CN210338265U - Sedan-chair formula wing body connection structure - Google Patents
Sedan-chair formula wing body connection structure Download PDFInfo
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- CN210338265U CN210338265U CN201920736431.2U CN201920736431U CN210338265U CN 210338265 U CN210338265 U CN 210338265U CN 201920736431 U CN201920736431 U CN 201920736431U CN 210338265 U CN210338265 U CN 210338265U
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Abstract
The utility model discloses a sedan-chair formula wing body connection structure, including fuselage frame and wing, the wing all lies in the oil tank with fuselage frame detachable connection portion, the both sides of fuselage frame lie in the same high symmetry and are provided with a plurality of montage head subassemblies, the joint subassembly includes wing front joint subassembly and wing middle joint subassembly, the web on the fuselage frame is connected with the upper wall panel of wing and front beam upper fringe through wing front joint subassembly, the fuselage frame middle joint on the fuselage frame is connected with the wall panel and the beam web panel of wing through wing middle joint subassembly; the wing front joint component comprises a wing front connecting bolt, a wing front locking nut and an angle box, the installation side of the angle box is attached to the outer side of the wing, and the connection side of the angle box is arranged in parallel to the web plate of the fuselage frame; the wing front connecting bolt penetrates through the connecting side of the web plate and the corner box and is installed, and a wing front locking nut is sleeved on one end of the wing front connecting bolt; the utility model has the advantages of simple structure, convenient installation, small volume, light weight and no influence on the whole oil tank of the wing.
Description
Technical Field
The utility model belongs to the technical field of aircraft structure, concretely relates to sedan-chair formula wing body connection structure.
Background
The sedan type wing body connecting structure is a connecting structure which is commonly used in connection of wings and a fuselage of an airplane at present, the wings on two sides of the fuselage are connected into a whole by adopting the sedan type connecting structure, the wings are connected with the wing body through a connecting device on the wing body, and the sedan type connecting structure is generally used for a lower single-wing airplane. The symmetrical bending moment of the left wing and the right wing in the wing body connection mode is balanced at the position of a plane symmetry plane BL0, the symmetrical bending moment is not transferred by the butt joint of the wings and the fuselage, and only the asymmetrical bending moment and the torque are transferred. The wing body connecting device is a key for realizing the connection of the wing body, the wing is often used as an integral oil tank structure while serving as a main lifting surface, the sizes of openings of machine bodies, installation spaces, structural complexity, assembly precision, maintenance requirements and the like of all machine types are different, and the connection forms of the wing body are also different. The existing sedan type wing body connecting structure mostly adopts the mode that a central wing is embedded and installed between two fuselage reinforcing frames, so that the reinforcing frames are of complete structures, meanwhile, a large and heavy joint is arranged on a wing beam of a wing, and the wing beam is connected onto the fuselage through a hollow pin. The joint in the existing sedan type connecting structure is positioned in the integral oil tank of the wing, and the joint easily causes the integral oil tank of the wing to break down; and the joint structure is complicated, bulky, heavy, has increased the weight of aircraft, and it is inconvenient to maintain simultaneously. Therefore, aiming at the defects of the existing sedan type wing body connecting structure, the sedan type connecting structure which is simple in structure, convenient to maintain and free of influence on the whole oil tank of the wing needs to be developed.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a sedan-chair formula wing body connection structure has simplified sedan-chair formula wing body connection structure, and the joint setting that will connect the usefulness simultaneously has simple structure, small, light in weight, does not influence the beneficial effect of the whole oil tank of wing in the whole oil tank outside of wing.
The utility model discloses a following technical scheme realizes:
a sedan type wing body connecting structure comprises a fuselage frame and wings, wherein detachable connecting parts of the wings and the fuselage frame are positioned outside an oil tank, a plurality of assembling joint assemblies are symmetrically arranged at the same height on two sides of the fuselage frame, each joint assembly comprises a wing front joint assembly and a wing middle joint assembly, a web plate on the fuselage frame is connected with an upper wall plate of the wings and an upper edge strip of a front beam through the wing front joint assemblies, and a fuselage frame middle joint on the fuselage frame is connected with the wall plate of the wings and a beam web plate through the wing middle joint assemblies; the wing front joint component comprises a wing front connecting bolt, a wing front locking nut and an angle box, wherein the installation side of the angle box is attached to the outer side of the wing, and the connection side of the angle box is arranged in parallel to a web plate of the fuselage frame; the front wing connecting bolt penetrates through the web plate and the connecting side of the angle box in sequence to be installed, and the front wing locking nut is sleeved on one end, extending out of the connecting side of the angle box, of the front wing connecting bolt.
