A satellite visibility assignment device (1) includes a visibility unit setter (21), a visibility unit selector (22), and an optimization calculator (23). The visibility unit setter (21) sets visibility units each including a combination of a satellite and a station to communicate with the satellite, a lower limit of a visibility start time, and an upper limit of a visibility end time. The optimization calculator (23) determines whether the visibility start time and the visibility end time are settable for each of the one or more combinations of the visibility units within a range satisfying a set constraint and calculates the visibility start time and the visibility end time through an optimization calculation. The visibility unit selector (22) selects, from the combinations of the visibility units, a combination of the visibility units to be used based on determination of the optimization calculator (23).

Provided is a failure diagnostic system for a spacecraft liquid propulsion system that enables to accurately diagnose a failure in a spacecraft and a failure diagnostic method for the spacecraft liquid propulsion system. This spacecraft liquid propulsion system includes a plurality of thrusters, and a supply pipe connected to the thrusters. This system includes a pressure sensor that detects an inner pressure of the supply pipe as time-series data, a frequency spectrum conversion unit that converts the time-series data into data of a frequency spectrum, a storage unit that stores data of a frequency spectrum generated based on an analytical model by computer simulation or a test result of a testing device as a data set, a comparator that compares the data set with the data of the frequency spectrum generated by the frequency spectrum conversion unit, and a determining unit that determines a failure in any one of the plurality of thrusters according to a comparison result of the comparator.

Provided is a failure diagnostic system for a spacecraft liquid propulsion system that enables to accurately diagnose a failure in a spacecraft and a failure diagnostic method for the spacecraft liquid propulsion system. This spacecraft liquid propulsion system includes a plurality of thrusters, and a supply pipe connected to the thrusters. This system includes a pressure sensor that detects an inner pressure of the supply pipe as time-series data, a frequency spectrum conversion unit that converts the time-series data into data of a frequency spectrum, a storage unit that stores data of a frequency spectrum generated based on an analytical model by computer simulation or a test result of a testing device as a data set, a comparator that compares the data set with the data of the frequency spectrum generated by the frequency spectrum conversion unit, and a determining unit that determines a failure in any one of the plurality of thrusters according to a comparison result of the comparator.

Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, an apparatus for collecting solar energy and simultaneously protecting against damage from a resulting energy beam includes a solar energy collection system including at least one concentrator and a target configured to use, store, or convert the solar energy, the collection system configured to cause solar energy to focus on the target, at least one sensor configured to detect misalignment of the concentrator by determining that some or all of the collected solar energy is offset from the target, and a safety system configured to redirect the energy or interpose a safety structure for shielding other non-target systems from receiving too much solar energy from the collection system.

A Magnetic Storage Unit (MSU) for on-board cargo/logistics storage in aspects of space exploration including spacecraft/space flights/launch vehicles and cargo/logistics on the International Space Station (ISS) is provided in the present invention. Further provides an integration of the Magnetic Storage Unit (MSU) including a power source for transferring power to a power wall and a Long Logistics Rod (LLR), the Long Logistics Rod (LLR) is linked to a control center for human interaction with each container secured with a holder.

A Magnetic Storage Unit (MSU) for on-board cargo/logistics storage in aspects of space exploration including spacecraft/space flights/launch vehicles and cargo/logistics on the International Space Station (ISS) is provided in the present invention. Further provides an integration of the Magnetic Storage Unit (MSU) including a power source for transferring power to a power wall and a Long Logistics Rod (LLR), the Long Logistics Rod (LLR) is linked to a control center for human interaction with each container secured with a holder.

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.

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.

Ruggedized avionics assemblies for use on kinetically launched space vehicles are disclosed. The avionic assemblies are able to maintain structural integrity and functionality under high acceleration forces generated during kinetic launch, including acceleration forces of >5,000 times Earth's gravity in a single direction of loading. The avionics assembly is ruggedized to withstand this level of acceleration force during launch via a plurality of constraining elements to constrain a plurality of printed circuit boards aligned in parallel to an acceleration vector. Further, a high specific strength and stiffness composition of the plurality of constraining elements aids in supporting the printed circuit boards and preventing them from bending and dislodging electronic components mounted to the printed circuit boards.

Systems, apparatuses, and methods provide for technology that locates one or more masses of a thunderstorm system, as the thunderstorm system starts to organize and before the thunderstorm system spawns a tornado, and controls a transmission of electromagnetic radiation from the space platform to the one or more masses, wherein the transmitted electromagnetic radiation tracks the one or more masses as the thunderstorm system is starting to organize and rotate, and wherein the transmitted electromagnetic radiation prevents the thunderstorm system from rotating and spawning the tornado.