CN114906313B - Connection structure of aircraft fin and fuselage - Google Patents
Connection structure of aircraft fin and fuselage Download PDFInfo
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- CN114906313B CN114906313B CN202210655425.0A CN202210655425A CN114906313B CN 114906313 B CN114906313 B CN 114906313B CN 202210655425 A CN202210655425 A CN 202210655425A CN 114906313 B CN114906313 B CN 114906313B
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- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 description 10
- 238000009434 installation Methods 0.000 description 8
- 238000012546 transfer Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The application relates to the technical field of aircrafts and discloses a connecting structure of an airplane tail wing and an airplane body, which comprises the tail wing, the airplane body and a connecting box, wherein the tail wing comprises a vertical tail and two horizontal tails, the airplane body comprises an airplane body frame and an airplane body wallboard, and the connecting box is fixedly connected to the airplane body wallboard above the airplane body tail; the connecting box comprises a supporting frame, a horizontal tail connecting frame and a vertical tail connecting frame, wherein the supporting beam comprises longitudinal beams parallel to the axis of the machine body, two sides of each longitudinal beam are respectively fixedly connected with cross beams symmetrically distributed on the axis of the machine body, the cross beams are perpendicular to the longitudinal beams and coplanar, the front ends of the longitudinal beams are respectively connected with two ends of the cross beams, the two ends of the cross beams are respectively connected with the horizontal tail connecting frame, the vertical tail connecting frame is connected above the longitudinal beams, the horizontal tail is respectively detachably connected with the corresponding horizontal tail connecting frame, and the vertical tail is detachably connected with the vertical tail connecting frame. The connection of the tail wing and the machine body is safe and reliable, and the stressed load of the tail wing can be uniformly transmitted to the machine body, so that the weight of the machine body is reduced.
Description
Technical Field
The application relates to the technical field of aircrafts, in particular to a connecting structure of an airplane tail wing and an airplane body.
Background
With the rapid development of aviation science and technology, new concepts and new layouts of new aviation aircrafts are layered endlessly. The structural design scheme of the machine body is also improved. The machine body structure realizes the use function with the lightest weight in the set use load range. In conventional designs, the main load transfer path is often first analyzed, and bending, shear and torsional loads are respectively considered or coupled to determine the structural scheme. However, the connecting joint is complicated in structure, various in load direction and difficult in process forming, and the material system is mainly made of metal materials such as aluminum alloy and titanium alloy.
Due to the design of the connection structure of the tail wing and the fuselage of the airplane, civil and commercial airplanes are mainly used for transportation personnel, and the cabin section of the fuselage is often required to be pressurized for simulating the ground air pressure environment. For this purpose, the fuselage cross-section is designed to be circular or approximately circular, converting the surface pressure from the pressurization into tension in the interior of the fuselage skin. The connection design of the fuselage and the tail wing is divided into components, such as the connection of the vertical tail and the upper part of the frame of the fuselage, and the horizontal tail penetrates through the interior of the fuselage and is commonly called as a low horizontal tail; the other is that the machine body is only connected with a vertical tail, and the vertical tail is arranged at the upper part of the machine body and commonly called as a high horizontal tail.
For the aircraft with square fuselage cross section, how safe and reliable is connected the fin with the fuselage, guarantee fin and fuselage are connected and are passed and carry efficiency higher, satisfy structural design adaptability good, safe and reliable, easy dismantlement, easy transportation, easy maintenance, low-cost demand, become the problem that needs to be solved urgently.
Disclosure of Invention
The application provides a connecting structure of an airplane tail body, which aims to solve the problem that a square-section body is safely and reliably connected with the tail body, ensure that load can be uniformly transmitted to the body, improve the convenience of installation and maintenance of the tail body and the body, improve the safety of flight and lighten the weight of the body.
The above-mentioned application purpose of the application is realized through the following technical scheme:
the application relates to a connection structure of an airplane tail wing and a fuselage, which comprises the tail wing, the fuselage and a connection box, wherein the tail wing comprises a vertical tail and two horizontal tails, the fuselage comprises a fuselage frame and a fuselage wall plate, the fuselage wall plate is connected to the outer side of the fuselage frame, and the connection box is fixedly connected to the horizontal fuselage wall plate above the tail part of the fuselage; the connecting box comprises a supporting frame, a horizontal tail connecting frame and a vertical tail connecting frame, wherein the supporting frame is spliced into a grid-shaped frame body through a supporting beam, the supporting beam comprises longitudinal beams parallel to the axis of the machine body, two sides of each longitudinal beam are fixedly connected with cross beams symmetrically distributed on the axis of the machine body respectively, the cross beams are perpendicular to the longitudinal beams and coplanar, the front ends of the longitudinal beams are connected with the two ends of the cross beams respectively, the two ends of the cross beams are connected with the horizontal tail connecting frame respectively, the vertical tail connecting frame is connected above the longitudinal beams, the horizontal tail is detachably connected with the corresponding horizontal tail connecting frame respectively, and the vertical tail is detachably connected with the vertical tail connecting frame.
