CN114558329A - Steering control structure of model airplane - Google Patents
Steering control structure of model airplane Download PDFInfo
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- CN114558329A CN114558329A CN202210127463.9A CN202210127463A CN114558329A CN 114558329 A CN114558329 A CN 114558329A CN 202210127463 A CN202210127463 A CN 202210127463A CN 114558329 A CN114558329 A CN 114558329A
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- OKKJLVBELUTLKV-UHFFFAOYSA-N Methanol Chemical compound OC OKKJLVBELUTLKV-UHFFFAOYSA-N 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/02—Model aircraft
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/14—Starting or launching devices for toy aircraft; Arrangements on toy aircraft for starting or launching
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H29/00—Drive mechanisms for toys in general
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Abstract
The invention belongs to the technical field of model airplanes, and particularly relates to a steering control structure of a model airplane, which comprises an airplane main body, a first main wing, a second main wing, a first opening-closing type control surface and a second opening-closing type control surface, wherein the first opening-closing type control surface is rotatably arranged on the first main wing, the second opening-closing type control surface is rotatably arranged on the second main wing, and the airplane steering is realized by changing the opening-closing angle of the first opening-closing type control surface and the second opening-closing type control surface. Compared with the prior art, the invention can realize the steering of the airplane by only controlling the opening and closing angles of the first opening and closing type control surface and the second opening and closing type control surface through the ingenious structural design. The structure is simple, the realization is easy, the blank of airplane steering in the field of model airplane without vertical tail is filled, and the method has great technical value and economic value.
Description
Technical Field
The invention belongs to the technical field of model airplanes, and particularly relates to a steering control structure of a model airplane.
Background
The model airplane generally refers to a model capable of flying in the air, and the model airplane mainly has the following classification methods:
first, the power system can be divided into an unpowered glider, a rubber band powered airplane, an electric airplane, a methanol internal combustion engine airplane, a gasoline internal combustion engine airplane, a turbine shaft powered airplane (helicopter), a turbojet powered airplane (fixed wing) and the like.
And secondly, dividing the models according to the types. Can be divided into fixed-wing aircraft, helicopters, gyroplanes, quadcopters and the like.
Thirdly, divide in a controlled manner. It can be divided into free flight (without remote control), wire control (by pulling wire to control the flight action of fixed wing aircraft), wireless remote control, etc.
Among them, a fixed wing aircraft is a more specific type, which is called a model airplane without vertical tail, and has a great steering difficulty because it has no vertical tail. The steering control of the model airplane without the vertical tail wing in the prior art is complex and cannot realize good steering control.
In view of the above, the present invention is directed to a steering control structure of an airplane model (especially an airplane model without vertical tail), which changes an opening and closing angle through a first opening and closing type control surface and a second opening and closing type control surface by a smart structural design, and when the opening and closing angle is increased by the first opening and closing type control surface and the opening and closing angle is decreased by the second opening and closing type control surface, the airplane generates a leftward deflection moment; when the opening and closing angle of the first opening and closing type control surface is reduced and the opening and closing angle of the second opening and closing type control surface is increased, the airplane can generate rightward deflection torque; thereby realizing the steering of the airplane.
Disclosure of Invention
The invention aims to: aiming at the defects of the prior art, the steering control structure of the model airplane is provided, the opening and closing angle is changed through the first opening and closing type control surface and the second opening and closing type control surface through the ingenious structural design, and when the opening and closing angle is increased by the first opening and closing type control surface and the opening and closing angle is reduced by the second opening and closing type control surface, the airplane can generate leftward deflection moment; when the opening and closing angle of the first opening and closing type control surface is reduced and the opening and closing angle of the second opening and closing type control surface is increased, the airplane can generate rightward deflection torque; thereby realizing the steering of the airplane.
