CN114104264A - Control surface mounting structure - Google Patents
Control surface mounting structure Download PDFInfo
- Publication number
- CN114104264A CN114104264A CN202111551512.3A CN202111551512A CN114104264A CN 114104264 A CN114104264 A CN 114104264A CN 202111551512 A CN202111551512 A CN 202111551512A CN 114104264 A CN114104264 A CN 114104264A
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- CN
- China
- Prior art keywords
- hole
- control surface
- shaft pin
- stabilizing
- flange plate
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- 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
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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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention relates to a design of a mounting and connecting mode of a movable control surface and a stabilizing surface or a fuselage structure, belonging to the structural design of airplanes. A control surface mounting structure is used for mounting a control surface on a stabilizing surface and comprises a flange plate and a shaft pin; the flange plate is arranged on the control surface and is positioned at the notch of the rotation axis of the control surface, and a hole is formed in the flange plate and is opposite to the hole, positioned at the rotation axis of the control surface, in the stabilizing surface; one end of the shaft pin is inserted into the hole, the other end of the shaft pin is inserted into the hole, and the shaft pin inserted into the hole is fixedly connected with the stabilizing surface through a fastener; when the control surface is arranged between the stabilizing surfaces, the control surface can rotate around the pivot pin, and deflection of the control surface is realized. The invention has the following advantages: the connecting structure is suitable for the airplane control surface, meets the requirement of control surface movement, and has the advantages of small quantity of connecting parts, light structure weight, simplicity and convenience in installation and disassembly and the like.
Description
Technical Field
The invention relates to a design of a mounting and connecting mode of a movable control surface and a stabilizing surface or a fuselage structure, belonging to the structural design of airplanes.
Background
When the movable control surface of the traditional airplane is connected with the stabilizing surface or the airplane body, a support arm, a support seat and other complex connecting structures are required, so that the number of connecting parts is large, the mounting and dismounting forms are complex, and the structural weight of the airplane is increased.
Disclosure of Invention
The invention aims to solve the problems in the prior art, and provides a control surface mounting structure which can realize the mounting of a control surface, is simple, convenient and quick in mounting and dismounting form, has a small number of connecting parts and also lightens the weight of an airplane structure.
In order to achieve the purpose, the invention adopts the following technical scheme: a control surface mounting structure is used for mounting a control surface on a stabilizing surface and comprises a flange plate and a shaft pin; the flange plate is arranged on the control surface and is positioned at the notch of the rotation axis of the control surface, and a hole is formed in the flange plate and is opposite to the hole, positioned at the rotation axis of the control surface, in the stabilizing surface; one end of the shaft pin is inserted into the hole, the other end of the shaft pin is inserted into the hole, and the shaft pin inserted into the hole is fixedly connected with the stabilizing surface through a fastener; when the control surface is arranged between the stabilizing surfaces, the control surface can rotate around the pivot pin, and deflection of the control surface is realized.
Preferably, a bearing is pressed into the hole of the flange plate, and one end of the shaft pin is inserted into the bearing.
Preferably, a through hole is formed in one end, inserted into the hole of the flange, of the shaft pin, the through hole is arranged along the radial direction of the shaft pin, and a split pin is inserted into the through hole and used for limiting the axial movement of the shaft pin along the through hole.
Preferably, the outer diameter of the flange is larger than the inner diameter of the notch of the rotation axis of the control surface, and the flange is installed at the notch through a screw and covers the notch.
Preferably, the stabilizing surface is provided with a hole for inserting a fastener, the hole is communicated with a hole positioned at the rotating axis of the control surface, the axis of the hole is vertical to the axis of the hole, and the fastener is inserted into the hole to fix the shaft pin on the upper end rib and the lower end rib of the stabilizing surface.
Preferably, the fastener is a set screw.
Preferably, the shaft pin is of a stepped structure, the small end of the shaft pin is inserted into the hole of the flange, and the end face of the stepped part is tightly attached to the upper surface of the flange.
The use process comprises the following steps: the two ends of the movable control surface are provided with flanges with bearings, the control surface is pushed between the stabilizing surfaces (machine bodies), the two ends of the stabilizing surfaces (machine bodies) are inserted with shaft pins into the bearing inner rings of the flanges, and the shaft pins are fixed, so that the movable control surface can be connected with the stabilizing surfaces (machine bodies).
