CN112758306B - Self-tensioning wing rib, wing and skin laying method - Google Patents
Self-tensioning wing rib, wing and skin laying method Download PDFInfo
- Publication number
- CN112758306B CN112758306B CN202110374792.9A CN202110374792A CN112758306B CN 112758306 B CN112758306 B CN 112758306B CN 202110374792 A CN202110374792 A CN 202110374792A CN 112758306 B CN112758306 B CN 112758306B
- Authority
- CN
- China
- Prior art keywords
- rib
- wing
- self
- section
- main body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
A self-tensioning wing rib, a wing and a skin laying method is disclosed, wherein the self-tensioning wing rib comprises a wing rib main body and a plurality of support rods, and the section of the wing rib main body is in an omega shape; the wing rib main body comprises a wing rib upper wing surface and a wing rib lower wing surface, the front end of the wing rib upper wing surface is smoothly connected with the front end of the wing rib lower wing surface, and the rear end of the wing rib upper wing surface is attached to the rear end of the wing rib lower wing surface; the two ends of the stay bar are respectively connected to the wing rib upper wing surface and the wing rib lower wing surface. The self-tensioning rib has the advantages that the section of the rib main body is in the omega shape, the self-tensioning adjusting function is realized when the skin is laid, and the laying quality of the skin can be improved.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a self-tensioning wing rib, a wing and a skin laying method.
Background
The light unmanned aerial vehicle adopts the film covering, and the laying quality of covering influences the aerodynamic performance of unmanned aerial vehicle. The traditional skin laying method is to strain two ends of a film skin and directly bond the film skin on a wing rib, and the skin laying quality is difficult to control by adopting the method. Therefore, it is desirable to design a new rib structure and corresponding skin-laying method to improve skin-laying quality.
Disclosure of Invention
The invention aims to provide a self-tensioning wing rib, a wing and a skin laying method, which can improve the skin laying quality.
In order to achieve the above object, the present invention provides a self-tensioning rib, comprising a rib main body and a plurality of struts, wherein the cross section of the rib main body is omega-shaped;
the wing rib main body comprises a wing rib upper wing surface and a wing rib lower wing surface, the front end of the wing rib upper wing surface is smoothly connected with the front end of the wing rib lower wing surface, and the rear end of the wing rib upper wing surface is attached to the rear end of the wing rib lower wing surface; and two ends of the stay bar are respectively connected to the wing rib upper wing surface and the wing rib lower wing surface.
Preferably, a plurality of the stay bars are sequentially arranged between the rib upper wing surface and the rib lower wing surface, and form a broken line structure.
Preferably, the omega-shaped section of the rib main body comprises a U-shaped section and a pair of flanges, and the pair of flanges are arranged on two sides of the opening end of the U-shaped section;
the omega-shaped section of the rib main body further comprises a reinforcing section, the reinforcing section is in a strip shape, one end of the reinforcing section is connected to the closed end of the U-shaped section, and the other end of the reinforcing section extends towards the direction far away from the U-shaped section.
Preferably, the rib upper airfoil surface and the rib lower airfoil surface are respectively provided with a pair of front beam bonding portions and a pair of rear beam bonding portions, the pair of front beam bonding portions are respectively arranged on the rib upper airfoil surface and the rib lower airfoil surface and are close to the front ends of the rib upper airfoil surface and the rib lower airfoil surface, the pair of rear beam bonding portions are respectively arranged on the rib upper airfoil surface and the rib lower airfoil surface and are close to the rear ends of the rib upper airfoil surface and the rib lower airfoil surface, and the pair of front beam bonding portions and the pair of rear beam bonding portions are respectively connected to the other ends of the reinforcing sections.
Preferably, the front beam bonding part and the rear beam bonding part are both of a plate type structure.
Preferably, the rib body is made of carbon fibre having a thickness of 0.3-1.3 mm.
The invention also provides a wing, which comprises the self-tensioning rib and at least one piece of skin.
