CN113830288A - Control mechanism for control surface of ducted aircraft - Google Patents
Control mechanism for control surface of ducted aircraft Download PDFInfo
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- CN113830288A CN113830288A CN202111319911.7A CN202111319911A CN113830288A CN 113830288 A CN113830288 A CN 113830288A CN 202111319911 A CN202111319911 A CN 202111319911A CN 113830288 A CN113830288 A CN 113830288A
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- control surface
- steering engine
- auxiliary
- main control
- sleeve
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- 230000007246 mechanism Effects 0.000 title claims abstract description 22
- 230000002093 peripheral effect Effects 0.000 claims description 14
- 230000005540 biological transmission Effects 0.000 claims description 4
- 238000009434 installation Methods 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Classifications
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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
- B64C9/04—Adjustable control surfaces or members, e.g. rudders with compound dependent movements
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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
- B64C9/06—Adjustable control surfaces or members, e.g. rudders with two or more independent movements
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Control Devices (AREA)
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Abstract
The invention discloses a control surface control mechanism of a ducted aircraft, which comprises a steering engine mounting bracket positioned in the center; the steering engine mounting bracket is provided with four mounting positions which are adjacent and spaced by 90 degrees in the horizontal direction; four groups of control surface mounting brackets are respectively arranged on four mounting positions of the steering engine mounting bracket; four groups of control surfaces are respectively arranged on the four groups of control surface mounting brackets; the control surface comprises a first auxiliary control surface, a main control surface and a second auxiliary control surface; the main control surface is driven by a steering engine, and the first auxiliary control surface and the second auxiliary control surface are linked with the main control surface. When the control surface control mechanism works, the main control surface rotates around the installation axis of the main control surface under the driving of the steering engine, and the two auxiliary control surfaces perform similar rotary motion along with the main control surface under the action of the corresponding connecting rods; the four groups of control units can independently operate, so that the real-time control of the posture of the ducted aircraft is realized, and the ducted aircraft is safe, reliable, simple in structure, convenient to install, low in manufacturing cost, long in service life and convenient for civil use and commercial use.
Description
Technical Field
The invention relates to the field of ducted aircrafts, in particular to a control surface control mechanism of a ducted aircraft.
Background
With the rapid development of air traffic, the design technology of the aircraft is mature, and various aircraft layout forms are proposed at present. The ducted aircraft is one of typical layout forms, and the flight state is not stable enough because the ducted aircraft does not have wings capable of adjusting the attitude. Therefore, in order to control the air attitude of the ducted aircraft, various forms of control surface control mechanisms have been proposed.
The control surface control mechanism commonly used at present adopts a flexible hinge to connect and control the control surface, and the system is complex, short in service life and low in control efficiency, is difficult to be suitable for the ducted aircraft needing to work for a long time, and is more difficult to be used for the ducted aircraft needing accurate control.
Therefore, there is a need for a control surface control mechanism with simple structure, light weight, easy assembly, low manufacturing cost, long service life and high reliability, which is convenient for civil and commercial ducted aircraft application.
Disclosure of Invention
The invention aims to provide a control surface control mechanism of a ducted aircraft, which is simple, reliable, long in service life, low in manufacturing cost and convenient for civil and commercial use.
In order to solve the technical problems, the invention adopts the following technical scheme:
the invention relates to a control mechanism of a ducted aircraft control surface, which comprises
A steering engine mounting bracket positioned in the center; the steering engine mounting bracket is provided with four mounting positions which are adjacent and spaced by 90 degrees in the horizontal direction;
four groups of control surface mounting brackets are respectively arranged on four mounting positions of the steering engine mounting bracket;
four groups of control surfaces are respectively arranged on the four groups of control surface mounting brackets; the control surface comprises a first auxiliary control surface, a main control surface and a second auxiliary control surface; the main control surface is driven by a steering engine, and the first auxiliary control surface and the second auxiliary control surface are linked with the main control surface.
