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Priorities in Space Science Enabled by Nuclear Power and Propulsion Appendixes

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Priorities in Space Science Enabled by Nuclear Power and Propulsion A Past U.S. Space Nuclear Power and Propulsion Programs The United States has a long history of developing space nuclear power and propulsion programs. The most common systems have been the various types of radioisotope power systems used for outer planet spacecraft such as Voyager and Cassini (see Table 1.2 for details). However, many other technologies have been studied and occasionally progressed to advanced testing or even launch. ROVER AND NERVA (1955–1972) Starting in the mid-1950s, the United States initiated a program to develop nuclear propulsion for spacecraft. The basic technology involved passing hydrogen through a very high temperature nuclear reactor, where it expanded and blasted out of the reactor at high velocity. Eventually NASA and the Atomic Energy Commission jointly ran two main programs, a reactor technology development program named Rover and a program to develop a flight-capable nuclear rocket engine known as NERVA. Under the Rover program, nuclear reactors were built at the Los Alamos National Laboratory’s Pajarito Site and tested at very low power, and then shipped to the Nevada Test Site for higher-power tests. Laboratory work also included developing and testing the fuel elements that powered the reactors. Phase one of Project Rover was called Kiwi and entailed building and testing eight reactors between 1959 and 1964. Phase two, called Phoebus, involved advanced nuclear reactors. NERVA began in 1961 and by the mid-1960s progressed to hardware development tests in the Nevada desert. The NERVA engine utilized a hot-bleed cycle in which a small amount of hydrogen gas is diverted from the thrust nozzle to drive the turbine that pumps fuel into the engine. NERVA reached an integrated system component demonstration readiness level. At various points NASA planned on using NERVA as a rocket upper stage, a space ferry for lunar missions, and a propulsion stage for human missions to Mars. However, after Apollo, none of these projects was approved, and NERVA therefore had no dedicated mission. Congress showed greater support for NERVA than did the White House, but the program was eventually canceled by 1972. ORION (1955–1965) The nuclear pulse drive was conceived by H-bomb designers Stanislaw Ulam and Cornelius Everett at Los Alamos in 1955 and sponsored primarily as a study project by the Atomic Energy Commission and then the U.S. Air Force under the name Project Orion.

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Priorities in Space Science Enabled by Nuclear Power and Propulsion Orion adapted nuclear explosives for space use: nuclear bombs would be ejected aft of a spacecraft and exploded some distance away. Propellant (water or wax) surrounding the bombs would be transformed into high-energy plasma and bounce off a pusher plate at the rear of the rocket and push it forward. Shock absorbers would reduce the substantial vibration caused by detonating nuclear weapons behind the craft approximately once every second. Although the plasma from the explosion would have a temperature of 80,000 K, the impulse would be brief and only a tiny layer of the ablative pusher plate would sublimate after each explosion. The vehicle would be ground launched from a remote location. The Orion design theoretically allowed vast payloads to be hurled to the planets. A typical design had a payload of hundreds of tons, meaning no complex environmental recycling systems or lightweight structures or equipment would be needed. The pusher plate was typically about one-third of the weight of the craft. The project was transferred to the Air Force in 1957 and produced small-scale demonstration tests involving conventional explosives detonated under a model suspended from a crane. The 1963 Nuclear Test Ban Treaty banned atmospheric nuclear tests, essentially killing the program. Funding was eliminated entirely in 1965. Even Orion’s designers had acknowledged that it was a difficult project with a limited chance of success. SYSTEMS FOR NUCLEAR AUXILIARY POWER REACTOR (1959–1971) The Air Force’s Project RAND first proposed using nuclear reactors to power satellites in 1946. At the time there was no other way to provide sufficient power to an orbiting satellite. The Air Force funded low-level study efforts of space nuclear reactors over the next decade, but the eventual development of solar cells made nuclear reactors unnecessary. By the late 1950s the Atomic Energy Commission began the Systems for Nuclear Auxiliary Power (SNAP) program to develop fission reactors and radioisotope power systems for both