An aerodynamic platform or spacecraft including a habitable 1G centripetal force rotating gravity producing interior corridor within an aerodynamic shell and an aerodynamic drone booster launch system with reentry and reuse capability.
대표청구항▼
1. 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
1. 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; andu) a track with an alignment system configured to eliminate full body rotation of said spacecraft body. 2. The system as described in claim 1, further comprising: a) a front pilots cabin with 90 degree rotating seats positioned within the interior region of said spacecraft body;b) a passenger sleep quarters;c) a spacecraft airlock associated with the interior region of said spacecraft body; andd) a storage area(s) within the interior region of said spacecraft body. 3. The system as described in claim 1, wherein the aerodynamic circular ring wing further comprises: a) an aerodynamic open center, and a washer-shaped ring wing surface;b) the plurality integral vertical stabilizers are retractable and are configured to serve as a retractable vertical landing strut assembly;c) an exterior underbody region recessed circular, aerodynamic concave receiving profile for said washer-shaped ring wing; andd) a mechanical interior housing for said plurality of vertical stabilizers when the aerodynamic circular ring wing is raised or retracted. 4. The system as described in claim 1, further comprising a plurality of single hinged recessed aerodynamic engine protection door(s) configured to rest in a concave three sided, triangular curved and tapered recess(s); said plurality of single hinged recessed aerodynamic engine protection door(s), hinged only on one side of said tapered recess(s) in the spacecraft body, the aerodynamic engine protection door(s), having a single side, single hinged, door pivot axis, recessed at one end forming a tapered aerodynamic indention on the exterior region forming an aerodynamic concave SCOOP; said system having the plurality of single hinged recessed aerodynamic engine protection door(s) further comprising: a) an actuator assembly;b) one or more door seal elements;c) an alignment and configuration of exterior body surfaces;d) a recessed triangular door frame(s);e) one or more exposed side(s) having protection surface layer(s);f) an internal structural door panel ribs strengthening element(s); andg) a recessed triangular exterior surface on the exterior region configured to receive one of said plurality of aerodynamic engine protection door(s) when opened, thereby enabling the one of said plurality of aerodynamic engine protection door(s) to securely rest against the aerodynamic body envelope within recessed variable side length triangular exterior surfaces conforming to contoured aerodynamic surfaces around engine bay protection door openings; said plurality of aerodynamic engine protection door(s) providing engine protection during reentry, and when in hazardous environments, eliminating double hinged, exterior door openings, double flaps, and non-aerodynamic components on exterior surfaces. 5. The system as described in claim 1, wherein the plurality of thrust propulsion engines further comprises a plurality of hybrid horizontal rear directed thrust and vertical downward directed thrust engineer said engineer comprising phased supersonic to hypersonic turbojet engines components wherein a first propellant fuel is atmospheric oxygen and jet fuel; said engines transition to rocket thrust engine components wherein a second propellant is liquid oxygen and rocket fuel. 6. The system as described in claim 1, further comprising a rotation track support alignment system supporting at least one or more freely independently rotating centripetal rotational gravity corridor(s), within said interior region of said spacecraft body rotating at variable speeds; said rotation track support alignment system comprising: a) a fixed alignment track(s);b) a roller pin alignment bracket assembly with axle slip spin dry lubricant surfaces attached to said fixed alignment track(s);c) an unfixed bearing track(s);d) a composite polymer ball bearing assembly between the said fixed and unfixed tracks; ande) a free self-lubricating, solid polymer, lubricant ball bearing separator-spacer assembly within facilitating even ball bearing migration and rotation of said centripetal rotational gravity corridor(s).
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (19)
Depeige, Alain; Jarrige, Jean-Luc, Boarding device for aircraft and flying wings equipped with such a device.
Anatoly Ivanovich Kiselev RU; Alexandr Alexeevich Medvedev RU; Jury Nikolaevich Trufanov RU; Igor Sergeevich Radugin RU; Jury Leonidovich Kuznetsov RU; Alexandr Alexandrovich Pankevich RU; Genn, Reusable booster for the first stage of a launcher.
MacConochie Ian O. (Yorktown VA) Briener Charles A. (Hampton VA), Two-stage earth-to-orbit transport with translating oblique wings for booster recovery.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.