The working principle and the using method are as follows:
the wing is a part of the lower fuselage, a plurality of assembly joint assemblies are symmetrically arranged at the same height on two sides of the fuselage frame and used for connecting the wing to the fuselage frame, and meanwhile, the assembly joint assemblies on the two sides of the fuselage frame are arranged in the same width size range in the spanwise direction of the fuselage. The joint component comprises a front wing joint component and a middle wing joint component, the front wing joint component and the middle wing joint component are both positioned at the wing root of the wing, the front wing joint component is arranged between the flange of the wing root of the wing and the fuselage frame, namely the front wing joint component is arranged along the contour of the flange of the wing, and a web plate on the fuselage frame is connected with the outer side of the wing through the front wing joint component; the wing middle joint assembly is arranged between a wing root of the wing and the fuselage frame, and the fuselage frame middle joint on the fuselage frame is connected with the outer side of the wing through the wing middle joint assembly. The wing front joint component comprises a wing front connecting bolt, a wing front locking nut and an angle box, wherein one side of the angle box close to the wing is a mounting side, one side of the angle box close to the fuselage frame is a connecting side, the mounting side of the angle box corresponds to the outer contour of the wing, and namely the mounting surface of the mounting side of the angle box is fixedly mounted by being attached to the outer contour of the wing. The connection face of the connection side of the angle box is parallel to the web plate, when the connection between the wing and the fuselage frame is carried out, the installation side of the angle box is attached and fixedly installed on the outer side of the wing, the connection side of the angle box is connected with the web plate through the wing front connecting bolt, the wing front connecting bolt sequentially penetrates through the installation face of the connection side of the web plate and the angle box, the threaded end of the wing front connecting bolt extends to the outside of the connection side of the angle box and is sleeved with the wing front locking nut, and the connection between the wing and the fuselage frame is achieved. Meanwhile, the middle part or the rear part of the fuselage frame is provided with a fuselage frame middle joint, and the fuselage frame middle joint is connected with the outer side of the wing through the wing middle connecting component.
In order to better realize the utility model, the wing middle joint component comprises a wing middle connecting stud, a wing middle locking nut, a wing connecting joint, a positioning bolt and a positioning nut, wherein the installation side of the wing connecting joint is fixedly connected with the outer side of the wing, the connecting side of the wing connecting joint is connected with the middle joint of the body frame through the wing middle connecting stud which is installed in a penetrating way, and the end of the wing middle connecting stud extending to the joint outer part of the body frame is sleeved with the wing middle locking nut; the positioning bolt sequentially and vertically penetrates through the wing connecting joint and the wing middle connecting stud to be installed, and a positioning nut is sleeved at the threaded end of the positioning bolt.
The side of the wing connecting joint close to the wing is a mounting side, and the side close to the fuselage frame is a connecting side. The installation side of the wing connecting joint is fixedly connected with the outer side of the wing, and the connecting side of the wing connecting joint is connected corresponding to the middle joint of the fuselage frame. The wing connecting joint and the middle joint of the fuselage frame are respectively and correspondingly provided with a stud mounting hole, when the wing is connected with the fuselage frame, a wing middle connecting stud is inserted into the stud mounting hole of the wing connecting joint and the stud mounting hole of the middle joint of the fuselage frame along the direction towards the wing, and then a wing middle locking nut is sleeved at one end of the wing middle connecting stud, which extends to the outer side of the middle joint of the fuselage frame, for locking; positioning holes vertical to the axial direction of the wing middle connecting stud are correspondingly arranged on the wing connecting joint and the wing middle connecting stud, positioning bolts are inserted into the positioning holes of the wing connecting joint and the wing middle connecting stud, namely the positioning bolts sequentially penetrate through the wing connecting joint and the wing middle connecting stud, then positioning nuts are sleeved at the threaded ends of the positioning bolts, the positioning bolts are used for locking the wing middle connecting stud, and finally the connection between the wing and the fuselage frame is realized.
