Saturn C-2 - Credit: © Mark Wade. 2,708 bytes. 62 x 625 pixels.

The launch vehicle initially considered for realizing the Apollo lunar landing at the earliest possible date. 15 launches and rendezvous required to assemble direct landing spacecraft in earth orbit.

LEO Payload: 21,500 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 6,800 kg. to a: Translunar trajectory. Liftoff Thrust: 682,200 kgf. Total Mass: 624,660 kg. Core Diameter: 6.6 m. Total Length: 82.0 m. Flyaway Unit Cost $: 107.30 million. in 1985 unit dollars.

• Stage Number: 1. 1 x Saturn I Gross Mass: 432,681 kg. Empty Mass: 45,267 kg. Thrust (vac): 773,160 kgf. Isp: 289 sec. Burn time: 150 sec. Isp(sl): 255 sec. Diameter: 6.5 m. Span: 6.5 m. Length: 24.5 m. Propellants: Lox/Kerosene No Engines: 8. H-1

• Stage Number: 2. 1 x Saturn S-II Gross Mass: 100,000 kg. Empty Mass: 14,000 kg. Thrust (vac): 362,745 kgf. Isp: 420 sec. Burn time: 100 sec. Isp(sl): 300 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 22.6 m. Propellants: Lox/LH2 No Engines: 4. J-2

• Stage Number: 3. 1 x Saturn IV Gross Mass: 50,576 kg. Empty Mass: 5,217 kg. Thrust (vac): 40,824 kgf. Isp: 410 sec. Burn time: 482 sec. Diameter: 5.5 m. Span: 5.5 m. Length: 12.2 m. Propellants: Lox/LH2 No Engines: 6. RL-10

• Stage Number: 4. 1 x Centaur C Gross Mass: 15,600 kg. Empty Mass: 1,996 kg. Thrust (vac): 13,608 kgf. Isp: 425 sec. Burn time: 430 sec. Isp(sl): 0 sec. Diameter: 3.1 m. Span: 3.1 m. Length: 9.1 m. Propellants: Lox/LH2 No Engines: 2. RL-10A-1

• National booster program, Dyna-Soar, and Mercury discussed Spacecraft: Mercury.

  The national booster program, Dyna-Soar, and Project Mercury were discussed by the Research Steering Committee. Members also presented reviews of Center programs related to manned space flight. Maxime A. Faget of STG endorsed lunar exploration as the present goal of the Committee although recognizing the end objective as manned interplanetary travel. George M. Low of NASA Headquarters recommended that the Committee:

  • Adopt the lunar landing mission as its long-range objective.
  • Investigate vehicle staging so that Saturn could be used for manned lunar landings without complete reliance on Nova.
  • Make a study of whether parachute or airport landing techniques should be emphasized.
  • Consider nuclear rocket propulsion possibilities for space flight.
  • Attach importance to research on auxiliary power plants such as hydrogen-oxygen systems.

• Lunar mission studies under way at the Army Spacecraft: Mercury.

  During the Research Steering Committee meeting, John H. Disher of NASA Headquarters discussed the lunar mission studies under way at the Army Ballistic Missile Agency (ABMA). Additional Details: Lunar mission studies under way at the Army.

• Army Ballistic Missile Agency mission possibilities

  H. H. Koelle told members of the Research Steering Committee of mission possibilities being considered at the Army Ballistic Missile Agency. These included an engineering satellite, an orbital return capsule, a space crew training vehicle, a manned orbital laboratory, a manned circumlunar vehicle, and a manned lunar landing and return vehicle. He described the current Saturn configurations, including the "C" launch vehicle to be operational in 1967. The Saturn C (larger than the C-1) would be able to boost 85,000 pounds into earth orbit and 25,000 pounds into an escape trajectory.

• Goett Committee

  Committee formed to recommend post-Mercury space program. After four meetings, and studying earth-orbit assembly using Saturn II or direct ascent using Nova, tended to back development of Nova.

