CN108045556B - Airplane flaperon motion mechanism - Google Patents
Airplane flaperon motion mechanism Download PDFInfo
- Publication number
- CN108045556B CN108045556B CN201711241533.9A CN201711241533A CN108045556B CN 108045556 B CN108045556 B CN 108045556B CN 201711241533 A CN201711241533 A CN 201711241533A CN 108045556 B CN108045556 B CN 108045556B
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- China
- Prior art keywords
- joint
- flap
- control surface
- vertex
- flaperon
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
Abstract
The invention provides an aircraft flaperon movement mechanism, which comprises a control surface, a control surface joint, a linkage joint, a flaperon driving rod, a flaperon auxiliary joint, a wing suspension joint, a flap driving rod and a flap auxiliary joint, wherein the control surface joint, the linkage joint and the wing suspension joint are all triangular components, the control surface is connected with one side edge of the control surface joint, the center of the control surface joint is hinged with a first vertex of the linkage joint, a second vertex of the linkage joint is hinged with a first vertex of the wing suspension joint arranged on the trailing edge of a wing, a third vertex of the linkage joint is hinged with the end part of a flap driving rod sleeved in the flap auxiliary joint, and the opposite vertex of the side edge of the control surface connected with the control surface joint is hinged with the end part of the flaperon driving rod sleeved in the flap auxiliary joint. The mechanism provided by the invention has the advantages of small number of parts, simple and convenient installation, clear motion relation, high reliability and low cost.
Description
Technical Field
The invention belongs to the field of airplane structure design, and particularly relates to an airplane flaperon movement mechanism.
Background
At present, most of the fly flap motion mechanisms of the airplanes adopt a connecting rod driving type, the number of parts is large, the motion relation is complex, and the reliability is relatively low.
Disclosure of Invention
The present invention aims to provide an efficient and compact mechanism for moving an aircraft flaperon, which overcomes or alleviates at least one of the above-mentioned disadvantages of the prior art.
The purpose of the invention is realized by the following technical scheme: the aircraft flaperon motion mechanism comprises a control surface, a control surface joint, a linkage joint, a flaperon drive rod, a flaperon auxiliary joint, a wing suspension joint, a flap drive rod and a flap auxiliary joint, wherein the control surface joint, the linkage joint and the wing suspension joint are all triangular components, the control surface is connected with one side edge of the control surface joint, the center of the control surface joint is hinged with a first vertex D of the linkage joint, a second vertex B of the linkage joint is hinged with a vertex of the wing suspension joint arranged on the trailing edge of a wing, a third vertex A of the linkage joint is hinged with the end part of a flap drive rod sleeved in the flap auxiliary joint, and a vertex C, opposite to the side edge of the control surface, connected with the control surface joint is hinged with the end part of the flaperon drive rod sleeved in the flap auxiliary joint.
Preferably, the flap driving rod moves in the flap auxiliary joint along the axis of the flap driving rod, so that the control surface deflects around the linkage joint second vertex B to realize the Fuller flap function.
Preferably, the aileron drive rod moves along its axis in the aileron tag joint, so that the control surface deflects around the linkage joint first vertex D, thereby realizing an aileron function.
Preferably, the flap driving rod moves in the flap auxiliary joint along the axis of the flap driving rod, so that the control surface deflects around the second vertex B of the linkage joint to realize a fullerene flap function, and then if the control surface needs to pitch, the aileron driving rod can be continuously operated to move in the aileron auxiliary joint along the axis of the aileron driving rod, so that the control surface deflects around the first vertex D of the linkage joint to realize an additional aileron function, thereby realizing a composite function.
Preferably, the flap drive rod is an electric screw; the aileron driving rod is a hydraulic actuating cylinder.
Preferably, the aileron secondary joints, the flap secondary joints are fixed-shaft rotating members with sliding tracks or cardan shaft assemblies with sliding tracks.
Preferably, the flap driving rod and the aileron driving rod are driven and controlled by a computer.
The flap and aileron movement mechanism of the airplane has the advantages that the movement mechanism not only can independently realize the control surface deflection function of the flap and the aileron, but also has the comprehensive functions of the fullerene flap and the aileron, so that a larger lift-drag ratio can be generated, the airplane has good maneuvering characteristics, and the purposes of improving the taking-off and landing performance of the airplane and improving the flexibility of maneuvering are realized.