In order to better realize the utility model discloses, furtherly, be provided with the cavity between the outside of wing attach fitting's installation side and wing, wing attach fitting is passed and the cavity is stretched into to stud's one end in the wing.
The cavity is arranged between the installation side of the wing connecting joint and the connecting end of the wing, so that the weight of the wing connecting joint can be further reduced, and meanwhile, one end of the connecting stud in the wing penetrates through the wing connecting joint and extends into the cavity, so that the installation of the connecting stud in the wing can be facilitated.
In order to better realize the utility model discloses, furtherly, still be provided with in the wing joint connection and the wing between the connecting stud with the wing in the coaxial joint bush of connecting stud.
A joint bushing is arranged between the wing connecting joint and the wing middle connecting stud, so that the abrasion of the wing middle connecting stud to a stud mounting hole in the wing connecting joint is reduced, and the service time of the wing connecting joint is prolonged. After long-time use, only need according to the wearing and tearing condition change connect the bush can, reduce maintenance cost.
In order to better realize the utility model discloses, furtherly, the one end that stud extends to the lock nut outside in the wing is provided with the split pin jack in the wing, the split pin has been inserted in the split pin jack.
After the wing middle locking nut is screwed and locked on the wing middle connecting stud, a cotter pin is inserted into a cotter pin jack at one end of the wing middle connecting stud, which extends to the outer side of the wing middle locking nut, to stop, and the cotter pin can prevent the wing middle locking nut from loosening or falling off from the wing middle connecting stud.
In order to better realize the utility model discloses, furtherly, still be provided with the cover between the connection side of web and angle box and establish the adjusting shim on the connecting bolt before the wing.
The gap between the wing and the fuselage frame can be adjusted by replacing adjusting shims with different thicknesses.
Compared with the prior art, the utility model, following advantage and beneficial effect have:
(1) the utility model realizes convenient connection between the wing and the fuselage frame through the wing front joint component and the wing middle joint component by symmetrically arranging the plurality of wing front joint components and the wing middle joint components at the same height on two sides of the fuselage frame, and the wing front joint components and the wing middle joint components are both positioned outside the wing; compare in traditional sedan-chair formula wing body connection structure, the utility model has the beneficial effect that connection structure is simple, the dismouting is convenient, do not influence the oil tank in the wing.
(2) The utility model has the advantages that the angle box is arranged between the web plate of the body frame and the outer side of the wing, the mounting side of the angle box is fixedly mounted corresponding to the flange of the wing, the front connecting bolt for mounting the wing is penetrated between the connecting side of the angle box and the web plate of the body frame and is locked through the front connecting nut, and the convenient connection between the wing and the body frame is realized; compare in traditional sedan-chair formula wing body connection structure, the utility model has the beneficial effect of simple structure, small, light in weight, installation are convenient.
(3) The utility model has the advantages that the wing connecting joint is arranged between the joint of the body frame and the wing, the installation side of the wing connecting joint is fixedly connected with the outer side of the wing, the connecting side of the wing connecting joint is connected with the middle joint of the body frame through the connecting stud in the wing and is locked through the locking nut in the wing, and then the positioning and locking are carried out through the positioning bolt which runs through the connecting stud in the wing and the wing connecting joint, so that the convenient connection between the wing and the body frame is realized; compare in traditional wing body connection structure, the utility model has the beneficial effects of simple and convenient, small, light in weight, the installation is convenient of structure.
Drawings
FIG. 1 is a schematic view of the arrangement of a joint assembly between a wing and a fuselage frame;
FIG. 2 is a schematic view of the structure of the wing nose joint assembly;
FIG. 3 is a schematic view of a joint assembly in a wing;
FIG. 4 is a schematic view of a cutaway in the direction A of the joint assembly in the wing;
FIG. 5 is a schematic view of the installation of the joint bushing;
fig. 6 is a schematic view of the installation of the cotter pin.
