Supersonic aircraft with shockwave canceling aerodynamic configuration
View Patent ↗Disclosed is a supersonic aircraft design having a single structural component that simultaneously joins the wings to the aircraft fuselage, the engines to the aircraft fuselage, and the wings to the engines, resulting in an airframe planform, which, in combination aerodynamic shaping and structural morphing technologies within the aircraft fuselage, enables the aircraft to be optimized to reduce sonic boom.
1. An aircraft apparatus capable of reaching supersonic speeds comprising:
A) a fuselage comprising:
(i) a nose tip at a first end of the fuselage;
(ii) a first portion of the fuselage aft of the nose tip and characterized by a first curvature profile producing a first shock wave as the aircraft approaches supersonic speeds; and
(iii) a second portion of the fuselage aft of the first portion of the fuselage and characterized by a second curvature profile producing a second shock wave as the aircraft approaches supersonic speeds, the second shock wave having greater pressure than the first shock wave;
B) a pair of main wings attached to the fuselage;
C) a tail attached to the fuselage aft of the pair of main wings;
D) aircraft engines;
E) a tailplane aft of the aircraft engines having horizontal aerodynamic surface, fully located within the wake of the aircraft engines, and the tailplane is arranged to provide lift to the aircraft apparatus as well as reduce shock cone pressure.
2. The aircraft apparatus of claim 1 wherein the second shock wave at least partially attenuates the magnitude of the first shock wave.
3. The aircraft apparatus of claim 1 wherein the first and second portions of the fuselage are disposed on a bottom portion of the aircraft fuselage.
4. The aircraft apparatus of claim 1 wherein the curvature profile of the first portion of the fuselage is characterized by a concave surface.
5. The aircraft apparatus of claim 4 wherein the curvature profile of the second portion of the fuselage is characterized by a convex surface in sequence after the concave surface.
6. An aircraft apparatus having a center of gravity, wherein the aircraft apparatus is capable of reaching supersonic speeds comprising:
A) a main fuselage;
B) a pair of main wings attached to the main fuselage, the wings having a center of wing mass relative to the main fuselage, a mean aerodynamic chord and an overall wetted surface area;
wherein the center of wing mass, the mean aerodynamic chord and the overall wetted surface area of the pair of main wings are aft of the center of gravity of the aircraft apparatus;
C) aircraft engines;
D) a tailplane aft of the aircraft engines having horizontal aerodynamic surface, fully located within the wake of the aircraft engines, and the tailplane is arranged to provide lift to the aircraft apparatus as well as reduce shock cone pressure.
7. The aircraft apparatus of claim 6 further comprising:
E) a V-shaped tail section aft of the pair of main wings between the pair of main wings and the tailplane.
8. The aircraft apparatus of claim 7 wherein the main wings have a center line relative to the main fuselage and wherein the V-shaped tail section is set three wing chord root thicknesses above the center line of the main wings.
9. The aircraft apparatus of claim 6 wherein the main wings have continuously curved leading edges.
10. An aircraft apparatus capable of reaching supersonic speeds comprising:
A) a fuselage comprising:
(i) a nose tip at a first end of the fuselage and producing a first shock wave as the aircraft approaches supersonic speeds; and
(ii) a first portion of the fuselage aft of the nose tip and producing a second shock wave as the aircraft approaches supersonic speeds,
wherein second shock wave at least partially attenuates the pressure magnitude of the first shock wave;
B) aircraft engines;
C) a tailplane aft of the aircraft engines having horizontal aerodynamic surface, fully located within the wake of the aircraft engines, and the tailplane is arranged to provide lift to the aircraft apparatus as well as reduce shock cone pressure.