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.

Retrofittable satellite systems for an in-orbit host satellite comprising an enhancement module for adding a capability to the in-orbit host satellite, modifying the function of the in-orbit host satellite, and/or extending the function of the in-orbit host satellite. The in-orbit, retrofittable satellite system comprises a transfer vehicle for transferring the enhancement module from a first to a second location and a service vehicle for receiving the enhancement module from the transfer vehicle and installing the enhancement module on the in-orbit host satellite. In-orbit space situational awareness systems, comprising one or more in-orbit host satellites having one or more enhancement modules attached thereto, the enhancement modules comprising sensors such as satellite spatial location/position sensors, range sensors, navigation sensors, and/or proximity sensors for detecting other objects in-orbit, their location, speed, acceleration, orbital trajectory or the like, wherein the enhancement modules communicate to create a mesh network between the satellites.

A space-debris capturing device includes a harpoon driven into target debris as space debris to be removed. The harpoon includes a first harpoon part having a large diameter, and a second harpoon part having a diameter smaller than the diameter of the first harpoon part and protruding from a leading surface in the direction of the drive of the first harpoon part into the target debris.

Methods of launching a vehicle using impulsive force are disclosed. In one instance, a vehicle is launched easterly with impulsive force in a plane corresponding to the vehicle's elliptical orbital path. In another instance, a method of closing a timing difference is disclosed. The vehicle undergoes a series of forces after impulsive launch. The first force establishes an orbit having a period significantly different from the orbital period of a satellite or desired vehicle location, closing the difference in an integer number of orbits. The second force establishes the vehicle in circular orbit with the satellite or desired vehicle location. In another instance, the vehicle launched impulsively from a first celestial body travels a first path, and the vehicle experiences a second force along a hyperbolic path about the second celestial body and enters circular orbit about the second celestial body.

A method for autonomously constructing structural bodies in a zero gravity environment utilizes an assembly line space structure to fabricate segments for constructing a modular space structure. An assembly housing provides an open ended structure through which materials are processed in order to construct a segment. The materials are loaded into a plurality of workstations positioned along the assembly housing through the use of a plurality of external manipulators adjacently connected to the assembly housing. Each of the plurality of workstations provides the equipment for sequentially loading materials into the assembly housing. An assembly line conveyor, positioned throughout the plurality of workstations, guides materials through the assembly housing as the materials are mated to form the segment. Upon completion of the segment, a plurality of segment transport units transports the segment to an orbital construction site, wherein the segment is mated with subsequent segments to form the space station.

A modular service interface is provided. The modular service interface includes separable first and second halves, one or more alignment features, a connector interface and one or more electropermanent magnet modules, connector interface configured to mate the first and second halves when activated and allow the first and second halves to be separated when inactivated. The modular service interface includes no mechanical actuators to retain the first half to the second half.

According to an aspect of the present invention, there is provided a method for rendezvous with an orbiting object comprising: launching a tug and a servicer into a client orbit; separating the servicer from the tug; and docking the servicer with a client. According to another aspect of the present invention, there is provided system for rendezvous with an orbiting object comprising: a first spacecraft raft comprising a tug capable of towing a second spacecraft, wherein the second spacecraft is a servicer configured to dock with a tumbling client orbiting object.

A space device includes: an adhesion part to adhere to a target existing in the space; and a propulsion part to obtain propulsion power. The space device that adheres to the target at the adhesion part moves together with the target by the propulsion part, thereby conveying the target to a predetermined target position.

A robotic gripper for rigidly grasping a section of a Marman ring of a satellite, the robotic gripper having an outboard jaw which interfaces to an outer diameter side of the Marman ring, a inboard jaw which interfaces to an inner diameter side of the Marman ring, and a palm which interfaces to a separation surface of the Marman ring. The jaws, when grasping the section of the Marman ring, execute a two-stage motion comprising a first movement toward the opposing jaw in a direction parallel to the palm, and a second movement of drawing the Marman ring down against the palm or other suitable surface in order to fully rigidize the grasp.

A debris removal device includes: an end mass adapted to approach debris to be removed; a debris capture device separably-mounted on the end mass; and a tether connecting the debris capture device and the end mass to each other. The debris capture device includes a harpoon adapted to penetrate into the debris, a shooting device adapted to shoot the harpoon, a guide member positioned to come into contact with the surface of the debris to adjust the shooting angle of the harpoon with respect to the surface of the debris, and a switch that sends the shooting signal to the shooting device. When the harpoon is penetrated into the debris, the end mass is separated from the debris capture device, and the tether is released into outer space.