This list of nuclear power systems in space includes 81 nuclear power systems that were flown to space, or at least launched in an attempt to reach space. Such used nuclear power systems include:
Systems never launched are not included here, see Nuclear power in space.
Initial total power is provided as either electrical power (We) or thermal power (Wt), depending on the intended application.
Nation | Mission | Launched | Fate / location | Technology | Nuclear fuel | Power (nominal) | Ref |
---|---|---|---|---|---|---|---|
USA | Transit-4A | 1961 | Earth orbit | RTG SNAP-3B | 238 Pu | 2.7 We | [1] |
USA | Transit-4B | 1961 | Earth orbit | RTG SNAP-3B | 238 Pu | 2.7 We | [1] |
USA | Transit 5BN-1 | 1963 | Earth orbit | RTG SNAP-9A | 238 Pu | 25.2 We | [1] |
USA | Transit 5BN-2 | 1963 | Earth orbit | RTG SNAP-9A | 238 Pu | 26.8 We | [1] |
USA | Transit 5BN-3 | 1964 | Failed to reach orbit, burned up in atmosphere. | RTG SNAP-9A | 238 Pu | 25 We | [2] |
USA | SNAPSHOT | 1965 | Low graveyard orbit in 1300 km height | fission reactor SNAP-10A | 235 U (uranium-zirconium hydride) | 500 We | [1] |
USA | Nimbus B (Nimbus-B1) | 1968-05-18 | Crashed at launch, radioactive material from RTG recovered from ocean and reused | RTG SNAP-19B (2) | 238 Pu | 56 We | [1] [3] |
USA | Nimbus 3 (Nimbus-B2) | 1969-04-14 | Earth re-entry 1972 | RTG SNAP-19B (2) | 238 Pu | 56 We | [1] |
USA | Nimbus IV | 1970 | Earth orbit | RTG SNAP-19 | [4] | ||
USA | Nimbus V | 1972 | Earth orbit | RTG SNAP-19 | [4] | ||
USA | Nimbus VI | 1975 | Earth orbit, damaged | RTG SNAP-19 | [4] | ||
USA | Nimbus VII | 1978 | Earth orbit, damaged | RTG SNAP-19 | [4] | ||
USA | Apollo 11 | 1969 | RHU (2) | 30 Wt | [1] | ||
USA | Apollo 12 ALSEP | 1969 | Lunar surface (Ocean of Storms) [5] | SNAP-27 | 238 Pu | 73.6 We | [1] |
USA | Apollo 13 ALSEP | 1970 | Earth re-entry (Pacific Ocean, Tonga Trench) | RTG SNAP-27 | 238 Pu | 73 We | [1] |
USA | Apollo 14 ALSEP | 1971 | Lunar surface (Fra Mauro) | RTG SNAP-27 | 238 Pu | 72.5 We | [1] |
USA | Apollo 15 ALSEP | 1971 | Lunar surface (Hadley–Apennine) | RTG SNAP-27 | 238 Pu | 74.7 We | [1] |
USA | Pioneer 10 | 1972 | Ejected from Solar System | RTG SNAP-19 (4) + RHU (12) | 238 Pu | 162.8 We + 12 Wt | [1] |
USA | Apollo 16 ALSEP | 1972 | Lunar surface (Descartes Highlands) | RTG SNAP-27 | 238 Pu | 70.9 We | [1] |
USA | TRAID-01-1X | 1972 | Earth orbit | RTG SNAP-19 | 238 Pu | 35.6 We | [1] |
USA | Apollo 17 ALSEP | 1972 | Lunar surface (Taurus–Littrow) | RTG SNAP-27 | 238 Pu | 75.4 We | [1] |
USA | Pioneer 11 | 1973 | Ejected from Solar System | RTG SNAP-19 (4) + RHU (12) | 238 Pu | 159.6 We + 12 Wt | [1] |
USA | Viking 1 | 1976 | Mars surface (Chryse Planitia) | lander modified RTG SNAP-19 (2) | 238 Pu | 84.6 We | [1] |
USA | Viking 2 | 1976 | Mars surface (Utopia Planitia) | lander modified RTG SNAP-19 (2) | 238 Pu | 86.2 We | [1] |
USA | LES-8 | 1976 | Near geostationary orbit | MHW-RTG (2) | 238 Pu | 307.4 We | [1] |
USA | LES-9 | 1976 | Near geostationary orbit | MHW-RTG (2) | 238 Pu | 308.4 We | [1] |
USA | Voyager 1 | 1977 | Ejected from Solar System | MHW-RTG (3) + RHU(9) | 238 Pu | 477.6 We + 9 Wt | [1] |
USA | Voyager 2 | 1977 | Ejected from Solar System | MHW-RTG (3) + RHU(9) | 238 Pu | 470.1 We + 9 Wt | [1] |
USA | Mars 2020/Perseverance | 2020 | Mars surface | MMRTG | 238 Pu | 110 We | [6] |
USA | Galileo | 1989 | Jupiter atmospheric entry | GPHS-RTG (2) | 576.8 We | [1] | |
USA | Ulysses | 1990 | Heliocentric orbit | GPHS-RTG | 283 We | [1] | |
USA | Cassini | 1997 | Burned-up in Saturn's Atmosphere | GPHS-RTG (3) | 238 Pu | 887 We | |
USA | New Horizons | 2006 | Pluto and beyond | GPHS-RTG (1) | 238 Pu | 249.6 We | |
USA | MSL/Curiosity rover | 2011 | Mars surface | MMRTG | 238 Pu | 113 We | |
Soviet Union | Kosmos 84 | 1965 | Earth orbit | Orion-1 RTG | 210 Po | [4] [7] | |
Soviet Union | Kosmos 90 | 1965 | Earth orbit | Orion-1 RTG | 210 Po | [4] [7] | |
Soviet Union | Kosmos 198 (RORSAT) | 1967-12-27 | Earth orbit | Fission reactor BES-5 ?? | 235 U | [4] [8] | |
Soviet Union | Kosmos 209 (RORSAT) | 1968-03-22 | Earth orbit | Fission reactor BES-5 ?? | 235 U | [4] [8] | |
Soviet Union | Kosmos 305 (Moon) | 1969-10-22 | Failed to leave Earth orbit towards the Moon, burned up in atmosphere 2 days after launch | ?? | ?? | ?? | [4] [9] [10] [11] |