By adopting the technical scheme, the longitudinal beam is parallel to the axis of the machine body, and the cross beam is perpendicular to the axis of the machine body, so that the support frame is spliced to form a grid-shaped frame body, the strength and rigidity of the support frame are improved, the horizontal tail connecting frames are arranged on two sides of the support frame, and the horizontal tail is detachably connected with the horizontal tail connecting frames; the top of the support frame is provided with a vertical tail connecting frame, and the vertical tail is detachably connected with the vertical tail connecting frame; the load can be uniformly transferred to the machine body, the convenience of installation and maintenance of the machine body and the tail wing is improved, and the weight of the machine body is reduced.
Preferably, the longitudinal beams comprise left longitudinal beams and right longitudinal beams which are parallel to the axis of the machine body and are symmetrically distributed, the cross beams comprise rear cross beams, middle cross beams and front cross beams which are distributed at intervals from back to front on the outer sides of the left longitudinal beams and the right longitudinal beams, the front ends of the left longitudinal beams and the right longitudinal beams are respectively connected with the outer ends of the corresponding front cross beams through oblique beams, and the front ends of the left longitudinal beams and the right longitudinal beams are connected through front connecting beams; the rear ends of the left longitudinal beam and the right longitudinal beam are connected through a rear connecting beam, and the middle parts of the left longitudinal beam and the right longitudinal beam are connected through a middle connecting beam.
Through adopting above-mentioned technical scheme, set up the parallel and symmetric distribution's of fuselage axis left longeron and right longeron, set up rear cross beam, middle cross beam and the front cross beam from the back to the front in the both sides of left longeron and right longeron, the front end of left longeron and right longeron is connected with corresponding front cross beam outer end through the sloping respectively, the latticed framework of support frame concatenation, the intensity and the rigidity of improvement support frame, the weight of lightening the support frame.
Preferably, the horizontal tail connecting frame comprises a first horizontal tail beam, a horizontal tail connecting beam and a second horizontal tail beam, wherein two ends of the first horizontal tail beam are respectively connected with the horizontal tail connecting beam which is inclined backwards, the two horizontal tail connecting beams are parallel to each other, the ends of the two horizontal tail connecting beams are respectively connected with the second horizontal tail beam which is parallel to the first horizontal tail beam, one side of the horizontal tail connecting beam, which is close to the supporting frame, is respectively connected with the corresponding oblique beam and the corresponding rear beam through connecting band plates, the middle part of the first horizontal tail beam is connected with the corresponding rear beam, and the first horizontal tail beam is parallel to the axis of the machine body.
Through adopting above-mentioned technical scheme, the both sides of support frame are connected the horizontal tail link respectively, and two parallel horizontal tail tie-beams on the horizontal tail link can be dismantled with the horizontal tail and be connected, convenient installation and the maintenance of horizontal tail.
Preferably, the horizontal tail connecting beam is in a necking trapezoid from inside to outside.
Through adopting above-mentioned technical scheme, the horizontal tail tie-beam is the trapezoidal of necking down from inside to outside, can reduce the weight of connecting the box, the assembly of horizontal tail connecting portion and horizontal tail tie-beam of being convenient for simultaneously.
Preferably, the vertical tail connecting frame comprises a first vertical tail beam, a vertical tail connecting beam and a second vertical tail beam, wherein the two ends of the first vertical tail beam are respectively connected with the vertical tail connecting beam which is inclined backwards, the two vertical tail connecting beams are mutually parallel, the ends of the vertical tail connecting beam are respectively connected with the second vertical tail beam which is parallel to the first vertical tail beam, the two vertical tail connecting beams are close to one side of the support frame and are respectively connected with the front connecting beam and the middle connecting beam through connecting band plates, and the first vertical tail beam is parallel to a machine body shaft.
