A harmless low-consumption on-orbit continuous launch system includes a satellite platform, a launch apparatus and a plurality of CubeSats. The satellite platform carries the launch apparatus and dozens or hundreds of CubeSats, and is launched from a ground into an orbit for on-orbit operation. The launch apparatus is configured to store the plurality of CubeSats and provide power for on-orbit launching of each of the CubeSats. A solid working medium in the launch apparatus is activated by heating to undergo a phase change, and the activated solid working medium expands instantly and is converted into a high-pressure gaseous working medium. The high-pressure gaseous working medium does work to eject the CubeSats, such that the CubeSats obtain a speed increment. The CubeSats enter a transfer orbit towards different target spacecraft through the speed increment applied by the launch apparatus to perform a plurality of different on-orbit serving missions.

An apparatus for launching, recovering, transporting, and storing vehicles is disclosed. The apparatus stabilizes the vehicle while it is in operation or inactive and has a frame connected to at least one stabilizer. In certain configurations, the apparatus stabilizes the vehicle without using the vehicle's onboard landing gear. The apparatus may also include at least one pad connected to the apparatus.

An interplanetary transportation system that includes a tunnel that spans between different planetary bodies and uses an electromagnetic propulsion system for propelling space-faring vehicles. The tunnel can be fixed and powered by outer space energy resources, such as the sunlight. The tunnels include fixed spaced rings and a mobile ring. The vehicle can be mounted to the mobile ring, wherein the spaced rings and the mobile ring propels the vehicle using motional EMF.

A representative system includes an alignment tool for aligning attachment interfaces of horizontally-oriented launch vehicle portions. The tool can include a receiver assembly for connecting to a first launch vehicle portion and an actuation assembly for connecting to a second launch vehicle portion. When a first connecting element of the receiver assembly is engaged with a second connecting element of the actuation assembly, the second connecting element can apply force to the receiver assembly, and the actuator assembly applies an opposite force to the second launch vehicle portion, to align fastening features in the launch vehicle portions and/or to reshape the launch vehicle portions. A representative method includes connecting the alignment tool to the launch vehicle portions and operating the tool to apply oppositely-directed forces to align the launch vehicle portions for installing fasteners to connect the launch vehicle portions. One or more bracing beams can connect two tools together.

The disclosed propulsion system of a space vehicle and the methods of operating the propulsion system use a microwave energy source to heat propellant in a propellant chamber that pierces and traverses a waveguide carrying the microwave energy. In some implementations, the microwave energy ionizes and further heats the propellant in the propellant chamber. The partially ionized and heated propellant may exit the propellant chamber via a nozzle to generate thrust.

The invention relates to a device and a method for the connection and linear separation of two elements, such as the two stages of a spacecraft, consisting in using a tube containing a pyrogenic-type material and a glue arranged around the tube, particularly in contact with the elements. The pyrotechnic triggering of the pyrogenic material causes heating and the melting or carbonisation of the glue and the separation of the two elements.

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.

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.

A vertical landing apparatus comprises a body, at least three legs, and at least three leg locks coupled to the body. The body comprises a body lower end and at least three leg housings. Each leg housing comprises a passage extending longitudinally upwardly from a leg housing lower opening. Each leg is translatable within the passage of a respective leg housing between deployed and leg locking positions. Each leg comprises a leg lower end that is longitudinally outboard of the body lower end. Each leg comprises a longitudinally outboard extent from the body lower end to the lower leg end that is longer when in the deployed position than the leg locking position. Each leg lock is associated with a respective leg and configured to move between a locked position in which translation of the leg is prevented and a disengaged position in which translation of the leg is allowed.

Thermal control of powered systems on-board a flight vehicle is achieved by leveraging the latent heat storage capacity of Phase Change Materials (PCMs) to maintain the operating temperature at or slightly above the melting temperature of the PCM. The invention is particularly well suited for use with powered systems such as laser, microwave emitters, RF sensors and high-density power electronics that must operate at a desired operating temperature while generating considerable waste heat in a confined packaging volume of smaller flight vehicles such as missiles, rockets, guided projectiles, drones or other such platforms.