View source for Radioisotope thermoelectric generator

[[Image:Cutdrawing of an GPHS-RTG.jpg|thumb|300px|Diagram of an RTG used on the [[Cassini probe]]]]

A '''radioisotope thermoelectric generator''' ('''RTG''', '''RITEG''') is a [[nuclear]] [[electrical generator]] that obtains its power from [[radioactive decay]]. In such a device, the [[heat]] released by the decay of a suitable [[radioactivity|radioactive]] material is converted into [[electricity]] by the [[Seebeck effect]] using an array of [[thermocouple]]s.

RTGs can be considered as a type of [[battery (electricity)|battery]] and have been used as power sources in [[satellite]]s, [[space probe]]s and unmanned remote facilities, such as a series of lighthouses built by the former Soviet Union inside the Arctic Circle. RTGs are usually the most desirable power source for unmanned or unmaintained situations needing a few hundred watts or less of power for durations too long for [[fuel cell]]s, batteries, or generators to provide economically, and in places where [[solar cell]]s are not viable.

== History ==

[[Image:Radioisotope thermoelectric generator plutonium pellet.jpg|thumb|300px|Image of a mostly thermally isolated plutonium RTG pellet glowing [[incandescence|red hot]].]]

The first RTG launched in space by the United States was SNAP 3 in 1961 aboard the Navy Transit 4A spacecraft. One of the first terrestrial uses of RTGs was in 1966 by the US Navy at the uninhabited [[Fairway Rock|Fairway Rock Island]] in Alaska, where it remained in use until its removal in 1995.

A common application of RTGs is as power sources on spacecraft. [[Systems for Nuclear Auxiliary Power]] (SNAP) units were used especially for probes that travel far enough from the Sun that [[Photovoltaic module|solar panel]]s are no longer viable. As such they are used with [[Pioneer 10]], [[Pioneer 11]], [[Voyager 1]], [[Voyager 2]], [[Galileo probe|Galileo]], [[Ulysses probe|Ulysses]], [[Cassini-Huygens|Cassini]] and [[New Horizons]]. In addition, RTGs were used to power the two [[Viking program|Viking]] landers and for the scientific experiments left on the Moon by the crews of [[Apollo program|Apollo]] [[Apollo 12|12]] through [[Apollo 17|17]] (SNAP 27s). Because [[Apollo_13#Spacecraft location|Apollo 13]] was aborted, its RTG now rests in the [[Pacific Ocean|South Pacific ocean]], in the vicinity of the [[Tonga Trench]]. RTGs were also used for the [[Nimbus program|Nimbus]], [[Transit (satellite)|Transit]] and [[Lincoln Experimental Satellite|LES]] satellites.  By comparison, only a few space vehicles have been launched using full-fledged [[nuclear reactor]]s: the Soviet [[RORSAT]] series and the American [[SNAP-10A]].

In addition to spacecraft, the [[Soviet Union]] constructed many unmanned [[lighthouse]]s and navigation beacons powered by RTGs<ref>[http://www.bellona.no/en/international/russia/navy/northern_fleet/incidents/37598.html Bellona report on Russian RTGs]</ref>. Powered by [[Strontium-90|<sup>90</sup>Sr]], they are very reliable and provide a steady source of power. However, critics argue that they could cause environmental and security problems, as leakage or theft of the radioactive material could pass unnoticed for years (or possibly forever: some of these lighthouses cannot be found because of poor record keeping). There has even been an instance where the radioactive compartments were opened by a thief<ref>[http://www.bellona.no/en/international/russia/navy/northern_fleet/incidents/37598.html ibid. (See Reference 41 in the report.)]</ref>. There was also the case of three woodcutters in the nation of [[Georgia (country)|Georgia]] who came across one of these units and slept close to it as a heat source during a cold night.  They were later hospitalized with severe radiation burns.<ref>{{citation |title=Nuclear Free Texas |publisher=[[Dallas Peace Center]] |url=http://dallaspeacecenter.org/Nuclear/Civilian |accessdate=2009-05-09}}</ref> The unit was eventually recovered and isolated.<ref>{{citation |title=IAEA Bulletin Volume 48, No.1 - Remote Control: Decommissioning RTGs | publisher=Malgorzata K. Sneve | url=http://www.iaea.org/Publications/Magazines/Bulletin/Bull481/pdfs/rtg.pdf|accessdate=2009-07-11}}</ref>