Through adopting above-mentioned technical scheme, the support frame top is connected the vertical fin link, and two parallel vertical fin tie-beams on the vertical fin link can be dismantled with the vertical fin and be connected, convenient installation and the maintenance of vertical fin.
Preferably, the horizontal tail comprises a horizontal tail fixing surface and a rear elevator, a horizontal tail connecting part is arranged at the root of the horizontal tail, the horizontal tail connecting part comprises two horizontal tail inserting beams and horizontal tail end ribs, the two horizontal tail inserting beams are parallel and respectively fixedly connected with corresponding spars in the horizontal tail fixing surface, the outer ends of the two horizontal tail inserting beams are connected with each other along one side in the width direction through the horizontal tail end ribs, the two horizontal tail inserting beams are matched with the intervals of the two horizontal tail connecting beams, and the horizontal tail inserting beams are connected with the corresponding horizontal tail connecting beams through bolt assemblies after being inserted.
Through adopting above-mentioned technical scheme, two horizontal tail spliced beams of horizontal tail connecting portion are connected through bolt assembly after inserting two horizontal tail spliced beams of horizontal tail link frame, the installation and the maintenance of the horizontal tail of being convenient for.
Preferably, the vertical fin comprises a vertical fin fixing surface and a rudder behind the vertical fin fixing surface, a vertical fin connecting portion is arranged at a vertical fin root portion, the vertical fin connecting portion comprises two vertical fin inserting beams and vertical fin end ribs, the two vertical fin inserting beams are parallel and respectively fixedly connected with corresponding spar in the vertical fin fixing surface, the outer ends of the two vertical fin inserting beams are connected with each other along one side of the width direction through the vertical fin end ribs, the two vertical fin inserting beams are matched with the distance between the two vertical fin connecting beams, and the vertical fin inserting beams are connected with the corresponding vertical fin connecting beams through bolt assemblies after being inserted.
Through adopting above-mentioned technical scheme, two vertical fin spliced beams of vertical fin connecting portion are connected through bolt assembly after inserting two vertical fin connecting beams of vertical fin connecting frame, the installation and the maintenance of the vertical fin of being convenient for.
Preferably, the frame is stacked and fixedly connected by a plurality of alloy plates, the frame comprises horizontal bearing beams, side beams extending downwards in an arc shape are arranged on two sides of the bearing beams, and the frame is provided with a plurality of spaced frames and gradually reduced from front to back.
Through adopting above-mentioned technical scheme, fuselage frame interval sets up a plurality of and from preceding to back gradual change dwindles, can improve the intensity of fuselage, lightens fuselage weight.
Preferably, the cross section of the supporting beam is C-shaped, the supporting beam comprises a web plate and rib plates, the rib plates are distributed at two ends of the width direction of the web plate, and the two rib plates are perpendicular to the web plate and are located on the same side of the web plate.
Through adopting above-mentioned technical scheme, adopt the cross-section to be C shape supporting beam, supporting beam includes web and floor to can lighten the weight of fuselage to transmit fin load to fuselage upper wall plate and fuselage frame.
Preferably, the left longitudinal beam and the right longitudinal beam are respectively connected with the front connecting beam, the middle connecting beam and the rear connecting beam through angle boxes between the adjacent supporting beams.
Through adopting above-mentioned technical scheme, between the adjacent supporting beam, left longeron and right longeron are connected through the angle box respectively with preceding tie-beam, well tie-beam and back tie-beam between, can improve the intensity of support frame, make things convenient for the installation and the maintenance of support frame
In summary, the beneficial technical effects of the application are as follows:
according to the application, the connecting box is arranged, and the connecting box, the vertical tail and the horizontal tail form a whole body, so that the load is transmitted to the machine body together, and the effect of maintaining the balance of the flight state of the aircraft is achieved; the support frame is spliced into the grid-shaped frame body through the support beam, the strength and the rigidity of the connecting box are improved, aerodynamic force generated by the vertical tail and the horizontal tail is transferred to the body wall plate on the upper portion of the body through the connecting box, the force transfer path is simple, the force transfer efficiency is high, the load can be guaranteed to be uniformly transferred to the body, the convenience of installation and maintenance is improved, the safety of flying is improved, and the weight of the body is reduced.
Drawings
FIG. 1 is a schematic diagram of the structure of the present application;
FIG. 2 is a schematic view of the structure of the junction box of the present application;
FIG. 3 is a schematic view of the structure of the support beam of the present application;
FIG. 4 is a schematic view of the structure of the present application with fuselage panels removed;
FIG. 5 is a schematic view of the structure of the present application with the upper skin removed from the horizontal tail;
FIG. 6 is a schematic view of the structure of the vertical fin removed skin of the present application.
