초록 ▼

“T-tailed Deltoid Main Wing” idea allows for design of high-subsonic passenger aircraft with a capacity between 200 and 650 passengers with outer dimensions fitting within 80 m box on class VI airports while having more than twice lower fuel consumption per unit of payload when compare

“T-tailed Deltoid Main Wing” idea allows for design of high-subsonic passenger aircraft with a capacity between 200 and 650 passengers with outer dimensions fitting within 80 m box on class VI airports while having more than twice lower fuel consumption per unit of payload when compared to the present classical-concept aircraft with fuselage that have the same passenger capacity. T-tailed deltoid main wing aircraft is satisfying all safety requirements for a passenger aircraft while having over 50% longer range than the aircraft of equivalent capacity with fuselage. Simple aerodynamic and structural solutions of T-tailed deltoid main wing aircraft are resulting with low development risks and production cost. Simple and reliable flight control systems of aircraft that are based on T-tailed deltoid main wing aerodynamic configuration allow for design of all-purpose, high-lift-capacity, and long range unmanned aircraft.

대표청구항 ▼

We claim: 1. A T-tailed deltoid main wing aircraft having a vertical symmetry plane oriented in airflow direction, said T-tailed deltoid main wing aircraft comprising: a. means for aerodynamic lift production, said means for aerodynamic lift production being symmetrical relative to said symmetry pl

We claim: 1. A T-tailed deltoid main wing aircraft having a vertical symmetry plane oriented in airflow direction, said T-tailed deltoid main wing aircraft comprising: a. means for aerodynamic lift production, said means for aerodynamic lift production being symmetrical relative to said symmetry plane, said means for aerodynamic lift production including a main wing, two symmetrical outer wings, and two symmetrical wing transition sections, said main wing being the central section of said means for aerodynamic lift production, the main wing trailing edge being defined by two straight lines, said two straight lines being symmetrical relative to said symmetry plane, the intersection of said two straight lines being a trailing tip of said main wing, said main wing trailing edge being substantially forward swept, thus said trailing tip being substantially shifted in aft direction behind the mean geometric chord of said means for aerodynamic lift production, said means for aerodynamic lift production being defined by efficient aft camber airfoils across the span thereof, b. a plurality of jet engines with jet engine support means and jet engine aerodynamic covers, each jet engine aerodynamic cover including a jet engine air intake, said jet engine support means being joined to said means for aerodynamic lift production, the top of said jet engine support means being above said means for aerodynamic lift production, said jet engines with said jet engine aerodynamic covers being joined to said jet engine support means on the top thereof, thus said jet engine air intake being subjected to free unobstructed airflow over the turbulent boundary layer of said means for aerodynamic lift production, said jet engine support means together with said jet engine aerodynamic covers being shaped as integral vertical aerodynamic surfaces, said integral vertical aerodynamic surfaces are positioned laterally from the rear portion of said main wing on both sides thereof, thus being the means for reduction of vortex activity around said rear portion, c. means for aerodynamic stabilization, said means for aerodynamic stabilization being symmetrical relative to said symmetry plane, said means for aerodynamic stabilization including a fin and a tailplane, said fin being joined directly to the upper side of said rear portion of said main wing, said fin being substantially extended in aft direction relative to said trailing tip, said fin having a sweepback angle, said tailplane being joined to said fin, said tailplane having an outermost aft position relative to said fin, the airframe of the root section of said fin forward of said trailing tip being integrated with the airframe of said rear portion as the upper reinforcement thereof, thus substantially increasing the bending resistance of said rear portion, hence said rear portion and said upper reinforcement with the unchanged weight thereof allowing for an additional substantial shift of said root section of said fin in aft direction relative to said trailing tip, as well as a substantially higher sweepback angle of said fin, whereby the substantially shifted said trailing tip in aft direction relative to said mean geometric chord of said means for aerodynamic lift production, said additional substantial shift of said root section relative to said trailing tip, said substantially higher sweepback angle of said fin, and said outermost aft position of said tailplane altogether providing for a substantial shift of the neutral point of said T-tailed deltoid main wing aircraft in aft direction along said mean geometric chord, said substantial shift of said neutral point allowing for a substantial shift of the gravity center with a positive static margin of said T-tailed deltoid main wing aircraft in aft direction along said mean geometric chord, said positive static margin satisfying the level of natural longitudinal dynamic stability of said T-tailed deltoid main wing aircraft that is required for commercial aircraft, said substantial shift of said gravity center in aft direction along said mean geometric chord of said means for aerodynamic lift production that are defined by said efficient aft camber airfoils providing for the longitudinal static stability of said T-tailed deltoid main wing aircraft in the cruising configuration thereof, said efficient aft camber airfoils across the span of said means for aerodynamic lift production providing for a substantially higher aerodynamic efficiency and lower fuel consumption per unit of payload of said T-tailed deltoid main wing aircraft at high subsonic and transonic speed when compared to prior art tailess and tailed flying wing aircraft.