A sample capture assembly and method of operating is provided. The assembly includes a sampler device configured to retrieve a sample from a surface. A first bellows having a first inlet is fluidly coupled to the sample device, the bellows being selectively movable between a compressed and an extended position. A gate valve having a second inlet is coupled to an end of the first bellows opposite the first inlet. A sample container is fluidly coupled to the gate valve.

A spacecraft including: an engine; a thrust vector control device controlling a thrust vector as a direction of a thrust acting on the spacecraft; and a main control device configured to acquire state quantities of the spacecraft in a powered descending in which the spacecraft is guided to a target point while the engine generates the thrust, and generate a throttling command by which combustion of the engine is controlled and an operation command by which the thrust vector control device is operated. The state quantities contain a first acceleration parameter and a second acceleration parameter. The first and second acceleration parameters are calculated as coefficients A and B obtained by fitting based on acceleration of the spacecraft previously detected, supposing the following equation is satisfied between a reciprocal number 1/a of the acceleration a of the spacecraft and time t:
1/a=−At+B  (1).

A system and method of acquiring and delivering samples, such as in association with an interplanetary vehicle is provided. The system includes a gas delivery assembly having a storage tank with a compressed gas. A sampler device is provided having a hollow interior, the hollow interior having a curved and angled surface, an open end and an exit end. A plurality of nozzles are fluidly coupled between the hollow interior and the storage tank, at least one of the plurality of nozzles arranged to direct the compressed gas towards the exit end. A sample capture assembly is further provided having a container fluidly coupled to the exit end.

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.

Methods, systems, and apparatus for designing, constructing and using instrument landers for in situ exploration of small solar system bodies, such as asteroids and comets. In one aspect, a lander includes a CubeSat-style platform; instrument packaging, wherein the CubeSat-style platform and the instrument packaging are configured and arranged for an uncontrolled descent, hopping landing on a surface of a body in a solar system, where a descending trajectory for the lander is designed based on gravitational force and solar radiation, with no lander-based propulsion; and a mobility mechanism configured and arranged to self-orient the lander on the surface of the body in the solar system.

According to an embodiment of the present invention, an apparatus for controlling a moving object includes a trajectory control unit configured to control a trajectory of the moving object and a position control unit configured to control a position of the moving object. Thus, it is possible to control an angle at which the moving object enters a target point.

A moon/planet complex, an orbiting docking spaceport, and transportation vehicles therebetween that includes i) moon/planet base station having a landing platform with a plurality of charged plates; ii) a moon/planet orbiting craft, docking spacecraft having landing platform with a plurality of charged plates; iii) a personnel transport spacecraft to shuttle personnel between an orbiting craft and planetary/moon base station having rotating electromagnetic rings 320 and/or rotating electromagnetic plates to interact with charged plates; iv) a large personnel/cargo transport spacecraft to shuttle personnel between an orbiting craft and planetary base station having rotating electromagnetic plates to interact with charged plates.

Current sensing devices that are capable of surviving harsh ambient environment of ocean worlds, such as Jupiter and Saturn moons are disclosed. The described devices can meet 300 Krad radiation requirements and can survive at cold temperatures down to −184° C. Exemplary implementations of the constituent circuits of the devices are presented. A scheduling algorithm to perform various measurement by the disclosed current sensing devices is also described.

A vehicle comprising a structure, a plurality of heating sources, and a transport mechanism. The structure is comprised of multiple materials, a composite such that some of the material constituents can be extracted leaving behind others via application of energy (such as de-alloying). The extracted material or materials are configured to be re-purposed into a propellant. The plurality of heating elements surrounds or is embedded within the structure configured to convert the material into the propellant. The transport mechanism is configured to transport the propellant from the structure to a reservoir or to the propulsion system.

A laser sample chamber for deep space exploration includes a sample chamber base and a sample chamber top cover. The sample chamber base is a hollow cylinder with bottom end being sealed and top end being open, and an internal cavity in the hollow cylinder is provided for receiving sample plates; and a body of the sample chamber top cover is a hollow cylinder with a top end being sealed and a bottom end being open, and the body consists of a plurality of components which comprise a hollow annulus positioned at a middle of the sample chamber top cover, a circular viewing window positioned at an opening at a top end of the hollow annulus, and a threaded port positioned at an opening at a bottom end of the hollow annulus and protruding outward.