terrestrial and space use. Radioisotope and reactor programs were given odd- and even-number designations, respectively. In 1965 the Air Force launched the SNAP-10A reactor into orbit. It operated for 43 days, producing 500 W of power until the failure of a voltage regulator caused it to shut down. The SNAP-10A reactor was a small zirconium hydride (ZrH) thermal reactor fueled by uranium-235. RADIOISOTOPE POWER SYSTEMS (1961–PRESENT) Radioisotope power systems (RPSs) convert heat generated by the natural decay of radioisotope fuel (typically plutonium-238 in the United States) into electricity through thermoelectric coupling. The first two RPS demonstration systems (called SNAP-3) were flown in 1961 and generated 3 W of power. Later ones were flown on several Earth-orbiting spacecraft. RPSs were used on Apollo 12, 14, 15, 16, and 17 to supply power to the Apollo lunar surface experiment packages. They were also used to provide primary power to Viking 1 and 2 (SNAP-19, 85 We total), Pioneer 10 and 11 (SNAP-19, 165 We total), Voyager 1 and 2 (each RPS provided 157 We), Galileo (300 We total, along with 120 lightweight radioisotope heater units), Ulysses (same as Galileo), and Cassini (three RTGs delivering 870 We, along with 117 lightweight radioisotope heater units). Many other systems, including all Mars rovers, have used lightweight radioisotope heater units to maintain appropriate temperatures for system electronics. Table A.1 gives a more complete list. These systems have been successfully deployed. SP-100 (1978–1995) In 1983, a triagency group (National Aeronautics and Space Administration, Department of Defense, and Department of Energy) began development of a 100-kilowatt-electric-class space nuclear reactor called the SP-100. The SP-100 was designed with a 2-MWt fast reactor unit and thermoelectric system delivering 100 kWe for a 7-year period. This reactor was intended to support a wide variety of deep-space exploration needs, defense applications, and planetary outpost power requirements. Because of high costs, schedule delays, and changing national space mission priorities, the SP-100 program was suspended in the early 1990s and later canceled.

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Priorities in Space Science Enabled by Nuclear Power and Propulsion TABLE A.1 Use of Radioisotope Power Systems on Spacecraft, 1961 to 2006 Power Source Spacecraft Mission Type Launch Date Status SNAP-3B7 Transit 4A Navigational 6-29-61 RPS operated for 15 years. Satellite now shut down but operational. SNAP-3B8 Transit 4B Navigational 11-15-61 RPS operated for 9 years. Satellite operated periodically after 1962 high-altitude test. Last reported signal in 1971. SNAP-9A Transit 5-BN-1 Navigational 9-28-63 RPS operated as planned. Non-RPS electrical problems on satellite caused satellite to fall after 9 months. SNAP-9A Transit 5-BN-2 Navigational 12-5-63 RPS operated for over 6 years. Satellite lost ability to navigate after 1.5 years. SNAP-9A Transit 5-BN-3 Navigational 4-21-64 Mission was aborted because of launch vehicle failure. RPS burned up on re-entry as designed. SNAP-19B2 Nimbus-B-1 Meteorological 5-18-68 Mission was aborted because of range safety destruct. RPS heat sources were recovered and recycled. SNAP-19B3 Nimbus III Meteorological 4-14-69 RPSs operated for over 2.5 years. RHU Apollo 11 Lunar Surface 7-14-69 Radioisotope heater units for seismic experimental package. Station was shut down 8-3-69. SNAP-27 Apollo 12 Lunar Surface 11-14-69 RPS operated for about 8 years until station was shut down. SNAP-27 Apollo 13 Lunar Surface 4-11-70 Mission aborted on the way to the Moon. RPS reentered Earth’s atmosphere and landed in South Pacific Ocean. No radiation was released. SNAP-27 Apollo 14 Lunar Surface 1-31-71 RPS operated for over 6.5 years until station was shut down. SNAP-27 Apollo 15 Lunar Surface 7-26-71 RPS operated for over 6 years until station was shut down. SNAP-19 Pioneer 10 Planetary 3-2-72 RPSs still operating. Spacecraft successfully operated to Jupiter and is now beyond orbit of Pluto. SNAP-27 Apollo 16 Lunar Surface 4-16-72 RPS operated for about 5.5 years until station was shut down. RPS “Transit” (Triad-01-1x) Navigational 9-2-72 Power system still operating. SNAP-27 Apollo 17 Lunar Surface 12-7-72 RPS operated for almost 5 years until station was shut down. SNAP-19 Pioneer 11 Planetary 4-5-73 RPSs still operating. Spacecraft successfully operated to Jupiter, Saturn, and beyond. SNAP-19 Viking 1 Mars Surface 8-20-75 RPSs operated for over 6 years until lander was shut down. SNAP-19 Viking 2 Mars Surface 9-9-75 RPSs operated for over 4 years until relay link was lost. MHW-RTG LES 8 Communications 3-14-76 RPSs still operating. MHW-RTG LES 9 Communications 3-14-76 RPSs still operating. MHW-RTG Voyager 2 Planetary 8-20-77 RPSs still