WO2014183611A1

WO2014183611A1 - Civil aircraft window body transparent element fastening structure and fastening method therefor

Info

Publication number: WO2014183611A1
Application number: PCT/CN2014/077240
Authority: WO
Inventors: 谢晓斌; 李震; 谢隽永
Original assignee: 一禾科技发展（上海）有限公司
Priority date: 2013-05-16
Filing date: 2014-05-12
Publication date: 2014-11-20
Also published as: CN103291184A; CN103291184B

Abstract

A civil aircraft window body transparent element fastening structure comprising an aircraft body (1) and a transparent element (2) mounted onto the aircraft body (1). An edge frame (3) is joined around the transparent element (2). A fastening structure matching the aircraft body (1) is formed on the edge frame (3). The edge frame (3) comprises a pressing component (31) and a fastening component (32). The pressing component (31) works in tandem with the transparent element (2) and presses onto the fastening component (32) to generate a prestress, thereby fastening the transparent element (2). The fastening structure does not disrupt an internal stress balance of the transparent element itself, thus ensuring structural stability.

Description

Civil aviation aircraft form transparent member fastening structure and fastening method thereof

The invention relates to various civil aviation aircrafts such as passenger aircrafts, freighters and trainers, and more particularly to a fastening structure of a transparent part of a civil aviation aircraft and a fastening method thereof. Background technique

Civil aviation aircraft mainly include passenger aircraft, freighters and trainers, etc. In addition to commercial airlines such as passenger and cargo regular routes and official flights, civil aviation also plays in various fields such as aviation measurement, physical prospecting, sowing, fertilization, spraying pesticides and aerial forest protection. An important role.

The transparent parts of civil aircraft aircraft generally include front windshield transparent parts, side windshield transparent parts and porthole transparent parts. The transparent part of the civil aircraft must have the following functions as an important optical structural component on the aircraft: First, it is called a structural member, and must have sufficient strength to withstand the cabin pressure, aerodynamic load, structural load of the aircraft, and flying birds. Impact load, etc.; the second is as a transparent observation window, which must have good optical properties, including transmittance, haze, resolution, optical angular deviation, optical distortion, ghosting, binocular parallax, birefringence, etc. The performance indicator; the third is that it must have reliability of use and a long service life. Its structural integrity, robustness and stability of use are closely related to the living environment of pilots, passengers and other crew members, and will directly affect flight safety and mission completion.

At present, the transparent parts of the civil aircraft's form are mostly laminated with a transparent organic material such as inorganic glass, PVB or polyurethane. The functional parts such as the conductive strip and the heating film are interposed between the laminated transparent parts and the sealant directly through the sealant. The fuselage skeleton is connected, or the hole is fixed in the transparent interlayer and fastened in the form of a bolt and a sleeve. The transparent structure of the window of the existing civil aircraft has the following several ways: As shown in Figure 5, the above methods usually have the following defects:

1. As shown in Figure 1-2, when the transparent member 2 is installed, since the sealant 1 is made of an elastic material and the fastening strength of each bolt is different, the aluminum alloy frame is pressed when the bolt is tightened to make the sealant 1 Deformation, and then tearing the edge of the sealant 1 causes a gap between the sealant 1 and the transparent member 2, so that moisture can easily penetrate into the interior of the transparent member 2, corroding the transparent organic material interlayer of the transparent member 2 (hereinafter referred to as an organic interlayer) 21 and the inside The structure accelerates its aging and failure, and causes the internal interlayer to degrade and crack, and even the glass and the intermediate interlayer are separated, which presents a major safety hazard.

2. As shown in Fig. 1 to Fig. 3 and Fig. 5, the opening of the organic interlayer 21 of the transparent member 2 has destroyed the initial internal stress balance of the interlayer, and the vicinity of the hole becomes a weak link in strength, and may be superimposed. The machining defects and assembly stresses are prone to cracks on the interlayer. In the course of use, if a foreign object impact or aerodynamic load or vibration of the body is encountered, the interlayer crack may be enlarged or even completely broken, which may cause the cabinet to become dense and dangerous.

3. As shown in FIG. 4, although the mounting structure avoids the internal stress balance damage and stress concentration caused by the interlayer punching of the transparent member 2, the transparent member 2 is not stably mounted on the fuselage skeleton, when transparent When the component 2 is affected by factors such as pressure difference, temperature difference change or external impact, the structural adhesive 1 becomes its only stable guarantee. As the structural adhesive 1 is aging, it will be difficult to bear the above load, and the transparent member 2 will be from the fuselage skeleton. The falling off caused an accident. 4. During the flight of the aircraft, the atmospheric pressure outside the cabin decreases with the increase of the flying height. For example, the air pressure at 18,000 meters is only about one-fifth of the ground, and the cabin is always in order to meet the physiological needs of crew members and passengers. Maintain an atmospheric pressure; the temperature outside the cabin will be reduced to about -60 ° C, while the cabin is maintained at about 20 ° C. Transparent member 2 Under such severe pressure difference and temperature difference, plus aerodynamic load, vibration and fatigue load, any small residual stress or assembly stress near the interlayer hole can be easily expanded into cracks, even The crack causes a flight accident such as blasting of the transparent member 2.

