CN214930554U

CN214930554U - Aircraft fuselage external equipment mounting structure adopting four connectors

Info

Publication number: CN214930554U
Application number: CN202121727158.0U
Authority: CN
Inventors: 陈一夫; 陈弘智; 关珊珊; 黄玉昆; 陈晨; 卢丽颖
Original assignee: Aircraft Maintenance And Engineering Corp
Current assignee: Aircraft Maintenance And Engineering Corp
Priority date: 2021-07-26
Filing date: 2021-07-26
Publication date: 2021-11-30
Anticipated expiration: 2031-07-26

Abstract

The aircraft fuselage external equipment mounting structure comprises four joints fixed on a fuselage skin of a fuselage and a mounting plate connected to the fuselage through the four joints, wherein the four joints comprise a front joint and a rear joint positioned on the front side and the rear side and a left joint and a right joint positioned on the two sides, the joint structures of the four joints are the same, the front joint and the rear joint are transversely arranged, the left joint and the right joint are vertically arranged, the mounting plate is fixed on the four joints through a plurality of mounting screws, and the joint structures comprise a lower joint, an upper joint and a connecting bolt for connecting the upper joint and the lower joint together; therefore, the utility model discloses simple structure, convenient operation through four joints and its layout mode, has realized firmly installing this type of equipment reliably outside the fuselage, does not restrict the fuselage structure deformation of aircraft again. The installation form has compact structure, low height, light weight and good practical value.

Description

Aircraft fuselage external equipment mounting structure adopting four connectors

Technical Field

The utility model relates to a technical field of aviation spare part especially relates to an adopt aircraft fuselage external equipment mounting structure of four-joint.

Background

With the development of the aviation industry and modern information technology, more and more airlines have a requirement of installing equipment outside an airplane body so as to realize functions of communication, monitoring, positioning and tracking and the like. The airplane body structure is a main structure for bearing load of the airplane, the failure of the airplane body structure can directly cause the catastrophic result of machine damage and death, and the airplane continuously undergoes the cycle of take-off, climbing, cruising, descending and landing during the service period, and repeatedly bears the load of high-low altitude pressure difference, gust, operation, landing, sliding and the like. The fuselage structure of an aircraft therefore needs to meet the requirements of civil aviation regulations for fatigue performance, prevent fatigue cracks from occurring and enable the aircraft to operate safely during service. Due to the functional requirements of the system, many devices need to be installed outside the aircraft fuselage in a manner that must have sufficient rigidity and strength to ensure that they can withstand the aerodynamic forces, inertial loads, and differential pressure loads of the aircraft flight without failing, and yet not be too rigid to limit the loaded deformation of the aircraft fuselage structure, avoid stress concentrations in the structural regions connected to the fuselage, and prevent fatigue cracks during service. With the complexity of the devices, the size and weight of the devices vary greatly, and how to securely and reliably mount the devices on the fuselage of the aircraft becomes a key technical problem. At present, no compact and firm installation structure which does not limit the deformation of an airplane fuselage structure exists for equipment with the length of 1-2 meters and the width of 0.3-1 meter, wherein the equipment is in the dozens of kilograms.

Therefore, in view of the above-mentioned drawbacks, the designer of the present invention has studied and designed an aircraft fuselage external device mounting structure using four joints by integrating the experience and achievement of the related industries for many years through careful study and design to overcome the above-mentioned drawbacks.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an adopt aircraft fuselage external equipment mounting structure of four joints, its simple structure, convenient operation through 4 joints and its layout mode, has realized firmly installing this type of equipment reliably in the fuselage outside, does not restrict the fuselage structure of aircraft again and warp. The installation form has compact structure, low height, light weight and good practical value.

In order to achieve the above object, the utility model discloses an adopt aircraft fuselage external equipment mounting structure of four joints, including four joints on being fixed in the fuselage covering of fuselage and the mounting panel of being connected to the fuselage through four joints, its characterized in that:

four joints contain the preceding joint that is located the front and back side and connect and be located the left side of both sides and connect with the right side, the joint design homogeneous phase that four connect, preceding joint wherein and back connect horizontal setting, and the left side connects and connects vertical setting with the right side, the mounting panel is fixed to four joints through a plurality of mounting screws.

