|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/13 ; 244/36 ; 244/110D ; 244/113|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 10 인용 특허 : 0|
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 ...
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 convent...