Further, the control surface mounting bracket comprises a central frame, a mounting joint and a peripheral frame; the steering engine mounting support is arranged on the steering engine mounting support, the central frame is arranged on the mounting position of the steering engine mounting support, the peripheral frame is fixed on the central frame through a mounting joint, the peripheral frame is opposite to the central frame, and the control surface is located between the peripheral frame and the central frame.
Still further, the first auxiliary control surface and the second auxiliary control surface are respectively located on two sides of the main control surface.
Still further, the first auxiliary control surface is in transmission with the main control surface through a first connecting rod.
Still further, the first link comprises a first link body, a first sleeve, a first ball head, a second sleeve and a second ball head; the two ends of the first connecting rod main body are connected with the first bulb and the second bulb through the first sleeve and the second sleeve respectively, and the first bulb and the second bulb are fixed on the first auxiliary control surface and the main control surface respectively.
Still further, the second auxiliary control surface is in transmission with the main control surface through a second connecting rod.
Still further, the second connecting rod comprises a second connecting rod main body, a third sleeve, a third ball head, a fourth sleeve and a fourth ball head; and two ends of the second connecting rod main body are respectively connected with a third bulb and a fourth bulb through a third sleeve and a fourth sleeve, and the third bulb and the fourth bulb are respectively fixed on the second auxiliary control surface and the main control surface.
Compared with the prior art, the invention has the following beneficial technical effects:
the control mechanism of the control surface of the ducted aircraft comprises four groups of control units, wherein each group of control unit comprises three control surfaces; when the control surface control mechanism works, the main control surface rotates around the installation axis of the main control surface under the driving of the steering engine, and the two auxiliary control surfaces perform similar rotary motion along with the main control surface under the action of the corresponding connecting rods; the four groups of control units can independently operate, so that the real-time control of the posture of the ducted aircraft is realized.
The control mechanism of the control surface of the ducted aircraft, which is composed of the four groups of control units, is safe and reliable, simple in structure, convenient to install, low in manufacturing cost, long in service life and convenient for civil use and commercial use.
Drawings
The invention is further illustrated in the following description with reference to the drawings.
FIG. 1 is a schematic structural diagram of one embodiment of a ducted aircraft control surface mechanism of the present invention;
description of reference numerals: 1. a steering engine mounting bracket;
2. a control surface mounting bracket; 21. a center frame; 22. installing a connector; 23. a perimeter frame;
3. a control surface; 31. a first secondary rudder surface; 32. a main control surface; 33. a second auxiliary control surface;
4. a first link; 41. a first link body; 42. a first sleeve; 43. a first ball head; 44. a second sleeve; 45. a second ball head;
5. a second link; 51. a second link body; 52. a third sleeve; 53. a third ball head; 54. a fourth sleeve; 55. and a fourth ball head.
Detailed Description
The invention is further described with reference to the following figures and detailed description.
As shown in fig. 1, the present invention provides one specific embodiment of a ducted aircraft control surface control mechanism, which includes a central steering engine mounting bracket 1, where the steering engine mounting bracket 1 has four mounting positions that are adjacent to each other at intervals of 90 ° in a horizontal direction, that is, the four mounting positions are uniformly distributed over 360 °. Each mounting location is provided with a set of control surface mounting brackets 2, and the control surface mounting brackets 2 comprise a central frame 21, mounting joints 22 and a peripheral frame 23. The central frame 21 is fixedly arranged on the mounting position of the steering engine mounting bracket 2, the peripheral frame 23 is fixed on the central frame 21 through a mounting joint 22, and the peripheral frame 23 is opposite to the central frame 21, so that a space is formed between the peripheral frame 23 and the central frame 21. The control surface 3 is swingably mounted between the perimeter frame 23 and the center frame 21, the control surface 3 comprising a first secondary control surface 31, a main control surface 32 and a second secondary control surface 33. The first auxiliary control surface 31, the main control surface 32 and the second auxiliary control surface 33 are all installed between the peripheral frame 23 and the central frame 21 through rotating shafts, and the rotating shafts of the first auxiliary control surface, the main control surface and the second auxiliary control surface are as close to the aerodynamic center of the control surfaces as possible so as to reduce the working strength of the steering engine. The main control surface 32 is driven by a steering engine, the first auxiliary control surface 31 and the second auxiliary control surface 33 are respectively located on two sides of the main control surface 32, the first auxiliary control surface 31 is linked with the main control surface 32 through the first connecting rod 4, and the second auxiliary control surface 33 is linked with the main control surface 32 through the second connecting rod 5.
