Mission: Hayabusa 2 |
Mission: Hayabusa 2 |
Apr 7 2014, 11:05 PM
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#91
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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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Apr 8 2014, 05:13 AM
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#92
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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 |
thank you Pandaneko, and welcome back!
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Apr 8 2014, 10:33 PM
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#93
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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 More pages (18,19,20,22) to follow. P (No need to translate pages 16 and 17) System configuration Hodoyoshi satellite system is used for the main system components of power and EDHS/EAOCS. (Tuning and improvements for deep space mission will be conducted for PROCYON) ①Comms. system (ISAS) ②Propulsion system (Univ. Tokyo and ISAS) ③ Mission system (Univ. Tokyo, Meisei Univ, Rikkyo Univ) (optical camera for asteroid observation) (geo-corona imager) P-18 Ultra smal comms. system for deep space probes We are developping ultra small X-band comms. system which is compatible with other deep space probes such as Hayabusa Specs. of PROCYON communication system 目仕様 Frequency band is X, category B Uplink frequency: 7.1 [GHz] Downlink frequency: 8.4 [GHz] Coherent ratio: 749/880 Output power: larger than 15W Command bit rate: 15.625, 125 [bps], 1 [kbps] Telemetry bit rate: 8 [bps] 〜4 [kbps] Maximum communicable distance: larger than 2 [AU] Orbit determination: R&RR Grund stations: Usuda and Uchinoura P-19 HGA(PZ plane) MGA(MZ plane) LGA(PZ,MZ plane) Unified propulsion system of ion thruster and cold gas jets (what follows is the character strings inside top square) Unified propulsion system using Xe based electrical propulsion (small acceleration and high specific impulse) and cold gas jet system for attitude control (RW unloading)+ orbit conrol (acceleration) (middle table contents as follows) Probe total mass: 60 kg Xe mass: 2.5 kg MIPS specific impulse: 1200s MIPS propulsion: 300Χ10-6N CGJ specific impulse: 25s CGJ propulsion: 11Χ10-3N (below satellite picture, colours correspond) Ion thruster thrust direction CGJ is used together with RCS for orbit control (character string at very bottom) Ion thruster for Hodoyoshi satellite P-20 (No need to translate page 21) Mission System (Optical navigation and flyby camera) Imaging system for high speed/ultra close flyby Realise angular resolution even by the small satellite borne telescope required for optical navigation during close flyby of asteroid Realise high speed changes in line of sight by controling the rotation of part of the telescope system (driving mechanism) through image feedback Optical system High speed line of sight changes by driving mirorr rotation →capable of tracking asteroid before and after closest approach (inside top right square) Optical system capable of observing objects as dim as magnitude 12 despite 50mm aperture and 150mm focal length (inside bottom right square) Driving mechanism capable of controling the rotational angle around optical axis of the telescope P-22 (end of pages 18, 19, 20, and 22) |
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Apr 9 2014, 04:56 AM
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#94
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Merciless Robot Group: Admin Posts: 8785 Joined: 8-December 05 From: Los Angeles Member No.: 602 |
Pandaneko, just wanted to thank you for yet another superb effort to help us English speakers understand yet another JAXA mission; it's very much appreciated!!!
-------------------- A few will take this knowledge and use this power of a dream realized as a force for change, an impetus for further discovery to make less ancient dreams real.
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Apr 10 2014, 11:16 AM
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#95
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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 What follows is the rest of my translation. P Development teams Joint project by JAXA (ISAS) and Tokyo University community aiming at entirely new form of deep space exploration (ultra small deep space probe) by bringing together knowhows (ultra small satellite technology/deep space probe technology) (System: Univ. Tokyo/ISAS) (Ground operation: ISAS) Propulsion system: Univ. Tokyo/ISAS SAP opening: Nihon Univ. Mission system: Meisei Univ./Univ. Tokyo Science instrument: Rikkyo Univ. Comms. : ISAS DH system: Tokyo Science Univ. P-23 Development schedule Flight model of each device is currently being manufactured in time for flight model integration in April 2014 Nearer events: System structure model/thermal model testing (mid Jan. to Feb.) Compatibility testing Usuda and Uchinoura ground stations (mid to end Feb.) (what follows is the translation of characters inside the chart) The character above 7 8 9 10 11 12 1 2 3 refers to fiscal 2013 and the numbers correspond to July (7), August, September up to March (3) The character above 4 5 6 7 8 9 10 1112 refers to fiscal 2014 and the numbers correspond to April(4), May, up to December (12) (Hereafter the chart is regarded as a matrix and from left and from topwise:) (C1:R1) :system (C1:R2): device (C2:R1): design (C2:R2): tests (C2:R3): newly developped devices (C2:R4): devices already developped (C4,5,6:R1): system design (C5,6,7,8:R3): BBM/EM manufacturing/test (C8,9,10,11:R3): FM manufacturing (some devices) (C5,6,7,8,9:R4): FM manufacturing/environment test (some devices) (and finally, diagonally across the bulk of chart from top left to bottom righ) STM/TTM test Usuda/Uchinoura compatibility test prior compatibility test all devices integration test final overall test margin launch site work/loading launch (December 2014) P-24 Summary Significance and possibility of ultra minitualisation of deep space probes Minitualisation/ultra minitualisation is an important direction to take in order to carry out low cost and frequent science missions (as stated in Space Science Roadmap) What is required is not a simple minitualisation of mission and system scales, thereby making compromises in the mission results Ultra minitualised satellite industry has been active at innovation by introducing advanced technologies available in private industries (by improving on introduction methods), thereby making it possible to produce light weight, small, and low cost satellites with high capabilities Other component technologies are increasingly becoming available in order to achieve ultra minitualisation of deep space probes Epsilon+4th satge may be able to send ultra miniture probes into orbits of Mars and beyond re. If increased from 50kg to 100kg they are still sufficiently light for dual (tandem) probing missions. PROCYON: 50kg class ultra small engineering test deep space probe Verification of ultra small deep space probe bus system and ultra close and high speed flyby approach to asteroid Collaboration between university teams and ISAS/JAX with a view to achieving new form of deep space exploration Piggy back launch on Hayabusa 2 is expected in December 2014 P-25 |
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Apr 10 2014, 11:19 AM
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#96
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Senior Member Group: Admin Posts: 3108 Joined: 21-December 05 From: Canberra, Australia Member No.: 615 |
Fantastic work Pandaneko. Thank you so much for translating all that information.
