Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.

The disclosure describes various aspects of a space-based radioisotope production system and methods use. In one aspect, a propellant is accelerated by decay energy to yield thrust. The decay energy is provided by activating a target material. In one aspect, a radioisotope rocket thruster may be recharged or “reactivated” in a space-borne charging station. The activated isotopes may also be used generate electricity. The space-borne charging station may also be used for irradiating other items in space for any number of purposes.

A system and method for vaporizing space debris in space. The system includes a spacecraft body, a primary solar concentrator mounted to the spacecraft body that collects and focuses solar flux from the sun, and a secondary solar concentrator positioned at a focal point of the primary solar concentrator that refocuses the focused solar flux. A manipulator arm coupled to the spacecraft body grabs the space debris in space and positions it at a location where the refocused solar flux vaporizes the debris. The secondary solar concentrator can be a point-source concentrator, the primary solar concentrator can be a parabolic mirror, a Fresnel lens or a light focusing element or assembly, and the space debris can be a retired spacecraft or launch vehicle upper stage or component.

Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.

A modular and scalable system to transfer space articles between space orbits. In one embodiment, the system employs a rendezvous vehicle which docks with a space article in an initial orbit, the connected stack then docking with a locomotive vehicle which maneuvers to a targeted orbit where the space article is detached. In one feature, the rendezvous vehicle and locomotive vehicle use a common propellant and the space article is a satellite.

A first spacecraft comprises a drive mechanism. A second spacecraft comprises a valve for filling/draining the second spacecraft. The coupling assembly comprises a first connector comprising an actuating member configured to engage and open the valve and a coupling member configured to couple to the drive mechanism. A second connector comprises a stop portion and a bore for transferring fluid. Operation of the drive mechanism rotates the coupling member and the second connector together to screw the second connector onto the valve until the stop portion engages the valve, the actuating member being prevented from moving relative to the second connector to open the valve whilst the lock is in the locked state. Once the stop portion engages the valve, operation of the drive mechanism to exert a torque on the coupling member greater than a predetermined torque level moves the lock to an unlocked state wherein the actuating member is moveable relative to the second connector to engage and open the valve.

This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.

A method for capturing and deorbiting space debris includes: providing a space debris capturing device; deploying the space debris capturing device in planetary orbit; determining, via an onboard global positioning system unit, the position and orbit velocity of the space debris capturing device; receiving an initial target set including a first database of space debris targets that are within range of the space debris capturing device; performing a first algorithm to convert the initial target set to an accessible target set including a second database of space debris targets that are within range of the space debris capturing device, the second database is smaller than the first database; performing a second algorithm to convert the accessible target set to a final target set including a third database of space debris targets to be captured by the space debris capturing device, the third database is smaller than the second database; transferring the space debris capturing device to a position within a capture range of a first space debris target of the third database; capturing the first space debris target via a capture mechanism of the space debris capturing device; jettisoning the capture mechanism and the first captured space debris target into a decaying orbit; repeating the transferring, capturing, and jettisoning steps for all but a final one of the remaining space debris targets of the third database; and positioning the space debris capturing device and the final captured space debris target into a decaying orbit.

The invention is methods for landing rockets with precision using deep reinforcement learning for control. Embodiments of the invention are comprised of three steps. First, sensors collect data about the rocket's physical landing environment, passing information to rocket's database and processors. Second, the processors manipulate the information with a deep reinforcement learning program to produce instructions. Third, the instructions command the rocket's control system for optimal performance during landing.

The Guideless Resilient Androgynous Serial Port (GRASP) mechanism provides an androgynous mechanical and electrical interface that can be tailored to the meet the requirements of a given application. Each mechanism is equipped with physical connections (spring pins) for both power and data transmission between modules.