Model: Saturn C-3.

Saturn C-3 Credit - © Mark Wade

Orbital launch vehicle. Family: Saturn. Other Family: Study. Country: USA. Status: Study 1960.

The launch vehicle concept considered for a time as the leading contender for the Earth Orbit Rendezvous approach to an American lunar landing.

Manufacturer: Von Braun. LEO Payload: 36,300 kg (80,000 lb). to: 556 km Orbit. at: 28.00 degrees. Payload: 13,600 kg (29,900 lb). to a: Translunar trajectory. Liftoff Thrust: 11,628.600 kN (2,614,213 lbf). Total Mass: 1,023,670 kg (2,256,800 lb). Core Diameter: 8.25 m (27.06 ft). Total Length: 82.00 m (269.00 ft). Flyaway Unit Cost $: 43.500 million. in: 1985 unit dollars.

• Stage1: 1 x Saturn S-IB-2. Gross Mass: 725,491 kg (1,599,433 lb). Empty Mass: 68,014 kg (149,945 lb). Motor: 2 x F-1. Thrust (vac): 13,339.956 kN (2,998,941 lbf). Isp: 304 sec. Burn time: 139 sec. Length: 34.50 m (113.10 ft). Diameter: 8.25 m (27.06 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Saturn S-II-C3. Gross Mass: 204,044 kg (449,840 lb). Empty Mass: 24,938 kg (54,978 lb). Motor: 4 x J-2. Thrust (vac): 3,557.313 kN (799,716 lbf). Isp: 420 sec. Burn time: 200 sec. Length: 21.30 m (69.80 ft). Diameter: 8.25 m (27.06 ft). Propellants: Lox/LH2.

• Stage3: 1 x Saturn IV. Gross Mass: 50,576 kg (111,500 lb). Empty Mass: 5,217 kg (11,501 lb). Motor: 6 x RL-10. Thrust (vac): 400.346 kN (90,001 lbf). Isp: 410 sec. Burn time: 482 sec. Length: 12.19 m (39.99 ft). Diameter: 5.49 m (18.01 ft). Propellants: Lox/LH2.

Model: Saturn C-3B.

Saturn C-33B 3 Stage Credit - © Mark Wade

Family: Saturn. Status: Study 1961.

Final configurtion of the Saturn C-3 at the time of selection of the Saturn C-5 configuration for the Apollo program in December 1961.

LEO Payload: 78,000 kg (171,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 25,000 kg (55,000 lb). to a: Translunar trajectory. Liftoff Thrust: 20,010.000 kN (4,498,420 lbf). Total Mass: 1,690,590 kg (3,727,110 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 85.00 m (278.00 ft).

• Stage1: 1 x Saturn IC C-3B. Gross Mass: 1,160,787 kg (2,559,097 lb). Empty Mass: 72,549 kg (159,943 lb). Motor: 5 x F-1. Thrust (vac): 22,954.798 kN (5,160,444 lbf). Isp: 304 sec. Burn time: 140 sec. Length: 34.41 m (112.89 ft). Diameter: 10.06 m (33.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Saturn II C-5A. Gross Mass: 384,057 kg (846,700 lb). Empty Mass: 31,740 kg (69,970 lb). Motor: 5 x J-2. Thrust (vac): 4,446.648 kN (999,646 lbf). Isp: 420 sec. Burn time: 320 sec. Length: 21.39 m (70.17 ft). Diameter: 10.06 m (33.00 ft). Propellants: Lox/LH2.

• Stage3: 1 x Saturn IVB C-3B. Gross Mass: 52,144 kg (114,957 lb). Empty Mass: 6,801 kg (14,993 lb). Motor: 1 x J-2. Thrust (vac): 889.325 kN (199,928 lbf). Isp: 420 sec. Burn time: 207 sec. Length: 15.40 m (50.50 ft). Diameter: 5.59 m (18.33 ft). Propellants: Lox/LH2.

Model: Saturn C-3BN.

Saturn C-3N Nov 61 Credit - © Mark Wade

Nuclear orbital launch vehicle. Family: Saturn. Status: Study 1961.

Version of Saturn C-3 considered with small nuclear thermal stage in place of S-IVB oxygen/hydrogen stage.

LEO Payload: 94,000 kg (207,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 38,000 kg (83,000 lb). to a: Translunar trajectory. Liftoff Thrust: 20,010.000 kN (4,498,420 lbf). Total Mass: 1,690,110 kg (3,726,050 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 87.00 m (285.00 ft).

• Stage1: 1 x Saturn IC C-3B. Gross Mass: 1,160,787 kg (2,559,097 lb). Empty Mass: 72,549 kg (159,943 lb). Motor: 5 x F-1. Thrust (vac): 22,954.798 kN (5,160,444 lbf). Isp: 304 sec. Burn time: 140 sec. Length: 34.41 m (112.89 ft). Diameter: 10.06 m (33.00 ft). Propellants: Lox/Kerosene.

