Requirements for Debris Mitigation

Propose a post-mission disposal (PMD) or active debris removal (ADR) device that satisfies the following requirements:

1. 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.
2. 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.
3. 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
   Eccentricity	0.001
   R.A.A.N	30 degree
   Argument of Perigee	210 degree
   Mean Anomaly	190 degree

Evaluation Criteria

The proposed deorbit device is evaluated according to the following criteria:

1. Originality (20)
2. Cost (20)
3. Technical feasibility (20)
4. Effectiveness (10)
5. Reliability (10)
6. Debris risk (10)
7. 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?