There are approximately 1,000 such RTGs in Russia. All of them have long exhausted their 10-year engineered life spans.  They are likely no longer functional, and may be in need of dismantling. Some of them have become the prey of metal hunters, who strip the RTGs' metal casings, regardless of the risk of radioactive contamination.<ref>{{citation |title=Report by Minister of Atomic Energy Alexander Rumyantsev at the IAEA conference "Security of Radioactive Sources," Vienna, Austria. March 11th 2003 (Internet Archive copy)| url=http://web.archive.org/web/20030806043406/http://www.iaea.org/worldatom/Press/Focus/RadSources/statement_rus.pdf| accessdate=2009-10-10}}</ref>

RTGs are also utilized by the [[United States Air Force]] to power remote sensing stations for Top-ROCC and Save-Igloo radar systems predominantly located in [[Alaska]].<ref>[http://www10.antenna.nl/wise/379-80/3724.html Alaska fire threatens air force nukes], [[World Information Service on Energy|WISE]]</ref>

In the past, small "plutonium cells" (very small <sup>238</sup>Pu-powered RTGs) were used in implanted [[Artificial pacemaker|heart pacemakers]] to ensure a very long "battery life". As of 2004 about 90 were still in use.  If the wearer dies and the generator is not removed before cremation the device will be subject to great heat. It is unlikely however, if the plutonium is in the form of the dioxide, that contamination will occur. Note that plutonium 238 is more able to disperse than plutonium 239, but the dioxide is an air stable solid which is normally [[Sintering|sintered]] in air at a temperature much higher than that used in the [[cremation]] of human remains (although they are designed to survive cremation).

Although not strictly RTGs, similar units called [[radioisotope heater units]] are also used by various spacecraft including the Russian [[Lunokhod]] moon rover (using a Polonium 210 heat generator), and the [[Mars Exploration Rovers]], [[Galileo (spacecraft)|Galileo]] and [[Cassini-Huygens|Cassini]].  These devices use small samples of radioactive material to produce heat directly, instead of electricity.

== Design ==

The design of an RTG is simple by the standards of [[nuclear technology]]: the main component is a sturdy container of a radioactive material (the fuel). [[Thermocouple]]s are placed in the walls of the container, with the outer end of each thermocouple connected to a [[heat sink]]. Radioactive decay of the fuel produces heat which flows through the thermocouples to the heat sink, generating electricity in the process.

A thermocouple is a [[thermoelectricity|thermoelectric]] device that converts thermal [[energy]] directly into electrical energy using the [[Peltier-Seebeck effect|Seebeck effect]]. It is made of two kinds of metal (or semiconductors) that can both conduct electricity. They are connected to each other in a closed loop. If the two junctions are at different [[temperature]]s, an electric current will flow in the loop.

== Fuels ==
[[Image:RTG radiation measurement.jpg|thumb|right|300px|Inspection of [[Cassini-Huygens|Cassini spacecraft]] RTGs before launch]]
[[Image:New Horizons 1.jpg|thumb| 300px|''[[New Horizons]]'' in [http://maps.google.com/maps?q=28.5100,+-80.6475+(Payload+Hazardous+Servicing+Facility)&t=k&iwloc=A&hl=en assembly hall] ]]

===Criteria===
The radioactive material used in RTGs must have several characteristics:

*It should produce high energy radiation. Energy release per decay is proportional to power production per [[mole]]. Alpha decays in general release about 10 times as much energy as the Beta decay of Strontium-90 or Caesium-137.
*Radiation must be of a type easily absorbed and transferred into thermal radiation, preferably [[Alpha particle|alpha radiation]]. The [[Beta particle|Beta radiation]] can give off considerable amounts of [[X-rays|Gamma/X-ray radiation]] through [[bremsstrahlung]] secondary radiation production, thus requiring heavy shielding. Isotopes must not produce significant amounts of gamma, [[neutron radiation]] or penetrating radiation in general through other [[decay mode]]s or [[decay chain]] products.
*The [[half-life]] must be long enough that it will release energy at a relatively continuous rate for a reasonable amount of time. The amount of energy released per time ([[Power (physics)|Power]]) of a given quantity is inversely proportional to half-life. Twice the half-life will result in half the power per [[mol]]. Typical half-lives for [[radioisotopes]] used in RTGs are therefore several decades, although [[isotopes]] with shorter half-lives could be used for specialized applications.
*For spaceflight use, the fuel must produce a large amount of power per [[mass]] and [[volume]] ([[density]]).  Density and weight are not as important for terrestrial use, unless there are size restrictions. <br />The [[decay energy]] can be calculated if the energy of radioactive radiation or the mass loss before and after radioactive decay is known.

