| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | FLYING VEHICLE AERODYNAMIC CONFIGURATION | RU93031341 | 1993-06-08 | RU2093417C1 | 1997-10-20 | GRIGOREV VLADIMIR G; GRIGOREV DMITRIJ V |
| FIELD: aerodynamic configurations of flying vehicles; manufacture of new flying vehicles and modification of existing flying vehicles. SUBSTANCE: flying vehicle includes case, wing and tail unit. Wing panels are mounted for rotation relative to case. Trailing edge of each wing panel is provided with additional control aerodynamic surface for rotation about axis parallel to axis of rotation of wing panel. Axles of wing panels are mounted without mechanical linkage with outlet of control actuators. Additional control aerodynamic surfaces are mechanically linked with outlet of control actuators of these surfaces. Tail unit panels are mounted for rotation relative to case and are mechanically linked with outlets of tail unit control actuators. EFFECT: enhanced efficiency. 1 dwg | ||||||
| 162 | РУЛЕВОЙ ПРИВОД УПРАВЛЯЕМОЙ АЭРОДИНАМИЧЕСКОЙ ПОВЕРХНОСТИ | RU94024244 | 1994-06-29 | RU94024244A | 1996-06-10 | GRIGOR EV V G; GRIGOR EV D V |
| Изобретениеможетиспользоватьсядляотклоненияуправляемыхаэродинамическихповерхностей (УАП) летательногоаппарата (ЛА). Цельизобретениясостоитв обеспеченииустойчивойработыприводав широкомдиапазонескоростейи высотполетаЛА. Дляэтогопривод, кромерычагауправления (РУ), установленногов корпусеЛА, дополнительнойуправляемойаэродинамическойповерхности (ДУАП), установленнойнаУАПв областиеезаднейкромкис возможностьювращениявокругоси, параллельнойосивращенияУАП, имеханическойпроводкиотРУк ДУАП, содержитпружинуи демпфер, установленныев корпусеЛАи механическисвязанныес УАП, анавыходеизкорпусаЛАк ДУАПмеханическаяпроводкапроложенавдольосивращенияУАП. 3 ил. | ||||||
| 163 | SISTEMA PARA EL CONTROL DE UNA SUPERFICIE AERODINAMICA MOVIL DE UNA AERONAVE. | ES87401289 | 1987-06-09 | ES2010710B3 | 1989-12-01 | BELLEGO ROGER; FOCH ETIENNE |
| SISTEMA PARA EL CONTROL DE UNA SUPERFICIE AERODINAMICA (2), MONTADA MOVIL SOBRE UNA AERONAVE (1) DE MANERA A PODER LIBREMENTE PIVOTAR ALREDEDOR DE UN EJE FIJO (10) Y PROVISTA DE UN ALERON COMPENSADOR (14) EL MISMO ARTICULADO SOBRE EL BORDE DE FUGA (12) DE DICHA SUPERFICIE AERODINAMICA (2), SIENDO TAL DICHO SISTEMA QUE SE PREVEN MEDIOS ELASTICOS DE ENLACE (18) ENTRE DICHO ALERON COMPENSADOR (14) Y DICHA SUPERFICIE AERODINAMICA (2) Y QUE DICHO ALERON COMPENSADOR (14) ES DIRECTAMENTE ACCIONABLE POR EL PILOTO, MEDIANTE UN ORGANO DE ACCIONAMIENTO VOLUNTARIO (16) Y DE UN VARILLAJE (17). ISTEMA SE CARACTERIZA EN QUE COMPRENDE: NTERPUESTO ENTRE DICHOS MEDIOS ELASTICOS DE ENLACES (18) Y DICHA SUPERFICIE AERODINAMICA (2); 4) DE DICHO ACCIONADOR (2); Y CHO DISPOSITIVO DE CONTROL (44) DEL ACCIONADOR CONTROLA TAMBIEN DICHO EMBRAGUE (46), DE MANERA QUE ESTE ESTE EN POSICION DESEMBRAGADA CUANDO DICHO ACCIONADOR ESTA ACTIVO Y EN POSICION EMBRAGADA CUANDO DICHO ACCIONADOR ESTA INACTIVO. | ||||||
