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Mission: Hayabusa 2
pandaneko
post Apr 7 2014, 11:05 PM
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QUOTE (Paolo @ Jan 31 2014, 05:18 PM) *
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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Paolo
post Apr 8 2014, 05:13 AM
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thank you Pandaneko, and welcome back!
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pandaneko
post Apr 8 2014, 10:33 PM
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QUOTE (Paolo @ Jan 31 2014, 05:18 PM) *
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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nprev
post Apr 9 2014, 04:56 AM
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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!!! smile.gif


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pandaneko
post Apr 10 2014, 11:16 AM
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QUOTE (Paolo @ Jan 31 2014, 05:18 PM) *
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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Astro0
post Apr 10 2014, 11:19 AM
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Fantastic work Pandaneko. Thank you so much for translating all that information. smile.gif
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pandaneko
post Apr 10 2014, 10:10 PM
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QUOTE (Paolo @ Dec 12 2013, 04:57 PM) *
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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Paolo
post Apr 11 2014, 05:26 AM
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QUOTE (pandaneko @ Apr 11 2014, 12:10 AM) *
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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pandaneko
post May 24 2014, 10:57 PM
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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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vikingmars
post May 25 2014, 03:17 PM
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Yes : thanks a lot Pandaneko for your translation. What an useful work ! wheel.gif wheel.gif wheel.gif wheel.gif wheel.gif
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elakdawalla
post Jun 13 2014, 04:47 AM
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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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Paolo
post Jun 14 2014, 04:16 PM
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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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Paolo
post Jul 21 2014, 08:00 AM
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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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pandaneko
post Jul 29 2014, 10:01 AM
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QUOTE (Paolo @ Jul 21 2014, 05:00 PM) *
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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pandaneko
post Aug 6 2014, 03:20 AM
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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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