=== Selection of isotopes ===
The first two criteria limit the number of possible fuels to fewer than 30 atomic isotopes within the entire [[table of nuclides]]. [[Plutonium-238]], [[Curium|Curium-244]] and [[Strontium-90]] are the most often cited candidate isotopes, but other isotopes such as [[Polonium-210]], [[Promethium-147]], [[Caesium-137]], [[Cerium]]-144, [[Ruthenium-106]], [[Cobalt-60]], [[Curium]]-242 and [[Thulium]] isotopes have also been studied.

=== <sup>238</sup>Pu, <sup>90</sup>Sr ===
[[Plutonium-238]] has the lowest shielding requirements and longest half-life. Only three candidate isotopes meet the last criterion (not all are listed above) and need less than 25&nbsp;mm of [[lead]] shielding to keep radiation. <sup>238</sup>Pu (the best of these three) needs less than 2.5&nbsp;mm, and in many cases no shielding is needed in a <sup>238</sup>Pu RTG, as the casing itself is adequate.

<sup>238</sup>Pu has become the most widely used fuel for RTGs, in the form of [[plutonium(IV) oxide]] (PuO<sub>2</sub>). <sup>238</sup>Pu has a half-life of 87.7 years, reasonable power density and exceptionally low gamma and neutron radiation levels.
Some Russian terrestrial RTGs have used [[Strontium-90]]; this isotope has a shorter half-life, much lower power density and produces gamma radiation, but is cheaper.

=== <sup>210</sup>Po ===
Some prototype RTGs, first built in 1958 by USA Atomic Energy Commission, have used [[polonium-210]]. This isotope provides phenomenal power density due to its high [[Radioactive_decay#Radioactive_decay_rates|radioactive activity]], but has limited use because of its very short half-life of 138 days, again due to its high activity. A kilogram  of pure <sup>210</sup>Po in the form of a cube would be about 48&nbsp;mm (about 2&nbsp;inches) on a side and emit about [[Decay energy|140kW]]. The heat of fusion is about 60kJ/kg, the heat of evaporation about 10 times larger. If there is no efficient cooling, the self heating power is sufficient for melting then partly vaporizing itself.

===<sup>242</sup>Cm, <sup>244</sup>Cm, <sup>241</sup>Am ===
[[Curium-242]] and curium-244 have also been studied well, but require heavy shielding from gamma and neutron radiation produced from [[spontaneous fission]].

[[Americium-241]] is a potential candidate isotope with a longer half-life than <sup>238</sup>Pu: <sup>241</sup>Am has a half-life of 432 years and could hypothetically power a device for centuries. However, the power density of <sup>241</sup>Am is only 1/4 that of <sup>238</sup>Pu, and <sup>241</sup>Am produces more penetrating radiation through decay chain products than <sup>238</sup>Pu and needs about 18&nbsp;mm worth of lead shielding. Even so, its shielding requirements in an RTG are the second lowest of all possible isotopes:  only <sup>238</sup>Pu requires less.

==Life span==
[[Image:Soviet RTG.jpg|thumb| 300px|right|Soviet RTGs in dilapidated and vandalized condition, powered by Strontium-90 [[Strontium-90|<sup>90</sup>Sr]].]]

Most RTGs use <sup>238</sup>Pu which decays with a half-life of 87.7 years. RTGs using this material will therefore diminish in power output by <math>1-{0.5}^{1/87.7}</math> or 0.787% of their capacity per year. 23 years after production, such an RTG will have decreased in power by <math>1-0.5^{23/87.7}</math> or 16.6%, i.e. providing 83.4% of its initial output. Thus, with a starting capacity of 470 W, after 23 years it would have a capacity of 0.834 * 470 W = 392 W.  However, the bi-metallic thermocouples used to convert [[thermal energy]] into [[electrical energy]] degrade as well; at the beginning of 2001, the power generated by the Voyager RTGs had dropped to 315 W for Voyager 1 and to 319 W for Voyager 2. Therefore in early 2001, the thermocouples were working at about 80% of their original capacity.

This life span was of particular importance during the [[Galileo (spacecraft)|Galileo]] mission. Originally intended to launch in 1986, it was delayed by the [[Space Shuttle Challenger]] [[STS-51L|accident]]. Due to this unforeseen event the probe had to sit in storage for 4 years before launching in 1989. Subsequently, its RTGs had decayed somewhat, necessitating replanning the power budget for the mission.