| 164 | SYSTEME POUR LA COMMANDE D'UNE SURFACE AERODYNAMIQUE MOBILE D'UN AERONEF. | FR8608652 | 1986-06-16 | FR2600035A1 | 1987-12-18 | BELLEGO ROGER; ROGER BELLEGO ET ETIENNE FOCH; FOCH ETIENNE |
| SYSTEME POUR LA COMMANDE D'UNE SURFACE AERODYNAMIQUE2, MONTEE MOBILE SUR UN AERONEF1 DE FACON A POUVOIR LIBREMENT PIVOTER AUTOUR D'UN AXE FIXE10 ET POURVUE D'UN VOLET COMPENSATEUR14 LUI-MEME ARTICULE SUR LE BORD DE FUITE12 DE LADITE SURFACE AERODYNAMIQUE2, LEDIT SYSTEME ETANT TEL QUE DES MOYENS ELASTIQUES DE LIAISON18 SONT PREVUS ENTRE LEDIT VOLET COMPENSATEUR14 ET LADITE SURFACE AERODYNAMIQUE2 ET QUE LEDIT VOLET COMPENSATEUR14 EST DIRECTEMENT ACTIONNABLE PAR LE PILOTE, PAR L'INTERMEDIAIRE D'UN ORGANE D'ACTIONNEMENT VOLONTAIRE16 ET D'UNE TIMONERIE17. SELON L'INVENTION, CE SYSTEME EST CARACTERISE EN CE QU'IL COMPORTE : -UN DISPOSITIF D'ACTIONNEMENT40 INTERPOSE ENTRE LESDITS MOYENS ELASTIQUES DE LIAISON18 ET LADITE SURFACE AERODYNAMIQUE2; UN DISPOSITIF DE COMMANDE44 DUDIT DISPOSITIF D'ACTIONNEMENT40; ET -UN EMBRAYAGE46 RELIANT LA STRUCTURE DE L'AERONEF A LADITE TIMONERIE17; ET EN CE QUE LEDIT DISPOSITIF DE COMMANDE44 DU DISPOSITIF D'ACTIONNEMENT COMMANDE EGALEMENT LEDIT EMBRAYAGE46, DE FACON QUE CELUI-CI SOIT EN POSITION DEBRAYEE LORSQUE LEDIT DISPOSITIF D'ACTIONNEMENT EST ACTIF ET EN POSITION EMBRAYEE LORSQUE LEDIT DISPOSITIF D'ACTIONNEMENT EST INACTIF. | ||||||
| 165 | DEVICE FOR THE AUTOMATIC CONTROL OF AN AERODYNAMIC TRIMMER ASSOCIATED WITH AN AERODYNAMIC CONTROL SURFACE OF AN AIRCRAFT | GB8523633 | 1985-09-25 | GB2164905B | 1987-10-21 | POCCARD JACQUES |
| 166 | A device for automatically controlling an aerodynamic compensator associated to an aerodynamic control surface of an aircraft | FR8415123 | 1984-10-02 | FR2571021B1 | 1986-12-05 | POCCARD JACQUES |
| 167 | An apparatus for automatically controlling an aerodynamic compensation device which is associated with an aerodynamic steuerflaeche an aircraft | DE3534611 | 1985-09-26 | DE3534611A1 | 1986-04-10 | POCCARD JACUES |
| 168 | A device for automatically controlling an aerodynamic compensator associated to an aerodynamic control surface of an aircraft | FR8415123 | 1984-10-02 | FR2571021A1 | 1986-04-04 | POCCARD JACQUES |
| <P>DISPOSITIF POUR LA COMMANDE AUTOMATIQUE D'UN COMPENSATEUR AERODYNAMIQUE9 ARTICULE A L'ARRIERE D'UNE SURFACE AERODYNAMIQUE DE COMMANDE8 D'UN AERONEF, ELLE-MEME ARTICULEE SUR LA STRUCTURE6 DUDIT AERONEF, COMPORTANT UNE TRINGLE19 ARTICULEE D'UN COTE SUR LEDIT COMPENSATEUR AERODYNAMIQUE9 ET RELIEE DE L'AUTRE COTE A LA STRUCTURE6 DE L'AERONEF DE FACON QU'UN BRAQUAGE COMMANDE DE LADITE SURFACE AERODYNAMIQUE DE COMMANDE8 ENTRAINE AUTOMATIQUEMENT LE BRAQUAGE DUDIT COMPENSATEUR AERODYNAMIQUE9 PAR RAPPORT A LADITE SURFACE AERODYNAMIQUE DE COMMANDE8.</P><P>SELON L'INVENTION, CE DISPOSITIF EST CARACTERISE EN CE QUE, DU COTE OPPOSE AU COMPENSATEUR AERODYNAMIQUE, LADITE TRINGLE19 EST ARTICULEE A UN LEVIER12, LUI-MEME ARTICULE SUR LADITE STRUCTURE6 DE L'AERONEF ET EN CE QUE DES MOYENS14 SONT PREVUS POUR DEPLACER LE POINT D'ARTICULATION11 DE LA TRINGLE19 ET DU LEVIER12 DANS UNE DIRECTION AU MOINS APPROXIMATIVEMENT TRANSVERSALE A LADITE SURFACE AERODYNAMIQUE8, EN LIAISON AVEC LE BRAQUAGE COMMANDE DE LADITE SURFACE AERODYNAMIQUE.</P> | ||||||
