Aircraft wing body fairing panel mounting structure

Abstract

The utility model discloses an aircraft wing body fairing panel mounting structure, and belongs to the technical field of aircraft manufacturing. The mounting structure comprises a wing body fairing framework, a wing body fairing panel and a positioning assembly, wherein a first positioning hole and a second positioning hole are respectively formed in two corner positions on a diagonal line of the wing body fairing framework; a third positioning hole and a fourth positioning hole are respectively formed in two corner positions on a diagonal line of the wing body fairing panel; the positioning assembly comprises a first positioning piece and a second positioning piece, the first positioning piece is inserted into the first positioning hole and the third positioning hole which are aligned to limit relative movement between the wing body fairing panel and the wing body fairing framework, and the second positioning piece is inserted into the second positioning hole and the fourth positioning hole which are aligned to limit relative movement between the wing body fairing panel and the wing body fairing framework. The relative rotation between the wing body fairing panel and the wing body fairing framework is limited, so that the relative position of the wing body fairing panel on the wing body fairing framework can be determined quickly and accurately.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft manufacturing, especially to an aircraft wing-body fairing panel mounting structure. BACKGROUND

[0002] When the connecting holes are processed on the wing-body fairing panel and the wing-body fairing framework, the matching hole method is usually adopted, that is, a connecting hole is first made on one of the wing-body fairing panel and the wing-body fairing framework, and then a corresponding connecting hole is made on the other one according to the made connecting hole to complete the drilling of the connecting hole; and then the fastener is screwed into the two aligned connecting holes to realize the mounting of the wing-body fairing panel on the wing-body fairing framework.

[0003] In the process of mounting the wing-body fairing panel on the wing-body fairing framework, the specific mounting position of the wing-body fairing panel on the wing-body fairing framework and the gap between the two adjacent wing-body fairing panels on the wing-body fairing framework are preliminarily determined by manual observation, and then the wing-body fairing panel is preliminarily fastened and mounted on the wing-body fairing framework by the fastener; and then the specific mounting position of the wing-body fairing panel needs to be adjusted for one or more times to ensure that the specific mounting position of the wing-body fairing panel on the wing-body fairing framework and the gap between the two adjacent wing-body fairing panels on the wing-body fairing framework meet the requirements.

[0004] However, the above mounting method of manual observation and repeated position adjustment has the following problems: 1) the installation position of the wing-body fairing panel is determined by manual observation, which takes a long time, and the wing-body fairing panel needs to be repeatedly disassembled and assembled during the installation process, resulting in low installation efficiency of the wing-body fairing panel; 2) due to human differences, it is difficult to ensure the accuracy of the installation position of the wing-body fairing panel on the wing-body fairing framework and the gap between the two adjacent wing-body fairing panels; 3) since the number of wing-body fairing panels mounted on the wing-body fairing framework is large and they are related to each other, it is difficult to ensure the installation effect of each wing-body fairing panel; 4) when the wing-body fairing panel needs to be replaced due to damage, the replaced wing-body fairing panel still needs to be reinstalled by the mounting method of manual observation and repeated position adjustment, which is time-consuming and laborious, and the wing-body fairing panel cannot be quickly replaced. SUMMARY

[0005] The utility model aims at providing an aircraft wing-body fairing panel mounting structure which can limit the degrees of freedom between the wing-body fairing panel and the wing-body fairing framework, quickly and accurately determine the relative position of the wing-body fairing panel on the wing-body fairing framework.

[0006] To achieve the above object, the utility model adopts the following technical scheme:

[0007] An aircraft wing-body fairing panel mounting structure comprises:

[0008] The wing-body fairing framework is provided with a first positioning hole and a second positioning hole at two corner positions on a pair of diagonal lines of the wing-body fairing framework respectively;

[0009] The wing-body fairing panel is provided with a third positioning hole and a fourth positioning hole at two corner positions on a pair of diagonal lines of the wing-body fairing panel respectively, the wing-body fairing panel is attached to one side surface of the wing-body fairing framework, and the third positioning hole is aligned with the first positioning hole, and the fourth positioning hole is aligned with the second positioning hole;

[0010] The positioning assembly comprises a first positioning member and a second positioning member, the first positioning member is inserted into the first positioning hole and the third positioning hole to limit the relative movement between the wing-body fairing panel and the wing-body fairing framework, and the second positioning member is inserted into the second positioning hole and the fourth positioning hole to limit the relative rotation between the wing-body fairing panel and the wing-body fairing framework.

