Abstract: A method and respective system for delivering cargoes into space by means of preliminary launching cargoes and then capturing cargoes by at least one container spacecraft, accumulating and further transferring to other spacecrafts, wherein the container spacecraft is designed for capturing cargoes as separate portions in the form of a cloud or stream as well as for use of a propulsion system to compensate for container spacecraft speed losses caused by the cargo capture and an aerodynamic drag, wherein the propulsion system being a reactive type with consumption of a part of the incoming cargoes as a working substance.

Abstract: A method for feeding a ramjet of a spacecraft beyond the dense layers of the atmosphere includes providing a fueling apparatus having an amount of a propellant for feeding a ramjet of the spacecraft. The propellant is ejected from the fueling apparatus in form of a solid and flexible propellant cord, wherein said propellant cord being placed on a flight path of the spacecraft. The solid and flexible propellant cord enters into the ramjet of the spacecraft. At least a part of a propellant of the solid and flexible propellant cord is used for feeding the ramjet. The cord includes an amount of a propellant stabilized in density relating to an environmental air by introducing one or more linear elements selected from ribbons, threads, or fibers, reticulate or membrane structures.

Abstract: The invention relates to the energy provision of space transport systems and to the organization of a load flow between spacecraft in planetary orbits. The method comprises a spacecraft tank trapping and accelerating atmospheric air and loads located in the trajectory of movement thereof. The loads are transported beforehand to said trajectory by corresponding spacecraft, including suborbital spacecraft, and are then transferred to other spacecraft. Velocity losses of the spacecraft tank due to the trapping and accelerating of atmospheric air, loads and to aerodynamic drag are compensated for by a propulsion unit. The propulsion unit may use reactive engines—with consumption of part of the incoming load—or electrodynamic cable systems. Operation of the propulsion unit of the spacecraft tank is ensured by a supply of load energy carriers using atmospheric gases.

Abstract: The inventions relate to engine systems of space transportation means. The method is carried out with the aid of a system which comprises a spacecraft (KLA/SC) with a propulsive jet engine (1) and a device (2) for storing a working substance (one of a fuel components). The system is also provided with a flying fueling apparatus (3) with a system for throwing a working substance (another fuel component). The system (4) forms a stabilized jet (5) of the working substance by means of one or more linear elements (threads, ribbons etc) or on a base of concentrated liquids and solid materials. As a result, a cord (5) for multiple or single use is formed. According to the method, the KLA/SC with the propulsive jet engine (1) and the flying fueling apparatus (3) with the working substance reserve are first launched. At a desired altitude, the working substance is ejected, from the flying fueling apparatus (3), in the form of the cords (5) the density of which are greater than the density of the environmental air.

Abstract: A method for delivering space cargo including inserting one or more container spacecrafts (CSCs) into orbit. A CSC comprises a hull, a device for receiving cargoes (an artificial medium), a braking medium container, an arrangement for separating the cargoes and the braking medium, storage tanks, a propulsion system, a satellite solar power station, and also heat dissipaters for cooling the braking medium. To compensate for loss of speed during cargo capture, the CSCs use propulsion systems supplied with power from said power station. A reactive-type propulsion system in which a part of the incoming cargo is consumed can be used as such system.