Drawings
FIG. 1 is a schematic view showing the connection of various parts of the fly wing movement mechanism of the airplane of the present invention;
FIG. 2 is a schematic structural view of an aircraft flaperon motion mechanism of the present invention;
FIG. 3 is a schematic view of the operation of the flap motion mechanism of the present invention for performing a flap function;
FIG. 4 is a schematic view of the operation of the present invention in an aircraft flaperon motion to perform the flaperon function;
FIG. 5 is a schematic view of the operation of the fly wing movement mechanism of the airplane to realize the complex function.
Reference numerals:
the system comprises a control plane 1, a control plane 2, a linkage joint 3, an aileron driving rod 4, an aileron auxiliary joint 5, a wing suspension joint 6, a flap driving rod 7 and a flap auxiliary joint 8.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The flap and aileron movement mechanism of the present invention will be further described in detail with reference to the accompanying drawings.
As shown in figures 1 and 2, the flaperon movement mechanism of the airplane comprises a control surface 1, a control surface joint 2, a linkage joint 3, a flaperon driving rod 4, a flaperon auxiliary joint 5, a wing suspension joint 6, a flap driving rod 7 and a flap auxiliary joint 8, wherein the control surface joint 2, the linkage joint 3 and the wing suspension joint 6 are all triangular components, the control surface 1 is connected with one side of the control surface joint 2, the center of the control surface joint 2 is hinged with a first vertex D of the linkage joint 3, the second vertex B of the linkage joint 3 is hinged with one vertex of a wing suspension joint 6 arranged on the trailing edge of the wing, the third vertex A of the linkage joint 3 is hinged with the end part of a flap driving rod 7 sleeved in a flap auxiliary joint 8, the opposite vertex C of the side edge of the control surface 1 connected with the control surface joint 2 is hinged with the end part of an aileron driving rod 4 sleeved in an aileron auxiliary joint 5. The auxiliary joints of the ailerons and the flaps can respectively rotate around the fixed rotating shafts of the ailerons and the flaps, and the suspension joint of the wings 6 is a fixed structure of the trailing edge of the wings.
Wherein, the driving rod explains that: the flap driving rod 7 is an electric screw rod or a similar telescopic mechanical rod; the aileron drive rods 4 are hydraulic rams or similar form of telescopic mechanical rods. Description of auxiliary joints: the auxiliary joint is used as an auxiliary device of a flap and aileron driving rod, and can be a fixed shaft rotating part with a sliding track or a universal shaft assembly with a sliding track according to the specific airfoil motion requirement. Description of drive form: the power control of the flap driving rod 7 and the aileron driving rod 4 can be computer control, and the computer control of the deflection of the control surface can be realized by designing the actuation proportional relation of the two driving rods according to a specific control law. Description of the joints: A. the B, C, D four-point rotary joint can be designed as a joint bearing according to design requirements. Description of the arrangement on an aircraft airfoil: a set of the motion component is arranged at the root of the control surface 1, and a plurality of suspension assemblies are arranged at other positions of the airfoil along the spanwise direction according to requirements to be matched with the overall motion; or a set of the motion components is respectively arranged at the root and the tip of the wing, but a linkage rod is needed to realize the coordinated motion of the two components.
The invention relates to a motion process which can be realized by a flap motion mechanism of an airplane.
Flap function: the flap driving rod 7 moves in the flap auxiliary joint 8 along the axis of the flap driving rod, so that the control surface 1 deflects around the second vertex B of the linkage joint 3, and the Fuller flap function is realized, as shown in figure 3.
Aileron function: the aileron function is achieved by the aileron drive rod 4 moving along its axis in the aileron tag 5, causing the control surface 1 to deflect around the first vertex D of the linkage joint 3, see fig. 4.