[0011] As an optional scheme, the outer circumferential surface of the first positioning member is in contact with the inner wall surface of the first positioning hole and the third positioning hole, and the outer circumferential surface of the second positioning member is in contact with the inner wall surface of the second positioning hole and the fourth positioning hole.

[0012] As an optional scheme, the first positioning hole and the third positioning hole are both first circular holes, and the hole diameter of the first positioning hole is equal to the hole diameter of the third positioning hole.

[0013] As an optional scheme, one of the second positioning hole and the fourth positioning hole is a second circular hole, and the other is an elliptical hole.

[0014] As an optional scheme, the hole diameter of the second circular hole, the minor axis of the elliptical hole, the hole diameter of the first positioning hole and the hole diameter of the third positioning hole are equal, and the major axis of the elliptical hole is greater than the minor axis of the elliptical hole.

[0015] As an optional scheme, the major axis direction of the elliptical hole is parallel to the wing-body fairing framework or the diagonal line direction of the wing-body fairing framework.

[0016] As an optional scheme, the wing-body fairing framework is provided with a first connecting hole, and the wing-body fairing panel is provided with a second connecting hole; the aircraft wing-body fairing panel mounting structure further comprises:

[0017] A fastener is connected to the aligned first connecting hole and the second connecting hole.

[0018] As an option, a gap is provided between the outer peripheral surface of the fastener and the inner wall surface of the first connecting hole and the second connecting hole.

[0019] As an option, a plurality of first connecting holes are provided on the four sides of the wing-body fairing framework, and a plurality of second connecting holes are provided on the four sides of the wing-body fairing panel, one first connecting hole is aligned with one second connecting hole, and each first connecting hole on the same side is arranged on a first straight line, and each second connecting hole on the same side is arranged on a second straight line.

[0020] As an option, the center of the first positioning hole and the center of the second positioning hole are respectively located on the outer side of the first straight line, and the center of the third positioning hole and the center of the fourth positioning hole are respectively located on the outer side of the second straight line.

[0021] The beneficial effects of the present application are as follows:

[0022] The airplane wing-body fairing panel mounting structure in the utility model, through setting up the first positioning hole and the second positioning hole which cooperate with each other at the two corner positions on the pair of angle lines of the wing-body fairing framework, and setting up the third positioning hole and the fourth positioning hole which cooperate with each other at the two corner positions on the pair of angle lines of the wing-body fairing panel simultaneously, when the wing-body fairing panel is pasted on one side of the wing-body fairing framework, the third positioning hole is aligned with the first positioning hole, and the fourth positioning hole is aligned with the second positioning hole, then the first positioning piece is inserted into the first positioning hole and the third positioning hole, so that the relative movement between the wing-body fairing panel and the wing-body fairing framework is limited through the inserting effect of the first positioning piece in the aligned first positioning hole and third positioning hole, meanwhile, the second positioning piece is inserted into the second positioning hole and the fourth positioning hole, so that the relative rotation between the wing-body fairing panel and the wing-body fairing framework is limited through the inserting effect of the second positioning piece in the aligned second positioning hole and fourth positioning hole, thereby the freedom between the wing-body fairing panel and the wing-body fairing framework can be limited, the relative position of the wing-body fairing panel on the wing-body fairing framework can be determined quickly, 1), the wing-body fairing panel can be positioned quickly on the wing-body fairing framework, the installation position of the wing-body fairing panel is determined in a short time, and the wing-body fairing panel does not need to be disassembled repeatedly in the installation process, so that the installation efficiency of the wing-body fairing panel is higher, 2), due to the accurate positioning effect of the first positioning piece and the second positioning piece, the installation position of the wing-body fairing panel on the wing-body fairing framework and the accuracy of the gap between the adjacent two wing-body fairing panels can be ensured, 3), due to the installation position of each wing-body fairing panel on the wing-body fairing framework can be determined quickly and accurately, so that the installation effect of each wing-body fairing panel can be ensured, 4), when the wing-body fairing panel needs to be replaced due to damage, the wing-body fairing panel after replacement only needs to be positioned and inserted through the first positioning piece and the second positioning piece, and does not need to be reinstalled through the installation mode of artificial observation and multiple repeated position adjustment, so that time and labor are saved, and the wing-body fairing panel can be replaced quickly. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 is the structure diagram of the airplane wing-body fairing panel mounting structure (provided with one installation area) provided by the utility model Figure 1 ;

