CN113277115B - Unmanned aerial vehicle wing assembling method - Google Patents
Unmanned aerial vehicle wing assembling method Download PDFInfo
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- CN113277115B CN113277115B CN202110751926.4A CN202110751926A CN113277115B CN 113277115 B CN113277115 B CN 113277115B CN 202110751926 A CN202110751926 A CN 202110751926A CN 113277115 B CN113277115 B CN 113277115B
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- 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
Abstract
The invention relates to the technical field of wing assembly, in particular to an unmanned aerial vehicle wing assembly method. The assembling method includes the steps that a channel to be sealed is reserved firstly during assembling, the channel to be sealed is sealed after the assembling is basically completed, meanwhile, the first positioning portion and the second positioning portion are adopted to guarantee accurate positioning and installation of the middle section of the rib plate, accurate positioning and installation of the middle section of the rib plate are achieved through the first positioning portion and the second positioning portion, errors possibly caused by installation of the rib plate in different times are reduced, the skin and the beam can be connected in a screwed mode, the structural strength of the wing is improved through glue and screw mixed connection or glue and rivet and screw mixed connection assembling, and limitation of structural design of the wing is reduced. On the other hand, the first positioning part and the second positioning part also increase the strength of the wing to a certain extent.
Description
Technical Field
The invention relates to the technical field of wing assembly, in particular to an unmanned aerial vehicle wing assembly method.
Background
The composite parts are widely applied to the aerospace field by the performances of high strength, high modulus, high temperature resistance, fatigue resistance and the like, and a large number of composite material structures are successfully adopted from military airplanes to civil airplanes.
In order to reduce the structural weight of the unmanned aerial vehicle, the wings of the unmanned aerial vehicle are designed to be of a full composite material structure and comprise honeycomb sandwich skins, birch board sandwich rib plates, carbon fiber composite material beams, root rib plates and the like. The beams and the ribs are distributed vertically and horizontally and are connected by pasting the angle sheets by a manual wet method.
The wing skin is of a honeycomb sandwich structure, the rigidity is poor, the positioning difficulty is high during combination, and in order to ensure the combination precision, an assembly jig needs to be specially designed to position the skin and the ribbed plates. On one hand, the combination between the skin and the framework (consisting of beams and ribs) requires high precision and has quite high strength requirement, and on the other hand, the skin and the framework are combined, and the wing forms a closed space, so that the reinforcing mode of the wing is limited. For the wings such as a high-speed unmanned aerial vehicle and the like which need high bearing capacity, in order to improve the bearing capacity of the wings, a glue-rivet mixed connection mode is adopted at the joint of a skin and a beam in a region (generally a wing root region) to be reinforced, namely, after the skin is glued with a framework, the skin is riveted and reinforced with the corresponding region of the beam from the outside, but for the part with thinner skin design, because the thickness is insufficient, the skin cannot be sunk, so that the rivet connection cannot be used, and the structural design of the wings is limited.
Disclosure of Invention
The invention aims to provide a wing assembling method, which solves the technical problem.
In order to achieve the purpose, the invention provides an unmanned aerial vehicle wing assembling method, which is used for assembling through an assembling fixture and comprises the following steps:
laying a first side skin on the assembly jig;
positioning and mounting the front beam, the rear beam and the rib plates by utilizing an assembly type frame to form a framework, wherein the root rib plate at the end part of the wing root is only provided with a front root rib plate section positioned at the front side of the front beam and a rear root rib plate section positioned at the rear side of the rear beam, a first positioning part extending towards the rear beam is arranged at the rear side of the front beam, a second positioning part extending towards the front beam is arranged at the front side of the rear beam, and the first positioning part and the second positioning part are provided with a gap in the front-rear direction to form a channel to be closed;
bonding the framework with the first side skin, and applying pressure to the framework to enable the framework to be firmly bonded with the first side skin;
bonding a second side skin with the other side of the framework, and applying pressure to the second side skin;
riveting the connecting parts of the front beam and the rear beam with the first side skin and the second side skin, screwing the positions which cannot be riveted due to insufficient thickness of the skins, and screwing nuts through the channel to be sealed;
and positioning and installing the middle section of the rib plate by utilizing the first positioning part and the second positioning part, riveting and fixing the middle section of the rib plate with the first side skin and the second side skin respectively, sealing the channel to be sealed, and finishing the assembly of the wing.
