Abstract: An impact-resistant balanced hydro-cylinder with pressure relief and buffering protection comprises a cylinder body (11), a piston (13), a piston rod (14), and a first valve core (21) and a second valve core (51) slidable relative to the cylinder body (11). A closed first gas cavity (22) and a closed second gas cavity (52) are respectively formed between the two valve cores and inner walls of two opposite ends of the cylinder body (11). A closed first oil cavity (32) and a closed second oil cavity (42) are respectively formed between the two valve cores and two end faces of the piston (13). A through hole (33) for the first oil cavity and a through hole (43) for the second oil cavity are respectively provided in the positions on the cylinder body (11) corresponding to the first oil cavity (32) and the second oil cavity (42).

Abstract: A fuel-free spacecraft propelling system having an open-ended outer cylinder of a propelling device and an atomic oxygen collecting device is disclosed. The latter is arranged at the forwardly-propelled front end of the outer cylinder and is hermetically connected with an RF generating device and an ion cyclotron wave heating device through a magnetic confinement device. A spiral wave discharge oxygen plasma inlet and a spiral wave discharge oxygen plasma outlet in the ion cyclotron wave heating device are respectively provided with another magnetic confinement device. The propulsion of the invention does not need to carry the propellant, which greatly reduces the launch costs, and enables a spacecraft to advantageously have an increased orbit life over existing spacecraft systems.

Abstract: A fuel-free spacecraft propelling system having an open-ended outer cylinder of a propelling device and an atomic oxygen collecting device is disclosed. The latter is arranged at the forwardly-propelled front end of the outer cylinder and is hermetically connected with an RF generating device and an ion cyclotron wave heating device through a magnetic confinement device. A spiral wave discharge oxygen plasma inlet and a spiral wave discharge oxygen plasma outlet in the ion cyclotron wave heating device are respectively provided with another magnetic confinement device. The propulsion of the invention does not need to carry the propellant, which greatly reduces the launch costs, and enables a spacecraft to advantageously have an increased orbit life over existing spacecraft systems.