Wherein: 1-a fuselage frame; 2-an airfoil; 3-a wing nose joint assembly; 4-wing mid-joint assembly; 31-wing front connecting bolt; 32-wing front lock nut; 33-corner boxes; 41-connecting stud in wing; 42-wing center lock nut; 43-wing connection joints; 44-a positioning bolt; 45-positioning the nut; 46-a joint bushing; 47-cotter pin; 01-a web; 02-fuselage frame middle joint.
Detailed Description
Example 1:
the sedan type wing body connecting structure of the embodiment is shown in fig. 1 and 2 and comprises a body frame 1 and wings 2, detachable connecting parts of the wings 2 and the body frame 1 are located outside an oil tank, a plurality of assembly connecting assemblies are symmetrically arranged on two sides of the body frame 1 at the same height and comprise a front wing connector assembly 3 and a middle wing connector assembly 4, a web plate 01 on the body frame 1 is connected with an upper wall plate of the wings 2 and an upper edge strip of a front beam through the front wing connector assembly 3, and a body frame middle connector 02 on the body frame 1 is connected with a wall plate and a beam web plate of the wings 2 through the middle wing connector assembly 4; the wing front joint component 3 comprises a wing front connecting bolt 31, a wing front locking nut 32 and an angle box 33, wherein the installation side of the angle box 33 is attached to the outer side of the wing 2, and the connection side of the angle box 33 is arranged in parallel to a web plate of the fuselage frame 1; the wing front connecting bolt 31 penetrates through the web 01 and the connecting side of the corner box 33 in sequence to be installed, and a wing front locking nut 32 is sleeved on one end, penetrating through the wing front connecting bolt 31 and extending out of the connecting side of the corner box 33.
The wing 2 is a part of the lower fuselage, and a plurality of assembly joint assemblies are symmetrically arranged at the same height on two sides of the fuselage frame 1 and are used for connecting the wing 2 to the fuselage frame 1. Meanwhile, the joint components on both sides of the fuselage frame 1 are arranged within the same width dimension in the spanwise direction of the wing 2. The joint components comprise a front wing joint component 3 and a middle wing joint component 4, the front wing joint component 3 and the middle wing joint component 4 are both positioned at the wing root of the wing 2, the front wing joint component 3 is arranged between the flange of the wing root of the wing 2 and the fuselage frame 1, namely the front wing joint component 3 is arranged along the flange contour of the wing 2; the mid-wing joint assembly 4 is arranged between the connecting section of the root of the wing 2 and the fuselage frame 1. The web 01 on the fuselage frame 1 is connected with the outer side of the wing 2 through the wing front joint component 3, the fuselage frame middle joint 02 on the fuselage frame 1 is connected with the outer side of the wing 2 through the wing middle joint component 4, and finally convenient connection between the fuselage frame 1 and the wing 2 is achieved.
The wing front joint component 3 comprises a wing front connecting bolt 31, a wing front locking nut 32 and an angle box 33, wherein one side of the angle box 33 close to the wing 2 is a mounting side, one side of the angle box 33 close to the fuselage frame 1 is a connecting side, and the mounting side of the angle box 33 is arranged corresponding to the outer contour of the wing 2, namely, the mounting surface of the mounting side of the angle box 33 is fixedly mounted by being attached to the outer contour of the wing 2. The connection surface of the connection side of the corner box 33 is arranged in parallel to the web 01 of the fuselage frame 1, when the wing 2 is connected with the fuselage frame 1, the installation side of the corner box 33 is fixedly attached to the outer side of the wing 2, the connection side of the corner box 33 is connected with the web 01 of the fuselage frame 1 through a wing front connection bolt 31, the wing front connection bolt 31 sequentially penetrates through the installation surfaces of the connection sides of the web 01 and the corner box 33, the threaded end of the wing front connection bolt 31 extends out of the connection side of the corner box 33 and is sleeved with a wing front locking nut 32, and connection of the wing 2 and the fuselage frame 1 is achieved. Meanwhile, the middle part and the rear part of the wing 2 are connected with the fuselage frame 1 through the wing middle joint component 4, and finally the whole wing 2 is connected with the fuselage frame 1. Compare in traditional sedan-chair formula wing body connection structure, the utility model discloses a convenient connection between wing 2 and fuselage frame 1 is realized to joint Assembly 4 in joint Assembly 3 and the wing before the wing, and corresponding joint Assembly 3 and wing in joint Assembly 4 all set up in the outside of wing 2 to do not influence or interfere the inside oil tank of wing 2, avoid the influence of joint Assembly 4 in joint Assembly 3 and the wing to the whole oil tank of wing before the wing. Meanwhile, the front wing joint component 3 and the middle wing joint component 4 are both positioned on the outer sides of the wing 2 and the fuselage frame 1, so that the operation of workers is more convenient, the connection structure between the wing 2 and the fuselage frame 1 is simpler, and the connection work is more convenient.