Preferably, the cross sections of the front beam and the rear beam are U-shaped, and the opening sides of the front beam and the rear beam are oppositely arranged;
one end of the first positioning part extends into and is fixedly connected with the front beam from the opening side of the front beam, and one end of the second positioning part extends into and is fixedly connected with the rear beam from the opening side of the rear beam.
Preferably, the cross section of the first positioning part is U-shaped, one end of the first positioning part, which is connected with the front beam, is provided with a first mounting plate, and the first positioning part is screwed with the front beam through the first mounting plate;
the cross section of the second positioning part is U-shaped, a second mounting plate is arranged at one end of the second positioning part connected with the back beam, and the second positioning part is in threaded connection with the back beam through the second mounting plate;
the cross section of the middle section of the rib plate is U-shaped, and the two ends of the rib plate are sleeved outside the first positioning part and the second positioning part to realize positioning and installation.
Preferably, a third positioning part is arranged on the front side of the front beam and used for positioning and mounting the front section of the root rib plate;
and a fourth positioning part is arranged at the rear side of the rear beam and used for positioning and installing the rear section of the rib plate.
Preferably, the cross section of the third positioning part is U-shaped, a third mounting plate is arranged at one end of the third positioning part connected with the front beam, and the third positioning part is in threaded connection with the front beam through the third mounting plate;
the cross section of the front section of the rib plate is U-shaped, and one end of the rib plate is sleeved outside the third positioning part to realize positioning and installation;
the cross section of the fourth positioning part is U-shaped, a fourth mounting plate is arranged at one end of the fourth positioning part connected with the rear beam, and the fourth positioning part is in threaded connection with the rear beam through the fourth mounting plate;
the cross section of the rear section of the rib plate is U-shaped, and one end of the rib plate is sleeved outside the fourth positioning part to realize positioning and installation.
Preferably, the same clamping plate set is adopted for pressing the framework and the second side skin, and the inner molded surface of the clamping plate is matched with the outer molded surface of the corresponding second side skin;
when the framework is pressed, the clamping plate is fixed on the frame body of the assembly type frame, a gap is formed between the inner profile surface of the clamping plate and the framework, the thickness of the gap is the same as that of the second side skin, and a plurality of gaskets are inserted into the gap at intervals along the front-back direction to realize the pressing of the framework;
when the framework is pressed, the clamping plate is fixed on the frame body of the assembly type frame, and the inner profile of the clamping plate is pressed on the second side skin in a fitting mode to apply pressure to the second side skin.
Preferably, the inner profile of the clamping plate is made of rubber.
Preferably, the gasket is a rubber gasket.
The technical scheme of the invention has the following advantages: according to the unmanned aerial vehicle wing assembly method provided by the invention, the channel to be sealed is reserved, after the assembly is basically finished, the channel to be sealed is sealed, meanwhile, the first positioning part and the second positioning part are adopted to ensure the accurate positioning and installation of the middle section of the rib plate, and the accurate positioning and installation of the middle section of the rib plate is realized by arranging the first positioning part and the second positioning part, so that errors possibly caused by the installation of the rib plate in different times are reduced, the screwing of the skin and the beam is possible, the structural strength of the wing is increased by the glue (bonding) screw (connection) mixed connection or the glue (bonding) riveting (connection) screw (connection) mixed connection assembly, and the limitation of the structural design of the wing is reduced. On the other hand, the first positioning part and the second positioning part also increase the strength of the wing to a certain extent.
Drawings
The drawings of the present invention are provided for illustrative purposes only, and the proportion and the number of the components in the drawings do not necessarily correspond to those of an actual product.
FIG. 1 is a schematic structural view of a method for assembling a frame to assemble a wing according to an embodiment of the present invention;
FIG. 2 is a schematic view of the assembled fixture of the embodiment of the present invention after being cut along the center line;
FIG. 3 is a schematic structural view of a wing (with the second side skin removed) in an embodiment of the invention;
FIG. 4 is a schematic view of another angle configuration of an airfoil (with the second side skin removed) in accordance with an embodiment of the present invention;
FIG. 5 is a schematic view of the structure of an airfoil (unassembled mid-rib section) according to an embodiment of the present invention;
fig. 6 is a schematic structural view of a wing root of an airfoil according to an embodiment of the invention.
