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{{Infobox spaceflight
{{Infobox_Spacecraft
| name = LUNAR-A<!--defaults to page title-->
| Name = '''LUNAR A'''
| names_list = <!--list of previous names if the spacecraft has been renamed.
| Image = [[Image:LUNAR A.jpg|300px]]
Include the dates applicable if possible, and separate each name with a linebreak.
| Caption = LUNAR A spacecraft, artist's impression
Omit if the spacecraft has only ever been known by one name.
| Organization = [[JAXA]]
Do not include Harvard, COSPAR/NSSDC or SATCAT/NORAD/NASA designations as alternative names-->
| Major_Contractors =
| Mission_Type = Orbiter, penetrator
| Flyby_Of =
| Satellite_Of = '''[[Moon]]'''
| Orbital_Insertion_Date =
| Launch = cancelled
| Launch_Vehicle = [[M-5]]
| Decay =
| Mission_Duration =
| NSSDC_ID = LUNAR-A
| Webpage = [http://www.jaxa.jp/missions/projects/sat/exploration/lunar_a/index_e.html LUNAR-A page]
| Mass = 520 kg
| Power =
| Orbital_elements =
| Semimajor_Axis =
| Eccentricity =
| Inclination = 30°
| Orbital_Period = 2h
| Apoapsis = 200 km
| Periapsis = 300 km
| Orbits =
}}


<!--image of the spacecraft/mission-->
'''LUNAR-A''' is a [[Japan]]ese [[spacecraft]] that was scheduled to be launched in August 2004. After many delays (primarily due to potential faults in its thrusters <ref>[http://www.spacetoday.net/Summary/2285 Lunar-A launch delayed] Space Today (March 31, 2004)</ref>, the project was eventually cancelled in January 2007.<ref>{{cite news |title=Japan's Moon mission in jeopardy |url=http://www.cbc.ca/technology/story/2007/01/15/japan-moon.html|publisher=[[Associated Press]] |date=[[2007-01-15]] |accessdate=2007-01-15 }}</ref> It would have been carried into space by a Japanese [[M-5 rocket|M-V]] launch vehicle from the [[Kagoshima Space Center]]. However, the development of its seismic penetrators will be continued until the end of FY 2007. They will reportedly be used on a future [[Russia]]n mission, most likely [[Luna-Glob]]. [[JAXA]] also plans to use the penetrators on other targets.
| image = <!--omit the "file" prefix-->
| image_caption = <!--image caption-->
| image_alt = <!--image alt text-->
| image_size = <!--include px/em; defaults to 220px-->


<!--Basic details-->
The vehicle would have been cylindrical in shape, with a diameter of 2.2&nbsp;m and a height of 1.7&nbsp;m. It would have had four [[Photovoltaic module|solar panel]]s and was engineered to be spin-stabilized. It would have entered into an elliptical orbit around the [[Moon]], and would have deployed two penetrators at an altitude of 40&nbsp;km on opposite sides of the lunar body. These were to have been braked by a small rocket at an altitude of 25&nbsp;km, then free fall to the surface. They were designed to withstand a collision of up to 330 meters per second, and would have readily penetrated the lunar [[regolith]].
| mission_type = <!--eg. Technology, Reconnaissance, ISS assembly, etc-->
| operator = [[JAXA]]<!--organisation(s) that operate(d) the spacecraft-->
| 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 = [http://global.jaxa.jp/projects/sat/lunar_a/ LUNAR-A page]<!--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-->
The penetrators would have contained [[seismometer]]s and heat-flow probes. They were designed to operate for a year, and would have transmitted data back to the orbiting craft. They were planned to observe lunar quakes and to determine if the Moon has a core. The lunar surface is considered nearly transparent at the transmission frequencies, so the compressed signals would have been received from orbit.
| 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 = {{convert|520|kg|abbr=on}}<!--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-->
Once the penetrators deployed, the LUNAR-A spacecraft would have maneuvered to an orbital altitude of 200&nbsp;km above the surface. The craft was to have carried a monochromatic imaging camera with a resolution of 30&nbsp;m.
| launch_date = Cancelled<!--{{start date|YYYY|MM|DD|hh|mm|ss|TZ=Z}}-->
| launch_rocket = [[M-5 rocket|M-5]]<!--Rocket that launched the satellite, include upper stage if distinct from rocket* and if possible flight/tail/serial number-->
| 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-->
<!-- Since the mission review in 2004, Lunar-A is currently under further technology testing. This phase will last until the end of FY 2007. A communication test with the penetrator was done in Mexico in June 2006. The test was successful. The final test of the penetrators will be done in Mexico around July 2007. -->
| 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 = <!--geocentric, selenocentric, etc - please link (e.g. [[Geocentric orbit|Geocentric]])-->
| 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 = <!--planet specific apsis term (eg. gee/helion/selene/etc - defaults to generic "apsis")-->