In order to achieve the purpose, the invention adopts the following technical scheme:
the utility model provides a steering control structure of model aeroplane and model ship aircraft, includes aircraft main part, first main wing, second main wing, rotationally set up in first open-close type rudder face on the first main wing and rotationally set up in the second open-close type rudder face on the second main wing, realize the aircraft steering through changing the angle that first open-close type rudder face and second open-close type rudder face opened and shut.
As an improvement of the steering control structure of the model airplane, when the opening and closing angle of the first opening and closing type control surface is increased and the opening and closing angle of the second opening and closing type control surface is reduced, the airplane generates leftward deflection torque; when the opening and closing angle of the first opening and closing type control surface is reduced and the opening and closing angle of the second opening and closing type control surface is increased, the airplane generates rightward deflection moment.
As an improvement of the steering control structure of the model airplane, when the opening and closing angle of the first opening and closing control surface and the second opening and closing control surface is increased, the airplane decelerates.
As an improvement of the steering control structure of the model airplane, the first open-close type control surface is connected with a first server structure which provides a rotating moment through a first pull rod and a second pull rod, the second open-close type control surface is connected with a second server structure which provides a rotating moment through a third pull rod and a fourth pull rod, the first server structure is fixed on the first main wing, and the second server structure is fixed on the second main wing.
As an improvement of the steering control structure of the model airplane, the first server structure and the second server structure each include a server fixing member, a server and a server cover plate, the server is disposed in an accommodating space formed by the server fixing member and the server cover plate, and the server fixing member is fixed on the first main wing or the second main wing.
As an improvement of the steering control structure of the model airplane, the first opening-closing control surface comprises a first control surface and a second control surface, one end of the first pull rod is connected with a first bulb, the other end of the first pull rod is connected with a second bulb, the first bulb is connected with the first server structure, and the second bulb is connected with the second control surface; one end of the second pull rod is connected with a third bulb, the other end of the second pull rod is connected with a fourth bulb, the third bulb is connected with the first server structure, and the fourth bulb is connected with the first control surface; a first rocker arm is further arranged between the first ball head and the third ball head.
As an improvement of the steering control structure of the model airplane, the second opening-closing type control surface comprises a third control surface and a fourth control surface, one end of the third pull rod is connected with a fifth ball head, the other end of the third pull rod is connected with a sixth ball head, the fifth ball head is connected with the second server structure, and the sixth ball head is connected with the fourth control surface; one end of the fourth pull rod is connected with a seventh bulb, the other end of the fourth pull rod is connected with a fifth bulb, the seventh bulb is structurally connected with the second server, and the eighth bulb is connected with the third control surface; a second rocker arm is further arranged between the fifth ball head and the seventh ball head.
As an improvement of the steering control structure of the model airplane, the first control surface is connected with the first main wing through a first fixing piece and can rotate relative to the first main wing, the second control surface is connected with the first main wing through a second fixing piece and can rotate relative to the first main wing.
As an improvement of the steering control structure of the model airplane, the control surface three-way is connected with the second main wing through a third fixing piece, the control surface three-way can rotate relative to the second main wing, the control surface four-way is connected with the second main wing through a fourth fixing piece, and the control surface four-way can rotate relative to the second main wing.
As an improvement of the steering control structure of the model airplane, the first main wing is provided with a first groove and a first cover plate covering the first groove, and the first pull rod, the second pull rod and the first server structure are all arranged in an accommodating space formed by the first groove and the first cover plate;
the second main wing is provided with a second groove and a second cover plate which is covered on the second groove, and the third pull rod, the fourth pull rod and the second server structure are arranged in an accommodating space formed by the second groove and the second cover plate.
