High aerodynamic lift asymmetric fuselage

The invention relates to the field of aviation and is intended for fuselages, aircraft (hereinafter referred to as "fuselage") of multi-purpose airplanes of sub-sound and supersonic speed.

The known fuselage, at its longitudinal axis level, has a combination of respective planes and guides which form a lifting device This device produces a high lifting force depending on the angle of attack of the fuselage (see U.S. Patent No. 5,366,180, 1993).

A disadvantage of the invention is that the apparatus of a similar scheme, by requiring additional control devices for the lifting force of the fuselage, increases resistance to the complexity and weight of the structure.

The object of the present invention is to optimize the longitudinal and cross-sectional contours of the fuselage, to create a high lifting force Lf at the pressures of planar currents on its upper and lower bearing surface, and to improve the L / D and aerodynamic characteristics of the aircraft. In addition to the main function of the fuselage mentioned above, which is to carry passengers, cargo, the creation of a high lifting force is an additional feature whose interaction is ensured by optimized fuselage forms.

For this purpose, a high load-bearing asymmetric fuselage configuration with nose, torso and tail portions forming aerodynamic surfaces with the upper surface higher than the lower surface and optimized longitudinal and cross-sectional contour geometry for different jet pressures has been developed. Pressures on high-load-bearing asymmetric fuselage bearing surfaces create high-lift L in all flight modes_f. The aforementioned fuselage, which has a cross-sectional width (not shown in the drawing) greater than height, and its h has some limitations, various profiles and S_p, depending on its purpose and speed characteristics. The present invention is useful for the manufacture of said fuselage with three-dimensional shapes which reduce some of the resistance components, improve the landing-landing characteristics of most fuselages without increasing their Sm and structural weight.

The author is not aware of the solutions with the features of the proposed solution, so I believe that he has significant new features.

The proposed technical solution is illustrated in the drawing.

In the illustrated fuselage plan (Fig. 1), the high-lift asymmetric fuselage consists of a nose portion 2 which extends smoothly to the torso portion 9 and the torso smoothly extends to the tail portion 8. The stroke 15 illustrates a possible tail shape with possible height, pivoting rudders, when the keel is abandoned and so on.

High lift asymmetric fuselage with profile (Fig. 2) consisting of upper (5) and lower surface (11) divided by centerline 10. The upper surface is higher than the lower surface and the height of the fuselage has limitations and cross-section (not shown). width greater than height. A portion 3 of the upper bearing plane of the torso 9 is parallel to the longitudinal axis, and the other portion 4 of said surface bearing plane has an angle relative to the longitudinal axis dependent on the positive angle of the nose 6 and the lower bearing plane of the torso 7. angle V relative to the fuselage destination and speed characteristics.

The proposed high lift asymmetric fuselage operates in the following manner. As the aircraft (with the aforementioned fuselage) flies in various flight and speed modes, the pressures of currents on the upper surface of the fuselage carrying planes 1, 3, 4, 12 and the lower surface carrying planes 6, 7,13 create L_f = P2> P-sound L asymmetric high lift asymmetric fuselage_f by airplane formula: L = Lf + L_w, or L = L_w+ L_f. (only given in L_w and L_f). These airplane formulas depend on the geometrical characteristics of the fuselages, the numbers M and Re, and so on. Supersonic High Load Asymmetric Fuselage L_f only available in the second airplane formula provided. Subwoofer and supersonic fuselage L_f and configurations are very different.

Experimental calculations have shown that the above-mentioned subwoofer transport or passenger fuselage has a high capacity and has corresponding height restrictions. The submarine airplane with the aforementioned fuselage has high take-off landing characteristics, does not require a large airport and, in the case of a forced take-off, has limited lane clearance.

DEFINITION OF INVENTION