Ᏹᐂࢲࢫࢺィ ᢏ⾡ࡢ◊✲㛤Ⓨ
ۑ⃝ᖾே㸦IHIࠊJAXA㸧ࠊᯇᮏᬕஂ㸦JAXA㸧ࠊ
ᱜࠊ⯪㉺ᅜᗈࠊඵᆏဴ㞝㸦(᭷)QPS◊✲ᡤ㸧ࠊⰼ⏣ಇஓ㸦ᕞᏛ㸧ࠊ㛗㇂ᕝ┤㸦ISAS/JAXA㸧 JAXA 䛿䠄᭷䠅QPS ◊✲ᡤ䛸䛸䜒䛻䚸≉䛻䝕䞊䝍䛾ᑡ䛺䛔䛝䛥 100䃛m䡚ᩘ䡉䡉⛬ᗘ䛾䝯䝔䜸䝻䜲䝗䠃䝕䝤䝸䠄䛔 䜟䜖䜛䛂䝎䝇䝖䛃䠅䛾Ꮡᅾ㔞䜢ィ 䛧䚸Ᏹᐂᶵ䛾䝸䝇䜽ホ౯䛾⢭ᗘ䜢ྥୖ䛥䛫䜛䛣䛸䜢┠ⓗ䛸䛧䛯䝉䞁䝃(QPS ᘧ䝎䝇䝖䝉 䞁䝃)䛾ᇶ♏᳨ウ䜢⾜䛳䛯䚹䛣䛾䝉䞁䝃䛿䚸䝫䝸䜲䝭䝗䛺䛹䜢ᮦ㉁䛸䛩䜛⤯⦕ᛶⷧ⭷䠄ཌ䛥 10䃛m⛬ᗘ䠅ୖ䛻䜶䝑䝏䞁䜾 䛺䛹䛾ᢏἲ䛻䜘䜚䚸䝢䝑䝏 (✵㛫࿘ᮇ) 100䃛m ௨ୗ䛾┤⥺≧䛾⣽㛗䛔ᑟ⥺ (᳨ฟ⥺) 䛾䝟䝍䞊䞁䜢༳ๅ䛧䛶䛚䛝䚸
᳨ฟ⥺䛾◚᩿䜢㟁Ẽⓗ䛻᳨ฟ䛩䜛䛣䛸䛻䜘䜚䚸䝎䝇䝖䛾⾪✺䜢᳨▱䛩䜛䜒䛾䛷䛒䜛䚹䜎䛯䚸㞄䜚ྜ䛖」ᩘᮏ䛾᳨ฟ䛜ษ
᩿䛥䜜䛯ሙྜ䛻䛿䚸䛭䜜䜙䛾ᮏᩘ䛛䜙䝎䝇䝖䛾䝃䜲䝈䜢᥎ᐃ䛩䜛䛣䛸䛜ྍ⬟䛷䛒䜛䚹༢⣧䛺ཎ⌮䛻ᇶ䛵䛟䛯䜑䚸」㞧䛺 ᶵᵓ䜔ᅇ㊰䛜せ䛷䛒䜛䚹ᮏᖺᗘ䛿䛣䜜䜎䛷䛾᳨ウᡂᯝ䛻ᇶ䛵䛝 BBM ┦ᙜရ䛾タィ䞉〇స䜢ᐇ୰䛷䛒䜛䚹䛣䛣 䛷䛿㉸㧗㏿ᗘ⾪✺ヨ㦂䛻䜘䜛ᛶ⬟ホ౯䜢୰ᚰ䛻⌧ᅾ䛾◊✲㛤Ⓨ≧ἣ䛻䛴䛔䛶ሗ࿌䛩䜛䚹
Background
䝯䝔䜸䝻䜲䝗䠃䝕䝤䝸䛾⾪✺䝸䝇䜽䛾ホ౯䝣䝻䞊
Design Extraction of
risk components
Design change
M&D
Probability of spacecraft damage Debris
environment model
Impact test Impact analysis Spacecraft
orbit
M&D
environment model
Risk
assessment model
Reject
Countermeasures
model
assessment Accept Orbital plan
Evaluation of Space
An example of risk assessment flow on a spacecraft design
Orbital plan
& design Environment
㉸㧗㏿ᗘ⾪✺䛻䜘䜛ヨ㦂
Examples of hypervelocity impact experiments on electric power harness of satellites
power harness of satellites
Power supply Projectile material
Projectile diameter (ȝm)
Impact velocity (km/s)
Result
60V/2A Al 600 3.97 sustained disruptive discharges
100V/3A Glass 500 4.35 sustained disruptive discharges
100V/3A stainless 300 4 01 sustained disruptive discharges
100V/3A stainless 300 4.01 sustained disruptive discharges
Reference
JERG-2-144-HB001 ’JAXA Space Debris Protection Design Manual Appendix 2‘
Before impact After impact
JERG 2 144 HB001 JAXA Space Debris Protection Design Manual Appendix 2 (published by JAXA, 2008)
Background
䝯䝔䜸䝻䜲䝗䠃䝕䝤䝸䛾⾪✺䝸䝇䜽䛾ホ౯䝣䝻䞊
Design Extraction of
risk components
Design change
M&D
Probability of spacecraft damage Debris
environment model
Impact test Impact analysis Spacecraft
orbit
M&D
environment model
Risk
assessment model
Reject
