Titan IV Launch Vehicle

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• Titan IV Launch Vehicle

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Titan IV Launch Vehicle
Titan IVA
Titan IVB
Titan IV Heritage
Titan IV Launch History
Reference Information
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Titan IVA Model Configuration
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Titan IVA Model Configuration
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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
6
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Mobile Service Tower has been retracted and the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.
http//saturn.jpl.nasa.gov/multimedia/images/image
-details.cfm?imageID948
7
Titan IVB Cassini
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.
Payload Fairing
Cassini High Gain Antenna
Huygens Probe
Centaur Upper Stage
http//saturn.jpl.nasa.gov/spacecraft/index.cfm
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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.
http//saturn.jpl.nasa.gov/multimedia/images/image
-details.cfm?imageID770
9
Titan IVB Cassini Launch

The launch of the Cassini - Huygens spacecraft on
October 15, 1997 is photographed from a Florida
beach.
http//www1.nasa.gov/mission_pages/cassini/whycass
ini/cassinif-20071011.html
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Titan IV Launch History
Sheet 1
Indicates Titan failure
http//www.spaceflightnow.com/titan/b26/051016hist
ory.html
http//www.astronautix.com/lvs/titan4.htm

Sources
11
Titan-4 Launch History Lockheed Martin
Astronautics Operations in Denver, CO, is under
contract to the US Air Force Space and Missile
Systems Center, Los Angeles Air Force Base, CA,
to complete the launch of 39 vehicles. The last
Titan IVB rocket to be launched from CCAFS was
off load from a C-5 Galaxy jet on 01 May 2003. As
of that date, there were four or five remaining
Titan IVB launches scheduled, three from Cape
Canaveral and one from Vandenberg Air Force Base.
The April 2003 Milstar launch was the 35th Titan
IV to be launched, including 24 from the Cape and
11 from Vandenberg. The Defense Support Program
Flight-22 payload will be the last to fly on a
Titan IVB rocket from Cape Canaveral in 2003.
This Titan IVB will transport this payload.
Titan 4 launches from Cape Canaveral
Titan IV Launch History
Sheet 2
http//www.spaceflightnow.com/titan/b26/051016hist
ory.html
http//www.astronautix.com/lvs/titan4.htm

Sources
12
Titan-4 Launch History Lockheed Martin
Astronautics Operations in Denver, CO, is under
contract to the US Air Force Space and Missile
Systems Center, Los Angeles Air Force Base, CA,
to complete the launch of 39 vehicles. The last
Titan IVB rocket to be launched from CCAFS was
off load from a C-5 Galaxy jet on 01 May 2003. As
of that date, there were four or five remaining
Titan IVB launches scheduled, three from Cape
Canaveral and one from Vandenberg Air Force Base.
The April 2003 Milstar launch was the 35th Titan
IV to be launched, including 24 from the Cape and
11 from Vandenberg. The Defense Support Program
Flight-22 payload will be the last to fly on a
Titan IVB rocket from Cape Canaveral in 2003.
This Titan IVB will transport this payload.
Titan 4 launches from Cape Canaveral
Titan IV Launch History
Sheet 3
http//www.spaceflightnow.com/titan/b26/051016hist
ory.html
http//www.astronautix.com/lvs/titan4.htm

Sources
13
Titan 4 launches from Cape Canaveral
Titan IV Launch History
Sheet 4
Indicates Titan failure Indicates
upper stage failure
http//www.spaceflightnow.com/titan/b26/051016hist
ory.html
http//www.astronautix.com/lvs/titan4.htm

Sources
14
Titan-4 Launch History Lockheed Martin
Astronautics Operations in Denver, CO, is under
contract to the US Air Force Space and Missile
Systems Center, Los Angeles Air Force Base, CA,
to complete the launch of 39 vehicles. The last
Titan IVB rocket to be launched from CCAFS was
off load from a C-5 Galaxy jet on 01 May 2003. As
of that date, there were four or five remaining
Titan IVB launches scheduled, three from Cape
Canaveral and one from Vandenberg Air Force Base.
The April 2003 Milstar launch was the 35th Titan
IV to be launched, including 24 from the Cape and
11 from Vandenberg. The Defense Support Program
Flight-22 payload will be the last to fly on a
Titan IVB rocket from Cape Canaveral in 2003.
This Titan IVB will transport this payload.
Titan 4 launches from Cape Canaveral
Titan IV Launch History
Sheet 5
http//www.spaceflightnow.com/titan/b26/051016hist
ory.html
http//www.astronautix.com/lvs/titan4.htm
http//www.space.com/missionlaunches/sfn_051020_ti
tan4_finalflight.html

Sources
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Titan IV Heritage
Titan I Titan II Gemini Titan 34B Titan
IIIC Titan IIIC Titan IIIC -
Titan Agena
MOL Centaur
http//upload.wikimedia.org/wikipedia/commons/1/1f
/Titan_Missile_Family.png
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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 back-up 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
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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?imageID948
• http//saturn.jpl.nasa.gov/spacecraft/index.cfm
• http//saturn.jpl.nasa.gov/multimedia/images/image
  -details.cfm?imageID770
• http//www1.nasa.gov/mission_pages/cassini/whycass
  ini/cassinif-20071011.html
• http//upload.wikimedia.org/wikipedia/commons/1/1f
  /Titan_Missile_Family.png
• Text only
• http//www.spaceflightnow.com/titan/b26/051016hist
  ory.html
• http//www.astronautix.com/lvs/titan4.htm
• http//www.space.com/missionlaunches/sfn_051020_ti
  tan4_finalflight.html
• http//www.spaceflightnow.com/titan/b26/051016tita
  n4b.html
• http//www.fas.org/spp/military/program/launch/tit
  an.htm
• http//www.space-travel.com/reports/ATK_Gives_Tita
  n_4_A_Boost.html

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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
  IV-Heavy 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.

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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.

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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
  solid-rocket 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.

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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.

22
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.