[0024] Figure 2 is the structure diagram of the wing-body fairing framework (provided with multiple installation areas) provided by the utility model

[0025] Figure 3 is the structure diagram of the airplane wing-body fairing panel mounting structure (provided with one installation area) provided by the utility model Figure 2 ;

[0026] Figure 4 This is an exploded view of the aircraft wing-body fairing panel mounting structure (which has a mounting area but no positioning components and fasteners) provided by this utility model from one perspective.

[0027] Figure 5 This is an exploded structural diagram of the aircraft wing-body fairing panel mounting structure (which has one mounting area but no positioning components and fasteners) provided by this utility model from another perspective.

[0028] Figure 6 yes Figure 5 A magnified schematic diagram of the local structure at point A;

[0029] Figure 7 yes Figure 5 A magnified view of the structure at point B in the middle;

[0030] Figure 8 yes Figure 5 A magnified schematic diagram of the local structure at point C;

[0031] Figure 9 yes Figure 5 A magnified schematic diagram of the local structure at point D;

[0032] Figure 10 This is a flowchart illustrating the processing method provided by this utility model;

[0033] Figure 11 This is a flowchart illustrating the calculation process of the tolerance value provided by this utility model.

[0034] Explanation of reference numerals in the attached figures:

[0035] 10 - Aircraft wing-body fairing panel mounting structure;

[0036] 1-Wing-body fairing frame; 11-First positioning hole; 12-Second positioning hole; 13-Mounting area; 14-First connection hole;

[0037] 2-Wing-body fairing panel; 21-Third positioning hole; 22-Fourth positioning hole; 23-Second connecting hole. Detailed Implementation

[0038] All features disclosed in this specification, or all steps in all disclosed methods or processes, may be combined in any way, except for mutually exclusive features and / or steps.

[0039] Any feature in the description disclosed herein can be replaced by alternative features serving the same, equivalent or a similar purpose, unless otherwise stated. That is, unless otherwise stated, each feature is one example only of a generic series of equivalent or similar features. Like reference numerals refer to like elements throughout the description.

[0040] In order to make the technical problems solved by the utility model, the technical scheme adopted and the technical effects reached more clear, the technical scheme of the utility model is further illustrated below by combining with the drawings and through specific implementation manners.

[0041] As Figures 1 to 5 shown, the present embodiment proposes an aircraft wing-body fairing panel mounting structure 10, which can realize quick positioning and installation of the wing-body fairing panel 2 on the wing-body fairing framework 1, and can quickly replace the wing-body fairing panel 2, so as to ensure that the installation efficiency of the wing-body fairing panel 2 is high and the accuracy of the installation position is high.

[0042] It is worth noting that the main improvement point in the present embodiment is the quick positioning and installation between the wing-body fairing panel 2 and the wing-body fairing framework 1, therefore, the working principle of the wing-body fairing panel 2 and the wing-body fairing framework 1 will not be described in detail here, and the working principle of the existing aircraft wing-body can be referred to.

[0043] Specifically, as Figures 1 to 9 shown, the aircraft wing-body fairing panel mounting structure 10 comprises the above-mentioned wing-body fairing framework 1, the above-mentioned wing-body fairing panel 2 and a positioning assembly; wherein two corner positions on a pair of diagonals of the wing-body fairing framework 1 are respectively provided with a first positioning hole 11 and a second positioning hole 12; two corner positions on a pair of diagonals of the wing-body fairing panel 2 are respectively provided with a third positioning hole 21 and a fourth positioning hole 22, the wing-body fairing panel 2 is attached to one side surface of the wing-body fairing framework 1, and the third positioning hole 21 is aligned with the first positioning hole 11, and the fourth positioning hole 22 is aligned with the second positioning hole 12; the positioning assembly comprises a first positioning member and a second positioning member, the first positioning member is inserted into the aligned first positioning hole 11 and third positioning hole 21, so as to limit the relative movement between the wing-body fairing panel 2 and the wing-body fairing framework 1, and the second positioning member is inserted into the aligned second positioning hole 12 and fourth positioning hole 22, so as to limit the relative rotation between the wing-body fairing panel 2 and the wing-body fairing framework 1.

