Atlas LV Media Gallery

First test version of Atlas with Centaur upper stage.

Manufacturer: Convair. Launches: 12. Failures: 4. Success Rate: 66.67%. First Launch Date: 1962-05-08. Last Launch Date: 1967-07-14. Launch data is: complete. Payload: 1,800 kg (3,900 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: Surveyor. Liftoff Thrust: 1,704.820 kN (383,259 lbf). Total Mass: 136,124 kg (300,102 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 33.00 m (108.00 ft).

Version with basic Centaur upper stage.

Payload: 1,700 kg (3,700 lb). to a: geosynchronous transfer orbit trajectory.

Version with Centaur D upper stage.

Payload: 1,700 kg (3,700 lb). to a: geosynchronous transfer orbit trajectory.

• Stage Number: 0. 1 x Stage: Atlas MA-3. Gross Mass: 3,174 kg (6,997 lb). Empty Mass: 3,174 kg (6,997 lb). Thrust (vac): 1,644.960 kN (369,802 lbf). Isp: 290 sec. Burn time: 120 sec. Isp(sl): 256 sec. Diameter: 4.90 m (16.00 ft). Span: 4.90 m (16.00 ft). Length: 0.00 m ( ft). Propellants: Lox/Kerosene. No Engines: 2. Engine: LR-89-5.

• Stage Number: 1. 1 x Stage: Atlas Centaur LV-3C. Gross Mass: 117,350 kg (258,710 lb). Empty Mass: 3,700 kg (8,100 lb). Thrust (vac): 363.218 kN (81,655 lbf). Isp: 309 sec. Burn time: 335 sec. Isp(sl): 215 sec. Diameter: 3.05 m (10.00 ft). Span: 4.90 m (16.00 ft). Length: 18.30 m (60.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: XLR-105-5.

• Stage Number: 2. 1 x Stage: Centaur C. Gross Mass: 15,600 kg (34,300 lb). Empty Mass: 1,996 kg (4,400 lb). Thrust (vac): 133.448 kN (30,000 lbf). Isp: 425 sec. Burn time: 430 sec. Isp(sl): 0 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.14 m (29.98 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-1.

1958 October 1 - Launch Vehicle: Atlas Centaur LV-3C.

• Centaur engine contract awarded. Nation: USA. Air Force awarded contract Pratt & Whitney for Centaur vehicle with hydrogen-burning chamber based on research of Lewis Research Center between 1953 and 1957. Centaur project later transferred to NASA. References: 17, 278.

• Centaur first contract. Nation: USA. Centaur project (Atlas upper stage) contracted for $7 million in its first year References: 4460.

• NASA National Space Vehicle Program Nation: USA. Program: Apollo. After consultation and discussion with DOD, NASA formulated a national space vehicle program. The central idea of the program was that a single launch vehicle should be developed for use in each series of future space missions. The launch vehicle would thus achieve a high degree of reliability, while the guidance and payload could be varied according to purpose of the mission. Four general-purpose launch vehicles were described: Vega, Centaur, Saturn, and Nova. The Nova booster stage would be powered by a cluster of four F-1 engines, the second stage by a single F-1, and the third stage would be the size of an intercontinental ballistic missile but would use liquid hydrogen as a fuel. This launch vehicle would be the first in a series that could transport a man to the lunar surface and return him safely to earth in a direct ascent mission. Four additional stages would be required in such a mission.References: 16.

• NASA Booster Development Plan for 60's Nation: USA. Program: Apollo. Class: Manned. NASA issues plan for development in next decade of Vega (later cancelled as too similar to Agena), Centaur, Saturn, and Nova launch vehicles. Juno V renamed Saturn I. References: 26, 27.

• Centaur tracking network test. Nation: USA. Under arrangements of the AACB (Aeronautics and Astronautics Coordinating Board), NASA will utilize existing NASA tracking stations for initial Centaur development vehicles and switch to the Advent network (which is to be planned, funded, and constructed by DOD) when Centaur is operational, perhaps as early as the fourth of 10 development launchings of Centaur.References: 17, 278.

• Liquid hydrogen tests. Nation: USA. NASA Aerobee-Hi successfully reached 96 miles above Wallops Station in test of behavior of liquid hydrogen in zero gravity for Lewis Research Center hydrogen propulsion development. References: 18.

• Centaur development milestones set. Nation: USA. Meeting of NASA and contractor personnel held at NASA headquarters to review Centaur development program. References: 18, 278.

• McDonnell studies of the redesigned Mercury spacecraft. Nation: USA. Program: Gemini. Spacecraft: Gemini. Walter F. Burke of McDonnell summarized the company's studies of the redesigned Mercury spacecraft for Space Task Group's senior staff. McDonnell had considered three configurations: (1) the minimum-change capsule, modified only to improve accessibility and handling, with an adapter added to carry such items as extra batteries; (2) a reconfigured capsule with an ejection seat installed and most of the equipment exterior to the pressure vessel on highly accessible pallets; and (3) a two-man capsule, similar to the reconfigured capsule except for the modification required for two rather than one-man operation. The capsule would be brought down on two Mercury-type main parachutes, the ejection seat serving as a redundant system. In evaluating the trajectory of the two-man capsule, McDonnell used Atlas Centaur booster performance data.

