CN114104261B - Wing beam of composite wing aircraft - Google Patents
Wing beam of composite wing aircraft Download PDFInfo
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- CN114104261B CN114104261B CN202210076487.6A CN202210076487A CN114104261B CN 114104261 B CN114104261 B CN 114104261B CN 202210076487 A CN202210076487 A CN 202210076487A CN 114104261 B CN114104261 B CN 114104261B
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- beams
- connecting piece
- fixedly connected
- wing
- hollow rectangular
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/185—Spars
Abstract
The invention discloses a wing spar of a composite wing aircraft, which comprises two horizontal integral beams arranged in a horizontal opposite row, wherein a crossed bearing beam for bearing bending moment is arranged between the two horizontal integral beams, the interior of the crossed bearing beam is of a hollow structure, and the end parts of the crossed bearing beam are fixedly connected with the two horizontal integral beams; the both ends of two horizontal whole roof beams all are provided with an end portion floor that is used for bearing the weight of the moment of torsion, two horizontal whole roof beams are connected fixedly through two end portion floors, the whole hollow structure that is of crossing carrier bar, great reduction the structure weight of wing, and simultaneously, the improvement of crossing carrier bar very big degree the bending resistance performance of carrier bar, be provided with the trough on the crossing carrier bar, simple and effectual the inside problem of depositing water and discharging of wing spar of having solved, increased the end portion floor and can obtain lighter weight under the prerequisite of certain intensity of torsion.
Description
Technical Field
The invention relates to the technical field of aircraft wing structures, in particular to a wing spar of a composite wing aircraft.
Background
At present, the research on the composite wing unmanned aerial vehicle is less at home and abroad, and the research on the form of the fixed wing beam of the composite wing aircraft is more rare. For a fixed-wing aircraft with skin frames as the structural form: the wing spar is a main bearing structure of the airplane, is one of important parts of the airplane and is the premise of ensuring the excellent performance of the airplane. Although the spar is used as a large main stress member of an airplane wing, the occupied proportion of the spar in the whole airplane manufacturing process is small, but the technology for manufacturing the spar with excellent performance by the airplane spar, particularly the spar of a large airplane, is very important due to the complex structure and stress condition of the airplane spar.
The skin skeleton type structure is mainly divided into a single-beam type, a multi-beam type, a single-block type and the like. The skin skeleton type structure mainly comprises a skin, a wing beam, wing ribs, stringers and longitudinal walls. The beam type wing has poor mechanical property, stress concentration phenomenon easily occurs when the structure is stressed, the utilization rate of materials is insufficient, and for a composite wing aircraft, the beam structure of the wing needs to have good bending and twisting resistance, which is not possessed by the existing beam type structure; in contrast, a monolithic structure modified on the basis of a beam structure better overcomes the above disadvantages and has better bending-torsion-resistant mechanical properties, but the monolithic structure makes the wing skin too thick to obtain better bending-torsion-resistant properties, increases the weight of the wing, and cannot be allowed by an aircraft with excellent properties.
Disclosure of Invention
In view of the above problems in the prior art, the present invention aims to provide a wing spar of a composite wing aircraft, which has a light weight structure and a large bending and twisting resistance mechanical property.
In order to achieve the purpose of the invention, the technical scheme adopted by the invention is as follows:
the wing beam of the composite wing aircraft comprises two horizontal integral beams which are horizontally arranged in an opposite row, a crossed bearing beam for bearing bending moment is arranged between the two horizontal integral beams, the interior of the crossed bearing beam is of a hollow structure, and the end parts of the crossed bearing beam are fixedly connected with the two horizontal integral beams; both ends of the two transverse integral beams are provided with end rib plates for bearing the bending moment, and the two transverse integral beams are fixedly connected through the two end rib plates.
The basic principle of the scheme is as follows: the cross bearing beam and the end rib plates are arranged between the two transverse integral beams, the bending and twisting resistance of the bearing beam is greatly improved by the cross bearing beam, the weight of the cross bearing beam is greatly reduced by the hollow structure inside the cross bearing beam, when the composite wing aircraft vertically takes off in water, when the height of the aircraft reaches a preset value, the rotor wing rises to move forward to the fixed wing, the load borne by the wing suddenly changes, the generated bending and twisting moment is mainly borne by the fork beam, and the transverse beams and the end rib plates provide part of bending and twisting resistance moment, so that the structural strength of wing spars is ensured, the requirement is met, and the flight performance of the composite wing aircraft is improved.
