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• Titan IV Launch Vehicle
Titan IV Launch Vehicle
Titan IVA
Titan IVB
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Image or
Text
Titan IV Launch History
Titan IV Heritage
Reference
Information
Titan IVA Model Configuration
Payload
Payload
Fairing
Centaur Upper
Stage
Stage 2
Stage 1
Stage 0
Solid Rocket
Motor (2 Places)
Thrust Control
Vector Tank
(2 Places)
Titan IVA Model Configuration
Stage 0
Solid Rocket Motor
(2 Places)
Thrust Control
Vector Tank
(2 Places)
Stage 1
Stage 2
Payload
Fairing
Centuar
Upper Stage
Payload
Titan IV First Launch
The first Titan IV vehicle launched
into space on June 14, 1989 from
Launch Complex 41 at Cape
Canaveral Air Force Station, FL.
The Titan IVA positioned a Defense
System Program ballistic missile
launch detection satellite into a
geosynchronous orbit.
Courtesy of
Martin Marietta
Titan IVB Configuration - Cassini
The Titan IVB vehicle is shown at Launch
Complex 40 at the Cape Canaveral Air
Station, FL. The Mobile Service Tower has
been retracted and the Titan IVB/Centaur
carrying the Cassini – Huygens spacecraft
stands ready for launch. The launch vehicle,
Cassini - Huygens spacecraft and attached
Centaur stage encased in the payload fairing,
stand about 183 feet tall. Mounted at the
base of the launch vehicle are two upgraded
solid rocket motors.
Cassini – Huygens is the cooperative project
of NASA, the European Space Agency and
the Italian Space Agency. The Jet Propulsion
Laboratory, a division of the California
Institute of Technology in Pasadena, Calif.,
manages the Cassini mission for NASA's
Office of Space Science, Washington, D.C.
Payload
Fairing
Stage 2
Stage 1
Stage 0
Solid
Rocket
Motor
(2 Places)
Titan IVB – Cassini
Payload
Fairing
Cassini
High Gain
Antenna
Huygens
Probe
The Cassini - Huygens spacecraft
is shown atop the Centaur upper
stage at Launch Complex 40,
Cape Canaveral Air Station, FL.
One segment of the payload fairing
has been installed and one
segment removed.
Cassini obtained Saturn orbit on
July 1, 2004. Cassini will study the
Saturnian system for four years.
On January 14, 2005, the
European Space Agency's
Huygens Probe parachuted to the
frozen surface of Saturn's moon
Titan and successfully gathered
information.
Centaur
Upper Stage
Titan IVB Cassini Launch
The Cassini spacecraft and Huygens probe begin their seven-year journey to
Saturn. The successful launch of Cassini aboard a Titan IVB/Centaur occurred
October 15, 1997. The four towers helped protect the vehicle from lightning.
Titan IVB Cassini Launch
The launch of the Cassini - Huygens spacecraft on October 15, 1997 is
photographed from a Florida beach.
Titan IV Launch History
Sheet 1
No.
Date
Site
Model
Payload
1
06/14/1989
SLC-41
CCAFS, FL
Titan 4A/IUS
DSP 14 - Defense System
Program early warning satellite
2
06/08/1990
SLC-41
CCAFS, FL
Titan 4A
NOSS - Naval reconnaisance
satellites
3
11/12/1990
SLC-41
CCAFS, FL
Titan 4A/IUS
DSP 15 - Defense System
Program early warning spacecraft
4
03/08/1991
SLC-4E
VAFB, CA
Titan 4A
Lacrosse 2 - surveillance satellite
5
11/07/1991
SLC-4E
VAFB, CA
Titan 4A
NOSS - Naval reconnaisance
satellites
6
11/28/1992
SLC-4E
VAFB, CA
Titan 4A
Keyhole - surveillance satellite
7*
08/02/1993
SLC-4E
VAFB, CA
Titan 4A
NOSS - Naval reconnaisance
satellites
8
02/07/1994
SLC-40
CCAFS, FL
Titan 4A/Centaur
Milstar 1-1 - communications
satellite
* Indicates Titan failure
Titan IV Launch History
Sheet 2
No.
Date
Site
Model
Payload
9
05/03/1994
SLC-41
CCAFS, FL
Titan 4A/Centaur
Trumpet - NRO/USAF satellite
10
08/27/1994
SLC-41
CCAFS, Fla.
Titan 4A/Centaur
Mercury - USAF satellite
11
12/22/1994
SLC-40
CCAFS, Fla.
Titan 4A/IUS
DSP 17 - Defense System
Program early warning satellite
12
05/14/1995
SLC-40
CCAFS, Fla.
Titan 4A/Centaur
Advanced Orion - NRO/CIA
satellite
13
07/10/1995
SLC-41
CCAFS, Fla.