In the figure: 1: assembling a fixture; 11: a frame body; 12: a clamping plate on the lower side; 13: a clamping plate on the upper side;
2: an airfoil; 21: a first side skin; 22: a front beam; 23: a rear beam; 24: a root rib plate; 241: a root rib plate front section; 242: a middle section of the root rib plate; 243: a root rib plate rear section; 25: a first positioning portion; 26: a second positioning portion; 27: a third positioning part; 28: a fourth positioning portion; 29: a second side skin.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
Root rib refers to a rib at the root end of the wing, which for convenience of description will be described in this application as a root rib.
The front and rear indication directions in the present application are based on the direction relationships shown in fig. 1 and 3, and are only for convenience of description and simplification of description, and thus, should not be construed as limiting the present application.
Furthermore, the terms "first," "second," "third," and "fourth" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Referring to fig. 1-6, in the method for assembling wings of an unmanned aerial vehicle according to the embodiment of the present invention, the unmanned aerial vehicle is assembled by using an assembly fixture 1, where the assembly fixture 1 is an existing structure.
Referring to fig. 1 and 2, the assembly jig 1 includes a frame body 11, a clamping plate 12 on the lower side and a clamping plate 13 on the upper side, the clamping plate 12 on the lower side and the clamping plate 13 on the upper side can be detachably fixed on the frame body 11, a first side skin 21 is laid on the clamping plate 12 on the lower side, and on this basis, the assembly jig 1 is adopted to assemble the framework, wherein the positioning and installation of the front beam 22, the rear beam 23 and the rib plate (except for the rib plate 24) are the prior art, and are not described herein again.
The root rib 24 is divided into a root rib front section 241, a root rib middle section 242, and a root rib rear section 243 by the front beam 22 and the rear beam 23. Referring to fig. 3 to 6, in the assembling process, when the rib 24 is installed, the rib front section 241 and the rib rear section 242 are installed first, and in order to ensure the positioning accuracy when the rib middle section 243 is installed subsequently, the first positioning portion 25 extending to the rear beam 23 is arranged on the rear side of the front beam 22, the second positioning portion 26 extending to the front beam 22 is arranged on the front side of the rear beam 23, and the first positioning portion 25 and the second positioning portion 26 are spaced in the front-rear direction to form a channel to be closed, as shown in fig. 3 to 5.
And bonding the skeleton with the first side skin 21, and applying pressure to the skeleton to firmly bond the skeleton with the first side skin 21. The second side skin 29 is then bonded to the other side of the carcass and pressure is applied to the second side skin 21 to bond the second side skin 29 firmly to the carcass.
Riveting the connecting parts of the front beam 22 and the rear beam 23 and the first side skin 21 and the second side skin 29, adopting bolt connection at the positions which can not be riveted due to insufficient thickness of the skins, and screwing nuts through the channel to be sealed.
Positioning and installing the rib middle section 243 by using the first positioning part 25 and the second positioning part 26, riveting and fixing the rib middle section 243 with the first side skin 21 and the second side skin 29 respectively, closing the channel to be closed, and completing the assembly of the wing 2, as shown in fig. 6.
In order to further improve the positioning accuracy and the frame strength of the first positioning portion 25 and the second positioning portion 26, in some preferred embodiments, referring to fig. 3 and 4, the cross sections of the front beam 22 and the rear beam 23 are U-shaped, and the front beam 22 is disposed opposite to the opening side of the rear beam 23. One end of the first positioning portion extends into the front beam from the opening side of the front beam to be fixedly connected with the front beam, so that the first positioning portion 25 can realize positioning in at least three directions. One end of the second positioning portion 26 extends into the rear beam 23 from the opening side of the rear beam 23 to be fixedly connected with the rear beam 23, so that the second positioning portion 26 is positioned in at least three directions.
In order to further improve the positioning and mounting accuracy of the middle section 243 of the rib plate, in some preferred embodiments, referring to fig. 3 and 4, the cross section of the first positioning portion 25 is U-shaped, one end of the first positioning portion 25 connected to the front beam 22 is provided with a first mounting plate, and the first positioning portion 25 is screwed and fixed with the front beam 22 through the first mounting plate;
the cross section of the second positioning portion 26 is U-shaped, and a second mounting plate is provided at the end connected to the back beam 23, so that the second positioning portion 26 is screwed and fixed to the back beam 23 through the second mounting plate.
