CN114906313A - Connection structure of aircraft empennage and fuselage - Google Patents
Connection structure of aircraft empennage and fuselage Download PDFInfo
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- CN114906313A CN114906313A CN202210655425.0A CN202210655425A CN114906313A CN 114906313 A CN114906313 A CN 114906313A CN 202210655425 A CN202210655425 A CN 202210655425A CN 114906313 A CN114906313 A CN 114906313A
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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
- 238000013461 design Methods 0.000 description 6
- 238000012546 transfer 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
- 230000006978 adaptation Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
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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
Abstract
The application relates to the technical field of aircrafts, and discloses a connection structure of an airplane empennage and a fuselage, which comprises an empennage, a fuselage and a connection box, wherein the empennage comprises a vertical tail and two horizontal tails; the connecting box comprises a supporting frame, a horizontal tail connecting frame and a vertical tail connecting frame, the supporting beam comprises a longitudinal beam parallel to the axis of the machine body, the two sides of the 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 beam and coplanar, the front end of each longitudinal beam and the two ends of each cross beam are connected with an oblique beam respectively, the two ends of each cross beam are connected with the horizontal tail connecting frame respectively, the vertical tail connecting frame is connected above the longitudinal beam, 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. The empennage is connected with the machine body safely and reliably, the stressed load of the empennage can be uniformly transmitted to the machine body, and the weight of the machine body is reduced.
Description
Technical Field
The application relates to the technical field of aircrafts, in particular to a connection structure of an airplane empennage and an airplane body.
Background
With the rapid development of aviation science and technology, new concepts and new layouts of novel aviation aircrafts emerge endlessly. The design scheme of the machine body structure is also new. The machine body structure realizes the use function with the lightest weight within the set use load range. In conventional designs, the load principal force transfer path is often first analyzed to determine the structural solution by considering or coupling the bending, shearing and torsional loads, respectively, into the design. However, the connecting joint is difficult to form by a process due to complex structure, various loading directions and difficult process, and the material system of the connecting joint still mainly adopts metal materials such as aluminum alloy, titanium alloy and the like.
The connection structure design of the empennage and the fuselage of the civil and commercial aircraft is mainly used for transporting personnel, and the fuselage cabin section usually needs pressurization design in order to simulate the ground air pressure environment. For this purpose, the fuselage cross section is designed to be circular or approximately circular, which converts the surface pressure resulting from the pressurization into a tension in the interior of the fuselage skin. Therefore, the connection of the machine body and the empennage is designed into a split type, if a vertical tail is connected with the upper part of a machine body frame, and a horizontal tail penetrates through the interior of the machine body, which is commonly called as a low horizontal tail; the other is that the machine body is only connected with a vertical fin which is arranged at the upper part of the machine body and is commonly called a high horizontal fin.
To the aircraft that the fuselage cross-section is square, how safe and reliable is connected fin and fuselage, guarantee that fin and fuselage are connected and carry the efficiency higher, satisfy structural design adaptability good, safe and reliable, quick detachable, easy transportation, easy maintenance, low-cost demand, become the problem that awaits the opportune moment and solve.
Disclosure of Invention
In order to solve the problem that the fuselage with a square section is safely and reliably connected with the empennage, the load can be uniformly transmitted to the fuselage, the convenience of installation and maintenance of the empennage and the fuselage is improved, the safety of flight is improved, and the weight of the fuselage is reduced, the application provides a connection structure of the fuselage of the airplane empennage.
The above application purpose of the present application is achieved by the following technical solutions:
the connection structure of the airplane empennage and the airplane body comprises the empennage, the airplane body and the connection box, wherein the empennage comprises a vertical tail and two horizontal tails, the airplane body comprises an airplane body frame and an airplane body wall plate, the airplane body wall plate is connected to the outer side of the airplane body frame, and the connection box is fixedly connected to the horizontal airplane body wall plate above the tail of the airplane body; the connecting box includes support frame, horizontal tail link and vertical tail link, the support frame splices into latticed framework through a supporting beam, a supporting beam includes the longeron parallel with the fuselage axis, the longeron both sides link firmly respectively with the crossbeam of fuselage axis symmetric distribution, the perpendicular longeron of crossbeam and coplane, the sloping is connected respectively with the both ends of crossbeam to the longeron front end, the horizontal tail link is connected respectively at the both ends of crossbeam, the vertical tail link is connected to the longeron top, the horizontal tail can be dismantled with corresponding horizontal tail link respectively and be connected, the vertical tail can be dismantled with the vertical tail link and be connected.
