CN214824050U - Wing structure capable of being provided with externally-hung airborne equipment - Google Patents
Wing structure capable of being provided with externally-hung airborne equipment Download PDFInfo
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- CN214824050U CN214824050U CN202023311276.1U CN202023311276U CN214824050U CN 214824050 U CN214824050 U CN 214824050U CN 202023311276 U CN202023311276 U CN 202023311276U CN 214824050 U CN214824050 U CN 214824050U
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Abstract
The utility model provides a wing structure capable of being provided with an external airborne device, which comprises a wing front beam and a wing rear beam of a wing which are arranged in parallel at intervals, and a first bulkhead and a second bulkhead which are arranged in parallel at intervals left and right; the plurality of stringers are arranged between the front wing beam and the rear wing beam in parallel with the front wing beam and the rear wing beam; the first reinforcement frame is connected with the first upper stringer, the first lower stringer and the second bulkhead respectively; the second stringer group includes a second stringer stiffener structure, and the second stiffener frame is connected to the second lower stringer and the second bulkhead, respectively. The utility model discloses a with the stores pylon to the skin and the power transmission of stringer to the wing bulkhead that structural strength is higher on to the wing after making the repacking satisfies the strength requirement, and has good commonality.
Description
Technical Field
The utility model belongs to the technical field of the aircraft design technique and specifically relates to aircraft wing structural design technique and specifically relates to a wing structure of external airborne equipment of mountable is related to.
Background
In some special fields, an airplane is used as an observation platform, and related equipment is required to be carried for observation measurement, data acquisition and the like. For example, in the aspect of meteorological observation, meteorological parameters such as cloud particles and precipitation particles can be observed through an airborne cloud particle spectrometer, a cloud particle imager, a precipitation particle imager and the like.
The observation devices are typically mounted on the wings of fixed-wing aircraft using a device pylon. Because the measurement devices to be mounted are different according to different requirements, the wings of the existing aircraft are usually modified to implement the device mounting.
However, the existing wing modification scheme has more changes to the original structure of the airplane, so that the modification engineering cost is high, the period is long, the influence on the original strength and the dynamic performance of the airplane is large, and the complexity of the related mechanical design calculation is greatly increased. Meanwhile, the existing modification scheme is only suitable for a specific machine type or specific airborne equipment generally, and the universality is poor.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a wing structure of external airborne equipment of mountable to simplify wing repacking technology, improve the wing intensity after the repacking, and have good commonality, be fit for multiple model and airborne equipment carry.
In order to achieve the purpose, the utility model provides a wing structure capable of being provided with an external airborne device, which comprises a wing front beam and a wing rear beam of a wing, a first bulkhead and a second bulkhead, wherein the wing front beam and the wing rear beam are arranged in parallel at intervals, and the first bulkhead and the second bulkhead are arranged in parallel at intervals; the plurality of stringers are arranged between the front wing girder and the rear wing girder in parallel with the front wing girder and the rear wing girder and comprise a first stringer group adjacent to the front wing girder and a second stringer group adjacent to the rear wing girder; wherein the first stringer group includes a first upper stringer and a first lower stringer, and the second stringer group includes a second upper stringer and a second lower stringer;
the first stringer group including a first stringer stiffening structure including a first stiffening frame connected to the first upper stringer, the first lower stringer, and the second bulkhead, respectively;
the second stringer group includes a second stringer stiffening structure including a second stiffening frame connected to the second lower stringer and the second bulkhead, respectively.
In other examples, the wing front spar is provided with a first local reinforcing structure comprising a reinforcing shim plate mounted at the bottom of the wing front spar.
Furthermore, the wing front beam is provided with a plurality of mounting holes for mounting equipment hangers, the reinforcing base plate corresponds to the mounting holes and is riveted with a plurality of supporting plate nuts, and screw holes of the supporting plate nuts are arranged corresponding to the mounting holes.
In other examples, the upper stringer is connected between the top of the first and second formers and the lower stringer is connected between the bottom of the first and second formers.
In some other examples, the first reinforcing frame is a right-angle trapezoidal member, and each side forms a right-angle folded edge; the folded edges of the upper bottom edge of the first reinforcing frame are connected with the first upper long purlin through a plurality of bolts, the folded edges of the lower bottom edge of the first reinforcing frame are connected with the first lower long purlin through a plurality of bolts, and the folded edges of the right-angle side edges of the first reinforcing frame are connected with the second separation frame through a plurality of bolts.