• Stage2: 1 x Saturn II C-5A. Gross Mass: 384,057 kg (846,700 lb). Empty Mass: 31,740 kg (69,970 lb). Motor: 5 x J-2. Thrust (vac): 4,446.648 kN (999,646 lbf). Isp: 420 sec. Burn time: 320 sec. Length: 21.39 m (70.17 ft). Diameter: 10.06 m (33.00 ft). Propellants: Lox/LH2.

• Stage3: 1 x Saturn S-N C-3BN. Gross Mass: 32,470 kg (71,580 lb). Empty Mass: 7,708 kg (16,993 lb). Motor: 1 x Nerva. Thrust (vac): 266.799 kN (59,979 lbf). Isp: 800 sec. Burn time: 720 sec. Length: 16.56 m (54.33 ft). Diameter: 10.06 m (33.00 ft). Propellants: Nuclear/LH2.

1954 October 18 - Nuclear rocket engine proposed. At the suggestion of Theodore von Kármán and following a request of Gen. H. B. Thatcher, an Ad Hoc Committee of the Scientific Advisory Board met in the Pentagon to consider the application of nuclear energy to missile propulsion. In its report, the Committee "noted that there was an almost complete hiatus in the study of the nuclear rocket from 1947 following a report by North American Aviation, until a 1953 report by the Oak Ridge National Laboratory. Because the technical problems appear so severe, and because another 6 years of no progress in this area would seem to be unfortunate," the Committee felt that a continuing study both analytical and experimental, at a modest level of effort, should be carried on.

1955 June 1 - NERVA project begins. NACA Lewis Laboratory presented ARDC with results of air-breathing nuclear propulsion systems for manned applications, leading to AEC-AF Pluto project, and also initiated comparison of nuclear rocket with chemical systems for ICBM, a concept of use to Rover program.

1955 November 2 - NERVA go-ahead. The Atomic Energy Commission approved, on the basis of a statement of interest by the Department of Defense, the proposed plans of the Los Alamos Scientific and the Radiation Laboratories of the University of California, for the study and development of nuclear power for rocket propulsion.

1957 March 18 - NERVA research cut back. As a result of guidance from the Secretary of Defense as to desired level of effort, the Atomic Energy Commission reduced its program on nuclear rocket propulsion to a single laboratory effort, phasing out work at the University of California Radiation Laboratory and concentrating AEC development efforts at Los Alamos Scientific Laboratory.

1957 June 1 - NERVA advanced concepts studied. Research on tungsten nuclear rocket propulsion systems initiated by NACA Lewis Laboratory, and other feasible systems for practical nuclear rocket systems, such as 1958 concept of coaxial jet gaseous reactor, followed.

1959 May 25-26 - 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.

1959 July 1 - Kiwi-A first experimental nuclear rocket tested. The first experimental reactor (Kiwi-A) in the nuclear space rocket program operated successfully at full temperature and duration at Jackass Flats, Nev.

1959 December 19 - NERVA development roles AEC/NASA. The Chairman, AEC, in a letter to the Administrator of NASA, proposed a flight test objective be established for the nuclear rocket program and proposed a technical program and division of agency responsibilities to achieve those objectives.

1960 July 5 - House recommends a high priority manned expedition to the moon The House Committee on Science and Astronautics declared: "A high priority program should be undertaken to place a manned expedition on the moon in this decade. A firm plan with this goal in view should be drawn up and submitted to the Congress by NASA. Such a plan, however, should be completely integrated with other goals, to minimize total costs. The modular concept deserves close study. Particular attention should be paid immediately to long lead-time phases of such a program." The Committee also recommended that development of the F-1 engine be expedited in expectation of the Nova launch vehicle, that there be more research on nuclear engines and less conventional engines before freezing the Nova concept, and that the Orion project be turned over to NASA. It was the view of the Committee that "NASA's 10-year program is a good program, as far as it goes, but it does not go far enough. Furthermore the space program is not being pushed with sufficient energy."

1960 July 8 - Kiwi-A Prime tested at full power. Second experimental reactor (Kiwi-A Prime) in the Project Rover nuclear rocket program was successfully tested at full power and duration at Jackass Flats, Nev.

1960 July 14-15 - 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.

1960 September 29 - RAND Corporation to evaluate nuclear propulsion missions In a memorandum to NASA Associate Administrator Robert C. Seamans, Jr., Robert L. King, Executive Secretary, described the action taken on certain items discussed at the July 14-15 meeting of the Space Exploration Program Council. Among these actions was the awarding of a contract to The RAND Corporation to evaluate missions for which nuclear propulsion would be desirable. Included in the study would be the determination of availability dates, cost of development, operational costs, the safety aspects of the missions, and an evaluation of research requirements.