Compared with the prior art, the invention has the following advantages: the connecting structure is suitable for the airplane control surface, meets the requirement of control surface movement, and has the advantages of small quantity of connecting parts, light structure weight, simplicity and convenience in installation and disassembly and the like.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a cross-sectional view taken along line C-C of FIG. 1;
FIG. 3 is a schematic view of a control surface structure in an embodiment of the invention;
FIG. 4 is a cross-sectional view A-A (at the rudder surface rotation axis) of FIG. 3;
FIG. 5 is a schematic view of the structure of an upper end rib of the control surface in the embodiment of the invention;
FIG. 6 is a schematic view of a rib structure at the lower end of the control surface in the embodiment of the invention;
FIG. 7 is a schematic structural view of a stabilizer in an embodiment of the present invention;
FIG. 8 is a sectional view taken along line G-G of FIG. 7;
FIG. 9 is a sectional view taken along line F-F of FIG. 7;
FIG. 10 is a schematic view of the upper rib structure of the stabilizing surface in the embodiment of the present invention;
FIG. 11 is a schematic view of a rib structure at the lower end of the stabilizing surface in the embodiment of the present invention;
FIG. 12 is a view showing the mounting structure of a flange and a bearing in the embodiment of the present invention;
FIG. 13 is a schematic view of a pin construction in accordance with an embodiment of the present invention;
in fig. 1-13, 1, a control surface upper end rib; 2. a control surface lower end rib; 3. a control surface; 4. a stabilizing surface upper end rib; 5. a stabilizing surface lower end rib; 6. stabilizing the flour; 7. a flange plate; 8. a screw; 9. tightening the screw; 10. a shaft pin; 11. a cotter pin; 12. a bearing; 13. the control surface axis of rotation.
Detailed Description
It should be noted that, in the present embodiment, the terms "upper", "lower", and the like are described according to the drawings, and do not limit the present invention.
The invention is described in further detail below with reference to the accompanying figures 1-13: a control surface mounting structure is used for mounting a control surface 3 on a stabilizing surface 6 and comprises a flange 7, a shaft pin 10, an opening pin 11 and a bearing 12; the flange 7 is arranged on the control surface 3 through a screw 8, is positioned at a gap of a rotation axis 13 of the control surface, and is provided with a hole which is opposite to a hole of the stabilizing surface 6 positioned at the rotation axis 13 of the control surface; one end of the shaft pin 10 is inserted into the hole, the other end of the shaft pin is inserted into the hole, and the shaft pin inserted into the hole is connected and fixed with the stabilizing surface 6 through a set screw 9; when the control surfaces 3 are mounted between the stabilizing surfaces 6, the control surfaces 3 rotate around the shaft pins 10, achieving deflection of the control surfaces.
In this embodiment, the specific structure is as follows:
as shown in fig. 3-6, the upper and lower edges of the control surface 3 are a control surface upper end rib 1 and an end surface lower end rib 2, the control surface upper end rib 1 and the end surface lower end rib 2 are both symmetrical structures with a chord line as an axis, and the control surface rotation axis 13 of the control surface upper end rib 1 and the end surface lower end rib 2 is a notch.
As shown in fig. 7-11, the edge of the stabilizing surface opposite to the control surface 3 is respectively a stabilizing surface upper end rib 4 and a stabilizing surface lower end face 5, in the mounting structure, the two are arranged oppositely and are symmetrical structures taking a chord line as an axis, a hole for inserting a set screw 9 is arranged on the stabilizing surface, the hole is communicated with a hole positioned at the rotation axis of the control surface and is vertical to the axis, the set screw 9 is inserted into the hole, and a shaft pin 10 is fixed on the stabilizing surface upper end rib 4 and the stabilizing surface lower end rib 5.
As shown in fig. 12, the outer diameter of the flange 7 is larger than the inner diameter of the gap of the control surface, the left and right ends of the flange are mounting lugs, a countersunk hole is formed in the mounting lugs, the flange 7 is mounted at the gap of the control surface through a screw 8 and used for covering the gap, a hole is formed in the center of the flange, the hole coincides with the axis of the hole in the stabilizing surface, and the bearing 12 is pressed into the hole.
As shown in fig. 13, the shaft pin has a stepped structure, the small end of the shaft pin is inserted into the hole of the flange, the end face of the stepped portion is tightly attached to the upper surface of the flange 7, a through hole is formed at one end of the shaft pin 10 inserted into the hole of the flange 7, the through hole is radially arranged along the shaft pin 10, the cotter pin 11 is inserted into the through hole and located below the lower surface of the flange, and the end face of the stepped portion and the cotter pin 11 are used for limiting the axial movement of the shaft pin 10.
The working principle is as follows: as shown in fig. 1-2, when the control surface is installed, a flange 7 pressed with a bearing 12 is installed on the upper end rib 1 and the lower end rib 2 of the control surface at the rotation axis area of the control surface through a bolt 8. The control surfaces are pushed between the stabilizing surfaces, two shaft pins 10 are inserted into inner rings of bearings 12 of a flange 7 at the rotating axis area of the control surfaces by an upper end rib 4 and a lower end rib 5 of the stabilizing surfaces, the shaft pins 10 are fixed on the upper end rib 4 and the lower end rib 5 of the stabilizing surfaces through set screws 9, and meanwhile, split pins are arranged at the holes of the shaft pins 10 at the notches of the rotating axis through the two ends of the control surfaces, so that the installation of the control surfaces is completed. The deflection of the control surface is realized by the rotation of an upper shaft pin 10 and a lower shaft pin 10 which are fixed on the stabilizing surface in the bearing inner ring of the flange 7.
When the control surface is disassembled, the upper set screw 9 and the lower set screw 9 of the stabilizing surface are disassembled, the cotter 11 on the shaft pin 10 is disassembled at the gap of the rotating axis through the two ends of the control surface, and the shaft pin 10 is removed, so that the control surface can be removed.