The diagram is 1, a tail wing; 11. a horizontal tail; 111. a horizontal tail fixing surface; 112. an elevator; 113. a horizontal tail connection part; 1131. a horizontal tail plug-in beam; 1132. a horizontal tail end rib; 12. a vertical tail; 121. a vertical tail fixing surface; 122. a rudder; 123. a vertical tail connecting part; 1231. a vertical tail plug-in beam; 1232. a vertical tail end rib; 2. a body; 21. a fuselage frame; 211. a load beam; 212. a side beam; 22. a fuselage panel; 3. a connection box; 4. a support frame; 41. a support beam; 41a, a web; 41b, rib plates; 411. a longitudinal beam; 4111. a left longitudinal beam; 4112. a right longitudinal beam; 412. a cross beam; 4121. a rear cross member; 4122. a middle cross beam; 4123. a front cross member; 413. a sloping beam; 414. a front connecting beam; 415. a middle connecting beam; 416. a rear connection beam; 5. a horizontal tail connecting frame; 51. a first flat tail boom; 52. a horizontal tail connecting beam; 53. a second flat tail boom; 6. a vertical tail connecting frame; 61. a first vertical tail boom; 62. a vertical tail connecting beam; 63. a second vertical tail boom; 7. connecting the band plates; 8. a corner box; 9. a spar; 91. tail rib.
Detailed Description
The application is described in further detail below with reference to fig. 1-6.
As shown in fig. 1 and 2, a connection structure of an aircraft tail wing and an aircraft body comprises a tail wing 1, an aircraft body 2 and a connection box 3, wherein the tail wing 1 comprises a vertical tail 12 and two horizontal tails 11, the aircraft body 2 comprises an aircraft body frame 21 and an aircraft body wallboard 22, the aircraft body wallboard 22 is connected to the outer side of the aircraft body frame 21, and the connection box 3 is fixedly connected to the aircraft body wallboard 22 above the tail part of the aircraft body 2; the connection box 3 comprises a support frame 4, a horizontal tail connection frame 5 and a vertical tail connection frame 6, wherein the support frame 4 is spliced into a grid-shaped frame body through a support beam 41, the support beam 41 comprises longitudinal beams 411 parallel to the axis of the machine body 2, two sides of each longitudinal beam 411 are respectively fixedly connected with cross beams 412 symmetrically distributed on the axis of the machine body 2, the longitudinal beams 411 are perpendicular to the longitudinal beams 411 and coplanar, the front ends of the longitudinal beams 411 and two ends of the cross beams 412 are respectively connected with oblique beams 413, two ends of each cross beam 412 are respectively connected with the horizontal tail connection frame 5, the vertical tail connection frame 6 is connected above the longitudinal beams 411, the horizontal tail 11 is respectively detachably connected with the corresponding horizontal tail connection frame 5, and the vertical tail 12 is detachably connected with the vertical tail connection frame 6. The cross beam 412 can balance the aerodynamic force of the horizontal tail 11 relative to the bending shear of the root of the horizontal tail 11, and can also transmit and diffuse the aerodynamic force of the vertical tail 12 to the frame 21 above the tail of the fuselage 2. The longitudinal beams 411 and the transverse beams 412 form a closed grid-shaped torsion box, so that torsional load of the vertical tail 12 rudder 122 can be conveniently transferred to the machine body 2; the diagonal beams 413 may provide inertial force support for the vertical tail 12 and horizontal tail 11.
As shown in fig. 3, the cross section of the support beam 41 of this embodiment is C-shaped, and the same mold can be used to realize mass production, and the support beam 41 is cut to a desired size, and includes a web 41a and rib plates 41b, wherein the rib plates 41b are distributed at both ends of the web 41a in the width direction, and the two rib plates 41b are perpendicular to the web 41a and are located on the same side of the web 41 a. The structural support beam 41 can better transfer the load of the tail wing 1 to the upper wall plate of the fuselage 2 and the fuselage frame 21. Of course, the support beam 41 may have an "i" shaped cross section.
The application is based on an aircraft with a square fuselage 2 in cross section, the fuselage wall 22 of which is straight, which effectively increases the space in the fuselage cell.
