CN108045556A - A kind of aircraft flaperon motion - Google Patents
A kind of aircraft flaperon motion Download PDFInfo
- Publication number
- CN108045556A CN108045556A CN201711241533.9A CN201711241533A CN108045556A CN 108045556 A CN108045556 A CN 108045556A CN 201711241533 A CN201711241533 A CN 201711241533A CN 108045556 A CN108045556 A CN 108045556A
- Authority
- CN
- China
- Prior art keywords
- joint
- aileron
- rudder face
- drive rod
- wing flap
- 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.)
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Classifications
-
- 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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
- Toys (AREA)
Abstract
The present invention provides a kind of aircraft flaperon motion, including rudder face, rudder face connector, linkage joint, aileron drive rod, aileron auxiliary joint, wing suspension joint, wing flap drive rod, wing flap auxiliary joint, wherein rudder face connector, linkage joint and wing suspension joint are triangular member, rudder face is connected with rudder face connector a side, it is hinged at the rudder face connector center with the first vertex of linkage joint, second apex of linkage joint is hinged with one vertex of wing suspension joint being arranged on trailing edge, the 3rd apex of linkage joint is hinged with the wing flap driving boom end being sleeved in wing flap auxiliary joint, the opposite apex in side that rudder face is connected in rudder face connector is hinged with the aileron driving boom end being sleeved in aileron auxiliary joint.Mechanism provided by the present invention, number of parts is few, installation is simple and direct, and movement relation is clear, and reliability is high, at low cost.
Description
Technical field
The invention belongs to field of airplane structure, and in particular to a kind of aircraft flaperon motion.
Background technology
Aircraft flaperon motion majority is using connecting rod drive-type at present, and number of parts is more, movement relation is complicated,
Reliability is relatively low.
The content of the invention
It is an object of the invention to provide a kind of efficient, succinct aircraft flaperon motions, overcome or alleviated by existing
At least one drawbacks described above of technology.
The purpose of the present invention is achieved through the following technical solutions：A kind of aircraft flaperon motion, including rudder face, rudder face
Connector, linkage joint, aileron drive rod, aileron auxiliary joint, wing suspension joint, wing flap drive rod, wing flap auxiliary joint,
Centered rudder plane tie, linkage joint and wing suspension joint are triangular member, and rudder face is connected with rudder face connector a side,
It is hinged at the rudder face connector center with the first vertex of linkage joint D, with being arranged at wing at the B of second vertex of linkage joint
One vertex of wing suspension joint on trailing edge is hinged, with being sleeved in wing flap auxiliary joint at the 3rd vertex A of the linkage joint
Wing flap driving boom end be hinged, be connected in rudder face connector at the opposite vertex C in side of rudder face and to be sleeved on aileron auxiliary
Aileron driving boom end in adjuvant grafting head is hinged.
Preferably, the wing flap drive rod is moved along own axes in the wing flap auxiliary joint so that the rudder
Face is deflected around the second vertex of linkage joint B, realizes Fowler flap function.
Preferably, the aileron drive rod is moved along own axes in the aileron auxiliary joint so that the rudder
Face is deflected around the first vertex of linkage joint D, realizes aileron function.
Preferably, the wing flap drive rod is moved along own axes in the wing flap auxiliary joint so that the rudder
Face is deflected around the second vertex of linkage joint B, realizes Fowler flap function, can if the rudder face has the needs of pitching afterwards
Continue to manipulate the aileron drive rod and be moved along own axes in the aileron auxiliary joint so that the rudder face is around described
Dynamic the first vertex of connector D deflections, realize additional aileron function, so as to fulfill complex function.
Preferably, the wing flap drive rod is electric screw leading screw；The aileron drive rod is hydraulic actuator.
Preferably, the aileron auxiliary joint, the wing flap auxiliary joint are the fixed-axis rotation part with sliding rail
Or it is the universal shaft assembly with sliding rail.
Preferably, the wing flap drive rod, the aileron drive rod by computer drives and control.
A kind of advantageous effect of aircraft flaperon motion provided by the present invention is that the motion can not only
The control surface deflection function of the flap, aileron is implemented separately, and has both the comprehensive function of Fowler flap, aileron, so as to generate compared with
Big lift resistance ratio, and make aircraft that there are good maneuvering characteristics, realize the flexibility that improvement takeoff and landing performance, promotion manipulate
Purpose.