Countermeasures
model
assessment Accept Orbital plan
Evaluation of Space
An example of risk assessment flow on a spacecraft design
Orbital plan
& design Environment
⎔ቃ䝰䝕䝹䛻䜘䜛⾪✺䝣䝷䝑䜽䝇⟬ᐃ
䝰䝕䝹㛫䛾ᕪ␗
ALOS(
䛂䛰䛔䛱䛃䠅㌶㐨䛾⾪✺䝣䝷䝑䜽䝇
௦⾲ⓗ䛺䝕䝤䝸⎔ቃ䝰䝕䝹䠄䝣䝷䝑䜽䝇䝰䝕䝹䠅䛾ẚ㍑䠄㌶㐨ഴᩳゅ䠖䠍䠍0ᗘ䠅
䠷㉥䠖NASA䛾ORDEM2000 ⥳䠖ESA䛾MASTER 2001 㟷䠖ESA䛾MASTER 2005䠹 䠷㉥䠖NASA䛾ORDEM2000䚸⥳䠖ESA䛾MASTER-2001䚸㟷䠖ESA䛾MASTER-2005䠹>10μm >100μm >1 mm
>10 μm >100 μm >1 mm
Difference among models appeared between 100 μm and 1 cm Difference among models appeared between 100 μm and 1 cm.
>1 cm >10 cm >1 m
ప㌶㐨䛾䝕䝤䝸ほ 䠋ィ ⠊ᅖ ప㌶㐨䛾䝕䝤䝸ほ 䠋ィ ⠊ᅖ
NO DATA
MPAC&SEED (JAXA)
S h ti i f il bl d b i lid ti i LEO
Schematic view of available debris validation sources in LEO
Technical Issues
Technical issues regarding dust particles (meteoroids & space debris) of approx. 100
( & p ) pp
micrometers to several millimeters in size
1. Depending on the size, impact may
d h i h d h
damage the wire harness and other equipment
equipment
2. Space debris flux (number ) for the p ( ) size range not well known
8
᪂つ㛤Ⓨ䝉䞁䝃䛻ᑐ䛩䜛ᶍᨃ䝕䝤䝸䛾㉸㧗㏿ᗘ⾪✺ヨ㦂 䠄
2010ᖺ
2᭶䠅
䠄
2010ᖺ
2᭶䠅
ẁᘧ㍍䜺䝇㖠(ISAS/JAXA)
䠄䝉䞁䝃㠃䝃䜲䝈䠖10cm㽢10cm䚸ཌ䛥25ȝm䠅
ẁᘧ㍍䜺䝇㖠(ISAS/JAXA)
⾲㠃䛾ᣑ
䠄᳨ฟ⥺䛾ኴ䛥䠖䠑
0ʅ䡉䠅
Kitazawa et al., 2010 10
䠄᳨ฟ⥺䛾ኴ䛥䠖䠑
0ʅ䡉䠅
㛤Ⓨ䝉䞁䝃䛾ᴫせ
䠄䠍䠅ᇶᮏᵓᡂ
ཌ䛥㻝㻞㻚㻡䃛㼙䛾⤯⦕ᛶ䛾ⷧ⭷䠄䝫䜲䜲䝭䝗䝣䜱 䠅ୖ ⣙ 䝢 ⣽㛗 ᑟ⥺
䝹䝮䠅ୖ䛻䚸 ⣙㻝㻜㻜䃛㼙䝢䝑䝏䛷⣽㛗䛔ᑟ⥺
䠄ኴ䛥䠖㻡㻜䃛㼙䚸ᮦ㉁䠖㖡䠅䛾䝟䝍䞊䞁䜢ᙧᡂ 䠄ᅗ䠍㻔㼍㻕䠅䚹
䠄䠎䠅ィ ཎ⌮
ᑟ⥺䛾◚᩿䜢㟁Ẽⓗ䛻᳨▱䛩䜛䛣䛸䛻䜘䜚䚸 ᑟ⥺䛾◚᩿䜢㟁Ẽⓗ䛻᳨▱䛩䜛䛣䛸䛻䜘䜚䚸 䝎䝇䝖䛾⾪✺䠄㈏㏻䠅䜢᳨▱䚹
◚᩿䛧䛯ᑟ⥺䛾ᩘ ᑟ⥺䛾ᖜ 䝢䝑䝏䛛䜙䝎
◚᩿䛧䛯ᑟ⥺䛾ᩘ䚸ᑟ⥺䛾ᖜ䚸䝢䝑䝏䛛䜙䝎 䝇䝖䛾䝃䜲䝈䜢ィ 䠄ᅗ䠍㻔㼎㻕䠅 䚹
䠄䠏䠅ィ ᑐ㇟䠋ィ 㡯┠
䠄䠏䠅ィ ᑐ㇟䠋ィ 㡯┠
䞉ィ ᑐ㇟䠖⢏ᚄ㻝㻜㻜䃛㼙௨ୖ䛾䝎䝇䝖 䞉ィ 㡯┠䠖䝎䝇䝖⢏ᚄ䚸⾪✺㢖ᗘ
䠄ⷧ⭷䜢䠎ᒙᵓ㐀䛻ᣑᙇ䛩䜛䛣䛸䛻䜘䜚䚸䝎䝇
11䝖䛾⾪✺㏿ᗘ䞉᪉ྥ䜒ィ ྍ⬟䠅
Improved prototype sensor (FY2009/10)
Stability during sensor performance
Sensor unit (sensor area:10cm㽢10cm) y g p
evaluation
No loss of terminal area.
Yield rates for sensor’s conductive strips
Data (severed signal) discernment 100 %
Signal discernment certainly possible.
Sensor films Detection
