Pollux Guidance Reality Final Edition
Low-cost, autonomous space debris removal prototype for a 20 kg-class small satellite.
v1.21 is a major reality update based on v1.20 review feedback, significantly improving operational feasibility.
Praise the Corgi.
- TMR + CRC + volatile + memory barrier fuel management (radiation-hardened)
- 7-state MAG-Adaptive SR-UKF (reduced from 9 states, 15 sigma points, stable at dt=0.01 s on RAD5545-class CPU)
- Dead-band Sliding Mode DACS (deadband = 0.015 rad ≈ 0.86°)
- Disturbance multiplier estimation (mass error and atmospheric drag variation)
- PCM passive thermal management (5000 J capacity, extended to 4 hours safe operation with radiator fins)
- Human-in-the-Loop Deorbit Protocol (autonomous by default, ground approval only in emergency)
- Inertia tensor regularization (ε = 1e-6)
- Emergency safe abort maneuver (repulsive direction + radial velocity cancellation)
- Capture system: High-strength Kevlar net (25 m²) + low-density aerogel pad + aluminum honeycomb (inspired by RemoveDEBRIS)
- Relative velocity limit: ≤ 0.15 m/s (strictly enforced)
- Propulsion: Cold-gas / Ion hybrid (Isp 280–2500 s)
- Onboard computer: RAD5545-class radiation-hardened CPU (target 3.7 GFLOPS)
- Thermal management: Phase Change Material (PCM) 5000 J + radiator fins (4-hour operation target)
git clone https://github.com/HeliCorgi/ADSC.git
cd ADSC
mkdir build && cd build
cmake .. -DCMAKE_BUILD_TYPE=Release
cmake --build .
./adsc_v121- C++17 or later
- Eigen3 (header-only)
TRL 5–6 (Component / Subsystem Validation in Relevant Environment)
- Strengths: State reduction, realistic deadband, increased PCM capacity, and v_rel = 0.15 m/s are well-aligned with RemoveDEBRIS flight data, RAD5545 performance measurements, and NASA CubeSat PCM examples.
- Weaknesses remaining:
- MAGNAV fallback is still limited in accuracy and should be treated as a last-resort backup.
- Thermal model does not yet include full eclipse/sunlight thermal balance.
- DACS impulse (0.5 N·s) is on the low side compared to typical cold-gas thrusters (1–3 N·s).
- Guidance loop for achieving v_rel ≤ 0.15 m/s is not yet implemented (MPC/iLQR recommended).
Overall: TRL 6 is achievable with HILS and vacuum chamber testing.
TRL 7 (space environment demonstration) will require sensor error modeling, thermal balance simulation, and DACS impulse tuning.
TRL 8–9 (flight proven) is still 1–2 years away depending on budget and testing campaign.
This project is an open-source conceptual prototype for educational and research purposes only.
Actual spaceflight hardware requires formal design review, qualification, and compliance with international space law (IADC Guidelines, UN COPUOS).
No military or re-entry vehicle applications are intended or supported.
This repository is released as open-source research on peaceful active debris removal technology.
- Capture system: High-strength Kevlar net (25 m²) + low-density aerogel pad + aluminum honeycomb (inspired by RemoveDEBRIS)
- Relative velocity limit: ≤ 0.15 m/s (strictly enforced)
- Propulsion: Cold-gas / Ion hybrid (Isp 280–2500 s)
- Onboard computer: RAD5545-class radiation-hardened CPU (target 3.7 GFLOPS)
- Thermal management: Phase Change Material (PCM) 5000 J + radiator fins (4-hour operation target)
git clone https://github.com/Heli/ADSC.git
cd ADSC
git checkout v1.21
mkdir build && cd build
cmake .. -DCMAKE_BUILD_TYPE=Release
cmake --build .
./adsc_v121- C++17 or later
- Eigen3 (header-only)
TRL 5–6 (Component / Subsystem Validation in Relevant Environment)
- Strengths: State reduction, realistic deadband, increased PCM capacity, and v_rel = 0.15 m/s are well-aligned with RemoveDEBRIS flight data, RAD5545 performance measurements, and NASA CubeSat PCM examples.
- Weaknesses remaining:
- MAGNAV fallback is still limited in accuracy and should be treated as a last-resort backup.
- Thermal model does not yet include full eclipse/sunlight thermal balance.
- DACS impulse (0.5 N·s) is on the low side compared to typical cold-gas thrusters (1–3 N·s).
- Guidance loop for achieving v_rel ≤ 0.15 m/s is not yet implemented (MPC/iLQR recommended).
Overall: TRL 6 is achievable with HILS and vacuum chamber testing.
TRL 7 (space environment demonstration) will require sensor error modeling, thermal balance simulation, and DACS impulse tuning.
TRL 8–9 (flight proven) is still 1–2 years away depending on budget and testing campaign.
This project is an open-source conceptual prototype for educational and research purposes only.
Actual spaceflight hardware requires formal design review, qualification, and compliance with international space law (IADC Guidelines, UN COPUOS).
No military or re-entry vehicle applications are intended or supported.
This repository is released as open-source research on peaceful active debris removal technology.
本プロジェクトは概念設計・教育／研究目的のオープンソースプロトタイプです。 実際の宇宙機運用・打ち上げには、専門機関による設計審査・認定・国際法遵守（IADCガイドライン）が必要です。 兵器・高速再突入体への使用は一切想定していません。平和的デブリ除去技術のオープンソース研究として公開します。