CN220204362U - Can realize connection structure that aircraft movable surface control bolt single face was dismantled - Google Patents
Can realize connection structure that aircraft movable surface control bolt single face was dismantled Download PDFInfo
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- CN220204362U CN220204362U CN202321952534.5U CN202321952534U CN220204362U CN 220204362 U CN220204362 U CN 220204362U CN 202321952534 U CN202321952534 U CN 202321952534U CN 220204362 U CN220204362 U CN 220204362U
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- movable surface
- shaft sleeve
- rib
- mounting hole
- aircraft
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- 238000009434 installation Methods 0.000 claims abstract description 14
- 210000001503 joint Anatomy 0.000 claims description 8
- 238000003032 molecular docking Methods 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 abstract description 3
- 239000000725 suspension Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 210000005069 ears Anatomy 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The application belongs to the field of aircraft movable surface connection structure design, and in particular relates to a connection structure capable of realizing single-sided disassembly of an aircraft movable surface control bolt. Comprising the following steps: the movable surface is provided with a support rib and an end rib, the end rib is positioned at the outer side of the support rib, the support rib is provided with a first mounting hole, and the end rib is provided with a second mounting hole; the control pull rod is provided with a third mounting hole; the shaft sleeve is arranged in the first mounting hole and the second mounting hole, and the butt bolt sequentially penetrates through the shaft sleeve and the third mounting hole from the inner side of the movable surface and is fixed in a matched manner through a nut positioned on the outer side of the control pull rod. The utility model discloses a can realize the transmission of operating system under the limited circumstances in little aircraft movable surface wing section height and space, guarantee the integrality of end rib simultaneously to mounting form is convenient, and operating axis mounted position is adjustable, and the installation accuracy is high, and weight is little, and possesses anti-rotation function, has solved the problem that can't arrange locking cardboard in narrow and small space.
Description
Technical Field
The application belongs to the field of aircraft movable surface connection structure design, and in particular relates to a connection structure capable of realizing single-sided disassembly of an aircraft movable surface control bolt.
Background
The movable surface of the aircraft refers to a movable airfoil surface on the wing or the tail wing of the aircraft, which is controlled by an operating system to move so as to adapt to the current flight environment. Typically, the steering bolts on the aircraft active surface, which are connected to the steering system ties, are mounted on a sufficiently strong binaural steering joint, the ears of which typically protrude from the wing profile and are arranged in the same rib plane as the suspension joints. However, for the movable surface of the small aircraft, because the height of the wing section is low, the rotating shaft is far away from the wing section, the structural space is limited, and in order to avoid overlarge holes on the rear edge of the wing during the movement of the control rod, the control point is sometimes arranged in a narrow space of the root of the wing section. When the binaural steering joint described above is employed in a mobile surface to steering linkage arrangement for a small aircraft, the following problems are faced: the steering joint needs to be designed to be thicker in order to obtain enough rigidity and strength, and meanwhile, the traditional double-lug joint cannot meet the requirements because the butt joint needs to be realized on a chord plane; the design of the steering joint breaks the integrity of the end rib.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The purpose of the application is to provide a connecting structure capable of realizing single-sided disassembly of an aircraft movable surface control bolt, so as to solve at least one problem existing in the prior art.
The technical scheme of the application is as follows:
a connection structure for enabling single-sided disassembly of an aircraft active surface control bolt, comprising:
the movable surface is provided with a support rib and an end rib, the end rib is positioned at the outer side of the support rib, the support rib is provided with a first mounting hole, and the end rib is provided with a second mounting hole;
the control pull rod is provided with a third mounting hole;
the shaft sleeve is installed in the first installation hole and the second installation hole, and the butt bolt penetrates through the shaft sleeve and the third installation hole from the inner side of the movable surface in sequence and is fixed through the nut on the outer side of the control pull rod in a matching mode.
In at least one embodiment of the present application, the sleeve includes a circular tube section and annular sleeve connecting portions located at two ends of the circular tube section, and the two sleeve connecting portions are respectively fixedly connected with the support rib and the web of the end rib.
In at least one embodiment of the present application, two shaft sleeve connecting portions are fixedly connected with the supporting rib and the web plate of the end rib through a plurality of bolts uniformly distributed in the circumferential direction.