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Apr 10 2014, 10:10 PM
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#97
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Member Group: Members Posts: 817 Joined: 17-April 10 From: Kamakura, Japan Member No.: 5323 |
Hayabusa 2 will be accompanied in solar orbit by two microspacecraft, PROCYON and Artsat 2 and possibly also by Shin'en 2. The most interesting of the bunch is PROCYON which, among other things, will demonstrate imaging techniques during at least one but possibly up to three close flybys of small NEOs a presentation of the mission and spacecraft is available here Paolo, thanks again for this. Do we know anything more about Artsat 2. If 2 was there 1? What was it? Also, Is the launcher of Hayabusa 2 still going to be H2A? I am confused because I realised during the course of my translation that they may be using this Epsilon. As far as I know its first launch was some time last year and I am not too sure if it is reliable. Again, it is not that important, and I am only curiious. P |
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Apr 11 2014, 05:26 AM
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#98
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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 |
Paolo, thanks again for this. Do we know anything more about Artsat 2. If 2 was there 1? What was it? pandaneko, Artsat 1 was launched in February as a secondary payload in Earth orbit. they have a good Facebook page |
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May 24 2014, 10:57 PM
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#99
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Member Group: Members Posts: 817 Joined: 17-April 10 From: Kamakura, Japan Member No.: 5323 |
This really is just in case what follows has evaded the attention of colleagues so far.
I have come across an interesting short video describing activities for MASCOT. Its URL is as follows. https://www.youtube.com/watch?v=DbLmmvki_Bo It is all German and yet it gives us an insight into the workings of this lander. Actually, if you come to think about it this is all the more interesting because with Hayabusa we had to imagine what the landing site looked like. However, MASCOT will give us actual images and I am already very exited about this prospect. P |
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May 25 2014, 03:17 PM
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#100
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Senior Member Group: Members Posts: 1089 Joined: 19-February 05 From: Close to Meudon Observatory in France Member No.: 172 |
Yes : thanks a lot Pandaneko for your translation. What an useful work !
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Jun 13 2014, 04:47 AM
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#101
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Administrator Group: Admin Posts: 5172 Joined: 4-August 05 From: Pasadena, CA, USA, Earth Member No.: 454 |
Here's a Hayabusa 2 trailer (hat tip to Junya Terazono, who also posted a tweet featuring our favorite Japanese energy drink)
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Jun 14 2014, 04:16 PM
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#102
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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 |
according to this abstract, a possible target for the PROCYON miniprobe would be 1999 JV6, a quasi-satellite of Earth in a 1-year orbit. flyby would be in March 2016.
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Jul 21 2014, 08:00 AM
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#103
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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 |
PROCYON will be flying a lightweight Lyman-alpha camera for imaging the Earth's geocorona at increasing distances.
Presentation in Japanese |
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Jul 29 2014, 10:01 AM
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#104
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Member Group: Members Posts: 817 Joined: 17-April 10 From: Kamakura, Japan Member No.: 5323 |
PROCYON will be flying a lightweight Lyman-alpha camera for imaging the Earth's geocorona at increasing distances. Presentation in Japanese Thanks, Paolo I have started translating this PPT file. I will upload it when complete, perhaps in 10 days time, I think. P |
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Aug 6 2014, 03:20 AM
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#105
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Member Group: Members Posts: 817 Joined: 17-April 10 From: Kamakura, Japan Member No.: 5323 |
My translation of PROCYON ppt file is now complete, but I have a problem.
It is at 4.8 MB, and I tried to divide it into parts so that I can upload them as attachments. One such was found to be still at 4.1 MB, containing only 3 pages. I will study sharing procedure, but it will take time, my apologies. I am not good at IT at all. P |
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