Omni-directional, extensible grasp mechanisms are disclosed. Such grasp mechanisms may be used as a robotic end effector for docking, grasping, and manipulating space structures, or to interconnect other structures or vehicles. Novel interconnected lattice structures may enable large arrays to be assembled. The grasp mechanisms may be used to create structures from parallel docking linkages. This may enable reconfiguration of multiple docked space vehicles and/or structures without the use of propellant. The grasp mechanisms have the ability to make and break connections multiple times, enabling a nondestructive and reversible docking process.

A release apparatus for releasing a satellite comprises a release plunger that can be preloaded by a release spring and that is held in a preloaded position by two two-armed pivot levers pivotable about a respective pivot axis, wherein each pivot lever can be held against a force of a spring in a holding position by a release element.

A release apparatus for releasing a satellite comprises a release plunger that can be preloaded by a release spring and that is held in a preloaded position by two two-armed pivot levers pivotable about a respective pivot axis, wherein each pivot lever can be held against a force of a spring in a holding position by a release element.

A method for manufacturing in space a rigid structure having a lattice is disclosed. The method includes creating of at least two framework elements from a coil of metal strip or wire, and creating of the lattice by cold-connecting the framework elements.

A method for manufacturing in space a rigid structure having a lattice is disclosed. The method includes creating of at least two framework elements from a coil of metal strip or wire, and creating of the lattice by cold-connecting the framework elements.

Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.

A system and method for vaporizing space debris in space. The system includes a spacecraft body, a primary solar concentrator mounted to the spacecraft body that collects and focuses solar flux from the sun, and a secondary solar concentrator positioned at a focal point of the primary solar concentrator that refocuses the focused solar flux. A manipulator arm coupled to the spacecraft body grabs the space debris in space and positions it at a location where the refocused solar flux vaporizes the debris. The secondary solar concentrator can be a point-source concentrator, the primary solar concentrator can be a parabolic mirror, a Fresnel lens or a light focusing element or assembly, and the space debris can be a retired spacecraft or launch vehicle upper stage or component.

A system and method for vaporizing space debris in space. The system includes a spacecraft body, a primary solar concentrator mounted to the spacecraft body that collects and focuses solar flux from the sun, and a secondary solar concentrator positioned at a focal point of the primary solar concentrator that refocuses the focused solar flux. A manipulator arm coupled to the spacecraft body grabs the space debris in space and positions it at a location where the refocused solar flux vaporizes the debris. The secondary solar concentrator can be a point-source concentrator, the primary solar concentrator can be a parabolic mirror, a Fresnel lens or a light focusing element or assembly, and the space debris can be a retired spacecraft or launch vehicle upper stage or component.

Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.

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.