Soviet Union | Kosmos 367 (RORSAT) | 1970-10-03 | Earth orbit, 579 mile altitude | Fission reactor BES-5 ?? | 235 U | 2 kWe | [4] [8] [12] |
Soviet Union | Kosmos 402 (RORSAT) | 1971 | Earth orbit | Fission reactor BES-5 ?? | 235 U | 2 kWe | [4] [8] |
Soviet Union | Kosmos 469 (RORSAT) | 1971 | High orbit | Fission reactor BES-5 (officially confirmed) | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 516 | 1972 | High orbited 1972 | Fission reactor BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | RORSAT | 1973 | Launch failure over Pacific Ocean, near Japan | Fission reactor BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 626 | 1973 | Earth orbit | Fission reactor BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 651 | 1974 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 654 | 1974 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 723 | 1975 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 724 | 1975 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 785 | 1975 | failed after reaching orbit | BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 860 | 1976 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 861 | 1976 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 952 | 1977 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 954 | 1977 | Exploded on re-entry 1978 (over Canada) | BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 1176 | 1980 | 11788/11971 Earth orbit 870–970 km | BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 1249 | 1981 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 1266 | 1981 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 1299 | 1981 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 1402 | 1982 | Earth re-entry 1983 (South Atlantic) | BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 1372 | 1982 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 1365 | 1982 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 1412 | 1982 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 1461 | 1983 | Earth orbit, exploded | BES-5 | 235 U | 2 kWe | [4] |
Soviet Union | Kosmos 1597 | 1984 | BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 1607 | 1984 | High orbited 1985 | BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 1670 | 1985 | High orbited 1985 | BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 1677 | 1985 | High orbited 1985 | BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 1736 | 1986 | High orbited 1986 | BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 1771 | 1986 | High orbited 1986 | BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 1900 | 1987 | Earth orbit, 454 mile altitude | BES-5 | 235 U | 2 kWe | [13] [12] |
Soviet Union | Kosmos 1860 | 1987 | Fission reactor BES-5 | 235 U | 2 kWe | [13] | |
Soviet Union | Kosmos 1932 | 1988 | Earth orbit 800–900 km | fission reactor BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 1682 | 1985 | High orbited 1986 | fission reactor BES-5 | 235 U | 2 kWe | [13] |
Soviet Union | Kosmos 1818 (RORSAT) | 1987 | Destroyed in high Earth orbit | fission reactor Topaz-I | 235 U | 5 kWe | [14] |
Soviet Union | Kosmos 1867 (RORSAT) | 1987 | Parked in high Earth orbit | fission reactor Topaz-I | 235 U | 5 kWe | [15] |
Soviet Union | Lunokhod 201 | 1969-02-19 | Rocket exploded at launch, radioactive material from RHU spread over Russia | RHU | 210 Po | [16] | |
Soviet Union | Lunokhod 1 | 1970 | Lunar surface | RHU | 210 Po | [16] | |
Soviet Union | Lunokhod 2 | 1973 | Lunar surface | RHU | 210 Po | [16] | |
Russia | Mars 96 | 1996 | Launch failure, entered Pacific Ocean | RHU (4) | 238 Pu | [16] | |
China | Chang'e 3 and Yutu | 2013 | Lunar surface | several RHU's, RTG (??) (some electricity provided by solar panels) | 238 Pu | [17] | |
India | Chandrayaan-3 | 2023 | Lunar orbit | RHU | 241Am | 2 Wt | [19] |
A nuclear electric rocket is a type of spacecraft propulsion system where thermal energy from a nuclear reactor is converted to electrical energy, which is used to drive an ion thruster or other electrical spacecraft propulsion technology. The nuclear electric rocket terminology is slightly inconsistent, as technically the "rocket" part of the propulsion system is non-nuclear and could also be driven by solar panels. This is in contrast with a nuclear thermal rocket, which directly uses reactor heat to add energy to a working fluid, which is then expelled out of a rocket nozzle.