Further, as a specific arrangement mode of the crossed bearing beam, the crossed bearing beam comprises two hollow rectangular beams with cross-connected middle parts; the head end of every cavity rectangle roof beam all is provided with first connecting piece, and the tail end of every cavity rectangle roof beam all is provided with a second connecting piece, and the both ends of every cavity rectangle roof beam are respectively through the inside wall fixed connection of first connecting piece and second connecting piece and two horizontal whole roof beams. The arrangement of the first connecting piece and the second connecting piece can increase the structural strength of the joint of the hollow rectangular beam and the two transverse integral beams, and the rigidity performance of the joint is improved.
Furthermore, in order to reduce the self gravity of the hollow rectangular beams and improve the flight performance of the composite wing aircraft, the side wall of each hollow rectangular beam is provided with an oval lightening hole.
Further, when the aircraft is in water, water can get into the cavity rectangular beam, in order to make the aircraft break away from the aquatic after, be convenient for get rid of the water in the cavity rectangular beam, the head end inner wall height of every cavity rectangular beam all is higher than the inside height of tail end, the tail end lower surface of every cavity rectangular beam all sets up the basin of walking rather than inside intercommunication.
Furthermore, the cross sections of the two transverse integral beams are of I-shaped structures, the transverse integral beams with the cross sections of the I-shaped structures can meet the requirement of reducing the self weight, the stress strength can be improved, the installation of a first connecting piece and a second connecting piece can be facilitated, and the first connecting piece and the second connecting piece are arranged in grooves in the inner side surfaces of the transverse integral beams;
the first connecting piece is of a hollow rectangular box-shaped structure, a plurality of mounting holes are formed in the first connecting piece, the first connecting piece partially exceeds the head ends of the two transverse integral beams, and the first connecting piece exceeding the first connecting piece is fixedly connected with the aircraft body; the first connecting piece is fixedly connected with the inner side surface of the transverse integral beam through the mounting hole; two ends of the end rib plate at the head ends of the two transverse integral beams are fixedly connected with the side surface of the first connecting piece.
The two second connecting pieces are symmetrically arranged, each second connecting piece comprises a first connecting box fixedly connected with end rib plates positioned at the tail ends of the two transverse integral beams, the end rib plates are positioned between the two first connecting boxes, the first connecting boxes are obliquely provided with second connecting boxes, and the inclination angles of the second connecting boxes are matched with that of the hollow rectangular beam; a plurality of mounting holes are formed in the first connecting box and the second connecting box;
the head ends of the two hollow rectangular beams are respectively inserted into the first connecting piece and fixedly connected with the head ends of the two transverse integral beams, and the tail ends of the two hollow rectangular beams are respectively inserted into the second connecting box and fixedly connected with the tail ends of the two transverse integral beams.
The setting of first connecting box and second connecting box is for the convenience of the connection of the tail end of two cavity rectangle roof beams, and sets up the second connecting box into inclined structure, is for the inclination of matching the cavity rectangle roof beam, constitutes a whole, and the at utmost provides intensity for the structure.
The invention has the beneficial effects that: wing spar of the composite wing aircraft in this scheme is used for installing on empty dual-purpose unmanned aerial vehicle of water, the whole hollow structure that is of crossing carrier bar, great has alleviateed the structural weight of wing, laying of cable can be carried out to hollow beam structure inside, it is clean and tidy orderly to save space again to make the overall arrangement, and simultaneously, the improvement of crossing carrier bar very big degree the anti kink performance of carrier bar, be provided with the trough on the crossing carrier bar, simple and effectual inside the problem of depositing water discharge of having solved wing spar, the tip floor has been increased and more light weight can be obtained under the prerequisite of certain kink intensity of definite.
Drawings
FIG. 1 is a schematic structural view of a wing spar of a composite wing aircraft.
Fig. 2 is a schematic structural diagram of a cross-type load beam.
Fig. 3 is a schematic structural view of the second connector.
Fig. 4 is a schematic structural diagram of the first connecting member.
Fig. 5 is a structural schematic diagram of two transverse integral beams.
Wherein, 1, transverse integral beam; 2. a crossed load beam; 3. end rib plates; 4. a hollow rectangular beam; 5. a first connecting member; 6. a second connecting member; 601. a first junction box; 602. a second connection box; 7. an elliptical relief hole; 8. a water trough.
Detailed Description
The following description of the embodiments of the present invention is provided to facilitate the understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and it will be apparent to those skilled in the art that various changes may be made without departing from the spirit and scope of the invention as defined and defined in the appended claims, and all matters produced by the invention using the inventive concept are protected.