By adopting the technical scheme, the longitudinal beams are parallel to the axis of the machine body, the cross beams are perpendicular to the axis of the machine body, so that the support frames are spliced into a latticed frame body, the strength and the rigidity of the support frames are improved, the horizontal tail connecting frames are arranged on two sides of the support frames, and the horizontal tails are 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 transmitted to the machine body, the installation and maintenance convenience of the machine body and the empennage is improved, and the weight of the machine body is reduced.
Preferably, the longitudinal beams comprise a left longitudinal beam and a right longitudinal beam which are parallel to the axis of the machine body and are symmetrically distributed, the cross beams comprise a rear cross beam, a middle cross beam and a front cross beam which are distributed on the outer sides of the left longitudinal beam and the right longitudinal beam at intervals from back to front, the front ends of the left longitudinal beam and the right longitudinal beam are respectively connected with the outer ends of the corresponding front cross beams through oblique beams, and the front ends of the left longitudinal beam and the right longitudinal beam are connected through a front connecting beam; 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.
By adopting the technical scheme, the left longitudinal beam and the right longitudinal beam are arranged, the axes of the machine body are parallel and symmetrically distributed, the rear cross beam, the middle cross beam and the front cross beam are arranged on the two sides of the left longitudinal beam and the right longitudinal beam from back to front, the front ends of the left longitudinal beam and the right longitudinal beam are respectively connected with the outer ends of the corresponding front cross beams through the oblique beams, the supporting frames are spliced into the latticed frame body, the strength and the rigidity of the supporting frames are improved, and the weight of the supporting frames is reduced.
Preferably, the horizontal tail connecting frame comprises a first horizontal tail beam, a horizontal tail connecting beam and a second horizontal tail beam, two ends of the first horizontal tail beam are respectively connected with the horizontal tail connecting beam inclined backwards, the two horizontal tail connecting beams are parallel to each other, the end parts of the two horizontal tail connecting beams are respectively connected with the second horizontal tail beam parallel to the first horizontal tail beam, one side, close to the supporting frame, of the two horizontal tail connecting beams is respectively connected with the corresponding oblique beam and the corresponding rear cross beam through connecting belt plates, the middle part of the first horizontal tail beam is connected with the corresponding rear cross beam, and the first horizontal tail beam is parallel to the axis of the fuselage.
Through adopting above-mentioned technical scheme, the horizontal tail link span is connected respectively to the both sides of support frame, and the horizontal tail tie-beam of two parallels on the horizontal tail link span can be dismantled with the horizontal tail and be connected, makes things convenient for the 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 box, the assembly of the horizontal tail connecting portion of being convenient for simultaneously and horizontal tail tie-beam.
Preferably, the vertical tail connecting frame comprises a first vertical tail beam, a vertical tail connecting beam and a second vertical tail beam, the vertical tail connecting beam inclined backwards is connected to the two ends of the first vertical tail beam respectively, the vertical tail connecting beam is parallel to the vertical tail connecting beam, the vertical tail connecting beam is parallel to the first vertical tail beam, the end portion of the vertical tail connecting beam is connected with the second vertical tail beam parallel to the first vertical tail beam respectively, the vertical tail connecting beam is connected with the front connecting beam and the middle connecting beam through a connecting band plate on one side close to the support frame, and the first vertical tail beam is parallel to the machine body shaft.
Through adopting above-mentioned technical scheme, the vertical fin link is connected to the support frame top, and the vertical fin tie-beam of two parallels on the vertical fin link can be dismantled with the vertical fin and be connected, makes things convenient for the installation and the maintenance of vertical fin.