Description of the drawings
Fig. 1 is the connection relationship diagram of each component of aircraft flaperon motion of the present invention；
Fig. 2 is the structure diagram of aircraft flaperon motion of the present invention；
Fig. 3 is operation chart when aircraft flaperon motion of the present invention realizes wing flap function；
Fig. 4 is operation chart when aircraft flaperon motion of the present invention realizes aileron function；
Fig. 5 is operation chart when aircraft flaperon motion of the present invention realizes complex function.
Reference numeral：
1- rudder faces, 2- rudder faces connector, 3- linkage joints, 4- ailerons drive rod, 5- ailerons auxiliary joint, the suspension of 6- wings connect
Head, 7- wing flaps drive rod, 8- wing flap auxiliary joints.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.
The aircraft flaperon motion of the present invention is described in further details below in conjunction with the accompanying drawings.
As depicted in figs. 1 and 2, a kind of aircraft flaperon motion, including rudder face 1, rudder face connector 2, linkage joint 3,
Aileron drive rod 4, aileron auxiliary joint 5, wing suspension joint 6, wing flap drive rod 7, wing flap auxiliary joint 8, wherein rudder face connect
First 2, linkage joint 3 and wing suspension joint 6 are triangular member, and rudder face 1 is connected with 2 a side of rudder face connector,
It is hinged at 2 center of rudder face connector with 3 first vertex D of linkage joint, with being arranged at machine at 3 second vertex B of the linkage joint
6 one vertex of wing suspension joint on wing trailing edge is hinged, and is connect at the 3rd vertex A of the linkage joint 3 with being sleeved on wing flap auxiliary
7 end of wing flap drive rod in first 8 is hinged, and is connected in rudder face connector 2 at the opposite vertex C in side of rudder face 1 and suit
4 end of aileron drive rod in aileron auxiliary joint 5 is hinged.Wherein, 5. aileron auxiliary joints and 8. wing flap auxiliary joints
It can be rotated rotating around the fixed rotating shaft of itself, 6 wing suspension joints are the fixed structure of trailing edge.
Wherein it should be noted that drive rod explanation：Wing flap drive rod 7 is the flexible of electric screw leading screw or similar type
Mechanical shaft；Aileron drive rod 4 is hydraulic actuator or the flexible mechanical shaft of similar type.Auxiliary joint explanation：Auxiliary joint is made
Can be the fixed-axis rotation with sliding rail by specific aerofoil movement needs for wing flap, the auxiliary device of aileron drive rod
Part or the universal shaft assembly with sliding rail.The explanation of drive form：Wing flap drive rod 7, aileron drive rod 4
Dynamic Control can be that computer controls, and pass through the start proportionate relationship of specific two drive rods of design of control law, you can real
Existing computer control control surface deflection.The explanation in joint：A, the cradle head of 4 points of B, C, D may be designed as joint according to the design needs
Bearing.The explanation arranged on plane airfoil：Arrange a set of this moving link in the wing root of rudder face 1, extend to aerofoil other
Several suspension assembly cooperation mass motions are arranged in position as needed；Or slightly respectively arrange this set of moving link in wing root, the wing,
But there need to be the coordinated movement of various economic factors that interlocking bar realizes the two.
The motion process that aircraft flaperon motion of the present invention can be realized below.
Wing flap function：It is moved by wing flap drive rod 7 along own axes in wing flap auxiliary joint 8 so that rudder face 1 is around connection
The 3 second vertex B deflections of dynamic connector, realize Fowler flap function, as shown in Figure 3.
Aileron function：It is moved by aileron drive rod 4 along own axes in aileron auxiliary joint 5 so that rudder face 1 is around connection
The 3 first vertex D deflections of dynamic connector, realize aileron function, as shown in Figure 4.
Complex function：It is moved by wing flap drive rod 7 along own axes in wing flap auxiliary joint 8 so that rudder face 1 is around connection
The 3 second vertex B deflections of dynamic connector, realize Fowler flap function, if rudder face 1 has the needs of pitching afterwards, can continue to manipulate aileron
Drive rod 4 is moved along own axes in aileron auxiliary joint 5 so that rudder face 1 is deflected around 3 first vertex D of linkage joint, is realized
Additional aileron function, so as to fulfill complex function, as shown in Figure 5.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, all should by the change or replacement that can be readily occurred in
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (7)
1. a kind of aircraft flaperon motion, which is characterized in that including rudder face (1), rudder face connector (2), linkage joint (3),
Aileron drive rod (4), aileron auxiliary joint (5), wing suspension joint (6), wing flap drive rod (7), wing flap auxiliary joint (8),
Wherein rudder face connector (2), linkage joint (3) and wing suspension joint (6) are triangular member, and rudder face (1) connects with rudder face
Head (2) a side is connected, and is hinged at rudder face connector (2) center with (3) first vertex D of linkage joint, which connects
It is hinged at (3) second vertex B of head with (6) one vertex of wing suspension joint being arranged on trailing edge, the linkage joint (3)
It is hinged at 3rd vertex A with wing flap drive rod (7) end being sleeved in wing flap auxiliary joint (8), in rudder face connector (2) even
It is connected to aileron drive rod (4) end phase with being sleeved in aileron auxiliary joint (5) at the opposite vertex C in side of rudder face (1)
It is hinged.