Compared with the prior art, the invention changes the opening and closing angle through the first opening and closing type control surface and the second opening and closing type control surface through ingenious structural design, and when the opening and closing angle is increased by the first opening and closing type control surface and is reduced by the second opening and closing type control surface, the airplane can generate leftward deflection moment; when the opening and closing angle of the first opening and closing type control surface is reduced and the opening and closing angle of the second opening and closing type control surface is increased, the airplane can generate rightward deflection torque; thereby realizing the airplane steering. And when the opening and closing angle of the first opening and closing type control surface and the second opening and closing type control surface is increased, the airplane decelerates. In other words, the invention can realize the steering of the airplane by only controlling the opening and closing angles of the first opening and closing type control surface and the second opening and closing type control surface through the ingenious structural design. The structure is simple, the realization is easy, the blank of airplane steering in the field of model airplane without vertical tail is filled, and the method has great technical value and economic value.
Drawings
FIG. 1 is a schematic illustration of the structure of a model airplane without vertical tail incorporating the present invention.
Fig. 2 is one of the structural schematic diagrams (opening cover plate) of the first opening-closing type rudder surface and the first main wing in the invention.
Fig. 3 is an enlarged schematic view of a portion a in fig. 2.
Fig. 4 is a second schematic structural view (opening cover plate) of the first opening/closing type rudder surface and the first main wing according to the present invention.
Fig. 5 is an enlarged schematic view of a portion B in fig. 4.
Fig. 6 is a schematic structural view of the first opening/closing control surface and the first main wing according to the present invention.
Fig. 7 is an exploded view of the first opening/closing control surface and the first main wing according to the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as upper, lower, left, right, front and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
As shown in fig. 1 to 7, the invention provides a steering control structure of an aeromodelling airplane, which comprises an airplane body 1, a first main wing 2, a second main wing 3, a first opening and closing type control surface 4 rotatably arranged on the first main wing 2, and a second opening and closing type control surface 5 rotatably arranged on the second main wing 3, wherein the airplane steering is realized by changing the opening and closing angle of the first opening and closing type control surface 4 and the second opening and closing type control surface 5.
When the opening and closing angle of the first opening and closing type control surface 4 is increased and the opening and closing angle of the second opening and closing type control surface 5 is decreased, the airplane generates leftward deflection moment, because the air flow velocity passing through the first main wing 2 is slow, the air flow velocity passing through the second main wing 3 is fast, and the main wings on the two sides generate different air flow velocities, so the leftward deflection moment is generated; when the first opening and closing type control surface 4 reduces the opening and closing angle and the second opening and closing type control surface 5 increases the opening and closing angle, the airplane generates the rightward deflection moment because the air flow speed passing through the first main wing 2 is high, the air flow speed passing through the second main wing 3 is low, and the main wings on the two sides generate different air flow speeds, so the rightward deflection moment is generated.
When the first opening and closing type control surface 4 and the second opening and closing type control surface 5 both increase the opening and closing angle, the airplane decelerates because the air flow velocity through the main wings on the two sides becomes slow, so that the effect similar to braking is generated, and the airplane decelerates.
The first open-close type control surface 4 is connected with a first server structure 8 providing a rotating moment through a first pull rod 6 and a second pull rod 7, similarly, the second open-close type control surface 5 is connected with a second server structure providing a rotating moment through a third pull rod and a fourth pull rod, the first server structure 8 is fixed on the first main wing 2, and the second server structure is fixed on the second main wing 3. That is to say, the structures for changing the opening and closing angles of the first opening and closing type control surface 4 and the second opening and closing type control surface 5 are identical, and therefore, the related structures of the second opening and closing type control surface 5 are not shown in the invention, and reference can be made to the related structures of the first opening and closing type control surface 4.
The first server structure 8 and the second server structure each include a server fixing member 81, a server 82, and a server cover plate 83, the server 82 is disposed in an accommodating space formed by the server fixing member 81 and the server cover plate 83, and the server fixing member 81 is fixed on the first main wing 2 or the second main wing 3.