operating. Spacecraft successfully operated to Jupiter, Saturn, Uranus, Neptune, and beyond. MHW-RTG Voyager 1 Planetary 9-5-77 RPSs still operating. Spacecraft successfully operated to Jupiter, Saturn, and beyond. GPHS-RTG and LWRHU Galileo Planetary 10-8-89 RPSs operated through 9-17-03, when the spacecraft completed its mission. GPHS-RTG Ulysses Planetary/Solar 10-6-90 RPS still operating. Spacecraft en route to solar polar flyby. LWRHU Mars Pathfinder Mars Surface 12-4-96 LWRHU provided essential heat to Sojourner electronics for 84 days. GPHS-RTG and LWRHU Cassini Planetary 10-15-97 RPS still operating. Cassini entered orbit about Saturn in July 2004. LWRHU Mars Exploration Rovers Mars Surface 6-25-03 and LWRHU provide essential heat to electronics. 7-5-03 GPHS-RTG New Horizons Planetary 1-19-06 RPS operating. Spacecraft en route to Pluto. NOTE: An RPS is a generic name for a family of different technologies, including the RHU, RTG, MHW-RTG, and others. SNAP, Systems for Nuclear Auxiliary Power program; RPS, radioisotope power system; RTG, radioisotope thermoelectric generator; RHU, radioisotope heater unit; MHW-RTG, multi-hundred-watt RTG; GPHS-RTG, general-purpose heat source RTG; LWRHU, lightweight radioisotope heater unit.

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Priorities in Space Science Enabled by Nuclear Power and Propulsion TIMBERWIND (1987–1992) The Timberwind space nuclear thermal propulsion program was initiated by the Strategic Defense Initiative Organization in November 1987. Timberwind was a highly classified program to develop technology for a very high acceleration nuclear-powered rocket to launch missile interceptors into space. The project was transferred to the Air Force in 1991 and terminated in 1992, at which point some of the material was declassified. The Project Timberwind concept was based on a particle-bed reactor using tiny uranium carbide pellets as fuel to heat hydrogen propellant. The exhaust would have been highly radioactive. Preliminary designs had been selected but no prototype components had been tested before the program was canceled. No system was ever launched. TOPAZ-2 (1980s–1990s) Launching dozens of nuclear reactors into space during the 1970s and 1980s, the Soviet Union had a far more active space nuclear power program than did the United States. Although full details remain inaccessible, the Soviet Union is known to have had several separate space nuclear reactor programs under development in the late 1980s. One of these projects, mistakenly labeled “Topaz-2” in the United States but actually known as “Enisey,” was purchased by the U.S. Ballistic Missile Defense Organization in the early 1990s. (Two Soviet nuclear reactors known as Topaz were flown in orbit in the later 1980s but were an entirely different design.) Six Topaz-2 reactors and supporting equipment were flown from Russia to the United States, where several of the reactors were extensively ground tested by a joint team of U.S., British, French, and Russian engineers. The reactors’ unique design allowed them to be tested without nuclear fuel. Topaz utilized a thermionic design for directly converting heat energy into electricity without using a circulating heat transfer fluid or turbine. Although the test program was considered highly successful and the United States retained several flight-capable reactors, no plans were pursued to actually use the equipment in any flight programs. BIBLIOGRAPHY Aftergood, Steven, “Background on Space Nuclear Power,” Science & Global Security 1(1–2): 93–108, 1989. Department of Defense Inspector General Audit Report, The Timber Wind Special Access Program, Report Number 93-033, December 16, 1992. See <> last accessed February 2, 2006. Dewar, James A., To the End of the Solar System: The Story of the Nuclear Rocket, University Press of Kentucky, Lexington, Ky., 2003. Dyson, George, Project Orion: The True Story of the Atomic Spaceship, Owl Books, 2003. General Accounting Office, Space Nuclear Propulsion: History, Cost, and Status of Programs, T-NSIAD-93-2. See <>. General Accounting Office, The SP-100 Nuclear Reactor Program: Should It Be Continued?, T-NSIAD-92-15. See <>. General Accounting Office, TOPAZ II Space Nuclear Power Program: Management, Funding, and Contracting Problems, OSI-98-3R. See <>. Mondt, Jack F., “SP-100 Space Reactor Power System for Lunar, Mars and Robotic Exploration,” IAF 92-0563, 43rd Congress of the International Astronautical Federation, August 28–September 5, 1992. National Research Council, Assessment of the Topaz International Program, Aeronautics and Space Engineering Board, June 27, 1996. National Research Council, Thermionics Quo Vadis? An Assessment of the DTRA’s Advanced Thermionics Research and Development Program, National Academy Press, Washington, D.C., 2001.