== Efficiency ==

RTGs use thermoelectric couples or "[[thermocouples]]" to convert heat from the radioactive material into electricity.  Thermocouples, though very reliable and long-lasting, are very inefficient; efficiencies above 10% have never been achieved and most RTGs have efficiencies between 3-7%. Thermoelectric materials in space missions to date have included silicon germanium alloys, lead telluride and tellurides of antimony, germanium and silver (TAGS). Studies have been done on improving efficiency by using other technologies to generate electricity from heat. Achieving higher efficiency would mean less radioactive fuel is needed to produce the same amount of power, and therefore a lighter overall weight for the generator.  This is a critically important factor in spaceflight launch cost considerations.

A [[thermionic converter]] -- an energy conversion device which relies on the principle of [[thermionic]] emission—can achieve efficiencies between 10-20%, but requires higher temperatures than those at which standard RTGs run. Some prototype <sup>210</sup>Po RTGs have used thermionics, and potentially other extremely radioactive isotopes could also provide power by this means, but short half-lives make these infeasible. Several space-bound nuclear reactors have used thermionics, but nuclear reactors are usually too heavy to use on most space probes.

[[Thermophotovoltaic cell]]s work by the same principles as a [[photovoltaic cell]], except that they convert [[infrared]] light  emitted by a hot surface rather than visible light into electricity. Thermophotovoltaic cells have an efficiency slightly higher than thermocouples and can be overlaid on top of thermocouples, potentially doubling efficiency.  Systems with radioisotope generators simulated by electric heaters have demonstrated efficiencies of 20%[http://gltrs.grc.nasa.gov/reports/2005/TM-2005-213980.pdf], but have not been tested with actual radioisotopes.  Some theoretical thermophotovoltaic cell designs have efficiencies up to 30%, but these have yet to be built or confirmed. Thermophotovoltaic cells and silicon thermocouples degrade faster than thermocouples, especially in the presence of ionizing radiation.

Dynamic generators can provide power at more than 4 times the conversion efficiency of RTGs.  NASA and DOE have been developing a next-generation radioisotope-fueled power source called the [[Stirling Radioisotope Generator]] (SRG) that uses free-piston [[Stirling engine]]s coupled to linear alternators to convert heat to electricity. SRG prototypes demonstrated an average efficiency of 23%. Greater efficiency can be achieved by increasing the temperature ratio between the hot and cold ends of the generator.  The use of non-contacting moving parts, non-degrading [[Flexure bearing|flexural bearings]], and a lubrication-free and hermetically sealed environment have, in test units, demonstrated no appreciable degradation over years of operation. Experimental results demonstrate that an SRG could continue running for decades without maintenance. Vibration can be eliminated as a concern by implementation of dynamic balancing or use of dual-opposed piston movement. Potential applications of a Stirling radioisotope power system include exploration and science missions to deep-space, Mars, and the Moon.

== Safety ==
[[Image:RTGmodule.png|thumb|right|350px|Diagram of a stack of [[General Purpose Heat Source|general purpose heat source]] modules as used in RTGs]]

===Radioactive contamination===
RTGs may pose a risk of [[radioactive contamination]]: if the container holding the fuel leaks, the radioactive material may contaminate the environment.

For spacecraft, the main concern is that if an accident were to occur during launch or a subsequent passage of a spacecraft close to Earth, harmful material could be released into the atmosphere; and their use in spacecraft and elsewhere has attracted controversy.<ref>[http://www.cnn.com/TECH/space/9908/16/cassini.flyby/ Nuclear-powered NASA craft to zoom by Earth on Tuesday], CNN news report, 16 August 1999</ref><ref>[http://www.mtexpress.com/index2.php?issue_date=07-22-2005&ID=2005104284 Valley says pee-eww to plutonium plan], Idaho Mountain Express and Guide, 22 July 2005</ref>

However, this event is not considered likely with current RTG cask designs. For instance, the environmental impact study for the Cassini-Huygens probe launched in 1997 estimated the probability of contamination accidents at various stages in the mission. The probability of an accident occurring which caused radioactive release from one or more of its 3 RTGs (or from its 129 [[radioisotope heater unit]]s) during the first 3.5 minutes following launch was estimated at 1 in 1,400; the chances of a release later in the ascent into orbit were 1 in 476; after that the likelihood of an accidental release fell off sharply to less than 1 in a million.<ref>[http://saturn.jpl.nasa.gov/spacecraft/safety/fseis4.pdf Cassini Final Supplemental Environmental Impact Statement], Chapter 4, NASA, September 1997 (Links to other chapters and associated documents can be found at [http://saturn.jpl.nasa.gov/spacecraft/safety-eis.cfm])</ref> If an accident which had the potential to cause contamination occurred during the launch phases (such as the spacecraft failing to reach orbit), the probability of contamination actually being caused by the RTGs was estimated at about 1 in 10.<ref>[http://saturn.jpl.nasa.gov/spacecraft/safety/fseisd.pdf Cassini Final Supplemental Environmental Impact Statement], Appendix D, Summary of tables of safety analysis results, Table D-1 on page D-4, see conditional  probability column for GPHS-RTG</ref> In any event, the launch was successful and Cassini-Huygens reached [[Saturn]].

