第 8 回 スペースデブリワークショップ 講演資料集 383 B17 模擬 SRM スラグ飛翔体を用いた超高速衝突実験計画 Experimental Plan of Hypervelocity Impact Using Simulated SRM Slag 赤星保浩 ( 九州工業大学 ), 東出真澄
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1 第 8 回 スペースデブリワークショップ 講演資料集 383 B17 模擬 SRM スラグ飛翔体を用いた超高速衝突実験計画 Experimental Plan of Hypervelocity Impact Using Simulated SRM Slag 赤星保浩 ( 九州工業大学 ), 東出真澄 (JAXA), 田上翔悟, 池田仁哉, 吉田冬威, 花草孝史, 古賀想大, 高良隆男 ( 九州工業大学 ) Yasuhiro Akahoshi (Kyutech), Masumi Higashide (JAXA), Shogo Tagami, Masaya Ikeda, Toui Yoshida, Takafumi Hanakusa, Sota Koga and Takao Koura (Kyutech) アルミニウム粉を含む固体ロケットエンジンではノズル手前の淀み点近傍において 燃焼後アルミナが凝集される傾向があり 固体ロケットエンジン停止前後においてこの凝集されたアルミナの塊 (SRM スラグ ) が放出される可能性がある 一段目の固体ロケットエンジンは軌道速度に到達しないので大きな問題とはならないが 二段目以降で地球に対する周回軌道に入る場合 この SRM スラグも軌道速度を獲得し スペースデブリとして周回する可能性がある ISO24113 の改定作業過程において ヨーロッパを中心に SRM スラグに対する規制を強める方向で議論が進んだ そこで 本研究では SRM スラグが仮にスペースデブリとして周回軌道に入ってしまったとして どの程度の危険性を有するのか 地上試験で SRM スラグを模擬した飛翔体を用意し 同じ大きさのアルミ球との比較を行う超高速衝突実験を立案することとした 本講演では この実験計画ならびに予備実験について講演を行う予定である Alumina particles trend to gather one another after combustion near stagnation point upper than nozzle of a solid rocket motor containing aluminum powder. Although there is no serious problem because the first solid rocket motor will not reach the earth orbit, SRM slag will reach the earth orbit and will go around the earth as space debris. In the process of revision of ISO24113, European P-members insisted to add regulation for SRM slag. So then in this we will study potential danger of SRM slag on space structures such as artificial satellites and so on if SRM slag goes around the earth orbit as space debris. Namely we will consider a plan of hypervelocity impact tests using a projectile which imitates SRM slag as well as aluminum sphere. In this presentation, we will address its experimental plan and some results of preliminary experiments.
2 384 宇宙航空研究開発機構特別資料 JAXA-SP th Space Debris Workshop Yasuhiro Akahoshi(Kyutech), Masumi HIGASHIDE(JAXA), Shogo TAGAMI(Kyutech), Masaya IKEDA, Toui YOSHIDA, Takafumi HANAKUSA, Sota KOGA, Takao KOURA Department of Mechanical Engineering, Kyushu Institute of Technology 1 Outline of Today s Presentation Department of Mechanical Engineering, Kyushu Institute of Technology 2
3 第 8 回 スペースデブリワークショップ 講演資料集 385 Outline of Today s Presentation Department of Mechanical Engineering, Kyushu Institute of Technology 3 SRM Slag Background ~~ SRM Slag (ref.: Sinya FUKUSHIGE, Yasuhiro AKAHOSHI, Yukihito KITAZAWA, Takeo GOKA, Comparison of Debris Environment Models; ORDEM2000, MASTER2001 and MASTER2005, IHI Engineering Review Vol. 40 No. 1 February (2007), p ) Total amount of debris 1 mm Generation causes of debris calculated by MASTER 2005 SRM Slag could be the second dominant between 0.1-1mm
