A spacecraft including a main body structure and at least a first deployable element is reconfigured from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a first arrangement. In the on-orbit configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a second arrangement. Reconfiguring the spacecraft includes detaching the first deployable element from the first arrangement, moving the first deployable element with respect to the spacecraft main body structure; and attaching the first deployable element to the second arrangement.

A spacecraft system and method includes a platform with a dock and an umbilical payout device. A robot is connected to an umbilical paid out by the umbilical payout device and is repeatedly deployable from the dock. The robot includes one or more imagers, an inertial measurement unit, and a plurality of thrusters. A command module receives image data from the one or more robot imagers and orientation data from the inertial measurement unit. An object recognition module is configured to recognize one or more objects from the received image data. The command module determines the robot's orientation with respect to an object and issues thruster control commands to control movement of the robot based on the robot's orientation. The combination of the space platform and robot on umbilical line can be used for towing another object to different orbital location, inspection including self-inspection of the robot carrying platform and for robotic servicing.

An airship includes a capsule and an external structure attached to the capsule and extending vertically above an upper portion of the capsule. A plurality of gas balloons are secured to the external structure and hold a lighter-than-air lifting gas. The volume of lifting gas in the plurality of balloons is at least a sufficient volume to lift the airship into the stratosphere. The airship may also include a first boom and second boom that extend horizontally outward from a lower portion of the capsule. The booms each include a weight or cargo container at a far end to assist in balancing and stabilizing the airship. The number and/or the sizes of the gas balloons may be adjusted and configured to obtain the volume of lifting gas needed to lift the airship to a desired altitude above the Earth.

A dimpled spherical storage unit is described in the form of a cargo ball. The cargo ball includes a spherical exterior surface and a plurality of dimples in a pattern on the exterior surface. At least a first cover is configured to extend outward from the center of the cargo ball and at least a first thruster is configured to be deployed from the cargo ball.

A spacecraft docking station is adapted to facilitate docking of spacecraft within outer space. According to one example, a spacecraft docking station may include a frame enclosing an area, and a net-like mesh coupled to the frame and filling the area enclosed by the frame. An autonomous robot may be coupled to the net-like mesh. One or more vessels may be coupled to the frame and/or the net-like mesh, where the one or more vessels include a propulsion mechanism. Other aspects, embodiments, and features are also included.

Disclosed are a method of flying on the moon and a device for flying using the method. A medium on a surface of a moon and a medium accelerating module are used in the flying method. The medium is transferred into the medium accelerating module, accelerated by the medium accelerating module, and ejected out of the medium accelerating module by using a power supply. A counterforce is generated in accordance with the momentum conservation, and the counterforce overcomes the lunar gravity and drives a load to take off. The method is suitable for the environment of the moon where flight by means of atmospheric buoyancy is impossible due to the shortage of atmosphere.

A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.

A spacecraft including a main body structure and at least a first deployable element is reconfigured from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a first arrangement. In the on-orbit configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a second arrangement. Reconfiguring the spacecraft includes detaching the first deployable element from the first arrangement, moving the first deployable element with respect to the spacecraft main body structure; and attaching the first deployable element to the second arrangement.

Provided is a system and method for robotic manipulation. The system includes a primary arm having a two arm linkage, a secondary tool, an attachment for attaching the secondary tool to the primary arm, and a controller of the primary arm for operating the secondary tool. The method includes removing a secondary arm from a storage location, securing the secondary arm to the primary arm, and operating the secondary arm with a controller of the primary arm.

A servicing system for on-orbit spacecrafts is disclosed. The system comprises a servicing or host spacecraft configured to perform on-orbit servicing of client spacecrafts. The servicing spacecraft comprises a dedicated, deployable, boom having capture and docking mechanisms. The capture mechanism comprises a plurality of capture arms attached to a grounding structure. In one embodiment, the capture arms are kinematically linked and are free to rotate with respect to the grounding structure using a single actuator, thereby synchronizing the rotation of the arms for any angular displacement of the actuator, thus the arms form a circle that is concentric with the boom axis. In a second embodiment, there are two sets of capture arms, with the arms in each set kinematically linked and independently actuated; thus, the two sets cooperatively form different grasping geometries. Further, the docking mechanism is configured to enable the host spacecraft to dock with the client spacecraft. The servicing spacecraft may also be configured to carry a robotic arm and a suite of end-effectors that can be automatically changed out on-orbit. The suite of end-effectors may include one configured with the disclosed capture mechanism, and another may be configured with the disclosed docking mechanism.