2. aircraft flaperon motion according to claim 1, which is characterized in that the wing flap drive rod (7) is along certainly
Body axis move in the wing flap auxiliary joint (8) so that the rudder face (1) is inclined around (3) the second vertex B of linkage joint
Turn, realize Fowler flap function.
3. aircraft flaperon motion according to claim 1, which is characterized in that the aileron drive rod (4) is along certainly
Body axis move in the aileron auxiliary joint (5) so that the rudder face (1) is inclined around (3) the first vertex D of linkage joint
Turn, realize aileron function.
4. aircraft flaperon motion according to claim 1, which is characterized in that the wing flap drive rod (7) is along certainly
Body axis move in the wing flap auxiliary joint (8) so that the rudder face (1) is inclined around (3) the second vertex B of linkage joint
Turn, realize Fowler flap function, the rudder face (1) can continue to manipulate the aileron drive rod (4) if there are the needs of pitching afterwards
It is moved along own axes in the aileron auxiliary joint (5) so that the rudder face (1) is pushed up around the linkage joint (3) first
Point D is deflected, and additional aileron function is realized, so as to fulfill complex function.
5. aircraft flaperon motion according to claim 1, which is characterized in that the wing flap drive rod (7) is electricity
Dynamic screw；The aileron drive rod (4) is hydraulic actuator.
6. aircraft flaperon motion according to claim 1, which is characterized in that the aileron auxiliary joint (5), institute
State wing flap auxiliary joint (8) for sliding rail fixed-axis rotation part or be the universal shaft assembly with sliding rail.
7. aircraft flaperon motion according to claim 1, which is characterized in that the wing flap drive rod (7), described
Aileron drive rod (4) is by computer drives and controls.
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 true CN108045556A (en) | 2018-05-18 |
| CN108045556B CN108045556B (en) | 2021-05-25 |
Family
ID=62121920
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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108045556B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606638A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of sinking hinge type wing flap rocker supporting structure |
| CN113562162A (en) * | 2021-08-07 | 2021-10-29 | 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 flaperon for improving large attack angle pitching characteristic of airplane |
Citations (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 |
| EP0081610B1 (en) * | 1981-12-16 | 1986-12-17 | The Boeing Company | Flap assembly aircraft wing |
| EP0407159B1 (en) * | 1989-07-06 | 1994-10-12 | Short Brothers Plc | A flap assembly |
| CN101115655A (en) * | 2005-02-04 | 2008-01-30 | 波音公司 | Systems and methods for controlling aircraft flaps and spoilers |
| CN101506050A (en) * | 2006-08-04 | 2009-08-12 | 空中客车德国有限公司 | 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 |
| CN106828880A (en) * | 2015-12-03 | 2017-06-13 | 波音公司 | Aircraft wing radome fairing drive component, system and method |
-
2017
- 2017-11-30 CN CN201711241533.9A patent/CN108045556B/en active Active
Patent Citations (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 |
| EP0081610B1 (en) * | 1981-12-16 | 1986-12-17 | The Boeing Company | Flap assembly aircraft wing |
| EP0407159B1 (en) * | 1989-07-06 | 1994-10-12 | Short Brothers Plc | A flap assembly |
| CN101115655A (en) * | 2005-02-04 | 2008-01-30 | 波音公司 | Systems and methods for controlling aircraft flaps and spoilers |
| CN101506050A (en) * | 2006-08-04 | 2009-08-12 | 空中客车德国有限公司 | 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 |
| CN106828880A (en) * | 2015-12-03 | 2017-06-13 | 波音公司 | Aircraft wing radome fairing drive component, system and method |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606638A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of sinking hinge type wing flap rocker supporting structure |
| CN113562162A (en) * | 2021-08-07 | 2021-10-29 | 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 flaperon for improving large attack angle pitching characteristic of airplane |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108045556B (en) | 2021-05-25 |
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