CN108674633A - Rudder plane controlling mechanism and model plane - Google Patents
Rudder plane controlling mechanism and model plane Download PDFInfo
- Publication number
- CN108674633A CN108674633A CN201810824199.8A CN201810824199A CN108674633A CN 108674633 A CN108674633 A CN 108674633A CN 201810824199 A CN201810824199 A CN 201810824199A CN 108674633 A CN108674633 A CN 108674633A
- Authority
- CN
- China
- Prior art keywords
- rudder
- linear actuator
- controlling mechanism
- mounting structure
- rudder face
- 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
- B64C9/08—Adjustable control surfaces or members, e.g. rudders bodily displaceable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of rudder plane controlling mechanisms comprising wing body, rudder face and linear actuator；Rudder face is hinged in wing body, and linear actuator can extend and shorten along length direction；The first end of linear actuator is directly connected with the first mounting structure of wing body, and the second end of linear actuator is directly movably connect with the second mounting structure of rudder face or the second end of linear actuator is movably connect by first connecting rod with the second mounting structure；Wherein, linear actuator is used to drive rudder face to rotate relative to wing body when length changes.The rudder plane controlling mechanism cathetus driver directly drives rudder face or only drives rudder face by a connecting rod, and the hinge gap of entire mechanism is small, and linear actuator drives the error of motion of rudder small, and the control accuracy of rudder face is high.Invention additionally discloses a kind of model plane, apply above-mentioned rudder plane controlling mechanism, and rudder face control accuracy is high.
Description
Technical field
The present invention relates to model plane technical fields to further relate to a kind of application more specifically to a kind of rudder plane controlling mechanism
The model plane of above-mentioned rudder plane controlling mechanism.
Background technology
Model plane are a kind of recyclable models for imitating aviation or spacecraft shape fabricating, are for sporting a kind of not manned
Aircraft.With the development of science and technology, model plane are widely used in the production and living of people.
The rudder face of model plane is the primary operational face of model plane, is specifically mounted on wing body (including wing, horizontal tail in model plane
The wing, vertical tail) rear at small fin or small aerofoil, the state of flight for controlling model plane.As aileron is peace in rudder face
The movable aerofoil of a fritter on the outside of the wingtip rear of wing, manipulates for model plane roll；Wing flap is mounted in wing
The movable aerofoil of a fritter on the inside of wing root rear makes model plane obtain different lift resistance ratios for changing wing curvature；Rudder is
The aerofoil movable mounted on a fritter of vertical tail rear, for controlling model plane course；Elevator is mounted in water in rudder face
The movable aerofoil of horizontal tail wing rear, the pitch attitude for controlling model plane.
In existing model plane, rudder face is movably mounted in wing body, and actuator drives motion of rudder by link mechanism, but
It is that link mechanism includes at least two connecting rods, there is hinge gap between each connecting rod, cumulative movement error is big, leads to rudder face control
Precision reduces.
Therefore, the control accuracy for how improving rudder face in model plane is those skilled in the art's urgent problem to be solved.
Invention content
In view of this, the present invention provides a kind of rudder plane controlling mechanism, linear actuator directly drives rudder face or only passes through
A piece connecting rod drives rudder face, and the hinge gap of entire mechanism is small, and linear actuator drives the error of motion of rudder small, the control of rudder face
Precision height processed.The present invention also provides a kind of model plane, apply above-mentioned rudder plane controlling mechanism, and rudder face control accuracy is high.
To achieve the above object, the present invention provides the following technical solutions：
A kind of rudder plane controlling mechanism, including：
Wing body；
The rudder face being hinged in the wing body；
Linear actuator, the linear actuator can extend and shorten along length direction；The linear actuator
First end be directly connected with the first mounting structure of the wing body, the second end of the linear actuator directly with the rudder face
The second mounting structure movably connect, or movably connect with second mounting structure by first connecting rod；
Wherein, the linear actuator when length changes for driving the rudder face to turn relative to the wing body
It is dynamic.
Preferably, in above-mentioned rudder plane controlling mechanism, the first end of the linear actuator is cut with scissors with first mounting structure
It connects；The second end of the linear actuator is hinged with second mounting structure.
Preferably, in above-mentioned rudder plane controlling mechanism, first mounting structure is the holder being fixed in the wing body, institute
It is the hinge being fixed on the rudder face to state the second mounting structure.
Preferably, in above-mentioned rudder plane controlling mechanism, the first end of the linear actuator is solid with first mounting structure
Fixed connection；The second end of the linear actuator is movably connect by first connecting rod with second mounting structure.
Preferably, in above-mentioned rudder plane controlling mechanism, the second end of one end of the first connecting rod and the linear actuator
Hinged, the other end is hinged with second mounting structure.