The first link 4 includes a first link body 41, a first sleeve 42, a first ball 43, a second sleeve 44, and a second ball 45. The two ends of the first connecting rod body 41 are respectively connected with a first bulb 43 and a second bulb 45 through a first sleeve 42 and a second sleeve 44, the first bulb 43 and the second bulb 45 are respectively fixed on the first auxiliary control surface 31 and the main control surface 32 to form the hinge joint of the first connecting rod body 41 and the first auxiliary control surface with the main control surface, and when the main control surface swings, the first auxiliary control surface also swings synchronously.
The second link 5 comprises a second link main body 51, a third sleeve 52, a third ball 53, a fourth sleeve 54 and a fourth ball 55; the two ends of the second connecting rod main body 51 are respectively connected with a third ball head 53 and a fourth ball head 55 through a third sleeve 52 and a fourth sleeve 54, the third ball head 53 and the fourth ball head 55 are respectively fixed on the second auxiliary control surface 33 and the main control surface 32 to form the hinge joint of the second connecting rod main body 51 and the second auxiliary control surface with the main control surface, and when the main control surface swings, the second auxiliary control surface also swings synchronously.
When the position of the control surface needs to be adjusted, the main control surface 32 is driven by the steering engine to rotate around the axis of the installation rotating shaft, and the first auxiliary control surface 31 and the second auxiliary control surface 32 rotate around the axis of the installation rotating shaft through the connection of the first connecting rod 4 and the second connecting rod 5, so that the combined motion of a group of control surface units is realized; the attitude control of the ducted aircraft can be realized by coordinating the control of the four control surface units.
In this embodiment, the control surface mounting bracket is composed of a central bracket, a mounting joint and a peripheral frame, and has a simple structure, is convenient to mount, and is not limited to this, and other structures may be adopted.
The above-described embodiments are merely illustrative of the preferred embodiments of the present invention, and do not limit the scope of the present invention, and various modifications and improvements of the technical solutions of the present invention can be made by those skilled in the art without departing from the spirit of the present invention, and the technical solutions of the present invention are within the scope of the present invention defined by the claims.
Claims (7)
1. The utility model provides a duct aircraft rudder face control mechanism which characterized in that: comprises that
A steering engine mounting bracket (1) positioned in the center; the steering engine mounting bracket (1) is provided with four mounting positions which are adjacent and spaced by 90 degrees in the horizontal direction;
four groups of control surface mounting brackets (2) respectively arranged on four mounting positions of the steering engine mounting bracket (1);
four groups of control surfaces (3) which are respectively arranged on the four groups of control surface mounting brackets (2); the control surface (3) comprises a first auxiliary control surface (31), a main control surface (32) and a second auxiliary control surface (33); the main control surface (32) is driven by a steering engine, and the first auxiliary control surface (31) and the second auxiliary control surface (33) are linked with the main control surface (32).
2. The ducted aircraft control surface control mechanism according to claim 1, characterized in that: the control surface mounting bracket (2) comprises a central frame (21), a mounting joint (22) and a peripheral frame (23); the steering engine is characterized in that the central frame (21) is arranged on a mounting position of the steering engine mounting bracket (2), the peripheral frame (23) is fixed on the central frame (21) through a mounting joint (22), the peripheral frame (23) is opposite to the central frame (21), and the control surface (3) is positioned between the peripheral frame (23) and the central frame (21).
3. The ducted aircraft control surface control mechanism in accordance with claim 2, wherein: the first auxiliary control surface (31) and the second auxiliary control surface (33) are respectively positioned on two sides of the main control surface (32).
4. The ducted aircraft control surface control mechanism in accordance with claim 3, wherein: the first auxiliary control surface (31) is in transmission with the main control surface (32) through a first connecting rod (4).