|interplanetary = <!--Infobox spaceflight/IP can be called multiple times for missions with multiple targets or combined orbiter/lander missions, etc-->
{{Infobox spaceflight/IP
|type = orbiter <!--delete as appropriate, MUST BE ONE OF THESE OPTIONS-->
|object = [[Moon]]<!--body visited - e.g. Jupiter, Venus, etc-->
|orbits = <!--number of orbits completed at target body (if applicable and known)-->
|component = <!--part of the spacecraft involved, if spacecraft split into multiple components-->
|arrival_date = <!--Flybys: date/time of closest approach; Orbiters; orbital insertion date; Impactors/Landers/Rovers: impact/landing date/time; Atmospheric probes: atmospheric entry time-->
|departure_date = <!--Date of leaving orbit for orbiters, date of launch for landers which took off again-->
|location = <!--landing/impact site, including EOM impacts for atmospheric probes and lunar/asteroid orbiters-->
|distance = <!--closest approach distance for flybys, distance travelled on surface for rovers, omit for others-->
|sample_mass = <!--mass of samples returned (sample return missions only)-->
|surface_EVAs = <!--number of EVAs on the surface-->
|surface_EVA_time = <!--time spent on surface EVAs-->
<!--Orbit parameters, ONLY USE IF THE ABOVE ORBIT PARAMETERS SECTION DOESN'T APPLY TO THE TARGET-->
|periapsis = 200&nbsp;km<!--periapsis altitude-->
|apoapsis = 300&nbsp;km<!--apoapsis altitude-->
|inclination = 30°<!--inclination to the object's equator-->
|apsis = selene<!--planet specific apsis term, as above-->
}}
{{Infobox spaceflight/IP
|type = impactor <!--delete as appropriate, MUST BE ONE OF THESE OPTIONS-->
|object = [[Moon]]<!--body visited - e.g. Jupiter, Venus, etc-->
|orbits = <!--number of orbits completed at target body (if applicable and known)-->
|component = <!--part of the spacecraft involved, if spacecraft split into multiple components-->
|arrival_date = <!--Flybys: date/time of closest approach; Orbiters; orbital insertion date; Impactors/Landers/Rovers: impact/landing date/time; Atmospheric probes: atmospheric entry time-->
|departure_date = <!--Date of leaving orbit for orbiters, date of launch for landers which took off again-->
|location = <!--landing/impact site, including EOM impacts for atmospheric probes and lunar/asteroid orbiters-->
|distance = <!--closest approach distance for flybys, distance travelled on surface for rovers, omit for others-->
|sample_mass = <!--mass of samples returned (sample return missions only)-->
|surface_EVAs = <!--number of EVAs on the surface-->
|surface_EVA_time = <!--time spent on surface EVAs-->
<!--Orbit parameters, ONLY USE IF THE ABOVE ORBIT PARAMETERS SECTION DOESN'T APPLY TO THE TARGET-->
|periapsis = <!--periapsis altitude-->
|apoapsis = <!--apoapsis altitude-->
|inclination = <!--inclination to the object's equator-->
|apsis = <!--planet specific apsis term, as above-->
}}

<!--Cargo parameters-->
| payload_items = <!--Major individual items (e.g. satellites deployed, etc)-->
| cargo_mass = <!--Mass of the cargo aboard-->
| cargo_mass_press = <!--Mass of pressurised cargo-->
| cargo_mass_unpress = <!--Mass of unpressurised cargo (e.g. Dragon Trunk)-->
| cargo_mass_fuel = <!--Mass of fuel transferred from spacecraft's tanks-->
| cargo_mass_gas = <!--Mass of gasses transferred (e.g. oxygen)-->
| cargo_mass_water = <!--Mass of water transferred-->

<!--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-->
}}

'''LUNAR-A''' was a cancelled [[Japan]]ese [[spacecraft]] project that was originally scheduled to be launched in 1995, then delayed to August 2004. After many delays (primarily due to potential thruster faults),<ref>[http://www.spacetoday.net/Summary/2285 Lunar-A launch delayed] Space Today (March 31, 2004)</ref> the project was eventually cancelled in January 2007.<ref>{{cite news |title=Japan's Moon mission in jeopardy |url=https://www.cbc.ca/news/science/japan-s-moon-mission-in-jeopardy-1.632859|publisher=[[Associated Press]] |date=2007-01-15 |access-date=2007-01-15 }}</ref> It was planned to be launched on a Japanese [[M-V]] rocket from the [[Kagoshima Space Center]].

