Systems and methods for production of hydrogen peroxide, such as high-test peroxide, are disclosed. Representative systems and methods also include aerospace systems and space exploration missions implementing systems and methods for production of hydrogen peroxide. A representative system for making hydrogen peroxide can include: a water electrolyzer for receiving water and separating at least some of the water into hydrogen and oxygen; a proton-exchange membrane cell for receiving water, hydrogen from the water electrolyzer, and oxygen from the water electrolyzer and for combining the hydrogen, the oxygen, and the water into a first hydrogen peroxide solution having a first concentration of hydrogen peroxide in water; and a hydrogen peroxide concentrator for removing at least some of the water from the first hydrogen peroxide solution to yield a second hydrogen peroxide solution that has a second concentration of hydrogen peroxide in water that is greater than the first concentration.

An object is to prevent satellites constituting a mega-constellation from remaining in outer space in large numbers after completing their missions. An artificial satellite includes a propulsion device. The artificial satellite has propellant to be used by the propulsion device, and the propellant is in an amount required for the artificial satellite to operate in orbit for a first period of L1 years, which is a satellite design life, and then enter the atmosphere within a period less than the first period of years after deorbit. A ground facility controls the artificial satellite so that the artificial satellite has the amount of propellant required to operate in orbit for the first period of L1 years, which is the satellite design life, and then enter the atmosphere within a period of less than the first period of L1 years after deorbit.

Methods and apparatus for Real-time Satellite Imaging System (10) are disclosed. More particularly, one embodiment of the present invention an imaging sensor (14) on a geostationary satellite having one or more co-collimated telescopes (18). The telescopes (18) illuminate local planes (22) which are sparsely populated with focal plane arrays (24). The focal plane arrays (24) record the entire observable Earth hemisphere at one time, at least once every ten seconds.

A method for capturing and deorbiting space debris includes: providing a space debris capturing device; deploying the space debris capturing device in planetary orbit; determining, via an onboard global positioning system unit, the position and orbit velocity of the space debris capturing device; receiving an initial target set including a first database of space debris targets that are within range of the space debris capturing device; performing a first algorithm to convert the initial target set to an accessible target set including a second database of space debris targets that are within range of the space debris capturing device, the second database is smaller than the first database; performing a second algorithm to convert the accessible target set to a final target set including a third database of space debris targets to be captured by the space debris capturing device, the third database is smaller than the second database; transferring the space debris capturing device to a position within a capture range of a first space debris target of the third database; capturing the first space debris target via a capture mechanism of the space debris capturing device; jettisoning the capture mechanism and the first captured space debris target into a decaying orbit; repeating the transferring, capturing, and jettisoning steps for all but a final one of the remaining space debris targets of the third database; and positioning the space debris capturing device and the final captured space debris target into a decaying orbit.

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).

A satellite constellation forming system (100) forms a satellite constellation which is composed of a satellite group and in which the satellite group cooperatively provides a service. The satellite constellation has a plurality of orbital planes in each of which a plurality of satellites fly at the same nominal orbital altitude. A satellite constellation forming unit (110) continues providing the service while avoiding a collision between satellites by both or one of control of an orbital altitude and control of a passage timing of a satellite group flying in a region where the plurality of orbital planes intersect.

A method of communication with a non-GEO constellation of satellites, includes providing an Earth-based terminal configured for communication with a satellite constellation, and establishing communication between the Earth-based terminal and a non-GEO constellation of satellites, the non-GEO constellation of satellites including a first plurality of satellites orbiting at a first inclination, wherein each of the satellites in the first plurality of satellites is in a discrete planar orbit to form a first snake of satellites, the first snake of satellites including adjacent satellites in adjacent orbits having adjacent RAAN (Right Ascension of the Ascending Node), wherein the Earth-based terminal is positioned and configured for continuous communication with at least one satellite from the non-GEO constellation of satellites.

The ever increasing number of orbiting bodies in low Earth orbit has made it infeasible to calculate potential conjunctions between orbiting bodies more than a few days in advance, even with the aid of supercomputers. Disclosed embodiments utilize machine learning to predict potential conjunctions between orbiting bodies faster than state-of-the art systems by orders of magnitude. This enables potential conjunctions to be identified well in advance (e.g., 30 days or more), so that they may be prioritized (e.g., for fine calculations), visualized, and remediated (e.g., via control of the impacted satellites).

A deorbit-sail deployment device for forming a deorbit sail that drives a satellite to deorbit is disclosed. The deorbit-sail deployment device comprises a non-folding sail and a folding sail that are rotatably connected to each other to form the deorbit sail The folding sail comprises at least one first skeleton that folds the sail body in the folded state and supports the sail body in the unfolded state. The folding sail can be folded to a compact size before launch.

An orbit transition apparatus that transitions an orbit of a payload in outer space includes a rotating body, an adapter disposed on a center part of the rotating body for docking a payload, a launch module disposed outside of the rotating body for launching the payload, and a thruster for rotating the rotating body. The launch module may launch the payload to a target orbit.