The cross section of the middle section 243 of the rib plate is U-shaped, and the two ends of the middle section are sleeved outside the first positioning portion 255 and the second positioning portion 26 to realize positioning and installation.
To facilitate the installation of the root rib front section 241, in some preferred embodiments, referring to fig. 3 and 4, a third positioning portion 27 is provided on the front side of the front beam 22 for positioning and installing the root rib front section 241. A fourth positioning portion 28 is provided on the rear side of the rear beam 23 for positioning and mounting the heel rib plate rear section 242.
In order to further improve the positioning and mounting accuracy and the mounting convenience of the front section 241 of the root rib plate, the cross section of the third positioning portion 27 is U-shaped, and a third mounting plate is provided at one end connected with the front beam 22, and the third positioning portion is screwed with the front beam 22 through the third mounting plate. The cross section of the root rib plate front section 241 is U-shaped, and one end of the root rib plate front section is sleeved outside the third positioning portion 27 to realize positioning and installation.
In order to further improve the positioning and mounting accuracy and the mounting convenience of the rib plate rear section 242, the cross section of the fourth positioning portion 28 is U-shaped, and a fourth mounting plate is provided at one end connected with the rear beam 23, and the fourth positioning portion 28 is screwed with the rear beam 23 through the fourth mounting plate. The cross section of the rib plate rear section 242 is U-shaped, and one end of the rib plate rear section is sleeved outside the fourth positioning portion 28 to achieve positioning and installation.
In one embodiment, the same set of clips are used for both the compression of the skeleton and the compression of the second side skin 29. Specifically, the upper side clamping plate 13 is used for pressing, the inner profile of the upper side clamping plate 13 is matched with the outer profile of the corresponding second side skin 29, namely when the upper side clamping plate 13 is normally fixed, the second side skin 29 can press the second side skin 29, so that when the upper side clamping plate 13 is used for pressing the framework, a gap is formed between the inner profile of the upper side clamping plate 13 and the framework, the gap is the same as the thickness of the second side skin 29, and a plurality of gaskets are inserted into the gap at intervals along the front-rear direction to transfer pressure to realize pressing on the framework. Of course, in other embodiments, mold pressing or the like may also be used.
Compared with the prior art, if the clamping plates are used for pressing, the framework and the second side skin 29 respectively adopt one set of matched clamping plates for pressing in the prior art, and one set of clamping plates is used for pressing in the embodiment, so that the cost is greatly saved.
In order to avoid damaging the skin, the inner profiles of the lower clamping plate 12 and the upper clamping plate 13 are made of rubber, and preferably a rubber layer is coated on the inner profiles. In a preferred embodiment, the gasket is a rubber gasket.
It should be noted that, in the present application, the end of the "front beam" and the "rear beam" at the wing root are both provided with a connector structure, and the connection structure is an existing structure and is irrelevant to the main improvement of the present invention, and therefore, the details are not described in the present application. In addition, for the same reason, the other ribs except the root rib are not described in detail in the present application.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: each embodiment does not include only one independent technical solution, and in the case of no conflict between the solutions, the technical features mentioned in the respective embodiments can be combined in any way to form other embodiments which can be understood by those skilled in the art.
Furthermore, modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of the technical features thereof, without departing from the scope of the present invention, and the essence of the corresponding technical solutions does not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (8)
1. An unmanned aerial vehicle wing assembling method is used for assembling through an assembling fixture and is characterized by comprising the following steps:
laying a first side skin on the assembly jig;
positioning and mounting a front beam, a rear beam and rib plates by using the assembly jig to form a framework, wherein the rib plates at the end parts of wing roots are only provided with a front rib plate section at the front side of the front beam and a rear rib plate section at the rear side of the rear beam, a first positioning part extending towards the rear beam is arranged at the rear side of the front beam, a second positioning part extending towards the front beam is arranged at the front side of the rear beam, and the first positioning part and the second positioning part are spaced in the front-rear direction to form a channel to be closed;
bonding the framework with the first side skin, and applying pressure to the framework to firmly bond the framework with the first side skin;
bonding a second side skin with the other side of the framework, and applying pressure to the second side skin;
riveting the connecting parts of the front beam and the rear beam with the first side skin and the second side skin, screwing the positions which cannot be riveted due to insufficient thickness of the skins, and screwing nuts through the channel to be sealed;
and positioning and installing the middle section of the rib plate by utilizing the first positioning part and the second positioning part, riveting and fixing the middle section of the rib plate with the first side skin and the second side skin respectively, sealing the channel to be sealed, and finishing the assembly of the wing.
