A rigidizing latch assembly, in embodiments, is a robotically compatible aerospace attachment mechanism may be used to rigidly attach units to a structure and typically comprises a male latch and a receptacle configured to cooperatively couple. The male latch typically comprises a male latch housing and a latch assembly movably disposed within the male latch housing; a driver operatively in communication with a latch support; a male latch core; a driver interface access port; and one or more extraction feet operatively in communication with the driver. The receptacle comprises a receptacle housing sized to receive a lower portion of the male latch housing; a positioning target adapted to provide a visual positioning targeting cue; and one or more latch interfaces dimensioned to releasably mate with a corresponding lead-in guide of the plurality of lead-in guides.

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 space-based circuit-replacing robotic system and method include a satellite grasper configured to grasp the satellite having a printed circuit onto which an integrated circuit is soldered and the integrated circuit is to be replaced; an access mechanism configured to remove the printed circuit and/or to provide access to the printed circuit; a printed circuit orientation device configured to orient a printed circuit such that sunlight is incident on the printed circuit; one or more temperature sensors configured to measure a temperature of the solder on the printed circuit; a processor configured to adjust a rate of heating to match a desired heating rate; a circuit grasping device configured to position the circuit for replacement; and an optical shield that is configured to be adjusted to allow light to pass substantially only to a desired area of the printed circuit.

Independently moving deployment and positioning space vehicles that are configured to deploy and/or position structures are disclosed. The deployment and positioning vehicles may provide a lighter weight, more flexible, and more reliable deployment and positioning system that enables the deployment of space structures that are potentially much larger than currently possible with mechanical components of the structure itself. The deployment and positioning vehicles could be used for removal of failure prone deployment mechanisms for spacecraft. Solar arrays, antennas, panels, instrument booms, etc. could be pulled open and locked into place, and then potentially repositioned and/or reoriented during a mission.

The present invention relates to an assembly apparatus for assembling components of spacecraft in space. The assembly apparatus includes: a core platform; and a mobile platform including an end effector configured to perform an assembly or manufacturing task. The mobile platform is connected to the core platform by a tether. The core platform includes a body and a coupling element connected to and extendable from the body such that the coupling element may be spaced from the body of the core platform. The tether connects the mobile platform to the body via the coupling element. The assembly apparatus further includes an actuator configured to vary the length of the tether extending between the coupling element and the mobile platform to control the position of the mobile platform relative to the body of the core platform.

An orbital satellite has a pair of multi-axis booms including both thrusters for course/attitude adjustment and an end effector for grappling payloads and manipulating other tools and objects. The satellite may launch with a primary payload affixed to a bus and one or more secondary payloads affixed to an ESPA ring. Once in orbit, the end effector may be used to grapple the primary and/or secondary payloads and rearrange them on the bus. In further aspects, the end effector may be used to make bus repairs or take measurements, or hold tools that are used to make bus repairs or take measurements.

A system and method of space exploration with a human-controlled proxy robot surrogates is disclosed. The method includes: training the human controlled proxy robot surrogates using human handlers; controlling the human-controlled proxy robot surrogates using the human handlers; and deploying a plurality of human-controlled proxy robot surrogates for extraterrestrial missions, missions on Earth, the Moon, and near-Earth locations. Each of the human-controlled proxy robot surrogates are in communication with each of the human handlers and wherein each one of the plurality of proxy robot surrogates is paired with each one of the plurality of human handlers. The human-controlled proxy robot surrogates further comprise an artificial intelligence (AI). The artificial intelligence of the disclosed method includes learned behavior.

The present invention relates to articulating spacecraft chassis and methods of making and using same. The present invention relates to spacecraft chassis and methods of making and using same. Such spacecraft chassis have a dynamic movement capability that allows the spacecraft to alter its structure while still maintaining industry volumetric launch standards. This capability increases opens up a wide range of achievable volumetric states and increases the ability to meet mission requirements by introducing a new tunable parameter. In addition, the judicious selection of certain dynamic movement parameters can result increased payload capabilities and improved maneuverability.

Disclosed are systems and methods for a distributed space transportation network. Satellite launches to orbit are more efficiently performed by large rockets. Modern satellites are in smaller form factor, leaving the large launch rockets with excess capacity. Small satellite operators can use ride-shares, but do not have efficient options for delivering their satellites to their desired destination and may be forced to operate their satellites in compromise orbits. The disclosed distributed space transportation network maintains a fleet of space tugs, which can dock with satellites in space at an initial arrival destination and transport the satellites to their final destinations. In one embodiment, the space tugs can dock with satellite depots to obtain fuel and repairs.

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.