A system and method for autonomous self-repair of a planetary rover. The system comprises a health monitoring module, a multi-modal sensor suite, a robotic manipulator, a spare component storage bay, and an intelligent decision-making module. In response to receiving a fault signature, the decision-making module autonomously executes an end-to-end self-repair protocol. The protocol comprises: ceasing a primary mission; evaluating a current location of the rover against a predefined stability threshold; and, only if the current location is determined to be unstable, analyzing terrain data from the sensor suite to identify a previously un-mapped, ad-hoc stable location. The rover navigates to the stable location and, after confirming arrival, commands the manipulator to physically replace a failed hardware component with a spare. This integrated, fault-contingent protocol provides a new paradigm of autonomous self-preservation.

A multi-armed robotic translation device includes a robotic body that includes a base section and a cover section attached to the base section. A plurality of tentacles is attached to the robotic body. The plurality of tentacles are configured to apply a shear force on the target object to grip the target object using an adhesive force, each tentacle including at least one shape memory alloy wire configured to move the tentacle. A control system is positioned in the robotic body and is configured to provide power and/or control signals to the tentacles.

A positioning device includes at least one processor. The at least one processor detects a light source and a target object different from the light source in an image captured by an imager. A moving object has the imager and moves in a space. The at least one processor derives a position of the moving object in the space based on positions of the light source and the target object in the image and known positions of the light source and the target object in the space.

Embodiments of the present invention implement a method, apparatus, and computer-readable medium for the use of a robotic arm for momentum unloading and orbit control. In some instances, a panel is attached to the end of a robotic arm. It is positioned, in angle and position, to optimize unloading. The robot arm can move about the spacecraft, giving additional degrees of freedom. The panel can be stowed when necessary.

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.

A spacecraft control architecture uses a multi-joint robotic arm carrying a reflective panel to generate controllable forces and torques from solar radiation pressure and, in some cases, aerodynamic drag. A plurality of attachment points on an exterior surface provide mechanical and electrical interfaces for end effectors of the arm. A control system determines a demanded change in stored momentum and/or orbital state, computes available external forces based on ephemeris and attitude data, and evaluates candidate arm and panel configurations subject to joint limits and keep-out regions for antennas, sensors, and solar wings. The control system selects a target configuration and commands the arm to walk between attachment points by alternately latching and unlatching the end effectors while maintaining at least one latched interface. The architecture can also place the panel in a stowed configuration that produces substantially zero net force and torque.

Independently moving deployment and positioning space vehicles that are configured to deploy and/or position structures are disclosed. The deployment and positioning vehicles work together to deploy and/or maintain the position/shape of a space structure. The deployment and positioning vehicles may include one or more thrusters, an attitude determination and control system (ADCS), a precision vehicle-to-vehicle location determination system, processing circuitry, etc. Two or more deployment and positioning vehicles are configured to coordinate the deployment and/or positioning of the space structure themselves or in concert with the other deployment and positioning vehicles in the deployment and positioning vehicle network, as well as achieve precision positioning.

Devices for the assembly of structures are described. More specifically, devices designed for the assembly of structures in space are described, with a particular focus on antenna structures and methods for their assembly and deployment in space. Even more specifically, it addresses the construction of mesh reflector antennas in space. The invention includes devices, systems, and methods designed to facilitate the creation and deployment of these antennas in a space environment by leveraging advanced assembly techniques.