And (3) complex functions: the flap driving rod 7 moves in the flap auxiliary joint 8 along the axis of the flap driving rod, so that the control surface 1 deflects around the second vertex B of the linkage joint 3 to realize the Fuller flap function, and then if the control surface 1 needs pitching, the aileron driving rod 4 can be continuously operated to move in the aileron auxiliary joint 5 along the axis of the flap driving rod 1, so that the control surface 1 deflects around the first vertex D of the linkage joint 3 to realize the additional aileron function, and further realize the composite function, which is shown in figure 5.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (6)
1. A flap and aileron movement mechanism of an airplane is characterized by comprising a control surface (1), a control surface joint (2), a linkage joint (3), an aileron driving rod (4), an aileron auxiliary joint (5), a wing suspension joint (6), a flap driving rod (7) and a flap auxiliary joint (8), wherein the control surface joint (2), the linkage joint (3) and the wing suspension joint (6) are triangular members, the control surface (1) is connected with one side of the control surface joint (2), the center of the control surface joint (2) is hinged with a first vertex D of the linkage joint (3), a second vertex B of the linkage joint (3) is hinged with one vertex of the wing suspension joint (6) arranged on the trailing edge of a wing, a third vertex A of the linkage joint (3) is hinged with the end part of the flap driving rod (7) sleeved in the flap auxiliary joint (8), the vertex C opposite to the side edge of the control surface (1) connected with the control surface joint (2) is hinged with the end part of an aileron driving rod (4) sleeved in an aileron auxiliary joint (5);
the auxiliary aileron joint (5) and the auxiliary flap joint (8) are fixed-shaft rotating parts with sliding tracks or universal shaft assemblies with sliding tracks.
2. The aircraft flaperon kinematics according to claim 1, characterized in that the flap drive lever (7) moves along its own axis in the flap auxiliary joint (8) so that the control surface (1) is deflected about the linkage joint (3) second vertex B, implementing a fuller flap function.
3. The aircraft flaperon kinematic mechanism according to claim 1, characterized in that the flaperon driving rod (4) moves along its own axis in the flaperon auxiliary joint (5) so that the control surface (1) is deflected around the linkage joint (3) first vertex D, achieving a flaperon function.
4. The aircraft flaperon kinematic according to claim 1, characterized in that the flap drive rod (7) moves along its own axis in the flap auxiliary joint (8) so that the control surface (1) is deflected around the linkage joint (3) second vertex B, realizing a fuller flap function, and the flap drive rod (4) is further manipulated to move along its own axis in the flap auxiliary joint (5) so that the control surface (1) is deflected around the linkage joint (3) first vertex D, realizing an additional flap function, thus realizing a composite function.
5. The aircraft flaperon kinematic mechanism according to claim 1, characterized in that the flap drive lever (7) is an electric screw; the aileron driving rod (4) is a hydraulic actuating cylinder.
6. The aircraft flaperon movement mechanism according to claim 1, characterized in that the flap drive lever (7), the flaperon drive lever (4) are driven and controlled by a computer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711241533.9A CN108045556B (en) | 2017-11-30 | 2017-11-30 | Airplane flaperon motion mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711241533.9A CN108045556B (en) | 2017-11-30 | 2017-11-30 | Airplane flaperon motion mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108045556A CN108045556A (en) | 2018-05-18 |
| CN108045556B true CN108045556B (en) | 2021-05-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711241533.9A Active CN108045556B (en) | 2017-11-30 | 2017-11-30 | Airplane flaperon motion mechanism |
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| Country | Link |
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| CN (1) | CN108045556B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606638B (en) * | 2018-11-07 | 2022-05-27 | 中国航空工业集团公司西安飞机设计研究所 | Sunken hinge type flap rocker arm supporting structure |
| CN113562162B (en) * | 2021-08-07 | 2023-12-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for using wing trailing edge flap for improving pitching characteristic of large incidence angle of aircraft |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1535785A (en) * | 1976-03-04 | 1978-12-13 | Hawker Siddeley Aviation Ltd | Wing leading edge flaps |
| DE3175717D1 (en) * | 1981-12-16 | 1987-01-29 | Boeing Co | Flap assembly aircraft wing |
| GB8915487D0 (en) * | 1989-07-06 | 1989-08-23 | Short Brothers Plc | A flap assembly |
| US7338018B2 (en) * | 2005-02-04 | 2008-03-04 | The Boeing Company | Systems and methods for controlling aircraft flaps and spoilers |
| DE102006036464B4 (en) * | 2006-08-04 | 2009-08-20 | Airbus Deutschland Gmbh | High-lift system for an aircraft |
| CN102040002A (en) * | 2010-12-02 | 2011-05-04 | 北京航空航天大学 | Curve slide-connecting rod mechanism in high lift device of large aircraft |
| US9856014B2 (en) * | 2015-12-03 | 2018-01-02 | The Boeing Company | Aircraft wing fairing drive assembly, system, and method |
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2017
- 2017-11-30 CN CN201711241533.9A patent/CN108045556B/en active Active
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| Publication number | Publication date |
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| CN108045556A (en) | 2018-05-18 |
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