Positive-pressure flying aircraft
A positive-pressure floating type airplane comprising an airfoil portion, left-right fuselages, a central fuselage, an elevator and a rudder disposed at the back of the airfoil portion, a thruster disposed at the back of the central fuselage, and a horizontal stabilizer disposed at the rear ends of the left-right fuselages. The individual front ends of the airfoil portion, the left-right fuselages and the central fuselage are formed into arcuate shapes in longitudinal sections. On the lower side of the airfoil portion, a recessed air capture is formed from the front end to the rear end. As a result, the positive-pressure floating type airplane is floated by the reaction from the air at the time when the air to pass the air capture through the airfoil portion is pushed by the thrust of the thruster, and is propelled forward by the component of that thrust.
1. A positive-pressure flying aircraft comprising:
a main body having a front end;
a right body disposed at one side of the main body and having a front end;
a left body disposed at the other side of the main body and having a front end, the front ends of the right and left bodies being behind the front end of the main body;
a wing supported by the main body, the right body and the left body and having a front end that is behind the front ends of the right and left bodies, an air path being defined longitudinally of the aircraft by a bottom surface of the wing and inner side surfaces of the right and left bodies;
a horizontal stabilizer;
a thrusting device in a gap;
a vertical fin in the middle of the horizontal stabilizer;
a rudder at the rear end of the vertical fin; and
an elevator at the rear end of the horizontal stabilizer,
wherein the wing has an upper surface which is flat and a lower surface with a positive camber, and the horizontal stabilizer has an upper surface with a positive camber and a lower surface which is flat, the wing gradually getting thinner rearward from a maximum thickness portion, the gap being formed between the wing and the horizontal stabilizer.
2. The aircraft of claim 1 , wherein the maximum thickness portion of the wing has a thickness ranging from 3/10 to 4/10 of a chord length of the wing, the maximum thickness portion being formed at a position of 2/10 to 3/10 of the chord length from a leading edge of the wing.
3. The aircraft of claim 1 , wherein the wing has a concave portion at the front end.
4. The aircraft of claim 1 , wherein each of the right body and the left body has a downward projection at the same position as that of the positive camber on the lower surface of the wing.
5. The aircraft of claim 1 , wherein the front end of the main body is formed as a hemisphere.
6. The aircraft of claim 1 , wherein the elevator is hinged to the rear end of the horizontal stabilizer, the elevator having an upper surface which is flat and a lower surface with a positive camber.
7. The aircraft of claim 1 , wherein the thrusting device comprises a propeller.
8. A positive-pressure flying aircraft comprising:
a main body having a front end;
a right body disposed at one side of the main body and having a front end;
a left body disposed at the other side of the main body and having a front end, the front ends of the right and left bodies being behind the front end of the main body;
a wing supported by the main body, the right body and the left body and having a front end that is behind the front ends of the right and left bodies, an air path being defined longitudinally of the aircraft by a bottom surface of the wing and inner side surfaces of the right and left bodies;
a horizontal stabilizer;
a thrusting device in a gap;
a vertical fin in the middle of the horizontal stabilizer;
a rudder at the rear end of the vertical fin; and
an elevator at the rear end of the horizontal stabilizer,
wherein one of the upper surface and the lower surface of the wing is flat, the other one of the upper surface and the lower surface of the wing has a positive camber, one of the upper surface and the lower surface of the horizontal stabilizer is flat, and the other one of the upper surface and the lower surface of the horizontal stabilizer has a positive camber, one of the upper surface of the wing and the upper surface of the horizontal stabilizer being flat, the other one of the upper surface of the wing and the upper surface of the horizontal stabilizer having a positive camber, the gap being formed between the wing and the horizontal stabilizer, and
wherein the front end of each of the right body and the left body is formed as a hemisphere.