4 386 宇宙航空研究開発機構特別資料 JAXA-SP Department of Mechanical Engineering, Kyushu Institute of Technology 5 6 Technical requirements 6.1 Avoiding the intentional release of space debris into Earth orbit during normal operations Space debris from pyrotechnics and solid rocket motors Solid rocket motors shall be designed and operated so as not to release space debris larger than 1 mm in their largest dimension into Earth orbit. NOTE The main aim of this requirement is to limit the generation of slag debris ejected into Earth orbit during the final phase of combustion. Slag debris is potentially hazardous to current and future space operations due to its size, number and orbital lifetime. This is particularly the case when slag debris is ejected into a high orbital region where it can pose an impact risk for a long period of time. Department of Mechanical Engineering, Kyushu Institute of Technology 6
5 第 8 回 スペースデブリワークショップ 講演資料集 387 WG1 Design WG2 Integ./ test WG3 Operations WG4 Environment WG5 Management WG6 Materials WG7 Debris ISO24113 is discussed in joint session between WG3 and WG7. 7 Crater Depth D c = 5.52 d H 1 4 ρ 1 % ( 2 % p ' * V p ' & ) & c ρ t d p : the projectile diameter H : Brinell hardness ρ p : the density of the projectile ρ t : the density of the t arget c : the sound velocity of the t arget ( * ) 2 3 8
6 388 宇宙航空研究開発機構特別資料 JAXA-SP Technical requirements 6.1 Avoiding the intentional release of space debris into Earth orbit during normal operations Space debris from pyrotechnics and solid rocket motors Solid rocket motors shall be designed and operated so as not to release space debris larger than 1 mm in their largest dimension into Earth orbit. There is no description on density of SRM Slag in Department of Mechanical Engineering, Kyushu Institute of Technology 9 Literature Survey of Density of SRM Slag ( A67= % UNV S K GP% ) (, )%/ I g BCB 3P) r ) Density of SRM Slag is ) =3BC7A ) 0 G KUG K VPG JK VN %, I =3BC7A g BNKHSPJ K GP% (00 BA= %, I =3BC7A distributed =3BC7A KU GP N V PG NS NV (%/ I between 1.6,(g + 7:C: (00, (%-, )%+ ( %( BA= 3KUSVTGIKo g I A7 AC % CA 0,,) ( /g 61 U g Ter I, 3 B K GP% (00. =3BC7A 0g - 3 C K GP% (00, 3:33 0, ).)0 and 2.6 g/cm 3. BA= I T,- ) (%(). e e (Summarized by Dr.Kitazawa) ( %) ( (%. ( (%-., (%-. ( (%-. I g ). )%,0 )/ )%+/, (%-0 g
7 第 8 回 スペースデブリワークショップ 講演資料集 389 Outline of Today s Presentation Department of Mechanical Engineering, Kyushu Institute of Technology 11 Guns in KIT (1/2) Large LGG Small LGG Air gun Pictures Length [m] Bore[mm] 5, 14, Pump tube[mm] Velocity [km/sec] ~ 5 ~ 5 ~ 0.3 Velocity measurement Research topics Wire-cut Deflection of asteroid Laser-cut Eject test based on International standardization Discharge test of solar array Laser-cut Highspeed camera Development fan case of jet engine
![1 1 1 Bore[mm] 10, 20 5 5x20 Velocity [m/sec] 20-100 2000 200 Velocity measurement Highspeed camera](/docs-images/103/157308435/images/8-4.jpg "Photo-detector laser-cut Research topics Harpoon for ADR No experiment No experiment Guns in KIT (1/2) Large")
![LGG Small LGG Air gun Pictures Length [m] 7 3 3 Bore[mm] 5, 14, 30 5 25 Pump tube[mm] 60 20 - Velocity [km/sec]](/docs-images/103/157308435/images/8-5.jpg "~ 5 ~ 5 ~ 0.")
