Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.

Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.

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.

A projectile landing apparatus for retrieving a projectile includes a plurality of grippers disposed to be spaced apart. The plurality of grippers may include a support, a guide having one side connected to one end of the support, and a shock absorber having one end connected to the other end of the support and having the other end connected to the guide. The plurality of grippers may guide a projectile, buffer a load, and safely retrieve the projectile.

A rocket booster stage landing apparatus for more reliably landing a returning booster stage for reuse in propelling and launching subsequent main rockets.

A rocket booster stage landing apparatus for more reliably landing a returning booster stage for reuse in propelling and launching subsequent main rockets.

The present invention presents an adjustable speed reusable rocket with attachable wings system which is optimized for multiple purpose, such as space travel, high-speed long-distance travel between different addresses on earth, etc. The rocket system comprises an adjustable speed rocket propulsion system (rocket booster), an attachable wings system, a payload or space shuttle and may include slider wings system, etc. Firstly, the rocket system flies at a lift force caused by the attachable wings system at a low speed (e.g., Mach 0.5˜3). While the rocket system reaches relatively high altitude (e.g., 25,000 meters), at this altitude, the air density is extremely low comparing with the surface of earth at zero sea level, and then the attachable wings system may detach from the rocket system and fly to a designated location as a glider or by its engine on a runway, and the rocket system begins to fully initiate propulsion system and exert the payload to forward at a super high speed. Comparing with rocket fully initiate propulsion system from earth surface, the aerodynamic friction and the aerodynamic heat caused by air is extremely small and low.

An electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field is disclosed. The assembly includes a plurality of coaxial cables for an electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field. Each coaxial cable includes an electrically conductive core surrounded by a first electrically insulating sheath, and an electrically conductive current return circuit mounted outside the first electrically insulating sheath. The current return circuit includes a first end electrically connected to a first end of the core of the coaxial cable.

An electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field is disclosed. The assembly includes a plurality of coaxial cables for an electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field. Each coaxial cable includes an electrically conductive core surrounded by a first electrically insulating sheath, and an electrically conductive current return circuit mounted outside the first electrically insulating sheath. The current return circuit includes a first end electrically connected to a first end of the core of the coaxial cable.

A method and a device for deorbiting artificial satellites from Earth orbit, the artificial satellite having multilayer insulation, at least partially detaches at least one layer of the multilayer insulation from the artificial satellite. Due to detachment of the layer, the underlying satellite structure is exposed to environmental influences. This exposure accelerates the self-disintegration of the artificial satellite, and thereby reduces the mass and increases the ballistic coefficient. Splaying out the layer augments its cross-sectional area and leads due to energy reduction to a premature re-entry into Earth's atmosphere. A number of layers can be arranged here so that regardless of a rotation of the satellite, at least one surface is always directed against the aerodynamic flow.