Furthermore, the first reinforcing frame is an aluminum alloy material workpiece, and a circular window is formed in the middle of the first reinforcing frame and used for cable routing and providing an operation space for a related installation process.
In some other examples, the second reinforcing frame is a right-angled triangular member, two right-angled sides of which form right-angled folds, the fold of the first right-angled side being connected to the second lower stringer by a plurality of bolts, and the fold of the second right-angled side being connected to the second bulkhead by a plurality of bolts.
Further, the second reinforcing frame is a stainless steel sheet metal part, and the bevel edge of the second reinforcing frame comprises a material removing part.
In other examples, a reinforcing lining plate is fixedly arranged on one side of the second bulkhead facing the first bulkhead, and the first reinforcing frame is connected with one side edge of the reinforcing lining plate to realize connection with the second bulkhead; the second reinforcing frame is connected with the other side plate of the reinforcing lining plate so as to realize connection with the second bulkhead.
Furthermore, a circular window is formed in the middle of the reinforcing lining plate and used for cable routing and providing an operation space for related installation processes.
Compared with the prior art, the utility model discloses a with the stores pylon to the skin and the power transmission of stringer to the wing bulkhead that structural strength is higher on to the wing after making the repacking satisfies the strength requirement, and has good commonality.
Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments of the invention, which proceeds with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are described herein, serve to provide a further understanding of the invention and constitute a part of this specification, and the exemplary embodiments and descriptions thereof are provided for explaining the invention without unduly limiting it. In the drawings:
fig. 1 is a schematic view of a wing structure on which an external airborne device can be mounted according to an embodiment of the present invention;
fig. 2 is an illustration of the use state of the mounting machine-mounted hanging rack of the utility model.
In the figure:
1-wing front spar;
2-wing back spar;
3-a first bulkhead;
4-a second bulkhead;
5-a first upper stringer;
6-a first lower stringer;
7-a second lower stringer;
8-reinforcing the base plate;
9-a first reinforcement frame;
10-a second reinforcing frame;
11-reinforcing the lining plate;
100-wing, 200-airborne pylon;
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Unless specifically stated otherwise, the relative arrangement of the components and steps, the numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present invention. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values.
According to the refitting requirement of an airplane, when a certain number of observation devices are required to be mounted at the lower part of the wing, the wing structure is required to be reinforced for mounting the observation devices. The design of the wing reinforcing structure needs to meet the requirements of the mounting equipment, cannot influence the lift force and the resistance of the airplane, and can meet the requirements of strength design and the like.
Fig. 1 shows a wing reinforcing structure for post-installation of an external airborne device according to an embodiment of the present invention, for example, for mounting a laser particle detector on a wing of a C90GTi aircraft, and particularly, locally reinforcing a bulkhead 169.829-184.0 of a left wing station and a right wing station of the aircraft.
As shown in fig. 1, a is a heading direction along which, from front to back, a wing front spar 1 and a wing back spar 2 of a wing are spaced parallel to each other, and a first bulkhead 3 and a second bulkhead 4 are spaced parallel to each other, wherein the first bulkhead 3 may be, for example, an 169.829 bulkhead, and the second bulkhead 4 may be, for example, a 184.0 bulkhead.
The wing front beam 1 is provided with a first local reinforcing structure which comprises a reinforcing base plate 8 arranged at the bottom of the wing front beam 1. The reinforcing base plate 8 is connected to the bottom of the wing front beam 1 through screws in a screwed mode, or the reinforcing base plate 8 can be fixed to the bottom of the wing front beam 1 through riveting.
The front wing beam 1 is provided with a plurality of mounting holes for mounting equipment hangers, the reinforcing base plate 8 is provided with a plurality of supporting plate nuts corresponding to the mounting holes, for example, 4-6M 6 double-supporting-lug nuts, and screw holes of the nuts are arranged corresponding to the mounting holes. Preferably, the double-lug nut is riveted on the reinforcing backing plate 8. Therefore, when the equipment hanging rack is disassembled and assembled, only the screw heads need to be unscrewed or screwed, and the wing and the equipment hanging rack are convenient to maintain.
Optionally, the reinforcing backing plate 8 is made of stainless steel, for example, stainless steel plate with a width of 16mm, a thickness of 4-6mm and a length of 200mm is used.
