IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0764925
(2010-04-21)
|
등록번호 |
US-7854409
(2011-02-14)
|
발명자
/ 주소 |
- Dizdarevic, Faruk
- Dizdarevic, Mithad
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
3 |
초록
▼
Canarded deltoid main wing aircraft idea allows for design of large supersonic civil and military aircraft with cruising speeds of up to Mach 3 at the altitude of over 25,000 meters. The fuel consumption per unit of payload of such aircraft would be at least twice lower with a longer range of over 5
Canarded deltoid main wing aircraft idea allows for design of large supersonic civil and military aircraft with cruising speeds of up to Mach 3 at the altitude of over 25,000 meters. The fuel consumption per unit of payload of such aircraft would be at least twice lower with a longer range of over 50% when compared to existing supersonic aircraft of the same size. Simultaneously, the flight safety and ride quality during takeoff and landing at low speeds would be similar to the existing subsonic passenger aircraft. A low fuel consumption, long range, high ride quality, and high flight safety of these aircraft are widely opening a door for design of supersonic long range continental and intercontinental passenger aircraft that would be highly competitive with existing long range high subsonic passenger aircraft.
대표청구항
▼
We claim: 1. A canarded deltoid main wing aircraft having a symmetry plane and a transversal axis, said transversal axis being perpendicular to said symmetry plane, said symmetry plane including a longitudinal and a vertical axis, said longitudinal axis coinciding with airflow direction, said canar
We claim: 1. A canarded deltoid main wing aircraft having a symmetry plane and a transversal axis, said transversal axis being perpendicular to said symmetry plane, said symmetry plane including a longitudinal and a vertical axis, said longitudinal axis coinciding with airflow direction, said canarded deltoid main wing aircraft comprising: a. means for aerodynamic lift production, said means for aerodynamic lift production being symmetrical relative to said symmetry plane, the cross-sections of said means for aerodynamic lift production being shaped as airfoils in airflow direction, the central section of said means for aerodynamic lift production providing inner space for bulky payload accommodation, the central section leading edge consists of two symmetrical straight lines, said central section leading edge having a predetermined sweepback angle, said means for aerodynamic lift production having a predetermined airlifting area for a predetermined payload capacity of said canarded deltoid main wing aircraft, said means for aerodynamic lift production including a leading and a trailing edge; b. front means for pitch control, said front means for pitch control consist of a port and a starboard canard section, the port canard section and the starboard canard section being mutually symmetrical relative to said symmetry plane, said port and said starboard canard section having their own axes of rotation, the axes of rotation of said port and said starboard canard section being perpendicular to said longitudinal axis, said canard sections being pivotal around their axes of rotation, the cross-sections of said canard sections being shaped as airfoils in airflow direction, the canard section leading edge having a predetermined sweepback angle, said front means for pitch control having a predetermined aerodynamic area, said front means for pitch control being positioned in front of the gravity center of said canarded deltoid main wing aircraft, said port and starboard canard sections each having a leading and a trailing edge, said leading edge of said means for aerodynamic lift production extending from said tailing edge of said port and starboard canard sections; c. canard connecting means, said canard connecting means being symmetrical relative to said symmetry plane, said canard connecting means being joined to said central section on the front side thereof, the airframe of said canard connecting means being fully integrated with the airframe of said central section, said canard connecting means having an upper and a lower surface, as well as a left and a right lateral surface, said left lateral surface and said right lateral surface being shaped as flat plains, said canard sections being joined to said canard connecting means on both lateral sides thereof, said canard sections being pivotally fastened to said canard connecting means, said left and said right lateral surface being perpendicular to said axes of rotation of said port and said starboard canard section respectfully, thus providing for an unobstructed rotation of said canard sections around said axes of rotation, said upper and said lower surface of said canard connecting means in front of said left and said right lateral surface forming a leading edge and a leading tip of said canard connecting means, the canard connecting means leading tip being the nose of said canarded deltoid main wing aircraft, the canard connecting means leading edge and said canard section leading edge constituting a front leading edge of said canarded deltoid main wing aircraft in cruising speed conditions, said canard connecting means having a predetermined wetted area, whereby said predetermined sweepback angle of said central section leading edge, said airfoils and said predetermined airlifting area of said means for aerodynamic lift production, said predetermined sweepback angle of said canard section leading edge, said airfoils, and said predetermined aerodynamic area of said front means for pitch control, said predetermined wetted area, as well as the shapes of said leading edge and said leading tip of said canard connecting means altogether providing for a substantially higher payload capacity and lower fuel consumption per unit of payload of said canarded deltoid main wing aircraft at supersonic speeds when compared to canardless supersonic aircraft with deltoid wings and fuselage, while simultaneously said airfoils, said predetermined aerodynamic area, and the longitudinal position of said front means for pitch control providing for a substantially higher ride quality and flight safety of said canarded deltoid main wing aircraft during landing when compared with said canardless supersonic aircraft. 2. The canarded deltoid main wing aircraft as claimed in claim 1, wherein said port and said starboard canard section consisting of a front and a rear portion, the front portions of said port and said starboard canard section being firmly fixed to said canard connecting means, thus substantially increasing the rigidity of the joint between said canard sections and said canard connecting means, the rear portions of said canard sections being pivotally connected to said front portions to allow for the change of the camber and attack angle of said canard sections in flight conditions, hence providing for the efficient pitch control of said canarded deltoid main wing aircraft, whereby the increased rigidity of said joint allowing for a substantial higher safety at high supersonic speeds of said canarded deltoid main wing aircraft with the fixed front portions of said canard sections relative to said canarded deltoid main aircraft with pivotal said canard sections.
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