[0044] The aircraft wing-body fairing panel mounting structure 10 in the embodiment adds four positioning holes and two positioning members which are used in cooperation with each other relative to the prior art; the first positioning hole 11 and the second positioning hole 12 which are used in cooperation with each other are arranged at two corner positions on a pair of diagonals of the wing-body fairing framework 1, and the third positioning hole 21 and the fourth positioning hole 22 which are used in cooperation with each other are arranged at two corner positions on a pair of diagonals of the wing-body fairing panel 2; when the wing-body fairing panel 2 is attached to one side of the wing-body fairing framework 1, the third positioning hole 21 is aligned with the first positioning hole 11, and the fourth positioning hole 22 is aligned with the second positioning hole 12; the first positioning member is inserted into the first positioning hole 11 and the third positioning hole 21, so that the relative movement between the wing-body fairing panel 2 and the wing-body fairing framework 1 is limited by the insertion of the first positioning member in the aligned first positioning hole 11 and third positioning hole 21; at the same time, the second positioning member is inserted into the second positioning hole 12 and the fourth positioning hole 22, so that the relative rotation between the wing-body fairing panel 2 and the wing-body fairing framework 1 is limited by the insertion of the second positioning member in the aligned second positioning hole 12 and fourth positioning hole 22; thereby the degrees of freedom between the wing-body fairing panel 2 and the wing-body fairing framework 1 can be limited, and the relative position of the wing-body fairing panel 2 on the wing-body fairing framework 1 can be quickly determined; 1) the wing-body fairing panel 2 can be quickly positioned on the wing-body fairing framework 1, so that the time for determining the installation position of the wing-body fairing panel 2 is short, and the wing-body fairing panel 2 does not need to be repeatedly disassembled and assembled during the installation process, so that the installation efficiency of the wing-body fairing panel 2 is high; 2) due to the accurate positioning effect of the first positioning member and the second positioning member, the accuracy of the installation position of the wing-body fairing panel 2 on the wing-body fairing framework 1 and the gap between two adjacent wing-body fairing panels 2 can be ensured; 3) since the installation position of each wing-body fairing panel 2 on the wing-body fairing framework 1 can be quickly and accurately determined, the installation effect of each wing-body fairing panel 2 can be ensured; 4) when the wing-body fairing panel 2 needs to be replaced due to damage, the replaced wing-body fairing panel 2 only needs to be positioned and inserted by the first positioning member and the second positioning member, and no longer needs to be reinstalled by the installation method of artificial observation and multiple repeated position adjustment, which saves time and effort and can realize the quick replacement of the wing-body fairing panel 2.

[0045] And, as Figure 4As shown, by arranging the first positioning hole 11 and the second positioning hole 12 on a pair of diagonals of the wing-body fairing framework 1, the first positioning hole 11 and the second positioning hole 12 can be arranged with a larger spacing on the wing-body fairing framework 1; meanwhile, by arranging the third positioning hole 21 and the fourth positioning hole 22 on a pair of diagonals of the wing-body fairing panel 2, the third positioning hole 21 and the fourth positioning hole 22 can be arranged with a larger spacing on the wing-body fairing panel 2; thus, the first positioning hole 11 and the second positioning hole 12 and the third positioning hole 21 and the fourth positioning hole 22 with a larger spacing can ensure better positioning effect, and thus the positioning stability and the positioning effect of the wing-body fairing panel 2 on the wing-body fairing framework 1 can be better ensured. In the embodiment, the first positioning member and the second positioning member can be a positioning pin.