Titan 4A/Centaur
Trumpet - NRO/USAF satellite
14
11/06/1995
SLC-40
CCAFS, Fla.
Titan 4A/Centaur
Milstar 1-2 - communications
satellite
15
12/05/1995
SLC-4E
VAFB, Calif.
Titan 4A
Keyhole - surveillance satellite
16
04/24/1996
SLC-41
CCAFS, Fla.
Titan 4A/Centaur
Mercury - NRO/USAF satellite
Titan IV Launch History
No.
Date
Site
17
Sheet 3
Model
Payload
05/12/1996
SLC-4E
VAFB, Calif.
Titan 4A
NOSS - communications,
reconnaisance and technology
satellites
18
07/02/1996
SLC-40
CCAFS, Fla.
Titan 4A
SDS-2 - NRO/USAF
communications satellite
19
12/20/1996
SLC-4E
VAFB, Calif.
Titan 4A
Keyhole - surveillance satellite
20
02/23/1997
SLC-40
CCAFS, Fla.
Titan 4B/IUS
DSP 18 - Defense System
Program early warning satellite
21
10/15/1997
SLC-40
CCAFS, Fla.
Titan 4B/Centaur
Cassini - NASA/ESA Saturn
exploration satellite
22
10/23/1997
SLC-4E
VAFB, Calif.
Titan 4A
Lacrosse 3 - surveillance satellite
23
11/07/1997
SLC-41
CCAFS, Fla.
Titan 4A/Centaur
Trumpet - NRO/USAF satellite
24
05/08/1998
SLC-40
CCAFS, Fla.
Titan 4B/Centaur
Advanced Orion - NRO/CIA
satellite
Titan IV Launch History
Sheet 4
No.
Date
Site
Model
Payload
25*
08/12/1998
SLC-41
CCAFS, Fla.
Titan 4A/Centaur
Mercury - USAF satellite
26~
04/09/1999
SLC-41
CCAFS, Fla.
Titan 4B/IUS
DSP 19 - Defense System
Program early warning satellite
27~
04/30/1999
SLC-40
CCAFS, Fla.
Titan 4B/Centaur
Milstar 2-1 - communications
satellite
28
05/22/1999
SLC-4E
VAFB, Calif.
Titan 4B
EIS 1 - reconnaissance satellite
29
05/08/2000
SLC-40
CCAFS, Fla.
Titan 4B/IUS
DSP 20 - Defense System
Program early warning satellite
30
08/17/2000
SLC-4E
VAFB, Calif.
Titan 4B
Lacrosse 4 - surveillance satellite
31
02/27/2001
SLC-40
CCAFS, Fla.
Titan 4B/Centaur
Milstar 2-2 - communications
satellite
*Indicates Titan failure
~Indicates upper stage failure
Titan IV Launch History
Sheet 5
No.
Date
Site
Model
Payload
32
08/06/2001
SLC-40
CCAFS, Fla.
Titan 4B/IUS
DSP 21 - Defense System
Program early warning satellite
33
10/05/2001
SLC-4E
VAFB, Calif.
Titan 4B
Keyhole - surveillance satellite
34
01/15/2002
SLC-40
CCAFS, Fla.
Titan 4B/Centaur
Milstar 2-3 - communications
satellite
35
04/08/2003
SLC-40
CCAFS, Fla.
Titan 4B/Centaur
Milstar 2-4 - communications
satellite
36
09/09/2003
SLC-40
CCAFS, Fla.
Titan 4B/Centaur
Advanced Orion - NRO/CIA
satellite
37
02/14/2004
SLC-40
CCAFS, Fla.
Titan 4B/IUS
DSP 22 - Defense System
Program early warning satellite
38
04/29/2005
SLC-40
CCAFS, Fla.
Titan 4B
Lacrosse 5 - surveillance satellite
39
10/19/2005
SLC-4E
VAFB, Calif.
Titan 4B
NRO satellite
Titan IV Heritage
Titan I
Titan II Gemini Titan 34B
Titan
Agena
Titan IIIC
Titan IIIC –
MOL
Titan IIIC Centaur
Titan IV Heritage
The Titan 34D was developed to
accommodate larger military
spacecraft during the transition to the
new Space Shuttle in the 1980s.
The Air Force was awarded funding
to develop the complementary
expendable launch vehicle as a backup for the Space Shuttle. The Titan
34D-7 design won the contract and
later was named the Titan IV.
The Titan 34D launch vehicle lifts off
from Cape Canaveral Air Force
Station, FL on November 28, 1987. A
classified payload was successfully
placed into orbit.
Courtesy of
Martin Marietta
Reference Information
End
Text:
First Operational Delta IV Heavy, Craig Covault, Aviation Week and Space Technology, Volume
167, page 28, November 19, 2007 - covers the first launch of the Delta IV - Heavy with an
operational satellite.