5. During the flight process, due to the continuous increase of the pressure difference between the inside and the outside, the transparent member 2 will deform outwardly and directly tear the edge of the sealant 1 to make a gap between the edge of the sealant 1 and the transparent member 2, The number of flights is continuously accumulated, and the gap between the edge of the sealant 1 and the transparent member 2 will gradually enlarge and the sealant 1 will fail, which will cause moisture to continuously penetrate into the transparent member 2, corrode the internal structural adhesive, accelerate its aging, and be fixed and transparent. The bolt of the piece 2 will also be loosened due to repeated deformation of the transparent member 2, which will reduce the service life of the transparent member 2 and become a great safety hazard.

6. When the polyurethane interlayer at the edge of the laminated transparent member 2 is eroded, it will change from transparent to milky white translucent, even yellowing, cracking and delamination, causing the conductive strip in the interlayer to be peeled off from the glass surface or even At the same time, an arc occurs at the boundary between the inner edge of the conductive strip and the heating film, and local overheating caused by the arc causes discoloration of the conductive strip and failure of the waterproof heating system, and more severely, the outer transparent member 2 is broken.

7. As shown in Fig. 2 to Fig. 4, the metal member 3 is added during installation to increase the fastness of the mounting structure of the transparent member 2. However, when the transparent member 2 is deformed due to pressure difference or the like, the hardness of the metal member 3 is greater than that of the transparent member. The hardness of the piece 2, so after the transparent member 2 is deformed, the metal member will become a lever fulcrum to break the internal stress state of the edge of the transparent member 2, causing cracks at the edge of the transparent member 2 and even directly causing damage to the edge of the transparent member 2.

8. Because the thermal expansion coefficient of the transparent member 2 and the metal frame of the fuselage is different, the thermal expansion coefficients of different materials in the laminated structural transparent member 2 are also different, and the laws of temperature change are also greatly different, so the air pressure is high. When the difference and the temperature difference change drastically, a complex stress state occurs near the mutual contact surface, and the degree of deformation of the inner and outer layers of the transparent member 2 is also different, which may affect or even destroy the stress state of the transparent member 2, especially near the screw hole.

In addition, the following is the aeronautical industry standard "Aircraft Cockpit Transparent Parts Design Manual" HB/Z 290-96, Section 6.1.3, issued by our Aviation Industry Corporation in 1996, summarizing the performance of various typical edge connectors. :

Hole margin 12mm typical structural element normal temperature tensile strength

Hole margin 15mm component original state normal temperature tensile strength

1 C - 1 Glue 1 Acrylic Glue

Kg/7.2cm! Kg/7.2cm | broken parts

1 2530 ! Bolt hole broken

2 1 2910 ! Bolt hole broken

3 2670 ! Bolt hole broken

4 2730 ' Bolt hole broken

5 1 2380

Hole damage average 2644 2560 Table 3 Hole margin 12mm Typical structural elements Original state Normal temperature fatigue life

C - 1 gel acrylic acid gel

Broken part of the broken part (times) (times)

1 346 edge hole o 8337 edge hole

2 427 edge hole 11107 edge hole

3 518 edge hole at 14267 edge hole

4 528 edge hole 1151 reinforcement sheet degumming slide

5 879 edge hole 25256 ! -- double hole edge break

1⁄2m

Average 539.6 12023.6 Table 4 Hole margin 12mm Typical structural components are 80°C χ 6h

Hole margin 15mm typical structural element original state room temperature fatigue life

C - 1 gel acrylic acid gel

Broken part 1 broken part (times) ― ( dO

11440 reinforcement transition 9454 edge hole

9614 edge hole 10368 edge hole

1782 Uninterrupted load ¹ 2552 edge hole

1745 uninterrupted stop; 1984 edge hole

1451 Uninterrupted stop 3906 edge hole

1952 edge hole

4166 edge hole table 6 hole margin 15mm typical structural component after 80 ° C χ 6h

Table 7 Hole margin 12mm Typical components after wet heat aging Room temperature fatigue life Acrylic glue (times) ^ Destruction site

13277 hole edge

10730 hole edge

14394 hole edge

6976 hole edge

19867! Hole edge Table 8 Typical structural components in the original state and single-sided heating, single-sided cold

The above tables detail the results of testing the performance of each edge connector under different conditions, from which the damage parts of the test piece under various conditions can be found, most of which occur at the bolt hole or edge of the transparent member. . Moreover, the test components specified in the standard have a structural unit and no assembly stress compared with the transparent parts used on the aircraft, and the test environment is far less complicated than the actual flight environment. It can be seen that the performance of the transparent member in the actual flight state is not up to the value in the above table, and is indeterminate and difficult to detect, so that the transparent member is perforated and connected to the fuselage skeleton through the bolt. The way, the security damage to the transparent part itself and even the entire fuselage structure is quite obvious.