• Centaur operational contracts initiated. Nation: USA. NASA directed Marshall Space Flight Center to enter contract negotiations with contractors for procurement of five operational Atlas-Centaur vehicles. These launchings were planned to begin in second quarter of 1964. References: 18, 278.

• Mariner moved to Atlas-Agena due to Centaur delay. Nation: USA. Program: Mariner. Class: Planetary. Type: Venus. Spacecraft: Mariner 1-2. NASA announced that instrumented Venus probe to be launched next year would be launched by an Atlas-Agena B rather than a Centaur rocket as originally planned. References: 18, 278.

• STG discussed development of automatic checkout system for the entire NASA launch vehicle program Nation: USA. Program: Apollo. The MSFC-STG Advanced Program Coordination Board met at STG and discussed the question of the development of an automatic checkout system which would include the entire launch vehicle program from the Saturn C-1 through the Nova. It agreed that the Apollo contractor should be instructed to make the spacecraft electrical subsystems compatible with the Saturn complex.

  In further discussion, Paul J. DeFries of Marshall Space Flight Center MSFC presented a list of proposed guidelines for use in studying early manned lunar landing missions:

  • The crew should draw on its own resources only when absolutely necessary. Equipment and service personnel external to the spacecraft should be used as much as possible.
  • Early lunar expeditions would receive active external support only up to the time of the launch from earth orbit.
  • The crew would board the spacecraft only after it was checked out and ready for final countdown and launch.
  • The first Apollo crews should have an emergency shelter available on the moon which could afford several months of lift: support and protection.
  • The capability for clocking an orbital launch vehicle with a propulsion stage - the "connecting mode" - should be possible.
  • The capability of fueling an orbital launch vehicle should be made available - "fueling mode."
  • The capability of making repairs, replacements, or adjustments in orbit should be developed.
  • For repairs, replacements, and adjustments on the orbital launch vehicle in earth orbit, two support vehicles would be necessary. These would be a Saturn C-1 launch vehicle manned by Apollo technicians and an unmanned Atlas-Centaur launch vehicle carrying repair kits.
  • Development of docking, testing of components, and techniques for docking and training of man in orbital operations could be carried out by a space ferry loaded with a Mercury capsule.
  Some of the points discussed in connection with these suggestions were:
  • Orbital launch operations were just as complex, if not more complex, than earth-launched operations.
  • A question existed as to how complex the orbital launch facility could be and what its function should be.
  • There was a possibility that the crew could do most of the checkout and launch operations. Studies should be made to define the role of the crew versus the role of a proposed MSFC auxiliary checkout and maintenance crew.
  After the discussion on orbital launch operations, the Board agreed that contemporary technology was inadequate to support such operations. Both STG and MSFC would need to study and develop both refueling and connector techniques.References: 16.

• RL-10 flight rating complete. Nation: USA. NASA announced the completion of the preliminary flight rating test of the Nation's first liquid-hydrogen rocket engine. The engine, the RL-10, was designed and developed by Pratt and Whitney, of United Aircraft, for the Marshall Space Flight Center, and 20 captive firings were competed within 5 days under simulated space conditions, consistently producing 15,000 pounds of thrust. RL-10, previously known as XLR-115, was initiated in October 1958 and over 700 firings were conducted in its development.References: 18, 278.

• Research and development launch Nation: USA. Agency: NASA. Apogee: 6.00 km (3.70 mi). First Centaur flight (unsuccessful). References: 5, 126, 278, 1684.

• Atlas Centaur 2 Nation: USA. Payload: Centaur 2B. Mass: 4,620 kg (10,180 lb). Class: Planetary. Type: Lunar. Spacecraft: Surveyor. Agency: NASA LeR. Perigee: 469 km (291 mi). Apogee: 1,478 km (918 mi). Inclination: 30.40 deg. Period: 104.60 min. COSPAR: 1963-047A. USAF Sat Cat: 694. Launch vehicle test. Launch vehicle put dummy payload into geosynchronous transfer orbit. First successful Centaur (liquid hydrogen-fueled) flight. References: 1, 2, 5, 6, 278.

• Centaur AC-3 Nation: USA. Payload: Centaur 1C. Mass: 4,815 kg (10,615 lb). Agency: NASA. Apogee: 500 km (310 mi). COSPAR: F640630A. Decay Date: 1964-06-30. Centaur test. Launch vehicle was to have put payload into geosynchronous transfer orbit References: 5, 126, 278.

• Surveyor SD-1 Nation: USA. Payload: Surveyor SD-1. Mass: 2,944 kg (6,490 lb). Class: Planetary. Type: Lunar. Spacecraft: Surveyor. Agency: NASA/JPL. Perigee: 165 km (102 mi). Apogee: 178 km (110 mi). Inclination: 30.70 deg. Period: 87.80 min. COSPAR: 1964-082A. USAF Sat Cat: 951. Decay Date: 1964-12-12. Launch vehicle test. Centaur AC-4 put dummy Surveyor payload into geosynchronous transfer orbit References: 1, 2, 5, 6, 278.

