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The reusable space launch system has a first stage vehicle or aerospacecraft, a second stage vehicle or reusable spacecraft and a third stage vehicle or reusable orbit transfercraft. All the stages have the basic aerodynamic vehicle elements of a fuselage, wings, and tail, with the incorporation of

The reusable space launch system has a first stage vehicle or aerospacecraft, a second stage vehicle or reusable spacecraft and a third stage vehicle or reusable orbit transfercraft. All the stages have the basic aerodynamic vehicle elements of a fuselage, wings, and tail, with the incorporation of control surfaces to supply lift, stability and control. The aerospacecraft is configured to use ejector ramjet engines for powered flight and includes equipment to capture air to supplement oxidizer for the ejector ramjet engine during take-off and extreme high altitude In order to optimize aerospacecraft performance in a pull up movement to exit the sensible atmosphere, the aerospacecraft may include auxiliary ascent rocket engines. The aerospacecraft payload bay is accessed by nose load re-closable payload fairings. The reusable spacecraft is mounted on tracks on each lower side of the aerospacecraft payload bay. For staging, a catapult ejects the reusable spacecraft and its payload through the opened payload fairings The aerospacecraft closes the payload fairings, re-enters the atmosphere, flies back to the operating base and lands for reuse. After ejection from the aerospacecraft, the reusable spacecraft and reusable orbit transfercraft may unfold their airfoils.

대표청구항 ▼

[We claim:] [1.]a) a fuselage, a pair of wings with a plurality of control surface and a tail with a rudder;b) the fuselage comprising:i) a conic curve shape for an upper fuselage from a nose end to a tail end;ii) a straight line conic shape for a lower fuselage from the nose end to an engine nacell

[We claim:] [1.]a) a fuselage, a pair of wings with a plurality of control surface and a tail with a rudder;b) the fuselage comprising:i) a conic curve shape for an upper fuselage from a nose end to a tail end;ii) a straight line conic shape for a lower fuselage from the nose end to an engine nacelle; the engine nacelle aft of a plurality of inlets having a constant semicircular cross section to a plurality of engine exhaust nozzles; and a lower aft fuselage having a decreasing concave conic shape to the tail end;iii) a maximum cross section dimension of the fuselage is at the wing root leading edge and is such to enclose a payload bay; and access to the payload bay is by means of two clam shell doors from the nose end aft being a payload bay hood and a payload bay ramp which may be opened to receive a payload, closed for flight operations and opened for payload removal;c) the wings comprising:i) a pair of wing strakes added to the fuselage at a centerline to accommodate the wings; andii) each wing leading edge is swept back from a strake junction with each wing outer portion curved back to a wing tip;d) the tail comprising:i) the tail mounted slightly forward of the tail end and a tail leading edge swept back from a tail root; andii) a tail outer portion curved back to a tail tip;e) an attitude control system with a plurality of attitude control rockets mounted in the payload bay hood and the wing tips with supporting a plurality of position fuel tanks;f) a nose gear and a set of mid section landing gears;g) an integral ascent tank contained in the fuselage aft of the payload pay, a plurality of auxiliary ascent tanks, and a cradle tank;h) an air liquification unit which receives air from the air liquification inlets connected by ducting contained in the engine nacelle and which liquifies the air for storage in a plurality of liquid air tanks;i) an avionics system, a plurality of helium tanks and a plurality of primary power propellant units; andj) a plurality of ejector ramjet engines mounted in the engine nacelle which receive ambient air from the engine nacelle inlets connected by engine inlet ducts.