CN103466079A - Manipulation and suspension coupled support arm component of airplane tail fin - Google Patents
Manipulation and suspension coupled support arm component of airplane tail fin Download PDFInfo
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- CN103466079A CN103466079A CN2013103744216A CN201310374421A CN103466079A CN 103466079 A CN103466079 A CN 103466079A CN 2013103744216 A CN2013103744216 A CN 2013103744216A CN 201310374421 A CN201310374421 A CN 201310374421A CN 103466079 A CN103466079 A CN 103466079A
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- suspension
- support arm
- manipulation
- actuator
- control surface
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention belongs to the technical field of airplane structure design and particularly relates to a manipulation and suspension coupled support arm component of an airplane tail fin. The component is characterized by comprising a manipulation and suspension coupled support arm, a control surface manipulation actuator and a manipulation and suspension coupled bearing, wherein a manipulation lug sheet and a suspension lug sheet are arranged on the coupled bearing; a suspension joint is arranged at one end of the coupled support arm; a mounting position of the control surface manipulation actuator on the coupled support arm is behind a suspension point of a control surface and before a connection point between the coupled support arm and a stabilizing surface; a connecting part between the coupled support arm and the stabilizing surface is not connected with the mounting position of the actuator; the other end of the control surface manipulation actuator is connected with the manipulation lug sheet of the coupled bearing; and the suspension lug sheet of the coupled bearing is connected with the suspension joint of the coupled support arm. The component solves the problem of deformation of a front beam of the control surface of an airplane, can reduce a load of the control surface manipulation actuator of the airplane on the stabilizing surface and the control surface of the airplane by approximately 50%, balances distribution of the suspension load of the control surface on two side wall plates of the stabilizing surface, and obviously reduces the weight of an airplane tail fin structure.
Description
Technical field
The invention belongs to the aeroplane structure design technical field, be specifically related to a kind of aircraft tail and handle suspension coupling support arm assembly.
Background technology
Large-scale and superjumbo plane generally adopts the power element of hydraulic actuator as control surface deflection.Consider remaining, installing space and system weight, each rudder face need to be installed two and handle actuator and two above suspension arms usually, and they are on the inner end face at different ribs arranged apart of aircraft tail stabilator trailing edge.Yet this layout makes the rudder face front-axle beam bear very large face external load in a manipulation point position, causes that the distortion of rudder face front-axle beam is excessive, does not meet the rigidity Design requirement, if increase rudder face rigidity, need to pay larger weight cost.The A320 aircraft evelvator of Air Passenger company just adopts above-mentioned arrangement form, sees Fig. 1 and Fig. 2.
Summary of the invention
The objective of the invention is: provide under a kind of prerequisite the aircraft rudder surface front-axle beam is not gained in weight, a kind of aircraft tail of the problem of the excessive deformation that solution aircraft rudder surface manipulation actuator causes the rudder face front-axle beam is handled and is hung the coupling support arm assembly.
Technical scheme of the present invention is: a kind of aircraft tail is handled and is hung the coupling support arm assembly, it is characterized in that, comprise handling and hang the coupling support arm, rudder face is handled actuator and is handled and hang the coupling bearing, handle to hang on the coupling bearing to be furnished with the suspension auricle that rudder face is handled the manipulation auricle of actuator and coupling support arm joint is installed is installed, handle suspension coupling support arm one end and be provided with suspension joint, after the installation site of rudder face manipulation actuator on the coupling support arm is arranged in control surface suspension point, before handling suspension coupling support arm and stabilator point of connection, handling suspension coupling support arm does not join with the connecting bridge of stabilator and the installation site of actuator, rudder face is handled the actuator other end and is connected on the manipulation auricle of handling suspension coupling bearing, handling the suspension auricle that hangs the coupling bearing is connected with the suspension joint of handling suspension coupling support arm.