• Surveyor SD-1 Nation: USA. Payload: Surveyor SD-1. Mass: 951 kg (2,096 lb). Spacecraft: Surveyor. Agency: NASA. COSPAR: F650302A. Decay Date: 1965-03-02. Launch vehicle test. Launch vehicle was to have put payload into geosynchronous transfer orbit References: 5, 126, 278.

• Surveyor; Atlas Centaur 6 Nation: USA. Payload: Surveyor-SD-2. Mass: 950 kg (2,090 lb). Class: Planetary. Type: Lunar. Spacecraft: Surveyor. Agency: NASA/JPL. COSPAR: 1965-064A. USAF Sat Cat: 1503. Centaur AC-6 launched dummy Surveyor payload into a barycentric / translunar orbit. References: 1, 2, 5, 6, 278.

• Surveyor Model Nation: USA. Payload: Surveyor SD-3. Mass: 784 kg (1,728 lb). Class: Planetary. Type: Lunar. Spacecraft: Surveyor. Agency: NASA/JPL. Perigee: 182 km (113 mi). Apogee: 336 km (208 mi). Inclination: 30.70 deg. Period: 89.70 min. COSPAR: 1966-030A. USAF Sat Cat: 2139. Decay Date: 1966-05-05. Launch vehicle test. Payload was dummy Surveyor spacecraft. References: 1, 2, 5, 6, 278.

• Surveyor 1 Nation: USA. Payload: Surveyor SC-1. Mass: 269 kg (593 lb). Class: Planetary. Type: Lunar. Spacecraft: Surveyor. Agency: NASA/JPL. COSPAR: 1966-045A. USAF Sat Cat: 2185. Decay Date: 1966-06-02. Surveyor 1 soft landed on the moon in the Ocean of Storms and began transmitting the first of more than 11,150 clear, detailed television pictures to Jet Propulsion Laboratory's Deep Space Facility, Goldstone, Calif. The landing sequence began 3,200 kilometers above the moon with the spacecraft traveling at a speed of 9,700 kilometers per hour. The spacecraft was successfully slowed to 5.6 kilometers per hour by the time it reached 4-meter altitude and then free-fell to the surface at 13 kilometers per hour. The landing was so precise that the three footpads touched the surface within 19 milliseconds of each other, and it confirmed that the lunar surface could support the LM. It was the first U.S. attempt to soft land on the moon.References: 1, 2, 5, 6, 16, 278.

• Surveyor 2 Nation: USA. Payload: Surveyor SC-2. Mass: 292 kg (643 lb). Class: Planetary. Type: Lunar. Spacecraft: Surveyor. Agency: NASA/JPL. COSPAR: 1966-084A. USAF Sat Cat: 2425. Decay Date: 1966-09-23. Soft lunar landing attempt failed. Surveyor II was launched from Cape Kennedy at 8:32 a.m. EDT. The Atlas-Centaur launch vehicle placed the spacecraft on a nearly perfect lunar intercept trajectory that would have missed the aim point by about 130 kilometers. Following injection, the spacecraft successfully accomplished all required sequences up to the midcourse thrust phase. This phase was not successful because of the failure of one of the three vernier engines to ignite, causing eventual loss of the mission. Contact with the spacecraft was lost at 5:35 a.m. EDT, September 22, and impact on the lunar surface was predicted at 11:18 p.m. on that day.References: 1, 2, 5, 6, 16, 278.

• Surveyor SD-4 Nation: USA. Payload: Surveyor SD-4. Mass: 951 kg (2,096 lb). Class: Planetary. Type: Lunar. Spacecraft: Surveyor. Agency: NASA/JPL. Perigee: 166 km (103 mi). Apogee: 406,200 km (252,400 mi). Inclination: 29.60 deg. Period: 15,912.00 min. COSPAR: 1966-095A. USAF Sat Cat: 2512. Decay Date: 1966-11-06. Launch vehicle test. Centaur D AC-9 put Surveyor spacecraft payload into geosynchronous transfer orbit References: 1, 2, 5, 6, 278.

• Surveyor 3 Nation: USA. Payload: Surveyor SC-3. Mass: 283 kg (623 lb). Class: Planetary. Type: Lunar. Spacecraft: Surveyor. Agency: NASA/JPL. COSPAR: 1967-035A. USAF Sat Cat: 2756. Decay Date: 1967-04-20. Soft landed on Moon; perrformed soil sample tests and imaged lunar surface. References: 1, 2, 5, 6, 278.

• Surveyor 4 Nation: USA. Payload: Surveyor SC-4. Mass: 283 kg (623 lb). Class: Planetary. Type: Lunar. Spacecraft: Surveyor. Agency: NASA/JPL. COSPAR: 1967-068A. USAF Sat Cat: 2875. Decay Date: 1967-07-17. Soft lunar landing attempt failed. References: 1, 2, 5, 6, 278.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Koelle, Heinz Hermann,, Handbook of Astronautical Engineering, McGraw-Hill,New York, 1961. The only such comprehensive handbook ever produced, and at the dawn of the space age.