2. The unmanned aerial vehicle wing assembly method of claim 1, wherein: the cross sections of the front beam and the rear beam are U-shaped, and the opening sides of the front beam and the rear beam are oppositely arranged;
one end of the first positioning part extends into the front beam from the opening side of the front beam and is fixedly connected with the front beam, and one end of the second positioning part extends into the rear beam from the opening side of the rear beam and is fixedly connected with the rear beam.
3. The unmanned aerial vehicle wing assembly method of claim 2, wherein: the cross section of the first positioning part is U-shaped, a first mounting plate is arranged at one end, connected with the front beam, of the first positioning part, and the first positioning part is in threaded connection with the front beam through the first mounting plate;
the cross section of the second positioning part is U-shaped, a second mounting plate is arranged at one end of the second positioning part connected with the rear beam, and the second positioning part is in threaded connection with the rear beam through the second mounting plate;
the cross section of the middle section of the root rib plate is U-shaped, and the two ends of the root rib plate are sleeved outside the first positioning part and the second positioning part to realize positioning and installation.
4. The unmanned aerial vehicle wing assembly method of claim 1, wherein: a third positioning part is arranged on the front side of the front beam and used for positioning and mounting the front section of the root rib plate;
and a fourth positioning part is arranged at the rear side of the rear beam and used for positioning and installing the rear section of the rib plate.
5. The unmanned aerial vehicle wing assembly method of claim 4, wherein:
the cross section of the third positioning part is U-shaped, a third mounting plate is arranged at one end, connected with the front beam, of the third positioning part, and the third positioning part is in threaded connection with the front beam through the third mounting plate;
the cross section of the front section of the rib plate is U-shaped, and one end of the rib plate is sleeved outside the third positioning part to realize positioning and installation;
the cross section of the fourth positioning part is U-shaped, a fourth mounting plate is arranged at one end of the fourth positioning part connected with the rear beam, and the fourth positioning part is in threaded connection with the rear beam through the fourth mounting plate;
the cross section of the rear section of the rib plate is U-shaped, and one end of the rib plate is sleeved on the outer side of the fourth positioning part to realize positioning and installation.
6. The unmanned aerial vehicle wing assembly method of claim 1, wherein: applying pressure to the framework and applying pressure to the second side skin by using the same clamping plate, wherein the inner molded surface of the clamping plate is matched with the outer molded surface of the corresponding second side skin;
when the framework is pressed, the clamping plate is fixed on the frame body of the assembly type frame, a gap is formed between the inner profile surface of the clamping plate and the framework, the thickness of the gap is the same as that of the second side skin, and a plurality of gaskets are inserted into the gap at intervals along the front-back direction to realize pressing on the framework;
when the framework is pressed, the clamping plate is fixed on the frame body of the assembly type frame, and the inner profile of the clamping plate is pressed on the second side skin in a fitting mode to apply pressure to the second side skin.
7. The unmanned aerial vehicle wing assembly method of claim 6, wherein: the inner molded surface of the clamping plate is made of rubber.
8. The unmanned aerial vehicle wing assembly method of claim 6, wherein: the gasket is a rubber gasket.
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| CN202110751926.4A CN113277115B (en) | 2021-07-02 | 2021-07-02 | Unmanned aerial vehicle wing assembling method |
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| CN202110751926.4A CN113277115B (en) | 2021-07-02 | 2021-07-02 | Unmanned aerial vehicle wing assembling method |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113859572A (en) * | 2021-10-08 | 2021-12-31 | 航天特种材料及工艺技术研究所 | Assembly jig of skin skeleton part and design method thereof |
| CN114013680B (en) * | 2021-11-19 | 2023-04-18 | 航天特种材料及工艺技术研究所 | Assembly fixture for wing end ribs and assembly method for wing butt joint mounting seat |
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