Self-adjusting air intake
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IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0582572
(2000-06-27)
|
우선권정보 |
RU-0121837 (1997-12-29) |
국제출원번호 |
PCT/RU98/00443
(1998-12-29)
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§371/§102 date |
20000627
(20000627)
|
국제공개번호 |
WO99/33701
(1999-07-08)
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발명자
/ 주소 |
- Vladimir Timofeevich Medvedev RU
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
5 인용 특허 :
3 |
초록
▼
The present invention increases the recovery ratio of air intake (AI) as the supersonic flight speed increases, by preventing the penetration of a non-decelerated flow into the channel. In a subsonic regime, all the tiltable panels (5, 8, 20 and 11, 12, 21) are located in a uniform flow and operate
The present invention increases the recovery ratio of air intake (AI) as the supersonic flight speed increases, by preventing the penetration of a non-decelerated flow into the channel. In a subsonic regime, all the tiltable panels (5, 8, 20 and 11, 12, 21) are located in a uniform flow and operate as vanes. The partitions serve as a guiding apparatus. In a supersonic regime, the pressure at the outer side of panels 5, 8, 20, which are adjacent to the profile of an expanding channel, is decreased. This decrease in pressure contributes to the panel rotation as the pressure increases in the boundary layer (b.l.) when the AI is throttled, wherein this pressure can be transmitted via a special channel 22. When the panels 11, 12, 21 are at the boundary of zones with different pressures, they are turned thereby forming an aerodynamically efficient shape of a subsonic channel. Slots 15, 16 are used for the boundary-layer bleeding, for transmitting pressure to panels 5, 8, and for the additional feeding of slots 17, 18 for blowing air into the boundary layer. In case of a weak throttling and when the terminal shock is in a distant zone, all the panels are located in an almost uniform supersonic flow in the vane position. When the throttling causes the expulsion of the normal shock beyond the entry plane, all the tiltable panels are in a subsonic flow and also take up the positions of vanes, thereby preparing the throat to the start of AI during the reduction thereof.
대표청구항
▼
1. A supersonic air intake comprising a supersonic zone, a throat, and a subsonic zone, characterized by the fact that in order to self-adjust the geometry of these zones to the current speed of incoming flow and counterpressure value, the air intake comprises at least one additional channel connect
1. A supersonic air intake comprising a supersonic zone, a throat, and a subsonic zone, characterized by the fact that in order to self-adjust the geometry of these zones to the current speed of incoming flow and counterpressure value, the air intake comprises at least one additional channel connecting the supersonic zone to the subsonic zone, and having at its entry located in the supersonic zone a tiltable panel rotated by aerodynamic forces with an upstream rotation axis which is installed at the side which is far from the intake cross section center.
이 특허에 인용된 특허 (3)
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Peinemann Manfred K. A. (Westlake Village CA), Breathing system for hypersonic aircraft.
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Dunn Baxton M. (Kent WA), Device to start an overcontracted mixed compression supersonic inlet.
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Syberg Jan (Kent WA), Supersonic inlet having variable area sideplate openings.
이 특허를 인용한 특허 (5)
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Schnoor, Martin, Air intake for an auxiliary power unit in an aircraft.
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Kelnhofer,Juergen, Aircraft ram air inlet with multi-member closure flap.
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Cheung, Lawrence Chih-hui; Pastouchenko, Nikolai N.; Ramakrishnan, Kishore, Deployable assembly for a propulsor.
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Bouldin, Bruce Dan; Kowal, Adam; Doras, Vincent; Robbins, Robert; Lyells, Jim, Ram door assemblies.
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Chase, James D.; Garzon, German Andres, Supersonic aircraft jet engine.
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