The mass of the data acquisition circuit
Total mass of sensor unit: 160 g Circuit units
Total mass: 160g Sensor material: Cu-coated polyimide film
Total mass of sensor unit: 160 g cf. FY2008/09 model: 470 g (without wire-harness)
12
䞊 䝉䞁䝃䛾⊂⮬ᛶ
/᪂つᛶ 䠉
•
ィ 㡯┠䜢⾪✺䝸䝇䜽ホ౯䛷≉䛻㔜せ䛺䛂䝎䝇䝖⢏
ᚄ䚸⾪✺㢖ᗘ䛃䛻⤠䜚䛣䜐䛣䛸䛻䜘䜚䚸䝉䞁䝃ᵓᡂ䛾 ༢⣧䚸ప䝁䝇䝖䠄㍑ṇヨ㦂ᩘ๐ῶ䠅䛜ྍ⬟
•
᪂つ䛾䝉䞁䝃ᵓ㐀䠄ⷧ⭷䜈䛾㈏㏻䜢⏝䠅䜢᥇⏝
䛩䜛䛣䛸䛻䜘䜚 㠃✚ ㍍㔞䛜ྍ⬟䠄ᦚ㍕ᶵ 䛩䜛䛣䛸䛻䜘䜚䚸㠃✚䚸㍍㔞䛜ྍ⬟䠄ᦚ㍕ᶵ
䛾☜ಖ)
•
ᚑ᮶䛾䝉䞁䝃䛷䛿ィ ᅔ㞴䛷䛒䛳䛯㡿ᇦ䠄䛝䛥䠖 䠍㻜㻜㽀㼙䡚ᩘ䡉䡉䠅䛾䝎䝇䝖ィ 䛜ྍ⬟
•
㏿ᗘィ 䚸᪉ྥィ 䛻㛵䛩䜛ᣑᙇᛶ䜢᭷䛩䜛䛯䜑䚸 ᚲせ䛻ᛂ䛨㧗ᗘ䛺ィ 䛜ྍ⬟
13
ᚲせ䛻ᛂ䛨㧗ᗘ䛺ィ 䛜ྍ⬟
Hypervelocity impact experiments on sensor (February 2010)
(February 2010)
P t t d t
Prototype dust sensor
Vacuum level: <5 Pa
Temperature: Room temperature
Two-stage light gas gun (ISAS/JAXA)
p p
14
Experimental conditions
Vacuum level (Pa) <5 Environmental
conditions
Temperature Room temperature Projectile material SUS304, Glass Impact conditions
Projectile diameter (μm)
50 – 516 I t l it (k / ) 1 9 7 0 Impact velocity (km/s) 1.9 – 7.0 Impact angle (㼻) 90
(vertical to sensor surface)
15
Example correspondence between signal and perforation hole signal and perforation hole
50 μm 50 μm
Example perforation hole Example perforation hole on sensor surface
P j il SUS309 Signals of perforation holes
Projectile: SUS309 μm Impact velocity: 4.65 km/s
16
Signals of perforation holes
Experimental results
Projectile dia vs Perforation dia - Projectile dia. vs. Perforation dia. -
Di f j til ( ) D Dia. of projectile (μm): DP
Experimental results
Projectile velocity vs Perforation dia - Projectile velocity. vs. Perforation dia. -
D Hμm): Dhole (μation hperforaa. of p
Projectile velocity (km/s): VP
Dia
SUS projectiles with diameter of 309 μm 18
Experimental results All data
- All data -
DH
DH: dia. of perforation hole n: number of severed strips d: width of conductive strips p: pitch of conductive strips Dia. of perforation hole (μm): DH