Preferably, a plurality of the self-tensioning ribs are arranged in parallel along the length of the wing and are connected with the spars or stringers of the wing.
Preferably, the skin is laid between adjacent self-tensioning ribs and connected to the open end of the omega-section of the rib body.
The invention also provides a method for laying the skin of the wing, which comprises the following steps:
arranging a plurality of said self-tensioning ribs in parallel;
for each self-tensioning rib, disposing a bead of beads within an open end of the omega-shaped cross-section of the rib body, thereby bracing the omega-shaped cross-section of the rib body;
respectively bonding each skin to the opening end of the omega-shaped section of the adjacent rib main body;
inserting a T-shaped pressing block into the opening end of the omega-shaped section of the rib main body, so as to tightly press the bonding part of the skin and the rib main body;
and after the bonding part of the skin and the wing rib main body is completely cured, sequentially taking out the T-shaped pressing block and the beads, and automatically tightening the wing rib main body so as to automatically tighten the skin.
The self-tensioning wing rib has the advantages that the section of the wing rib main body is in the shape of omega, the self-tensioning adjusting function is achieved when the skin is laid, and the laying quality of the skin can be improved.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout.
FIG. 1 shows a schematic structural view of a self-tensioning rib according to one embodiment of the present invention;
FIG. 2 shows another schematic angular structure of a self-tensioning rib according to an embodiment of the present invention;
FIG. 3 shows a schematic cross-sectional view of a rib body of a self-tensioning rib according to an embodiment of the invention;
FIG. 4 shows a schematic cross-sectional view of a rib body and a nose girder bond of a self-tensioning rib according to one embodiment of the invention;
FIG. 5 shows a schematic cross-sectional view of a self-tensioning rib of a wing without a skin laid in accordance with an embodiment of the invention;
FIG. 6 illustrates a schematic cross-sectional view of a beaded hold-off rib body when the skin is not laid for a wing according to one embodiment of the present invention;
FIG. 7 shows a schematic cross-sectional view of a self-tensioning rib as it lays down a skin of a wing according to one embodiment of the invention;
FIG. 8 shows a schematic cross-sectional view of a T-shaped compact of an airfoil as it compresses a skin according to one embodiment of the invention;
FIG. 9 shows a schematic cross-sectional view of a wing after skin laying according to an embodiment of the invention;
figure 10 shows a schematic representation of the structure of a wing after skin laying according to one embodiment of the invention.
Description of reference numerals:
1. the rib structure comprises a rib main body, 11, a rib upper wing surface, 12, a rib lower wing surface, 13, a U-shaped section, 14, a flanging, 15, a reinforcing section, 2, a support rod, 3, a front beam bonding part, 4, a back beam bonding part, 5, a bead string, 6, a T-shaped pressing block, 7 and a skin.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the following describes preferred embodiments of the present invention, it should be understood that the present invention may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
In order to solve the problems in the prior art, the invention provides a self-tensioning wing rib, which comprises a wing rib main body and a plurality of support rods, wherein the cross section of the wing rib main body is in an omega shape;
the wing rib main body comprises a wing rib upper wing surface and a wing rib lower wing surface, the front end of the wing rib upper wing surface is smoothly connected with the front end of the wing rib lower wing surface, and the rear end of the wing rib upper wing surface is attached to the rear end of the wing rib lower wing surface; the two ends of the stay bar are respectively connected to the wing rib upper wing surface and the wing rib lower wing surface.
According to the self-tensioning wing rib provided by the invention, the section of the wing rib main body is in an omega shape, the self-tensioning adjusting function is realized when the skin is laid, and the laying quality of the skin can be improved.
Preferably, a plurality of struts are sequentially arranged between the rib upper airfoil surface and the rib lower airfoil surface, and form a broken line structure. The support rods are used for enhancing the rigidity of the wing rib, the position, the arrangement mode and the number of the wing rib are determined according to actual requirements, and the shape of the wing rib main body is determined by the wing profile of the wing. Optionally, the stay bar can be made of carbon fiber materials, and is bonded with the wing rib main body after being formed independently through a pipe twisting process, so that the production flow is simplified, and the stay bar can be flexibly replaced.