Preferably, the horizontal tail includes the elevator behind horizontal tail stationary plane and the horizontal tail fixed surface, the horizontal tail root is equipped with horizontal tail connecting portion, horizontal tail connecting portion include two horizontal tail grafting roof beams and horizontal tail end rib, two horizontal tail grafting roof beam is parallel and links firmly with corresponding spar in the horizontal tail stationary plane respectively, two horizontal tail grafting roof beam outer end is connected through horizontal tail end rib along width direction one side, two horizontal tail grafting roof beam and two horizontal tail connecting beam's interval adaptation, horizontal tail grafting roof beam is connected through bolt assembly with corresponding horizontal tail connecting beam after the interpolation.
Through adopting above-mentioned technical scheme, two horizontal tail splicing beams of horizontal tail connecting portion are inserted with two horizontal tail splicing beams of horizontal tail link and are closed the back and pass through bolt assembly and connect, the installation and the maintenance of the horizontal tail of being convenient for.
Preferably, the vertical fin includes the rudder behind vertical fin fixed surface and the vertical fin, the vertical fin root is equipped with vertical fin connecting portion, vertical fin connecting portion include two vertical fin grafting roof beams and vertical fin end rib, two the parallel corresponding spar that just links firmly in the fixed surface with the vertical fin respectively of vertical fin grafting roof beam links firmly two the outer end of vertical fin grafting roof beam is connected through vertical fin end rib along width direction one side, two the interval adaptation of vertical fin grafting roof beam and two vertical fin connecting beams, the vertical fin grafting roof beam is connected through bolt assembly with corresponding vertical fin connecting beam after the interpolation.
Through adopting above-mentioned technical scheme, two vertical fin splicing beams of vertical fin connecting portion are inserted with two vertical fin connecting beams of vertical fin link and are closed the back and be connected through bolt assembly, the installation and the maintenance of the vertical fin of being convenient for.
Preferably, the machine body frame is fixedly connected by a plurality of alloy plates in an overlapping mode, the machine body frame comprises a horizontal bearing beam, side beams extending downwards in an arc shape are arranged on two sides of the bearing beam, and the machine body frame is arranged at intervals and gradually reduced from front to back.
By adopting the technical scheme, the plurality of machine body frames are arranged at intervals and gradually reduced from front to back, so that the strength of the machine body can be improved, and the weight of the machine body is reduced.
Preferably, the cross section of the support beam is C-shaped, the support beam comprises a web plate and rib plates, the rib plates are distributed at two ends of the web plate in the width direction, and the two rib plates are perpendicular to the web plate and are positioned at the same side of the web plate.
By adopting the technical scheme, the cross section of the supporting beam is C-shaped, and the supporting beam comprises the web plate and the rib plate, so that the weight of the fuselage can be reduced, and the tail wing load is transferred to the upper wall plate and the fuselage frame of the fuselage.
Preferably, between adjacent supporting beams, 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.
Through adopting above-mentioned technical scheme, between the adjacent supporting beam, left longeron and right longeron are connected through the angle box between with preceding tie-beam, well tie-beam and the back tie-beam respectively, can improve the intensity of support frame, make things convenient for the installation and the maintenance of support frame
To sum up, the beneficial technical effect of this application does:
the connecting box is arranged, the connecting box, the vertical tail and the horizontal tail form a whole, and loads are transmitted to the airplane body together, so that the effect of maintaining the balance of the airplane flight state is achieved; the support frame splices into latticed framework through a supporting beam, improves the intensity and the rigidity of connecting box, and the aerodynamic force that the peaceful tail of vertical tail produced passes through the connecting box and transmits to fuselage upper portion horizontally fuselage wallboard, and it is simple to pass the power route, and it is efficient to pass power, guarantees that the load can evenly transmit for the fuselage, improves the convenience of installation maintenance, improves the security of flight, alleviates the weight of organism.
Drawings
FIG. 1 is a schematic structural diagram of the present application;
FIG. 2 is a schematic view of a junction box of the present application;
FIG. 3 is a schematic structural view of a support beam according to the present application;
FIG. 4 is a schematic illustration of the present application with the fuselage panels removed;
FIG. 5 is a schematic structural view of the present application with the upper skin removed at the butt end;
FIG. 6 is a schematic view of the present application with one side skin removed.