5. The ducted aircraft control surface control mechanism in accordance with claim 4, wherein: the first connecting rod (4) comprises a first connecting rod main body (41), a first sleeve (42), a first ball head (43), a second sleeve (44) and a second ball head (45); two ends of the first connecting rod main body (41) are respectively connected with a first bulb (43) and a second bulb (45) through a first sleeve (42) and a second sleeve (44), and the first bulb (43) and the second bulb (45) are respectively fixed on the first auxiliary control surface (31) and the main control surface (32).
6. The ducted aircraft control surface control mechanism in accordance with claim 3, wherein: the second auxiliary control surface (33) is in transmission with the main control surface (32) through a second connecting rod (5).
7. The ducted aircraft control surface control mechanism in accordance with claim 6, wherein: the second connecting rod (5) comprises a second connecting rod main body (51), a third sleeve (52), a third ball head (53), a fourth sleeve (54) and a fourth ball head (55); two ends of the second connecting rod main body (51) are respectively connected with a third ball head (53) and a fourth ball head (55) through a third sleeve (52) and a fourth sleeve (54), and the third ball head (53) and the fourth ball head (55) are respectively fixed on the second auxiliary control surface (33) and the main control surface (32).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111319911.7A CN113830288B (en) | 2021-11-09 | 2021-11-09 | Control surface control mechanism of ducted aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111319911.7A CN113830288B (en) | 2021-11-09 | 2021-11-09 | Control surface control mechanism of ducted aircraft |
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| Publication Number | Publication Date |
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| CN113830288A true CN113830288A (en) | 2021-12-24 |
| CN113830288B CN113830288B (en) | 2024-06-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111319911.7A Active CN113830288B (en) | 2021-11-09 | 2021-11-09 | Control surface control mechanism of ducted aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114194384A (en) * | 2022-01-05 | 2022-03-18 | 河北福莱卡航空科技有限公司 | Duct type aircraft |
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| US20030136873A1 (en) * | 2000-10-03 | 2003-07-24 | Churchman Charles Gilpin | V/STOL biplane aircraft |
| CN202711065U (en) * | 2012-07-30 | 2013-01-30 | 北京理工大学 | Ducted fan unmanned plane |
| ITTO20130084U1 (en) * | 2013-05-28 | 2014-11-29 | Selex Es Spa | VTOL AIRCRAFT WITH INTUBATED MINI AND MICRO UAV CLASSES |
| CN204236766U (en) * | 2014-11-27 | 2015-04-01 | 哈尔滨盛世特种飞行器有限公司 | The novel control vane of culvert type list rotor unmanned aircraft |
| CN105000180A (en) * | 2015-06-28 | 2015-10-28 | 杨盛 | Aircraft aerodynamic configuration device |
| CN106828908A (en) * | 2017-01-24 | 2017-06-13 | 北京电子工程总体研究所 | A kind of electronic single shaft shrouded propeller aircraft |
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2021
- 2021-11-09 CN CN202111319911.7A patent/CN113830288B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030136873A1 (en) * | 2000-10-03 | 2003-07-24 | Churchman Charles Gilpin | V/STOL biplane aircraft |
| CN202711065U (en) * | 2012-07-30 | 2013-01-30 | 北京理工大学 | Ducted fan unmanned plane |
| ITTO20130084U1 (en) * | 2013-05-28 | 2014-11-29 | Selex Es Spa | VTOL AIRCRAFT WITH INTUBATED MINI AND MICRO UAV CLASSES |
| CN204236766U (en) * | 2014-11-27 | 2015-04-01 | 哈尔滨盛世特种飞行器有限公司 | The novel control vane of culvert type list rotor unmanned aircraft |
| CN105000180A (en) * | 2015-06-28 | 2015-10-28 | 杨盛 | Aircraft aerodynamic configuration device |
| CN106828908A (en) * | 2017-01-24 | 2017-06-13 | 北京电子工程总体研究所 | A kind of electronic single shaft shrouded propeller aircraft |
| CN106927031A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114194384A (en) * | 2022-01-05 | 2022-03-18 | 河北福莱卡航空科技有限公司 | Duct type aircraft |
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| CN113830288B (en) | 2024-06-18 |
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