As shown in fig. 1 to 5, the invention provides a wing spar of a composite wing aircraft, which comprises two horizontal integral beams 1 arranged in a horizontal opposite row, wherein a cross-type carrier beam 2 for carrying a bending moment is arranged between the two horizontal integral beams 1, the interior of the cross-type carrier beam 2 is of a hollow structure, and the end parts of the cross-type carrier beam 2 are fixedly connected with the two horizontal integral beams 1; both ends of the two transverse integral beams 1 are respectively provided with an end rib plate 3 for bearing the bending moment, and the two transverse integral beams 1 are fixedly connected through the two end rib plates 3.
The basic principle of the scheme is as follows: the crossed bearing beam 2 and the end rib plate 3 are arranged between the two transverse integral beams 1, the bending and torsion resistance of the bearing beam is greatly improved by the crossed bearing beam 2, the internal part of the crossed bearing beam 2 is of a hollow structure, the self weight is greatly reduced, when the composite wing aircraft vertically takes off in water, when the height of the aircraft reaches a preset value, the rotor wing rises to be changed into the fixed wing to move forwards, the load borne by the wing suddenly changes, the generated bending and torsion moment is mainly borne by the crossed beam, and the transverse beam and the end rib plate 3 provide a part of bending and torsion moment, so that the structural strength of wing spars is ensured, the requirement is met, and the flight performance of the composite wing aircraft is improved.
As a specific arrangement mode of the crossed bearing beam 2, the crossed bearing beam 2 comprises two hollow rectangular beams 4 with the middle parts crossed and connected; the head end of every cavity rectangle roof beam 4 all is provided with first connecting piece 5, and the tail end of every cavity rectangle roof beam 4 all is provided with a second connecting piece 6, and the both ends of every cavity rectangle roof beam 4 are respectively through the inside wall fixed connection of first connecting piece 5 and second connecting piece 6 and two horizontal whole roof beams 1. The arrangement of the first connecting piece and the second connecting piece 6 can increase the structural strength of the joint of the hollow rectangular beam 4 and the two transverse integral beams 1, and is used for improving the rigidity performance of the joint.
In order to reduce the self gravity of the hollow rectangular beams 4 and improve the flight performance of the composite wing aircraft, the side wall of each hollow rectangular beam 4 is provided with an oval lightening hole 7.
When the aircraft was in aqueous, water can get into cavity rectangular beam 4 in, after in order to make the aircraft break away from aqueous, was convenient for get rid of the water in cavity rectangular beam 4, and the head end inner wall height of every cavity rectangular beam 4 all is higher than the inside height of tail end, and the tail end lower surface of every cavity rectangular beam 4 all sets up the basin 8 of walking rather than inside intercommunication.
The cross section of two horizontal whole roof beams 1 all is "worker" font structure, and the transversal whole roof beam 1 who personally submits "worker" font structure can also promote the stress intensity when satisfying to alleviate self weight, and also can make things convenient for the installation of first connecting piece 5 and second connecting piece 6, and first connecting piece 5 and second connecting piece 6 all set up in the recess of the medial surface of horizontal whole roof beam 1.
The first connecting piece 5 is of a hollow rectangular box-shaped structure, a plurality of mounting holes are formed in the first connecting piece 5, the first connecting piece 5 partially exceeds the head ends of the two transverse integral beams 1, and the first connecting piece 5 exceeding the first connecting piece 5 is fixedly connected with an aircraft fuselage; the first connecting piece 5 is fixedly connected with the inner side surface of the transverse integral beam 1 through a mounting hole; two ends of the end rib plate 3 at the head ends of the two transverse integral beams 1 are fixedly connected with the side surface of the first connecting piece 5.
The two second connecting pieces 6 are symmetrically arranged, each of the two second connecting pieces 6 comprises a first connecting box 601 fixedly connected with end rib plates 3 positioned at the tail ends of the two transverse integral beams 1, the end rib plates 3 are positioned between the two first connecting boxes 601, the first connecting boxes 601 are obliquely provided with second connecting boxes 602, and the inclination angles of the second connecting boxes 602 are matched with the inclination angle of the hollow rectangular beam 4; a plurality of mounting holes are provided on each of the first connection box 601 and the second connection box 602.
The head ends of the two hollow rectangular beams 4 are respectively inserted into the first connecting piece 5 and fixedly connected with the head ends of the two transverse integral beams 1, and the tail ends of the two hollow rectangular beams 4 are respectively inserted into the second connecting box 602 and fixedly connected with the tail ends of the two transverse integral beams 1.