Figure, 1, tail; 11. flattening the tail; 111. a horizontal tail fixing surface; 112. an elevator; 113. a horizontal tail connecting part; 1131. a flat tail is spliced with the beam; 1132. a butt end rib; 12. hanging a tail; 121. a vertical fin fixing surface; 122. a rudder; 123. a vertical fin connecting part; 1231. a vertical tail spliced beam; 1232. a vertical tail end rib; 2. a body; 21. a body frame; 211. a bearing 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, a rib plate; 411. a stringer; 4111. a left stringer; 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. an oblique beam; 414. a front connecting beam; 415. a middle connecting beam; 416. a rear connecting beam; 5. a horizontal tail connecting frame; 51. a first flat tail beam; 52. a horizontal tail connecting beam; 53. a second flat tail beam; 6. a vertical tail connecting frame; 61. a first trailing beam; 62. the vertical tail is connected with the beam; 63. a second trailing beam; 7. connecting the band plate; 8. a corner box; 9. a spar; 91. and a tail rib.
Detailed Description
The present application is described in further detail below with reference to figures 1-6.
As shown in fig. 1 and 2, a connection structure of an airplane empennage and a fuselage comprises an empennage 1, a fuselage 2 and a connection box 3, wherein the empennage 1 comprises a vertical tail 12 and two horizontal tails 11, the fuselage 2 comprises a fuselage frame 21 and a fuselage wall plate 22, the fuselage wall plate 22 is connected to the outer side of the fuselage frame 21, and the connection box 3 is fixedly connected to the fuselage wall plate 22 horizontally above the tail of the fuselage 2; the connecting box 3 comprises a supporting frame 4, a horizontal tail connecting frame 5 and a vertical tail connecting frame 6, the supporting frame 4 is spliced into a latticed frame body through a supporting beam 41, the supporting beam 41 comprises a longitudinal beam 411 parallel to the axis of the machine body 2, the two sides of the longitudinal beam 411 are fixedly connected with a cross beam 412 symmetrically distributed to the axis of the machine body 2 respectively, the cross beam 412 is perpendicular to the longitudinal beam 411 and coplanar, an oblique beam 413 is respectively connected with the two ends of the front end of the longitudinal beam 411 and the cross beam 412, the two ends of the cross beam 412 are respectively connected with the horizontal tail connecting frame 5, the vertical tail connecting frame 6 is connected above the longitudinal beam 411, the horizontal tail 11 is respectively detachably connected with the corresponding horizontal tail connecting frame 5, and the vertical tail 12 is detachably connected with the vertical tail connecting frame 6. The cross member 412 can balance the bending shear of the horizontal tail 11 relative to the root of the horizontal tail 11 and can also transfer 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 cross beams 412 form a closed latticed torsion box, so that the torsion load of the rudder 122 of the vertical tail 12 can be conveniently transmitted to the machine body 2; the angled beam 413 may provide inertial force support for the vertical tail 12 and the horizontal tail 11.
As shown in fig. 3, the supporting beam 41 of the present embodiment has a C-shaped cross section, and can be manufactured in batch by using the same mold, and is cut to a desired size, the supporting beam 41 includes a web 41a and ribs 41b, the ribs 41b are distributed at both ends of the web 41a in the width direction, and both the ribs 41b are perpendicular to the web 41a and are located at the same side of the web 41 a. The structural support beams 41 can better transmit the load of the tail fin 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 present application is based on an aircraft with a square fuselage 2, the fuselage wall 22 of which is straight and can effectively increase the space available in the fuselage cabin.
The vertical tail 12 and the horizontal tail 11 are both made of composite materials and have a structural form of a double-wing-beam 9 multi-tail wing rib 91. The airfoil and tail ribs 91 act as the primary aerodynamic force-collecting components to transfer loads to the spar 9, the spar 9 acting as the main load-bearing structure to transfer loads to the junction box 3. The junction box is integrated with the vertical tail 12 and the horizontal tail 11, and transmits the load to the fuselage 2 together, thereby playing a role in maintaining the balance of the flight state of the aircraft.