Titan IV Propulsion Systems, Aerojet TechSystems, January 1988 - provides concise technical
information about the Titan IVA propulsion systems.
Text and Images:
http://saturn.jpl.nasa.gov/multimedia/images/image-details.cfm?imageID=948
http://saturn.jpl.nasa.gov/spacecraft/index.cfm
http://saturn.jpl.nasa.gov/multimedia/images/image-details.cfm?imageID=770
http://www1.nasa.gov/mission_pages/cassini/whycassini/cassinif-20071011.html
http://upload.wikimedia.org/wikipedia/commons/1/1f/Titan_Missile_Family.png
Text only:
http://www.spaceflightnow.com/titan/b26/051016history.html
http://www.astronautix.com/lvs/titan4.htm
http://www.space.com/missionlaunches/sfn_051020_titan4_finalflight.html
http://www.spaceflightnow.com/titan/b26/051016titan4b.html
http://www.fas.org/spp/military/program/launch/titan.htm
http://www.space-travel.com/reports/ATK_Gives_Titan_4_A_Boost.html
Titan IV
As a result of the January 1986 Space Shuttle Challenger accident, the Department of Defense
embarked on a recovery plan to launch large military satellites. Martin Marietta, located in
Denver, CO, was selected to develop the complementary expendable launch vehicle called the
Titan IV.
The Titan IV was the nation's largest expendable launch vehicle from 1989 through 2005
providing access to space for the United States’ largest payloads. Overall length was up to 204
feet with a maximum overall weight of approximately 1,900,000 pounds. The Titan IV was
launched from Cape Canaveral Air Force Station, FL and Vandenberg Air Force Base, CA.
In 1989, a follow-on procurement to the original Titan IVA space lift vehicle resulted in the Titan
IVB . The upgraded rocket incorporated significant technology. The Titan IVB was capable of
placing 47,800 pounds into low-Earth orbit or more than 12,700 pounds into geosynchronous
orbit 22,300 miles above the Earth.
The Titan IVB consisted of two solid-propellant stage motors, a liquid propellant two-stage core
and a 16.7 ft diameter payload fairing. Upgraded three-segment solid rocket motors increased
the vehicle's payload capability by approximately 25% over the Titan IVA. The stage 1 and 2
core rocket engines burned nitrogen tetroxide (N2O4) oxidizer with unsymmetrical dimethyl
hydrazine (UDMH) fuel.
The Titan IV has been replaced by the evolved expendable launch vehicle Delta IV-Heavy and
the Atlas V-Heavy supplied by the United Launch Alliance (ULA). The first operational Delta IVHeavy rocket was launched on November 10, 2007 from Cape Canaveral, FL carrying the final
Defense Support Program missile warning satellite for the U.S. Air Force.
Titan IVA Configuration
Titan IVA launch vehicles consisted of three basic elements: liquid rocket cores, solid rocket
motors and upper stages. The 10 ft diameter liquid rocket core, together with the solid rocket
motors, served as the basic propulsion element for all Titan IVA vehicles.
Stage 0, built by United Technologies Corporation, was comprised of two identical, segmented
solid propellant rocket motors. The solid rocket motors (SRMs) were attached to the Stage
I/Stage II core vehicle. Each SRM was 112.9 ft long, weighed 683,700 lbs and developed 1.5
million lbs of thrust. The SRM liquid injection thrust vector control (TVC) system provided control
of the solids. The TVC injectant, nitrogen tetroxide, was carried in a tank mounted on the side of
the motor and was pressure-fed into the nozzle exit section by gaseous nitrogen.
Stage 1 consisted of an Aerojet LR87-AJ-11 liquid propellant rocket engine attached to an
airframe that included the fuel and oxidizer tanks, inner tank structure, forward skirt and aft skirt.
The rocket engine developed 548,000 lbs vacuum thrust. Thrust vector control was
accomplished by gimbaling the engine to provide pitch, yaw, and roll corrections.
Stage 2 used an Aerojet LR91-AJ-11 liquid propellant rocket engine attached to an airframe
similar in construction to Stage I. The rocket engine delivered 105,000 lbs of thrust in vacuum.
Thrust vector control was accomplished by gimbaling the chamber, but roll control was provided
by ducting pump turbine exhaust through a swiveled nozzle to produce thrust.
Centaur was a high-energy upper stage with multiple restart capability. Two thrust chamber
assemblies provided a vacuum thrust of 33,100 lbs. The cryogenic propellants were liquid
hydrogen and liquid oxygen. The payload fairing enclosed both the Centaur stage and payload,
and provided environmental protection for the stage and spacecraft on the ground and in flight.
Titan IVA Final Assembly & Flight Sequence
Final Assembly
After shipping to Cape Canaveral Air Force Station, FL, the rocket engines were installed in
Stage 1 and 2 and the core vehicle was erected in the Vertical Integration Building (VIB).