At present, the installation structure of the transparent parts of various types of civil aviation aircraft in the world is almost the same, but the material, the glue and the manufacturing process of the laminated transparent parts are improved, and the installation structure of the transparent parts and the skeleton of the fuselage is not greatly changed. If the above problems do not have an effective solution, the related technical problems such as excessive aging of the sealant of the civil aircraft form transparent parts, short service life, difficulty in unit detection, and unstable moisture-proof sealing performance are difficult to overcome. The above problems still exist. The transparent mounting structure of the transparent parts of the civil aircraft has also become a major problem for the relevant technical personnel.

However, with the progress of the times, the professional skills of all walks of life are constantly updated, and the demand for civil aviation aircraft is also increasing. However, the technology that can effectively improve the safety and economy of the transparent parts of civil aircraft aircraft remains unresolved. . There is no reasonable solution to such important problems affecting people's lives and property safety, and the present invention fills this A blank in the field. Summary of the invention

SUMMARY OF THE INVENTION An object of the present invention is to overcome the deficiencies of the prior art and to provide a new fastening structure for a transparent member of a civil aircraft.

In order to solve the above technical problem, the present invention discloses a window transparent member fastening structure for a civil aircraft, comprising a body and a transparent member mounted on the body; the periphery of the transparent member is coupled with a frame on the frame Forming a mounting structure that cooperates with the body, the frame includes a pressing assembly and a fastening assembly, and the fastening assembly compresses the fastening assembly to generate a pre-stress by the cooperation of the pressing assembly and the transparent member to thereby fasten the transparent member.

According to a further improvement of the present invention, the fastening assembly includes two arcuate arms symmetrically clamped to the transparent member, and the two arcuate arms are interposed to form a surrounding space, and the arcuate arm includes a first arm and a second force arm connecting the first force arm, a joint of the first force arm and the second force arm forming a slip end, and the first force arm is away from the second force arm Forming a compression end, the second force arm forming a fastening end on a side away from the first force arm, the pressure end of the first force arm receiving the compression of the compression component and cooperating with the transparent The member drives the first and second force arms to generate a pre-stress.

A further improvement of the present invention is that the pressing assembly includes a first pressure bar and a second pressure bar; the first pressure bar is disposed outside the first force arm of the arcuate arm; The two sliding ends of the arcuate arms abut against the first pressure strip; the two pressure receiving ends of the arcuate arms abut against the second pressure strip, and the two fastening ends of the arcuate arms abut the Both sides of the transparent member;

The first pressure bar and the second pressure bar respectively open a plurality of corresponding bolt holes; the first pressure bar and the second pressure bar are fastened by bolts; the second pressure bar presses the The two compression ends of the arcuate arms are displaced toward the first pressure bar, and the two sliding ends of the arcuate arms are displaced from each other, and the two fastening ends of the arcuate arms are limited by the transparent member. Thereby driving the first force arm and the second force arm to generate a pre-stressed fastening of the transparent member.

According to a further improvement of the present invention, the transparent member performs position adjustment of a first direction and a second direction through the enclosure space.

A further improvement of the present invention is that the transparent member includes at least one organic interlayer; the frame includes a limiting pin; the organic interlayer forms a limiting hole that cooperates with the limiting pin, and the limiting pin is inserted in In the limit hole.

A further improvement of the invention resides in that the transparent member comprises a spaced apart array of one or more arrays of organic interlayers and one or more sets of inorganic glass layers.

A further improvement of the present invention consists in comprising a plurality of the fastening components, the fastening components being sleeved with each other and the fastening ends of each of the fastening components abutting against a corresponding set of organic interlayers or a group of inorganic glasses Outside the layer.

According to a further improvement of the present invention, a rubber strip is provided on the outer side of the frame.

A further improvement of the invention resides in that the second pressure strip is a T-piece.

According to a further improvement of the invention, the first force arm is a short straight arm and the second force arm is an arcuate arm. According to a further improvement of the present invention, a pressing plate is coupled to the fastening end, and a connecting area of the pressing plate and the second force arm is recessed inward to form a platen position adjusting area.

According to a further improvement of the present invention, the adhesive tape and the double-sided adhesive can be applied between the two fastening ends and the transparent member. Or pad cushion.

According to a further improvement of the present invention, the second force arm is spaced apart to form a plurality of overflow grooves; the enclosed space is filled with a sealant.

According to a further improvement of the present invention, the sliding end of the arcuate arm has a circular arc surface or a sloped surface.

A further improvement of the invention is that the thickness of the second force arm forms a thick to thin gradient from the slip end to the fastening end.

According to a further improvement of the present invention, the compressed end of the arcuate arm of the fastening assembly extends to form a rotational positioning rib, and the second pressure strip is formed with a rotary positioning groove corresponding to the rotational positioning edge of the fastening component.

A further improvement of the invention consists in that the pressed ends of the arcuate arms are connected by an arcuate deformation zone.