The vertical fin 12 and the horizontal fin 11 are made of composite materials and are provided with a double-spar 9 multi-fin rib 91 structure. The wing and tail rib 91 serves as the primary aerodynamic force collecting member to transfer loads to the spar 9, and the spar 9 serves as the primary load carrying structure to transfer loads to the junction box 3. The connecting box forms a whole with the vertical tail 12 and the horizontal tail 11, and transmits the load to the machine body 2 together, thereby playing a role in maintaining the balance of the flight state of the aircraft.
As shown in fig. 2, the stringers 411 of the present embodiment include a left stringer 4111 and a right stringer 4112 which are parallel to the axis of the fuselage 2 and symmetrically distributed, and the cross member 412 includes a rear cross member 4121, a middle cross member 4122 and a front cross member 4123 which are spaced from the outside of the left stringer 4111 and the right stringer 4112 from the rear to the front, and the front ends of the left stringer 4111 and the right stringer 4112 are respectively connected to the outer ends of the corresponding front cross member 4123 by a diagonal member 413, and the front ends of the left stringer 4111 and the right stringer 4112 are connected by a front connecting member 414; the rear ends of the left side member 4111 and the right side member 4112 are connected by a rear connecting beam 416, and the middle portions of the left side member 4111 and the right side member 4112 are connected by a middle connecting beam 415. The rear connecting beam 416 and the rear cross beam 4121 may be integrally formed, and two intermediate connecting beams 415 are provided in this embodiment. The left longitudinal beam 4111 and the right longitudinal beam 4112 are connected with the front connecting beam 414, the middle connecting beam 415 and the rear connecting beam 416 between the adjacent supporting beams 41 through the corner boxes 8, and the grid-shaped frame body of the connecting box 3 can bear complex pulling loads and is convenient to install and detach.
As shown in fig. 2, the horizontal tail connecting frame 5 of the present embodiment includes a first horizontal tail beam 51, a horizontal tail connecting beam 52 and a second horizontal tail beam 53, both ends of the first horizontal tail beam 51 are respectively connected with the horizontal tail connecting beam 52 inclined backward, the two horizontal tail connecting beams 52 are parallel to each other, the ends of the two horizontal tail connecting beams 52 are respectively connected with the second horizontal tail beam 53 parallel to the first horizontal tail beam 51, one side of the two horizontal tail connecting beams 52 close to the supporting frame 4 is respectively connected with the corresponding diagonal beam 413 and the rear cross beam 4121 through the connecting band plate 7, the middle part of the first horizontal tail beam 51 is connected with the corresponding rear cross beam 4121, and the first horizontal tail beam 51 is parallel to the axis of the machine body 2.
The horizontal tail connecting beam 52 is in a necking trapezoid from inside to outside, so that the weight of the support frame 4 can be reduced, and the assembly or maintenance of the horizontal tail inserting beam 1131 and the horizontal tail connecting beam 52 is facilitated.
As shown in fig. 2, the vertical tail connecting frame 6 includes a first vertical tail beam 61, a vertical tail connecting beam 62 and a second vertical tail beam 63, two ends of the first vertical tail beam 61 are respectively connected with the vertical tail connecting beam 62 inclined backward, the two vertical tail connecting beams 62 are parallel to each other, ends of the two vertical tail connecting beams 62 are respectively connected with the second vertical tail beam 63 parallel to the first vertical tail beam 61, one side of the two vertical tail connecting beams 62 close to the supporting frame 4 is respectively connected with the front connecting beam 414 and the middle connecting beam 415 through connecting band plates 7, and the first vertical tail beam 61 is parallel to the axis of the machine body 2.
As shown in fig. 4 and 5, the horizontal tail 11 includes a horizontal tail fixing surface 111 and a rear elevator 112, the root of the horizontal tail 11 is provided with a horizontal tail connecting portion 113, the horizontal tail connecting portion 113 includes two horizontal tail inserting beams 1131 and a horizontal tail end rib 1132, the two horizontal tail inserting beams 1131 are parallel and respectively fixedly connected with the corresponding spar 9 in the horizontal tail fixing surface 111, the outer ends of the two horizontal tail inserting beams 1131 are connected through the horizontal tail end rib 1132 along one side in the width direction, and the horizontal tail end rib 1132 can improve the strength of the horizontal tail connecting portion 113; the horizontal tail end ribs 1132 may also be disposed on two sides of the outer ends of the two horizontal tail inserting beams 1131 along the width direction, so long as the channels for inserting the horizontal tail inserting beams 1131 and the horizontal tail connecting beams 52 are avoided; the spacing between the two horizontal tail inserting beams 1131 and the two horizontal tail connecting beams 52 is adapted, and the horizontal tail inserting beams 1131 are connected with the corresponding horizontal tail connecting beams 52 through bolt assemblies after being inserted.
