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THE DELTA FAMILY
Thor: (1957) Thor IRBM with no upper stage.
Thor Able: (1958) Thor with Able upper stage derived from Vanguard second stage.
Thor Agena A: (1959) Thor with Agena A second stage.
Delta: (1960) Commercial name for the military's Thor-Delta. The name of the Delta second stage eventually was applied to subsequent commercial follow-ons.
Thor Able-Star: (1960) Thor with Able-Star second stage.
Thor Agena B: (1960) Thor with Agena B second stage.
Delta A: (1962) Upgraded Delta.
Delta B: (1962) Based on Delta A but with uprated second stage.
Thor Agena D: (1962) Thor with Agena D second stage.
Delta C: (1963) Same configuration as Delta B.
Delta D: (1964) Also known as Thrust Augmented Thor. Introduction of uprated Delta Thor TA first stage with 3 x Castor 1 solid strap-ons.
Delta E: (1965) Introduction of uprated Delta E second stage, FW-4D third stage, and 3 x Castor 2 solid strap-ons.
Delta G: (1966) Delta E less third stage and strap-ons.
Delta J: (1968) Based on Delta E but with Burner 2 third stage.
Delta M: (1968) Also known as Long Tank Thor. Based on Delta J but with larger capacity first stage and 6 strap-ons.
Delta N: (1968) Delta M less third stage.
Delta L: (1969) Delta N with FW-4D third stage.
Delta 100: (1972) Based on Delta M but with uprated second stage and 9 strap-ons.
Delta 1914: (1972) Based on Delta 100 but with uprated first stage introducing RS-27 engine.
Delta 2914: (1974) Based on Delta 1914 but with TR-201 stage 2 engine derived from Apollo LM descent engine.
Delta 2910: Configuration 2914 less Burner 2 third stage.
Delta N: (1975) Licensed version of Delta built in Japan using both US and Japanese components.
Delta 3914: (1976) Based on Delta 2914 but with uprated Castor 4 solid strap-ons.
Thor Burner: (1976) Thor with Burner 2 second and third stages.
Delta 3910: Configuration 3914 less Burner 2 third stage.
Delta 3910/PAM: (1980) Configuration 3910 with PAM Payload Assist Module third stage.
Delta N-2: (1981) Licensed version of Delta built in Japan using both US and Japanese components.
Delta 3920: (1982) Upgraded Delta 3910 with larger capacity second stage.
Delta 3920/PAM: (1982) Also known as Delta 3925. Configuration 3920 with PAM third stage.
Delta 4925: (1989) Based on Delta 3920/PAM but with uprated Castor 4A solid strap-ons.
Delta 5920: (1989) Configuration 4925 less PAM third stage.
Delta II, 6925: (1989) Based on Delta 4925 but with upgraded first stage.
Delta II, 6920: (1990) Configuration 6925 less PAM third stage.
Delta II, 7925: (1990) Based on Delta 6925 but with modified first stage and uprated Alliant GEM solid strap-ons.
Delta II, 7920: (1995) Configuration 7925 less PAM third stage.
Delta III, 8930: (1998) Based on Delta II first stage with larger GEM solid strap-ons and a new cryogenic upper stage.
Delta IV, Medium: (2003) Basic Delta IV vehicle with no strap-ons, common booster core, cryogenic upper stage, and 4 m fairing.
Delta IV, M+ (4,2): (2002) Same as Delta IV Medium but with two GEM-60 solid rocket motor strap-ons.
Delta IV, Heavy: (2004) Two Delta IV CBC strap-ons flanking CBC first stage, with heavy cyrogenic upper stage and 5-m fairing.
DELTA FAMILY RECORD
First launch: 13-May-1960
Number launched: 280 to Aug-2000
Launch sites: Cape Canaveral pads 17A/B; Vandenberg AFB SLC-2W
Vehicle success rate: 94.64%
Success rate, past 25 launches: 92% to Aug-2000
DELTA II, 7925/7920 SPECIFICATIONS
First launch: 26-Nov-1990
Number launched: 61 to Aug-2000
Launch sites: Cape Canaveral pads 17A/B, VAFB SLC-2W
Principal uses: launches of GPS Navstar Block 2A; medium class telecom satellites
into GTO
Vehicle success rate: 98.36% to Aug-2000
Performance:
GTO: 1,842 kg (1,882 kg from Dec-1995)
GPS: 2,090 kg (2,141 kg from Dec-1995)
LEO (28.7o): 5,039 kg 7920 2-stage
Sun-synchronous (830 km): 3,175 kg 7920 VAFB
Molniya-type (370 x 40,000 km, 63.4o): 1,275 kg
Lunar delivery: 1,240 kg
Availability: typically 30 months from contract signature to launch
Number of stages: 3 + 9 strap-ons (7920 excludes stage 3)
Overall length: 38.41 m
Principal diameter: 2.44 m
Launch mass: 231,870 kg
Launch thrust: 3,110 kN (six solids fire at launch)
Guidance: The digital inertial guidance system is mounted inside a cylinder at stage 2's forward end, controlling the vehicle during stage 1/2 and commanding spin-up/separation of stage 3 in addition to triggering its fuze-based sequencing system.