The [[plutonium 238]] used in these RTGs has a [[half-life]] of 87.74 years, in contrast to the 24,110 year half-life of [[plutonium 239]] used in [[nuclear weapons]] and [[Nuclear reactor|reactors]]. A consequence of the shorter half life is that plutonium 238 is about 275 times more radioactive than plutonium 239 (i.e. 17.3 [[Curie|Ci]]/[[gram|g]] compared to 0.063 Ci/g<ref>[http://www.ieer.org/fctsheet/pu-props.html Physical, Nuclear, and Chemical, Properties of Plutonium], IEER Factsheet</ref>). For instance, 3.6 [[kilogram|kg]] of plutonium 238 undergoes the same number of radioactive decays per second as 1 tonne of plutonium 239. Since the morbidity of the two isotopes in terms of absorbed radioactivity is almost exactly the same<ref>[http://www.ead.anl.gov/pub/doc/tbl1-rad-rc.pdf Mortality and Morbidity Risk Coefficients for Selected Radionuclides], Argonne National Laboratory</ref>, plutonium 238 is around 275 times more toxic by weight than plutonium 239.

The alpha radiation emitted by either isotope will not penetrate the skin, but it can irradiate internal organs if plutonium is inhaled or ingested. Particularly at risk is the [[skeleton]], the surface of which is likely to absorb the isotope, and the [[liver]], where the isotope will collect and become concentrated.

There have been six known accidents involving RTG-powered spacecraft. The first one was a launch failure on 21 April 1964 in which the U.S. [[Transit (satellite)|Transit-5BN-3]] navigation satellite failed to achieve orbit and burnt up on re-entry north of [[Madagascar]].<ref>[http://www.astronautix.com/craft/transit.htm astronautix.com]</ref><ref>[www.icsu-scope.org/downloadpubs/scope50/chapter02.html#t2.10]</ref> The 17,000 Ci (630 [[becquerel|TBq]]) plutonium metal fuel in its [[Systems Nuclear Auxiliary Power Program|SNAP]]-9a RTG was injected into the atmosphere over the Southern Hemisphere where it burnt up, and traces of plutonium 238 were detected in the area a few months later. The second was the Nimbus B-1 weather satellite whose launch vehicle was deliberately destroyed shortly after launch on 21 May 1968 because of erratic trajectory. Launched from the [[Vandenberg Air Force Base]], its SNAP-19 RTG containing relatively inert [[plutonium dioxide]] was recovered intact from the seabed in the [[Santa Barbara Channel]] five months later and no environmental contamination was detected.<ref>
{{Citation | title = Space Nuclear Power | author = A. Angelo Jr. and D. Buden  | year = 1985 | publisher = Krieger Publishing Company | isbn = 0894640003 }}</ref>

Two more were failures of Soviet [[Cosmos (satellite)|Cosmos]] missions containing RTG-powered lunar rovers in 1969, both of which released radioactivity as they burnt up. There were also five failures involving Soviet or Russian spacecraft which were carrying nuclear reactors rather than RTGs between 1973 and 1993 (see [[RORSAT]]).<ref>[http://www.iaass.org/pdf/FINAL%20DRAFT1_IAASS%20Stragtegic%20Plan%20Complete_Rev4.pdf IASS Strategic Plan 2005-2009], page 39</ref>

[[File:ALSEP Apollo 14 RTG.jpg|thumb|left|350px|A SNAP-27 RTG deployed by the astronauts of Apollo 14 identical to the one lost in the reentry of Apollo 13]]

The failure of the [[Apollo 13]] mission in April 1970 meant that the [[Lunar Module]] reentered the atmosphere carrying an RTG and burnt up over [[Fiji]]. It carried a SNAP-27 RTG containing 44,500 curies (1,650 TBq) of plutonium dioxide which survived reentry into the Earth's atmosphere intact, as it was designed to do, the trajectory being arranged so that it would plunge into 6-9 kilometers of water in the [[Tonga trench]] in the [[Pacific Ocean]]. The absence of plutonium 238 contamination in atmospheric and seawater sampling confirmed the assumption that the cask is intact on the seabed.  The cask is expected to contain the fuel for at least 10 half-lives (i.e. 870 years). The US Department of Energy has conducted seawater tests and determined that the graphite casing, which was designed to withstand reentry, is stable and no release of plutonium should occur. Subsequent investigations have found no increase in the natural background radiation in the area.  The Apollo 13 accident represents an extreme scenario due to the high re-entry velocities of the craft returning from [[cislunar space]].  This accident has served to validate the design of later-generation RTGs as highly safe.