As shown in fig. 4 and 6, the vertical tail 12 includes a vertical tail fixing surface 121 and a rudder 122 behind the vertical tail fixing surface, a vertical tail connecting portion 123 is provided at the root of the vertical tail 12, the vertical tail connecting portion 123 includes two vertical tail inserting beams 1231 and a vertical tail rib 1232, the two vertical tail inserting beams 1231 are parallel and respectively fixedly connected with corresponding spar in the vertical tail fixing surface 121, the outer ends of the two vertical tail inserting beams 1231 are connected by the vertical tail rib 1232 along one side in the width direction, and the vertical tail rib 1232 can improve the strength of the vertical tail connecting portion 123; the vertical tail end ribs 1232 can also be arranged at two sides of the outer ends of the two vertical tail inserting beams 1231 along the width direction, so long as a passage for inserting the vertical tail inserting beams 1231 and the vertical tail connecting beam 62 is avoided; the two vertical fin plug beams 1231 are adapted to the distance between the two vertical fin connection beams 62, and the vertical fin plug beams 1231 are connected with the corresponding vertical fin connection beams 62 by means of bolt assemblies after being plugged.
As shown in fig. 5 and 6, two parallel wing beams 9 are respectively arranged in the vertical tail fixing surface 121 and the horizontal tail fixing surface 111, a plurality of tail ribs 91 connected between the two wing beams 9 form a main bearing structure of the tail wing 1, the main bearing structure is connected with the connecting box 3 through the vertical tail connecting part 123 and the horizontal tail connecting part 113, and a body wall plate 22 at the upper part of the body 2 forms an integral force transmission structure, so that the force transmission path is concise and the force transmission efficiency is high. The tail wing 1 is connected with the connecting box 3, so that the safety and the reliability are high, and meanwhile, the maintainability and the detachability are both considered. The spar 9, the horizontal tail connecting part 113, the vertical tail connecting part 123, the horizontal tail connecting frame 5, the vertical tail connecting frame 6 and the supporting frame 4 are connected with each other, and an integral force transmission structure is formed on the surface of the wall plate 22 above the tail part of the fuselage 2.
As shown in fig. 4, the frame 21 is formed by stacking and fixedly connecting a plurality of high-strength alloy plates, the frame 21 comprises a horizontal bearing beam 211, two sides of the bearing beam 211 are provided with side beams 212 extending downwards in an arc shape, and the frame 21 is provided with a plurality of spaced frames and gradually reduced from front to back. The frame 21 is a C-shaped metal member with a downward opening, the opening of the frame 21 is the opening boundary of the frame, the downward extension can be used for loading goods, and the frame 21 can be made of aluminum or titanium alloy materials.
The fuselage wall plate 22 and the fuselage frame 21 can transmit loads to the fuselage 2, so that the safety of the aircraft in flight is ensured.
The vertical fin 12, the horizontal fin 11, the longitudinal beam 411, the cross beam 412, the diagonal beam 413 and the fuselage wall panel 22 of the present embodiment are all made of fiber reinforced resin composite materials, and have the characteristics of high strength and light weight. The corner box 8 and the connecting band plate 7 are made of metal materials, so that the connection strength of the connecting box 3 is improved.
The embodiments of the present application are all preferred embodiments of the present application, and are not intended to limit the scope of the present application in this way, therefore: all equivalent changes in structure, shape and principle of the application should be covered in the scope of protection of the application.
Claims (9)
1. The connecting structure of the airplane tail wing and the airplane body is characterized by comprising the tail wing (1), the airplane body (2) and a connecting box (3), wherein the tail wing (1) comprises a vertical tail (12) and two horizontal tails (11), the airplane body (2) comprises an airplane body frame (21) and an airplane body wall plate (22), the airplane body wall plate (22) is connected to the outer side of the airplane body frame (21), and the connecting box (3) is fixedly connected to the airplane body wall plate (22) horizontally above the tail part of the airplane body (2); the connecting box (3) comprises a supporting frame (4), a horizontal tail connecting frame (5) and a vertical tail connecting frame (6), wherein the supporting frame (4) is spliced into a grid-shaped frame body through a supporting beam (41), the supporting beam (41) comprises longitudinal beams (411) parallel to the axis of the machine body (2), two sides of each longitudinal beam (411) are fixedly connected with cross beams (412) symmetrically distributed on the axis of the machine body (2) respectively, the cross beams (412) are perpendicular to the longitudinal beams (411) and coplanar, the front ends of the longitudinal beams (411) are connected with two ends of the cross beams (412) respectively, the two ends of the cross beams (412) are connected with the horizontal tail connecting frame (5) respectively, the vertical tail connecting frame (6) is connected above the longitudinal beams (411), the horizontal tail (11) is detachably connected with the corresponding horizontal tail connecting frame (5) respectively, and the vertical tail (12) is detachably connected with the vertical tail connecting frame (6).