Example 2:
the embodiment is further optimized on the basis of embodiment 1, as shown in fig. 3 and 4, the wing middle joint assembly 4 includes a wing middle connecting stud 41, a wing middle locking nut 42, a wing connecting joint 43, a positioning bolt 44, and a positioning nut 45, the installation side of the wing connecting joint 43 is fixedly connected with the outer side of the wing 2, the connection side of the wing connecting joint 43 is connected with the fuselage frame middle joint 02 through the wing middle connecting stud 41 installed in a penetrating manner, and the wing middle locking nut 42 is sleeved on one end of the wing middle connecting stud 41 extending to the joint outer portion of the fuselage frame 1; the positioning bolt 44 penetrates through the wing connecting joint 43 and the wing middle connecting stud 41 in sequence and is installed, and a positioning nut 45 is sleeved at the threaded end of the positioning bolt 44.
The side of the wing connecting joint 43 close to the wing 2 is a mounting side, and the side of the wing connecting joint 43 close to the fuselage frame 1 is a connecting side. The installation side of the wing connecting joint 43 is fixedly connected with the outer side of the wing 2, the middle of the wing connecting joint 43 is a web surface, two sides of the web surface are parallel edge strips, and the web surface and the edge strips form a [ -structure, namely, the cross section of the wing connecting joint 43 is [ -shaped. The web surface and the edge strip of the wing connecting joint 43 are respectively and correspondingly fixedly connected with the wall plate and the beam web plate on the outer side of the wing 2, so that the fixed installation of the wing connecting joint 43 on the outer side of the wing 2 is realized. The connection side of the wing connection joint 43 is connected to the fuselage frame intermediate joint 02 on the fuselage frame 1. Stud mounting holes are correspondingly formed in the wing connecting joint 43 and the fuselage frame middle joint 02, when the wing 2 is connected with the fuselage frame 1, the wing middle connecting stud 41 is inserted into the stud mounting hole of the wing connecting joint 43 and the stud mounting hole of the fuselage frame middle joint 02 along the direction towards the wing 2, and then the wing middle locking nut 42 is sleeved at one end, extending to the outer side of the fuselage frame middle joint 02, of the wing middle connecting stud 41 for locking; positioning holes perpendicular to the axial direction of the wing middle connecting stud 41 are correspondingly formed in the wing connecting joint 43 and the wing middle connecting stud 41, positioning bolts 44 are inserted into the positioning holes of the wing connecting joint 43 and the wing middle connecting stud 41, namely the positioning bolts 44 sequentially penetrate through the wing connecting joint 43 and the wing middle connecting stud 41, then positioning nuts 45 are sleeved on threaded ends of the positioning bolts 44, the wing middle connecting stud 41 is locked by the positioning bolts 44, and finally the connection between the wing 2 and the fuselage frame 1 is achieved. The connecting mode replaces the mode of connecting the large forging of the fuselage frame, the large forging of the beam joint and the hollow pin in the traditional sedan connecting structure, so that the connecting structure between the wing 2 and the fuselage frame 1 is simpler and more convenient, and has smaller volume and lighter weight.
Other parts of this embodiment are the same as embodiment 1, and thus are not described again.
Example 3:
this embodiment is further optimized on the basis of the above embodiment 1 or 2, a cavity is provided between the installation side of the wing connection joint 43 and the outer side of the wing 2, and one end of the connection stud 41 in the wing passes through the wing connection joint 43 and extends into the cavity.