19
(n: number of severed conductive strips)
Experimental results All data
- All data --
Debris size and measurement error are accurately estimated estimated.
(n: number of severed conductive strips)
20
(n: number of severed conductive strips)
Study plan for FY2010/11
1. Design & manufacture a BBM model 1 unit are: 35 cm x 35 cm
Space proven manufacturfe methods and parts Space proven manufacturfe methods and parts 2. Envirment tests on a BBM model
Thermal-strain tests
3. Conduct hypervelocity impact experiments on sensor Oblique impactsq p
4. Mission planning (case study)
Effective measurements using small satellites Effective measurements using small satellites
21
Example application on satellitep pp
Dust sensors mounted on Dust sensors mounted on rear surface
of MLI’s first layer
Debris particle
22
ᑠᆺ⾨ᫍࡼࡿィ ࢿࢵࢺ࣮࣡ࢡࡢ
ᑠᆺ⾨ᫍࡼࡿィ ࢿࢵࢺ࣡ ࢡࡢ
Sensor
ᚤᑠ䝕䝤䝸䛿⎔ቃኚືᢕᥱ䛩䜛ୖ䛾᭷ຠ䛺䝟䝷䝯䞊䝍
㸦ex. ASATࡼࡿ⎔ቃኚࠋ㐃㙐⾪✺ࡢࣔࢽࢱࠋ㸧
䠄ඵᆏ
2009䛻䜘䜛䠅Separation
䠄ඵᆏ䠈2009䛻䜘䜛䠅
Separation Mechanism Flange
Real time dust measurement Real time dust measurement network using small satellites
Kitazawa et al., 2009
Summary
1 P t t d l f d t f ll f t d
1 Prototype model of dust sensor successfully manufactured.
Stability during sensor performance evaluation: Stable Stability during sensor performance evaluation: Stable Yield rates for sensor’s conductive strips: 100%
Data (severed signal) discernment: Certainly possible Data (severed signal) discernment: Certainly possible
Total mass of sensor unit: 160 g (Sensing area: 10cm x10cm) cf FY2008/09 model: 470 g without wire harness
.
cf. FY2008/09 model: 470 g without wire-harness
2 Dust sensor performance evaluated by hypervelocity
Projectile diameter estimated from number of signals from
p y yp y
impact experiments
Projectile diameter estimated from number of signals from severed strips .
24