Preferably, in above-mentioned rudder plane controlling mechanism, the linear actuator includes shell and push rod, and the push rod can be stretched
Contracting ground is arranged in the shell.
Preferably, in above-mentioned rudder plane controlling mechanism, the wing body is wing, and the rudder face is aileron.
A kind of model plane, including rudder plane controlling mechanism, the rudder plane controlling mechanism are any one of above-mentioned technical proposal institute
The rudder plane controlling mechanism stated.
The present invention provides a kind of rudder plane controlling mechanism comprising wing body, rudder face and linear actuator；Rudder face is hinged on wing body
On, linear actuator can extend and shorten along length direction；The first end of linear actuator directly with wing body first
Mounting structure is connected, and the second end of linear actuator is directly movably connect with the second mounting structure of rudder face or straight line drives
The second end of dynamic device is movably connect by first connecting rod with the second mounting structure；Wherein, linear actuator is used for from height
Driving rudder face is rotated relative to wing body when degree variation.
In rudder plane controlling mechanism provided by the invention, the driving force of linear actuator directly acts on the second installation of rudder face
Structure, or above-mentioned second mounting structure is only acted on by first connecting rod, middle actuator passes through connecting rod compared with the prior art
Mechanism drives the mode of rudder face, and multiple structures being hinged and connected are eliminated between linear actuator and rudder face, reduce the two
Between hinge gap, kinematic error of the rudder face under linear actuator driving effect is small, and the control accuracy of rudder face is high.
The present invention also provides a kind of model plane, apply above-mentioned rudder plane controlling mechanism, and rudder face control accuracy is high.
Description of the drawings
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technology description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
Obtain other attached drawings according to these attached drawings.
Fig. 1 is the structural schematic diagram of model plane provided in an embodiment of the present invention；
Fig. 2 is the structural schematic diagram of rudder plane controlling mechanism provided in an embodiment of the present invention；
Structural schematic diagram when Fig. 3 is another state of rudder plane controlling mechanism shown in Fig. 2；
Fig. 4 is the structural schematic diagram of another rudder plane controlling mechanism provided in an embodiment of the present invention；
Structural schematic diagram when Fig. 5 is another state of rudder plane controlling mechanism shown in Fig. 4；
Wherein, in Fig. 1-Fig. 5：
Fuselage 1；Wing 2；Aileron 3；Linear actuator 4；Holder 5；Hinge 6；First connecting rod 7.
Specific implementation mode
The embodiment of the invention discloses a kind of rudder plane controlling mechanism, linear actuator 4 directly drives rudder face or only passes through
A piece connecting rod drives rudder face, and the hinge gap of entire mechanism is small, and linear actuator 4 drives the error of motion of rudder small, rudder face
Control accuracy is high.The embodiment of the invention also discloses a kind of model plane, apply above-mentioned rudder plane controlling mechanism, rudder face control accuracy
It is high.
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
- Fig. 5 is please referred to Fig.1, the embodiment of the present invention provides a kind of rudder plane controlling mechanism comprising wing body, rudder face and straight line
Driver 4；Rudder face is hinged in wing body, and linear actuator 4 can extend and shorten along length direction；Linear actuator 4
First end be directly connected with the first mounting structure of wing body, the second end of linear actuator 4 directly with the second installation of rudder face
Structure movably connects or the second end of linear actuator 4 is movably connect by first connecting rod 7 with the second mounting structure；
Wherein, linear actuator 4 is used to drive rudder face to rotate relative to wing body when length changes.
In rudder plane controlling mechanism provided in an embodiment of the present invention, the driving force of linear actuator 4 directly acts on rudder face
Second mounting structure, or above-mentioned second mounting structure is only acted on by first connecting rod 7, compared with the prior art in actuator
In such a way that link mechanism drives rudder face, multiple structures being hinged and connected are eliminated between linear actuator 4 and rudder face, are reduced
Hinge gap between the two, keeps kinematic error of the rudder face under 4 driving effect of linear actuator small, the control accuracy of rudder face
It is high.
First mounting structure may be configured as a part for wing body, may also be configured to be fixed on the equal components of holder 5 in wing body,
Second mounting structure may be configured as a part for rudder face, may also be configured to be fixed on the equal components of hinge 6 on rudder face, the present embodiment
The concrete structure of first mounting structure and the second mounting structure is not limited.
Specifically, in the rudder plane controlling mechanism that as above embodiment provides, the first end of linear actuator 4 is tied with the first installation
Structure is hinged；The second end of linear actuator 4 is hinged with the second mounting structure.In the present solution, linear actuator 4 respectively with first and
Second mounting structure is hinged, simple in structure, easy to assembly.
Further, in the rudder plane controlling mechanism that above-described embodiment provides, the first mounting structure is to be fixed in wing body
Holder 5, the second mounting structure are the hinge 6 being fixed on rudder face.