• Lunar Exploration Program Based Upon Saturn Systems

  The Army Ballistic Missile Agency submitted to NASA the study entitled "A Lunar Exploration Program Based Upon Saturn-Boosted Systems." In addition to the subjects specified in the preliminary report of October 1, 1959, it included manned lunar landings.

• Guidelines for an advanced manned spacecraft program presented by STG Spacecraft: Apollo CSM.

  Members of STG presented guidelines for an advanced manned spacecraft program to NASA Centers to enlist research assistance in formulating spacecraft and mission design.

  To open these discussions, Director Robert R. Gilruth summarized the guidelines: manned lunar reconnaissance with a lunar mission module, corollary earth orbital missions with a lunar mission module and with a space laboratory, compatibility with the Saturn C-1 or C-2 boosters (weight not to exceed 15,000 pounds for a complete lunar spacecraft and 25,000 pounds for an earth orbiting spacecraft), 14-day flight time, safe recovery from aborts, ground and water landing and avoidance of local hazards, point (ten square-mile) landing, 72-hour postlanding survival period, auxiliary propulsion for maneuvering in space, a "shirtsleeve" environment, a three-man crew, radiation protection, primary command of mission on board, and expanded communications and tracking facilities. In addition, a tentative time schedule was included, projecting multiman earth orbit qualification flights beginning near the end of the first quarter of calendar year 1966.

  ---

  Saturn A-1 to C-5 Credit: © Mark Wade. 12,176 bytes. 639 x 461 pixels.

  ---

• Guidelines for the advanced manned spacecraft program

  STG's Robert O. Piland, during briefings at NASA Centers, presented a detailed description of the guidelines for missions, propulsion, and flight time in the advanced manned spacecraft program:

  1. The spacecraft should be capable ultimately of manned circumlunar reconnaissance. As a logical intermediate step toward future goals of lunar and planetary landing many of the problems associated with manned circumlunar flight would need to be solved.
  2. The lunar spacecraft should be capable of earth orbit missions for initial evaluation and training. The reentry component of this spacecraft should be capable of missions in conjunction with space laboratories or space stations. To accomplish lunar reconnaissance before a manned landing, it would be desirable to approach the moon closer than several thousand miles. Fifty miles appeared to be a reasonable first target for study purposes.
  3. The spacecraft should be designed to be compatible with the Saturn C-1 or C-2 boosters for the lunar mission. The multiman advanced spacecraft should not weigh more than 15,000 pounds including auxiliary propulsion and attaching structure.
  4. A flight-time capability of the spacecraft for 14 days without resupply should be possible. Considerable study of storage batteries, fuel cells, auxiliary power units, and solar batteries would be necessary. Items considered included the percentage of the power units to be placed in the "caboose" (space laboratory), preference for the use of storage batteries for both power and radiation shielding, and redundancy for reliability by using two different types of systems versus two of the same system.

  ---

  Saturn C-2 early - Saturn C-2 early concept Credit: © Mark Wade. 2,557 bytes. 62 x 573 pixels.

  ---

• Space Exploration Program Council

  The third meeting of the Space Exploration Program Council was held at NASA Headquarters. The question of a speedup of Saturn C-2 production and the possibility of using nuclear upper stages with the Saturn booster were discussed. The Office of Launch Vehicle Programs would plan a study on the merits of using nuclear propulsion for some of NASA's more sophisticated missions. If the study substantiated such a need, the amount of in-house basic research could then be determined.

• Apollo Study Bidder's Conference Spacecraft: Apollo CSM.

  Bidder's conference for circumlunar Apollo. Specification: Saturn C-2 compatability (6,800 kg mass for circumlunar mission); 14 day flight time; three-man crew in shirt-sleeve environment.