1960 October 7 - NERVA test facilities bidder's conference. AEC briefing held at the Nevada Test Site at Jackass Flats, Nev., for representatives of 26 companies for proposals to study the requirements for a National Nuclear Rocket Engine Development Facility. Existing test facilities are fully committed to the development of nuclear reactors.

1960 October 19 - Project Rover request for bids. Kiwi-A No. 3 static test of nuclear rocket propulsion was successfully conducted at AEC Nevada test site, resulting in NASA-AEC call for bids for industrial development phase of Project Rover on November 1, 1960.

1961 February 2 - NERVA Request for Proposal. NASA-AEC Space Nuclear Propulsion Office invited industry to submit proposals for participation in development of Nerva (nuclear engine for rocket vehicle application), a part of Project Rover initiated in 1955 by USAF-AEC.

1961 June 10 - Lundin Committee recommended earth orbit rendezvous mode Spacecraft: Apollo Lunar Landing. '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.

1961 June 20 - Donald Heaton had been appointed Chairman of an Ad Hoc Task Group Robert C. Seamans, Jr., NASA Associate Administrator, notified the Directors of Launch Vehicle Program, Space Flight Programs, Advanced Research Programs, and Life Sciences Programs that Donald H. Heaton had been appointed Chairman of an Ad Hoc Task Group. It would establish program plans and supporting resources necessary to accomplish the manned lunar landing mission by the use of rendezvous techniques, using the Saturn C-3 launch vehicle, with a target date of 1967. Guidelines and operating methods were similar to those of the Fleming Committee. Members of the Task Group would be appointed from the Offices of Launch Vehicle Programs, Space Flight Program, Advanced Research Programs, and Life Sciences Programs. The work of the Group (Heaton Committee) would be reviewed weekly. The study was completed during August.

1961 June 22 - First decision on Apollo launch vehicles Spacecraft: Apollo Lunar Landing. 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.

1961 June 23 - NASA / DOD agree to define support requirements NASA Associate Administrator Robert C. Seamans, Jr., requested Kurt H. Debus, Director of the NASA Launch Operations Directorate, and Maj. Gen. Leighton I. Davis, Commander of the Air Force Missile Test Center, to make a joint analysis of all major factors regarding the launch requirements, methods, and procedures needed in support of an early manned lunar landing. The schedules and early requirements were to be considered in two phases:

1. in line with the Fleming Report, a direct flight to the moon would be assumed, using the Saturn C-1 and C-3 launch vehicles in early support phases and liquid- or solid-fueled Nova launch vehicles for the lunar landing;
2. as a possible alternative or parallel program, orbital rendezvous operations using Saturn C-3 and liquid-fueled Nova.

1961 June 23 - Saturn C-2 discontinued Spacecraft: Apollo Lunar Landing. 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.

1961 July 6 - Manned Lunar Landing Coordination Group At NASA Headquarters, the first meeting was held of the Manned Lunar Landing Coordination Group, attended by NASA Associate Administrator Robert C. Seamans, Jr., Ira H. Abbott, Don R. Ostrander, Charles H. Roadman, William A. Fleming, DeMarquis D. Wyatt (part-time), and George M. Low (in place of Abe Silverstein). This Headquarters Group, appointed by Seamans, was to coordinate problems that jointly affected several NASA Offices, during the interim period while the manned space flight organization was being formed. Members of the steering group included NASA program directors, with participation by Wernher von Braun of Marshall Space Flight Center, Robert R. Gilruth of STG, and Wyatt and Abraham Hyatt of NASA Headquarters, as required. Fleming acted as Secretary of the Group. A list of decisions and actions required to implement an accelerated lunar landing program was drawn up as a tentative agenda for the next meeting:

• Begin Nova systems integration studies and develop the general arrangement of second and third stages. The studies should include spacecraft propulsion stages and spacecraft.
• Begin Saturn C-3 systems integration studies.
• Begin developing Nova and C-3 first-stage specifications in preparation to letting contracts
• Continue Launch Operations Directorate-Air Force Missile Test Center studies of Nova and C-3 launch sites at Atlantic Missile Range (AMR).
• Take steps to bring the contractor aboard as soon as possible for Nova and C-3 launch facility and test stand designs.
• Accelerate F-1 engine funding to provide adequate production engines for the Nova and C-3.
• Examine the Marshall Space Flight Center (MSFC) proposal for static test facilities for large vehicle stages with a view toward beginning detailed site examination.
• Accelerate funding of the J-2 engine to provide acceptance test stands.
• Determine the necessity for a one-million-pound-thrust liquid- hydrogen - liquid-oxygen engine.
• Begin design studies on spacecraft propulsion systems and develop specifications. Define management responsibilities.
• Begin preparations for letting the contract for a spacecraft operations facility at AMR.
• Determine the relationships and responsibilities of MSFC and STG on guidance and control.