Certainly, in rudder plane controlling mechanism as above, linear actuator 4 may also be configured to first end and be fixed with the first mounting structure
Connection, second end are movably connect by first connecting rod 7 with the second mounting structure.
Specifically, the second end of one end of first connecting rod 7 and linear actuator 4 is hinged, the other end of first connecting rod 7 and the
Two mounting structures are hinged.Above-mentioned first mounting structure is a part for wing body, and the second installing mechanism is the hinge being fixed on rudder face
Chain 6.
In rudder plane controlling mechanism provided in this embodiment, linear actuator 4 is fixedly connected with wing body, has both ensured that the two is reliable
Connection, and linear actuator 4 is avoided to influence the flight attitudes of model plane because relative motion occurs with wing body.
In the rudder plane controlling mechanism that above-described embodiment provides, linear actuator 4 includes shell and push rod, and push rod can stretch
Ground is arranged inside the shell.Linear actuator 4 is set as the existing linear actuator 4 with self-locking function, push rod energy when powering off
The extension elongation of enough lockings when power is off, to still keep the posture of rudder face when power is off, in addition, the control of linear actuator 4
Precision is high, and easy for installation flexible, occupies little space.The first end of linear actuator 4 is to stretch out direction phase with push rod on shell
The end deviated from, second end are the overhanging end of push rod.Linear actuator is specifically configured to public application No. is 201710570338.4
The number of opening is the linear actuator that the Chinese patent of CN107127749A provides.
Below using wing body as wing 2, rudder face is that aileron 3 is specifically introduced：
1. please referring to Fig.1-Fig. 3, wing 2 is fixed on the fuselage 1 of model plane, and aileron 3 is hinged on wing 2；It is solid on wing 2
Surely there is holder 5, hinge 6 is fixed on aileron 3；The first end of linear actuator 4 is hinged on holder 5, and the of linear actuator 4
Two ends are hinged on hinge 6；Linear actuator 4 is located at the lower section of wing 2, and mould is navigated when being in state of flight in lower section, on wing 2
Towards the side on ground.
In aileron 3 and 2 keeping parallelism of wing, the push rod of linear actuator 4 is in overhanging state, as shown in Figure 2；Straight line
Aileron 3 can be driven to be rotated around wing 2 downwards after the push rod retraction of driver 4, form state as shown in Figure 3.
2. please referring to Fig. 4-5, hinge 6 is fixed on aileron 3；The first end of linear actuator 4 is fixed on wing 2, directly
The second end of line drive 4 is hinged with one end of first connecting rod 7, and the other end and hinge 6 of first connecting rod 7 are hinged；Linear drives
Device 4 is located at the lower section of wing 2, and mould is navigated when being in state of flight in lower section, towards the side on ground on wing 2.
In aileron 3 and 2 keeping parallelism of wing, the push rod of linear actuator 4 is in overhanging state, and the extension of push rod
Direction with the angle of the extending direction of first connecting rod 7 is 180 ° or 180 ° approximate；It can be driven after the push rod retraction of linear actuator 4
Dynamic aileron 3 is rotated around wing 2 downwards, and the angle of push rod and first connecting rod 7 reduces, as shown in Figure 5.
Above-described embodiment is provided in rudder plane controlling mechanism, and rudder face may also be configured to wing flap, and corresponding wing body is wing 2；Rudder
Face may also be configured to rudder, and corresponding wing body is vertical tail；Rudder face may also be configured to elevator, and corresponding wing body is level
Empennage.The present embodiment does not limit the type of rudder face, and user can be specifically arranged as needed.
Rudder plane controlling mechanism provided in this embodiment is simple in structure, flexible for installation, and manufacture easy to produce.
The embodiment of the present invention also provides a kind of model plane, including rudder plane controlling mechanism, and wherein rudder plane controlling mechanism is above-mentioned reality
The rudder plane controlling mechanism of example offer is provided.
Model plane provided in this embodiment apply the rudder plane controlling mechanism of above-described embodiment offer, have rudder face control accuracy
High feature.Certainly, the other effects for the rudder plane controlling mechanism that model plane provided in this embodiment are also provided with above-described embodiment,
Details are not described herein.
Each embodiment is described by the way of progressive in this specification, the highlights of each of the examples are with other
The difference of embodiment, just to refer each other for identical similar portion between each embodiment.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest range caused.
Claims (8)
1. a kind of rudder plane controlling mechanism, which is characterized in that including：
Wing body；
The rudder face being hinged in the wing body；
Linear actuator, the linear actuator can extend and shorten along length direction；The of the linear actuator
One end is directly connected with the first mounting structure of the wing body, the second end of the linear actuator directly with the rudder face
Two mounting structures movably connect, or are movably connect with second mounting structure by first connecting rod；
Wherein, the linear actuator when length changes for driving the rudder face to be rotated relative to the wing body.