8 390 宇宙航空研究開発機構特別資料 JAXA-SP Guns in KIT (2/2) Single stage gun Plasma drug gun Rail gun Pictures Length [m] Bore[mm] 10, x20 Velocity [m/sec] Velocity measurement Highspeed camera Photo-detector laser-cut Research topics Harpoon for ADR No experiment No experiment Guns in KIT (1/2) Large LGG Small LGG Air gun Pictures Length [m] Bore[mm] 5, 14, Pump tube[mm] Velocity [km/sec] ~ 5 ~ 5 ~ 0.3 Velocity measurement Research topics Wire-cut Deflection of asteroid Laser-cut Eject test based on International standardization Discharge test of solar array Laser-cut Highspeed camera Development fan case of jet engine
9 第 8 回 スペースデブリワークショップ 講演資料集 391 Test Facility Witness plate Sabot separation plate Velocity measurement section Launch tube Pump tube powder room Target Test chamber 1 Pa Polyester film Sabot separation section 7 kpa High pressure coupling Blast tank Two-stage light gas gun Material A2017 Diameter φ mm Mass : 1.5 mg Material PC Diameter φ6.0mm Mass : 120 mg Projectile Sabot 15 16
10 392 宇宙航空研究開発機構特別資料 JAXA-SP Experimental condition Target 100 mm Witness plate Projectile Configuration diagram of target Projectile Material : aluminum (Al2017) Shape : sphere Size : diameter of 1mm Impact velocity: around 5km/sec Target Material : synthetic fused silica Size : 50 x 50 x 20mm Supporter : sponge rubber Witness Plate Material : Copper (JIS H3100 C1100-1/4H) Hole diameter : 30 mm at its center Surface : machined finish Witness plate is in 100 mm front of target High-speed Video Experimental results Shot No V= 4.03 km/sec, Witness plate Target: 100 mm Recoding rate: 250 kfps, Pixels: 312 x 260 pixels
11 第 8 回 スペースデブリワークショップ 講演資料集 393 ü Discharge by debris impact High density plasma is created by debris impact Discharge occurs through the plasma : Primary Arc (PA) NASA The Orbital Debris Quarterly News Vol.18-4 (2014, Oct) Permanent Sustained Arc (PSA) Electricity does not flow to the payload and the power generation capacity is reduced Department of Mechanical Engineering, Kyushu Institute of Technology 19 IADC Month Year Spacecraft Component Vulnerability for Space Debris Impact 2 Solar Array Issued by IADC Working Group 3 Action Item 31.3 Table of Contents Revision History... List of Authors... List of Affiliations... Scope... 1 Risk Assessment for Spacecraft... 2 Solar Array Damage Mode Impact Experiments and Numerical Simulations / KIT Summary of Conditions and Results Details Recommendation for MMOD risk reduction References... 3 Cables Damage Mode In recent years, a solar array of a spacecraft has become larger with the voltage higher because a spacecraft needs a large amount of power in requests from an advanced mission. Therefore the risk of a space debris impact and discharge on the solar array is increasing because the number of small space debris such as ejecta is increasing [2-1]. Space debris impact to the solar array causes not only mechanical damage such as destruction of a solar cell and insulation layer but also electrical damage due to local high density plasma induced by impact energy [2-2]. This plasma can lead to arcing between solar cells or cell and substrate on the solar array [2-3]. In the worst case, Joule heating of arcing can carbonize insulation layer and create permanent short-circuit path [2-4]. This phenomena is called Permanent Sustained Arc (PSA). Department of Mechanical Engineering, Kyushu Institute of Technology Impact Experiments and Numerical Simulations / KIT
![Voltage [V] Current [A] Discharge Type Resistance [Ω] Time [µs] 18-018 192 4.](/docs-images/103/157308435/images/12-5.jpg "8 PSA 10 Impact point PSA generation condition (192V) Waveform of discharge Discharge time needs more than 2 μs")
12 394 宇宙航空研究開発機構特別資料 JAXA-SP Measurement Positions of Current Probes in Electric Circuit used at Discharge Test due to Hypervelocity Impact Department of Mechanical Engineering, Kyushu Institute of Technology 21 Test No. Voltage [V] Current [A] Discharge Type Resistance [Ω] Time [µs] PSA 10 Impact point PSA generation condition (192V) Waveform of discharge Discharge time needs more than 2 μs Maximum discharge current needs about 3 A 22
13 第 8 回 スペースデブリワークショップ 講演資料集 395 Outline of Today s Presentation Department of Mechanical Engineering, Kyushu Institute of Technology 23 Target Witness Plate Figure C.1 Sketch of target and witness plate assembly Figure C.2 Picture of target and witness plate set-up Test impact configuration is based on Annex C of ISO Department of Mechanical Engineering, Kyushu Institute of Technology 24