==History==
The vehicle would have been cylindrical, with a diameter of 2.2&nbsp;m and a height of 1.7&nbsp;m. It would have had four [[Photovoltaics|solar panels]] and was engineered to be [[Spin stabilization|spin-stabilized]]. Plans called for it to enter an [[Elliptic orbit|elliptical orbit]] around the [[Moon]], and deploy two penetrators at an altitude of 40&nbsp;km on opposite sides of the lunar body. The penetrators were to have been braked by a small rocket at an altitude of 25&nbsp;km, then free fall to the surface. They were designed to withstand a collision speed of 330 meters per second to deeply penetrate the lunar [[regolith]].<ref>{{cite web|title=LUNAR-A Lunar Explorer|url=https://global.jaxa.jp/activity/pr/brochure/files/sat15.pdf|website=JAXA|access-date=March 19, 2023}}</ref>

Once the penetrators deployed, the LUNAR-A spacecraft was mission-planned to maneuver to an orbital altitude of 200&nbsp;km above the lunar surface. The craft was to have carried a monochromatic imaging camera with a resolution of 30&nbsp;m.<ref>{{cite web|title=Lunar-A|url=https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=LUNAR-A|website=NASA NSSDCA|access-date=March 19, 2023}}</ref>


==See also==
==See also==
Line 47: Line 165:


==External links==
==External links==
* [http://www.jaxa.jp/missions/projects/sat/exploration/lunar_a/index_e.html JAXA page]
* [http://global.jaxa.jp/projects/sat/lunar_a/index.html JAXA page]
* [http://www.isas.jaxa.jp/e/enterp/missions/lunar-a/index.shtml ISAS page]
* [http://www.isas.jaxa.jp/en/missions/spacecraft/others/lunar-a.html ISAS page]
* [http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=LUNAR-A NASA Page about LUNAR-A]
* [https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=LUNAR-A NASA Page about LUNAR-A]
* [http://solarsystem.nasa.gov/missions/profile.cfm?MCode=LUNAR-A LUNAR-A Mission Profile] by [http://solarsystem.nasa.gov NASA's Solar System Exploration]
* [https://web.archive.org/web/20040114210530/http://solarsystem.nasa.gov/missions/profile.cfm?MCode=LUNAR-A LUNAR-A Mission Profile] by [http://solarsystem.nasa.gov NASA's Solar System Exploration]


{{Japanese space program}}
{{Japanese space program}}
{{Moon spacecraft}}


[[Category:Lunar spacecraft]]
[[Category:Missions to the Moon]]
[[Category:Japanese space program]]
[[Category:Japanese space probes]]
[[Category:Japanese probes]]
[[Category:Cancelled space probes]]
[[Category:Cancelled spacecraft]]
[[Category:Japanese Lunar Exploration Program]]

[[de:LUNAR-A]]
[[es:LUNAR-A]]
[[ja:LUNAR-A]]

Latest revision as of 15:29, 23 October 2024

LUNAR-A
OperatorJAXA
WebsiteLUNAR-A page
Spacecraft properties
Launch mass520 kg (1,150 lb)
Start of mission
Launch dateCancelled
RocketM-5
Moon orbiter
Orbital parameters
Periselene altitude200 km
Aposelene altitude300 km
Inclination30°
Moon impactor

LUNAR-A was a cancelled Japanese spacecraft project that was originally scheduled to be launched in 1995, then delayed to August 2004. After many delays (primarily due to potential thruster faults),[1] the project was eventually cancelled in January 2007.[2] It was planned to be launched on a Japanese M-V rocket from the Kagoshima Space Center.

History

[edit]

The vehicle would have been cylindrical, with a diameter of 2.2 m and a height of 1.7 m. It would have had four solar panels and was engineered to be spin-stabilized. Plans called for it to enter an elliptical orbit around the Moon, and deploy two penetrators at an altitude of 40 km on opposite sides of the lunar body. The penetrators were to have been braked by a small rocket at an altitude of 25 km, then free fall to the surface. They were designed to withstand a collision speed of 330 meters per second to deeply penetrate the lunar regolith.[3]

Once the penetrators deployed, the LUNAR-A spacecraft was mission-planned to maneuver to an orbital altitude of 200 km above the lunar surface. The craft was to have carried a monochromatic imaging camera with a resolution of 30 m.[4]

See also

[edit]

References

[edit]
  1. ^ Lunar-A launch delayed Space Today (March 31, 2004)
  2. ^ "Japan's Moon mission in jeopardy". Associated Press. 2007-01-15. Retrieved 2007-01-15.
  3. ^ "LUNAR-A Lunar Explorer" (PDF). JAXA. Retrieved March 19, 2023.
  4. ^ "Lunar-A". NASA NSSDCA. Retrieved March 19, 2023.
[edit]
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