View source for SELENE-2

{{Short description|Cancelled Japanese lunar exploration mission}}
{{Infobox spaceflight
| name                  = SELENE-2
| names_list            = <!--list of previous names if the spacecraft has been renamed. 
Include the dates applicable if possible, and separate each name with a linebreak. 
Omit if the spacecraft has only ever been known by one name. 
Do not include Harvard, COSPAR/NSSDC or SATCAT/NORAD/NASA designations as alternative names-->

<!--image of the spacecraft/mission-->
| image                 = [[File:Selene-2.jpg|250px]]
| image_caption         = <!--image caption-->
| image_alt             = <!--image alt text-->
| image_size            = <!--include px/em; defaults to 220px-->

<!--Basic details-->
| mission_type          = [[Orbiter]]<br/>[[Lander (spacecraft)|lander]]<br/>[[Rover (space exploration)|rover]]
| operator              = [[JAXA]]<ref name='Hashimoto 2017'>{{cite web| url=https://repository.exst.jaxa.jp/dspace/bitstream/a-is/609724/1/SA6000060041.pdf| title=Lunar Polar Exploration Mission|year=2017|archive-url=https://web.archive.org/web/20170709125641/https://repository.exst.jaxa.jp/dspace/bitstream/a-is/609724/1/SA6000060041.pdf|archive-date= 9 July 2017}}</ref>
| Harvard_designation   = <!--spacecraft launched 1962 and earlier only (eg. 1957 Alpha 2)-->
| COSPAR_ID             = <!--spacecraft launched since 1963 only (aka NSSDC ID; eg. 1998-067A)-->
| SATCAT                = <!--satellite catalogue number, omit leading zeroes (e.g. 25544)-->
| website               = <!--Homepage of the craft/mission, OFFICIAL PAGES ONLY-->
| mission_duration      = <!--How long the mission lasted-->
| distance_travelled    = <!--How far the spacecraft travelled (if known)-->
| orbits_completed      = <!--number of times the spacecraft orbited the Earth - see below for spacecraft beyond Earth orbit-->
| suborbital_range      = <!--downrange distance reached if spacecraft did not enter orbit-->
| suborbital_apogee     = <!--altitude reached if spacecraft did not enter orbit-->

<!--Spacecraft properties-->
| spacecraft            = <!--Spacecraft name/serial number (eg. Space Shuttle ''Discovery'', Apollo CM-118), etc-->
| spacecraft_type       = <!--eg. GPS Block II, Kobalt-M, US-K, etc-->
| spacecraft_bus        = <!--eg. A2100M, Star-2, etc-->
| manufacturer          = <!--company or companies who built the satellite-->
| launch_mass           = 5,000 kg<ref name='Hashimoto 2017'/> <!--fuelled mass at launch, not including rocket or upper stage-->
| BOL_mass              = <!--spacecraft mass in orbit at beginning of operational life, after LEOP phase-->
| landing_mass          = <!--Mass after landing (recovered spacecraft only)-->
| dry_mass              = <!--spacecraft mass in orbit without fuel-->
| payload_mass          = <!--Mass of cargo carried by spacecraft (eg. for Space Shuttle), or total mass of instrumentation/equipment/experiments for mission-->
| dimensions            = <!--body dimensions and solar array span-->
| power                 = <!--end-of-life power, in watts-->

<!--Launch details-->
| launch_date           = Cancelled <ref name='HARUYAMA 2015'>[https://www.jstage.jst.go.jp/article/tastj/14/ists30/14_Pk_147/_pdf Mission Concepts of Unprecedented Zipangu Underworld of the Moon Exploration (UZUME) Project]. (PDF). Junichi HARUYAMA, Isao KAWANO, Takashi KUBOTA, etal. ''J-Stage''. 3 July 2015. Accessed: 24 September 2018. Quote: "SELENE-2 was a mission with
an intention to send a landing module to the Moon, and a lunar hole was a candidate for the landing site. However, the SELENE-2 mission was officially terminated in March 2015."</ref>

<!--{{start date|YYYY|MM|DD|hh|mm|ss|TZ=Z}}-->
| launch_rocket         = [[H-IIA]]
| launch_site           = <!--Where the rocket launched from, including complex and pad; do not include the full address or country-->
| launch_contractor     = <!--organisation(s) that conducted the launch (eg. United Launch Alliance, Arianespace, etc)-->
| deployment_from       = <!--place where deployed from-->
| deployment_date       = <!--date deployed-->
| entered_service       = <!--date on which the spacecraft entered service, if it did not do so immediately after launch-->
<!-- * - e.g. Proton-M/Briz-M not Proton-M, but Titan IV(401)A not Titan IV(401)A-Centaur-->