Moving on a special rail system to the Solid Motor Assembly Building (SMAB), the core vehicle
was mated with the lower five Solid Rocket Motor (SRM) segments. The remaining two SRM
segments, the upper stage, and payload were then mounted atop the assembled vehicles.
Flight Sequence
 A typical upper stage geosynchronous equatorial launch from Cape Canaveral began with
Stage 0 ignition and liftoff. The two solids burned for about 131 seconds propelling the vehicle
to an altitude of 187,000 ft in its arcing trajectory toward orbit.
 Stage 1 ignited, followed by separation of the SRMs by explosive bolts, and then the solidrocket staging motor fired.
 The payload fairing was jettisoned at 232 seconds and 385,000 ft altitude. At 308 seconds
Stage 2 fired and Stage 1 was jettisoned. By this time, the vehicle would have reached an
altitude of 500,000 ft. About 549 seconds after launch, Stage 2 injected the spacecraft into
mission orbit.
 The Centaur upper stage and spacecraft were separated as a unit into a low-altitude parking
orbit at an altitude of approximately 95 nautical miles.
 The Centaur provided attitude stabilization while coasting until the desired equatorial crossing
was achieved. The Centaur reoriented itself and then the engine burned placing the spacecraft
in a transfer orbit. Coast-attitude stabilization was maintained for the 5 1/4 hours required to
reach apogee.
 The Centaur reoriented for injection into geosynchronous orbit, fired its upper stage, trimmed
the final orbit, and separated the spacecraft for its mission.
Titan IVB Configuration
Titan IVB consisted of a 10 ft diameter liquid propellant core of two stages with a pair of Solid
Rocket Motor Upgrades (SRMUs) attached to the core to provide the initial stage of boost
during liftoff.
Stage 0, built by Alliant Techsystems, was comprised of two identical, segmented solid
propellant rocket motors. The solid rocket motors (SRMs) were attached to the Stage I/Stage II
core vehicle. Each SRM was 112 ft long and 10.5 ft in diameter and developed 1.5 million lbs of
thrust. Pitch, yaw, and roll corrections were accomplished by gimbaling the engine.
Stage 1 consisted of an Aerojet LR87-AJ-11A liquid propellant rocket engine attached to an
airframe that included the fuel and oxidizer tanks, inner tank structure, forward skirt and aft skirt.
The rocket engine developed 548,000 pounds vacuum thrust. Thrust vector control was
produced by gimbaling the engine to provide pitch, yaw, and roll corrections.
Stage 2 used an Aerojet LR91-AJ-11A liquid propellant rocket engine attached to an airframe
similar in construction to the Stage I. The rocket engine delivered 105,000 lbs of thrust in
vacuum. Thrust vector control was generated by gimbaling the chamber, but roll control was
provided by ducting pump turbine exhaust through a swiveled nozzle to produce thrust.
Centaur was a high-energy upper stage with multiple restart capability. Two thrust chamber
assemblies provided a vacuum thrust of 33,100 lb. The cryogenic propellants were liquid
hydrogen and liquid oxygen. The payload fairing enclosed both the Centaur stage and payload,
and provided environmental protection for the stage and spacecraft on the ground and in flight.
Titan IV Heritage
 The Titan family of launch vehicles was established in December 1955 when the Air Force
awarded the Martin Company (today Lockheed Martin) a contract to build an Inter-Continental
Ballistic Missile (ICBM) that would be more advanced than the Atlas. It became known as the
Titan 1, the nation's first two-stage ICBM.
 The Titan I rocket provided many structural and propulsion techniques that were later
incorporated into the Titan II that became the first underground silo-based ICBM in 1964.
Martin Company and Martin Marietta Corporation, located in Denver, CO, built more than 140
Titan ICBMs - the vanguard of America's nuclear deterrent force for 23 years.
 NASA selected the Titan II as the launch vehicle for the Gemini manned space program in
1961, flying 12 missions that prepared the way to the first manned landing on the moon in 1969.
 Deactivation of the Titan II ICBM system began in July 1982, and the last missile was taken
from its silo at Little Rock Air Force Base, Arkansas, on June 23, 1987.
 The Titan II space launch vehicle evolved into the Titan III and Titan IIIC in the mid 1960s.
Titan IIIs sent 82 military and civilian satellites into orbit between 1965 and 1982. Titan IIIC was
intended by the Air Force to be modified for the Manned Orbiting Laboratory (MOL) program
conducting reconnaissance from a space station. Titan IIIE rockets with Centaur upper stages
carried Viking to Mars and Voyager missions into space.
 The larger Titan IV expendable space launch vehicle was originally developed as a backup for
the space shuttle in the 1980s and became a mainstay for heavy payloads. The Titan IVB
represented significant improvements from the Titan IVA from which it evolved.