Wherein: the joint design contains lower clutch, top connection and will go up the connecting bolt that the joint connection is in the same place, the both sides of lower clutch are equipped with a plurality of fuselage connecting holes in order to be fixed to the fuselage covering, the middle part of lower clutch is equipped with the auricle, the auricle is equipped with the lower through-hole that supplies connecting bolt to run through, the top connection is equipped with a plurality of mounting bracket connecting holes, the lower extreme of top connection is equipped with the ears piece of arranging the auricle both sides in branch, thereby the ears piece is equipped with the rotatable fixed of realizing the top connection after supplying connecting bolt through-hole in proper order runs through auricle and auricle piece.

Wherein: the front end of mounting panel is circular-arc, and the rear end is the mounting bracket edge of taper shape, the periphery of mounting bracket is equipped with radome fairing connection structure.

Wherein: the position that the mounting panel corresponds four joints is equipped with respectively and connects mounting structure, connect mounting structure to contain the interval and set up a plurality of installation through-holes that supply the mounting screw to run through.

Wherein: the number of the mounting through holes is larger than the number required for fixing each joint, so that the mounting position can be adjusted to adapt to different positions and mounting requirements.

Wherein: the mounting panel is equipped with a plurality of equipment fixing hole and topology optimization structure, the front and back portion of mounting panel is equipped with the ground connection hole respectively.

Wherein: the lower end of each mounting frame connecting hole is provided with a supporting plate nut for fixing a mounting screw through threads.

Wherein: the lower through hole is provided with a spherical bearing.

Wherein: the both sides of lower clutch are equipped with arc connecting portion respectively, the fuselage connecting hole is located on the side bottom plate of arc connecting portion.

Wherein: connecting bolt's one end is equipped with locking structure, locking structure contains locking cover and stop pin, connecting bolt's end is located to locking cover detachable cover, and locking cover and connecting bolt are equipped with the pinhole that supplies the stop pin to run through in order to lock connecting bolt.

As can be seen from the above, the aircraft fuselage external device mounting structure using the four-joint of the present invention has the following effects:

1. the equipment with the weight of dozens of kilograms, the length of 1-2 meters and the width of 0.3-1 meter can be firmly installed outside the airplane body.

2. The mounting structure is compact and light, the distance between the upper surface of the mounting rack and the top of the airplane body can be lower than 40mm, and the weight can be controlled within 20 kilograms. Aerodynamic force on the external structure of the airplane body is reduced, meanwhile, the weight is light, and flying fuel consumption can be saved.

3. The design of four joints is adopted, the design concept of breakage-safety is realized, any joint fails, and the mounting frame and the equipment can still be fixed by the remaining three joints.

4. The installation and maintenance are easy, and if the equipment breaks down, the equipment is only required to be detached from the mounting frame for replacement.

5. Can release aircraft fuselage structure loaded deformation through the design of 4 joints and cross overall arrangement, can not cause the stress concentration with fuselage connection region.

6. The applicability is good, and to different models, through connecting the reservation position on the mounting bracket, the interval that each connects can be adjusted, realizes that one set of mounting structure satisfies the size of different models.

The details of the present invention can be obtained from the following description and the attached drawings.

Drawings

Fig. 1 shows a schematic structural diagram of the aircraft fuselage external equipment mounting structure adopting the four-joint of the present invention.

Figure 2 shows a front view of the position of the four joints of the present invention.

Fig. 3 shows a top view of the four joint positions in the present invention.

Fig. 4 shows a schematic structural diagram of the mounting plate of the present invention.

Fig. 5 shows a front view of the middle joint structure of the present invention.

Fig. 6 shows a top view of the middle joint structure of the present invention.

Fig. 7 shows an exploded view of the middle joint structure of the present invention.

Reference numerals:

10. a body; 11. a fuselage skin; 20. mounting a plate; 21. mounting screws; 22. an equipment mounting hole; 23. a joint mounting structure; 24. a ground hole; 25. a topology optimization structure; 26. a mounting frame edge; 27. a cowl connection structure; 31. a lower joint; 32. an upper joint; 33. a connecting bolt; 34. a machine body connecting hole; 35. an arc-shaped connecting part; 36. a single tab; 37. a spherical bearing; 38. opening a grounding hole; 39. a mounting bracket connection hole; 41. a pallet nut; 42. double-lug pieces; 43. a locking structure; 30. a front joint; 40. a rear joint; 50. a left joint; 60. and a right joint.

Detailed Description

Referring to fig. 1 to 7, the aircraft body external device mounting structure using the four-joint of the present invention is shown.