As shown in fig. 2, the longitudinal beam 411 of the present embodiment includes a left longitudinal beam 4111 and a right longitudinal beam 4112 which are parallel to the axis of the fuselage 2 and symmetrically distributed, the cross beam 412 includes a rear cross beam 4121, a middle cross beam 4122 and a front cross beam 4123 which are distributed at intervals from the rear to the front outside of the left longitudinal beam 4111 and the right longitudinal beam 4112, the front ends of the left longitudinal beam 4111 and the right longitudinal beam 4112 are respectively connected with the outer ends of the corresponding front cross beam 4123 through an oblique beam 413, and the front ends of the left longitudinal beam 4111 and the right longitudinal beam 4112 are connected through a front connecting beam 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. The rear connecting beam 416 and the rear cross member 4121 may be integrally formed, and two connecting beams 415 are provided in this embodiment. Between adjacent supporting beams 41, left longitudinal beam 4111 and right longitudinal beam 4112 are connected with front connecting beam 414, middle connecting beam 415 and rear connecting beam 416 through corner boxes 8, and the latticed frame body of the connecting box 3 can bear complex tension and compression loads and is convenient to mount and dismount.
As shown in fig. 2, the flattail joint carriage 5 of the present embodiment includes a first flattail beam 51, a flattail joint beam 52 and a second flattail beam 53, two ends of the first flattail beam 51 are respectively connected to the flattail joint beams 52 inclined backward, the two flattail joint beams 52 are parallel to each other, ends of the two flattail joint beams 52 are respectively connected to the second flattail beam 53 parallel to the first flattail beam 51, one sides of the two flattail joint beams 52 close to the support frame 4 are respectively connected to the corresponding oblique beam 413 and the rear cross beam 4121 through the connecting band plate 7, a middle portion of the first flattail beam 51 is connected to the corresponding rear cross beam 4121, and the first flattail beam 51 is parallel to the axis of the fuselage 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, the 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, the 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 support frame 4 is respectively connected with the front connecting beam 414 and the middle connecting beam 415 through the connecting band plate 7, and the first vertical tail beam 61 is parallel to the axis of the fuselage 2.
As shown in fig. 4 and 5, the horizontal tail 11 includes a horizontal tail fixing surface 111 and an elevator 112 behind the horizontal tail fixing surface, a horizontal tail connecting portion 113 is disposed at the root of the horizontal tail 11, the horizontal tail connecting portion 113 includes two horizontal tail insertion beams 1131 and a horizontal tail rib 1132, the two horizontal tail insertion beams 1131 are parallel and are respectively and fixedly connected with the corresponding spars 9 in the horizontal tail fixing surface 111, the outer ends of the two horizontal tail insertion beams 1131 are connected by the horizontal tail end rib 1132 along one side of 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 rib 1132 can also be arranged on two sides of the outer ends of the two horizontal tail inserting beams 1131 along the width direction, so long as a channel for inserting and combining the horizontal tail inserting beams 1131 and the horizontal tail connecting beam 52 is avoided; the two horizontal tail inserting beams 1131 are matched with the two horizontal tail connecting beams 52 in distance, 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 therebehind, the root of the vertical tail 12 is provided with a vertical tail connecting portion 123, the vertical tail connecting portion 123 includes two vertical tail insertion beams 1231 and a vertical tail end rib 1232, the two vertical tail insertion beams 1231 are parallel and respectively and fixedly connected with corresponding spars in the vertical tail fixing surface 121, the outer ends of the two vertical tail insertion beams 1231 are connected by the vertical tail end rib 1232 along one side of the width direction, and the vertical tail end rib 1232 can improve the strength of the vertical tail connecting portion 123; the vertical tail end ribs 1232 can also be arranged on two sides of the outer ends of the two vertical tail insertion beams 1231 along the width direction, and only a channel for inserting and combining the vertical tail insertion beams 1231 and the vertical tail connecting beams 62 is avoided; the two vertical fin inserting beams 1231 are matched with the two vertical fin connecting beams 62 in distance, and the vertical fin inserting beams 1231 are connected with the corresponding vertical fin connecting beams 62 through bolt assemblies after being inserted.
As shown in fig. 5 and 6, two parallel wing spars 9 are arranged in each of the vertical fin fixing surface 121 and the horizontal fin fixing surface 111, a plurality of tail ribs 91 connected between the two wing spars 9 form a main bearing structure of the tail fin 1, and are connected with the connecting box 3 through the vertical fin connecting portion 123 and the horizontal fin connecting portion 113, so that the fuselage wall panels 22 on the upper portion of the fuselage 2 form an integral force transmission structure, and the force transmission path is simple and the force transmission efficiency is high. The connection of fin 1 and junction box 3, its security, reliability are higher, compromise maintainability, detachability simultaneously. 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 support frame 4 are connected with each other, and an integral force transmission structure is formed on the surface of the body wall plate 22 above the tail part of the body 2.