The present invention has the beneficial effects of using the above technical solutions:

1. In the invention, the transparent member is fastened by the frame and the skeleton of the body, and the bolt hole is no longer needed on the transparent member, and the internal stress balance of the transparent member is not damaged, and the original strength of the transparent member is maintained, and the stress is not weak. At the point, there is no assembly difficulty due to processing defects and the like, and stress concentration during the assembly process; there is no superposition and expansion of the above stresses during use.

2. In the present invention, the transparent member is fastened to the fuselage frame in a positionally adjustable manner, and the fastening component has a certain tolerance for the manufacturing error of the transparent member, thereby making the assembly of the transparent member and the skeleton more convenient, Avoid the generation of assembly stress, and at the same time greatly improve the assembly interchangeability of transparent parts.

3. The invention engages the plane of the transparent member through the prestressed structure, and generates a rigid frame integrated with the periphery of the transparent member, and fixes the transparent member to the skeleton frame through the frame, thereby forming a brand new The overall force-bearing structure of the transparent member with the pre-stress buffer function and the fuselage effectively transmits the load of the transparent member to the fuselage through the pre-stressed structure, ensuring the integrity of the fuselage structure.

4. The transparent part of the civil aviation aircraft of the invention is fastened by the prestressed structure and the skeleton of the fuselage, and the fastening component is selected from materials having considerable strength and at the same time having certain elasticity and toughness, and the transparent member and the fuselage skeleton during flight When different degrees of deformation occur due to different thermal expansion coefficients, it can be buffered by the pre-stress compensation function of the fastening component itself, effectively solving the destructive force generated by the difference between the two, and maintaining the safety and stability of the fuselage structure. .

5. In the present invention, the sealant and the structural adhesive are wrapped by the prestressed structural component to make it stronger and longer adhered to the edge of the transparent member, thereby greatly increasing the service life of the sealant and the structural adhesive, and laminating the transparent member. The polyurethane interlayer will not be corroded by moisture due to the failure of the sealant, avoiding the phenomenon of discoloration, cracking and delamination of the polyurethane interlayer in the laminated transparent member, protecting the conductive strip in the laminated transparent member and avoiding the conduction. The arc phenomenon caused by the breakage of the strip; and the compression and fastening of the laminated transparent member by the prestressed structural component, so that the relationship between the interlayers in the laminated transparent member is controlled, so that the interlayers in the laminated transparent member are laminated It can be bonded more effectively through the polyurethane interlayer, which will greatly increase the service life of the laminated transparent member, reduce the frequency of replacement of the laminated transparent member, reduce the cost, and improve the use efficiency.

6. In the present invention, the fastening component is made of a material having considerable strength and a certain elasticity and toughness. During the flight, the transparent member is subjected to deformation and stress changes caused by pressure difference, temperature difference, bird impact and the like. It can be buffered by the release and re-generation process of the pre-stress contained in the fastening component itself, which not only does not superimpose various complex stresses, but can eliminate or reduce the stress concentration to a certain extent, and maintain The structure of the fuselage is safe and stable.

7. The process of fastening the transparent member and the fuselage frame of the present invention eliminates the need to open a bolt hole in the transparent member. The choice of the transparent material will no longer be plagued and limited by the way of fastening. It is believed that more safe and reasonable aerospace glass forms will be used in the transparent parts of civil aircraft.

8. The present invention has the above-mentioned characteristics, so that the curved transparent windshield and the arcuate porthole and other unique shaped transparent pieces on the civil aircraft will be used more, and the stability of the transparent part of the window is improved and the life is prolonged. The maintenance strength has been reduced and other positive contributions have been made.

9. The prestressed fastening process of the present invention is to pre-stress the fastening component by tightening the relevant bolts. In the specific operation, the selection of the raw materials of each component and the geometric design are adopted in the design module of the previous stage. After the workers can tighten the relevant bolts in place, the preset tightening force can be obtained without being affected by uncertain factors such as the operating force, which greatly reduces the operating conditions and technical requirements.

10. In actual use, the edge of the transparent part of some civil aircraft forms has a circular arc surface. In the present invention, the second force arm of the fastening component is split into a plurality of jaws, so that the fastening end of the fastening component can be more closely attached to the arc surface of the transparent part of the civil aircraft window, so that the fastening component is not Under the premise of destroying the internal stress of the transparent part of the civil aircraft, the transparent parts of the civil aircraft form are tightened more firmly and stably. DRAWINGS

Figure 1-5 is a partial prior art installation structure of a transparent form of a civil aviation aircraft;

Figure 6 is a schematic view showing the overall structure of the aircraft of the window transparent member fastening structure of the present invention;

Figure 7 is a perspective view of a plane transparent member of a fastening structure for a transparent part of a civil aircraft of the present invention;

Figure 8 is a perspective view of a curved transparent member of a fastening structure for a transparent part of a civil aircraft of the present invention;

9 is a perspective view showing a connection structure between a transparent member and a frame according to an embodiment of the present invention;

Figure 10 is an exploded view of Figure 9;

11 is a schematic plan view showing a connection structure between a transparent member and a frame according to an embodiment of the present invention;

