ES2010710B3 - Sistema para el control de una superficie aerodinamica movil de una aeronave. - Google Patents
Sistema para el control de una superficie aerodinamica movil de una aeronave.Info
- Publication number
- ES2010710B3 ES2010710B3 ES87401289T ES87401289T ES2010710B3 ES 2010710 B3 ES2010710 B3 ES 2010710B3 ES 87401289 T ES87401289 T ES 87401289T ES 87401289 T ES87401289 T ES 87401289T ES 2010710 B3 ES2010710 B3 ES 2010710B3
- Authority
- ES
- Spain
- Prior art keywords
- actuator
- aerodynamic surface
- aircraft
- wing
- control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/10—Adjustable control surfaces or members, e.g. rudders one surface adjusted by movement of another, e.g. servo tabs
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Operated Clutches (AREA)
- Mechanical Control Devices (AREA)
- Catching Or Destruction (AREA)
- Feedback Control In General (AREA)
- Traffic Control Systems (AREA)
- Details Of Aerials (AREA)
Abstract
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.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR8608652A FR2600035B1 (fr) | 1986-06-16 | 1986-06-16 | Systeme pour la commande d'une surface aerodynamique mobile d'un aeronef. |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| ES2010710B3 true ES2010710B3 (es) | 1989-12-01 |
Family
ID=9336355
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| ES87401289T Expired ES2010710B3 (es) | 1986-06-16 | 1987-06-09 | Sistema para el control de una superficie aerodinamica movil de una aeronave. |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US4765572A (es) |
| EP (1) | EP0250293B1 (es) |
| JP (1) | JPS632795A (es) |
| CA (1) | CA1300114C (es) |
| DE (1) | DE3760445D1 (es) |
| ES (1) | ES2010710B3 (es) |
| FR (1) | FR2600035B1 (es) |
Families Citing this family (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4884748A (en) * | 1988-09-02 | 1989-12-05 | United Technologies Corporation | Fairing flap arrangement |
| FR2737698B1 (fr) * | 1995-08-08 | 1997-10-24 | Aerospatiale | Systeme pour commander une gouverne articulee sur une structure d'un vehicule |
| FR2748720B1 (fr) * | 1996-05-17 | 1998-07-24 | Aerospatiale | Systeme pour la commande d'un volet compensateur de gouverne d'aeronef |
| US6257528B1 (en) * | 1999-07-20 | 2001-07-10 | The Boeing Company | Vehicle control system and method employing control surface and geared tab |
| US8256710B2 (en) * | 2007-09-14 | 2012-09-04 | Spectrum Aeronautical, Llc | Live trim tabs |
| US8876063B2 (en) * | 2007-12-10 | 2014-11-04 | The Boeing Company | Flight control using multiple actuators on primary control surfaces with tabs |
| RU2370412C1 (ru) * | 2008-02-26 | 2009-10-20 | Открытое акционерное общество "Государственное машиностроительное конструкторское бюро "Вымпел" им. И.И. Торопова" | Блок рулевых приводов |
| RU2387577C1 (ru) * | 2009-02-02 | 2010-04-27 | Открытое акционерное общество "Государственное машиностроительное конструкторское бюро "Вымпел" им. И.И. Торопова" | Рулевой привод |
| RU2444463C1 (ru) * | 2010-09-15 | 2012-03-10 | Открытое акционерное общество "Государственное машиностроительное конструкторское бюро "Вымпел" им. И.И. Торопова" | Рулевой привод |
| US9180961B2 (en) | 2013-01-28 | 2015-11-10 | The Boeing Company | Control surface for creating variable camber along a wing |
| EP2805879B1 (en) * | 2013-05-22 | 2017-07-05 | Airbus Operations GmbH | Flap arrangement for a wing of an aircraft and an aircraft with a wing comprising such a flap arrangement |
| CN104648657A (zh) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | 一种可抑制振动的带调整片操纵面 |
| CN104908956A (zh) * | 2015-05-21 | 2015-09-16 | 江西洪都航空工业集团有限责任公司 | 自动纠偏脚蹬弹簧机构 |
| CN108082448B (zh) * | 2017-11-03 | 2022-10-28 | 中航通飞研究院有限公司 | 一种双腔液压助力器非线性补偿装置 |
| CN113998095B (zh) * | 2021-11-08 | 2024-07-02 | 陕西千山航空电子有限责任公司 | 一种教练机后缘襟翼控制系统的控制方法 |
| EP4331975A1 (en) * | 2022-09-01 | 2024-03-06 | Airbus Operations GmbH | Trailing edge system for a wing of an aircraft, method of operating control surfaces of an aircraft, aircraft wing and aircraft |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2395671A (en) * | 1940-09-26 | 1946-02-26 | Douglas Aircraft Co Inc | Control means for airfoils |
| US2623717A (en) * | 1946-05-06 | 1952-12-30 | Sperry Corp | Control system for controlled airfoils of aircraft |
| US2843344A (en) * | 1948-06-02 | 1958-07-15 | Gen Dynamics Corp | Aircraft trim tab control |
| FR1142454A (fr) * | 1954-12-24 | 1957-09-18 | Bristol Aeroplane Co Ltd | Perfectionnements aux commandes de vol d'un avion |
| US3378217A (en) * | 1966-09-02 | 1968-04-16 | Bendix Corp | Trim disconnect device for an aircraft control system |
| US3790108A (en) * | 1972-11-13 | 1974-02-05 | Mc Donnell Douglas Corp | Redundant stabilizer control |
-
1986
- 1986-06-16 FR FR8608652A patent/FR2600035B1/fr not_active Expired
-
1987
- 1987-06-09 EP EP87401289A patent/EP0250293B1/fr not_active Expired
- 1987-06-09 ES ES87401289T patent/ES2010710B3/es not_active Expired
- 1987-06-09 DE DE8787401289T patent/DE3760445D1/de not_active Expired
- 1987-06-12 US US07/061,145 patent/US4765572A/en not_active Expired - Lifetime
- 1987-06-16 JP JP62148162A patent/JPS632795A/ja active Pending
- 1987-06-16 CA CA000539756A patent/CA1300114C/fr not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| US4765572A (en) | 1988-08-23 |
| JPS632795A (ja) | 1988-01-07 |
| FR2600035A1 (fr) | 1987-12-18 |
| CA1300114C (fr) | 1992-05-05 |
| EP0250293B1 (fr) | 1989-08-16 |
| EP0250293A1 (fr) | 1987-12-23 |
| DE3760445D1 (en) | 1989-09-21 |
| FR2600035B1 (fr) | 1988-10-21 |
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