The invention has the beneficial effects as follows: aircraft tail is handled and is hung the problem on deformation that coupling assembly has solved the aircraft rudder surface front-axle beam, aircraft rudder surface can be handled to actuator simultaneously the load of aircraft stabilator and aircraft rudder surface is reduced approximately to 50 percent, balance the distribution of control surface suspension load on the stabilator two side wall panels, obvious to the aircraft tail Structure weight reduce.
The accompanying drawing explanation
Fig. 1: rudder face is handled the actuator erection plan
Fig. 2: control surface suspension arm is installed
Fig. 3: handle and hang coupling assembly scheme of installation (front elevation)
Fig. 4: handle and hang coupling assembly scheme of installation (birds-eye view)
Fig. 5: handle and hang the coupling schematic diagram
Fig. 6: handle and hang coupling support arm schematic diagram (front elevation)
Fig. 7: handle and hang coupling support arm schematic diagram (birds-eye view)
1, rudder face front-axle beam 2, rudder face is handled bearing 3, handle actuator 4, actuator erection support 5, the stabilator back rest 6, docking bolt assembly 7, the docking bolt assembly, 8, suspension arm crossover sub 9, suspension arm, 10, docking bolt assembly 11, the control surface suspension bearing, 12, docking bolt assembly 13, coupling support arm 14, the docking bolt assembly, 15, docking bolt assembly 16, the coupling bearing, 17, hang auricle 18, handle auricle, 19, suspension joint 20, trough girder 21, grooved column 22, load coupled section 23, handle actuator installation site 24, on base with the connecting bridge 25 of stabilator wallboard, on base with the connecting bridge 26 of the stabilator back rest, the part be connected with the stabilator wallboard on base
The specific embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail:
A kind of aircraft tail is handled and is hung the coupling support arm assembly, it is characterized in that, comprise handling and hang coupling support arm 13, rudder face is handled actuator and is handled and hang coupling bearing 16, handle to hang on the coupling bearing to be furnished with the suspension auricle 17 that rudder face is handled the manipulation auricle 18 of actuator and coupling support arm joint is installed is installed, handle suspension coupling support arm one end and be provided with suspension joint, after the installation site of rudder face manipulation actuator on the coupling support arm is arranged in the control surface suspension joint, before handling suspension coupling support arm and stabilator point of connection, handling suspension coupling support arm does not join with the connecting bridge of stabilator and the installation site of actuator, rudder face is handled the actuator other end and is connected on the manipulation auricle of handling suspension coupling bearing, handling the suspension auricle that hangs the coupling bearing is connected with the suspension joint of handling suspension coupling support arm.
Above-mentioned manipulation is hung the coupling support arm by being that six parts form, be followed successively by control surface suspension 19 joints near rudder face one end, up and down four trough girders 20, connecting support arm both sides trough girder grooved column 21, load coupled section 22, handle actuator installation site 23 and near the base 24,25,26 of stabilator one side.The form that the control surface suspension joint can be designed to crossover sub is connected on the coupling support arm with bolt; The suspension joint of four trough girder connecting support arms and load coupled section up and down; The grooved column can strengthen support arm rigidity; Suspended load and actuator load is partial offset on the load coupled section of support arm; Handling actuator installation stud only is connected with the load coupled section; Support arm base is connected with the load coupled section, externally with the stabilator two side wall panels, with the stabilator back rest, is connected respectively.
