Titan II GLV
Titan II GLV General Arrangement (2-Bit) (344 kb GIF)
Titan II GLV General Arrangement (8-Bit) (Scan 1) (2.14 MB GIF)
Titan II GLV General Arrangement (8-Bit) (Scan 2) (1.91 MB GIF)
Titan II GLV General Arrangement (8-Bit) (Scan 3) (1.86 MB GIF)
Titan II GLV General Arrangement (8-Bit) (Scan 4) (1.81 MB GIF)
Titan II GLV General Arrangement (8-Bit) (Scan 5) (2.38 MB GIF)
Titan II GLV General Arrangement (8-Bit) (Scan 6) (1.91 MB GIF)
Titan II GLV Cutaway Artwork (1.08 MB GIF)
Modifications made to Titan II for GLV configuration (1.09 MB GIF)
Titan II GLV Components
Titan II GLV/Spacecraft Launch Configuration Drawing
Titan II GLV/Spacecraft Launch Configuration Drawing by Peter Alway
Stage I Fuel Tank Volume: 1,627.24 ft3  (based upon
analysis of 26 sets of Titan II and 5 sets of GLV tanks)
Stage I Oxidizer Tank Volume: 1,924.84 ft3  (based upon analysis of 26 sets of Titan II and 5 sets of GLV tanks)
Stage I Fuel: 88,176 lbs 
Stage I Oxidizer: 169,297 lbs 
Stage I Total Propellant: 257,474 lbs 
Stage I Unburned Propellant: Maximum of 1,194 lbs, mean of 408 lbs 
Stage II Fuel: 21,622 lbs 
Stage II Oxidizer: 38,217 lbs 
Stage II Total Propellant: 59,839 lbs 
Stage I Unburned Propellant: Maximum of 581 lbs, mean of 195 lbs 
Notes: Fuel/Oxidizer totals, as well as unburned masses are averages of five different GLVs (3, 5, 6, 6A, and 8) in Reference 1.
 Gemini Launch Vehicle: PROGRAM AND FACILITIES MONTHLY PROGRESS (SEPTEMBER 1964)
GEMINI LAUNCH VEHICLE DEVELOPMENT, by Walter D. Smith, Program Director, Gemini Program, Martin-Marietta Corp.
The fundamental modifications made to the Titan II to adapt it for use as the GLV were—
(1) The Titan II inertial guidance system was replaced with a radio guidance system.
(2) Provision was made for a redundant flight-control and guidance system which can be automatically or manually commanded to take over and safely complete the entire launch phase in the event of a primary system failure. This system addition was required because of the extremely short time available for the crew to command abort and escape, in the event of critical flight-control failures during the high-dynamic-pressure region of stage I flight. This redundant system was added primarily to insure crew safety in case of a critical malfunction ; however, it also significantly increases the probability of overall mission success.
(3) A malfunction detection system, designed to sense critical failure conditions in the launch vehicle, was included. The action initiated by the malfunction detection system, in the case of flight-control or guidance failures, is a command to switch over to the secondary flight-control and guidance system. For other failures, appropriate displays are presented to the crew.
(4) Redundancy was added in the electrical system to the point of having two completely independent power buses provided to critical components, and redundancy for all inflight sequencing. The wiring for each power subsystem is routed along opposite sides of the launch vehicle for full redundancy. 400 Hz and 25 VDC power supplies were added to power the primary and secondary guidance flight-control systems added for the GLV.
(5) The Titan II retrorockets and vernier rockets were eliminated because no requirement existed for them on the GLV. These deletions resulted in a valuable weight savings and an increase in mission reliability.
(6) A new stage II oxidizer-tank forward skirt assembly was designed to mate the launch vehicle to the spacecraft.
(7) The Titan II equipment-support truss was modified to accommodate GLV equipment requirements.
(8) Devices were added to the GLV stage 1 propellant lines to attenuate the launch vehicle longitudinal oscillations, or POGO effect.
(9) The Titan II range-safety and ordnance systems were modified, by the addition of certain logic circuitry and by changes to the destruct initiators, to increase crew safety.
Gemini Program Mission Report: Gemini X (August 1966)
Stage I Oxidizer: 171,383 lbs
Stage I Fuel: 89,339 lbs
Stage I Thrust (Std Inlet): 437,769
Stage I ISP (Std Inlet): 261.03
Stage I O/F (Std Inlet): 1.9098
Stage II Oxidizer Flow Rate: 1100.34 lb/sec
Stage II Fuel Flow Rate: 576.72 lb/sec
Stage II Oxidizer: 38,850 lbs
Stage II Fuel: 21,945 lbs
Stage II Thrust (Std Inlet): 99,474
Stage II ISP (Std Inlet): 309.82
Stage II O/F (Std Inlet): 1.8020
Stage II Oxidizer Flow Rate: 206.64 lb/sec
Stage II Fuel Flow Rate: 114.43 lb/sec
Gemini Spacecraft #10: 8,295 lbs
Total Ground Ignition Weight: 344,856 lbs