RU2008102211A - HELICOPTER - Google Patents
HELICOPTER Download PDFInfo
- Publication number
- RU2008102211A RU2008102211A RU2008102211/11A RU2008102211A RU2008102211A RU 2008102211 A RU2008102211 A RU 2008102211A RU 2008102211/11 A RU2008102211/11 A RU 2008102211/11A RU 2008102211 A RU2008102211 A RU 2008102211A RU 2008102211 A RU2008102211 A RU 2008102211A
- Authority
- RU
- Russia
- Prior art keywords
- helicopter
- wing
- engines
- equipment
- profile
- Prior art date
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Abstract
1. Вертолет, содержащий шасси, крыло, двигатели, два несущих винта, расположенные согласно поперечной схеме, и систему управления вертолетом, отличающийся тем, что вертолет дополнительно содержит средство синхронизации несущих винтов, двигатели с несущими винтами установлены на противоположных концах крыла, между двигателями установлено средство синхронизации несущих винтов, на нижней поверхности крыла расположены элементы подвески вооружения, оси несущих винтов в продольной плоскости наклонены во внешнюю от плоскости симметрии вертолета сторону на угол β=3…6°, а их проекции на плоскость симметрии вертолета перпендикулярны к поверхности земли, при этом крыло выполнено подкрепленным с помощью силового набора, с большой строительной высотой и с полостью для размещения аппаратуры вертолета, а проекция перпендикуляра к строительной горизонтали крыла на плоскость симметрии вертолета образует угол γ=4…10° к вертикали; где с - высота профиля крыла; b - хорда профиля крыла, строительная горизонталь крыла - прямая, относительно которой построен профиль крыла, проходящая через хорду профиля крыла b. ! 2. Вертолет по п.1, отличающийся тем, что в полости для размещения аппаратуры вертолета расположены система управления вертолетом, двигатели, топливная система, включающая в себя топливные баки, элементы трансмиссии, электрооборудование.1. A helicopter comprising a landing gear, a wing, engines, two rotors located according to the transverse diagram, and a helicopter control system, characterized in that the helicopter further comprises rotor synchronization means, engines with rotors are installed at opposite ends of the wing, between engines rotor synchronization means, armament suspension elements are located on the lower surface of the wing, the rotor axes in the longitudinal plane are inclined to the vert summer, the angle β = 3 ... 6 °, and their projections on the plane of symmetry of the helicopter are perpendicular to the surface of the earth, while the wing is reinforced with a power set, with a large building height and with a cavity for placing the helicopter equipment, and the projection of the perpendicular to the building the wing horizontal to the plane of symmetry of the helicopter forms an angle γ = 4 ... 10 ° to the vertical; where c is the height of the wing profile; b is the chord of the wing profile, the construction horizontal of the wing is a straight line relative to which the wing profile is built, passing through the chord of the wing profile b. ! 2. The helicopter according to claim 1, characterized in that in the cavity for accommodating the equipment of the helicopter there are a helicopter control system, engines, a fuel system including fuel tanks, transmission elements, electrical equipment.
Claims (2)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2008102211/11A RU2373113C2 (en) | 2008-01-25 | 2008-01-25 | Helicopter |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2008102211/11A RU2373113C2 (en) | 2008-01-25 | 2008-01-25 | Helicopter |
Publications (2)
Publication Number | Publication Date |
---|---|
RU2008102211A true RU2008102211A (en) | 2009-07-27 |
RU2373113C2 RU2373113C2 (en) | 2009-11-20 |
Family
ID=41048013
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2008102211/11A RU2373113C2 (en) | 2008-01-25 | 2008-01-25 | Helicopter |
Country Status (1)
Country | Link |
---|---|
RU (1) | RU2373113C2 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110203383B (en) * | 2019-06-24 | 2024-04-16 | 南京航空航天大学 | Modularized cross type column unmanned helicopter and working method thereof |
-
2008
- 2008-01-25 RU RU2008102211/11A patent/RU2373113C2/en not_active IP Right Cessation
Also Published As
Publication number | Publication date |
---|---|
RU2373113C2 (en) | 2009-11-20 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20100126 |