Mission: Hayabusa 2 |
Mission: Hayabusa 2 |
Jan 22 2008, 02:59 PM
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#1
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Junior Member Group: Members Posts: 58 Joined: 17-September 06 Member No.: 1150 |
JAXA wants to continue with Hayabusa 2. However there is/was a huge fight about the budget. Main problem was the budget for the launch vehicle. 2 months ago or so there was a report which said, that JAXA had to find another launch vehicle or the project gets cancelled. Now the Italian space agency played saviour and overed the VEGA. So finally we might see another Hayabusa in 2011.
It was mentioned here: http://www.jspec.jaxa.jp/080110Final_IPEWG-ProgramBook.pdf |
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Jan 31 2014, 08:18 AM
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#2
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Senior Member Group: Members Posts: 1729 Joined: 3-August 06 From: 43° 35' 53" N 1° 26' 35" E Member No.: 1004 |
a rather detailed description of PROCYON (in Japanese) is available here
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Apr 7 2014, 11:05 PM
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#3
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Member Group: Members Posts: 817 Joined: 17-April 10 From: Kamakura, Japan Member No.: 5323 |
a rather detailed description of PROCYON (in Japanese) is available here Translation of pages 10 to 15. More will follow. P Significance of ultra minitualisation in deep space probes: even lighter and even deeper (character set on the graph, top right) (figure: courtesy of ISAS) (characters along the solid lines from top to bottom) reinforcement LEO 3 ton class reinforcement LEO 2 ton class 4th stage (character set lower right at top as follows) 50kg class, Ultra small probes X 4 (character set lower right at bottom as follows) 50kg class, Ultra small probes, C3 approx.40 (Ceres) (and at the very bottom as follows) (C3:how much deeper can we throw into?) P-10 Ultra small deep space probes - mission varieties (1) * Piggy back on larger space probes and missions – examples: IKAROS (on Akatsuki),PROCYON(on Hayabusa 2) – frequency is minimal, but offers precious opportunity despite the lack of merit arising from low cost and high frequency potential * Piggy back on GTO (geostationary transfer orbit) missions –small kick stage (approx. a few 100kg) added to the top of launcher is used to insert small probe into orbits outside gravity (C3>0) after main satellite insertion into GTO – after that the probe will move into its own mission orbit by EDVEGA etc. (electric propulsion as used in Hayabusa) P-11 Ultra small deep space probes - mission varieties (2) * single probe launch by low cost, medium rocket (Epsilon) – insertion into orbit which reaches ultra far astronomical object making use of its light weight (approx. 50kg) – conducting risky project as precursor to future medium to large missions * cluster of probes launched by medium, low cost rocket (Epsilon) –simultaneous launch of ultra light probes by a single rocket – insertion into far reaching orbit is not possible, but individual orbit manuevability can secure limited mission freedom and variation (--> leading to low cost and frequent deep space missions P-12 Technologies required for lutra small deep space probes (header) • electricity generation very far from Sun --> ultra light weight power generating system (above all photos) • highly efficient and small propulsion system for orbital manipulation (above middle two photos) • overall weight reduction in bus related devices >> (attitude control system, power system, computers etc.) (above bottom three photos) (and at the very bottom) Component technologies for ultra small deep space probes are becoming available P-13 Presentation contents • Possibility and significance of ultra small deep space probes • References made in space science and probing roadmap • What is meant by "Ultra small probes"? •Current status of ultra small probe industry • Mission varieties and realisability of ultra small deep space probes • PROCYON- 50kg class ultra small deep space probes • Mission outline • Outline of probe system • Development • Development schedule P-14 Outline of PROCYON mission (PRoximate Object Close flYby with Optical Navigation) Mission sequence Dec 2014: launch, followed by a series of various component engineering test missions Dec 2015: Earth swingby After Jan. 2016: Planetary flyby mission Outline of mission components 1. 50kg class ultra small deep space probe bus technology testing (nominal mission) (contents in bottom left square) a. orbit determination, comms., attitude control, temp. control, and power generation in deep space b. orbit manipulation in deep space by ultra small electric propulsion system 2. Verification of deep space probing technologies (contents in bottom right square) (Advanced mission: additional mission components) c. comms. by highly efficient X-band power amp. using GaN d. VLBI navigation in deep space e. flyby around asteroids using combined radio and optical wave navigation f. asteroid flyby in ultra proximity and at high velocity using line of sight tracking <Outline of ultra close, high velocity asteroid flyby> (explanation on the right handside picture of probe) Relative velocity in flyby > a few km/s Minimum approach distance a few 10km line of sight control Flyby at ultra close range and obtain high resolution pictures by mirror driving on board and line of sight tracking feedback of pictures End of P-15 |
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