[0046] Further, the outer periphery of the first positioning member is in contact with the inner wall of the first positioning hole 11 and the third positioning hole 21, so that the first positioning member can not have a certain amount of movement in the first positioning hole 11 and the third positioning hole 21, and the position of the first positioning member in the first positioning hole 11 and the third positioning hole 21 is fixed, so that the first positioning member cannot relatively shake or deviate; and the outer periphery of the second positioning member is in contact with the inner wall of the second positioning hole 12 and the fourth positioning hole 22, so that the second positioning member can not have a certain amount of movement in the second positioning hole 12 and the fourth positioning hole 22, and the position of the second positioning member in the second positioning hole 12 and the fourth positioning hole 22 is fixed, so that the second positioning member cannot relatively shake or deviate; thus, the first positioning member and the second positioning member with fixed positions can stably limit the freedom between the wing-body fairing panel 2 and the wing-body fairing framework 1, and after the positioning limitation of the first positioning member and the second positioning member, the installation position of the wing-body fairing panel 2 on the wing-body fairing framework 1 can be accurately unchanged.

[0047] It should be noted that the outer periphery of the first positioning member being in contact with the inner wall of the first positioning hole 11 and the third positioning hole 21 and the outer periphery of the second positioning member being in contact with the inner wall of the second positioning hole 12 and the fourth positioning hole 22 specifically means that there is substantially no gap between the outer periphery of the first positioning member and the inner wall of the first positioning hole 11 and the third positioning hole 21 and between the outer periphery of the second positioning member and the inner wall of the second positioning hole 12 and the fourth positioning hole 22, so that the position of the first positioning member and the second positioning member can be fixed while the machining difficulty of each positioning hole is reduced, and thus the machining difficulty of the wing-body fairing panel 2 and the wing-body fairing framework 1 is reduced.

[0048] Further, as shown in FIG. 4, the first positioning member and the second positioning member can be arranged on the wing-body fairing panel 2, and the first positioning hole 11 and the third positioning hole 21 can be arranged on the wing-body fairing framework 1. Figures 4 to 8As shown, the first positioning hole 11 and the third positioning hole 21 are both first circular holes, so as to facilitate the machining of the first positioning hole 11 and the third positioning hole 21, and further reduce the machining difficulty of the fuselage fairing framework 1 and the fuselage fairing panel 2; and the diameter of the first positioning hole 11 is equal to the diameter of the third positioning hole 21, so as to facilitate the accurate alignment between the first positioning hole 11 and the third positioning hole 21.

[0049] Specifically, as shown in Figures 4 to 9 , one of the second positioning hole 12 and the fourth positioning hole 22 is a second circular hole, and the other is an elliptical hole; on the one hand, it can facilitate the machining of the second positioning hole 12 and the fourth positioning hole 22, and better reduce the machining difficulty of the fuselage fairing framework 1 and the fuselage fairing panel 2; on the other hand, the elliptical structure of the elliptical hole can be quickly aligned with the second circular hole, avoiding the difficulty of inserting the second positioning member into the second positioning hole 12 and the fourth positioning hole 22 due to machining errors, thereby ensuring that the second positioning member can be smoothly inserted into the aligned second positioning hole 12 and fourth positioning hole 22.

[0050] In this embodiment, as shown in Figure 7 and Figure 9 , the second positioning hole 12 is an elliptical hole, and the fourth positioning hole 22 is a second circular hole, so as to avoid the problem of unsightly appearance of the fuselage fairing panel 2 exposed outside caused by setting the fourth positioning hole 22 as an elliptical hole, thereby ensuring that the overall structure of the fuselage fairing panel 2 and the fuselage fairing framework 1 after installation has better appearance. In other embodiments, the second positioning hole 12 can also be a square hole, which is not limited here, as long as the second positioning member can be smoothly inserted into the aligned second positioning hole 12 and fourth positioning hole 22.

[0051] Further, the diameter of the second circular hole, the minor axis of the elliptical hole, the diameter of the first positioning hole 11 and the diameter of the third positioning hole 21 are equal, and the major axis of the elliptical hole is greater than the minor axis of the elliptical hole, so as to facilitate the accurate alignment between the first positioning hole 11 and the third positioning hole 21, and the accurate alignment between the second positioning hole 12 and the fourth positioning hole 22.