In at least one embodiment of the present application, the apertures of the first mounting hole and the second mounting hole are larger than the aperture of the circular tube section of the sleeve.
In at least one embodiment of the present application, the central hole of the boss connection part connected with the support rib is in a hexagonal shape adapted to the head of the docking bolt.
In at least one embodiment of the present application, the tail of the butt bolt rod is provided with a cotter hole, the nut is provided with a pin slot, and the cotter pin is matched to prevent the nut from loosening.
The utility model has at least the following beneficial technical effects:
the utility model provides a can realize connection structure that aircraft movable surface control bolt single face was dismantled can realize the control system transmission under the limited circumstances in little aircraft movable surface wing section height and space, guarantees the integrality of end rib simultaneously to mounting form is convenient, and the operating axis mounted position is adjustable, and the installation accuracy is high, and weight is little, and possesses anti-rotation function, has solved the problem that can't arrange locking cardboard in narrow and small space.
Drawings
FIG. 1 is a schematic illustration of a prior art aircraft active surface steering connection and suspension connection;
fig. 2 is a schematic view of a single-sided detachable connection structure of an aircraft active surface control bolt according to one embodiment of the present application.
Wherein:
1-movable surface; 2-manipulating the pull rod; 3-butting bolts; 4-nuts; 5-shaft sleeve; 6-end ribs; 7-support ribs.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application. Embodiments of the present application are described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of protection of the present application.
The present application is described in further detail below in conjunction with figures 1 to 2.
The application provides a can realize connection structure that aircraft movable surface control bolt single face was dismantled, including axle sleeve 5, docking bolt 3 and nut 4.
Specifically, the movable surface 1 is provided with a support rib 7 and an end rib 6, the end rib 6 is positioned at the outer side of the support rib 7, the support rib 7 is provided with a first mounting hole, and the end rib 6 is provided with a second mounting hole; the control pull rod 2 is provided with a third mounting hole; the shaft sleeve 5 is installed in the first installation hole and the second installation hole, and the butt bolt 3 sequentially penetrates through the shaft sleeve 5 and the third installation hole from the inner side of the movable surface 1 and is matched and fixed through the nut 4 at the outer side of the control pull rod 2.
The utility model provides a can realize connection structure that aircraft movable surface control bolt single face was dismantled, butt joint bolt 3 nestification is inside axle sleeve 5, provides fixed stay for butt joint bolt 3 through axle sleeve 5, and butt joint bolt 3 is worn out from inside to outside from movable surface 1 inside, and the part that exposes is docked with control pull rod 2 to install nut 4 in control pull rod 2 outside, the installation is realized to the preferential cooperation gasket of nut 4.
In the preferred embodiment of the present application, the sleeve 5 comprises a central circular tube section and annular sleeve connecting portions at both ends of the circular tube section, the two sleeve connecting portions being fixedly connected with the support rib 7 and the web of the end rib 6, respectively. In this embodiment, the two shaft sleeve connecting portions are respectively attached to the webs of the support rib 7 and the end rib 6, and are fixedly connected by a plurality of bolts uniformly distributed in the circumferential direction, so that the concentrated load transmitted by the butt bolts 3 is diffused to the webs of the two ribs. The shaft sleeve 5 has a certain width, and two ends of the shaft sleeve are supported by the supporting ribs 7 and the end ribs 6, so that the strength and rigidity requirements of the control butt joint part can be met under the condition of minimum weight.
Advantageously, in this embodiment, the apertures of the first mounting hole and the second mounting hole are larger than the aperture of the circular tube section of the shaft sleeve 5, and fine adjustment of the position of the steering axis can be achieved by adjusting the mounting position of the shaft sleeve 5, so as to ensure the mounting accuracy of the steering point.
Advantageously, in this embodiment, the docking bolt 3 is pre-embedded inside the sleeve 5, and the docking bolt 3 is required to customize the thread length according to the length of the circular tube portion of the sleeve 5 and the operating lever 2. The central hole of the shaft sleeve connecting part connected with the supporting rib 7 on the shaft sleeve 5 is hexagonal in shape matched with the head of the butt bolt 3, so that the butt bolt 3 can be prevented from rotating, and the problem that an anti-loosening clamping plate cannot be arranged in a narrow space is solved.
