CN204433037U - The servo-actuated seal structure of a kind of vehicle rudder leading edge - Google Patents
The servo-actuated seal structure of a kind of vehicle rudder leading edge Download PDFInfo
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- CN204433037U CN204433037U CN201420815590.9U CN201420815590U CN204433037U CN 204433037 U CN204433037 U CN 204433037U CN 201420815590 U CN201420815590 U CN 201420815590U CN 204433037 U CN204433037 U CN 204433037U
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Abstract
The utility model belongs to Aeronautics and Astronautics and near space technical field, relates to the servo-actuated seal structure of a kind of vehicle rudder leading edge.The utility model have employed connecting rod mechanism, and control surface deflection drives drag link mechanism, then drives control surface deflection, realizes servo-actuated obturaging.Adopt seal structure of the present utility model, servo-actuated obturaging can be realized, and good rigidity, load-carrying capacity is strong, and reliability is high; And the problem of obturaging of the complicated aerofoil profile of complex appearance can be solved by piecemeal multimachine structure.Especially obturage especially effective to the rudder face of rudder face rotating shaft not in the middle of aerofoil profile.Also heat insulation, the requirement of obturaging to re-entry space vehicle and near space vehicle can be met.
Description
Technical field
The utility model belongs to Aeronautics and Astronautics and near space technical field, relates to the servo-actuated densification device of a kind of vehicle rudder leading edge.
Background technology
Aircraft, re-entry space vehicle and high speed near space vehicle are all generally improve aeroperformance by rudder face, between rudder face and fixing body, inevitably there is gap, this gap can leak through air-flow, affect the effect of rudder face, and the gap of high-speed aircraft and re-entry space vehicle also can cause Aerodynamic Heating to enter inside, affect normally using and running of inner structure and equipment.Therefore aircraft all will take certain measure to obturage to rudder face leading edge.
The mode of obturaging of current aircraft generally adds plate of obturaging between rudder face and fixed sturcture, and plate of obturaging generally is arranged on the trailing edge of fixed sturcture, is generally cantilever design, is arranged on the trailing edge of fixed sturcture in bar for shape.This kind of seal structure is relatively simple for structure, but poor rigidity, easily damaged, weak effect of obturaging when control surface deflection angle is larger.
And if the rotating shaft of rudder face is not when the midway location of aerofoil profile, namely rotating shaft is relatively when top airfoil or lower aerofoil, then opposite side obturage plate due to cantilever very long, rigidity can be very poor, and the problem of weak effect of obturaging is especially outstanding.
Summary of the invention
The purpose of this utility model be propose a kind of can according to the deflection situation of rudder face, meet the servo-actuated seal structure of vehicle rudder leading edge of the obturaging of the gap between rudder face and main structure, insulation requirement in real time.
Technical solution of the present utility model adopts connecting rod mechanism, relies on control surface deflection drivening rod structure to realize servo-actuated obturaging.This cover mechanism comprises L shape part, plate suspension joint of obturaging, bearing, plate front connector of obturaging, plate pull bar of obturaging, rudder face pull bar, joint, rudder face rod head, rudder face rod head, plate of obturaging after plate of obturaging.
Wherein obturage plate suspension joint and bearing is arranged on fixed sturcture, and rudder face rod head is arranged on movable rudder face, and after obturage plate front connector and plate of obturaging, jiont treatment is being obturaged on plate; L shape part is provided with three hinge-points, and the hinge-point of its rotation angle position is arranged on bearing, and two other hinge-point is connected with rudder face pull bar and plate pull bar of obturaging respectively; Plate pull bar one end of obturaging is connected with L shape part, and the other end is connected with joint after plate of obturaging; Rudder face pull bar one end is connected with rudder face rod head, and the other end is connected with L shape part.
Obturage plate pull bar and the equal adjustable length of rudder face pull bar, plate pull bar middle opening of wherein obturaging, to ensure installation and the proper motion of rudder face pull bar, avoids the hinge not bias that causes of coplanar.
The control surface suspension joint of main plane and the upper joint of rudder face hinged.
All can many groups be arranged, to meet the requirement such as rigidity, intensity with top connection, pull bar etc.Pull bar adjustable length, obturages and mechanism kinematic needs with satisfied guarantee.
The advantage that the utility model has and beneficial effect
Mechanism of obturaging of the present utility model, without the need to extra power driven, drives the deflection of L shape part by rudder face pull bar during control surface deflection, and the deflection of L shape part has drive plate pull bar of obturaging to pull plate deflection of obturaging, thus realizes obturaging the servo-actuated of plate.
Adopt seal structure of the present utility model, according to control surface deflection situation, servo-actuated in real time obturaging can be realized, and good rigidity, load-carrying capacity is strong, and reliability is high; And the problem of obturaging of the complicated aerofoil profile of complex appearance can be solved by piecemeal multimachine structure.Especially obturage especially effective to the rudder face of rudder face rotating shaft not in the middle of aerofoil profile.Also heat insulation, the requirement of obturaging to re-entry space vehicle and near space vehicle can be met.
Mechanism of obturaging of the present utility model, without the need to extra power driven, by mechanisms such as rudder face pull bars during control surface deflection, realizes plate interlock of obturaging.
Accompanying drawing explanation
Fig. 1 is the utility model one embodiment structural representation.
Fig. 2 is the utility model one embodiment structure shaft side figure.
Fig. 3 is the utility model one embodiment structure shaft side figure.
Fig. 4 the utility model is obturaged plate pull bar middle opening situation map.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described in further detail, refers to Fig. 1 to Fig. 4.