ALLIANT GEM 40 SOLID STRAP-ONS
Length: 12.96 m
Diameter: 1.02 m
Mass at ignition: 13,232 kg each for six ignited on pad; 13,061 kg each for three air-lit
Propellant: HTPB solid
Propellant mass: each 11,765 kg
Thrust: each 446.0 kN SL average, 499.2 kN vac
Burn time: 63.3 s
Burn sequence: Six GEMs are ignite at launch, followed by the remaining three 2.5 s after their burnout at 63 s. The original six are spring-separated (under command of a sequencer between stage 1's tanks) in two symmetrical sets at 66/67 s; the final three burn out at 129 s and separate 3 s later.
DELTA 7920/7925 STAGE 1
Engines: Rocketdyne RS-27A single-start liquid bipropellant; with two Rocketdyne LR-101-NA-11 verniers
Length: 26.05 m
Diameter: 2.44 m
Stage mass: 101,718 kg
Oxidizer: liquid oxygen
Fuel: RP-1 hydrocarbon
Propellant mass: 96,033 kg (usable)
Thrust: 890 kN SL, 1,085 kN vac + two 4.45 kN verniers
Burn time: 260.5 s
Attitude control: Main engine hydraulically gimbaled for pitch/yaw control, two verniers provide roll control.
INTERSTAGE
The 4.72 m long isogrid interstage extends from the top of stage 1 to stage 2's miniskirt, encircling most of the upper stage until explosive bolt detonation 8 s after stage 1 burnout; six spring-driven separation rods at the forward end then separate the stages and stage 2 ignition occurs 5 s later.
DELTA 7920/7925 STAGE 2
Engine: pressure-fed restartable Aerojet AJ10-118K
Length: 5.89 m
Diameter: 1.70 m, suspended by 2.44 m diameter mini-skirt and support truss
Stage mass: 6,930 kg
Oxidizer: nitrogen tetroxide
Fuel: Aerozine-50
Propellant mass: 6,006 kg (usable)
Thrust: 43.37 kN vac
Burn time: 432 s (restartable)
Attitude control: The nitrogen cold gas jet Redundant Attitude Control System (RACS) provides 3-axis control during coast periods and roll control during powered flight; hydraulic gimballing of the main engine provides pitch/yaw control.
DELTA 7925 STAGE 3
Designation: PAM-D
Motor: Thiokol Star 48B solid
Length: 2.04 m
Diameter: 1.24 m
Mass at ignition: 2,141 kg (132 kg after burnout)
Propellant: solid
Propellant mass: 1,756-2,025 kg, depending on mission requirements
Thrust: 66.4 kN vac
Burn Time: 87.1 s
FAIRING/PAYLOAD ACCOMODATION
The spacecraft is protected by an 8.49 m long, 839 kg aluminum fairing 2.44 m diameter at the base and 2.90 m at the widest portion. The halves are pyrotechnically separated during second stage burning at a height of about 111 km where aerodynamic heating has reduced to 1,135 W/m2. Also available are 2.44/3.05 m diameter versions. Air conditioning on the pad can provide 14-26.7oC, maximum humidity 50%.
