter
DUAL SPACECRAFT SYSTEM (DSS) ENVELOPES
5-m Diameter
Atlas V 5-m
Long
ATLAS V NAMING CONVENTION
Atlas V 551
0
Payload Fairing Diameter (Meters)
Number of Solid Rocket Boosters (0-5)
Number of Centaur Engines (1-2)
Aft Views
Delta IV 5-m
62.7-ft Long
DELTA IV PAYLOAD FAIRING ENVELOPES
4,727
186.1
1,322
52.1
dia
10,345
407.3
10,805
425.4
Atlas
4-m XEPF
Atlas V
401
Delta 4-m
38.5-ft Long
Atlas V
411
Atlas V
421
Atlas V
431
Atlas V
501
Atlas V
511
Atlas V
521
Atlas V
531
Atlas V
541
Atlas V
551
Delta IV
Medium
Delta IV
Medium+ (4,2)
Delta IV
Medium+ (5,2)
Delta IV
Medium+ (5,4)
Delta IV
Heavy
DELTA IV NAMING CONVENTION
28
12
912
35.9
dia
3,750
147.6
dia
38.5-ft Long
4-m Diameter
4,526
178.2
1,322
52.1
dia
4,727
186.1
6,570
258.7
5,273
207.6
11,268
443.6
5,788
227.9
4,572
180.0
dia
6,720
264.5
47.0-ft Long
5-m Diameter
4,572
180.0
dia
62.7-ft Long
5-m Diameter
4,445
175
2,540
100
dia
DSS-4
4,445
175
3-Plug Shown (Compatible with Any
ULA 4-m-diameter Payload Fairing)
PERFORMANCE (kg/lb)
Sep
Plane
10,988
5,525
432.6
217.5
Sep
Plane
3,750
147.6
dia
5,525
217.5
DSS-5 (Short)
(Compatible with Any ULA
5-m-diameter Payload Fairing)
All dimensions are mm
in
Delta IV M+ (5,4)
Vehicle Class
Payload Fairing Diameter (Meters)
Number of Solid Rocket Motors (0, 2 or 4)
13
GEO
N/A
N/A
2,850/6,280
3,290/7,270
N/A
N/A
2,540/5,610
3,080/6,800
3,530/7,800
3,850/8,500
1,030/2,280
2,080/4,590
1,840/4,060
2,710/5,970
6,300/13,890
GTO
4,750/10,470
5,950/13,110
6,890/15,180
7,700/16,970
3,780/8,330
5,250/11,570
6,480/14,280
7,450/16,420
8,290/18,270
8,900/19,620
4,210/9,280
6,160/13,580
5,080/11,200
6,890/15,190
13,810/30,440
LEO-Reference
9,800/21,600
12,030/26,530
13,600/29,980
15,260/33,660
8,210/18,100
11,000/24,250
13,500/29,760
15,530/34,250
17,410/38,400
18,850/41,570
9,190/20,250
12,900/28,440
11,060/24,380
13,730/30,250
28,370/62,540
LEO-ISS
8,910/19,640
10,670/23,530
12,060/26,600
13,250/29,220
7,540/16,630
10,160/22,410
12,510/27,590
14,480/31,920
16,290/35,920
17,720/39,080
8,510/18,760
12,000/26,450
10,220/22,530
12,820/28,270
25,980/57,280
LEO-Polar
8,080/17,820
9,980/22,020
11,140/24,560
12,130/26,750
6,770/14,930
9,060/19,990
11,160/24,610
12,880/28,410
14,480/31,940
15,760/34,750
7,690/16,960
10,530/23,210
9,610/21,180
11,600/25,580
23,560/51,950
GEO (Geosynchronous Earth Orbit) = 35,786 km circular at 0 deg | GTO (Geosynchronous Transfer Orbit) = 35,786 km x 185 km at 27.0 deg | LEO-Reference (Low Earth Orbit-Reference) = 200 km circular at 28.7 deg | LEO-ISS (Low Earth Orbit-International Space Station) = 407 km circular at 51.6 deg | LEO-Polar (Low Earth Orbit-Polar) = 200 km circular at 90 deg
14
15
29
30
Atlas V 551
TM
Delta IV Medium+ (5,4)
Launching a higher standard
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