The first opening and closing type control surface 4 comprises a first control surface 41 and a second control surface 42, one end of a first pull rod 6 is connected with a first bulb 9, the other end of the first pull rod 6 is connected with a second bulb 10, the first bulb 9 is connected with a first server structure 8, and the second bulb 10 is connected with the second control surface 42; one end of the second pull rod 7 is connected with a third ball head 11, the other end of the second pull rod 7 is connected with a fourth ball head 12, the third ball head 11 is connected with the first server structure 8, and the fourth ball head 12 is connected with the first control surface 41; a first rocker arm 13 is also arranged between the first ball head 9 and the third ball head 11. The first servo structure 8 provides a rotating moment to drive the first rocker arm 13, so as to drive the first ball head 9 and the third ball head 11 to rotate, so that the first pull rod 6 and the second pull rod 7 are pushed, the second ball head 10, the second control surface 42 connected with the second ball head, the fourth ball head 12 and the first control surface 41 connected with the fourth ball head are further driven to move, and the opening and closing actions of the first opening and closing control surface 4 are realized. Specifically, the first servo structure 8 drives the first rocker arm 13 to rotate, when the first rocker arm 13 rotates anticlockwise, the first pull rod 6 and the second pull rod 7 respectively drive the second control surface 42 and the first control surface 41 to be pushed away outwards, so that an included angle between the second control surface 42 and the first control surface 41 is gradually increased, and when the first rocker arm 13 rotates clockwise, the first pull rod 6 and the second pull rod 7 respectively drive the second control surface 42 and the first control surface 41 to be folded inwards, so that the included angle between the second control surface 42 and the first control surface 41 is gradually reduced until the first rocker arm is closed, and accordingly, the first opening-closing type control surface 4 can be freely opened and closed.
Similarly, the second opening-closing type control surface comprises a third control surface and a fourth control surface, one end of a third pull rod is connected with a fifth bulb, the other end of the third pull rod is connected with a sixth bulb, the fifth bulb is structurally connected with a second server, and the sixth bulb is connected with the fourth control surface; one end of a fourth pull rod is connected with a seventh bulb, the other end of the fourth pull rod is connected with a fifth bulb, the seventh bulb is structurally connected with a second server, and an eighth bulb is connected with the third control surface; a second rocker arm is further arranged between the fifth ball head and the seventh ball head.
The first control surface 41 is connected with the first main wing 2 through the first fixing member 14, and the first control surface 41 is rotatable (specifically, hinged structure) relative to the first main wing 2, and the second control surface 42 is connected with the first main wing 2 through the second fixing member 15, and the second control surface 42 is rotatable (specifically, hinged structure) relative to the first main wing 2.
Similarly, the control surface three is connected to the second main wing through the third fixing member, and the control surface three is rotatable relative to the second main wing (specifically, in a hinged structure), the control surface four is connected to the second main wing through the fourth fixing member, and the control surface four is rotatable relative to the second main wing (specifically, in a hinged structure).
The first main wing 2 is provided with a first groove 21 and a first cover plate 22 covering the first groove 21, and the first pull rod 6, the second pull rod 7 and the first server structure 8 are all arranged in an accommodating space formed by the first groove 21 and the first cover plate 22;
similarly, a second groove and a second cover plate covering the second groove are arranged on the second main wing 3, and the third pull rod, the fourth pull rod and the second server structure are all arranged in an accommodating space formed by the second groove and the second cover plate. The arrangement of the first recess 21 and the second recess saves space and also makes the whole aircraft more attractive.
In a word, through ingenious structural design, the opening and closing angle is changed through the first opening and closing type control surface 4 and the second opening and closing type control surface 5, and when the opening and closing angle is increased by the first opening and closing type control surface 4 and the opening and closing angle is reduced by the second opening and closing type control surface 5, the airplane can generate leftward deflection torque; when the opening and closing angle of the first opening and closing type control surface 4 is reduced and the opening and closing angle of the second opening and closing type control surface 5 is increased, the airplane can generate rightward deflection moment; thereby realizing the steering of the airplane. And when the opening and closing angle of the first opening and closing type control surface 4 and the second opening and closing type control surface 5 is increased, the airplane decelerates. In other words, the invention can realize the steering of the airplane by only controlling the opening and closing angles of the first opening and closing type control surface 4 and the second opening and closing type control surface 5 through the ingenious structural design. The structure is simple, the realization is easy, the blank of airplane steering in the field of model airplane without vertical tail is filled, and the method has great technical value and economic value.