As shown in fig. 1, the aircraft fuselage external equipment mounting structure using four joints includes four joints fixed to a fuselage skin 11 of a fuselage 10 and a mounting plate 20 connected to the fuselage 10 through the four joints, and referring to fig. 2 and 3, arrows in fig. 1 and 3 are in a nose direction, the four joints include front joints 30 and rear joints 40 located on front and rear sides and left joints 50 and right joints 60 located on both sides, joint structures of the four joints are the same, the front joints 30 and the rear joints 40 are arranged laterally, the left joints 50 and the right joints 60 are arranged vertically, and the mounting plate 20 is fixed to the four joints through a plurality of mounting screws 21.

As shown in fig. 4, in one embodiment of the mounting plate 20, the front end of the mounting plate is arc-shaped, the rear end of the mounting plate is tapered mounting frame edge 26, the periphery of the mounting frame 20 is provided with a fairing connecting structure 27, the positions of the mounting plate 20 corresponding to the four joints are respectively provided with a joint mounting structure 23, the joint mounting structure 23 comprises a plurality of mounting through holes for the mounting screws 21 to penetrate through, the number of the mounting through holes is greater than the number of the mounting through holes required for fixing each joint, so that the mounting position can be adjusted to adapt to different positions and mounting requirements, the mounting plate 20 is provided with a plurality of device mounting holes 22 and a topology optimization structure 25, the device mounting holes 22 can fix required devices, and the front and rear portions of the mounting plate 20 are respectively provided with grounding holes 24.

Referring to fig. 5, 6 and 7, one embodiment of a joint structure is shown, the joint structure includes a lower joint 31, an upper joint 32 and a connecting bolt 44 connecting the lower joint and the upper joint together, two sides of the lower joint 31 are provided with a plurality of fuselage connecting holes 34 to be fixed to the fuselage skin 11 by screws and the like, preferably, two sides of the lower joint 31 are respectively provided with an arc-shaped connecting portion 35, the fuselage connecting holes 34 are provided on side bottom plates of the arc-shaped connecting portions 35, the arc-shaped connecting portions 35 better fit the fuselage, a single lug 36 is provided in the middle of the lower joint 31, the single lug 36 is provided with a lower through hole for the connecting bolt 37 to pass through, the lower through hole may be provided with a spherical bearing 37, and preferably, one side of the lower joint 31 is provided with a grounding hole 38.

The upper joint 32 can be an i-shaped structure as shown in the drawing, and is provided with a plurality of mounting frame connecting holes 39, the mounting frame connecting holes 39 are used for the installation screws 21 to penetrate and fix, the lower ends of the mounting frame connecting holes 39 are provided with supporting plate nuts 41 for fixing the installation screws 21 through threads, the lower end of the upper joint 32 is provided with double lug pieces 42 which are respectively arranged at two sides of the single lug piece 36, the double lug pieces 42 are provided with upper through holes for the connection bolts 37 to penetrate, and therefore the rotatable fixation of the upper joint and the lower joint is achieved after the connection bolts sequentially penetrate through the double lug pieces and the single lug pieces.

Wherein, connecting bolt's one end is equipped with locking structure 43, locking structure 43 can contain locking cover and stop pin, connecting bolt's end is located to locking cover detachable cover, and locking cover and connecting bolt are equipped with the pinhole that supplies the stop pin to run through to lock connecting bolt.

The left joint and the right joint of the airplane mainly bear aerodynamic force and inertia force in the front-back direction of the airplane, deformation displacement of the airplane body in the Y direction is released, and the axis direction of a connecting bolt of the left joint and the right joint is along the Y direction of the airplane body; the front joint and the rear joint mainly bear lateral aerodynamic force and inertial force of an airplane, the deformation displacement of the airplane body in the X direction is released, and the axis direction of the connecting bolt of the front joint and the rear joint is along the X direction of the airplane body.

The mounting bracket is equipped with edge appearance and the connection structure that can match the external equipment radome fairing, and topology optimization structure can reduce the weight of mounting bracket, and the earthing hole can be used for carrying out electrically conductive through the bonding area with the mounting bracket with the earthing through-hole of lower clutch, realizes the equipotential.

