A spacecraft for the distribution of electrical energy to client craft at points situated in free space, in orbit and/or on a celestial body includes a main structure equipped with an electric thruster, with a chemical thruster and with a solar generator, a first fuel container for fuel intended for the electric thruster, and a second fuel container for fuel intended for the chemical thruster. The spacecraft is able to be modulated such that the main structure can be coupled/decoupled alternatively to/from the first container or the second container, the first container and the second container are able to be coupled/decoupled to/from one another, and the solar generator can be deployed or retracted.

A sampling method includes: obtaining topographical information about a predetermined wide area by using a first sensor on a work machine; selecting a candidate area within the wide area, the candidate area is less than an area of the wide area, and setting a movement route based on the information about the wide area, the movement route allows a distal end portion of an arm provided on the work machine to reach a preparation position without coming into contact with an obstacle, the preparation position being located above the candidate area; moving the distal end portion of the arm along the movement route to the preparation position, and obtaining topographical information about the candidate area by using a second sensor on the distal end portion of the arm; and specifying a sampling point based on the information about the candidate area and performing sampling at the specified sampling point.

A sample collection system for an extraterrestrial vehicle and method of operating is provided. The system includes an inlet conduit configured to receive a gas stream. A chamber having an inlet is fluidly coupled to the inlet conduit, the inlet and chamber configured to induce cyclonic flow. A container is removably disposed within the chamber, the container having a first opening fluidly coupled to the inlet and an outlet. An exhaust conduit is fluidly coupled to the outlet. A filter is disposed between the exhaust conduit and the chamber.

An embodiment of the present invention discloses a repair system for a planetary exploration parachute. The repair system includes a folding piece and a fuse, the fuse is provided in the folding piece, a sensing signal for reflecting an impact force of dust is received by the fuse, fusing is generated in the fuse when the sensing signal is greater than a preset threshold, and the folding piece is changed from a folded state to an unfolded state after the fusing is generated in the fuse, so as to automatically repair a damaged part of the parachute.

A lunar base supply method which enables supplying a base on a surface of the moon more easily than carrying materials from the earth to the moon and building the base on the surface of the moon. The lunar base supply method includes the steps of: (a) carrying materials to be used to build a structure to sky of the earth, and causing the materials to revolve along an orbit around the earth; (b) building the structure by using the materials on the orbit around the earth; and (c) moving the built structure from the orbit around the earth toward the moon, and causing the built structure to make a soft landing onto a surface of the moon and thereby to be available as a base.

The present disclosure relates to the field of robot technology, and discloses a spherical robot and a method of controlling the same. The spherical robot includes: a spherical shell, a spherical shell drive mechanism mounted inside the spherical shell to drive the spherical shell to spin about a center of sphere thereof, and a camera module. The spherical robot further includes a head shell in which the camera module is mounted, the head shell is located outside the spherical shell and is slideable along an outer surface of the spherical shell; and, the head shell is provided with a first magnetic component, the spherical shell drive mechanism is provided with a second magnetic component, and the first magnetic component is in a magnetic connection with the second magnetic component.

A method, operable in the presence of ambient cosmic rays, is provided for braking a craft upon approach to a planet, moon or other space body, e.g. in preparation for landing. Deuterium-containing particle fuel material is projected in a specified direction outward of the craft, which interacts with both the cosmic rays and their principal decay product muons to generate energetic micro-fusion products that produce a braking thrust on the craft for a specified trajectory. The micro-fusion products may push directly against the craft, e.g. upon a pressure plate, or upon a sail or parachute connected to the craft, to decelerate the craft. A prepositioned automated landing system at a landing site may project the fuel material toward the craft based on telemetry tracking of an incoming craft and likewise directly disperse the material cloud to form a braking cushion at the landing site. The micro-fusion landing system may be part of a site-to-site transport, where the craft was launched using either conventional chemical rockets or micro-fusion for accelerating thrust.

An innovative landing system for a spacecraft according to the invention comprises a foldable tether-based carrier structure that when unfolded assumes wheel-type shape and in its centre supports a carrier platform for the payload of the spacecraft.

A first step of propelling a transport ship from a low earth orbit or a geostationary transfer orbit to a targeted orbit or a destination with electric propulsion is provided.

An exploration method includes: a step of exploring a natural resource on a satellite, a minor planet, or a planet; a step of acquiring the natural resource detected by the exploration; and a step of storing the acquired natural resource.