As shown in fig. 4, the fuselage frame 21 is fixedly connected by stacking a plurality of high-strength alloy plates, the fuselage frame 21 includes a horizontal bearing beam 211, side beams 212 extending in an arc shape are arranged on two sides of the bearing beam 211, and the fuselage frame 21 is arranged at intervals and gradually reduced from front to back. The fuselage frame 21 is a C-shaped metal component with a downward opening, the opening of the fuselage frame 21 is an opening boundary of the fuselage, the downward opening can be used for loading goods, and the fuselage frame 21 can be made of aluminum or titanium alloy materials.
The fuselage panels 22 and the fuselage frames 21 transfer the loads to the fuselage 2, ensuring the safety of the aircraft in flight.
The vertical tail 12, the horizontal tail 11, the longitudinal beams 411, the cross beams 412, the oblique beams 413 and the fuselage 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 angle box 8 and the connecting band plate 7 are made of metal materials, so that the connecting strength of the connecting box 3 is improved.
The embodiments of the present invention are preferred embodiments of the present application, and the scope of protection of the present application is not limited by the embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (10)
1. The connection structure of the airplane empennage and the airplane body is characterized by comprising an empennage (1), an airplane body (2) and a connection box (3), wherein the empennage (1) comprises a vertical fin (12) and two horizontal fins (11), the airplane body (2) comprises an airplane body frame (21) and an airplane body wallboard (22), the airplane body wallboard (22) is connected to the outer side of the airplane body frame (21), and the connection box (3) is fixedly connected to the airplane body wallboard (22) which is horizontally arranged above the tail 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), the supporting frames (4) are spliced into a latticed frame body through supporting beams (41), the supporting beams (41) comprise longitudinal beams (411) parallel to the axis of the machine body (2), two sides of the longitudinal beam (411) are respectively and fixedly connected with a cross beam (412) which is symmetrically distributed with the axis of the machine body (2), the cross beam (412) is vertical to the longitudinal beam (411) and is coplanar, the front end of the longitudinal beam (411) and the two ends of the cross beam (412) are respectively connected with an oblique beam (413), two ends of the cross beam (412) are respectively connected with a horizontal tail connecting frame (5), a vertical tail connecting frame (6) is connected above the longitudinal beam (411), the horizontal tails (11) are detachably connected with the corresponding horizontal tail connecting frames (5) respectively, and the vertical tails (12) are detachably connected with the vertical tail connecting frames (6).
2. An aircraft tail and fuselage connection structure as claimed in claim 1, characterized in that the longitudinal beams (411) comprise a left longitudinal beam (4111) and a right longitudinal beam (4112) which are parallel to the axis of the fuselage (2) and symmetrically distributed, the cross beam (412) comprises a rear cross beam (4121), a middle cross beam (4122) and a front cross beam (4123) which are distributed at intervals from the rear to the front outside of the left longitudinal beam (4111) and the right longitudinal beam (4112), the front ends of the left longitudinal beam (4111) and the right longitudinal beam (4112) are respectively connected with the outer end of the corresponding front cross beam (4123) through an oblique beam (413), and the front ends of the left longitudinal beam (4111) and the right longitudinal beam (4112) are connected through a front connecting beam (414); the rear end of left longeron (4111) and right longeron (4112) is connected through back tie-beam (416), connect through well tie-beam (415) between left longeron (4111) and right longeron (4112) the middle part.
3. An aircraft tail and fuselage connection structure according to claim 2, characterized in that the horizontal tail boom (5) comprises a first horizontal tail boom (51), a horizontal tail boom (52) and a second horizontal tail boom (53), the two ends of the first flat tail beam (51) are respectively connected with a backward inclined flat tail connecting beam (52), the two flat tail connecting beams (52) are parallel to each other, the end parts of the two flat tail connecting beams (52) are respectively connected with a second flat tail beam (53) parallel to the first flat tail beam (51), one side of the two flat tail connecting beams (52) close to the support frame (4) is respectively connected with a corresponding oblique beam (413) and a rear cross beam (4121) through a connecting band plate (7), the middle part of the first tail beam (51) is connected with the corresponding rear cross beam (4121), and the first tail beam (51) is parallel to the axis of the fuselage (2).