[0052] Specifically, as shown in Figure 5 and Figure 7 , the major axis direction of the elliptical hole is parallel to the diagonal direction of the fuselage fairing framework 1 or the fuselage fairing framework 1, so as to facilitate the restriction of the relative rotation between the fuselage fairing panel 2 and the fuselage fairing framework 1 by the two long edges of the elliptical hole, thereby ensuring that the rotation restriction between the fuselage fairing panel 2 and the fuselage fairing framework 1 is stable and reliable.

[0053] Further, as shown in Figures 1 to 9As shown in the drawings, the wing-body fairing skeleton 1 is further provided with a first connecting hole 14, and the wing-body fairing panel 2 is further provided with a second connecting hole 23; the wing-body fairing panel mounting structure 10 further comprises a fastener, the fastener is connected to the aligned first connecting hole 14 and the second connecting hole 23, so as to realize the stable connection between the wing-body fairing panel 2 and the wing-body fairing skeleton 1. Specifically, the fastener can be a connecting bolt.

[0054] Specifically, the outer circumferential surface of the fastener has a gap with the inner wall surface of the first connecting hole 14 and the second connecting hole 23, on the one hand, it can reduce the processing difficulty of the first connecting hole 14 and the second connecting hole 23, and further reduce the processing difficulty of the wing-body fairing skeleton 1 and the wing-body fairing panel 2; on the other hand, it can be beneficial to the connection and fixation of the fastener in the first connecting hole 14 and the second connecting hole 23, and will not damage the first connecting hole 14 and the second connecting hole 23.

[0055] Further, as shown in the drawings, Figures 1 to 9 a plurality of first connecting holes 14 are arranged on the four sides of the wing-body fairing skeleton 1, and a plurality of second connecting holes 23 are arranged on the four sides of the wing-body fairing panel 2, one first connecting hole 14 is aligned with one second connecting hole 23, so as to better ensure the stable connection between the wing-body fairing panel 2 and the wing-body fairing skeleton 1.

[0056] Specifically, as shown in the drawings, Figures 1 to 9 each first connecting hole 14 on the same side is arranged on a first straight line, and each second connecting hole 23 on the same side is arranged on a second straight line, so as to facilitate the rapid alignment of the wing-body fairing panel 2 and the wing-body fairing skeleton 1, and reduce the processing difficulty of each first connecting hole 14 and each second connecting hole 23, thereby further reducing the processing difficulty of the wing-body fairing skeleton 1 and the wing-body fairing panel 2.

[0057] Further, the hole diameter of each first connecting hole 14 is equal, the hole diameter of each second connecting hole 23 is equal, and the hole diameter of the first connecting hole 14 is slightly larger than the hole diameter of the second connecting hole 23, so as to more facilitate the rapid alignment of the wing-body fairing panel 2 on the wing-body fairing skeleton 1.

[0058] Specifically, as shown in the drawings, Figures 4 to 9As shown, the center of the first positioning hole 11 and the center of the second positioning hole 12 are respectively located outside the first straight line, so that the distance between the first positioning hole 11 and the second positioning hole 12 is farther and the span is larger; and the center of the third positioning hole 21 and the center of the fourth positioning hole 22 are respectively located outside the second straight line, so that the distance between the third positioning hole 21 and the fourth positioning hole 22 is farther and the span is larger; so that the positioning effect of the wing-body fairing panel 2 on the wing-body fairing framework 1 is further ensured through the first positioning hole 11 and the second positioning hole 12 and the third positioning hole 21 and the fourth positioning hole 22 which are farther apart and have a larger span.

[0059] Specifically, as shown in Figure 1 and Figure 2 A plurality of mounting areas 13 are formed on the wing-body fairing framework 1, and the first positioning hole 11, the second positioning hole 12, and the first connecting hole 14 are arranged in each mounting area 13, so that one wing-body fairing panel 2 can be quickly positioned and mounted in one mounting area 13, and a plurality of wing-body fairing panels 2 can be simultaneously mounted on one wing-body fairing framework 1; and due to the positioning effect, the distance between two adjacent wing-body fairing panels 2 can meet the requirements.

[0060] It is worth noting that, as shown in Figure 1 and Figure 2 One square frame structure forms one mounting area 13, and the square frame structures are connected to each other to form a complete wing-body fairing framework 1 in a square structure, and the square frame structure can avoid the protruding structure of the wing-body fairing panel 2, so as to ensure the close fit between the wing-body fairing panel 2 and the wing-body fairing framework 1; the wing-body fairing panel 2 is in a square plate structure as a whole.