Because the wing front beam 1 is made of aluminum alloy, the strength of the wing front beam is reduced due to the fact that the equipment hanger mounting holes are formed in the wing front beam, and the local strength of the wing front beam is strengthened by arranging the reinforcing base plate 9 on the wing front beam.
The plurality of stringers are arranged between the wing front beam 1 and the wing rear beam 2 in parallel with the wing front beam 1 and the wing rear beam 2 and comprise upper stringers and lower stringers, wherein the upper stringers are connected between the tops of the first partition frame 3 and the second partition frame 4, and the lower stringers are connected between the bottoms of the first partition frame 3 and the second partition frame 4.
According to an embodiment of the invention, the stringers comprise a first stringer group adjacent to the wing front spar 1 and a second stringer group adjacent to the wing back spar 2. Wherein the first stringer group includes a first upper stringer 5 and a first lower stringer 6, and the second stringer group includes a second upper stringer (not labeled in the figures) and a second lower stringer 7.
The first stringer group includes a first stringer stiffening structure including a first stiffening frame 9, the first stiffening frame 9 being connected to the first upper stringer 5, the first lower stringer 6 and the second bulkhead 4, respectively.
As shown in fig. 1, the first reinforcing frame 9 is a right-angled trapezoidal member, and each side is formed with a right-angled folded edge to improve the bending strength of the member. The folded edges of the upper bottom edge of the first reinforcing frame 9 are connected with the first upper stringer 5 through a plurality of bolts, the folded edges of the lower bottom edge are connected with the first lower stringer 6 through a plurality of bolts, and the folded edges of the right-angle side edges are connected with the second bulkhead 4 through a plurality of bolts.
Optionally, the first reinforcing frame 9 is a numerical control workpiece made of an aluminum alloy material, and a circular window is formed in the middle of the first reinforcing frame and used for cable routing and providing an operation space for a related installation process. At the same time, the component weight is reduced by removing part of the material.
The second stringer group includes a second stringer stiffening structure including a second stiffening frame 10, the second stiffening frame 10 being connected to the second lower stringer 7 and the second bulkhead 4, respectively.
As shown in fig. 1, the second reinforcing frame 10 is a right-angled triangular member, and two right-angled sides of the right-angled triangular member form right-angled folded edges respectively, so as to improve the bending strength of the member. The folded edge of the first right-angle side of the second reinforcing frame 10 is connected with the second lower stringer 7 through a plurality of bolts, and the folded edge of the second right-angle side is connected with the second bulkhead 4 through a plurality of bolts.
Optionally, the second reinforcing frame 10 is a stainless steel sheet metal part, for example, a stainless steel plate with a thickness of 1mm is cut and bent. Further, the beveled edge thereof includes a material removal portion, by which material is removed, the weight of the component is reduced.
The utility model discloses in, second bulkhead 4 towards one side of first bulkhead 3 is equipped with strengthens welt 11, and this enhancement welt 11 adopts fixed connection structure such as connecting pieces such as bolts or riveting to fix on the second bulkhead 4. The right-angled side edge of the first reinforcing frame 9 is connected to one side edge of the reinforcing lining plate 11, so as to be connected to the second bulkhead 4. The second right-angle side of the second reinforcing frame 10 is connected with the other side plate of the reinforcing lining plate 11 so as to realize connection with the second bulkhead 4.
Furthermore, a circular window is formed in the middle of the reinforcing lining plate 11 and used for cable routing and providing an operation space for related installation processes. At the same time, the component weight is reduced by removing part of the material.
The upper bottom edge of the first reinforcing frame 9 is connected with the first upper stringer 5, the lower bottom edge of the first reinforcing frame is connected with the first lower stringer 6 and the aircraft skin through the original machine rivet hole in a screwed mode, and the rivet hole is a connecting rivet hole of the original stringer and the aircraft wing lower skin.
Similarly, the first right-angle side of the second reinforcing frame 10, the second lower stringer 7 and the aircraft skin are also screwed through the original machine rivet hole, and the rivet hole is a connecting rivet hole of the original second stringer and the aircraft wing lower skin.
Further, the aircraft skin between the first lower stringer 6 and the second lower stringer 7 is provided with a recovery flap. Because need install the cable in this flap department after installing the stores pylon additional, if directly punch on former flap, can lead to the aircraft can't restore to the original condition before the repacking. Therefore, the utility model discloses set up the flap alone. The recovery flap comprises two parts, one part is provided with a thread hole and is installed before the hanging rack is installed, and the other part is a closing cover and is installed after the hanging rack is installed.
