Apparatuses, methods, and systems are disclosed to use thermoelectric generating (TEG) devices to generate electricity from heat generated by a power cable. An apparatus includes multiple thermoelectric generating (TEG) devices. Each of the TEG devices has a first surface configured to be positioned in thermal communication with an outer surface of the power cable and a second surface configured to be positioned proximate to an ambient environment around the power cable. The apparatus also includes a set of terminals electrically coupled to the TEG devices. When a temperature differential exists between the first surface and the second surface, the TEG devices convert heat into electricity presented at the set of terminals.

A system and methods are disclosed for an upper stage space launch vehicle that uses gases from the propellant tanks to power an internal combustion engine that produces mechanical power for driving other components including a generator for generation of electrical current for operating compressors and fluid pumps and for charging batteries. These components and others comprise a thermodynamic system from which system enthalpy may be leveraged by extracting and moving heat to increase the efficient use of propellant and the longevity and performance of the launch vehicle.

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.

A launch vehicle with a rocket body having a longitudinal axis which has at least one propulsion stage which can be driven by a reaction propulsion system acting predominantly parallel to the longitudinal axis, wherein the launch vehicle is provided with a plurality of rotors which can be driven by means of a respective rotor drive and whose respective rotor axis is aligned substantially parallel to the longitudinal axis of the rocket body, is characterized in that a separate takeoff stage is provided which is coupled or can be coupled to the rocket body and/or the propulsion stage, which is coupled to or can be coupled to and decoupled from the separate takeoff stage, which has the plurality of outer rotors, in that the outer rotors are arranged in the manner of a multi-copter radially outside the rocket body and surrounding the rocket body.