Nuclear pulse propulsion or external pulsed plasma propulsion is a hypothetical method of spacecraft propulsion that uses nuclear explosions for thrust. It originated as Project Orion with support from DARPA, after a suggestion by Stanislaw Ulam in 1947. Newer designs using inertial confinement fusion have been the baseline for most later designs, including Project Daedalus and Project Longshot.
A radioisotope thermoelectric generator, sometimes referred to as a radioisotope power system (RPS), is a type of nuclear battery that uses an array of thermocouples to convert the heat released by the decay of a suitable radioactive material into electricity by the Seebeck effect. This type of generator has no moving parts. Because they don't need solar energy, RTGs are ideal for remote and harsh environments for extended periods of time, and because they have no moving parts, there is no risk of parts wearing out or malfunctioning.
Nuclear propulsion includes a wide variety of propulsion methods that use some form of nuclear reaction as their primary power source. The idea of using nuclear material for propulsion dates back to the beginning of the 20th century. In 1903 it was hypothesized that radioactive material, radium, might be a suitable fuel for engines to propel cars, planes, and boats. H. G. Wells picked up this idea in his 1914 fiction work The World Set Free. Many aircraft carriers and submarines currently use uranium fueled nuclear reactors that can provide propulsion for long periods without refueling. There are also applications in the space sector with nuclear thermal and nuclear electric engines which could be more efficient than conventional rocket engines.
A radioisotope rocket or radioisotope thermal rocket is a type of thermal rocket engine that uses the heat generated by the decay of radioactive elements to heat a working fluid, which is then exhausted through a rocket nozzle to produce thrust. They are similar in nature to nuclear thermal rockets such as NERVA, but are considerably simpler and often have no moving parts. Alternatively, radioisotopes may be used in a radioisotope electric rocket, in which energy from nuclear decay is used to generate the electricity used to power an electric propulsion system.
A radioisotope heater unit (RHU) is a small device that provides heat through radioactive decay. They are similar to tiny radioisotope thermoelectric generators (RTG) and normally provide about one watt of heat each, derived from the decay of a few grams of plutonium-238—although other radioactive isotopes could be used. The heat produced by these RHUs is given off continuously for several decades and, theoretically, for up to a century or more.
An atomic battery, nuclear battery, radioisotope battery or radioisotope generator is a device which uses energy from the decay of a radioactive isotope to generate electricity. Like nuclear reactors, they generate electricity from nuclear energy, but differ in that they do not use a chain reaction. Although commonly called batteries, they are technically not electrochemical and cannot be charged or recharged. They are very costly, but have an extremely long life and high energy density, and so they are typically used as power sources for equipment that must operate unattended for long periods of time, such as spacecraft, pacemakers, underwater systems and automated scientific stations in remote parts of the world.
SNAP-10A was a US experimental nuclear powered satellite launched into space in 1965 as part of the SNAPSHOT program. The test marked both the world's first operation of a nuclear reactor in orbit, and the first operation of an ion thruster system in orbit. It is the only fission reactor power system launched into space by the United States. The reactor stopped working after just 43 days due to a non-nuclear electrical component failure. The Systems Nuclear Auxiliary Power Program reactor was specifically developed for satellite use in the 1950s and early 1960s under the supervision of the U.S. Atomic Energy Commission.
Neptunium (93Np) is usually considered an artificial element, although trace quantities are found in nature, so a standard atomic weight cannot be given. Like all trace or artificial elements, it has no stable isotopes. The first isotope to be synthesized and identified was 239Np in 1940, produced by bombarding 238
U
with neutrons to produce 239
U
, which then underwent beta decay to 239
Np
.
Plutonium-238 is a radioactive isotope of plutonium that has a half-life of 87.7 years.