• Space Exploration Program Council

  The fourth meeting of the Space Exploration Program Council was held at NASA Headquarters. The results of a study on Saturn development and utilization was presented by the Ad Hoc Saturn Study Committee. Objectives of the study were to determine (1) if and when the Saturn C-2 launch vehicle should be developed and (2) if mission and spacecraft planning was consistent with the Saturn vehicle development schedule. No change in the NASA Fiscal Year 1962 budget was contemplated. The Committee recommended that the Saturn C-2 development should proceed on schedule (S-II stage contract in Fiscal Year 1962, first flight in 1965). The C-2 would be essential, the study reported, for Apollo manned circumlunar missions, lunar unmanned exploration, Mars and Venus orbiters and capsule landers, probes to other planets and out-of- ecliptic, and for orbital starting of nuclear upper stages. Additional Details: Space Exploration Program Council.

  ---

  Saturn C1 to C5 - Saturn C1 C2 C3 C4 C5 Credit: © Mark Wade. 12,176 bytes. 639 x 461 pixels.

  ---

• Final report of the Low Committee

  The Manned Lunar Landing Task Group (Low Committee) transmitted its final report to NASA Associate Administrator Robert C. Seamans, Jr. The Group found that the manned lunar landing mission could be accomplished during the decade, using either the earth orbit rendezvous or direct ascent technique. Multiple launchings of Saturn C-2 launch vehicles would be necessary in the earth orbital mode, while the direct ascent technique would require the development of a Nova-class vehicle. Information to be obtained through supporting unmanned lunar exploration programs, such as Ranger and Surveyor, was felt to be essential in carrying out the manned lunar mission. Total funding for the program was estimated at just under $7 billion through Fiscal Year 1968.

• Current Saturn launch vehicle configurations announced

  The current Saturn launch vehicle configurations were announced:

  C-1:

  S-I stage eight H-1 engines, 1.5 million pounds of thrust; S-IV stage four (LR-119 engines, 70,000 pounds of thrust); and S-V stage (two LR-119 engines, 35,000 pounds of thrust).

  C-2 (four-stage version):

  S-1 stage (same as first stage of the C-1); S-II (not determined); S-IV (same as second stage of the C-1); S-V (same as third Stage of C- 1).

  C-2 (three-stage version):

  S-I (same as first stage of C-1); S-II (not determined); and S-IV (same as third stage of C-1).

• Configuration changes for the Saturn C-1 launch vehicles

  ---

  Saturn C-2 with RIFT - Saturn C-2 with RIFT (Reactor In-Flight Test) Nuclear upper stage Credit: © Mark Wade. 2,573 bytes. 62 x 578 pixels.

  ---

  Representatives of Marshall Space Flight Center recommended configuration changes for the Saturn C-1 launch vehicles to NASA Headquarters. These included:
  • Elimination of third-stage development, since two stages could put more than ten tons into earth orbit.
  • Use of six LR-115 (15,000-pound) Centaur engines (second-stage thrust thus increased from 70,000 to 90,000 pounds).
  • Redesign of the first stage (S-1) to offer more safety for manned missions.
  Plans were also presented to accelerate the development of the Saturn C- 2, and a recommendation was made that a prime contractor be selected to work on the second stage (S-II) of the C-2. NASA Headquarters approved the C-2 plans on March 31.

• Ad Hoc Task Group for a Manned Lunar Landing Study

  NASA Associate Administrator Robert C. Seamans, Jr., established the Ad Hoc Task Group for a Manned Lunar Landing Study, to be chaired by William A. Fleming of NASA Headquarters. The study was expected to produce the following information:

