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특허 상세정보
Reactive orthotropic lattice diffuser for noise reduction
| 국가/구분 | United States(US) Patent 등록 |
|---|---|
| 국제특허분류(IPC7판) | B64C-003/50 B64C-001/40 |
| 출원번호 | US-0764062 (2013-02-11) |
| 등록번호 | US-9227719 (2016-01-05) |
| 발명자 / 주소 | |
| 출원인 / 주소 | |
| 대리인 / 주소 |
|
| 인용정보 | 피인용 횟수 : 1 인용 특허 : 26 |
초록
An orthotropic lattice structure interconnects porous surfaces of the flap with internal lattice-structured perforations to equalize the steady pressure field on the flap surfaces adjacent to the end and to reduce the amplitude of the fluctuations in the flow field near the flap end. The global communication that exists within all of the perforations provides the mechanism to lessen the pressure gradients experienced by the end portion of the flap. In addition to having diffusive effects (diffusing the incoming flow), the three-dimensional orthogonal lat...
대표
청구항
1. A flap of the type that is movably connected to an aircraft wing to provide control of an aircraft in flight, the flap comprising: an elongated flap structure defining inboard and outboard ends and forward and rearward portions extending between the inboard and outboard ends, the elongated flap structure defining an upper side extending between the inboard and outboard ends and between the forward and rearward portions, and a lower side, wherein the upper side generally faces upwardly in use, and the lower side generally faces downwardly in use, and w...
이 특허에 인용된 특허 (26)
- Harper, Cedric B.. Acoustic liners. USP2011067967108.
- Shmilovich, Arvin; Yadlin, Yoram; Clark, Roger W.. Active systems and methods for controlling an airfoil vortex. USP2011098016244.
- Mau, Knut; Grünewald, Michael; Reichenberger, Johann; Borchers, Ingo; Drobietz, Roger. Aerodynamic flap of an aircraft having a device which influences the flap vortex. USP2012018096513.
- Hogeboom William H. ; Bielak Gerald W.. Aircraft engine acoustic liner. USP1998075782082.
- Jeffrey W. Moe. Aircraft wing and method for reducing airframe-generated noise. USP2002096454219.
- Shmilovich,Arvin; Yadlin,Yoram; Clark,Roger; Leopold,Donald. Apparatus and method for the control of trailing wake flows. USP2006097100875.
- Craig L. Streett ; John C. Lin. Device and method for reducing aircraft noise. USP2002106471157.
- Chow,Leung Choi; Rondeau,David Leonard; Wood,Christopher Neil. Landing gear door assembly. USP2008127458542.
- Moe, Jeffrey W.; Whitmire, Julia; Kwan, Hwa-Wan; Abeysinghe, Amal. Landing gear noise attenuation. USP2011067954757.
- Shmilovich, Arvin; Yadlin, Yoram; Clark, Roger W.. Lift augmentation system and associated method. USP2011108033510.
- Hieu T. Ngo ; Lisa E. Barlow. Lifting surface with active variable tip member and method for influencing lifting surface behavior therewith. USP2002056394397.
- Harper, Cedric B; Creagh, Michael; Humphries, Neil; Martindale, Ian G. Liner for a gas turbine engine casing. USP2011017866939.
- Wilson Robert S. (Belfast GB5). Noise attenuation panel. USP1996085543198.
- Harris Alfred W. (Bellevue WA). Noise reducing air inlet for gas turbine engines. USP1980124240250.
- Ingo Borchers DE; Roger Drobietz DE; Michael Gruenewald DE; Knut Mau DE; Johann Reichenberger DE. Noise reducing vortex generators on aircraft wing control surfaces. USP2002126491260.
- Hutcheson,Florence V.; Brooks,Thomas F.. Noise reduction of aircraft flap. USP2009027484930.
- Lin, Juhn-Shyue; Hoffman, Herbert L.; Chewning, Gary R.; Kosanchick, III, Melvin; Poling, Hugh. Particle-filled wing-to-body fairing and method for reducing fairing vibrations. USP2011118056850.
- Takanori Tsukahara JP; Masahiro Obukata JP. Rotary blade of helicopter. USP2002106467732.
- Leishman, John G.; Han, Yong Oun. Rotor blade system with reduced blade-vortex interaction noise. USP2005096948906.
- Glenn E. Warnaka. Sound absorbing structure. USP2002086435303.
- Warnaka Glenn E. (Erie PA). Sound absorbing structure. USP1979024141433.
- Pal, Anadish Kumar. Surface flow diverting and static charging ducted pores on wing or blade tip to reduce wake and BVI noise. USP2009127637462.
- Bussom,Richard; McVeigh,Michael A.; Narducci,Robert P.; Zientek,Thomas A.. System and method for improved rotor tip performance. USP2007097264200.
- Pitt, Dale M.. System and method for varying the porosity of an aerodynamic surface. USP2012088251317.
- Wagenfeld Robert E. (New York NY). System for reducing aircraft noise and hush kit. USP1989064836469.
- Shmilovich, Arvin; Yadlin, Yoram; Clark, Roger W.; Leopold, Donald H.. Systems and methods for destabilizing an airfoil vortex. USP2010027661629.