To minimize the risk of the radioactive material being released, the fuel is stored in individual modular units with their own heat shielding. They are surrounded by a layer of [[iridium]] metal and encased in high-strength [[graphite]] blocks. These two materials are corrosion- and heat-resistant. Surrounding the graphite blocks is an aeroshell, designed to protect the entire assembly against the heat of reentering the Earth's atmosphere. The plutonium fuel is also stored in a ceramic form that is heat-resistant, minimising the risk of vaporization and aerosolization. The ceramic is also highly [[solubility|insoluble]].

The most recent accident involving a spacecraft RTG was the failure of the Russian [[Mars 96]] probe launch on 16 November 1996. The two RTGs onboard carried in total 200 g of plutonium and are assumed to have survived reentry (as they were designed to do). They are thought to now lie somewhere in a northeast-southwest running oval 320&nbsp;km long by 80&nbsp;km wide which is centred 32&nbsp;km east of [[Iquique]], [[Chile]].<ref>[http://nssdc.gsfc.nasa.gov/planetary/text/mars96_timeline.txt Mars 96 timeline], NASA</ref>

Many [[Beta-M]] RTGs produced by the Soviet Union to power [[lighthouse]]s and [[beacon]]s have become [[orphan source|orphaned sources]] of radiation.  Several of these units have been illegally dismantled for scrap metal resulting in the complete exposure of the [[Sr-90]] source, fallen into the ocean, or have defective shielding due to poor design or physical damage.  The [[US Department of Defense]] cooperative threat reduction program has expressed concern that material from the Beta-M RTGs can be used by [[terrorist]]s to construct a [[dirty bomb]].  [http://www.bellona.no/bellona.org/english_import_area/international/russia/navy/northern_fleet/incidents/37598]

The [[NASA]] claims 28 U.S. space missions have safely flown radioisotope energy sources since 1961.<ref>[http://sse.jpl.nasa.gov/scitech/display.cfm?ST_ID=2149 NASA: Enabling Exploration: Small Radioisotope Power Systems]</ref>

===Nuclear fission===
RTGs and [[nuclear power]] reactors use very different nuclear reactions. Nuclear power reactors use controlled [[nuclear fission]]. When an atom of U-235 or Pu-239 fuel fissions, neutrons are released that trigger additional fissions in a [[chain reaction]] at a rate that can be controlled with neutron absorbers. This is an advantage in that power can be varied with demand or shut off entirely for maintenance. It is also a disadvantage in that care is needed to avoid uncontrolled operation at dangerously high power levels.

Chain reactions do not occur in RTGs, so heat is produced at a fully predictable and steadily decreasing rate that depends only on the amount of fuel isotope and its half-life. An accidental power excursion is impossible. On the other hand, heat generation cannot be varied with demand or shut off when not needed. Auxiliary power supplies (such as rechargeable batteries) may be needed to meet peak demand, and adequate cooling must be provided at all times including the prelaunch and early flight phases of a space mission.

There are no [[nuclear proliferation]] risks associated with plutonium-238. The same properties, primarily its high specific power, that make it a desirable RTG fuel make it useless in nuclear weapons. Pu-238 is [[fissionable]], not [[fissile]]. It will occasionally spontaneously fission instead of undergoing alpha decay or it can be induced to fission with an external source of fast neutrons produced by various [[nuclear fusion|fusion]] reactions, but it cannot sustain the chain-reaction needed in a nuclear weapon fission primary. Because of its relatively high spontaneous fission rate compared with that of the fissile bomb fuel isotope Pu-239, its presence even as a contaminant would degrade performance by increasing the likelihood of a [[fizzle]], a low yield caused by premature initiation of the chain reaction before optimum conditions have been reached. Any significant amounts of Pu-238 would also generate heat that would have to be continually dissipated until the bomb was used.

Pu-238 could in principle be used as the tertiary stage to boost the yield of a fission-fusion-fission (thermonuclear) weapon, but there is no reason to use it in this way. Natural or even [[depleted uranium]] will also fission with fast fusion neutrons, is far more readily available, and generates essentially no heat in storage.

Pu-238 could conceivably be used in a [[radiological]] or [[dirty bomb]] to exploit the significant public fear of plutonium.