Acceleration load: 6.25 g max at end of stage 1 burn for heaviest GTO payloads; 4.24 g at stage 3 burnout, 1.31 g at launch
Acoustic load: maximum about 130 dB at launch/transonic
Temperature: 33oC max on fairing inner wall after 300 s
DELTA III, 8930 SPECIFICATIONS
First launch: 27-Aug-1998
Last launch: 23-Aug-2000
Number launched: 3
Vehicle success rate: 33.33%
Performance:
GTO (200 x 35,786 km, 28.7o): 3,810 kg
LEO (185 km, 28.7o): 8,290 kg
ISS (407 km, 51.6o): 7,300 kg
Polar (200 km, 90o): 6,770 kg
Sun-synchronous (800 km, 98.6o): 6,100 kg
Number of stages: 2 + 9 strap-ons
Overall length: 35.0 m
Principal diameter: 2.44 m / 4.0 m
Launch mass: 301,450 kg
Launch thrust: 4,114 kN (six solids fire at launch)
ALLIANT GEM 46 SOLID STRAP-ONS
Length: 14.66 m
Diameter: 1.17 m
Mass at ignition: 19,327 kg each for three with thrust vector control; 19,082 kg each for six non-TVC
Propellant: HTPB solid
Propellant mass: each 17,045 kg
Thrust: each 537.4 kN SL average, 628.3 kN vac
Specific impulse: 243 s SL, 284 s vac
Burn time: 75.2 s
Burn sequence: Six GEMs are ignite at launch, followed by the remaining three after burnout.
DELTA 8930 STAGE 1
Engines: Rocketdyne RS-27A single-start liquid bipropellant; with two Rocketdyne LR-101-NA-11 verniers
Length: 20.0 m
Diameter: 2.44 m, flaring to 4.0 m at forward end
Stage mass: 104,380 kg
Oxidizer: liquid oxygen
Fuel: RP-1 hydrocarbon
Propellant mass: 95,550 kg
Thrust: 890 kN SL, 1,085 kN vac + two 4.45 kN verniers
Burn time: 261 s
Attitude control: Main engine hydraulically gimbaled for pitch/yaw control, two verniers provide roll control.
DELTA 8930 STAGE 2
Engine: Pratt & Whitney RL-10B-2
Length: 8.8 m
Diameter: 4.0 m
Stage mass: 19,300 kg
Oxidizer: liquid oxygen
Fuel: liquid hydrogen
Propellant mass: 16,820 kg
Thrust: 110.1 kN vac
Burn time: 700 s
DELTA IV
The Delta IV launch system comes in five vehicle configurations: the Delta IV Medium, three variants of Delta IV Medium-Plus, and the Delta IV Heavy. Each has a newly developed first stage, called the common booster core (CBC), using cryogenic propellants. The Delta IV-M employs a first-stage CBC, a 4-m diameter cryogenic second stage, and a 4-m diameter composite payload fairing (PLF). The Delta IV-M+ comes in three different configurations. One configuration uses two strap-on solid rocket motors (SRMs) to augment the first-stage CBC, a 4-m diameter cryogenic second stage, and a 4-m composite PLF. This configuration is designated as Delta IV-M+ (4,2); the first digit in parentheses refers to the diameter of the second stage, and the second digit refers to the numbers of strap-on SRMs. The other two configurations are the Delta IV-M+ (5,2) and M+ (5,4) that have two and four SRMs respectively. Both of these configurations employ a 5-m diameter cryogenic second stage and a 5-m composite PLF. The Delta IV-H employs two additional CBCs as strap-on liquid rocket boosters (LRBs) to augment the first stage CBC, a cryogenic 5-m second stage, and either a 5-m composite or 5-m metallic PLF.
First launch: 20-Nov-2002
Number launched: 4 to end-2004
Launch sites: Cape Canaveral SLC-37, VAFB SLC-6
Principal uses: delivery of single or double payloads to LEO or GTO/GEO
Vehicle success rate: 100% to end-2004
Performance:
GTO (185 x 35,786 km, 27.0o): 4,231 kg (IV-M), 5,941 kg (IV-M+ 4,2), 4,869 kg (IV-M+ 5,2), 6,822 kg (IV-M+ 5,4), 12,757 kg (IV-H)
GEO (35,786 km, 0o): 1,138 kg (IV-M), 2,036 kg (IV-M+ 4,2), 1,686 kg (IV-M+ 5,2), 2,786 kg (IV-M+ 5,4), 6,276 kg (IV-H)
LEO (407 km, 28.7o): 9,106 kg (IV-M), 12,300 kg (IV-M+ 4,2), 10,616 kg (IV-M+ 5,2), 13,869 kg (IV-M+ 5,4), 21,892 kg (IV-H)