Claims (1)
1. an aircraft tail is handled and is hung the coupling support arm assembly, it is characterized in that, comprise handling and hang the coupling support arm, rudder face is handled actuator and is handled and hang the coupling bearing, handle to hang on the coupling bearing to be furnished with the suspension auricle that rudder face is handled the manipulation auricle of actuator and coupling support arm joint is installed is installed, handle suspension coupling support arm one end and be provided with suspension joint, after the installation site of rudder face manipulation actuator on the coupling support arm is arranged in control surface suspension point, before handling suspension coupling support arm and stabilator point of connection, handling suspension coupling support arm does not join with the connecting bridge of stabilator and the installation site of actuator, rudder face is handled the actuator other end and is connected on the manipulation auricle of handling suspension coupling bearing, handling the suspension auricle that hangs the coupling bearing is connected with the suspension joint of handling suspension coupling support arm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013103744216A CN103466079A (en) | 2013-08-23 | 2013-08-23 | Manipulation and suspension coupled support arm component of airplane tail fin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013103744216A CN103466079A (en) | 2013-08-23 | 2013-08-23 | Manipulation and suspension coupled support arm component of airplane tail fin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103466079A true CN103466079A (en) | 2013-12-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013103744216A Pending CN103466079A (en) | 2013-08-23 | 2013-08-23 | Manipulation and suspension coupled support arm component of airplane tail fin |
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| CN (1) | CN103466079A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104154109A (en) * | 2014-04-17 | 2014-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Bi-directional high load-bearing capacity wear-resistant mechanism |
| CN108082449A (en) * | 2018-03-06 | 2018-05-29 | 中航通飞研究院有限公司 | A kind of large aircraft control surface suspension structure |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2354420B2 (en) * | 1973-10-31 | 1977-08-11 | Dornier Gmbh, 7990 Friedrichshafen | FLAP CONTROL ARRANGEMENT ON A WING FOR AIRCRAFT |
| US4470569A (en) * | 1981-12-28 | 1984-09-11 | Mcdonnell Douglas Corporation | Locking, redundant slat drive mechanism |
| DE3636053A1 (en) * | 1986-10-23 | 1988-05-11 | Messerschmitt Boelkow Blohm | Device for the extension of slats |
| US5538202A (en) * | 1993-11-02 | 1996-07-23 | Northrop Grumman Corporation | Hydraulic actuation system for aircraft control surfaces |
| US20110139938A1 (en) * | 2009-12-11 | 2011-06-16 | Nabtesco Corporation | Aircraft reaction link |
| CN102791574A (en) * | 2009-11-13 | 2012-11-21 | 空中客车运作有限责任公司 | Flap adjusting system of an aircraft with a regulating flap |
| EP2530012A2 (en) * | 2011-06-02 | 2012-12-05 | Nabtesco Corporation | Aircraft control surface drive mechanism |
-
2013
- 2013-08-23 CN CN2013103744216A patent/CN103466079A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2354420B2 (en) * | 1973-10-31 | 1977-08-11 | Dornier Gmbh, 7990 Friedrichshafen | FLAP CONTROL ARRANGEMENT ON A WING FOR AIRCRAFT |
| US4470569A (en) * | 1981-12-28 | 1984-09-11 | Mcdonnell Douglas Corporation | Locking, redundant slat drive mechanism |
| DE3636053A1 (en) * | 1986-10-23 | 1988-05-11 | Messerschmitt Boelkow Blohm | Device for the extension of slats |
| US5538202A (en) * | 1993-11-02 | 1996-07-23 | Northrop Grumman Corporation | Hydraulic actuation system for aircraft control surfaces |
| CN102791574A (en) * | 2009-11-13 | 2012-11-21 | 空中客车运作有限责任公司 | Flap adjusting system of an aircraft with a regulating flap |
| US20110139938A1 (en) * | 2009-12-11 | 2011-06-16 | Nabtesco Corporation | Aircraft reaction link |
| EP2530012A2 (en) * | 2011-06-02 | 2012-12-05 | Nabtesco Corporation | Aircraft control surface drive mechanism |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104154109A (en) * | 2014-04-17 | 2014-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Bi-directional high load-bearing capacity wear-resistant mechanism |
| CN104154109B (en) * | 2014-04-17 | 2017-02-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Bi-directional high load-bearing capacity wear-resistant mechanism |
| CN108082449A (en) * | 2018-03-06 | 2018-05-29 | 中航通飞研究院有限公司 | A kind of large aircraft control surface suspension structure |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20131225 |