A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure

Disclosed are systems and methods for carrying an aeronautical or launch vehicle to altitude for release to independent flight. The system may comprise one or more mounting elements affixed to a carrier aircraft along a mounting axis and actuatable from a retention configuration to a release configuration. The retention configuration enables the mounting elements to secure the vehicle to the carrier aircraft. Actuation from retention configuration to release configuration releases the vehicle from the carrier aircraft. A detent element is configured to restrict movement of the vehicle rotationally about, and axially along, a roll axis of the vehicle with respect to the carrier aircraft when the vehicle is secured to the carrier aircraft. The system may include an adaptor beam to which each mounting element is fastened, and by which the affixing is achieved. The retention configuration may enable the mounting elements to secure the vehicle beneath the carrier aircraft.

Enclosures for facilitating activities in space, and associated systems and methods, are disclosed. A representative system includes a spacecraft having an enclosed interior volume (which can be formed by an inflatable membrane) and one or more unmanned aerial vehicles (UAVs) carried by the spacecraft and positioned to deploy into the enclosed interior volume. The system can include a remote-control system to control the one or more UAVs from a terrestrial location while the spacecraft is in space. A wireless charging system can provide electrical power to the one or more UAVs. A representative method includes configuring one or more controllers to launch a first spacecraft to a first orbit, launch a second spacecraft to a second orbit, move the first spacecraft to the second orbit, dock the first spacecraft with the second spacecraft, and broadcast an event within an interior volume of the first spacecraft to a terrestrial location.

A system for imparting linear momentum transfer may include a catching mechanism of a target space vehicle and a tether that is configured to impart a linear momentum transfer from the tether to the target space vehicle. The tether may be fixedly or detachably connected to a Kinetic Energy Storage and Transfer (KEST) vehicle that maneuvers and potentially retrieves the tether. Alternatively, the tether may be separate from the KEST vehicle and may be retrieved by a suitable retrieving mechanism, such as a robotic arm.

A satellite system includes a so-called carrier satellite and a so-called piggyback satellite, each one having an Earth face. The piggyback satellite is attached to the carrier satellite by fastening elements that can be released on command. The piggyback satellite includes propulsion elements suitable for maintaining same in orbit, and the carrier satellite includes propulsion elements for performing a change of orbit of the satellite system including the carrier satellite and the piggyback satellite. The piggyback satellite is attached to the Earth face of the carrier satellite in such a way that the Earth face of the piggyback satellite is essentially perpendicular to the Earth face of the carrier satellite.

A metal encapsulated ceramic tile thermal insulation system for rockets and associated methods is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end and includes a heat shield positioned at the second end. The heat shield includes a plurality of thermal protection apparatuses, where individual of the thermal protection apparatuses include ceramic tiles encapsulated by inner and outer metal layers, which are positioned on opposing top and bottom surfaces of the ceramic tiles. The plurality of thermal protection apparatuses includes a plurality of pins positioned within corresponding holes drilled through the ceramic tiles and are secured to the metal layers. The outer metal layer can protect the ceramic tile from tool strikes and debris and can also prevent water from reaching and being absorbed by the ceramic tile.

A system for air-launching a liquid fueled rocket launch vehicle using a tubular rocket support structure for holding the launch vehicle and for supplying the launch vehicle with make-up cryogenics, electrical power, and control signals, and for providing coupling to a launch-assist aircraft. The tubular rocket support structure contains cryogenic fluids, in addition to fuel and oxidizer, to cool the fuel and oxidizer during the pre-launch phase. The tubular rocket support structure has features that keep the liquid fuel and oxidizer from sloshing away from the tank outlet ports to the launch vehicle's rocket engine after release from the aircraft but before rocket launch. In operation, the aircraft controllably releases the tubular rocket support structure containing the launch vehicle, and the launch vehicle then launches from the rocket support structure.

A rocket launch system includes a tubular rocket launcher carriage with electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage is conveyed to a docking station supported into the stratosphere by a pair of secondary cables suspended under an attachment frame for tensioning balloons. The carriage is engaged by a carriage end gripper guided by two sets of secondary cables and two sets of tertiary cables and lifted by a lower hoist guided by the secondary cables to a lift ring assembly. This lower hoist is supported by an upper hoist suspended from the tensioning balloons attachment frame. The carriage, which engages a lift ring guided by two secondary cables, is elevated further, rotated in azimuth and elevation, and rocket ejection occurs from a launch tube during freefall of the carriage, with engine ignition occurring at a safe distance. The carriages have traction drives which grip cables from which they derive power and rotate to drive the carriage from the low altitude to the high altitude. The traction drives rotate in the opposite direction as the carriage descends the cable following the launch of a rocket under gravitational force. The kinetic energy of the traction drive is converted to electrical energy which is fed back to the cables during descent of the carriage.

A series of the relay of the electromagnetic launcher with a gun and a floating launch platform to launch projectiles in space, wherein the projectile is accelerated along a path using electromagnetic force until the projectile reaches a desired direction and position. The direction of the path is determined by orienting the path in the desired direction using a catcher. the catcher and rail gun projectile as high above as possible, coming close to near space. When the said projectile will reach the last platform, it will be launched by the railgun and ignite its rocket engine to take the payload in space or as required to eliminate the need for large rocket boosters to launch the projectile.

An electromagnetic lock release mechanism and a method for separating a satellite from a rocket are provided. The electromagnetic lock release mechanism includes: a frame, an ejection unit, a satellite unit, a lock release unit, and a lock release drive unit; the ejection unit includes an ejection spring, an ejection jack, and a spring sleeve; the lock release unit includes a locking pin, a locking slider, an unlocking spring, and a base; the lock release drive unit includes an electromagnet limit nut, an electromagnet moving core, and an electromagnet. Advantages of the present invention are as follows. The present invention is a point positioning lock release mechanism that can be used to separate micro-satellites and rockets and repeatedly tested, which provides reliable locking and separating of satellites and rockets in a complex mechanical environment, and can be repeatedly tested on the ground. The separation is entirely a mechanism action without pollution. The separation action is a continuous mechanism action, which has no impact on the satellite. The present invention reduces the cost of satellite development.