Centripetal aerodynamic platform spacecraft

A centripetal aerodynamic platform spacecraft, thruster engine propelled, space access system, having accent, orbital and reentry configurations;

• said system comprising:
• a) a spacecraft body;
• b) an exterior region of said spacecraft body;
• c) an interior region of said spacecraft body;
• d) a plurality of thrust propulsion engines comprising air intake and thrust exhaust conduit within said interior region of said spacecraft body;
• e) the exterior region streamlined on said spacecraft body, and configured to allow high speed flight and aerodynamic atmospheric reentry capability;
• f) a plurality of loading ramp doors and cargo bay doors disposed on said spacecraft exterior region;
• g) the spacecraft body, comprising a balanced rotational center of mass and aerodynamic lifting and control surfaces;
• h) the spacecraft body, comprising a flattened sphere or disk-shaped, lifting body;
• i) the exterior region of said spacecraft body comprising an aerodynamic shape configured to enable airplane operational utility and a spacecraft hull maintaining habitable interiors;
• said exterior region comprising an aerodynamic flattened sphere profile;
• j) the interior region of said spacecraft body having a lifting body interior circumference boundary(s) that shapes the spacecraft hull of said spacecraft;
• k) the interior region of said spacecraft body is configured to simulate a desired percentage(s) of earth's 1G gravity when said lifting body interior circumference boundary(s) is attached within the interior region and is in full spacecraft body rotation, spinning about a vertical -Z- axis at a point in space, in obit or when transporting humans in space;
• l) the interior region of said spacecraft body comprising aerospace navigation utility systems, engine instrumentation, energy storage, life support systems, electrical storage and generation and fuel storage around a central cargo bay flanked by the plurality of thrust propulsion engines;
• m) the plurality of said thrust propulsion engines comprising one or more forward-front interior cased, vertical lift, downward directed thrust engines and a plurality of interior cased rear-aft directed thrust engines having horizontal to vertical nozzle pivot thrust capability;
• n) a plurality of fuel and oxidizer storage disposed within the spacecraft body;
• o) an aerodynamic circular shaped ring wing with integral vertical stabilizers on an underside of said exterior region of said spacecraft body;
• p) a plurality of engine air intake protection door(s) and recessed aerodynamic combustion air inlet(s) disposed on said spacecraft body;
• q) a plurality of retractable landing gear, disposed on a lower exterior region of the spacecraft body;
• r) plurality of maneuvering thrusters disposed on the said exterior region;
• s) a prelaunch compatible curved saddling common wing connecting two boosters comprising a releasable connection assembly;
• t) a heavy lift vertical booster prelaunch connecting means comprising a prelaunch booster connection assembly and in flight stage separation guide rail assembly for heavy lift booster launching;
• and
• u) a track with an alignment system configured to eliminate full body rotation of said spacecraft body.