| 169 | AIRCRAFT FLYING CONTROL SYSTEMS | GB8331086 | 1983-11-22 | GB8331086D0 | 1983-12-29 | |
| 170 | Empennage for air- and spacecraft | DE2855203 | 1978-12-21 | DE2855203A1 | 1980-06-26 | LASCHKA BORIS PROF DIPL ING DR |
| 171 | AIRCRAFT PITCH TRIM | AU2210977 | 1977-02-09 | AU2210977A | 1978-08-17 | BARTOE OTTO EDWIN JR |
| 172 | PL18181475 | 1975-07-04 | PL98970B1 | 1978-06-30 | ||
| 173 | A method and arrangement for nick trim in aircraft | DE2707598 | 1977-02-18 | DE2707598A1 | 1977-09-22 | BARTOE JUN OTTO E |
| 174 | SE1770067 | 1967-12-22 | SE331952B | 1971-01-18 | INGELMAN-SUNDBERG A | |
| 175 | Improved method and means for operating trimming or balancing flaps on the control surfaces of aircraft | GB563437 | 1937-02-25 | GB489392A | 1938-07-26 | |
| 489,392. Controlling aircraft. BOULTON PAUL AIRCRAFT, Ltd., and CLARKE, W. H. V. Feb. 25, 1937, No. 5634. [Class 4] In means for controlling either or both trimming and balancing tabs hinged to aircraft-control surfaces, a lever 5 is hinged to the frame of and is disposed wholly within the control surface 2, the lever is operatively connected to the tab and is connected to a member 4 which passes into or is attached to a fixed part 1 of the aircraft, the connection being at or in the vicinity of the hinge axis of the surface, the displacement of the connection from the axis along the lever determines the movement of the tab consequent upon movement of the surface. In one form, the surface 2 is pivoted to the part 1 by a hinge pin passed through interleaving brackets and the member 4 is slidable in a bracket carried by the part 1. In a modification, the member 4 is pivoted to the lever 5 so that it is in line with the rod 8. In a further form, the lever is formed with bifurcated arms, the arm 18, Fig. 8, being formed by a slot in which the end of the member 4 is engaged and the other arm carrying a pivot pin 9 which is connected to the rod 8. In this case, the bracket through which the member 4 slides is displaceably mounted on a screwthreaded bolt. | ||||||
| 176 | Рулевое устройство для летательных аппаратов | SU11009 | 1926-09-06 | SU7254A1 | 1928-12-31 | A FLETTNER |
| 177 | NL15549C - | NL15810 | 1920-07-27 | NL15549C | 1926-12-15 | |
| 178 | Improvements in apparatus for steering aircraft | GB1898820 | 1920-07-06 | GB147034A | 1922-01-06 | |