Appropriate variations and modifications of the embodiments described above will occur to those skilled in the art, in light of the above disclosure and teachings. Therefore, the present invention is not limited to the specific embodiments disclosed and described above, and some modifications and variations of the present invention should fall within the scope of the claims of the present invention. Furthermore, although specific terms are employed herein, they are used in a generic and descriptive sense only and not for purposes of limitation.
Claims (10)
1. A steering control structure of an aeromodelling airplane is characterized in that: the aircraft comprises an aircraft body, a first main wing, a second main wing, a first opening-closing type control surface and a second opening-closing type control surface, wherein the first opening-closing type control surface is rotatably arranged on the first main wing, the second opening-closing type control surface is rotatably arranged on the second main wing, and the aircraft steering is realized by changing the opening-closing angle of the first opening-closing type control surface and the second opening-closing type control surface.
2. The steering control structure of an aircraft according to claim 1, characterized in that: when the opening and closing angle of the first opening and closing type control surface is increased and the opening and closing angle of the second opening and closing type control surface is reduced, the airplane generates leftward deflection moment; when the opening and closing angle of the first opening and closing type control surface is reduced and the opening and closing angle of the second opening and closing type control surface is increased, the airplane generates rightward deflection moment.
3. The steering control structure of an aircraft according to claim 1, characterized in that: when the opening and closing angle of the first opening and closing type control surface and the second opening and closing type control surface is increased, the airplane decelerates.
4. The steering control structure of an aircraft according to claim 1, characterized in that: the first open-close type control surface is connected with a first server structure for providing a rotating moment through a first pull rod and a second pull rod, the second open-close type control surface is connected with a second server structure for providing a rotating moment through a third pull rod and a fourth pull rod, the first server structure is fixed on the first main wing, and the second server structure is fixed on the second main wing.
5. The steering control structure of an aircraft according to claim 4, characterized in that: the first server structure and the second server structure respectively comprise a server fixing piece, a server and a server cover plate, the server is arranged in an accommodating space formed by the server fixing piece and the server cover plate, and the server fixing piece is fixed on the first main wing or the second main wing.
6. The steering control structure of an aircraft according to claim 5, characterized in that: the first opening-closing type control surface comprises a first control surface and a second control surface, one end of the first pull rod is connected with a first bulb, the other end of the first pull rod is connected with a second bulb, the first bulb is structurally connected with the first server, and the second bulb is connected with the second control surface; one end of the second pull rod is connected with a third bulb, the other end of the second pull rod is connected with a fourth bulb, the third bulb is connected with the first server structure, and the fourth bulb is connected with the first control surface; and a first rocker arm is also arranged between the first ball head and the third ball head.
7. The steering control structure of an aircraft according to claim 5, characterized in that: the second opening-closing type control surface comprises a third control surface and a fourth control surface, one end of a third pull rod is connected with a fifth bulb, the other end of the third pull rod is connected with a sixth bulb, the fifth bulb is structurally connected with the second server, and the sixth bulb is connected with the fourth control surface; one end of the fourth pull rod is connected with a seventh bulb, the other end of the fourth pull rod is connected with a fifth bulb, the seventh bulb is structurally connected with the second server, and the eighth bulb is connected with the third control surface; and a second rocker arm is also arranged between the fifth ball head and the seventh ball head.
8. The steering control structure of an aircraft according to claim 6, characterized in that: the first control surface is connected with the first main wing through a first fixing piece and can rotate relative to the first main wing, the second control surface is connected with the first main wing through a second fixing piece and can rotate relative to the first main wing.
9. The steering control structure of an aircraft according to claim 7, characterized in that: the third control surface is connected with the second main wing through a third fixing piece and can rotate relative to the second main wing, the fourth control surface is connected with the second main wing through a fourth fixing piece and can rotate relative to the second main wing.