Figure 12 is a plan view showing the fastening assembly of the present invention;

Figure 13 is a schematic view showing the compression deformation of the arc deformation zone of the fastening assembly of the present invention;

Figure 14 is a schematic view showing the principle of fastening the frame and the transparent member in the fastening structure of the transparent member of the civil aircraft form of the present invention;

15 is a schematic plan view showing a connection structure between a transparent member and a frame according to Embodiment 2 of the present invention;

16 is a schematic plan view showing a connection structure between a transparent member and a frame according to Embodiment 3 of the present invention;

17 is a schematic plan view showing a connection structure between a transparent member and a frame according to Embodiment 4 of the present invention;

18-19 are schematic plan views showing a connection structure between a transparent member and a frame according to Embodiment 5 of the present invention;

20 is a schematic plan view showing a connection structure between a transparent member and a frame according to Embodiment 6 of the present invention.

Figure 21 is a schematic view of another preferred embodiment of the fastening assembly of the civil aircraft window transparent member fastening structure of the present invention. detailed description

The invention will now be further described in conjunction with specific embodiments.

Referring to Figures 6-8, in a first preferred embodiment of the present invention, a transparent form of a form of a civil aircraft of the present invention is tight The solid mounting structure includes a body 1 and a transparent member 2 mounted on the body 1; a periphery of the transparent member 2 is coupled to a frame 3, and the frame 3 is formed with a mounting structure for engaging the body 1. The frame 3 includes a pressing assembly 31 and a fastening assembly 32. The pressing member 32 is pressed by the pressing member 32 and the transparent member 2 to generate a pre-stress to thereby tighten the transparent member 2. The transparent member 2 can be made of the flat transparent member 2 shown in Fig. 7; the curved transparent member 2 shown in Fig. 8 can also be used.

Referring to Figures 9-14, the following definitions are now made in this embodiment for ease of description: The horizontal mounting direction of the transparent member 2 in Figures 9 and 10 is taken as the X-axis direction, and the thickness direction of the transparent member 2 is taken as the Y-axis direction. The vertical mounting direction of the transparent member 2 is taken as the Z-axis direction, and the X-axis is perpendicular to the Y-axis, and the Z-axis is perpendicular to the plane formed by the X-axis and the Y-axis;

The fastening component 32 comprises two arcuate arms 321 symmetrically clamped on the transparent member 2, and the material thereof should be selected from materials having considerable strength and elasticity and toughness, such as metal, engineering plastics, polymer materials, etc.; An arming space 320 is formed between the arms 321 , and the arcuate arm 321 includes a first force arm 3211 and a second force arm 3212 connecting the first force arm 3211 , and a joint of the first force arm 3211 and the second force arm 3212 . A sliding end 3213 is formed, and the sliding end 3213 has a circular arc surface or a sloped surface to ensure less resistance during the sliding process; the first force arm 3211 is pressed against the side away from the second force arm 3212. The end 3214, the pressure receiving end 3214 extends to form a rotating positioning edge 3217; the second force arm 3212 forms a fastening end 3215 on a side away from the first force arm 3211, the fastening end 3215 is coupled with a pressure plate 3216, and the pressure plate 3216 and The connecting portion of the second force arm 3212 is recessed inwardly to form a platen position adjusting portion 3218. The platen position adjusting portion 3218 can realize the slight self-position adjustment of the platen 3216 during the fastening process, so that the flat plate is more transparently attached. The second end of the first force arm 3211 and the second force arm 3212 are prestressed by the pressing member 31. In this embodiment, the first force arm 3211 is a short straight arm, the second force arm 3212 is an arcuate arm, and the thickness of the second force arm 3212 forms a thickness from the sliding end 3213 to the fastening end 3215. With a thin gradient, this structure ensures that the entire curved arm is fully and evenly deformed and is not easily broken. The two arcuate arms 321 are connected between the two pressure receiving ends 3214 by providing an arc deformation zone 3219. When the pressure receiving end 3214 of the first force arm 3211 is pressed, the arc deformation zone 3219 is pressed from the arc shape. The drawing process of the curved deformation zone 3219 is shown in FIG. 13; the design of the arc deformation zone 3219 ensures that the fastening component 32 has a certain extension space; the two compression ends 3214 of the fastening component 32 are matched. A plurality of bolt holes are formed. An adhesive (such as UV glue) or a double-sided tape (such as 3M glue) or a cushion (such as a rubber sheet) may be applied between the two fastening ends 3215 and the transparent member 2. The second force arm 3212 is spaced apart to form a plurality of overflow grooves. The use of the overflow groove serves to overflow the excess unsolidified sealant when the fastening component 32 is clamped and prevent the expansion or contraction of the sealant during the solidification process. The effect of the pre-stress generated by the solid assembly 32 ensures pre-stressed fastening between the fastening assembly 32 and the transparent member 2 and at the same time achieves a seal.

