| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | Helicopter having high advanced speed | JP26440186 | 1986-11-06 | JPS62168793A | 1987-07-25 | HERUBERUTO TSUIMAA |
| 2 | Circulation control rotor | JP16862690 | 1990-06-28 | JPH0345497A | 1991-02-27 | AAMANDO EFU AMERIO; UIRIAMU SHII FUITSUSHIYAA JIYU |
| PURPOSE: To improve control responsiveness by making an opening area of an edge groove variable by a cam device in an apparatus which releases compressed air from an edge groove of each rotor blade in a circulation control rotor device used for an aircraft with X blades. CONSTITUTION: An aircraft with X blades is equipped with a rotor device 12 including four blades 14 and hub parts 16 on the top of an airframe. Each blade 14 is a circulation control airfoil, and has a panel 66 mounted by screws 68 along an edge on the inboard side, and edge on the outboard side is bent due to rotation of a cam 64 and forms each edge groove for reading and trailing with variable opening area between it and a Coanda surface 70. Compressed air from a compressed air supply device which is supplied from the opening, groove through a rotation annular chamber device 26, and supply duct 30 is released. Rotation of the cam 64 is controlled by an actuator according to flight condition of the aircraft. COPYRIGHT: (C)1991,JPO | ||||||
| 3 | Rotor blade for circulation control aircraft | JP16844785 | 1985-07-30 | JPS61102396A | 1986-05-21 | DONARUDO AARU KAATAA; TEIMOSHII EI KURAUSU; MASHIYUU SEDORAKU |
| 4 | Rotor-revolution controller for rotor aircraft | JP26440086 | 1986-11-06 | JPS62155199A | 1987-07-10 | HERUBERUTO TSUIMAA |
| 5 | Main rotor blade for helicopter and method of improving performance of advance flight thereof | JP29978386 | 1986-12-16 | JPS62143798A | 1987-06-27 | EBUAN EI FURADENBAAGU |
| 6 | Fluggerät, insbesondere Drehflügelfluggerät in der Art eines Flugschraubers für höhere Fluggeschwindigkeiten | EP86114933.4 | 1986-10-27 | EP0229896B1 | 1990-09-19 | Zimmer, Herbert, Dr.-Ing. |
| 7 | Aircraft, in particular a high-speed helicopter | EP86114933 | 1986-10-27 | EP0229896A3 | 1988-07-20 | ZIMMER, HERBERT, DR.-ING. |
| 8 | Circulation-controlled rotor system for aircraft | EP86114934 | 1986-10-27 | EP0223117A3 | 1988-10-12 | ZIMMER, HERBERT, DR.-ING. |
| 9 | Fluggerät, insbesondere Drehflügelfluggerät in der Art eines Flugschraubers für höhere Fluggeschwindigkeiten | EP86114933.4 | 1986-10-27 | EP0229896A2 | 1987-07-29 | Zimmer, Herbert, Dr.-Ing. |
Fluggerät, insbesondere Drehflügelfluggerät in der Art eines Flugschraubers für höhere Fluggeschwindigkeiten, mit einem über Schwenkachsen vertikalschuberzeugenden Hauptrotor und einen vom Hauptrotor getrennt wirkenden, vorwärtsschuberzeugenden Propellerantrieb, sowie einer der Luftschraube des Propellerantriebes nachgeordneten Giersteuerung bzw. Giermomenten-Ausgleichssteuerung, wobei die Luftschraube (6) freifahrend angeordnet und der als Druckschraube arbeitenden Luftschraube (6) zu beiden Seiten der senkrechten Fluggeräte-Längsmittelebene im Propellernachlaufstrom je ein Strahlruder bzw. Seitenruder (27 bzw. 27') zugeordnet und ferner die Strahlruder (27 bzw. 27') von einem fluggerätefesten Trägergestell (20) über Schwenkachsen (29 bzw. 29') schwenkbar getragen sind, und wobei außerdem das Gestell für die Seitenruder (27 bzw. 27') zumindest teilweise durch Elemente (22, 22'; 24, 24') des Leitwerks gebildet ist. |
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| 10 | Adaptive rotor blade | EP12198610.3 | 2012-12-20 | EP2631175A3 | 2017-12-27 | Scott, Mark W. |
MISSION ADAPTIVE ROTOR BLADE ABSTRACT OF THE DISCLOSURE A rotor assembly (12) for a rotary wing aircraft (10) includes a plurality of rotor blades (20) operably connected to a rotor shaft (22). Two or more active adaptive devices, such as flaps (28), air outlets (36) or jet tip outlets (48), are located at one or more rotor blades (20) of the plurality of rotor blades. The one or more active adaptive devices (28, 36, 48) are operably connected to an aircraft flight control system (34) such that, when activated, the one or more active adaptive devices (28, 36, 48) change one or more operational characteristics of the rotor assembly (12). A method of operating a rotor assembly (12) of a rotary wing aircraft (10) includes rotating a plurality of rotor blades (20) about a rotor shaft (22). Two or more active adaptive devices (28, 36, 48) located at one or more rotor blades (20) of the plurality of rotor blades are activated and change one or more operational characteristics of the rotor assembly (12).
