概要：
This paper presents SATEBAL, a CubeSat mission designed to demonstrate a semi-passive orbital attitude stabilization and deorbiting strategy integrating a controllable deployment mechanism. The system consists of two main phases: passive attitude control using deployable booms with tip masses and accelerated orbital decay via a deployable drag sail. In the first phase, the CubeSat's mass distribution on the booms is adaptively tuned to passively stabilize its orientation under gravity gradient torque by optimizing the principal moments of inertia. A FreeRTOS-based OBDH system enables precise real-time coordination of control tasks. In the second phase, a cross-shaped Mylar sail is deployed to enhance atmospheric drag, ensuring the satellite reenters within 70 days, as verified by STK simulations. Aerodynamic modeling, using Free Molecular Flow and Response Surface Methodology, validates drag coefficients under varying flow conditions. A hybrid ADCS combining passive and magnetorquer-based active control is proposed, with Lyapunov-based stability guarantees under external disturbances. Structural and thermal analyses confirm mission viability. This mission provides a compact, energy-efficient platform for attitude control and post-mission disposal, supporting future CubeSat designs aiming for agility and sustainability in low Earth orbit operations.

概要：
本ミッションでは，接着型膜展開デバイスによる新たなActive Debris Removal（ADR）手法を提案する．従来は事前に宇宙機に搭載するPost Mission Disposal（PMD）デバイスとして利用されていた膜展開式軌道離脱装置DOM®に，接着機構を搭載しADRデバイスへと拡張する．接着機構付きDOM®をターゲットに向けて射出し，接着させることにより，運用終了後の宇宙機に後付けでDOM®を付与し，膜による大気抵抗で軌道降下を実現する．本アイデアは，1台の衛星で複数のデブリ除去が可能であり，既存装置を応用しているため実現可能性も高い．

概要：
This paper presents SATEBAL, a CubeSat mission designed to demonstrate a semi-passive orbital attitude stabilization and deorbiting strategy integrating a controllable deployment mechanism. The system consists of two main phases: passive attitude control using deployable booms with tip masses and accelerated orbital decay via a deployable drag sail. In the first phase, the CubeSat's mass distribution on the booms is adaptively tuned to passively stabilize its orientation under gravity gradient torque by optimizing the principal moments of inertia. A FreeRTOS-based OBDH system enables precise real-time coordination of control tasks. In the second phase, a cross-shaped Mylar sail is deployed to enhance atmospheric drag, ensuring the satellite reenters within 70 days, as verified by STK simulations. Aerodynamic modeling, using Free Molecular Flow and Response Surface Methodology, validates drag coefficients under varying flow conditions. A hybrid ADCS combining passive and magnetorquer-based active control is proposed, with Lyapunov-based stability guarantees under external disturbances. Structural and thermal analyses confirm mission viability. This mission provides a compact, energy-efficient platform for attitude control and post-mission disposal, supporting future CubeSat designs aiming for agility and sustainability in low Earth orbit operations.

概要：
This paper presents SATEBAL, a CubeSat mission designed to demonstrate a semi-passive orbital attitude stabilization and deorbiting strategy integrating a controllable deployment mechanism. The system consists of two main phases: passive attitude control using deployable booms with tip masses and accelerated orbital decay via a deployable drag sail. In the first phase, the CubeSat's mass distribution on the booms is adaptively tuned to passively stabilize its orientation under gravity gradient torque by optimizing the principal moments of inertia. A FreeRTOS-based OBDH system enables precise real-time coordination of control tasks. In the second phase, a cross-shaped Mylar sail is deployed to enhance atmospheric drag, ensuring the satellite reenters within 70 days, as verified by STK simulations. Aerodynamic modeling, using Free Molecular Flow and Response Surface Methodology, validates drag coefficients under varying flow conditions. A hybrid ADCS combining passive and magnetorquer-based active control is proposed, with Lyapunov-based stability guarantees under external disturbances. Structural and thermal analyses confirm mission viability. This mission provides a compact, energy-efficient platform for attitude control and post-mission disposal, supporting future CubeSat designs aiming for agility and sustainability in low Earth orbit operations.

概要：
火星のメデューサ・フォッサエ層に着陸するランダーにソーラーアレイと小型風力タービンを搭載し、夜間やダストストーム時における継続的な電力供給の確保と、火星大気中の風力エネルギーの回収・利用技術の実証を目的とする。火星のような低レイノルズ数環境であっても、太陽光や原子力に代わる代替エネルギー源として風力の活用可能性を立証することを目指す。これにより、今後の有人探査や火星拠点建設においても、新たなエネルギー供給手段としての応用が期待される。加えて、風成地形が発達し、地下に水氷の存在が示唆される、メデューサ・フォッサエ層での探査を通じて、古代の気候変動や、生命の痕跡に関する新たな知見の獲得も期待される。

概要：
微小デブリ分布情報を取得するため，大面積（150m2）の薄膜を宇宙空間に長期曝露し，膜の表面にデブリ衝突痕を蓄積する衛星「DIAR-Sat」を提案する．膜はリエントリーカプセル内から展開され，3 年間の観測期間終了後に再収納される．その後はリエントリーカプセルを大気圏に再突入させ，地上回収した膜の表面検査によりデブリ衝突痕データを取得する．得られたデータにより，ORDEM やMASTERといったデブリ環境モデルの推定精度向上やモデル間の推定結果の乖離是正を期待できる．

概要：
土星の衛星タイタンの大気に特徴的なスーパーローテーションの原理の解明は，惑星大気の物理過程の理解に大きく寄与し，また太陽系外の惑星の大気環境を理解する上で重要である．本ミッションでは，タイタンの大気環境を衛星間電波掩蔽観測によって全球的かつ高分解能に観測することで，スーパーローテーションのメカニズム解明をはじめとする様々な理学的研究に貢献することを目指す．