Referring to FIGS. 6, 10, and 11, the transparent member 2 includes at least one organic interlayer 21; and the side of the transparent member 2 is recessed to form the mounting groove 20; the transparent member 2 includes an organic interlayer 21 and inorganic materials bonded to both sides of the organic interlayer 21. The glass layer 22; the inorganic glass layer 22 is combined with the organic interlayer 21 to form the mounting groove 20.

The pressing member 31 includes a first pressure strip 311 and a second pressure strip 312. The second pressure strip 312 is a T-shaped member. The middle portion of the second pressure strip 312 forms a ridge 3122. The rib 3122 is embedded in the mounting groove 20. The first pressure bar 311, the fastening component 32 and the rib 3122 of the second pressure bar 312 are fastened through the bolt, thereby driving the first force arm 321 and the second force arm 322 of the fastening component 32 to generate pre-stress fastening. Transparent member 2.

The surface of the second pressure strip 312 is provided with two long-length rotary positioning grooves 3121, and the radius of the rotary positioning groove 3121 is equal to or slightly larger than the radius of the rotary positioning edge 3217, so that the entire transparent member is fastened. Knot When the structure is in the pre-fastening and fastening state, the rotation positioning edge 3217 can be effectively positioned and rotated in the rotation positioning groove 3121, and the two sliding ends 3213 are only displaced in the Y-axis direction on the surface of the first pressure bar.

The first pressure bar 311 is disposed on the outer side of the first force arm 3211 of the arcuate arm 321; the two sliding ends 3213 of the arcuate arm 321 of the fastening component 32 abut against the first pressure bar 311; the two pressure ends of the arcuate arm 321 3214 abuts against the second pressure strip 312, and the two fastening ends 3215 of the arcuate arm 321 abut against both sides of the transparent member 2.

The first pressure bar 311 and the second pressure bar 312 respectively open a plurality of corresponding bolt holes; the first pressure bar 311 and the second pressure bar 312 are fastened by bolts; the second pressure bar 312 presses the two pressures of the bow arm 321 The end 3214 is displaced toward the first pressure bar 311, and the two sliding ends 3213 of the arcuate arm 321 are displaced away from each other. The two fastening ends 3215 of the arcuate arm 321 are constrained by the transparent member 2, thereby driving the first force arm 3211. A pre-stressed fastening transparent member 2 is generated with the second force arm 3212.

The transparent member 2 is adjusted in the X-axis direction and the Z-axis direction by the enclosed space 320. The first pressure bar 311 is formed on the side of the pressing end 3111, and the side of the pressing end 3111 is formed as a connecting end 3112. In this embodiment, the connecting end 3112 is a mounting structure for the body 1. The first pressure bar 311 is fixed to the body 1 through the connecting end 3112. The mounting structure can also use other connection structures.

Further, a sealant may be filled in the gap between the second force arm 3212, the transparent member 2, and the second pressure strip 312, thereby achieving more stable fastening.

When the transparent member 2 is assembled, the second pressure strip 312 is placed in the enclosed space 320 of the fastening assembly 32 and the rotary positioning groove 3121 is engaged with the rotary positioning edge 3217, and then the sealant 320 is filled with the sealant in the enclosed space 320. The two fastening ends 3215 of the arm 321 abut against the two sides of the transparent member 2, the protruding strips 3122 are inserted into the mounting groove 20; the first pressure bar 311 is disposed on the outer side of the first force arm 3211; the two of the arcuate arms 321 The sliding end 3213 abuts against the first pressure strip 311, and the two pressure receiving ends 3214 of the arcuate arm 321 abut against the outer surface of the second pressure strip 312, through the first pressure strip 311, the fastening component 32 and the first The bolts of the bolt holes of the two pressure strips 312 are pre-tightened, and the transparent member 2 is adjusted in the X-axis direction and the Z-axis direction by the enclosure space 320. After the position of the transparent member 2 is adjusted, the first bolt is fastened by the bolt. The pressure bar 311 and the second pressure bar 312 are completed to be fastened.

The working principle of the entire fastening process is further described below with reference to FIGS. 10 and 14. The two pressure receiving ends 3214 of the arcuate arms 321 are displaced in the direction of the first pressure bar 311 by the compression of the second pressure bar 312, and the rotation positioning edge 3217 is rotated. The cooperation with the rotary positioning groove 3121 ensures that the compressed end 3214 is only displaced in the X-axis direction during the movement, and the distance between the compressed ends 3214 of the two arched arms 321 is controllable (unchanged) during the fastening process. At the same time, the two sliding ends 3213 are displaced away from each other by the inner side surface of the first pressure strip 311, and the two fastening ends 3215 are displaced close to each other until they abut against the side of the transparent member 2, so the two fastenings The distance between the pressure plates 3216 of the end 3215 is also controllable, and the fastening point on the transparent member 2 is also controllable; further pressing the two pressure receiving ends 3214 to the direction of the first pressure bar 311, thereby driving the two slips The ends 3213 continue to move away from each other, and the two fastening ends 3215 are now abutted against the side of the transparent member 2 and thus are constrained, and the first force arm 3211 and the second force arm 3212 are deformed thereby and prestressed. Stable response The transparent member 2 of the force structure and the frame 3 are brought into a fastening state, and the transparent member 2 is fastened. Similarly, when the prestressing needs to be released, as long as the corresponding bolt is loosened, the deformation of the arcuate arm 321 will return to the previously unfastened state, at which time the prestressing force automatically disappears, and the transparent member of the entire aircraft is fastened to the mounting structural component. They are lossless and reusable, saving cost and being environmentally friendly. Referring to FIG. 15, in a second preferred embodiment of the present invention, a main structure of a transparent fastening mounting structure for a civil aircraft of the present invention is the same as that of the first embodiment, except that: the rib 3122 is adjacent to the inorganic glass. A limiting pin 34 is formed on one side of the layer 22, and the organic interlayer 21 forms a limiting hole 211 that cooperates with the limiting pin 34. The limiting pin 34 is inserted into the limiting hole 211, and the limiting pin 34 and the limiting hole 211 are The contact does not occur under normal conditions, and the limit escape prevention effect is only achieved after the transparent member 2 is broken and deformed.