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| 11 | Zirkulationsgesteuertes Rotorsystem für Luftfahrzeuge | EP86114934.2 | 1986-10-27 | EP0223117B1 | 1990-09-12 | Zimmer, Herbert, Dr.-Ing. |
| 12 | Zirkulationsgesteuertes Rotorsystem für Luftfahrzeuge | EP86114934.2 | 1986-10-27 | EP0223117A2 | 1987-05-27 | Zimmer, Herbert, Dr.-Ing. |
Zirkulationsgesteuertes Rotorsystem für Luftfahrzeuge, enthaltend Rotorblätter mit Ausblaseschlitzen und Steuerventileinheiten zur Erzielung einer zyklischen und bzw. oder multizyklischen bzw. kollektiven Rotorblattverstellung mittels differenzierter Druckgaszuführung von einer Druckkammer zu den Rotorblattschlitzen, und dem vorgegebenen Steuergesetz entsprechend verformbaren Steuergliedern, wobei die Steuerglieder (51; 52) Steuerflächen (58) mit ringförmigem Grundriß, entsprechend der von den Öffnungen (59) der Druckgasführung (60, 61 bzw. 66, 67) bei Rotation überdeckten Ringfläche aufweisen und ferner die Steuerglieder (51; 52) in Richtung des Ringflächenumfanges (U) und quer dazu längenveränderlich ausgebildet sind in einer Größenordnung, entsprechend der Verformung der Steuerglieder zur Änderung der Steuerspalte (S) zwischen den Öffnungen (59) und der Steuerfläche (58) der Steuerventileinheiten (16). |
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| 13 | Active Flow Control For Ducted Fans And Fan-In-Wing Configurations | US15596170 | 2017-05-16 | US20180346108A1 | 2018-12-06 | Chunhua Sheng; Qiuying Zhao |
| Systems, methods, lift fans, and aircraft involving active flow control of a ducted fan or fan-in-wing configuration are described. | ||||||
| 14 | Mission adaptive rotor blade | US13403364 | 2012-02-23 | US09505492B2 | 2016-11-29 | Mark W. Scott |
| A rotor assembly for a rotary wing aircraft includes a plurality of rotor blades operably connected to a rotor shaft. Two or more active adaptive devices are located at one or more rotor blades of the plurality of rotor blades. The one or more active adaptive devices are operably connected to an aircraft flight control system such that, when activated, the one or more active adaptive devices change one or more operational characteristics of the rotor assembly. A method of operating a rotor assembly of a rotary wing aircraft includes rotating a plurality of rotor blades about a rotor shaft. Two or more active adaptive devices located at one or more rotor blades of the plurality of rotor blades are activated and change one or more operational characteristics of the rotor assembly. | ||||||
| 15 | Mechanically actuated slot for circulation control rotor | US379305 | 1989-07-13 | US4966526A | 1990-10-30 | Armand F. Amelio; William C. Fischer, Jr. |
| A circulation control rotor system for aircraft in which compressed air is directly supplied at generally constant pressure to plenums in the rotor blades and discharged through area controlled slots, the area controlling means involving camming surfaces and being actuated by cyclic, collective, aircraft vibration and flight stability inputs. | ||||||
| 16 | Rotor blade construction for circulation control aircraft | US664738 | 1984-10-25 | US4626171A | 1986-12-02 | Donald R. Carter, Sr.; Timothy A. Krauss; Matthew Sedlak |
| A circulation control aircraft rotor blade having a spanwise Coanda surface 16 and a plurality of spanwise extending flexible composite material panels 18 cooperating with the surface to define slots for the discharge of compressed air from within the blade with each panel having first flexure means 60 associated with screw adjustments 36 for establishing a slot opening preload and second flexure means 62 associated with screw adjustments 38 for establishing a slot maximum opening. | ||||||
| 17 | Circulation controlled rotor blade | US810539 | 1977-06-27 | US4131390A | 1978-12-26 | Jacob Schmidt, deceased |
| A circulation controlled rotor blade which reduces rotor flutter by introing a laminar flow over the trailing edge. A trailing edge structure has a deformable tube to control a spanwise slot formed by the juxtaposition of an upper trailing edge lip over the deformable tube. The laminar flow is created by compressed fluid directed through the rotor blade and through the slot. | ||||||
| 18 | Cam and nozzle control valve for fluid flow modulation | US43272674 | 1974-01-11 | US3917435A | 1975-11-04 | WILKERSON JOSEPH B; READER KENNETH R |
| A hub valve for a CCR helicopter comprising a nonrotating central cam and a movable nozzle at the inlet to each blade. The cam determines the azimuthal position and relative magnitude of the cyclic lift and the nozzles, which move radially inward and outward, determine the magnitude of the collective lift. In a second embodiment, the nozzles are cycled radially in sequence to provide cyclic lift control at a fundamental frequency as well as at harmonics of this frequency.
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| 19 | Higher harmonics hub valve | US41311073 | 1973-11-05 | US3904313A | 1975-09-09 | BERNAERTS HENRY J |
| A hub valve for a circulation control rotor having the inherent capability of producing pulses of air at a given frequency and at harmonics of that frequency. The valve comprises a series of diaphragm or other seals, one for each blade, at the inlet to the air passage in the blade. Each seal is connected by means of a connecting rod to a crankpin on the end of a crankarm. The crankarm is fixed to a support and control shaft in the middle of the hub. The rotational speed of the hub determines the primary frequency of the airflow pulses; the connecting rod and crankarm mechanism superimpose harmonics onto this primary frequency.
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| 20 | Labyrinth air valve for rotor hub | US38032273 | 1973-07-18 | US3853424A | 1974-12-10 | BERNAERTS H |
| An air valve for a circulation control helicopter rotor. The valve comprises an inner member and a rotating blade-carrying outer member with an air passage between the two; the inner member can be translated to a position that is eccentric with respect to the rotating outer member to cause a cyclic variation in the amount of air received by each blade. Sealing means are provided at the entrance to each rotor blade, the preferred form being a labyrinth structure on both the inner and outer members.
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