10. The steering control structure of the model airplane according to claim 4, wherein: the first main wing is provided with a first groove and a first cover plate covering the first groove, and the first pull rod, the second pull rod and the first server structure are all arranged in an accommodating space formed by the first groove and the first cover plate;
the second main wing is provided with a second groove and a second cover plate which is covered on the second groove, and the third pull rod, the fourth pull rod and the second server structure are arranged in an accommodating space formed by the second groove and the second cover plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210127463.9A CN114558329B (en) | 2022-02-11 | 2022-02-11 | Steering control structure of model airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210127463.9A CN114558329B (en) | 2022-02-11 | 2022-02-11 | Steering control structure of model airplane |
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| Publication Number | Publication Date |
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| CN114558329A true CN114558329A (en) | 2022-05-31 |
| CN114558329B CN114558329B (en) | 2024-06-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210127463.9A Active CN114558329B (en) | 2022-02-11 | 2022-02-11 | Steering control structure of model airplane |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020047068A1 (en) * | 2000-07-26 | 2002-04-25 | Minoru Uchida | Flap operating device |
| US20020061698A1 (en) * | 2000-07-14 | 2002-05-23 | Yu Tian | Remote electro-aeroplane |
| CN2560404Y (en) * | 2002-07-09 | 2003-07-16 | 楼英俊 | Model airplane tail surface capable of automatically resetting rudder |
| CN2619696Y (en) * | 2003-04-07 | 2004-06-09 | 程智斌 | Electric remote-controlled model aircraft |
| CN1623853A (en) * | 2003-12-03 | 2005-06-08 | 田瑜 | Method for controlling tail rudder of model aircraft |
| CN1636616A (en) * | 2004-12-17 | 2005-07-13 | 蔡东青 | Rudder plane controlling mechanism for miniature remote controlled model airplane |
| CN201085932Y (en) * | 2007-09-18 | 2008-07-16 | 深圳市艾特航模有限公司 | Direct drive control plane steering mechanism of miniature motor |
| CN206885333U (en) * | 2017-05-09 | 2018-01-16 | 昊翔电能运动科技(昆山)有限公司 | Wing rudder face action control mechanism |
| CN109334950A (en) * | 2018-10-18 | 2019-02-15 | 珠海展祥模型有限公司 | A kind of fixed wing aircraft |
-
2022
- 2022-02-11 CN CN202210127463.9A patent/CN114558329B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020061698A1 (en) * | 2000-07-14 | 2002-05-23 | Yu Tian | Remote electro-aeroplane |
| US20020047068A1 (en) * | 2000-07-26 | 2002-04-25 | Minoru Uchida | Flap operating device |
| CN2560404Y (en) * | 2002-07-09 | 2003-07-16 | 楼英俊 | Model airplane tail surface capable of automatically resetting rudder |
| CN2619696Y (en) * | 2003-04-07 | 2004-06-09 | 程智斌 | Electric remote-controlled model aircraft |
| CN1623853A (en) * | 2003-12-03 | 2005-06-08 | 田瑜 | Method for controlling tail rudder of model aircraft |
| CN1636616A (en) * | 2004-12-17 | 2005-07-13 | 蔡东青 | Rudder plane controlling mechanism for miniature remote controlled model airplane |
| CN201085932Y (en) * | 2007-09-18 | 2008-07-16 | 深圳市艾特航模有限公司 | Direct drive control plane steering mechanism of miniature motor |
| CN206885333U (en) * | 2017-05-09 | 2018-01-16 | 昊翔电能运动科技(昆山)有限公司 | Wing rudder face action control mechanism |
| CN109334950A (en) * | 2018-10-18 | 2019-02-15 | 珠海展祥模型有限公司 | A kind of fixed wing aircraft |
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| Publication number | Publication date |
|---|---|
| CN114558329B (en) | 2024-06-14 |
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