Referring to FIG. 16, in a third preferred embodiment of the present invention, the main structure of the window transparent member fastening structure of a civil aircraft of the present invention is the same as that of the second embodiment, except that the transparent member 2 includes a gap is formed between the two organic interlayers 21 and the two organic interlayers 21; the organic interlayer 21 on both sides of the gap is formed to form the mounting groove 20; the two sides of the protruding strips 3122 respectively form a limiting pin 34, and the two organic interlayers 21 respectively form a limiting pin 34 matching limit hole 211.

Referring to FIG. 17, in the fourth preferred embodiment of the present invention, the main structure of the window transparent member fastening structure of a civil aircraft of the present invention is the same as that of the second embodiment, and the difference is as follows: There is a seal 4.

Referring to FIG. 18, in a fifth preferred embodiment of the present invention, the main structure of the window transparent member fastening structure of a civil aircraft of the present invention is the same as that of the second embodiment, except that the transparent member 2 includes A set of organic interlayers 21 and a set of inorganic glass layers 22 are disposed at intervals, wherein the set of inorganic glass layers 22 are disposed outside the set of organic interlayers 21, and an inorganic glass layer 22 is further disposed between the set of organic interlayers 21. A fastening assembly 32 is included that is nested with one another and the fastening ends 3215 of each fastening assembly 32 abut against a corresponding set of organic interlayers 21 or a plurality of inorganic glass layers 22. Wherein, the two fastening ends 3125 of the inner fastening component 32 abut against the outer side of the set of organic interlayers; the two fastening ends 3125 of the outer fastening component 32 abut against the reconstituted inorganic glass layer The outer side. Since the strength of the organic interlayer 21 and the inorganic glass layer 22 are different, the required clamping force is also different. Therefore, by using the plurality of fastening components 32, the most suitable pre-preparation for matching the material to the transparent interlayer of different materials is realized. The stress prevents the unbalanced effect of pre-stressing on different transparent interlayers when a single fastening component 32 is used, avoids the problem of excessive prestressing of different transparent interlayers, or the problem that the pre-stress is too small to be sufficiently fastened.

Alternatively, a structure in which a plurality of fastening members 32 as shown in Fig. 19 are sleeved can be used.

Referring to FIG. 20, in a sixth preferred embodiment of the present invention, the main structure of the window transparent member fastening structure of a civil aircraft of the present invention is the same as that of the second embodiment, except that the transparent member 2 includes An organic interlayer 21, the inorganic interlayer 21 is respectively combined with an inorganic glass layer 22; the organic interlayer 21 forms a mounting groove 20; the protruding strip 3122 extends to form a positioning plate 31221, and a positioning pin 34 is formed on each side of the positioning plate 31221, the mounting groove The organic interlayer 21 on both sides of the 20 position forms a limiting hole 211 that cooperates with the limiting pin 34. The positioning plate 31221 functions to generate the limiting pin 34, which is not in direct contact with the transparent member 2 under normal conditions.

Referring to FIG. 21, when the edge of the transparent member 2 has a circular arc surface, the second force arm 3212 of the fastening component 32 can be split into a plurality of jaws to better conform to the circular arc surface of the transparent member 2, so that The fastening assembly 32 secures the transparent member 2 more firmly and stably without damaging the internal stress of the transparent member 2; further, an overflow groove is formed between the mutually split jaws, and the overflow groove is used. The excess unsolidified sealant spillage when the fastening assembly 32 is clamped and the effect of the expansion or contraction of the sealant during the solidification process on the pre-stressing of the fastening assembly 32 is prevented.

The present invention has been described in detail above with reference to the embodiments of the drawings, and various modifications of the present invention can be made by those skilled in the art in light of the above description. Therefore, some of the details of the embodiments are not to be construed as limiting the scope of the invention, and the scope of the invention is defined by the scope of the appended claims.