The spherical bearing is embedded into the single lug of the lower joint, so that the bearing can rotate in a certain angle, the special use working condition of the airplane is facilitated, the lower joint and the contact surface part of the airplane body adopt the arc-shaped design, the outline of the airplane body can be better attached, the double lugs of the upper joint are designed, so that enough gaps are designed between the lugs, and the upper joint and the lower joint can move along the axis of the connecting bolt to each other

The utility model discloses a 4 connect and place on the fuselage covering according to the overall arrangement that figure 3 shows, the distance between the joint can be according to different model adjustment. Bolts are used to pass through round holes in the joints to connect the joints with the fuselage structure, and then the mounting frame can be connected to the four joints through connecting bolts, and the specific mounting steps are as follows:

step 1: lower joints are mounted on the fuselage, each lower joint being mounted to the aircraft fuselage structure by means of 4 high-lock bolts. The high-locking bolt penetrates through the skin and is connected to the internal structure of the fuselage;

step 2: installing an upper joint, connecting the upper joint and the lower joint by using bolts, and making a safety to prevent loosening;

and step 3: placing a mounting frame, and mounting the mounting frame to the upper joint by using bolts;

and 4, step 4: and (4) mounting external equipment, and mounting the equipment on the mounting frame by using bolts.

Thus, the integral installation of the external equipment and the installation structure on the airplane is realized.

It is to be understood that the above description and illustrations are exemplary only and are not intended to limit the present disclosure, application, or uses. While embodiments have been described in the embodiments and depicted in the drawings, the present invention is not limited to the particular examples illustrated by the drawings and described in the embodiments as the best mode presently contemplated for carrying out the teachings of the present invention, and the scope of the present invention is intended to include any embodiments that fall within the foregoing description and the appended claims.

Claims

1. The utility model provides an adopt aircraft fuselage external equipment mounting structure of four joints, includes four joints on the fuselage skin that is fixed in the fuselage and connects to the mounting panel of fuselage through four joints, its characterized in that:

2. An aircraft fuselage exterior equipment mounting structure using a quad joint as claimed in claim 1, wherein: the joint design contains lower clutch, top connection and will go up the connecting bolt that the joint connection is in the same place, the both sides of lower clutch are equipped with a plurality of fuselage connecting holes in order to be fixed to the fuselage covering, the middle part of lower clutch is equipped with the auricle, the auricle is equipped with the lower through-hole that supplies connecting bolt to run through, the top connection is equipped with a plurality of mounting bracket connecting holes, the lower extreme of top connection is equipped with the ears piece of arranging the auricle both sides in branch, thereby the ears piece is equipped with the rotatable fixed of realizing the top connection after supplying connecting bolt through-hole in proper order runs through auricle and auricle piece.

3. An aircraft fuselage exterior equipment mounting structure using a quad joint as claimed in claim 1, wherein: the front end of mounting panel is circular-arc, and the rear end is the mounting bracket edge of taper shape, the periphery of mounting bracket is equipped with radome fairing connection structure.

4. An aircraft fuselage exterior equipment mounting structure using a quad joint as claimed in claim 1, wherein: the position that the mounting panel corresponds four joints is equipped with respectively and connects mounting structure, connect mounting structure to contain the interval and set up a plurality of installation through-holes that supply the mounting screw to run through.

5. An aircraft fuselage exterior equipment mounting structure using a quad-joint as defined in claim 4, wherein: the number of the mounting through holes is larger than the number required for fixing each joint, so that the mounting position can be adjusted to adapt to different positions and mounting requirements.

6. An aircraft fuselage exterior equipment mounting structure using a quad joint as claimed in claim 1, wherein: the mounting panel is equipped with a plurality of equipment fixing hole and topology optimization structure, the front and back portion of mounting panel is equipped with the ground connection hole respectively.

7. An aircraft fuselage exterior equipment mounting structure using a quad joint as claimed in claim 2, wherein: the lower end of each mounting frame connecting hole is provided with a supporting plate nut for fixing a mounting screw through threads.

8. An aircraft fuselage exterior equipment mounting structure using a quad joint as claimed in claim 2, wherein: the lower through hole is provided with a spherical bearing.

9. An aircraft fuselage exterior equipment mounting structure using a quad joint as claimed in claim 2, wherein: the both sides of lower clutch are equipped with arc connecting portion respectively, the fuselage connecting hole is located on the side bottom plate of arc connecting portion.

10. An aircraft fuselage exterior equipment mounting structure using a quad joint as claimed in claim 2, wherein: connecting bolt's one end is equipped with locking structure, locking structure contains locking cover and stop pin, connecting bolt's end is located to locking cover detachable cover, and locking cover and connecting bolt are equipped with the pinhole that supplies the stop pin to run through in order to lock connecting bolt.