Preferably, the omega-shaped section of the rib main body comprises a U-shaped section and a pair of flanges, and the pair of flanges are arranged on two sides of the opening end of the U-shaped section;
the omega-shaped section of the rib main body further comprises a reinforcing section, the reinforcing section is in a strip shape, one end of the reinforcing section is connected to the closed end of the U-shaped section, and the other end of the reinforcing section extends towards the direction far away from the U-shaped section.
The connection part of the flanging and the U-shaped section is in arc transition connection, namely a round angle is formed between the flanging and the U-shaped section to improve rigidity, the flanging and the U-shaped section form an omega-shaped structure with a closing-in, the open end of the omega-shaped structure is arranged outwards, the structure can provide tension, wherein the closing-in angle and the section height of the omega-shaped section are main variables,
if the closing angle of the omega-shaped section is alpha and the section height is H, the larger the closing angle alpha is and the larger the section height H is, the larger the tension force provided by the wing rib to the film skin is, and conversely, the smaller the closing angle alpha is and the smaller the section height H is, the smaller the tension force provided by the wing rib to the film skin is. According to the tension force required by actual conditions, the closing-in angle alpha and the section height H can be flexibly adjusted, so that the shape of the wing rib is determined.
Preferably, the closing angle alpha of the omega-shaped section of the wing rib main body is 2-15 degrees. The closing angle α of the Ω -shaped cross section of the rib main body when not subjected to the external force is an initial value, and the initial value of the closing angle α may be determined according to the actual situation.
The reinforcing section is of a strip structure and is arranged at the closed end of the U-shaped section, so that the moment of inertia of the section of the rib can be increased, and the rigidity of the rib is increased. The rib body of omega-shaped cross-section can be applied to all airfoils.
Preferably, the reinforcing section comprises a pair of front beam bonding parts and a pair of back beam bonding parts, the pair of front beam bonding parts are respectively arranged on the rib upper wing surface and the rib lower wing surface and are close to the front ends of the rib upper wing surface and the rib lower wing surface, the pair of back beam bonding parts are respectively arranged on the rib upper wing surface and the rib lower wing surface and are close to the back ends of the rib upper wing surface and the rib lower wing surface, and the pair of front beam bonding parts and the pair of back beam bonding parts are respectively connected to the other end of the reinforcing section.
The front and rear spar bonds are used to mount the spars or stringers of the wing, the specific location and shape of which is determined by the overall layout of the aircraft.
Preferably, the front beam bonding part and the rear beam bonding part are both plate-shaped structures. Alternatively, the front beam bonding part and the rear beam bonding part may have a flat plate structure, and the surface of the front beam bonding part and the surface of the rear beam bonding part are connected to the tail end of the reinforcing section, or the front beam bonding part and the rear beam bonding part may be bent to both sides with the tail end of the reinforcing section as a center. The front beam bonding part and the rear beam bonding part are made of carbon fibers and can be integrally formed with the rib main body.
Preferably, the rib body is made of carbon fibre with a thickness of 0.3-1.3mm to reduce the weight of the rib on the basis of meeting the requirements of use.
The invention also provides a wing, which comprises the self-tensioning rib and at least one piece of skin.
Preferably, a plurality of self-tensioning ribs are arranged in parallel along the length of the wing and are connected to the spars or stringers of the wing. The self-tensioning rib is mounted on a spar or stringer of the wing by a front spar bond and a rear spar bond.
Preferably, the skin is laid between adjacent self-tensioning ribs and connected to the open end of the omega-section of the rib body. The covering is arranged on the upper side and the lower side of the self-tensioning wing rib, and is connected to the wing rib main body in a surface leveling mode in a laying and bonding mode.