The above examples are merely preferred embodiments of the present invention and are not to be construed as limiting the invention. Any extensions, variations, equivalents and the like of those skilled in the art without departing from the principle of the present invention shall be included in the scope of the present invention.
Claims (7)
1. The utility model provides a control surface mounting structure for install the control surface on the stabilizer, its characterized in that: the mounting structure comprises a flange plate and a shaft pin; the flange plate is arranged on the control surface and is positioned at the notch of the rotation axis of the control surface, and a hole is formed in the flange plate and is opposite to the hole, positioned at the rotation axis of the control surface, in the stabilizing surface; one end of the shaft pin is inserted into the hole, the other end of the shaft pin is inserted into the hole, and the shaft pin inserted into the hole is fixedly connected with the stabilizing surface through a fastener; when the control surface is arranged between the stabilizing surfaces, the control surface rotates around the pivot pin to realize the deflection of the control surface.
2. Rudder surface mounting structure according to claim 1, characterised in that: a bearing is pressed in the hole of the flange plate, and one end of the shaft pin is inserted into the bearing.
3. Rudder surface mounting structure according to claim 1 or 2, characterised in that: a through hole is formed in one end, inserted into the hole of the flange plate, of the shaft pin, the through hole is arranged along the radial direction of the shaft pin, and a split pin is inserted into the through hole and used for limiting the axial movement of the shaft pin along the shaft pin.
4. Rudder surface mounting structure according to claim 1, characterised in that: the outer diameter of the flange plate is larger than the inner diameter of the notch of the rotating axis of the control surface, and the flange plate is installed at the notch through screws and covers the notch.
5. Rudder surface mounting structure according to claim 1, characterised in that: and a hole for inserting a fastener is formed in the stabilizing surface, the hole is communicated with the hole positioned at the rotating axis of the control surface, the axis of the hole is vertical to the axis of the hole, and the fastener is inserted into the hole to fix the shaft pin on the upper end rib and the lower end rib of the stabilizing surface.
6. Rudder surface mounting structure according to claim 5, characterised in that: the fastener is a set screw.
7. Rudder surface mounting structure according to claim 1, characterised in that: the shaft pin is of a stepped structure, the small end of the shaft pin is inserted into the hole of the flange plate, and the end face of the stepped part is tightly attached to the upper surface of the flange plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111551512.3A CN114104264A (en) | 2021-12-17 | 2021-12-17 | Control surface mounting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111551512.3A CN114104264A (en) | 2021-12-17 | 2021-12-17 | Control surface mounting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114104264A true CN114104264A (en) | 2022-03-01 |
Family
ID=80365862
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111551512.3A Pending CN114104264A (en) | 2021-12-17 | 2021-12-17 | Control surface mounting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114104264A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2564215Y (en) * | 2002-07-31 | 2003-08-06 | 程智斌 | Electric remote-controlled model aircraft |
| CN105235904A (en) * | 2015-10-29 | 2016-01-13 | 北京航天科颐技术有限公司 | Connecting device of drone aircraft and splicing-type drone aircraft |
| US20160376003A1 (en) * | 2015-06-26 | 2016-12-29 | Yuri Feldman | Aircraft |
| CN107264778A (en) * | 2016-04-08 | 2017-10-20 | 陕西飞机工业（集团）有限公司 | A kind of empennage axis of rudder bearing attachment structure |
| CN108082449A (en) * | 2018-03-06 | 2018-05-29 | 中航通飞研究院有限公司 | A kind of large aircraft control surface suspension structure |
| EP3412560A1 (en) * | 2017-06-05 | 2018-12-12 | AeroMobil R&D, s. r. o. | Wing folding |
| CN109080814A (en) * | 2018-09-30 | 2018-12-25 | 西安爱生技术集团公司 | A kind of full-height foam core unmanned plane lifting rudder face shaft installing mechanism |
| CN112173073A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Single steering engine control double-vertical-tail control structure |
-
2021
- 2021-12-17 CN CN202111551512.3A patent/CN114104264A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2564215Y (en) * | 2002-07-31 | 2003-08-06 | 程智斌 | Electric remote-controlled model aircraft |
| US20160376003A1 (en) * | 2015-06-26 | 2016-12-29 | Yuri Feldman | Aircraft |
| CN105235904A (en) * | 2015-10-29 | 2016-01-13 | 北京航天科颐技术有限公司 | Connecting device of drone aircraft and splicing-type drone aircraft |
| CN107264778A (en) * | 2016-04-08 | 2017-10-20 | 陕西飞机工业（集团）有限公司 | A kind of empennage axis of rudder bearing attachment structure |
| EP3412560A1 (en) * | 2017-06-05 | 2018-12-12 | AeroMobil R&D, s. r. o. | Wing folding |
| CN108082449A (en) * | 2018-03-06 | 2018-05-29 | 中航通飞研究院有限公司 | A kind of large aircraft control surface suspension structure |
| CN109080814A (en) * | 2018-09-30 | 2018-12-25 | 西安爱生技术集团公司 | A kind of full-height foam core unmanned plane lifting rudder face shaft installing mechanism |
| CN112173073A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Single steering engine control double-vertical-tail control structure |
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