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Titan IV Solid Rocket Motor (SRM)

Two types of Titan IV systems are defined based on the Solid Rocket Motor (SRM) configuration used for the Launch Vehicles' Stage 0. The first type, Titan IVA, employs two standard seven segment Solid Rocket Motors (SRMs) by Chemical Systems Division (CSD) of United Technologies Corporation. The second type, Titan IVB, employs three segment Solid Rocket Motor Upgrades (SRMUs) by Alliant, Inc. for the Stage 0.

Solid Rocket Motor (SRM)

  • Length: 113ft
  • Diameter: 10ft
  • Propellant: 84% PBAN
  • Thrust: 1,600,000lbs (7.0 MN) Vac
  • ISP: 271.6sec Vac
  • Total Impulse: 160.52x10^6lbs-sec
  • TVC: N2O4 Liquid Injection

CHARACTERISTICS: On Titan IVA initial liftoff thrust is provided by two identical SRMs which are attached to the Core Vehicle Stages I and II by means of a forward support ring structure and Core attach support arms in the aft support skirt assembly. The two SRMs are mounted 180 degrees apart in the Core Vehicle yaw plane. Each SRM is about 113 ft long in a static condition, the motor length increases less than one inch after ignition due to pressurization. In the dynamic condition, the length is about 115 ft. The dry weight of each SRM is about 95,000 lbs and the loaded weight is almost 700,000 lbs.

STAGING MOTOR SYSTEM: The requirement for this system is to provide a lateral staging impulse to each SRM for movement away from the Core Vehicle. This is accomplished by eight staging motors, four in the nose section and four in the aft section (for each SRM). The thrust of the staging motors is offset relative to the booster centerline in order to impart a rotation to the SRM. When fired simultaneously the staging motors provide an impulse to rotate and move the expended SRMs away from the Core Vehicle.

THRUST VECTOR CONTROL SYSTEM: The TVC is used to maintain a proper vehicle flight path and orientation during the Stage 0 portion of the mission tragectory via signals from the Core Vehicle guidance computer. The desired flight profile is achieved by exerting side forces on each SRM by injecting a flow of gas, at a specified angle, at a defined velocity and for a calculated time into the SRM gas flow stream through the nozzle. The SRM nozzles are at a fixed angle and do not gimbal.

Solid Rocket Motor Upgrade (SRMU)

  • Length: 112ft
  • Diameter: 11ft
  • Propellant: 88% HTPB
  • Thrust: 1,700,000lbs (7.5 MN) Vac
  • ISP: 285.6sec Vac
  • Total Impulse: 196.69x10^6lbs-sec
  • TVC: Gimballed Nozzle

CHARACTERISTICS: The three segment SRMU assemblies are mounted to the Titan IV Core in an arrangement similar to the Titan IV Type I SRM configuration. The SRMU is about 112 ft long and has about a 11 ft nominal inside core diameter. The total nominal weight of each SRMU is 770,673 lbs, of which 688,853 lbs is propellant.

STAGING MOTOR SYSTEM: Again, the purpose of the staging rockets is the separation of the expended SRMUs from the Core Vehicle. This is accomplished by six staging rockets, three forward in the nose cone assembly and three in the aft skirt assembly (for each SRMU).

THRUST VECTOR CONTROL SYSTEM: The TVC system is of a redundant configuration that includes turbocentrifugal pumps, gas generators and servoactuator assemblies. After the system has been initiated, the Titan IV Core Vehicle commands the nozzle to an off-nul position and responds to flight





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Page last modified: 21-07-2011 00:49:00 ZULU