The invention also provides a method for paving the skin of the wing, which comprises the following steps:
arranging a plurality of self-tensioning ribs in parallel;
for each self-tensioning rib, disposing a bead of beads within the open end of the omega-shaped cross-section of the rib body, thereby distracting the omega-shaped cross-section of the rib body; the beads are of a string structure and are arranged along the circumferential direction of the rib main body so as to completely support the omega-shaped section of the rib main body;
respectively bonding each skin to the opening end of the omega-shaped section of the adjacent rib main body; when the skin is laid and bonded, the surface needs to be kept flat;
inserting the T-shaped pressing block into the opening end of the omega-shaped section of the rib main body, and pressing the bonding part of the skin and the rib main body; the T-shaped pressing block applies pressure to the skin to ensure the bonding strength, the T-shaped pressing block comprises a vertical part and a transverse part, and the vertical part and the transverse part are in transition through a fillet to match a flange of the omega-shaped section of the rib main body with the fillet of the U-shaped section;
and after the bonding part of the skin and the wing rib main body is completely cured, sequentially taking out the T-shaped pressing block and the bead string to automatically tighten the wing rib main body, so that the skin is automatically tensioned.
The self-tensioning wing ribs are arranged on the girders or stringers of the wings in parallel and are fixedly bonded with the girders or stringers through the front girder bonding parts and the rear girder bonding parts.
The beads act to distract the cross-section of the rib body and therefore can be replaced with bendable rods or tubing as desired. After the T-shaped pressing block and the beads are taken out, under the action of the rigidity of the omega-shaped section of the rib main body, the pair of flanges of the omega-shaped section move oppositely and are folded inwards, so that the skin bonded on the adjacent rib main body is stretched, the skin tensioning effect is achieved, and the laying quality of the skin is improved.
Examples
As shown in fig. 1 to 10, the present invention provides a self-tensioning rib, comprising a rib body 1 and a plurality of struts 2, wherein the cross section of the rib body 1 is in an omega shape;
the rib main body 1 comprises a rib upper wing surface 11 and a rib lower wing surface 12, wherein the rib upper wing surface 11 is smoothly connected with the front end of the rib lower wing surface 12, and the rear end of the rib upper wing surface is attached to the rear end of the rib lower wing surface 12; the strut 2 is connected at both ends to a rib upper airfoil surface 11 and a rib lower airfoil surface 12, respectively.
In the present embodiment, a plurality of struts 2 are sequentially disposed between the rib upper wing surface 11 and the rib lower wing surface 12, and form a broken line structure. The stay bar 2 is made of carbon fiber materials, and is bonded with the wing rib main body 1 after being formed independently through a pipe twisting process.
The omega-shaped section of the rib main body 1 comprises a U-shaped section 13 and a pair of flanges 14, and the pair of flanges 14 are arranged on two sides of the opening end of the U-shaped section 13; the omega-shaped section of the rib main body 1 further comprises a reinforcing section 15, the reinforcing section 15 is strip-shaped, one end of the reinforcing section is connected to the closed end of the U-shaped section 13, and the other end of the reinforcing section extends in the direction away from the U-shaped section 13. The connection part of the flanging 14 and the U-shaped section 13 is in circular arc transition connection, namely, a round angle is formed between the flanging 14 and the U-shaped section 13 to improve rigidity, the flanging 14 and the U-shaped section 13 form an omega-shaped structure with a closed end, and the open end of the omega-shaped structure is arranged outwards, so that the structure can provide tension, wherein the closed angle and the section height of the omega-shaped section are main variables, the closed angle of the omega-shaped section is set to be alpha, and the section height is H, when the closed angle alpha is larger and the section height H is larger, the tension provided by the wing rib to the film skin is larger, and conversely, when the closed angle alpha is smaller and the section height H is smaller, the tension provided by the wing rib to the film skin is smaller.
The closing angle alpha of the omega-shaped section of the wing rib main body is 2-15 degrees.