The longitudinal beams (411) comprise left longitudinal beams (4111) and right longitudinal beams (4112) which are parallel to the axis of the machine body (2) and symmetrically distributed, the cross beams (412) comprise rear cross beams (4121), middle cross beams (4122) and front cross beams (4123) which are distributed at intervals from back to front outside the left longitudinal beams (4111) and the right longitudinal beams (4112), the front ends of the left longitudinal beams (4111) and the right longitudinal beams (4112) are respectively connected with the outer ends of the corresponding front cross beams (4123) through oblique beams (413), and the front ends of the left longitudinal beams (4111) and the right longitudinal beams (4112) are connected through front connecting beams (414); the rear ends of the left longitudinal beam (4111) and the right longitudinal beam (4112) are connected through a rear connecting beam (416), and the middle parts of the left longitudinal beam (4111) and the right longitudinal beam (4112) are connected through a middle connecting beam (415).
2. The connection structure of an aircraft tail wing and a fuselage according to claim 1, wherein the horizontal tail connection frame (5) comprises a first horizontal tail beam (51), a horizontal tail connection beam (52) and a second horizontal tail beam (53), two ends of the first horizontal tail beam (51) are respectively connected with the horizontal tail connection beam (52) inclined backwards, the two horizontal tail connection beams (52) are parallel to each other, end parts of the two horizontal tail connection beams (52) are respectively connected with the second horizontal tail beam (53) parallel to the first horizontal tail beam (51), one side of the two horizontal tail connection beams (52) close to the support frame (4) is respectively connected with the corresponding oblique beam (413) and the rear cross beam (4121) through connection band plates (7), the middle part of the first horizontal tail beam (51) is connected with the corresponding rear cross beam (4121), and the first horizontal tail beam (51) is parallel to the axis of the fuselage (2).
3. The aircraft tail to fuselage connection of claim 2, wherein the horizontal tail connection beams (52) are necked down from inside to outside.
4. The connection structure of an aircraft tail wing and a fuselage according to claim 1, wherein the vertical tail connection frame (6) comprises a first vertical tail beam (61), a vertical tail connection beam (62) and a second vertical tail beam (63), two vertical tail connection beams (62) which are inclined backwards are respectively connected to two ends of the first vertical tail beam (61), two vertical tail connection beams (62) are parallel to each other, two vertical tail connection beams (63) which are parallel to the first vertical tail beam (61) are respectively connected to the ends of the two vertical tail connection beams (62), one side of the vertical tail connection beam (62) close to the support frame (4) is respectively connected with a front connection beam (414) and a middle connection beam (415) through connection band plates (7), and the first vertical tail beam (61) is parallel to the axis of the fuselage (2).
5. The connection structure of an aircraft tail wing and a fuselage according to claim 2, wherein the horizontal tail (11) comprises a horizontal tail fixing surface (111) and a rear elevator (112), a horizontal tail connecting portion (113) is arranged at the root of the horizontal tail (11), the horizontal tail connecting portion (113) comprises two horizontal tail inserting beams (1131) and a horizontal tail rib (1132), the two horizontal tail inserting beams (1131) are parallel and are respectively fixedly connected with corresponding spars in the horizontal tail fixing surface (111), one side of the outer end of each horizontal tail inserting beam (1131) in the width direction is connected with the corresponding horizontal tail connecting beam (52) through a horizontal tail end rib (1132), the two horizontal tail inserting beams (1131) are matched with the interval between the two horizontal tail connecting beams (52), and the horizontal tail inserting beams (1131) are connected with the corresponding horizontal tail connecting beams (52) through bolt assemblies after being inserted.
