EA201101206A1 - FUSELY AND METHOD OF REDUCTION OF RESISTANCE - Google Patents
FUSELY AND METHOD OF REDUCTION OF RESISTANCEInfo
- Publication number
- EA201101206A1 EA201101206A1 EA201101206A EA201101206A EA201101206A1 EA 201101206 A1 EA201101206 A1 EA 201101206A1 EA 201101206 A EA201101206 A EA 201101206A EA 201101206 A EA201101206 A EA 201101206A EA 201101206 A1 EA201101206 A1 EA 201101206A1
- Authority
- EA
- Eurasian Patent Office
- Prior art keywords
- fuselage
- airfoil
- possibly
- resistance
- ekranolet
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Toys (AREA)
- Body Structure For Vehicles (AREA)
Abstract
Изобретение относится к авиационной технике и применимо для улучшения аэродинамического качества вертолетов, самолетов, в том числе крупных аэробусов классической схемы и амфибий, экранолетов и судов на воздушной подушке, возможно путем проведения их модернизации. Технической задачей является уменьшение сопротивления полету, возможно, в результате модернизации вертолета, самолета, экранолета, судна на воздушной подушке. Технический результат достигается уменьшением площади контакта внешней поверхности хвостовой часта фюзеляжа со скоростным воздушным потоком, для чего упомянутую площадь контакта уменьшают путем увеличения площади отверстий в хвостовой части фюзеляжа. Для увеличения подъемной силы без увеличения сопротивления давления у аэродинамического канала дно выполняют выпуклым вверх, например выгнутым вверх, по форме выпуклой стороны аэродинамического профиля. Верхнее отверстие в обшивке фюзеляжа для аэродинамического канала может быть размещено в пространстве вдоль средней части киля, выполнено разделенным вдоль килем направо и налево, например пополам. Аэродинамический канал выполнен сквозным и может быть открытым. Отверстие, совмещенное с передней верхней кромкой аэродинамического канала, выполнено большей площади, чем заднее отверстие, совмещенное с концом фюзеляжа, возможно в виде и путем среза конца фюзеляжа.The invention relates to aeronautical engineering and is applicable to improve the aerodynamic quality of helicopters, airplanes, including large airbuses of the classical scheme and amphibians, ekranolet and hovercraft, possibly by modernizing them. The technical challenge is to reduce the resistance to flight, possibly as a result of the modernization of a helicopter, an airplane, an ekranolet, a hovercraft. The technical result is achieved by reducing the contact area of the outer surface of the tail section of the fuselage with high-speed air flow, for which the said contact area is reduced by increasing the area of the holes in the tail section of the fuselage. To increase the lifting force without increasing the pressure resistance at the airfoil, the bottom is made convex upward, for example, curved upward, in the shape of the convex side of the airfoil. The upper opening in the skin of the fuselage for the airfoil can be placed in space along the middle part of the keel, divided along the keel to the right and to the left, for example, in half. The aerodynamic channel is made through and can be open. The hole aligned with the front upper edge of the airfoil is made with a larger area than the rear hole aligned with the end of the fuselage, possibly in the form and by cutting off the end of the fuselage.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2010114786/11A RU2010114786A (en) | 2010-04-14 | 2010-04-14 | FUSELAGE AND METHOD OF MODERNIZING CRASH |
| PCT/RU2011/000227 WO2011129721A1 (en) | 2010-04-14 | 2011-04-06 | Fuselage and method for reducing resistance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| EA201101206A1 true EA201101206A1 (en) | 2012-07-30 |
Family
ID=44798874
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EA201101206A EA201101206A1 (en) | 2010-04-14 | 2011-04-06 | FUSELY AND METHOD OF REDUCTION OF RESISTANCE |
Country Status (3)
| Country | Link |
|---|---|
| EA (1) | EA201101206A1 (en) |
| RU (1) | RU2010114786A (en) |
| WO (1) | WO2011129721A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10370110B2 (en) | 2016-09-21 | 2019-08-06 | General Electric Company | Aircraft having an aft engine |
| US10399670B2 (en) | 2016-09-26 | 2019-09-03 | General Electric Company | Aircraft having an aft engine and internal flow passages |
| US10364021B2 (en) | 2016-09-26 | 2019-07-30 | General Electric Company | Aircraft having an aft engine and stabilizer root fillet |
| US10486796B2 (en) | 2016-09-26 | 2019-11-26 | General Electric Company | Aircraft having an AFT engine and stabilizer with a varying line of maximum thickness |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1168084A (en) * | 1956-12-10 | 1958-12-04 | Carrier-fuselage aircraft with integrated propulsion | |
| US4726546A (en) * | 1986-11-17 | 1988-02-23 | Angelis Lawrence J De | Semi-venturi airfoil aircraft |
| RU2092386C1 (en) * | 1995-12-26 | 1997-10-10 | Акционерное общество открытого типа "Авиационный комплекс им.С.В.Ильюшина" | Flying vehicle cargo cabin for transportation of cargo in containers |
| RU2274584C2 (en) * | 2002-01-31 | 2006-04-20 | Геннадий Трофимович Крещишин | Tail section of aeroplane and method for reducing the air flow swirlings |
| RU2384461C2 (en) * | 2005-12-07 | 2010-03-20 | Геннадий Трофимович Крещишин | Aircraft and kreshchishin method for decreasing aircraft resistance to flight |
| RU2007134266A (en) * | 2007-09-14 | 2009-03-20 | Геннадий Трофимович Крещишин (RU) | TAIL OF THE AIRCRAFT CHRISTIAN AND METHOD OF MODERNIZATION WITH REDUCTION OF THE FULL RESISTANCE OF THE AIRCRAFT CRASHIN |
-
2010
- 2010-04-14 RU RU2010114786/11A patent/RU2010114786A/en not_active Application Discontinuation
-
2011
- 2011-04-06 EA EA201101206A patent/EA201101206A1/en unknown
- 2011-04-06 WO PCT/RU2011/000227 patent/WO2011129721A1/en active Application Filing
Also Published As
| Publication number | Publication date |
|---|---|
| RU2010114786A (en) | 2011-10-20 |
| WO2011129721A1 (en) | 2011-10-20 |
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