14 396 宇宙航空研究開発機構特別資料 JAXA-SP Experimental Conditions Using Imitated Projectile Projectile : A2017, φ1mm with/without 0.3mm perforation hole Target : A2024-T3 plate, 80 x 100 x 6 mm Impact Velocity : 5km/s Experimental Results Shot No. KIT KIT KIT Diameter of Projectile [mm] Mass of Projectile [mg] mm perforation hole No Yes Yes Impact Velocity [km/s] Diameter of Crater [mm] Depth of Crater [mm] Volume of Crater [mm 3 ] Mass of Ejecta [mg] Department of Mechanical Engineering, Kyushu Institute of Technology 26
15 第 8 回 スペースデブリワークショップ 講演資料集 397 Experimental Results Shot No. KIT KIT Diameter [mm] Projectile Mass [mg] mm hole No Yes Velocity [km/s] Diameter [mm] Crater Depth [mm] Volume [mm 3 ] Department of Mechanical Engineering, Kyushu Institute of Technology 27 Current status of conventional impact tests using simulated SRM slag projectiles 12 porous alumina balls were given to Kyutech by JAXA and conventional impact tests will be done next month in Kyutech. Department of Mechanical Engineering, Kyushu Institute of Technology 29
16 398 宇宙航空研究開発機構特別資料 JAXA-SP Outline of Today s Presentation Department of Mechanical Engineering, Kyushu Institute of Technology 30 Porosity of SRM Slag could be 30% and it could be very fragile. So then it could be broken during acceleration (>10 4 G) in a twostage light gas gun. Reverse Impact should be introduced. Department of Mechanical Engineering, Kyushu Institute of Technology 31
![第 8 回 スペースデブリワークショップ 講演資料集 399 Guns in KIT (1/2) Large LGG Small LGG Air gun Pictures Length [m] 7 3 3 Bore[mm] 5, 14, 30 5 25 Pump tube[mm] 60 20 - Velocity [km/sec] ~ 5 ~ 5 ~ 0.](/docs-images/103/157308435/images/17-0.jpg "3 Velocity measurement Research topics Wire-cut Deflection of asteroid Laser-cut Eject test based on International standardization Discharge test of solar array Laser-cut Highspeed camera Development")
17 第 8 回 スペースデブリワークショップ 講演資料集 399 Guns in KIT (1/2) Large LGG Small LGG Air gun Pictures Length [m] Bore[mm] 5, 14, Pump tube[mm] Velocity [km/sec] ~ 5 ~ 5 ~ 0.3 Velocity measurement Research topics Wire-cut Deflection of asteroid Laser-cut Eject test based on International standardization Discharge test of solar array Laser-cut Highspeed camera Development fan case of jet engine Concept of Counter-Impact (FY2006) Delay Controller Condenser Bank Trigger Sensors Test Chamber Guide Rail System Large-TSLGG f30 Bumper Target 4 km/s Flash X-ray Systems Defense Wall ETC-TSLGG f3 Al ball 6 km/s Target Projectile
18 400 宇宙航空研究開発機構特別資料 JAXA-SP Soft recover system Reverse Impact Test Test Chamber Recovery Material Pickup Coil Free Fright Section Launch Tube Impact Position 2.5m (Section 3) 2.0 m (Section 2) 1.4 m (Section 1) 5.9 m Target projectile Guide rail for target projectile Pickup coil Example of recovered target projectile Successfully recover of target projectile
19 第 8 回 スペースデブリワークショップ 講演資料集 401 Flash X-ray image of secondary debris cloud in reverse impact test Aluminum ball Fig. V = 2.27 km/s (LTS06-60) Another Reverse Impact Test (FY2013) Sample return from surface of asteroid Fig. Sampler fixed in impact axis. 38
20 402 宇宙航空研究開発機構特別資料 JAXA-SP Experimental Result of Reverse Impact (a) t 83µs (b) t + 13µs (c) t + 59µs (d) t + 103µs Fig. Snapshots of Reverse Impact (V=0.969 km/s) 39 Current status of reverse impact tests using imitated and simulated SRM slag projectiles (1) Porous alumina balls were given by JAXA and reverse impact tests are under preparation in Kyutech. (2) Manufacturer of porous alumina ball (same size, same mass (same density), and spherical shape are ideal) is looked for by JAXA. Department of Mechanical Engineering, Kyushu Institute of Technology 40
21 第 8 回 スペースデブリワークショップ 講演資料集 403 Outline of Today s Presentation Department of Mechanical Engineering, Kyushu Institute of Technology 41 Closure In Draft IS24113 it is written that solid rocket motors shall be designed and operated so as not release space debris larger then 1mm in their largest dimension into Earth orbit. Draft IS24113 is now under DIS voting. Preliminary experiments using imitated projectile were successfully done in the manner of conventional impact. Reverse impact test is under consideration instead of acceleration of a fragile projectile which is made of 30% porous alumina. Density of SRM slag was reviewed based on published papers, and it is distributed between 1.6 and 2.6 [g/cm 3 ]. Department of Mechanical Engineering, Kyushu Institute of Technology 42
22 404 宇宙航空研究開発機構特別資料 JAXA-SP Thank you for your attention. Department of Mechanical Engineering, Kyushu Institute of Technology 43
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