The reinforcing section 15 is of a strip structure and is arranged at the closed end of the U-shaped section 13, so that the moment of inertia of the section of the rib can be increased, and the rigidity of the rib is increased.
The self-tensioning rib further comprises a pair of front beam bonding parts 3 and a pair of rear beam bonding parts 4, the pair of front beam bonding parts 3 are respectively arranged on the rib upper wing surface 11 and the rib lower wing surface 12 and are close to the front ends of the rib upper wing surface 11 and the rib lower wing surface 12, the pair of rear beam bonding parts 4 are respectively arranged on the rib upper wing surface 11 and the rib lower wing surface 12 and are close to the rear ends of the rib upper wing surface 11 and the rib lower wing surface 12, and the pair of front beam bonding parts 3 and the pair of rear beam bonding parts 4 are respectively connected to the other end of the reinforcing section 15. The front spar bond 3 and the rear spar bond 4 are used to mount the spars or stringers of the wing.
The front beam bonding part 3 and the rear beam bonding part 4 are both plate-shaped structures. The front beam bonding part 3 and the rear beam bonding part 4 are of flat plate structures, and the surfaces of the front beam bonding part and the rear beam bonding part are connected to the tail ends of the reinforcing sections 15. The front beam bonding portion 3 and the rear beam bonding portion 4 are made of carbon fiber and are integrally formed with the rib main body 1. The rib body 1 is made of carbon fiber having a thickness of 0.3-1.3 mm.
The invention also provides a wing comprising the self-tensioning rib and at least one skin 7.
In this embodiment, a plurality of self-tensioning ribs are arranged in parallel along the length of the wing and are connected to the spars or stringers of the wing. The self-tensioning rib is mounted on the spar or stringer of the wing by a front spar bond 3 and a rear spar bond 4.
The skin 7 is laid between adjacent self-tensioning ribs and is connected to the open end of the omega-shaped section of the rib body 1. The skins 7 are arranged on the upper side and the lower side of the self-tensioning rib, and are connected to the rib main body 1 in a surface-flattening manner in a laying and bonding manner.
The invention also provides a method for paving the skin of the wing, which comprises the following steps:
arranging a plurality of self-tensioning ribs in parallel;
for each self-tensioning rib, beads 5 are placed within the open end of the omega-shaped cross-section of rib body 1, thereby distracting the omega-shaped cross-section of rib body 1; the beads 5 are in a string structure and are arranged along the circumferential direction of the rib main body 1 so as to completely expand the omega-shaped section of the rib main body 1;
respectively bonding each skin 7 to the opening end of the omega-shaped section of the adjacent rib main body 1; when the skin 7 is laid and bonded, the surface needs to be kept flat;
inserting the T-shaped pressing block 6 into the opening end of the omega-shaped section of the rib main body 1, and pressing the bonding part of the skin 7 and the rib main body 1; the T-shaped pressing block 6 applies pressure to the skin 7 to ensure the bonding strength, the T-shaped pressing block 6 comprises a vertical part and a horizontal part, and the vertical part and the horizontal part are in round corner transition to match a flange 14 of an omega-shaped section of the rib main body 1 with a round corner at a U-shaped section 13;
and after the bonding part of the skin 7 and the rib main body 1 is completely cured, the T-shaped pressing block 6 and the bead 5 are sequentially taken out, so that the rib main body 1 is automatically tightened. After the T-shaped pressing block 6 and the beads 5 are taken out, under the action of the rigidity of the wing rib main body 1, the pair of flanges 14 of the omega-shaped section move in opposite directions and are retracted, so that the skin 7 is automatically tensioned, the skin 7 is tensioned, and the laying quality of the skin 7 is improved.
