A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

A docking node transporter tug is disclosed. The tug can dock with various spacecraft to allow access by people between the spacecraft. Further, the tug may dock with other specialty tugs to form a custom system.

The invention relates to a method for transferring a space payload from a first orbit to a second orbit. Said method is characterized in that the space payload, moving about the first orbit, is attached to a removable orbital towing assistance device including at least one fuel pouch. Said method includes the steps of: attaching (E1) an orbital transfer vehicle to the removable orbital towing assistance device; and transferring (E2) the space payload and the removable orbital towing assistance device to the second orbit by means of the orbital transfer vehicle. The invention also relates to a removable orbital towing assistance device intended for a space payload and an orbital transfer vehicle and enabling direct supply of fuel to the vehicle and/or the space payload.

Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

The present invention discloses a multi-sensor merging based super-close distance autonomous navigation apparatus and method. The apparatus includes a sensor subsystem, an information merging subsystem, a sensor scanning structure, and an orientation guiding structure, wherein a visible light imaging sensor and an infrared imaging sensor are combined together, and data are acquired by combining a passive measurement mode composed of an optical imaging sensor and an active measurement mode composed of a laser distance measuring sensor. Autonomous navigation is divided into three stages, that is, a remote distance stage, implemented by adopting a navigation mode where a binocular visible light imaging sensor and a binocular infrared imaging sensor are combined, a close distance stage, implemented by adopting a navigation mode where a binocular visible light imaging sensor, a binocular infrared imaging sensor and a laser distance measuring sensor array are combined, and an ultra-close distance stage, implemented by adopting a navigation mode of a laser distance measuring sensor array. Through the present invention, the field of view and the exploration range are widened, the problem of shielding existing in passive measurement is effectively solved, the precision of data measurement is ensured, and the navigation efficiency and the safety and reliability of navigation are improved.

A system for maintenance of a spacecraft constellation comprises a first spacecraft, configured to perform a primary mission while maintaining a primary orbit, and a second spacecraft. The second spacecraft is configured to perform the primary mission while maintaining the primary orbit and to determine a failure of the first spacecraft. The second spacecraft is further configured to, at least in part responsive to determining the failure of the first spacecraft, perform a secondary mission, wherein the secondary mission includes removing the first spacecraft from the primary orbit by the second spacecraft.

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.

Satellite systems and methods to perform rendezvous between a servicer satellite and an on-orbit satellite, and specifically to satellite systems and methods to perform rendezvous between a servicer satellite and an on-orbit client satellite using electric propulsion thrusters. In one aspect, a servicer satellite fires thrusters to reduce a separation distance between the servicer satellite and the client satellite and to remove an angular momentum or a rotational velocity of the servicer satellite, and fires thrusters to reduce a rate of closure between the servicer satellite and the client satellite and to remove the angular momentum or the rotational velocity of the servicer satellite.

A superconductive, electromagnetic launch system is implemented on a stratospheric airship. The launcher includes a plurality of twisted cylinders, wherein each of the plurality of cylinders has an infinity-type shape or other shape including one or two lobes. The lobes of the plurality of cylinders are aligned, and adjacent cylinders are connected by a bridge to form one continuous guideway. Superconducting coils are positioned external to a bore in the guideway and generate a magnetic field or flux within the bore that levitates and propels the vessel. A cooling system cools the superconducting coils to a transition temperature at which one or more superconducting materials in the plurality of coils transition to a superconducting state. The vessel is accelerated in the guideway and launched from a stratospheric altitude of the airship at a velocity necessary to reach space.

Vehicle capture assemblies and related devices, systems, and methods include one or more probe assemblies for engaging with and securing the target vehicle. The one or more probe assemblies may include one or more attenuation features or movable joints to enable and/or dampen movement of the one or more probe assemblies relative to a capture vehicle.