<!--end of mission-->
| disposal_type         = <!--Whether the spacecraft was deorbited, decommissioned, placed in a graveyard orbit, etc-->
| deactivated           = <!--when craft was decommissioned-->
| destroyed             = <!--when craft was destroyed (if other than by re-entry)-->
| last_contact          = <!--when last signal received if not decommissioned-->
| recovery_by           = <!--recovered by-->
| recovery_date         = <!--recovery date-->
| decay_date            = <!--when craft re-entered the atmosphere, not needed if it landed-->
| landing_date          = <!--when the spacecraft made a controlled landing, not needed if it did not return intact-->
| landing_site          = <!--where the craft landed; site/runway or coordinates-->
<!--
    The following template should be used for ONE of the three above fields "end_of_mission", "decay" or "landing" if the spacecraft is no longer operational.
    If it landed intact, use it for the landing time, otherwise for the date it ceased operations, or the decay date if it was still operational when it re-entered.
    {{end date|YYYY|MM|DD|hh|mm|ss|TZ=Z}} (for Zulu/UTC) or {{end date|YYYY|MM|DD}} (if time unknown) 
-->

<!--orbit parameters-->
<!--as science-related articles, SI units should be the principal units of measurement, however we usually use {{convert}} to display imperial units in parentheses after the initial values-->
| orbit_reference       = [[Selenocentric orbit|Selenocentric]]
| orbit_regime          = <!--high, low, medium, molniya, GSO - please link (e.g. [[Low Earth orbit|Low Earth]] - please don't use acronyms-->
| orbit_longitude       = <!--geosynchronous satellites only-->
| orbit_slot            = <!--Designation of orbital position or slot, if not longitude (e.g plane and position of a GPS satellite)-->
| orbit_semimajor       = <!--semimajor axis-->
| orbit_eccentricity    = <!--orbital eccentricity-->
| orbit_periapsis       = <!--periapsis altitude--> 
| orbit_apoapsis        = <!--apoapsis altitude--> 
| orbit_inclination     = <!--orbital inclination--> 
| orbit_period          = <!--time taken to complete an orbit-->
| orbit_RAAN            = <!--right ascension of the ascending node-->
| orbit_arg_periapsis   = <!--argument of perigee/periapsis-->
| orbit_mean_anomaly    = <!--mean anomaly at epoch, only use in conjunction with an epoch value-->
| orbit_mean_motion     = <!--mean motion of the satellite, usually measured in orbits per day-->
| orbit_repeat          = <!--repeat interval/revisit time-->
| orbit_velocity        = <!--speed at which the spacecraft was travelling at epoch - only use for spacecraft with low orbital eccentricity-->
| orbit_epoch           = <!--the date at which the orbit parameters were correct-->
| orbit_rev_number      = <!--revolution number-->
| apsis                 = selene

|interplanetary         = <!--Infobox spaceflight/IP can be called multiple times for missions with multiple targets or combined orbiter/lander missions, etc-->

<!--transponder parameters-->
| trans_band            = <!--Transponder frequency bands-->
| trans_frequency       = <!--specific frequencies-->
| trans_bandwidth       = <!--bandwidth-->
| trans_capacity        = <!--capacity of the transponders-->
| trans_coverage        = <!--area covered-->
| trans_TWTA            = <!--TWTA output power-->
| trans_EIRP            = <!--equivalent isotropic power-->
| trans_HPBW            = <!--half-power beam width-->

<!--Only use where a spacecraft/mission is part of a clear programme of sequential missions. 
If in doubt, leave it out-->
| programme             = 
| previous_mission      =
| next_mission          =

<!--mission insignia or patch-->
| insignia              = <!--omit the "file" prefix-->
| insignia_caption      = <!--image caption-->
| insignia_alt          = <!--image alt text-->
| insignia_size         = <!--include px/em; defaults to 180px-->
}}
'''SELENE-2''' {{IPAc-en|ˈ|s|ɛ|l|ᵻ|n|iː}}, or the '''Selenological and Engineering Explorer 2''', is a cancelled [[Japan]]ese [[robotic spacecraft|robotic mission]] to the [[Moon]] that would have included an [[orbiter]], a [[lander (spacecraft)|lander]] and a [[lunar rover|rover]].<ref name="as">{{cite web |url=http://www.asianscientist.com/topnews/japan-announces-selene-2-lunar-mission-2017/ |title=Japan SELENE-2 Lunar Mission Planned For 2017 |author=Srinivas Laxman |date=2012-07-16|access-date= 2012-08-07|work=Asian Scientist}}</ref> It was intended as a successor to the 2007 [[SELENE|SELENE (Kaguya)]] lunar orbiter.<ref name="jaxa">{{cite web | url=http://www.jspec.jaxa.jp/e/activity/selene2.html | title=Moon lander SELENE-2 | publisher=JAXA Space Exploration Center | date=24 December 2009 | access-date=2010-05-07 | url-status=dead | archive-url=https://web.archive.org/web/20100723055617/http://www.jspec.jaxa.jp/e/activity/selene2.html | archive-date=23 July 2010 }}</ref>

