초록 ▼

An aircraft having a composite configuration comprising a conventional fuselage forebody portion which symmetrically and variformly blends into a relatively wide, substantially flat beaver-tail-like afterbody, with the afterbody having an integral pitch trimming camber and a composite pitch control

An aircraft having a composite configuration comprising a conventional fuselage forebody portion which symmetrically and variformly blends into a relatively wide, substantially flat beaver-tail-like afterbody, with the afterbody having an integral pitch trimming camber and a composite pitch control device and air brake, hinged transversely thereacross and forming at least a part of its trailing edge. The beaver-tail afterbody is geometrically blended into and joined with the after portion of the conventional forebody through the medium of an intervening medial body defined by a geometric transition piece. The composite aircraft is further capable of fixedly accommodating any type of conventional wing configuration without the necessity for any adaptative, structural change or modification and also carries conventional propulsion units and control surface components.

대표청구항 ▼

In a supersonic aircraft having propulsion means, stabilizer fin means and a supersonic configuration fuselage provided with wings extended to opposite sides thereof, the improved fuselage that has a longitudinally and transversely cambered airfoil configuration of high fineness ratio in which the a

In a supersonic aircraft having propulsion means, stabilizer fin means and a supersonic configuration fuselage provided with wings extended to opposite sides thereof, the improved fuselage that has a longitudinally and transversely cambered airfoil configuration of high fineness ratio in which the airfoil fuselage extends flat-like substantially continuously from the forebody portion of the fuselage to the trailing edge thereof which comprises: a supersonically faired fuselage forebody component for accommodating the aircraft crew and for housing conventional apparatus and instruments for operation and control of the aircraft; a fuselage afterbody component having a beaver-tail-like planform and a longitudinally cambered airfoil cross-sectional profile with a relatively wide, flat-like lateral cross-section for effecting optimum pitch trim while operating in a desired supersonic speed regime; a fuselage intervenient body component adapted for attachment of aircraft wings thereto and having a longitudinally cambered airfoil cross-sectional profile with a generally flat-like lateral cross-section that flattens progressively from the forebody component towards the rear of the aircraft so as to aerodynamically blend and fair said forebody into said afterbody; said fuselage forebody component extending from the aircraft nose to about the area of attachment of the forward portion of the wing structure to the fuselage; the intervenient body component extending therefrom aft to about the area of attachment of the rear portion of the wing to the fuselage; and the afterbody component extending therefrom aft to the rearmost edge or tip of the airplane fuselage; said fuselage intervenient and afterbody components having upper and lower surfaces together forming a substantially smoothly continuous airfoil section extending continuously from said forebody component to the trailing edge of said afterbody component, the upper surface of the fuselage intervenient body component extending as a flat-like substantially constant transverse curvature throughout substantially the full longitudinal extent of the intervenient body component and at least a portion of said afterbody component; attachment means carried by said intervenient body component for affixing aircraft wing structure thereto so as to extend on opposite sides thereof; said forebody component, intervenient body component and afterbody component forming an airfoil configured high fineness ratio fuselage that is both progressively flattened and longitudinally and transversely cambered in longitudinal cross-section substantially continuously from said forebody to saiD trailing edge, said fuselage afterbody component having the lateral edges thereof approximately parallel for the major portion of the length thereof; whereby at supersonic speed drag resulting from wake turbulence from said fuselage afterbody is largely eliminated and aerodynamic force is gained from said fuselage independent of the aircraft wing structure to thereby reduce trim drag otherwise tending to slow the speed of the aircraft.