A cavity is arranged between the mounting side of the wing connection joint 43 and the outer side of the wing 2, so that the weight of the wing connection joint 43 can be further reduced, and meanwhile, one end of the wing middle connection stud 41 penetrates through the wing connection joint 43 and extends into the cavity, so that the mounting of the wing middle connection stud 41 can be facilitated.
The rest of this embodiment is the same as embodiment 1 or 2, and therefore, the description thereof is omitted.
Example 4:
this embodiment is further optimized on the basis of any of the above embodiments 1 to 3, and as shown in fig. 5, a joint bushing 46 coaxial with the wing middle connection stud 41 is further provided between the wing connection joint 43 and the wing middle connection stud 41.
The joint bushing 46 is provided between the wing connection joint 43 and the wing middle connection stud 41 to reduce the wear of the wing middle connection stud 41 to the stud mounting hole on the wing connection joint 43 and to prolong the service time of the wing connection joint 43. After long-time use, only need to change according to the wearing and tearing condition joint bush 46 can, reduce the maintenance cost. Meanwhile, in order to facilitate the positioning bolt 44 to pass through the wing connection joint 43 and the wing middle connection stud 41, a positioning hole through which the positioning bolt 44 passes is correspondingly arranged on the joint bushing 46 in a direction perpendicular to the axial direction of the wing middle connection stud 41.
Other parts of this embodiment are the same as any of embodiments 1 to 3, and thus are not described again.
Example 5:
this embodiment is further optimized on the basis of any one of the above embodiments 1 to 4, and as shown in fig. 6, a cotter pin inserting hole is formed in one end of the wing, which extends from the connecting stud 41 to the outer side of the wing middle lock nut 42, and a cotter pin 47 is inserted into the cotter pin inserting hole.
After the wing middle lock nut 42 is tightened and locked on the wing middle lock nut 41, a cotter 47 is inserted into a cotter insertion hole at an end of the wing middle lock nut 41 extending to an outer side of the wing middle lock nut 42 to be stopped, and the cotter 47 can prevent the wing middle lock nut 42 from being loosened or falling off from the wing middle lock nut 41.
Other parts of this embodiment are the same as any of embodiments 1 to 4, and thus are not described again.
Example 6:
this embodiment is further optimized on the basis of any one of the above embodiments 1 to 5, and an adjusting gasket sleeved on the wing front connecting bolt 31 is further disposed between the web 01 of the fuselage frame 1 and the connecting side of the corner box 33.
The gap between the web 01 of the fuselage frame 1 and the connecting side of the corner box 33 can be adjusted by replacing adjusting shims with different thicknesses.
Other parts of this embodiment are the same as any of embodiments 1 to 5, and thus are not described again.
Example 7:
in this embodiment, a further optimization is performed on the basis of any one of the above embodiments 1 to 6, as shown in fig. 1, a group of wing front joint assemblies 3 and two groups of wing middle joint assemblies 4 are symmetrically arranged at the same height on two sides of the fuselage frame 1, and the group of wing front joint assemblies 3 is arranged between the front flange of the wing root of the wing 2 and the fuselage frame 1; the two groups of wing middle joint assemblies 4 are respectively arranged between the middle part of the wing root of the wing 2 and the fuselage frame 1 and between the rear part of the wing root of the wing 2 and the fuselage frame 1.
Three sets of joint components are arranged on one side of the fuselage frame 1 at the same height, and comprise a front wing joint component 3 positioned at the front part of the wing root of the wing 2 and middle wing joint components 4 positioned in the middle part and the rear part of the wing root of the wing 2, wherein the three sets of joint components are arranged in the same width size range along the spanwise direction of the wing 2. When the wing 2 is subjected to bending deformation, the same chord plane of the wing 2 rotates relative to the fuselage frame 1 at the same time, the symmetrical bending moments of the wing 2 on the two sides are balanced in the BL0 plane, and at the moment, the joint assembly does not transmit the symmetrical bending moments of the wing 2 and only transmits the asymmetrical bending moments and torque.
Other parts of this embodiment are the same as any of embodiments 1 to 6, and thus are not described again.
The above is only the preferred embodiment of the present invention, not to the limitation of the present invention in any form, all the technical matters of the present invention all fall into the protection scope of the present invention to any simple modification and equivalent change of the above embodiments.