ISS (407 km, 51.6o): 8,501 kg (IV-M), 11,455 kg (IV-M+ 4,2), 9,782 kg (IV-M+ 5,2), 12,894 kg (IV-M+ 5,4), 21,892 kg (IV-H)
Moon: 3,132 kg (IV-M), 4,445 kg (IV-M+ 4,2), 3,623 kg (IV-M+ 5,2), 4,858 kg (IV-M+ 5,4), 9,956 kg (IV-H)
Mars: 2,347 kg (IV-M), 3,465 kg (IV-M+ 4,2), 2,743 kg (IV-M+ 5,2), 3,792 kg (IV-M+ 5,4), 8,005 kg (IV-H)
Number of stages: 2 + 0 to 4 strap-ons
Overall length: 62.8 m (IV-M & IV-M+ 4,2), 66.1 m (IV-M+ 5,2 & 5,4), 71.0 m (IV-H)
Principal diameter: 5.13 m
Launch mass: 249,500 kg (IV-M), 317,100 kg (IV-M+ 4,2), 337,000 kg (IV-M+ 5,2), 404,600 kg (IV-M+ 5,4), 733,400 kg (IV-H)
Launch thrust: 2,891 kN (IV-M), 4,359 kN (IV-M+ 4,2 & 5,2), 5,827 kN (IV-M+ 5,4), 8,673 kN (IV-H)
DELTA IV SOLID ROCKET MOTORS (SRM)
Motor: Alliant GEM 60
Length: 16.15 m
Diameter: 1.52 m
Mass at ignition: 33,798 kg each with thrust vector control; 33,199 kg each for non-TVC
Propellant: HTPB solid
Propellant mass: each 29,949 kg
Thrust: each 734 kN SL average, 827 kN vac
Specific impulse: 243 s SL, 275 s vac
Burn time: 97 s
Burn sequence: Ignited at liftoff, first pair jettisoned at 100 s, second pair (if used) at 102 s.
DELTA IV LIQUID ROCKET BOOSTERS (LRB)
The LRBs, used on the Delta IV-H, are identical to the CBC except they are fitted with nose cones and separation motors.
Burn sequence: 100% thrust at liftoff, throttled to 60% at 238-244 s, cut-off at 249 s, jettisoned at 251 s.
DELTA IV COMMON BOOSTER CORE (CBC)
Engine: Rocketdyne RS-68
Length: 40.8 m
Diameter: 5.13 m
Stage mass: 226,400 kg
Oxidizer: liquid oxygen
Fuel: liquid hydrogen
Propellant mass: 199,640 kg
Thrust: 2,891 kN SL, 3,314 kN vac
Burn time: 246 s
Attitude control: Engine hydraulically gimbaled for pitch/yaw control. Roll for single-CBC vehicles is provided by vectoring the RS-68 turbine exhaust gases; roll for Heavy vehicle is provided by gimbaling the LRB engines.
Burn sequence: Delta IV-H: 100% thrust at liftoff, throttled to 60% at 56 s, throttled-up to 100% at 252-257 s, cut-off at 327 s, separation at 332 s. All others: 100% thrust, cut-off at 246 s, separation at 251 s.
INTERSTAGE ADAPTER
The CBC has an overall diameter of 5 m, so the interstage is tapered down to 4-m diameter for the Delta IV-M and M+ (4,2) configurations that use a 4-m cryogenic second stage. The interstages for the Delta IV-M+ (5,2), M+ (5,4), and Heavy configurations have a 5-m diameter cylinder.
DELTA IV STAGE 2
Two second stage configurations are offered on Delta IV, a 4-m version and a 5-m version. Both second stages use the Delta III RL10B-2 engine. Specifications below are for the 4-m version with figures for the 5-m version, where different, in parentheses.
Engine: Pratt & Whitney RL10B-2
Length: 12.2 m (13.7 m)
Diameter: 4.0 m (5.0 m)
Stage mass: 24,170 kg (30,710 kg)
Oxidizer: liquid oxygen
Fuel: liquid hydrogen
Propellant mass: 21,320 kg (27,220 kg)
Thrust: 110.1 kN vac
Burn time: 850 s (1,125 s)
PAYLOAD FAIRING
The Delta IV launch system offers PLFs for different vehicle configurations. The 4-m fairing is a stretched Delta III 4-m composite bisector design, and is 11.75 m long. The 5-m composite fairing for single-manifest missions is also based in that of Delta III and comes in two standard lengths: 14.3 m and 19.1 m. The dual-manifest fairing consists of two sections - a 5-m composite bisector fairing and a lower 5-m composite dual-payload canister (DPC), and is available in two lengths: 19.1 m and 22.4 m. The 5-m metallic trisector fairing (the baseline for government programs) is a modified version of the flight-proven Titan IV aluminum isogrid fairing, and is 19.8 m long.