The self-tensioning ribs are arranged on the girders or stringers of the wing in parallel and are bonded and fixed with the girders or stringers through the front girder bonding parts 3 and the rear girder bonding parts 4.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (9)
1. A self-tensioning rib is characterized by comprising a rib main body (1) and a plurality of support rods (2), wherein the section of the rib main body (1) is in an omega shape;
the rib main body (1) comprises a rib upper wing surface (11) and a rib lower wing surface (12), wherein the rib upper wing surface (11) is smoothly connected with the front end of the rib lower wing surface (12), and the rear end of the rib upper wing surface is attached to the rear end of the rib lower wing surface; the two ends of the stay bar (2) are respectively connected to the rib upper wing surface (11) and the rib lower wing surface (12);
the omega-shaped section of the rib main body (1) comprises a U-shaped section (13) and a pair of flanges (14), and the pair of flanges (14) are arranged on two sides of the opening end of the U-shaped section (13);
the omega-shaped section of the rib main body (1) further comprises a reinforcing section (15), the reinforcing section (15) is strip-shaped, one end of the reinforcing section is connected to the closed end of the U-shaped section (13), and the other end of the reinforcing section extends in the direction far away from the U-shaped section (13).
2. Self-tensioning rib according to claim 1, characterized in that a plurality of said struts (2) are arranged in succession between said rib upper airfoil surface (11) and said rib lower airfoil surface (12) and form a broken line structure.
3. The self-tensioning rib according to claim 1, further comprising a pair of front beam bonds (3) and a pair of back beam bonds (4), the pair of front beam bonds (3) being provided on the rib upper airfoil (11) and the rib lower airfoil (12), respectively, and being proximate to the front ends of the rib upper airfoil (11) and the rib lower airfoil (12), the pair of back beam bonds (4) being provided on the rib upper airfoil (11) and the rib lower airfoil (12), respectively, and being proximate to the back ends of the rib upper airfoil (11) and the rib lower airfoil (12), the pair of front beam bonds (3) and the pair of back beam bonds (4) being connected to the other end of the reinforcing section (15), respectively.
4. Self-tensioning rib according to claim 3, characterized in that the front beam bonding part (3) and the rear beam bonding part (4) are both of plate-type structure.
5. Self-tensioning rib according to claim 1, characterized in that the rib body (1) is made of carbon fiber with a thickness of 0.3-1.3 mm.
6. Wing, characterized in that it comprises a plurality of self-tensioning ribs according to any one of claims 1 to 5 and at least one skin (7).
7. The wing of claim 6 wherein a plurality of said self-tensioning ribs are disposed in parallel along the length of the wing and are connected to the spars or stringers of the wing.
8. The wing as claimed in claim 7, characterized in that the skin (7) is laid between adjacent self-tensioning ribs and is connected to the open end of the omega-section of the rib body (1).
9. A method of laying down the skin of an airfoil as claimed in claim 6, the method comprising:
arranging a plurality of said self-tensioning ribs in parallel;
for each self-tensioning rib, disposing a bead (5) within the open end of the omega-shaped cross-section of the rib body (1) to thereby distract the omega-shaped cross-section of the rib body (1);
respectively bonding each skin (7) to the opening end of the omega-shaped section of the adjacent rib main body (1);
inserting a T-shaped pressing block (6) into the opening end of the omega-shaped section of the rib main body (1) so as to press the bonding part of the skin (7) and the rib main body (1);
and after the bonding part of the skin (7) and the rib main body (1) is completely cured, sequentially taking out the T-shaped pressing block (6) and the beads (5) to automatically tighten the rib main body (1), so that the skin (7) is automatically tensioned.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110374792.9A CN112758306B (en) | 2021-04-08 | 2021-04-08 | Self-tensioning wing rib, wing and skin laying method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110374792.9A CN112758306B (en) | 2021-04-08 | 2021-04-08 | Self-tensioning wing rib, wing and skin laying method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112758306A CN112758306A (en) | 2021-05-07 |