A Stirling radioisotope generator (SRG) is a type of radioisotope generator based on a Stirling engine powered by a large radioisotope heater unit. The hot end of the Stirling converter reaches high temperature and heated helium drives the piston, with heat being rejected at the cold end of the engine. A generator or alternator converts the motion into electricity. Given the very constrained supply of plutonium, the Stirling converter is notable for producing about four times as much electric power from the plutonium fuel as compared to a radioisotope thermoelectric generator (RTG).
The Systems Nuclear Auxiliary POWER (SNAP) program was a program of experimental radioisotope thermoelectric generators (RTGs) and space nuclear reactors flown during the 1960s by NASA.
The advanced Stirling radioisotope generator (ASRG) is a radioisotope power system first developed at NASA's Glenn Research Center. It uses a Stirling power conversion technology to convert radioactive-decay heat into electricity for use on spacecraft. The energy conversion process used by an ASRG is significantly more efficient than previous radioisotope systems, using one quarter of the plutonium-238 to produce the same amount of power.
GPHS-RTG or general-purpose heat source — radioisotope thermoelectric generator, is a specific design of the radioisotope thermoelectric generator (RTG) used on US space missions. The GPHS-RTG was used on Ulysses (1), Galileo (2), Cassini-Huygens (3), and New Horizons (1).
The multi-mission radioisotope thermoelectric generator (MMRTG) is a type of radioisotope thermoelectric generator (RTG) developed for NASA space missions such as the Mars Science Laboratory (MSL), under the jurisdiction of the United States Department of Energy's Office of Space and Defense Power Systems within the Office of Nuclear Energy. The MMRTG was developed by an industry team of Aerojet Rocketdyne and Teledyne Energy Systems.
Nuclear power in space is the use of nuclear power in outer space, typically either small fission systems or radioactive decay for electricity or heat. Another use is for scientific observation, as in a Mössbauer spectrometer. The most common type is a radioisotope thermoelectric generator, which has been used on many space probes and on crewed lunar missions. Small fission reactors for Earth observation satellites, such as the TOPAZ nuclear reactor, have also been flown. A radioisotope heater unit is powered by radioactive decay and can keep components from becoming too cold to function, potentially over a span of decades.
The Multihundred-Watt radioisotope thermoelectric generator is a type of US radioisotope thermoelectric generator (RTG) developed for the Voyager spacecraft, Voyager 1 and Voyager 2.
Silicon-germanium (SiGe) thermoelectrics have been used for converting heat into power in spacecraft designed for deep-space NASA missions since 1976. This material is used in the radioisotope thermoelectric generators (RTGs) that power Voyager 1, Voyager 2, Galileo, Ulysses, Cassini, and New Horizons spacecraft. SiGe thermoelectric material converts enough radiated heat into electrical power to fully meet the power demands of each spacecraft. The properties of the material and the remaining components of the RTG contribute towards the efficiency of this thermoelectric conversion.
Kilopower is an experimental project aimed at producing new nuclear reactors for space travel. The project started in October 2015, led by NASA and the DoE’s National Nuclear Security Administration (NNSA). As of 2017, the Kilopower reactors were intended to come in four sizes, able to produce from one to ten kilowatts of electrical power (1-10 kWe) continuously for twelve to fifteen years. The fission reactor uses uranium-235 to generate heat that is carried to the Stirling converters with passive sodium heat pipes. In 2018, positive test results for the Kilopower Reactor Using Stirling Technology (KRUSTY) demonstration reactor were announced.
Americium-241 is an isotope of americium. Like all isotopes of americium, it is radioactive, with a half-life of 432.2 years. 241
Am
is the most common isotope of americium as well as the most prevalent isotope of americium in nuclear waste. It is commonly found in ionization type smoke detectors and is a potential fuel for long-lifetime radioisotope thermoelectric generators (RTGs). Its common parent nuclides are β− from 241
Pu
, EC from 241
Cm
, and α from 245
Bk
. 241
Am
is fissile and the critical mass of a bare sphere is 57.6–75.6 kilograms (127.0–166.7 lb) and a sphere diameter of 19–21 centimetres (7.5–8.3 in). Americium-241 has a specific activity of 3.43 Ci/g (126.91 GBq/g). It is commonly found in the form of americium-241 dioxide. This isotope also has one meta state, 241m
Am
, with an excitation energy of 2.2 MeV (0.35 pJ) and a half-life of 1.23 μs. The presence of americium-241 in plutonium is determined by the original concentration of plutonium-241 and the sample age. Because of the low penetration of alpha radiation, americium-241 only poses a health risk when ingested or inhaled. Older samples of plutonium containing 241
Pu
contain a buildup of 241
Am
. A chemical removal of americium-241 from reworked plutonium may be required in some cases.