| 147,034. Flettner, A. March 20, 1918, [Convention date]. Steering and balancing.-In means for facilitating the operation of the steering-surfaces of aircraft by arranging the hand control of gyroscopic stabilizing-apparatus to adjust small auxiliary surfaces the air pressure on which then acts through lever arms to move the main steering- surfaces, the auxiliary, plane g is arranged at the rear edge of the main steering-plane f and operated by the traction devices indicated in dotted lines. According to the Specification as open to inspection under Sect. 91 (3) (a), the auxiliary plane d, Fig. 1 (Cancelled), adjusted by the wires indicated by dotted lines, is connected by a lever arm c to the compensating-plane b of an aileron c. One or more other auxiliary planes may be interposed between the operating-device and the plane d. This subject-matter does not appear in the Specification as accepted. | ||||||
| 179 | DISPOSITIVO O QUAL EM USO É SUBMETIDO AO FLUXO DE FLUIDO, MÉTODO DE OPERAR UMA AERONAVE PELO REFERIDO DISPOSITIVO E AERONAVE | BRPI1000973 | 2010-02-22 | BRPI1000973B8 | 2022-12-13 | STEPHEN DAYNES; PAUL WEAVER; KEVIN POTTER |
| DISPOSITIVO QUE É SUBMETIDO A FLUXO DE FLUIDO Um dispositivo (15) tal como um aerofólio o qual em USO é submetido ao fluxo de fluido, inclui uma parte de superfície externa (24b, 25b) cuja geometria é variável para afetar o fluxo de fluido, o dispositivo (15) incluindo uma estrutura de suporte (31) que suporta a parte de superfície externa (24b, 25b), a estrutura de suporte (31) sendo interna ao dispositivo (15) e incluindo vários membros de suporte (32) de material composto, a geometria da estrutura de suporte (31) podendo ser mudada por um equipamento de acionamento (50) entre uma primeira geometria estável e uma segunda geometria estável para efetuar variação na geometria da parte de superfície externa (24b,25b), os membros de suporte (32) proporcionando rigidez estrutural à parte de superfície externa (24b, 25b). | ||||||
| 180 | Controlling aerodynamic spanload control devices | GB201709131 | 2017-06-08 | GB2563261A | 2018-12-12 | MURRAY CROSS |
| An aerodynamic structure 111, such as an aircraft wing, has a lifting surface 11, which deforms in flight; a control device 12, such as a wing tip device, is movably attached to the lifting surface; an actuation mechanism 14 transmits the deformation movement of the lifting surface to the control device. The lifting surface may twist about a spanwise flexural axis x. Twisting deformation of the lifting surface, in either direction, may move the control device into a deployed position, in which it generates torque and/or force effective about the flexural axis in the opposing direction to the deformation. The actuator may have two fixed length wires (fig.2,242), each with an attachment location on the lifting surface, near an upper and a lower surface respectively, with their other ends attached to a rotating control wheel (fig.2,243). Rotation of the control wheel about its axis causes rotation of the control device about an axis of rotation at an angle to that of the control wheel. An avionics system may be coupled to a deformation sensor and a locking mechanism to prevent movement of the control device in response to certain sensed conditions or failure of actuation mechanism components. | ||||||
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