4. An aircraft tail and fuselage connection according to claim 3, characterized in that the horizontal tail connecting beam (52) is of a trapezoidal shape with a narrowing from the inside to the outside.
5. The connection structure of an airplane empennage and a fuselage as claimed in claim 2, characterized in that the vertical tail connecting frame (6) comprises a first vertical tail beam (61), a vertical tail connecting beam (62) and a second vertical tail beam (63), wherein the two ends of the first vertical tail beam (61) are respectively connected with the vertical tail connecting beam (62) inclined backwards, the two vertical tail connecting beams (62) are parallel to each other, the end parts 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), the sides of the two vertical tail connecting beams (62) close to the supporting frame (4) are respectively connected with the front connecting beam (414) and the middle connecting beam (415) through connecting strips (7), and the first vertical tail beam (61) is parallel to the axis of the fuselage (2).
6. The connection structure of an airplane tail wing and a fuselage according to claim 3, characterized in that the horizontal tail (11) comprises a horizontal tail fixing surface (111) and a subsequent elevator (112), the root of the horizontal tail (11) is provided with a horizontal tail connection part (113), the horizontal tail connection part (113) comprises two horizontal tail insertion beams (1131) and horizontal tail end ribs (1132), the two horizontal tail insertion beams (1131) are parallel and are respectively fixedly connected with corresponding wing spars in the horizontal tail fixing surface (111), the outer ends of the two horizontal tail insertion beams (1131) are connected through the horizontal tail end ribs (1132) along one side of the width direction, the two horizontal tail insertion beams (1131) are matched with the distance between the two horizontal tail connection beams (52), and the horizontal tail insertion beams (1131) are connected through bolt assemblies after being inserted with the corresponding horizontal tail connection beams (52).
7. The connection structure of an aircraft empennage and fuselage as claimed in claim 5, characterized in that the vertical fin (12) comprises a vertical fin fixing surface (121) and a rudder (122) behind the vertical fin (12), the root of the vertical fin (12) is provided with a vertical fin connection part (123), the vertical fin connection part (123) comprises two vertical fin insertion beams (1231) and vertical fin end ribs (1232), the two vertical fin insertion beams (1231) are parallel and are respectively fixedly connected with corresponding spars in the vertical fin fixing surface (121), the outer ends of the two vertical fin insertion beams (1231) are connected through the vertical fin end ribs (1232) along one side of the width direction, the two vertical fin insertion beams (1231) are matched with the distance between the two vertical fin connection beams (62), and the vertical fin insertion beams (1231) are connected through bolt assemblies after being inserted into the corresponding vertical fin connection beams (62).
8. The connection structure of the empennage and the fuselage of the airplane as claimed in claim 1, wherein the fuselage frame (21) is fixedly connected by stacking a plurality of alloy plates, the fuselage frame (21) comprises a horizontal bearing beam (211), side beams (212) extending downwards in an arc shape are arranged on two sides of the bearing beam (211), and the fuselage frame (21) is arranged in a plurality at intervals and gradually reduced from front to back.
9. The connection structure of an airplane empennage and fuselage as claimed in claim 1, wherein the cross-section of the support beam (41) is C-shaped, the support beam (41) comprises a web (41a) and ribs (41b), the ribs (41b) are distributed at both ends of the web (41a) in the width direction, and the ribs (41b) are perpendicular to the web (41a) and are located at the same side of the web (41 a).
10. An aircraft tail and fuselage connection structure according to claim 2, characterized in that between adjacent support beams (41), the left and right longitudinal beams (4111, 4112) are connected with the front (414), middle (415) and rear (416) connection beams 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 true CN114906313A (en) | 2022-08-16 |
| CN114906313B CN114906313B (en) | 2023-11-10 |
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Cited By (1)
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| CN114906313B (en) | 2023-11-10 |
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