Claims (6)
1. The sedan type wing body connecting structure comprises a fuselage frame (1) and wings (2), wherein detachable connecting parts of the wings (2) and the fuselage frame (1) are positioned outside an oil tank, and the sedan type wing body connecting structure is characterized in that two sides of the fuselage frame (1) are positioned at the same height and symmetrically provided with a plurality of assembly joint assemblies, each assembly joint assembly comprises a front wing joint assembly (3) and a middle wing joint assembly (4), a web plate (01) on the fuselage frame (1) is connected with an upper wall plate and an upper edge strip of a front beam of the wings (2) through the front wing joint assembly (3), and a middle fuselage frame joint (02) on the fuselage frame (1) is connected with a wall plate and a beam web plate of the wings (2) through the middle wing joint assemblies (4); the wing front joint assembly (3) comprises a wing front connecting bolt (31), a wing front locking nut (32) and an angle box (33), the installation side of the angle box (33) is attached to the outer side of the wing (2), and the connection side of the angle box (33) is arranged in parallel to a web plate of the fuselage frame (1); the front wing connecting bolt (31) penetrates through the web plate (01) and the connecting side of the corner box (33) in sequence to be installed, and the front wing locking nut (32) is sleeved on one end, extending out of the connecting side of the corner box (33), of the front wing connecting bolt (31).
2. The sedan-type wing body connection structure of claim 1, wherein the wing middle joint assembly (4) comprises a wing middle connecting stud (41), a wing middle locking nut (42), a wing connecting joint (43), a positioning bolt (44) and a positioning nut (45), the installation side of the wing connecting joint (43) is fixedly connected with the outer side of the wing (2), the connecting side of the wing connecting joint (43) is connected with the fuselage frame middle joint (02) through the wing middle connecting stud (41) which is installed in a penetrating mode, and the end, extending to the joint outer portion of the fuselage frame (1), of the wing middle connecting stud (41) is sleeved with the wing middle locking nut (42); the positioning bolt (44) sequentially and vertically penetrates through the wing connecting joint (43) and the wing middle connecting stud (41) to be installed, and a positioning nut (45) is sleeved at the threaded end of the positioning bolt (44).
3. The sedan-type wing body connection structure of claim 2, wherein a cavity is provided between the mounting side of the wing connection joint (43) and the outer side of the wing (2), and one end of the wing middle connection stud (41) passes through the wing connection joint (43) and extends into the cavity.
4. The sedan-type wing body connection structure of claim 3, wherein a joint bushing (46) coaxial with the wing middle connection stud (41) is further provided between the wing connection joint (43) and the wing middle connection stud (41).
5. The connecting structure of a sedan type wing body according to any one of claims 2 to 4, wherein one end of the wing middle connecting stud (41) extending to the outer side of the wing middle locking nut (42) is provided with a cotter pin inserting hole, and a cotter pin (47) is inserted into the cotter pin inserting hole.
6. The sedan-type wing body connection structure of claim 1, wherein an adjusting gasket sleeved on the wing front connecting bolt (31) is further arranged between the web (01) and the connection side of the corner box (33).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201920736431.2U CN210338265U (en) | 2019-05-22 | 2019-05-22 | Sedan-chair formula wing body connection structure |
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| CN201920736431.2U CN210338265U (en) | 2019-05-22 | 2019-05-22 | Sedan-chair formula wing body connection structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112098035A (en) * | 2020-11-19 | 2020-12-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft test system |
| CN113978909A (en) * | 2021-12-30 | 2022-01-28 | 四川腾盾科技有限公司 | Large unmanned aerial vehicle transportation fixing device and sedan type constraint method |
-
2019
- 2019-05-22 CN CN201920736431.2U patent/CN210338265U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112098035A (en) * | 2020-11-19 | 2020-12-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft test system |
| CN113978909A (en) * | 2021-12-30 | 2022-01-28 | 四川腾盾科技有限公司 | Large unmanned aerial vehicle transportation fixing device and sedan type constraint method |
| CN113978909B (en) * | 2021-12-30 | 2022-03-22 | 四川腾盾科技有限公司 | Large unmanned aerial vehicle transportation fixing device and sedan type constraint method |
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