[0061] The specific installation process of the aircraft wing-body fairing panel mounting structure 10 in the embodiment is as follows:

[0062] First, the wing-body fairing panel 2 is parallelly attached to one side of the wing-body fairing framework 1, and the third positioning hole 21 is aligned with the first positioning hole 11, and the fourth positioning hole is aligned with the second positioning hole 12; then the first positioning member is inserted into the aligned first positioning hole 11 and third positioning hole 21, and the second positioning member is inserted into the aligned second positioning hole 12 and fourth positioning hole 22, and the outer periphery of the first positioning member and the inner wall of the first positioning hole 11 and the third positioning hole 21 are substantially gapless, and the outer periphery of the second positioning member and the inner wall of the second positioning hole 12 and the fourth positioning hole 22 are substantially gapless, so as to quickly and accurately position the wing-body fairing panel 2 on the wing-body fairing framework 1.

[0063] Then, the fastener is installed into the aligned first connecting hole 14 and second connecting hole 23, so as to accurately and stably install the wing-body fairing panel 2 onto the wing-body fairing framework 1, thereby realizing the installation between the wing-body fairing panel 2 and the wing-body fairing framework 1.

[0064] The aircraft wing-body fairing panel installation structure 10 in the embodiment can ensure the quick and accurate positioning of the wing-body fairing panel 2 on the wing-body fairing framework 1 through the first positioning member and the second positioning member, thereby ensuring the accuracy of the installation position of the wing-body fairing panel 2 on the wing-body fairing framework 1 and the gap between the adjacent two wing-body fairing panels 2, and the manual observation positioning is not needed, and the installation efficiency of the wing-body fairing panel 2 is improved.

[0065] The embodiment further provides a processing method based on the aircraft wing-body fairing panel installation structure 10 as described above, as shown in the figure, the processing method comprises the following steps: Figure 10 S1: data confirmation, the processing theoretical values of the wing-body fairing panel 2 and the wing-body fairing framework 1 need to be confirmed; S2: accurate positioning reference, the appropriate positioning references of the wing-body fairing panel 2 and the wing-body fairing framework 1 need to be determined; S3: obtain the tolerance scheme, according to the processing theoretical values determined in step S1 and the positioning references determined in step S2, and through the Monte Carlo calculation method, the specific tolerance scheme can be determined; S4: processing and positioning installation, the wing-body fairing panel 2 and the wing-body fairing framework 1 are processed according to the tolerance scheme obtained in step S3, so that the wing-body fairing panel 2 and the wing-body fairing framework 1 processed through the above steps can meet the requirements of quick positioning installation and quick replacement.

[0066] Specifically, in step S1, the processing theoretical values of the wing-body fairing panel 2 and the wing-body fairing framework 1 to be confirmed are specifically shown in the processing theoretical value table in Table 1; wherein the theoretical value of the hole diameter of the first positioning hole 11, the hole diameter of the third positioning hole 21 and the hole diameter of the fourth positioning hole 22 are all equal to D1 in Table 1, the theoretical value of the short diameter of the second positioning hole 12 is equal to D1 in Table 1, the theoretical value of the long diameter of the second positioning hole 12 is equal to D2 in Table 1, and D2>D1.

[0067] Table 1

[0068]

[0069] Furthermore, in step S2, the suitable positioning references for the wing-body fairing panel 2 to be determined are shown in Table 2 below, and the suitable positioning references for the wing-body fairing frame 1 to be determined are shown in Table 3 below. Step S2 is a key step to achieve rapid positioning and installation of the wing-body fairing panel 2. Selecting appropriate positioning references can greatly ensure the installation efficiency of the wing-body fairing panel 2.