==Models ==
=== Space ===

MHW = Multi-Hundred Watt

{| border="1" class="wikitable"
|-
!rowspan="2"|Name & Model
!rowspan="2"|Used On (# of RTGs per User)
!colspan="2"| Maximum output
!rowspan="2"|Radio-<br />isotope
!rowspan="2"|Max fuel<br />used (kg)
!rowspan="2"|Mass (kg)
|-
!Electrical ([[watt|W]]) ||Heat (W)
|-
|ASRG* ||in prototype phase, [[Discovery Program]]  || ~140 (2x70) ||  ~500 || [[Plutonium-238|<sup>238</sup>Pu]] || ~1 || ~34
|-
|[[Multi-Mission Radioisotope Thermoelectric Generator|MMRTG]] ||in prototype phase, [[Mars Science Laboratory|MSL]] || ~110        || ~2000 || <sup>238</sup>Pu || ~4 || <45
|-
|[[GPHS-RTG]] || [[Cassini-Huygens|Cassini (3)]], [[New Horizons|New Horizons (1)]], [[Galileo probe|Galileo (2)]], [[Ulysses probe|Ulysses (1)]] || 300 || 4400 || <sup>238</sup>Pu || 7.8 || 55.9-57.8<ref name="GLB"/>
|-
|[[MHW-RTG]] || [[LES-8/9]], [[Voyager 1|Voyager&nbsp;1 (3)]], [[Voyager 2|Voyager&nbsp;2 (3)]] || 160<ref name="GLB"/> || 2400<ref name="tose"/> || <sup>238</sup>Pu || ~4.5 || 37.7<ref name="GLB"/>
|-
|[[Systems Nuclear Auxiliary Power Program|SNAP-3B]] || [[Transit-4A]] (1) || 2.7<ref name="GLB"/>|| 52.5<ref name="tose">http://www.totse.com/en/technology/space_astronomy_nasa/spacnuke.html</ref> || <sup>238</sup>Pu || ? || 2.1<ref name="GLB"/>
|-
|SNAP-9A || [[Transit 5BN1/2]] (1) || 25<ref name="GLB"/>|| 525<ref name="tose"/> || <sup>238</sup>Pu || ~1 || 12.3<ref name="GLB"/>
|-
|SNAP-19 || [[Nimbus-3]] (2), [[Pioneer 10|Pioneer&nbsp;10 (4)]], [[Pioneer 11|Pioneer&nbsp;11 (4)]] || 40.3<ref name="GLB">http://www.fas.org/nuke/space/bennett0706.pdf "Space Nuclear Power" G.L.Bennett 2006</ref>|| 525 || <sup>238</sup>Pu || ~1 || 13.6<ref name="GLB"/>
|-
|modified SNAP-19 || [[Viking program|Viking 1 (2)]], Viking&nbsp;2 (2) || 42.7<ref name="GLB"/>|| 525 || <sup>238</sup>Pu || ~1 || 15.2<ref name="GLB"/>
|-
|SNAP-27 || [[Project Apollo|Apollo 12-17]] [[ALSEP]] (1) || 73 || 1480 || <sup>238</sup>Pu || 3.8 || 20
|}

* The ASRG is in fact not an RTG; it is a [[Stirling engine|stirling]] power device.

=== Terrestrial ===
{| border="1" class="wikitable"
|-
!rowspan="2"|Name & Model
!rowspan="2"|Used On (# of RTGs per User)
!colspan="2"| Maximum output
!rowspan="2"|Radioisotope
!rowspan="2"|Max fuel used<br /> (kg)
!rowspan="2"|Mass (kg)
|-
!Electrical (W) ||Heat (W)
|-
|[[Beta-M]] || rowspan=8 | Obsolete Soviet unmanned lighthouses & beacons || 10 || 230 || [[Strontium-90|<sup>90</sup>Sr]] || 0.26 || 560
|-
|Efir-MA || 30 ||  720 || ? || ? || 1250
|-
|IEU-1 	 || 80 || 2200 || ? || ? || 2500
|-
|IEU-2 	 || 14 ||  580 || ? || ? || 600
|-
|Gong    || 18 ||  315 || ? || ? || 600
|-
|Gorn    || 60 || 1100 || <sup>90</sup>Sr || ? || 1050
|-
|IEU-2M  || 20 ||  690 || ? || ? || 600
|-
|IEU-1M  || 120 (180) || 2200 (3300) || ? || ? || 2(3) × 1050
|-
|Sentinel 25 <ref name=OTA>{{Citation
  | title = Power Sources for Remote Arctic Applications
  | date = June 1994
  | pages =
  | place = Washington, DC
  | publisher = U.S. Congress, Office of Technology Assessment
  | url = http://govinfo.library.unt.edu/ota/Ota_1/DATA/1994/9423.PDF
  | doi =
  | id = OTA-BP-ETI-129 }}</ref>
 || || 9 - 20 || || SrTiO<sub>J</sub> || 0.54 || 907 - 1814
|-
|Sentinel 100F<ref name=OTA/> || || 53 || || Sr<sub>2</sub>Ti0<sub>4</sub> || 1.77 || 1234
|-
|}