Instead of SELENE-2, JAXA is working with the [[ISRO|Indian Space Research Organisation]] (ISRO) to plan a joint mission called the [[Lunar Polar Exploration Mission]] (LUPEX).<ref>{{Cite news |date=2023-11-17 |title=ISRO working on ambitious lunar missions LUPEX, Chandrayaan-4: Official |work=The Economic Times |url=https://economictimes.indiatimes.com/news/science/isro-working-on-ambitious-lunar-missions-lupex-chandrayaan-4-official/articleshow/105292411.cms |access-date=2023-12-15 |issn=0013-0389}}</ref><ref name=":1">{{cite web |date=8 September 2019 |title=India's next Moon shot will be bigger, in pact with Japan |url=https://timesofindia.indiatimes.com/india/indias-next-moon-shot-will-be-bigger-in-pact-with-japan/articleshow/71030437.cms |access-date=10 March 2021 |quote=For our next mission — Chandrayaan-3 — which will be accomplished in collaboration with [[JAXA]] (Japanese Space Agency), we will invite other countries too to participate with their payloads. |newspaper=The Times of India}}</ref><ref name="GER2020">{{cite web |date=August 2020 |title=Global Exploration Roadmap - Supplement August 2020 - Lunar Surface Exploration Scenario Update |url=https://www.globalspaceexploration.org/wp-content/uploads/2020/08/GER_2020_supplement.pdf |access-date=10 March 2021 |publisher=NASA}} {{PD-notice}}</ref><ref>{{Cite news |date=2023-08-22 |title=ISRO's next Moon mission in collaboration with Japanese space agency gathers steam |work=The Economic Times |url=https://economictimes.indiatimes.com/news/science/isros-next-moon-mission-in-collaboration-with-japanese-space-agency-gathers-steam/articleshow/102943227.cms |access-date=2023-12-22 |issn=0013-0389}}</ref> The mission would send an [[Uncrewed spacecraft|uncrewed]] [[lunar lander]] and [[Lunar rover|rover]] to explore the [[Lunar south pole|south pole region]] of the [[Moon]] no earlier than 2026.<ref name="LUPEX_2026_28">{{Cite AV media |url=https://www.youtube.com/watch?v=vf-tBT7UTx4&t=4689s |title=4th IPSC 2023 Inauguration |date=2023-03-22 |time=1:18:09}}</ref> JAXA is likely to provide the under-development [[H3 (rocket)|H3]] [[launch vehicle]] and the rover, while ISRO would be providing the lander.<ref name=":0">{{cite web |date=4 January 2019 |title=Episode 82: JAXA and International Collaboration with Professor Fujimoto Masaki |url=https://astrotalkuk.org/episode-82-jaxa-and-international-collaboration-with-professor-fujimoto-masaki/ |access-date=10 March 2021 |publisher=Astro Talk UK}}</ref>

==Overview==

The lander would have targeted lava tubes and other permanently shadowed areas, which function as cold trap volatiles such as water. Water ice could be processed by future missions to produce spacecraft propellant ([[Liquid oxygen|LOX]]/H<sub>2</sub>).<ref name='Hashimoto 2017'/>

;Orbiter
The orbiter would have a mass of  700&nbsp;kg.<ref name="as"/>

;Lander
The lander would have a mass of 1,000&nbsp;kg, and would be able to deliver up to 340&nbsp;kg<ref name='Hashimoto 2017'/> of payload, including the rover. Its mission would last two weeks.<ref name="as"/>

;Rover
The rover would have a mass of 100&nbsp;kg, and it would operate for two weeks.

== Penetrators ==
One option [[JAXA]] was investigating in 2006, was to integrate a small data relay satellite and penetrators into the mission.<ref>{{cite web | author=Tatsuaki Hashimoto| title=Robotic Lunar Exploration Scenario | format=.PDF | publisher=JAXA | url=http://esamultimedia.esa.int/docs/spineto/2006/splinter_sessions/splinter4/1_JAXA.pdf | date=May 2006 | access-date=2010-05-07}}</ref>

== See also ==

* [[Hiten (spacecraft)|Hiten]] (MUSES-A)
* [[Lunar-A]]
* [[SELENE]] (Kaguya)
* [[Smart Lander for Investigating Moon]] (SLIM)

== References ==
{{Reflist}}

== External links ==
* Manabu Kato, [http://lunar.gsfc.nasa.gov/library/3-04aLunar-A-Kato.pdf The Current Status of the Japanese Penetrator Mission Lunar-A], ISAS/JAXA,   Information about the penetrator tests.

{{Moon spacecraft}}
{{Lunar Rovers}}
{{Japanese space program}}

[[Category:Cancelled space probes]]
[[Category:Missions to the Moon]]
[[Category:Japanese Lunar Exploration Program]]
[[Category:Lunar rovers]]
[[Category:Robots of Japan]]
[[Category:Japanese space probes]]