Requirements for Debris Mitigation
Propose a post-mission disposal (PMD) or active debris removal (ADR) device that satisfies the following requirements:
- The device must be designed for the removal of a potentially non-cooperative lean satellite of 50 kg mass and maximum dimension of 1 meter. Total mass of a satellite and device can exceed 50 kg.
- The device will enable the satellite to re-entry within 11 years (i.e. one solar cycle) after activating. You can use any systems such as thruster, tether, membrane or electric propulsion.
- The device will be activated at 00:00:00 UTC, January 1, 2020 with the following orbit element:
|Semi-major axis||7128 km|
|Orbital inclination||98.4 degree|
|Argument of Perigee||210 degree|
|Mean Anomaly||190 degree|
The proposed deorbit device is evaluated according to the following criteria:
- Originality (20)
- Cost (20)
- Technical feasibility (20)
- Effectiveness (10)
- Reliability (10)
- Debris risk (10)
- Impact on/for satellite (10)
- 1. Originality
- Has the idea not yet been realized or proposed? Is there enough originality in the idea?
- 2. Cost
- Is it affordable for lean space missions?
- 3. Technical feasibility - Mechanical and electrical design
- Can the idea be realized with current or emerging technology?
- 4. Effectiveness
- How effective and how fast can the satellite re-enter?
- 5. Reliability
- Is the idea designed to fail with a low probability?
- 6. Debris risk
- Does the idea generate risks in producing additional debris? Will it function even if the satellite is non-cooperative?
- 7. Impact on/for satellite
- What is the mass, volume, power and operational requirement on/for the satellite to be removed?