(WO/2001/058752) MULTIFUNCTIONNAL FIGHTER (MFF)
- Biblio. Data
- Description
- Claims
- National Phase
- Notices
- Documents
| Latest bibliographic data on file with the International Bureau
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| IPC: | B64C 30/00 (2006.01), B64D 7/00 (2006.01) | ||||||||||||||||||
| Applicant: | MUKHAMEDOV, Fatidin Abdurakhmanovich [RU/RU]; (RU). | ||||||||||||||||||
| Inventor: | MUKHAMEDOV, Fatidin Abdurakhmanovich; (RU). | ||||||||||||||||||
| Agent: | SHTYLKOV, Vitaly Viktorovich; a/ya 55 Moscow, 127562 (RU). | ||||||||||||||||||
| Priority Data: |
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| Title: | MULTIFUNCTIONNAL FIGHTER (MFF) | ||||||||||||||||||
| Abstract: | The invention relates to aviation. The inventive multifunctionnal fighter comprises a wing (1) with a center wing (2) embodied in the form of a profiled carrying disc provided with a leading (3) and rear (4) edge arranged along a generating line thereof. Outer wings (5) are connected to the center wing (2). Each outer wing (5) is embodied in a rotatable manner and equipped with a droop nose (6) The carrying disc of the center wing (2) has aft segments (7). The aft segments (7) are embodied in a rotatable manner and can therefore operate differentially. A fuselage (8) is displaced along the aircraft axis of the bank ahead with respect to the carrying disc of the center wing (2). Aerodynamic seals (9) are mounted between the carrying disc of the center wing (2) and each outer wing (5) of the wing (1). Aerodynamic controlling surfaces embodied in the form of leading segments (14) and mounted on the carrying disc of the center wing (2) are provided with a leading edge (3) which is arranged along the disc generating circular curve. A pivot (16) of the droop nose (6) of each rotatable outer wing (5) and a pivot (15) of the adjacent leading segments (14) of the carrying disc of the center wing (2) are parallel to each other on the same plane. The point of application of the summarized positive or negative ascensional power of the aircraft ?$g(D)Y at the motion of the rotatable outer wings (5) is maximum approaching the point of aerodynamic center point of the aircraft, making it possible to fly the fighter without changing a longitudinal moment thereof in the ascensional power controlling system. | ||||||||||||||||||
| Designated States: |
AT, BR, CA, CN, DE, GB, IL, IN, JP, KR, SE, SG, UA, US. European Patent Office (EPO) (AT, BE, CH, CY, DE, DK, ES, FI, FR, GB, GR, IE, IT, LU, MC, NL, PT, SE, TR). | ||||||||||||||||||
| Publication Language: | Russian (RU) |
| Filing Language: | Russian (RU) |
