Provided is a space vehicle that includes: a main body; a movable portion configured to reciprocate in an axial direction with respect to the main body; and a magnetic force generation unit attached to a distal end of the movable portion, and attracts, by a magnetic force, a platelike body attached to an object in outer space. The magnetic force generation unit includes: a magnet support member attached to a distal end of the movable portion via a buffer elastic body; and a plurality of permanent magnets laid on a surface of the magnet support member to form an attraction region. When a drive unit moves the movable portion away from the main body, the attraction region protrudes from the main body while maintaining a fixed orientation crossing the axial direction, and is changeable in position and/or orientation by the buffer elastic body when an external force is applied.

A spacecraft for the distribution of electrical energy to client craft at points situated in free space, in orbit and/or on a celestial body includes a main structure equipped with an electric thruster, with a chemical thruster and with a solar generator, a first fuel container for fuel intended for the electric thruster, and a second fuel container for fuel intended for the chemical thruster. The spacecraft is able to be modulated such that the main structure can be coupled/decoupled alternatively to/from the first container or the second container, the first container and the second container are able to be coupled/decoupled to/from one another, and the solar generator can be deployed or retracted.

Movable platforms for use with a vehicle capture assembly of a capture vehicle and related devices, systems, and methods include floors with rotatable legs extending between the floors. The rotation of the legs relative to one or more of the floors enables the movable platform to move from an initial position to a displaced position as one or more of the floors move relative to each other.

A seal assembly is provided that includes a protective shroud to protect a sealing element from hazardous elements and/or a hazardous environment.

The present disclosure relates to a low mass system for releasably securing a robotic arm to a spacecraft and also securing various payloads to the robotic arm and to each other, permitting the robotic arm to be both moved from one location to another suitably equipped location on a spacecraft to another and to allow the free end of the robotic arm to be secured to any payload also similarly equipped such that this payload may be manipulated by the robotic arm.

Simplify, downsize and reduce power of devices which comprise the satellite navigation system used in approach and docking in space. The navigation system 1 which estimates an attitude of a target object T in space comprises: an optical marker 10 that is attached to the target T and reflects light; a lighting device 20 that irradiates the target object T with light of a predetermined wavelength band; an image acquisition device 30 that acquires an image of the optical marker 10 which has reflected the light of the predetermined wavelength band; and an image processing device 40 that processes the image acquired by the image acquisition device 30 and thereby estimates the attitude of the target object T. The lighting device 20 and the image processing device 30 are loaded on an aerospace vehicle 2.

A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.

A pin array release and capture chamber system includes a chamber assembly having two parallel plates of pin arrays from which a plurality of pins extends and retract vertically opposite each other so as to release and capture a space vehicle. The pin arrays are separated from each other by a space having two vertical and two horizontal sides, and the space is sized so as to receive the space vehicle. Each pin arrays may be housed in a pin array chamber enclosure. The chamber assembly may be attached to a moving object, such as a host space vessel.

Cell-based systems may interlock in a reconfigurable configuration to support a mission. Space systems, for example, of a relatively large size may be assembled using an ensemble of individual cells, which are individual space vehicles. The cells may be held together via magnets, electromagnets, mechanical interlocks, etc. The topology or shape of the joined cells may be altered by cells hopping, rotating, or rolling along the joint ensemble. The cells may be multifunctional, mass producible units. Rotation of cell faces, or of components within cells, may change the functionality of the cell. The cell maybe collapsible for stowage or during launch.

Cell-based space systems with nested-ring structures that interlock and can change configuration to support a mission are provided. The cells may self-assemble into a larger structure to carry out a mission. Multiple rotatable rings may be included in a cell, with a payload/control section in the center. The rings may provide power and/or data to trams that move about the rails. Trams may interlock with other cells, carry sensors or other devices, etc. Cells may be stowed in a cell stack that is deployable. Such cell-based systems may have various applications in space, on Earth, other celestial bodies, and underwater.