There is provided an apparatus for capturing a space object, the apparatus comprising a harpoon element for penetrating the object, the harpoon element being configured to form part of a harpoon for launching towards the object; and penetration control means for controlling the penetration of the harpoon element into the object. The penetration control means can comprise a compressible component, forming part of the harpoon, for absorbing some of the kinetic energy of the harpoon. Alternatively or additionally, it may comprise means for varying the launch speed of the harpoon.

The present invention extends to methods, systems, devices, apparatus, and computer program products for aligning a target with and/or over and/or into a specific position and orientation. Embodiments include one or more capture components, such as, engagement lines, spars, or struts, that can be actuated together or independently to position a vehicle in a capture area defined by a ring or other geometry. A vehicle can include a sloped surface feature configured to engage with the capture components. When actuated, the capture components draw the sloped surface feature towards and down into the center of the defined capture area. Variations allow a vehicle to be rotated in place, repositioned in place, or clamped securely in place. Positioning and rotation allows alignment with replenishment devices for resupplying and refueling. In this way, a vehicle is relieved from having to have precision terminal guidance for landing and recharging.

A space vehicle includes a massless payload. The massless payload comprises dynamically modifiable software configured to indicate one or more actions to be taken by the space vehicle. The space vehicle also includes a primary controller that includes software that is not modified based on modifications to the massless payload, a test controller operatively communicating with the massless payload. The system also includes one or more operational systems including at least one of actuators or sensors of the space vehicle that are controlled based on commands from the test controller during a test condition generated to implement the one or more actions indicated by the massless payload and by the primary controller during normal operation.

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 one or more electromagnets spaced apart and suspended on a frame that may include means for compensating for any out of plane misalignments during capture. The client spacecraft includes a striker plate that covers an area, nominally larger than the footprint of the capture mechanism, that is sized to accommodate a capture envelope determined by the rendezvous and proximity sensing systems. The electromagnets attract the striker plate to capture the client spacecraft in order to provide on-orbit servicing. The docking system has multiple degrees of freedom that are independent of the capture system; docking is accomplished by mechanically coupling the two spacecrafts together, post capture. During docking, electrical and fluid transfer connections may also be accomplished. The servicing spacecraft further comprises a manipulator arm that may be configured to position/align the captured client spacecraft for docking, thereby permitting a very flexible, larger, capture envelope, and reducing operational complexity.

An example system for controlling a target satellite includes: a satellite-control spacecraft including: a propulsion subsystem configured to propel and navigate the spacecraft proximate the target satellite; and a satellite-capture subsystem configured to: capture the target satellite; apply a control medium to the target satellite, the control medium including an electrically conducting and/or magnetic material; and release the target satellite; and an energization assembly configured to energize the control medium to release energy for controlling, propelling and navigating the target satellite.

Systems and methods for transferring, storing, and/or processing materials, such as fuel or propellant, in space, are disclosed. A representative system includes a flexible container that is changeable between a stowed configuration in which the flexible container is contained within a satellite, and a deployed configuration in which the flexible container extends away from the satellite. The system can include a tanker with a storage container to dock with and refuel a satellite. Another representative system includes a controller programmed with instructions that position a spacecraft with a storage container in a first orbit, transfer the spacecraft to a second orbit, dock the spacecraft with a satellite in the second orbit, transfer material between the storage container and the satellite, undock the spacecraft from the satellite, and, optionally, return the spacecraft to the first orbit. An androgynous coupling system with mechanical and fluid connectors facilitates docking and material transfer.

The invention relates to the protection of spacecraft from debris and to de-orbiting devices of the atmospheric drag type, and to debris sweeping apparatus for the removal of debris from the space environment. The debris shielding apparatus for a spacecraft has a shield unit including a shielding surface for impeding incident debris. The shield unit is attached to the spacecraft body and has a drive mechanism for positioning the shield unit in relation to the spacecraft body. The drive mechanism is capable of moving the shield unit between a stowed first position and a deployed second position. In the deployed second position the plane of the shielding surface is at an angle to the spacecraft body.

This present invention describes initial sequential methods for constructing and placing into operation a multi-purpose maintenance complex and a space dock in high geosynchronous orbit. This is dual function complex that can provide a orbital platforms to a commercial profitable enterprise or to the Department of Defense (DoD) to enhance their capabilities. A complex will have the capability to fabricate, assemble, test, and place into full operation any size orbital and planetary surface complexes and spacecraft. DoD mission capabilities embracing satellite repairs, research, national security and deterrence, space junk disposal support and other services while in orbit.

Herein is disclosed a tool, system and method for refueling on-orbit spacecraft. The tool and system are configured to allow for resupply of spacecraft configured to be propelled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The refueling tool is particularly suited for resupply of satellites not originally prepared for refueling but the system may also be used for satellites specifically designed for refueling.

A fuel depot in space is provided. The fuel depot has a collapsible housing with a guidance, navigation, and control (GNC) system, a power management system, and a reaction control system (RNC). Connected to the housing are a plurality of fuel tanks that are connected via collapsible rods. The fuel tanks have pipe systems that are in communication with a plurality of pumps to transfer fuel from the tanks through a refueling arm and into a spacecraft during refueling.