  • All tasks associated with the mission.
  • Interdependent time-phasing of the tasks.
  • Areas requiring considerable technological advancements from the current state of the art.
  • Tasks for which multiple approach solutions were advisable.
  • Important action and decision points in the mission plan.
  • A refined estimate by task and by fiscal year of the dollar resources required for the mission.
  • Refined estimates of in-house manpower requirements, by task and by fiscal year
  • Tentative in-house and contractor task assignments accompanying the dollar and manpower resource requirements.
  The study began on May 8 and the final report was submitted on June 16. Guidelines served as a starting point for the study:
  • The manned lunar landing target date was 1967.
  • Intermediate missions of multiman orbital satellites and manned circumlunar missions were desirable at the earliest possible time.
  • Man's mission on the moon as it affected the study was to be determined by the Ad Hoc Task Group - i.e., the time to be spent on the lunar surface and the tasks to be performed while there.
  • In establishing the mission plan, the use of the Saturn C-2 launch vehicle was to be evaluated as compared with an alternative launch vehicle having a higher thrust first stage and C-2 upper-stage components.
  • The mission plan was to include parallel development of liquid and solid propulsion leading to a Nova vehicle 400,000 pounds in earth orbit and should indicate when the decision should be made on the final Nova configuration.
  • Nuclear-powered launch vehicles should not be considered for use in the first manned lunar landing mission.
  • The flight test program should be laid out with enough launchings to meet the needs of the program considering the reliability requirements.
  • Alternative approaches should be provided in critical areas - e.g., upper stages and mission modes.

  The engineering sketch drawn by John D. Bird of Langley Research Center on May 3, 1961, indicated the thinking of that period: By launching two Saturn C-2's, the lunar landing mission could be accomplished by using both earth rendezvous and lunar rendezvous at various stages of the mission.

  ---

  Saturn II (1959) - Saturn II configuration for Project Horizon Credit: US Army. 2,913 bytes. 152 x 496 pixels.

  ---

• Lundin Committee recommended earth orbit rendezvous mode

  'The Lundin Committee completed its study of various vehicle systems for the manned lunar landing mission, as requested on May 25 by NASA associate Administrator Robert C. Seamans, Jr. The Committee had considered alternative methods of rendezvous: earth orbit, lunar orbit, a combination of earth and lunar orbit, and lunar surface. Launch vehicles studied were the Saturn C-2 and C-3. Conclusion was that 43,000 kg stage (85% fuel) was needed for a lunar landing mission. The concept of a low- altitude earth orbit rendezvous using two or three C-3's was clearly preferred by the Committee. Reasons for this preference were the small number of launches and orbital operations required and the fact that the Saturn C- 3 was considered to be an efficient launch vehicle of great utility and future growth.

• First decision on Apollo launch vehicles

  Meeting with Webb/Dryden, work on Saturn C-2 stopped; preliminary design of C-3 and continuing studies of larger vehicles for landing missions requested. STG push for 4 x 6.6 m diameter solid cluster first stage rejected for safety and ground handling reasons.

• Saturn C-2 discontinued

  NASA announced that further engineering design work on the Saturn C-2 configuration would be discontinued and that effort instead would be redirected toward clarification of the Saturn C-3 and Nova concepts. Investigations were specifically directed toward determining capabilities of the proposed C-3 configuration in supporting the Apollo mission.

  ---

  Saturn II Stages - Saturn II, Stages 1 through 4, configuration for Project Horizon (1959) Credit: US Army. 6,097 bytes. 424 x 358 pixels.

  ---

• Changes in Saturn launch vehicle configurations

  Changes in Saturn launch vehicle configurations were announced :

  C-1:

  Stages S-I (1.5 million pounds of thrust) and S-IV

  C-2:

  Stages S-I, S-II, and S-IV

  C-3:

  Stages S-IB (3 million pounds of thrust), S-II, and S-IV.

• 45 - Koelle, Heinz Hermann,, Handbook of Astronautical Engineering, McGraw-Hill,New York, 1961.
• 222 - Bilstein, Roger E, Stages to Saturn, US Government Printing Office, 1980.
• 228 - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. HTML when accessed: http://www.webcreations.com/ptm
• 231 - Stuhlinger, Ernst, et. al., Astronautical Engineering and Science: From Peenemuende to Planetary Space, McGraw-Hill, New York, 1964.