The first connection box 601 and the second connection box 602 are arranged to facilitate connection of the tail ends of the two hollow rectangular beams 4, and the second connection box 602 is arranged to be an inclined structure to match the inclination angle of the hollow rectangular beams, so as to form a whole, and provide strength for the structure to the greatest extent.
The transverse integral beam 1, the crossed bearing beam 2, the end rib plate 3, the first connecting piece 5 and the second connecting piece 6 are all made of composite materials such as light aluminum alloy, so that the mass can be greatly reduced, and the flight performance of wing spars is improved.
To sum up, the wing spar of the composite wing aircraft in this scheme is used for installing on empty dual-purpose unmanned aerial vehicle of water, crossing carrier bar 2 wholly is hollow structure, great has alleviateed the structural weight of wing, laying of cable can be carried out to hollow beam structure inside, it is clean and tidy orderly to save space again make the overall arrangement, and simultaneously, the anti kink performance of carrier bar has been improved to crossing carrier bar 2 to a great extent, be provided with the trough 8 on crossing carrier bar 2, simple and effectual inside water discharge's problem of depositing of having solved wing spar, tip floor 3 has been increased and can obtain lighter weight under the prerequisite of certain kink intensity is confirmed.
Claims (2)
1. The wing beam of the composite wing aircraft is characterized by comprising two horizontal integral beams which are horizontally arranged in opposite rows, wherein a crossed bearing beam for bearing bending moment is arranged between the two horizontal integral beams, the interior of the crossed bearing beam is of a hollow structure, and the end parts of the crossed bearing beam are fixedly connected with the two horizontal integral beams;
two ends of each transverse integral beam are respectively provided with an end rib plate for bearing the bending moment, and the two transverse integral beams are fixedly connected through the two end rib plates; the crossed bearing beam comprises two hollow rectangular beams with the middle parts crossed and connected; the head end of each hollow rectangular beam is provided with a first connecting piece, the tail end of each hollow rectangular beam is provided with a second connecting piece, and two ends of each hollow rectangular beam are fixedly connected with the inner side walls of the two transverse integral beams through the first connecting pieces and the second connecting pieces respectively; the side wall of each hollow rectangular beam is provided with an oval lightening hole; every the head end inner wall height of cavity rectangular beam all is higher than the inside height of tail end, and the tail end lower surface of every cavity rectangular beam all sets up the water trough rather than inside intercommunication.
2. The wing spar of the composite wing aircraft of claim 1, wherein the cross-sections of the two transverse integral beams are both in an I-shaped structure, and the first connecting piece and the second connecting piece are both arranged in a groove on the inner side surface of the transverse integral beam;
the first connecting piece is of a hollow rectangular box-shaped structure, a plurality of mounting holes are formed in the first connecting piece, the first connecting piece partially exceeds the head ends of the two transverse integral beams, and the first connecting piece is fixedly connected with the inner side faces of the transverse integral beams through the mounting holes; two ends of the end rib plate at the head ends of the two transverse integral beams are fixedly connected with the side surface of the first connecting piece;
the two second connecting pieces are symmetrically arranged, each of the two second connecting pieces comprises a first connecting box fixedly connected with end rib plates positioned at the tail ends of the two transverse integral beams, the end rib plates are positioned between the two first connecting boxes, the first connecting boxes are obliquely provided with second connecting boxes, and the inclination angles of the second connecting boxes are matched with the inclination angles of the hollow rectangular beams; a plurality of mounting holes are formed in the first connecting box and the second connecting box;
the head ends of the two hollow rectangular beams are respectively inserted into the first connecting piece and fixedly connected with the head ends of the two transverse integral beams, and the tail ends of the two hollow rectangular beams are respectively inserted into the second connecting box and fixedly connected with the tail ends of the two transverse integral beams.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210076487.6A CN114104261B (en) | 2022-01-24 | 2022-01-24 | Wing beam of composite wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210076487.6A CN114104261B (en) | 2022-01-24 | 2022-01-24 | Wing beam of composite wing aircraft |
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| Publication Number | Publication Date |
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| CN114104261A CN114104261A (en) | 2022-03-01 |
| CN114104261B true CN114104261B (en) | 2022-04-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210076487.6A Active CN114104261B (en) | 2022-01-24 | 2022-01-24 | Wing beam of composite wing aircraft |
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|---|---|
| CN114104261A (en) | 2022-03-01 |
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