Claims

claims

1. A fastening structure for transparent parts of civil aviation aircraft windows, including a body and a transparent part installed on the body; It is characterized in that a frame is combined around the transparent part, and a frame is formed on the frame to match the body The fastening structure of the frame includes a pressing component and a fastening component, and the pressing component cooperates with the transparent part to press the fastening component to generate prestress and thereby fasten the transparent part.

2. The fastening structure of the window transparent part of a civil aviation aircraft as claimed in claim 1, characterized in that the fastening assembly includes two arcuate arms symmetrically clamped on the transparent part, and the two arcuate arms are sandwiched between them. Assuming that an enclosed space is formed, the arcuate arm includes a first force arm and a second force arm connected to the first force arm, and the connection between the first force arm and the second force arm forms a sliding end. , the first force arm forms a pressure end on a side away from the second force arm, the second force arm forms a fastening end on a side away from the first force arm, the first force arm The pressure-receiving end of the arm receives the pressure of the compression component and cooperates with the transparent member to drive the first force arm and the second force arm to generate prestress.

3. The window transparent part fastening structure of civil aviation aircraft as claimed in claim 2, characterized in that the pressing component includes a first pressure strip and a second pressure strip;

The first pressure strip is arranged outside the first force arm of the arcuate arm; the two sliding ends of the arcuate arm of the fastening assembly are against the first pressure strip; the two receiving ends of the arcuate arm are The pressing end is against the second pressure bar, and the two fastening ends of the arcuate arm are against both sides of the transparent piece;

The first pressure strip and the second pressure strip are respectively provided with a plurality of corresponding bolt holes; the first pressure strip and the second pressure strip are fastened by bolts; the second pressure strip presses the The two pressure-receiving ends of the arcuate arm are displaced in the direction of the first pressure bar, the two sliding ends of the arcuate arm are displaced away from each other, and the two fastening ends of the arcuate arm are limited by the transparent member, Thereby, the first force arm and the second force arm are driven to generate prestress to fasten the transparent member.

4. The fastening structure for window transparent parts of civil aviation aircraft according to claim 3, characterized in that the position of the transparent part is adjusted in a first direction and a second direction through the enclosed space.

5. The fastening structure of the window transparent part of the civil aviation aircraft as claimed in claim 4, wherein the transparent part includes at least one organic interlayer; the frame includes a limiting pin; the organic interlayer is formed with the The limiting hole is matched with the limiting pin, and the limiting pin is inserted into the limiting hole.

6. The fastening structure for window transparent parts of civil aviation aircraft as claimed in claim 5, characterized in that the transparent part includes one or more groups of organic interlayers and one or more groups of inorganic glass layers arranged at intervals.

7. The fastening structure for window transparent parts of civil aviation aircraft as claimed in claim 6, characterized in that it includes a plurality of said fastening components, said fastening components are nested with each other and each said fastening component The fastening end is against the outside of a corresponding set of organic interlayers or a set of inorganic glass layers.

8. The fastening structure for transparent parts of civil aviation aircraft windows according to any one of claims 5 to 7, characterized in that a seal is provided on the outside of the frame.

9. The window transparent part fastening structure of civil aviation aircraft according to any one of claims 5-7, characterized in that the second pressure strip is a T-shaped part.

10. The fastening structure for transparent parts of civil aviation aircraft windows according to any one of claims 2 to 7, characterized in that the first force arm is a short straight arm, and the second force arm is a short straight arm. Curved arm.

11. The fastening structure for window transparent parts of civil aviation aircraft according to any one of claims 2 to 7, characterized in that, a pressure plate is combined with the fastening end, and the pressure plate and the second force The connecting area of the arm is recessed inward to form a pressure plate position adjustment area.

12. The fastening structure for the window transparent part of a civil aviation aircraft according to any one of claims 2 to 7, characterized in that adhesive glue or clamping can be applied between the two fastening ends and the transparent part. Install double-sided tape or a cushion pad.

13. The fastening structure for transparent parts of civil aviation aircraft windows according to any one of claims 2 to 7, characterized in that the second force arms form a plurality of overflow grooves at intervals; in the enclosed space Filled with sealant.

14. The fastening structure for window transparent parts of civil aviation aircraft according to any one of claims 2 to 7, characterized in that: the sliding end of the arcuate arm is in the form of an arc surface or an inclined surface.

15 The fastening structure for window transparent parts of civil aviation aircraft according to any one of claims 2 to 7, characterized in that the thickness of the second force arm forms a thickness from the sliding end to the fastening end. Gradient from thick to thin.

16. The fastening structure for window transparent parts of civil aviation aircraft according to any one of claims 2 to 7, characterized in that: the pressure-receiving end of the arcuate arm of the fastening component extends to form a rotation positioning edge, so The second pressure strip is formed with a rotation positioning groove corresponding to the rotation positioning edge of the fastening component.

17. The fastening structure for window transparent parts of civil aviation aircraft according to any one of claims 2 to 7, characterized in that: the pressure-receiving ends of the arcuate arms are connected through an arc-shaped deformation zone.

18. A method for fastening window transparent parts of civil aviation aircraft using the fastening structure of any one of claims 1 to 7.