The space debris problem emerged in the second half of the 20th century with the launch of first artificial Earth satellites. Left at earth orbits, space objects began to pose a threat to functioning spacecraft and, in particular, to stations with crews on board.

With the expansion of space exploration the population of space debris began to grow rapidly. It required appropriate measures to be taken. In 1993, a number of space agencies created the Inter-Agency Space Debris Coordination Committee (IADC). The primary purposes of this organization are to exchange information between committee members, to facilitate opportunities for cooperation, and to identify debris mitigation options. This committee has developed the “IADC Space Debris Mitigation Guidelines”.

Ukraine has also developed and adopted an appropriate document “Limitation of Near-Earth Orbital Debris Making at Operation of Space Technical Equipment” from July 19th, 2006 which dictates fundamental rules of space activities in Ukraine. All basic regulations of this document correspond to the Inter-Agency Space Debris Coordination Committee’s international recommendations.

Currently, many leading space companies are developing space debris removal systems. These systems can conditionally be divided into two types: passive and active ones.

Passive systems are mounted onto objects that have to be deorbited in advance, and are activated after their mission’s complete. These systems can use different physics for deorbitation. The Yuzhnoye State Design Office proposes devices the operation principle of which lies in augmentation of their aerodynamic drag force by creating a large surface area due to inflation/deployment of special structures.

Active systems represent autonomous spacecraft able to deorbit space debris objects and/or remove them to special graveyard orbits.

Active systems

LEOSWEEP PROJECT

Currently, the Yuzhnoye State Design Office in cooperation with other Ukrainian organizations is taking part in an international project LEOSWEEP, which is partially funded by the European Union within the 7th Framework Program.

This project is to investigate the possibility to deorbit large objects (e.g. launch vehicle stages) from near-Earth orbits with an ion beam created on board a spacecraft orbiting nearby a space debris object.

SPACE SYSTEM FOR ACTIVE SPACE DEBRIS REMOVAL

The Space System is designed for effective deorbitation of medium-size space debris objects (with weights up to 1,000 kg and 5 m across) from low Earth orbits (up to 1,000 km).

The Space System includes:

• Interceptor Spacecraft equipped with a set of modules for capturing and deorbiting of space debris objects;
• Ground control station.

Deorbitation time of a 1,000-kg space debris object from an altitude of 1,000 km is one and a half orbit passes.

Passive systems

INFLATABLE DRAG SYSTEM

The Inflatable Frame Drag System consists of an inflatable frame and a ball-shaped shell. The frame represents a tubular structure that consists of hermetic elements.

The length of the sleeve elements is chosen in such a way that, when operating, the inflatable frame’s shape would ensure the stretching of external shell close to the form of a sphere.

Inflating of the frame is conducted through separate sleeves each of which fills with gas its own frame element. The system does not lose its operability even if one of the frame elements is damaged by space debris.

Technical characterictics

• The system’s weight is no more than 3% of that of the space debris object.
• Material: polyethylene terephthalate film with external aluminum metallization, the film thickness is 6 microns. External metallization ensures the shell’s protection from atomic oxygen and ultraviolet radiation in space.
• The system’s shaping is ensured by inflation of the frame from a special gas source.
• Pressurant: nitrogen. Inflatable structures’ shells are filled with gas through dedicated sleeves (gasways).

SAIL DRAG SYSTEM

The removal system with self-deploying beams is done in the form of a four-sided pyramid attached to the object with its top. The base is a regular square. Four lateral sides of the pyramid are formed by triangular sails attached to the beams that are situated along four edges of the pyramid.

The size and form of the system are chosen in terms of ensuring the pyramid’s average cross area of 178 m2, and minimization of dimensions and weight of the system in a transportation position. The sail system switches to its operating position due to accumulated strain energy of the rolled beams.

Technical characterictics

• The system’s weight is 20 kg which is 1% of that of the space debris object (3rd stage of “Cyclone-4” LV).
• Material: polyimide film, the film thickness is 12 microns.
• In transportation position: volume ~ 45 dm3, dimensions: diameter ­­– 532 mm, height – 204 mm.
• In operating state: beam length is 13.5 m, angle between the beam and the pyramid base – 15°, base dimensions – about 18x18 m.

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