2. rudder plane controlling mechanism according to claim 1, which is characterized in that the first end of the linear actuator with it is described
First mounting structure is hinged；The second end of the linear actuator is hinged with second mounting structure.
3. rudder plane controlling mechanism according to claim 2, which is characterized in that first mounting structure is described to be fixed on
Holder in wing body, second mounting structure are the hinge being fixed on the rudder face.
4. rudder plane controlling mechanism according to claim 1, which is characterized in that the first end of the linear actuator with it is described
First mounting structure is fixedly connected；The second end of the linear actuator is movable by first connecting rod and second mounting structure
Ground connects.
5. rudder plane controlling mechanism according to claim 4, which is characterized in that one end of the first connecting rod and the straight line
The second end of driver is hinged, and the other end is hinged with second mounting structure.
6. rudder plane controlling mechanism according to claim 1, which is characterized in that the linear actuator includes shell and pushes away
Bar, the push rod can be telescopically arranged in the shell.
7. rudder plane controlling mechanism according to claim 1, which is characterized in that the wing body is wing, and the rudder face is pair
The wing.
8. a kind of model plane, including rudder plane controlling mechanism, which is characterized in that the rudder plane controlling mechanism is that claim 1-7 is arbitrary
Rudder plane controlling mechanism described in one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810824199.8A CN108674633A (en) | 2018-07-25 | 2018-07-25 | Rudder plane controlling mechanism and model plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810824199.8A CN108674633A (en) | 2018-07-25 | 2018-07-25 | Rudder plane controlling mechanism and model plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108674633A true CN108674633A (en) | 2018-10-19 |
Family
ID=63815885
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810824199.8A Pending CN108674633A (en) | 2018-07-25 | 2018-07-25 | Rudder plane controlling mechanism and model plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108674633A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110888459A (en) * | 2019-12-02 | 2020-03-17 | 中国空气动力研究与发展中心 | Vertical wind tunnel tail spin test model movable control surface deflection control mechanism |
| CN112607000A (en) * | 2020-12-23 | 2021-04-06 | 武汉量宇智能科技有限公司 | Aircraft control surface control mechanism |
| CN113911330A (en) * | 2021-11-12 | 2022-01-11 | 北京航空航天大学 | Oil moves duct aircraft |
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| CN1636616A (en) * | 2004-12-17 | 2005-07-13 | 蔡东青 | Rudder plane controlling mechanism for miniature remote controlled model airplane |
| US20100327111A1 (en) * | 2009-06-25 | 2010-12-30 | Airbus Operations Limited | Electrical power transmitting telescopic strut |
| CN102239083A (en) * | 2008-12-04 | 2011-11-09 | 空中客车运作有限公司 | Aircraft directional control and stabilizing surface |
| CN204208303U (en) * | 2014-11-27 | 2015-03-18 | 王航 | Wing flap is adopted to improve the aeromodelling airplane of lift-drag ratio |
| CN104875874A (en) * | 2015-06-24 | 2015-09-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane aileron execution mechanism |
| CN208593490U (en) * | 2018-07-25 | 2019-03-12 | 北京因时机器人科技有限公司 | Rudder plane controlling mechanism and model plane |
-
2018
- 2018-07-25 CN CN201810824199.8A patent/CN108674633A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1636616A (en) * | 2004-12-17 | 2005-07-13 | 蔡东青 | Rudder plane controlling mechanism for miniature remote controlled model airplane |
| CN102239083A (en) * | 2008-12-04 | 2011-11-09 | 空中客车运作有限公司 | Aircraft directional control and stabilizing surface |
| US20100327111A1 (en) * | 2009-06-25 | 2010-12-30 | Airbus Operations Limited | Electrical power transmitting telescopic strut |
| CN204208303U (en) * | 2014-11-27 | 2015-03-18 | 王航 | Wing flap is adopted to improve the aeromodelling airplane of lift-drag ratio |
| CN104875874A (en) * | 2015-06-24 | 2015-09-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane aileron execution mechanism |
| CN208593490U (en) * | 2018-07-25 | 2019-03-12 | 北京因时机器人科技有限公司 | Rudder plane controlling mechanism and model plane |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110888459A (en) * | 2019-12-02 | 2020-03-17 | 中国空气动力研究与发展中心 | Vertical wind tunnel tail spin test model movable control surface deflection control mechanism |
| CN112607000A (en) * | 2020-12-23 | 2021-04-06 | 武汉量宇智能科技有限公司 | Aircraft control surface control mechanism |
| CN113911330A (en) * | 2021-11-12 | 2022-01-11 | 北京航空航天大学 | Oil moves duct aircraft |
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