As shown in Figure 1, Figure 2, shown in Fig. 3 and Fig. 4, the servo-actuated mechanism of obturaging of a kind of rudder face leading edge.Comprise, L shape part 1, plate suspension joint 2 of obturaging, bearing 3, plate front connector 4 of obturaging, plate pull bar 5 of obturaging, rudder face pull bar 6, joint 7 after plate of obturaging, rudder face rod head 8, obturage plate 9-.Described servo-actuated seal structure is bar linkage structure, its L shape part 1 is provided with three hinge-points, respectively with bearing 3, rudder face pull bar 6 and plate pull bar 5 of obturaging are articulated and connected, described bearing 3 is arranged on primary aircraft structure web surface, described plate suspension joint 2 of obturaging is arranged on primary aircraft structure web surface, after described obturage plate pull bar 5 and L shape part 1 and plate of obturaging, joint 7 is articulated and connected respectively, described rudder face pull bar 6 is articulated and connected respectively with L shape part 1 and rudder face rod head 8, after described obturage plate front connector 4 and plate of obturaging, joint 7 is arranged on and obturages on plate 9, described plate front connector 4 of obturaging is articulated and connected with plate suspension joint 2 of obturaging.
Preferably, plate pull bar 5 of obturaging described in is installed rear in X-shaped crossing condition with rudder face pull bar 6.
Preferably, described in obturage in the middle part of plate pull bar 5 and open long through-hole 10, ensure installation and the proper motion of rudder face pull bar 6.
Preferably, to obturage described in plate pull bar 5 and rudder face pull bar 6 adjustable in length.
As shown in Figure 1, Figure 2, Figure 3 and Figure 4, during use, need according to the size of the Position Design angle-shaped piece of aircraft aerofoil profile height and control surface suspension joint and pull bar length, and each jiont treatment position.
If aerofoil profile complexity can design Duo Zu mechanism, to meet requirement of obturaging.
Plate suspension joint of obturaging can arrange many groups, with proof strength and rigidity requirement.
Each hinge-point should ensure enough precision, meets structure motion requirement.
During control surface deflection, drive L shape part 1 to deflect by rudder face pull bar 6, L shape part 1 deflects drive plate pull bar 5 of obturaging and pulls plate 9 of obturaging to deflect, thus realizes obturaging the servo-actuated of plate.
Claims (4)
1. the servo-actuated seal structure of vehicle rudder leading edge, it is characterized in that, servo-actuated seal structure comprises L shape part (1), to obturage plate suspension joint (2), bearing (3), to obturage plate front connector (4), to obturage plate pull bar (5), rudder face pull bar (6), to obturage joint (7) after plate, rudder face rod head (8), to obturage plate (9), long through-hole (10), described servo-actuated seal structure is connecting rod mechanism, described L shape part (1) is provided with three hinge-points, the hinge-point of its rotation angle position is arranged on bearing (3), two other hinge-point is articulated and connected with rudder face pull bar (6) and plate pull bar (5) of obturaging respectively, described bearing (3) is arranged on the web surface of primary aircraft structure, described plate suspension joint (2) of obturaging is arranged on the web surface of primary aircraft structure, after described obturage plate pull bar (5) and L shape part (1) and plate of obturaging, joint (7) is articulated and connected respectively, described rudder face pull bar (6) is articulated and connected respectively with L shape part (1) and rudder face rod head (8), after described obturage plate front connector (4) and plate of obturaging, joint (7) is arranged on plate of obturaging (9), described plate front connector (4) of obturaging is articulated and connected with plate suspension joint (2) of obturaging.
2. the servo-actuated seal structure of a kind of vehicle rudder leading edge according to claim 1, is characterized in that, described plate pull bar (5) of obturaging is X-shaped crossing condition after installing with rudder face pull bar (6).
3. the servo-actuated seal structure of a kind of vehicle rudder leading edge according to claim 1, is characterized in that, long through-hole (10) is opened at described plate pull bar (5) middle part of obturaging.
4. the servo-actuated seal structure of a kind of vehicle rudder leading edge according to claim 1, is characterized in that, described obturage plate pull bar (5) and rudder face pull bar (6) adjustable in length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420815590.9U CN204433037U (en) | 2014-12-19 | 2014-12-19 | The servo-actuated seal structure of a kind of vehicle rudder leading edge |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420815590.9U CN204433037U (en) | 2014-12-19 | 2014-12-19 | The servo-actuated seal structure of a kind of vehicle rudder leading edge |
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| Publication Number | Publication Date |
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| CN204433037U true CN204433037U (en) | 2015-07-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420815590.9U Active CN204433037U (en) | 2014-12-19 | 2014-12-19 | The servo-actuated seal structure of a kind of vehicle rudder leading edge |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN108146616A (en) * | 2016-12-02 | 2018-06-12 | 中国航空工业集团公司成都飞机设计研究所 | A kind of rudder face seal structure of all-metal Varying-thickness |
-
2014
- 2014-12-19 CN CN201420815590.9U patent/CN204433037U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108146616A (en) * | 2016-12-02 | 2018-06-12 | 中国航空工业集团公司成都飞机设计研究所 | A kind of rudder face seal structure of all-metal Varying-thickness |
| CN108146616B (en) * | 2016-12-02 | 2020-11-13 | 中国航空工业集团公司成都飞机设计研究所 | All-metal variable-thickness control surface sealing structure |
| 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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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee after: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |
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| CP01 | Change in the name or title of a patent holder |