Fig. 2 shows a schematic view of the installation of the wing 100 and the airborne pylon 200 mounted thereon.
The utility model adopts the above structure, with the stores pylon to the skin and the power transmission of stringer to the higher wing bulkhead of structural strength on to the wing after making the repacking satisfies the intensity requirement.
Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention. Without departing from the spirit of the present invention, it should be understood that the scope of the claims is intended to cover all such modifications and variations.
Claims (10)
1. The wing structure capable of being provided with the external airborne equipment is characterized by comprising a wing front beam and a wing rear beam of a wing, a first bulkhead and a second bulkhead, wherein the wing front beam and the wing rear beam are arranged in parallel at intervals, and the first bulkhead and the second bulkhead are arranged in parallel at intervals left and right; the plurality of stringers are arranged between the front wing girder and the rear wing girder in parallel with the front wing girder and the rear wing girder and comprise a first stringer group adjacent to the front wing girder and a second stringer group adjacent to the rear wing girder; wherein the first stringer group includes a first upper stringer and a first lower stringer, and the second stringer group includes a second upper stringer and a second lower stringer;
the first stringer group including a first stringer stiffening structure including a first stiffening frame connected to the first upper stringer, the first lower stringer, and the second bulkhead, respectively;
the second stringer group includes a second stringer stiffening structure including a second stiffening frame connected to the second lower stringer and the second bulkhead, respectively.
2. The wing structure of claim 1, wherein the wing front spar is provided with a first local stiffening structure comprising a stiffening shim plate mounted at the bottom of the wing front spar.
3. The wing structure of claim 2, wherein the wing front spar is provided with a plurality of mounting holes for mounting equipment hangers, the reinforcing backing plate is riveted with a plurality of supporting plate nuts corresponding to the mounting holes, and screw holes of the supporting plate nuts are arranged corresponding to the mounting holes.
4. The wing structure of claim 1, wherein the upper stringer is connected between the tops of the first and second bulkheads and the lower stringer is connected between the bottoms of the first and second bulkheads.
5. The wing structure of claim 1, wherein the first stiffening frame is a right angle trapezoidal member, each side forming a right angle hem; the folded edges of the upper bottom edge of the first reinforcing frame are connected with the first upper long purlin through a plurality of bolts, the folded edges of the lower bottom edge of the first reinforcing frame are connected with the first lower long purlin through a plurality of bolts, and the folded edges of the right-angle side edges of the first reinforcing frame are connected with the second separation frame through a plurality of bolts.
6. The wing structure of claim 5, wherein the first reinforcing frame is an aluminum alloy workpiece, and a circular window is formed in the middle of the first reinforcing frame for cable routing and providing an operating space for an associated installation process.
7. The wing structure of claim 1, wherein the second stiffening frame is a right-angled triangular member having two right-angled sides each forming a right-angled hem, the hem of the first right-angled side being connected to the second lower stringer by a plurality of bolts, and the hem of the second right-angled side being connected to the second bulkhead by a plurality of bolts.
8. The wing structure of claim 7, wherein the second stiffening frame is a sheet metal part of stainless steel material, the hypotenuse of which includes a material removal portion.
9. The wing structure of claim 1, wherein a reinforcing lining plate is fixedly arranged on one side of the second bulkhead facing the first bulkhead, and the first reinforcing frame is connected with one side edge of the reinforcing lining plate to realize connection with the second bulkhead; the second reinforcing frame is connected with the other side plate of the reinforcing lining plate so as to realize connection with the second bulkhead.
10. The wing structure of claim 9, wherein a circular window is formed in the middle of the reinforcing patch for routing cables and providing an operating space for an associated installation process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023311276.1U CN214824050U (en) | 2020-12-31 | 2020-12-31 | Wing structure capable of being provided with externally-hung airborne equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023311276.1U CN214824050U (en) | 2020-12-31 | 2020-12-31 | Wing structure capable of being provided with externally-hung airborne equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214824050U true CN214824050U (en) | 2021-11-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202023311276.1U Active CN214824050U (en) | 2020-12-31 | 2020-12-31 | Wing structure capable of being provided with externally-hung airborne equipment |
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| Country | Link |
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| CN (1) | CN214824050U (en) |
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