ROCKETDYNE / RS-68
Application: Delta IV common booster core
First flown: 20-Nov-2002
Dry mass: 6,604 kg
Mounting: hydraulically gimbaled for pitch/yaw control
Engine cycle: gas generator
Oxidizer: liquid oxygen, delivered at 700 kg/s
Fuel: liquid hydrogen, delivered at 117 kg/s
Mixture ratio: 6.0
Thrust: 2,891 kN SL, 3,314 kN vac, can be throttled to 60%
Specific impulse: 365 s SL, 410 s vac
Expansion ratio: 21.5:1
Combustion chamber pressure: 95.9 atm
ROCKETDYNE / RS-27, RS-27A
The RS-27 powerplant comprises an RS2701A/B main engine and twin LR101-NA-11 verniers. The uprated RS-27A version is employed by the 7000 series; its specifications are given below, where different, in parentheses.
Application: Delta 6000 series (RS-27A: 7000 & 8000 series)
First flown: 18-Jan-1974 (RS-27A debut 1990)
Number flown: 107 Delta + 21 Atlas (RS-27A: 20) to end-1995
Dry mass: 1,027 kg (1,091 kg)
Length: 3.63 m from top of thrust ring (3.78 m)
Maximum diameter: 1.70 m
Mounting: gimbal-mounted for pitch/yaw control + gimbaled verniers for roll control
Engine cycle: gas generator
Oxidizer: liquid oxygen, delivered at 250 kg/s
Fuel: RP-1, delivered at 111 kg/s
Mixture ratio: 2.245
Oxidizer turbopump: 6,784 rpm (7,085 rpm at altitude), 1,900 kW, 70 atm discharge pressure
Fuel turbopump: 1,289 kW, 70 atm discharge pressure
Thrust: 971 kN SL, 1,032 kN vac (890 kN SL, 1,054.2 kN vac)
Specific impulse: 264 s SL, 295 s vac (255 s SL, 302 s vac)
Expansion ratio: 8:1 (12:1)
Combustion chamber pressure: 48 atm
Combustion chamber temperature: 3,315oC
Burn time: 274 s
Verniers: each 21.8 kg mass, 4.63/5.30 kN SL/vac thrust, 206/246 s SL/vac Isp, 1.8 mixture ratio, 5.6 expansion ratio (9.8 cm exit diameter), 283 s burn time
AEROJET / AJ10-118K
Application: Delta II stage 2
First flown: Aug-1982
Dry mass: 124.7 kg
Length: 2.69 m
Mounting: fixed
Engine cycle: pressure-fed
Oxidizer: nitrogen tetroxide, delivered at 9.1 kg/s
Fuel: Aerozine-50, delivered at 4.76 kg/s
Mixture ratio: 1.9
Thrust: 43.48 kN vac
Specific impulse: 320.5 s vac
Expansion ratio: 65:1
Combustion chamber pressure: 8.84 atm
Burn time: qualified up to 500 s (unlimted starts)
P&W / RL10B-2
Application: Delta III & IV stage 2
First flown: Aug-1998
Number flown: 7 to end-2004
Dry mass: 301 kg
Maximum diameter: 2.14 m
Mounting: electromechanically gimbaled for pitch/yaw control
Oxidizer: liquid oxygen, delivered at 20.6 kg/s
Fuel: liquid hydrogen, delivered at 3.5 kg/s
Mixture ratio: 5.88
Thrust: 110.1 kN vac
Specific impulse: 465.5 s vac
Expansion ratio: 250:1 with extendable nozzle
Burn time: up to 1,125 s
THIOKOL / STAR 48B
The TE-M-711-17 is employed in McDonnell Douglas's PAM for satellite launches from the Space Shuttle and Delta. The TE-M-711-18 has a longer exit cone for use in launches from Delta; its specifications are given below, where different, in parentheses.
Designation: TE-M-711-17 (and TE-M-711-18)
Application: PAM for satellite launches from Shuttle and Delta
Mass: 2,137 kg (2,142 kg)
Length: 2.03 m (2.235 m)
Diameter: 1.245 m
Propellant
type: AP/HTPB/Al
mass fraction: 0.941 (0.939)
Propellant mass: 2,011 kg
Burn time: 84 s
Thrust: 66 kN vac average
Specific impulse: 286 s vac (292.1 s vac)
Total impulse: 5,647 kNs (5,799 kNs)