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 modular service interface is provided. The modular service interface includes separable first and second halves, one or more alignment features, a connector interface and one or more electropermanent magnet modules, connector interface configured to mate the first and second halves when activated and allow the first and second halves to be separated when inactivated. The modular service interface includes no mechanical actuators to retain the first half to the second half.

A system to create a magnetic field around the outside of a spacecraft to afford human occupants and electronic equipment with protection from cosmic and solar radiation. Using electromagnets to generate magnetic fields placed on the outer surface of the spacecraft, cosmic and solar radiation may be deflected from entering the main body of the spacecraft. In addition, the magnetic field lines are kept away from the human occupants and interior electronic equipment. Side electromagnets are placed on the side outer surface of the spacecraft and separate electromagnetics are positioned in a cross shaped configuration at the front and rear of the spacecraft in alignment with the side electromagnets. Magnetic field lines are channeled around the outside of the spacecraft or centered on the center of quadrupole magnets placed either at the front of rear of the spacecraft.

A spacecraft refueling and storage system comprising a first tank and a second tank for storing propellant, a rotatable shaft to which the first and second tanks are mounted for rotating the first and second tanks about an axis of the shaft, and a drive motor for rotating the shaft so that upon rotation of the first and second tanks, liquid propellant is separated from gas in the propellant and settled to an outer portion of the first and second tanks.

Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.

A spacecraft for changing an orbit or an attitude of a target in outer space by irradiating the target with a laser, the spacecraft includes: a laser apparatus configured to generate the laser; a focusing unit configured to converge the laser; a detecting unit configured to acquire detection information including a distance between the spacecraft and the target; and an irradiation control unit configured to control the focusing unit on the basis of the distance so that the laser converges on the target.

Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.

Spacecraft servicing systems include a spacecraft servicing device and at least one mission extension pod comprising at least one spacecraft servicing component. The spacecraft servicing device is configured to transfer the at least pod to a target spacecraft in order to service the target spacecraft with the at least one spacecraft servicing component of the at least one pod. Spacecraft servicing pods configured to be supplied to a spacecraft with a spacecraft servicing device include at least one spacecraft servicing component.

A system and method for installing, deploying, and recovering a plurality of spacecraft that provides an ease of use and structural stability, and facilitates a standardization of spacecraft design. In embodiments of this invention, threaded rods are arranged orthogonal to a surface of a baseplate, and each spacecraft includes a coupling mechanism that selectively engages or disengages each threaded rod. Each spacecraft is added to the stack by engaging its coupling mechanism and rotating the threaded rods while the preceding spacecraft on the stack disengage their coupling mechanisms, thereby enabling the spacecraft to travel along the threaded rods toward the baseplate. When all the spacecraft are added to the stack, the stack is preloaded by rotating the treaded rods into a terminator component at the top of the stack while the coupling mechanisms in all of the spacecraft are disengaged. Spacecraft are deployed by reversing the process.

A coupling system and a method of coupling two objects is provided. The coupling system including a passive unit having a first side and an opposing second side, the first side having a recess with a lip. The coupling system further having an active unit that includes an actuator, a cam mechanism and a plurality of capture rollers. The cam mechanism is operably coupled to the actuator, the cam mechanism being movable from a stowed position to a deployed position. The plurality of capture rollers is operably coupled to the cam mechanism to move from a first position to a second position in response to the cam mechanism moving from the stowed position to the deployed position, the plurality of capture rollers engaging the lip in the second position when the passive unit is in contact with the active unit.