長谷川 直

JAXA has been developing In-Situ Debris Environment Awareness System. The objective of the system is to measure small size debris (between 100 μm and several cm). The distribution and flux of the debris of the size range are not well understood. The size range is difficult to measure from the ground observation, although the impact risk evaluation on space system caused by the size range is important. For the measurement system on the size range, combination of an optical sensor and a dust detector is under studying by JAXA with JAXA's collaborators. The in-situ measurement of the size range is useful for; 1) verifications of meteoroid and debris environment models, 2) verifications of meteoroid and debris environment evolution models, 3) real time detection of unexpected events, such as explosions and/or collisions on an orbit. In present status, in-situ optical observation system is under conceptual study and a dust sensor is already in BBM (Bread Board Model) phase. This paper reports the study results of measurement system and describes details of the development of dust sensor. The dust sensor especially to monitor the size range 100 μm to a few mm, must have a large detection area, while the constraints of a space environment deployment require that these systems be low in mass, low in power, robust and have low telemetry requirements. JAXA has been developing a simple in-situ sensor to detect dust particles ranging from a hundred micrometers to several millimeters. Multitudes of thin, conductive strips (material: copper) are formed with fine pitch (pitch: 100 μm) on a thin film of nonconductive material (thickness: 12.5 μm, material: polyimide). A dust particle impact is detected when one or more strips are severed by the perforation hole. The sensor is simple to produce and use and requires almost no calibration as it is essentially a digital system. BBM model was manufactured successfully with applying printed wiring board product technology. The sensor area of BBM is 35 cm x 35 cm, and thermal-strain experiments and hypervelocity impact experiments on the BBM model were performed.

第4回スペースデブリワークショップ(2010年12月16-17日, 宇宙航空研究開発機構調布航空宇宙センター)スペースデブリ衝突が無人宇宙機へ与える影響を評価するため,衛星構体パネルに超高速衝突試験を実施した.模擬筐体として厚さ5mmのA2024板をチャンバ内に設置し,その表面に模擬構体パネルとしてアルミハニカムサンドイッチパネルを図のように配置した.直径015-1mmのSUS304球を6km/secで衝突させた飛翔体直径が0.3mm以上の時,飛翔体はハニカムサンドイッチパネル裏面を貫通したⅩ線でハニカムコアを観察すると,飛翔体の衝突でハニカムセルは変形したが,裏面の損傷は飛翔体衝突を受けたセルのみに集中することがわかった.A2024板上に生じたクレータを計測した結果,デブリ直径から最大クレータ深さを導出する実験式を得ることができた.この式から,衛星の筐体厚さはA2024板に生じる最大クレータ深さ以上の厚みが必要であると言える.更に,ハニカムサンドイッチパネルとA2024板の距離を10mm離して設置すれば,最大クレータ深さを約150%低減できることがわかった.形態: カラー図版あり資料番号: AA0064966019レポート番号: JAXA-SP-10-011