[0070] Table 2

[0071] Positioning datum Corresponding feature name A1 Fitting surface to wing-body fairing skeleton B1 Third positioning hole C1 Fourth positioning hole

[0072] Table 3

[0073] Positioning datum Corresponding feature name A2 Fitting surface to wing-body fairing panel B2 First positioning hole C2 Second positioning hole

[0074] Based on the theoretical processing values ​​determined in Table 1 and the positioning references determined in Tables 2 and 3, and using the Monte Carlo calculation method, a specific tolerance scheme can be determined, such as... Figure 11 As shown, various tolerance values ​​are obtained; among them, the tolerance values ​​of the wing-body fairing panel 2 are shown in Table 4 below, and the wing-body fairing panel 2 is manufactured according to the tolerance value table; and the tolerance values ​​of the wing-body fairing frame 1 are shown in Table 5 below, and the wing-body fairing frame 1 is manufactured according to the tolerance value table; then, the positioning references A1, B1, and C1 on the wing-body fairing panel 2 in Table 2 above, and the corresponding positioning references A2, B2, and C2 on the wing-body fairing frame 1 in Table 3 above are used to complete the rapid positioning, installation, and replacement of the wing-body fairing panel 2 on the wing-body fairing frame 1.

[0075] Table 4

[0076]

[0077] Table 5

[0078]

[0079] Step S3 above is a key step to achieve the interchangeability and rapid positioning and installation requirements of the wing-body fairing panel 2. By adopting a reasonable tolerance scheme, it is possible to achieve rapid interchangeability of the wing-body fairing panel 2 and reasonable gap between two adjacent wing-body fairing panels 2 after the wing-body fairing panel 2 is assembled to the wing-body fairing frame 1.

[0080] The above merely describes preferred embodiments of the present application, and for those skilled in the art, according to the idea of the present application, changes can be made in the specific implementation manner and application range, and the content of the specification should not be understood as a limitation of the present application.

Claims

1. An aircraft wing-body fairing panel mounting structure, characterized by, The application relates to an aircraft wing-body fairing panel mounting structure. The first positioning hole (11) and the third positioning hole (21) are both first circular holes, and the hole diameter of the first positioning hole (11) is equal to the hole diameter of the third positioning hole (21). One of the second positioning hole (12) and the fourth positioning hole (22) is a second circular hole, and the other is an elliptical hole. The hole diameter of the second circular hole, the minor axis of the elliptical hole, the hole diameter of the first positioning hole (11) and the hole diameter of the third positioning hole (21) are equal, and the major axis of the elliptical hole is larger than the minor axis of the elliptical hole.

2. The aircraft wing-body fuselage fairing panel mounting structure as defined in claim 1, wherein, The major axis direction of the elliptical hole is parallel to the wing-body fairing framework (1) or the diagonal direction of the wing-body fairing framework (1).

3. The aircraft fuselage fairing panel mounting structure as defined in claim 1, wherein, The wing-body fairing framework (1) is provided with a first connecting hole (14), and the wing-body fairing panel (2) is provided with a second connecting hole (23).

4. The aircraft fuselage fairing panel mounting structure as defined in claim 1, wherein, The aircraft wing-body fairing panel mounting structure further comprises:

5. The aircraft fuselage fairing panel mounting structure as defined in claim 4, wherein, A fastener connected to the aligned first connecting hole (14) and the second connecting hole (23).

6. The aircraft fuselage fairing panel mounting structure as defined in claim 4, wherein, The outer periphery of the fastener has a gap with the inner wall surface of the first connecting hole (14) and the second connecting hole (23).

7. The aircraft wing-body fairing panel mounting structure of any of claims 1-6, wherein, The four sides of the wing-body fairing framework (1) are respectively provided with a plurality of first connecting holes (14), and the four sides of the wing-body fairing panel (2) are respectively provided with a plurality of second connecting holes (23); one first connecting hole (14) is aligned with one second connecting hole (23), and each first connecting hole (14) on the same side is arranged on a first straight line, and each second connecting hole (23) on the same side is arranged on a second straight line. ​ ​ 8. The aircraft wing-body fuselage fairing panel mounting structure as defined in claim 7, wherein, ​ 9. The aircraft fuselage panel mounting structure of Claim 7, wherein, ​ 10. The aircraft fuselage fairing panel mounting structure as defined in claim 9, wherein, The center of the first positioning hole (11) and the center of the second positioning hole (12) are respectively located outside the first straight line, and the center of the third positioning hole (21) and the center of the fourth positioning hole (22) are respectively located outside the second straight line.

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