==See also==
{{Portal|Sustainable development}}
* [[Radioactive isotope]]
* [[Atomic battery]]
* [[Betavoltaics]]
* [[Optoelectric nuclear battery]]
* [[Radioisotope heater units]]
* [[Alkali-metal thermal to electric converter]]

==References ==
{{Reflist|2}}
{{Refbegin|2}}
*[http://saturn.jpl.nasa.gov/spacecraft/safety.cfm Safety discussion of the RTGs used on the Cassini-Huygens mission.]
*[http://www.bellona.no/en/international/russia/navy/northern_fleet/incidents/31772.html Bellona's report on RTG lighthouses.]
*[http://www.ne.doe.gov/pubs/npspace.pdf Nuclear Power in Space (PDF)]
*[http://saturn.jpl.nasa.gov/spacecraft/safety/eisss2.pdf Detailed report on Cassini RTG (PDF)]
*[http://fti.neep.wisc.edu/neep602/SPRING00/lecture5.pdf Detailed lecture on RTG fuels (PDF)]
*[http://atom.kaeri.re.kr/ton/nuc1.html Detailed chart of all radioisotopes]
*[http://www.grc.nasa.gov/WWW/RT2002/5000/5490thieme.html Stirling Thermoelectic Generator]
*[http://www.atsdr.cdc.gov/toxprofiles/tp143.pdf Toxicity profile for plutonium], Agency for Toxic substances and Disease Registry, U.S. Public Health Service, December 1990
*[http://saturn.jpl.nasa.gov/spacecraft/safety/fseis4.pdf Environmental Impact of Cassini-Huygens Mission.]
*[http://solarsystem.nasa.gov/multimedia/downloads/Standard_RPS_Report_Final_011205.pdf Expanding Frontiers with Radioisotope Power Systems (PDF)]
{{Refend}}

==External links==
{{Commons category|Radioisotope thermoelectric generators}}
*[http://solarsystem.nasa.gov/scitech/display.cfm?ST_ID=705 NASA JPL briefing, Expanding Frontiers with Radioisotope Power Systems] - gives RTG information and a link to a longer presentation
*[http://www.seds.org/spaceviews/cassini/rtgpages.html SpaceViews: The Cassini RTG Debate]
*[http://www.grc.nasa.gov/WWW/RT/2004/RP/RPT-shah.html Stirling Radioisotope Generator]
*[http://www.osti.gov/accomplishments/rtg.html DOE contributions - good links ]
* [https://inlportal.inl.gov/portal/server.pt?open=514&objID=1482&parentname=CommunityPage&parentid=17&mode=2&in_hi_userid=200&cached=true Idaho National Laboratory - Producer of RTGs]

{{Nuclear Technology}}

[[Category:Nuclear power in space]]
[[Category:Nuclear technology]]
[[Category:Electrical generators]]
[[Category:Battery (electricity)]]

[[ar:المولدات الكهروحرارية التي تعمل بالنظائر المشعة]]
[[ca:Generador termoelèctric per radioisòtops]]
[[cs:Radioizotopový termoelektrický generátor]]
[[da:Radioisotopgenerator]]
[[de:Radionuklidbatterie]]
[[es:Generador termoeléctrico de radioisótopos]]
[[eo:Radioizotopa termoelektra generatoro]]
[[fr:Générateur thermoélectrique à radioisotope]]
[[ko:방사성동위원소 열전기 발전기]]
[[it:Generatore termoelettrico a radioisotopi]]
[[lv:Radioizotopiskais termoelektroģenerators]]
[[lt:Radioizotopinis termoelektrinis generatorius]]
[[hu:Radioizotópos termoelektromos generátor]]
[[nl:Radio-isotoop thermo-elektrische generator]]
[[no:Radioisotopgenerator]]
[[pl:Radioizotopowy generator termoelektryczny]]
[[pt:Gerador termoelétrico de radioisótopos]]
[[ru:РИТЭГ]]
[[sv:Radioisotopgenerator]]
[[zh:放射性同位素熱電機]]
[[Category:2Fix]]