| CN112758306B true CN112758306B (en) | 2021-07-16 |
Family
ID=75691296
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110374792.9A Active CN112758306B (en) | 2021-04-08 | 2021-04-08 | Self-tensioning wing rib, wing and skin laying method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112758306B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1897803A1 (en) * | 2006-09-08 | 2008-03-12 | Airbus Deutschland GmbH | Holding element for fastening an equipment element to a supporting rail |
| CN203698648U (en) * | 2014-01-20 | 2014-07-09 | 谭大刚 | Flexible skin A-shaped aerofoil capable of being quickly unfolded and folded |
| CN203698650U (en) * | 2014-01-20 | 2014-07-09 | 谭大刚 | Flexible skin M-shaped aerofoil capable of being quickly unfolded and folded |
| CN107554751A (en) * | 2017-08-22 | 2018-01-09 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of stringer protection device |
| CN207157531U (en) * | 2017-08-23 | 2018-03-30 | 周袭明 | Flapping-wing aircraft fixed-wing and flapping-wing aircraft |
| CN212047860U (en) * | 2020-04-29 | 2020-12-01 | 成都师范学院 | Solar unmanned aerial vehicle wing structure |
| CN112589424A (en) * | 2021-03-05 | 2021-04-02 | 中国航天空气动力技术研究院 | Flexible pressing tool and method for controlling assembly damage of front edge of unmanned aerial vehicle |
-
2021
- 2021-04-08 CN CN202110374792.9A patent/CN112758306B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1897803A1 (en) * | 2006-09-08 | 2008-03-12 | Airbus Deutschland GmbH | Holding element for fastening an equipment element to a supporting rail |
| CN203698648U (en) * | 2014-01-20 | 2014-07-09 | 谭大刚 | Flexible skin A-shaped aerofoil capable of being quickly unfolded and folded |
| CN203698650U (en) * | 2014-01-20 | 2014-07-09 | 谭大刚 | Flexible skin M-shaped aerofoil capable of being quickly unfolded and folded |
| CN107554751A (en) * | 2017-08-22 | 2018-01-09 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of stringer protection device |
| CN207157531U (en) * | 2017-08-23 | 2018-03-30 | 周袭明 | Flapping-wing aircraft fixed-wing and flapping-wing aircraft |
| CN212047860U (en) * | 2020-04-29 | 2020-12-01 | 成都师范学院 | Solar unmanned aerial vehicle wing structure |
| CN112589424A (en) * | 2021-03-05 | 2021-04-02 | 中国航天空气动力技术研究院 | Flexible pressing tool and method for controlling assembly damage of front edge of unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112758306A (en) | 2021-05-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8074929B1 (en) | Methods and systems for composite structural truss | |
| JP4607583B2 (en) | One piece co-cured composite wing | |
| US7080805B2 (en) | Stiffened structures and associated methods | |
| ES2654855T3 (en) | Curved composite beams with tapered tip and corresponding panels | |
| KR102066754B1 (en) | Vertically integrated stringers | |
| US6173925B1 (en) | Skin-rib structure | |
| US8371537B2 (en) | Aircraft structure with hinge rib assembly | |
| JP5939488B2 (en) | Manufacturing method of central wing box | |
| US10940936B2 (en) | Stringer with plank ply and skin construction for aircraft | |
| US9944378B2 (en) | Structural element for an aircraft fuselage that prevents lateral-torsional buckling | |
| US20080245928A1 (en) | Methods and systems for composite structural truss | |
| US9957032B2 (en) | Fibre composite component, winglet and aircraft with a fibre composite component | |
| US8899522B2 (en) | Aircraft fuselage with high strength frames | |
| CN102481972A (en) | Shell segment for producing a fuselage cell section for a fuselage cell of an airplane | |
| CN112758306B (en) | Self-tensioning wing rib, wing and skin laying method | |
| EP2626291B1 (en) | Structural joint having continuous skin with inside and outside stringers | |
| US20140027573A1 (en) | Aircraft fuselage structural element with variable cross-section | |
| CN111605716A (en) | Main structure of aircraft hanging rack and aircraft | |
| EP3798115A1 (en) | Wing rib | |
| US11505301B2 (en) | Bulb stiffener with sinusoidal web |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |