Systems and methods for launching a plurality of spacecraft, provided in a stack of spacecraft, from a launch vehicle traveling along an in-track path include releasing, in a first separation event occurring at a first time, a first spacecraft from the stack of spacecraft using a first separation force having a first separation force in-track component along the in-track path. Subsequently, in a second separation event occurring at a second time, a second spacecraft is released from the stack of spacecraft using a second separation force having a second separation force in-track component along the in-track path, wherein the second time occurs a first time delay after the first time. The first and second separation in-track components may be different, such as by varying a magnitude of the separation force or an angle at which the spacecraft is launched.

A modular and scalable system to transfer space articles between space orbits. In one embodiment, the system employs a rendezvous vehicle which docks with a space article in an initial orbit, the connected stack then docking with a locomotive vehicle which maneuvers to a targeted orbit where the space article is detached. In one feature, the rendezvous vehicle and locomotive vehicle use a common propellant and the space article is a satellite.

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.

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.

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.

A method for estimating a direction of a satellite in the transfer phase. The direction of the satellite is estimated relative to a measurement antenna by executing steps for measuring the reception power, by the measurement antenna, of a target signal emitted by the satellite, for different pointing directions of the measurement antenna. The target signal has a substantially sinusoidal component referred to as a single-frequency component. Each power measurement step includes a transposition in the frequency domain of a digital signal, obtained from a signal supplied by the measurement antenna, to obtain a frequency spectrum of the digital signal over a predetermined frequency band having the single-frequency component. The power measurement for the pointing direction being considered is determined based on a maximum value of the frequency spectrum.

A system and method of operating a focal plane array of a camera assembly for a space vehicle in orbit includes scanning across a scene containing a target surface using the focal plane array, generating a plurality of sampled signals for the scene using a plurality of detectors of the focal plane array, co-adding the sampled signals to produce an output having a constant spatial resolution, and correcting a temporal shift in a line-of-sight of the focal plane array by rotating the space vehicle or the camera assembly to null relative motion at a center point of a scan.

Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft.

A satellite system may have a constellation of communications satellites in orbits such as highly inclined eccentric geosynchronous orbits and low earth orbits. To place satellites in inclined eccentric geosynchronous orbits, a series of launch vehicles may be launched. Each launch vehicle may be used to place a set of satellites, such as a set of three satellites, into a common orbital plane with distinct longitude of ascending node values. To place satellites in low earth orbits, a series of launch vehicles may be launched, each of which releases satellites in sequence from a stack of satellites into a common orbital plane. After desired separations have been produced between the released satellites, circularization procedures may be performed using the propulsion systems of the satellites to place the satellites into final orbit.

Systems and methods for transferring, storing, and/or processing materials, such as fuel or propellant, in space, are disclosed. A representative system includes a flexible container that is changeable between a stowed configuration in which the flexible container is contained within a satellite, and a deployed configuration in which the flexible container extends away from the satellite. The system can include a tanker with a storage container to dock with and refuel a satellite. Another representative system includes a controller programmed with instructions that position a spacecraft with a storage container in a first orbit, transfer the spacecraft to a second orbit, dock the spacecraft with a satellite in the second orbit, transfer material between the storage container and the satellite, undock the spacecraft from the satellite, and, optionally, return the spacecraft to the first orbit. An androgynous coupling system with mechanical and fluid connectors facilitates docking and material transfer.