Abstract: Described herein is a method of constructing a landing pad using a rocket engine while in-flight. Among other benefits, this method can reduce ejecta that otherwise would occur during landing on an unimproved surface. While a spacecraft is hovering over an unimproved surface, the spacecraft can inject particles into its rocket engine, after which the particles absorb heat from the engine and are projected at ballistic speeds toward the unimproved surface to create a landing pad. After constructing the landing pad and waiting for the landing pad to cool, the spacecraft can land on the landing pad. Also described herein are landing pads created from such particles as they impact the surface in a disc splat mode into the unimproved surface.

Abstract: A spacecraft includes a body having a motor, a lander interface, a sensor and a power source for powering the motor and the sensor, and the power source being mounted thereon. An integrated avionics unit has a module and an integrated circuit with the module having a central computer and a motor controller for controlling the motor and the integrated circuit having a temperature monitoring system for monitoring the temperature of the spacecraft and a power regulator having a cell balancer for regulating the power of the power source. The module and the integrated circuit are connected to one another for constant communication therebetween. The central computer communicates with the sensor.

Abstract: A pair of interconnected vertical solar arrays at two preselected lunar sites are provided. A cable transmits power between one of the vertical solar arrays and the other vertical solar array, so that one of the vertical solar arrays can send collected energy to other vertical solar array, when the other vertical solar array is not collecting energy, to maintain the temperature of the other vertical solar array. A power storage device receives solar energy from the vertical solar arrays. A charging interface distributes energy to one or more lunar devices on the lunar surface. A landing vehicle has a payload thereon for carrying at least one of the pair of interconnected vertical solar arrays, the cable, the power storage device, and the charging interface.

Abstract: An additively manufactured non-uniform porous material in-situ with dense material for the in situ additive manufacturing of both porous and dense material in the same part so that no secondary process is required. The additively manufactured non-uniform porous material in-situ with dense material generally includes additively manufactured porous material which can be tuned for porosity and density, has the ability to be built in situ with dense material, and can also be tuned for response to pressure waves. Also included are computer program products, methods and components and systems manufactured using the methods.

Abstract: Mining apparatuses, systems and methods related to the use of a rocket engine's plume and a collection manifold to efficiently displace, collect, process and store frozen volatiles embedded within or below a surface is disclosed. The plume contacts and churns up the surface. The frozen volatiles are displaced and/or evaporated within a closed environment under a collection manifold. The collection manifold has related components for addressing these frozen or gaseous volatiles downstream. Various apparatuses and subsystems are also disclosed including a rover, processing plants, collection manifold, and vapor manifold.