RU2000128399A - METHOD FOR PROTECTING THE EARTH AGAINST COLLISIONS WITH DANGEROUS SPACE OBJECTS - Google Patents

Claims (2)

1. A method of protecting the Earth from collisions with dangerous space objects (OKO), based on the use of a spacecraft (KA) transported to the OKO by means of delivery and containing an onboard energy source, an energy installation that ensures the operation of low-thrust electric propulsion engines (MTE) to carry out the necessary the removal of the OKO from the Earth to a safe distance, while the thrust of the engines is directed parallel to the speed vector of the OKO, characterized in that the spacecraft is additionally equipped with a metal film and with an aluminum tape with a dielectric substrate, and its delivery is carried out in the vicinity of the OKO, after which the metal film is deployed in space in the form of a surface ensuring its equidistance with respect to the part of the surface of the OKO opposite to the metal film, while the rotation is carried out symmetrically to the axis of the spacecraft, which is oriented to the center of mass of the OKO in the direction of its speed, and the metal tape is moved from the spacecraft to the OKO in a folded form, its end is fixed on the surface of the OKO, for example, using harpoons, and p bend it on the OKO as it rotates around its axis to a full turn with its other end fixed on the surface of the OKO, while the metal tape adheres to the surface of the OKO with a dielectric substrate, then the location of the spacecraft is adjusted to allow electrical interaction between the surfaces of the metal film and the metal tape located on the surface of the OKO, determined by the fact that the distance between the metal film and the metal tape located on the surface of the OKO, It is 0.1. . . 1 is the square root of the area of the metal film, the interaction being created by electrically charging the spacecraft’s metal film from an onboard energy source, and the metal tape located on the surface of the Earth’s surface is charged with ions using ion sources, while the necessary deviation of the Earth’s surface from the Earth by a safe distance provide, maintaining the accepted position of the spacecraft relative to the OKO for the time required to complete this deviation through a system of forces of interaction between the spacecraft and the OKO at Luden equilibrium between the thrust F generated ERE MT, the electrostatic force generated by an electric field strength E, the gravitational force F between the spacecraft and _{the burdens} OKO as determined by the relation
ε ₀ εE ² S / 2 = P ± F _burdens ,
where ε is the relative dielectric constant of the medium;
ε ₀ is the electric constant;
S is the area of the opened film.  2. The method according to p. 1, characterized in that the ring sources with a closed Hall current are used as ion sources.