1961 July 31 - NASA-DOD report on launch sites for Apollo Phase I of a joint NASA-DOD report on facilities and resources required at launch sites to support the manned lunar landing program was submitted to Associate Administrator Robert C. Seamans, Jr., by Kurt H. Debus, Director, Launch Operations Directorate, and Maj. Gen. Leighton I. Davis, Commander of the Air Force Missile Test Center. The report, requested by Seamans on June 23, was based on the use of Nova- class launch vehicles for the manned lunar landing in a direct ascent mode, with the Saturn C-3 in supporting missions. Eight launch sites were considered: Cape Canaveral (on-shore); Cape Canaveral (off- shore); Mayaguana Island (Atlantic Missile Range downrange); Cumberland Island, Ga.; Brownsville, Tex.; White Sands Missile Range, N. Mex.; Christmas Island, Pacific Ocean; and South Point, Hawaii. On the basis of minimum cost and use of existing national resources, and taking into consideration the stringent time schedule, White Sands Missile Range and Cape Canaveral (on-shore) were favored. White Sands presented serious limitations on launch azimuths because of first-stage impact hazards on populated areas.

1961 July - Improved Mercury proposed for lunar landing Spacecraft: Gemini LOR, Apollo Lunar Landing. James A. Chamberlin and James T. Rose of STG proposed adapting the improved Mercury spacecraft to a 35,000-pound payload, including a 5,000-pound "lunar lander." This payload would be launched by a Saturn C-3 in the lunar orbit rendezvous mode. The proposal was in direct competition with the Apollo proposals that favored direct landing on the moon and involved a 150,000-pound payload launched by a Nova-class vehicle with approximately 12 million pounds of thrust.

1961 August 28 - NERVA facilities contract. NASA selected Vitro Engineering Co. for negotiation of a design contract for an engine maintenance and disassembly building, one of the facilities to be a part of the National Nuclear Rocket Development Center.

1961 August 31 - Chamberlain proposes lunar landing by Gemini Spacecraft: Gemini. Landing by Gemini using 4,000 kg wet/680 kg empty lander and Saturn C-3 booster. Landing by January 1966.

1961 August - Heaton Committee recommends earth orbit rendezvous for Apollo mission Spacecraft: Apollo Lunar Landing. The Ad Hoc Task Group for Study of Manned Lunar Landing by Rendezvous Techniques, Donald H. Heaton, Chairman, reported its conclusions: rendezvous offered the earliest possibility for a successful lunar landing, the proposed Saturn C-4 configuration should offer a higher probability of an earlier successful manned lunar landing than the C-3, the rendezvous technique recommended involved rendezvous and docking in earth orbit of a propulsion unit and a manned spacecraft, the cost of the total program through first lunar landing by rendezvous was significantly less than by direct ascent.

1961 September 7 - Selection of Saturn first stage assembly plant NASA announced that the government-owned Michoud Ordnance Plant near New Orleans, La., would be the site for fabrication and assembly of the Saturn C-3 first stage as well as larger vehicles. Finalists were two government-owned plants in St. Louis and New Orleans. The height of the factory roof at Michoud meant that an 8 x F-1 engined vehicle could not be built; 4 or 5 engines would have to be the maximum.

1961 November 6 - Working group on large launch vehicles In a memorandum to D. Brainerd Holmes, Director, Office of Manned Space Flight (OMSF), Milton W. Rosen, Director of Launch Vehicles and Propulsion, OMSF, described the organization of a working group to recommend to the Director a large launch vehicle program which would meet the requirements of manned space flight and which would have broad and continuing national utility for other NASA and DOD programs. The group would include members from the NASA Office of Launch Vehicles and Propulsion (Rosen, Chairman, Richard B. Canright, Eldon W. Hall, Elliott Mitchell, Norman Rafel, Melvyn Savage, and Adelbert O. Tischler); from the Marshall Space Flight Center (William A. Mrazek, Hans H. Maus, and James B. Bramlet); and from the NASA Office of Spacecraft and Flight Missions (John H. Disher). (David M. Hammock of MSC was later added to the group.) The principal background material to be used by the group would consist of reports of the Large Launch Vehicle Planning Group (Golovin Committee), the Fleming Committee, the Lundin Committee, the Heaton Committee, and the Debus-Davis Committee. Some of the subjects the group would be considering were:

1. an assessment of the problems involved in orbital rendezvous,
2. an evaluation of intermediate vehicles (Saturn C-3, C-4, and C-5),
3. an evaluation of Nova-class vehicles,
4. an assessment of the future course of large solid-fuel rocket motor development,
5. an evaluation of the utility of the Titan III for NASA missions, and
6. an evaluation of the realism of the spacecraft development program (schedules, weights, performances).