6. The connection structure of an aircraft tail wing and a fuselage according to claim 4, wherein the vertical tail (12) comprises a vertical tail fixing surface (121) and a rudder (122) behind the vertical tail fixing surface, a vertical tail connecting portion (123) is arranged at the root of the vertical tail (12), the vertical tail connecting portion (123) comprises two vertical tail inserting beams (1231) and a vertical tail end rib (1232), the two vertical tail inserting beams (1231) are parallel and respectively fixedly connected with corresponding spars in the vertical tail fixing surface (121), the outer ends of the two vertical tail inserting beams (1231) are connected with each other along one side in the width direction through vertical tail end ribs (1232), the two vertical tail inserting beams (1231) are matched with the intervals of the two vertical tail connecting beams (62), and the vertical tail inserting beams (1231) are connected with the corresponding vertical tail connecting beams (62) through bolt assemblies after being inserted.
7. The connection structure of an aircraft tail and an aircraft fuselage according to claim 1, wherein the fuselage frame (21) is fixedly connected by stacking a plurality of alloy plates, the fuselage frame (21) comprises horizontal bearing beams (211), side beams (212) extending downwards in an arc shape are arranged on two sides of the bearing beams (211), and the fuselage frame (21) is provided with a plurality of spaced side beams and gradually reduced from front to back.
8. The structure for connecting an aircraft tail with a fuselage according to claim 1, wherein the cross section of the supporting beam (41) is C-shaped, the supporting beam (41) comprises a web (41 a) and ribs (41 b), the ribs (41 b) are distributed at two ends of the web (41 a) in the width direction, and two ribs (41 b) are perpendicular to the web (41 a) and are located at the same side of the web (41 a).
9. The connection structure of an aircraft tail to a fuselage according to claim 1, wherein between adjacent support beams (41), the left side member (4111) and the right side member (4112) are connected to a front connection beam (414), a middle connection beam (415), and a rear connection beam (416), respectively, by corner boxes (8).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210655425.0A CN114906313B (en) | 2022-06-10 | 2022-06-10 | Connection structure of aircraft fin and fuselage |
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| CN202210655425.0A CN114906313B (en) | 2022-06-10 | 2022-06-10 | Connection structure of aircraft fin and fuselage |
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| CN114906313A CN114906313A (en) | 2022-08-16 |
| CN114906313B true CN114906313B (en) | 2023-11-10 |
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| CN115520370A (en) * | 2022-09-22 | 2022-12-27 | 中国商用飞机有限责任公司 | Wing system integrated with power battery module and electric airplane |
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|---|---|---|---|---|
| CN102105353A (en) * | 2008-06-27 | 2011-06-22 | 空客运营有限公司 | Structure of an aircraft aerofoil |
| CN113306699A (en) * | 2021-01-15 | 2021-08-27 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Connecting structure and method for horizontal tail and vertical tail of T-tail layout aircraft |
| CN214648983U (en) * | 2021-04-16 | 2021-11-09 | 常州启赋安泰复合材料科技有限公司 | Connection structure of wing and body of light airplane |
| CN113955080A (en) * | 2021-11-29 | 2022-01-21 | 中国商用飞机有限责任公司 | Balance type horizontal tail connecting structure |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004025946A (en) * | 2002-06-24 | 2004-01-29 | Honda Motor Co Ltd | Wing structure of aircraft |
| FR2872782B1 (en) * | 2004-07-08 | 2007-10-05 | Airbus France Sas | FLOOR FOR AIRCRAFT |
| EP2832636A1 (en) * | 2013-07-30 | 2015-02-04 | Airbus Operations S.L. | Rear fuselage section of an aircraft |
| FR3020347B1 (en) * | 2014-04-28 | 2016-05-20 | Airbus Operations Sas | METHOD FOR ASSEMBLING A REAR AIRCRAFT PART |
| EP3015361A1 (en) * | 2014-10-30 | 2016-05-04 | Airbus Operations, S.L. | Central area arrangement for continuous horizontal tail plane torsion box |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102105353A (en) * | 2008-06-27 | 2011-06-22 | 空客运营有限公司 | Structure of an aircraft aerofoil |
| CN113306699A (en) * | 2021-01-15 | 2021-08-27 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Connecting structure and method for horizontal tail and vertical tail of T-tail layout aircraft |
| CN214648983U (en) * | 2021-04-16 | 2021-11-09 | 常州启赋安泰复合材料科技有限公司 | Connection structure of wing and body of light airplane |
| CN113955080A (en) * | 2021-11-29 | 2022-01-21 | 中国商用飞机有限责任公司 | Balance type horizontal tail connecting structure |
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