A rocket-powered space launch system comprises both a vehicle segment with an integrally designed propulsion subsystem and a supporting ground facility segment. Elements of a propulsion unit as easily accessed for removal and replacement of individual components. Said launch system is highly reusable, operable, and facilitates governmental agency regulatory compliant safety of occupants and public without passenger escape function and/or commanded vehicle destruction.

A rocket-powered space launch system comprises both a vehicle segment with an integrally designed propulsion subsystem and a supporting ground facility segment. Elements of a propulsion unit as easily accessed for removal and replacement of individual components. Said launch system is highly reusable, operable, and facilitates governmental agency regulatory compliant safety of occupants and public without passenger escape function and/or commanded vehicle destruction.

A system and method for acceleration of a flying object, preferably with large take-off mass is described. The system can accelerate an object with a mass of several hundred thousand tons. The system includes the use for object acceleration of free (for the period of direct acceleration) energy of exhaust gases of the system elements' jet engines, pushing-out force of water, force of Earth's gravity, initial movement energy of the compressed spring and vacuum, lifting force of light gases, as well as energy consuming, for the period of acceleration, action of the system elements' jet engines, gunpowder gases and drives. The system and the method include acceleration of an object simultaneously in several systems accelerating one inside the other with the summation and increase of acceleration speed. The main elements of the system: launch barrel, carrier and booster pistons with jet engines, and pushing the pistons support.

An engine start system includes a facility that has a ground based hydraulic pressurization system and a combustor of a liquid propellant rocket engine. The engine is fluidly coupled to the ground based hydraulic pressurization system. The liquid propellant rocket engine is operably detachable from the ground based hydraulic pressurization system.

An engine start system includes a facility that has a ground based hydraulic pressurization system and a combustor of a liquid propellant rocket engine. The engine is fluidly coupled to the ground based hydraulic pressurization system. The liquid propellant rocket engine is operably detachable from the ground based hydraulic pressurization system.

An interlocking paver system including a polygon paver and a spacer paver is provided. The polygon paver may have a top level having a top level polygon paver perimeter and a bottom level secured to and protruding from the top level and having a bottom level polygon paver perimeter contained within the top level polygon paver perimeter. The spacer paver may have a top level having a top level spacer paver perimeter and a bottom level secured to and protruding from the top level and having a bottom level spacer paver perimeter extending beyond an entirety of the top level spacer paver perimeter The spacer paver may be configured to selectively interlock with the polygon paver. The top level spacer paver perimeter, top level polygon paver perimeter, and bottom level spacer paver perimeter are different from one another.

Systems, methods, devices, and non-transitory media of the various embodiments may enable the identification of launch opportunities. The integrated approach of the various embodiments leverages instrumentation, data and communication systems available about, or from, the National Airspace System (NAS), Marine Transportation System (MTS), and orbital catalog to enable safe passage for space vehicles, passengers, and payloads. The condition-based launch criteria of the various embodiments may improve mission assurance and public safety while simultaneously supporting a customer's launch on readiness schedule.

A universal white room disposed at the distal end of an access arm of a launch pad service tower utilizes multiple interchangeable modular rooms of varying shapes, sizes and configurations to interface with access points on multiple differently configured launch vehicles and/or payload(s). The interchangeable modular rooms attach to a common portal in the white room allowing a single white room to be used. The modular rooms may be stationary relative to the white room or movable relative to the white room.

A universal white room disposed at the distal end of an access arm of a launch pad service tower utilizes multiple interchangeable modular rooms of varying shapes, sizes and configurations to interface with access points on multiple differently configured launch vehicles and/or payload(s). The interchangeable modular rooms attach to a common portal in the white room allowing a single white room to be used. The modular rooms may be stationary relative to the white room or movable relative to the white room.

The present invention relates to a table (2) on which additive manufacturing is carried out; a plurality of panels (3) which are produced by the additive manufacturing method and surround a plurality of satellite elements (E) such as payload, satellite electronic circuits and mechanisms such that they protect the satellite elements (E) from space conditions, wherein satellite elements (E) are mounted on the panels (3) in a removable manner; at least one hinge (4) which allows the panels (3) to rotate around each other, and produced by additive manufacturing method in an integrated manner with the panels (3).