Advantageously, in this embodiment, the tail of the butt bolt rod 3 is provided with a cotter hole, the nut 4 is provided with a pin slot, and the nut 4 is prevented from loosening by matching with the cotter pin.
The connecting structure capable of realizing single-sided disassembly of the airplane movable surface control bolt can realize the transmission of the control system under the condition that the height and the space of the wing profile of the small airplane movable surface are limited, and simultaneously ensure the integrity of the end rib 6; the end ribs and the supporting ribs are adopted, and the shaft sleeve is convenient to install in a combined mode; the support rib 7 and the holes on the end rib 6 are larger than the aperture of the shaft sleeve 5, and the fine adjustment of the position of the steering shaft line can be realized by adjusting the installation position of the shaft sleeve 5, so that the installation precision of the steering point is ensured; the shaft sleeve 5 has a certain width, and two ends of the shaft sleeve are supported by the end ribs 6 and the supporting ribs 7, so that the strength and rigidity requirements of the control butt joint part can be met under the condition of minimum weight; one end of the shaft sleeve 5 is designed into a hexagonal hole matched with the bolt head, so that the rotation of the bolt can be prevented, and the problem that an anti-loosening clamping plate cannot be arranged in a narrow space is solved.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. Can realize connection structure that aircraft movable surface control bolt single face was dismantled, characterized in that includes:
the movable surface (1), the movable surface (1) is provided with a supporting rib (7) and an end rib (6), the end rib (6) is positioned at the outer side of the supporting rib (7), the supporting rib (7) is provided with a first mounting hole, and the end rib (6) is provided with a second mounting hole;
the control pull rod (2) is provided with a third mounting hole;
the shaft sleeve (5) is installed in the first installation hole and the second installation hole, and the butt bolt (3) sequentially penetrates through the shaft sleeve (5) and the third installation hole from the inner side of the movable surface (1) and is fixed in a matched mode through a nut (4) positioned on the outer side of the control pull rod (2).
2. The connecting structure capable of realizing single-sided disassembly of an aircraft movable surface control bolt according to claim 1, wherein the shaft sleeve (5) comprises a circular pipe section and annular shaft sleeve connecting parts positioned at two ends of the circular pipe section, and the two shaft sleeve connecting parts are respectively fixedly connected with the supporting ribs (7) and webs of the end ribs (6).
3. The connecting structure capable of realizing single-sided disassembly of the aircraft movable surface control bolt according to claim 2, wherein the two shaft sleeve connecting parts are fixedly connected with the web plates of the supporting rib (7) and the end rib (6) through a plurality of bolts uniformly distributed in the circumferential direction.
4. A connection structure enabling single-sided detachment of an aircraft active surface control bolt according to claim 3, characterized in that the apertures of the first and second mounting holes are larger than the aperture of the circular tube section of the sleeve (5).
5. The connection structure for realizing the single-sided detachment of the aircraft active surface control bolt according to claim 2, characterized in that the central hole of the shaft sleeve connection part connected with the support rib (7) is hexagonal in shape adapted to the head of the docking bolt (3).
6. The connecting structure capable of realizing single-sided disassembly of the aircraft movable surface control bolt according to claim 1, wherein the tail part of the butt joint bolt (3) is provided with a split pin hole, the nut (4) is provided with a pin groove, and the nut is prevented from loosening by matching with the split pin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321952534.5U CN220204362U (en) | 2023-07-24 | 2023-07-24 | Can realize connection structure that aircraft movable surface control bolt single face was dismantled |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321952534.5U CN220204362U (en) | 2023-07-24 | 2023-07-24 | Can realize connection structure that aircraft movable surface control bolt single face was dismantled |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220204362U true CN220204362U (en) | 2023-12-19 |
Family
ID=89154604
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321952534.5U Active CN220204362U (en) | 2023-07-24 | 2023-07-24 | Can realize connection structure that aircraft movable surface control bolt single face was dismantled |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220204362U (en) |
-
2023
- 2023-07-24 CN CN202321952534.5U patent/CN220204362U/en active Active
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