Fastening structure and fastening method of transparent parts of civil aviation aircraft window

Abstract

The invention discloses a fastening structure of a window transparent part of a civil aviation aircraft, which comprises a body and a transparent part installed on the body; a frame of a prestressed structure is combined on the periphery of the transparent part, and a matching frame is formed on the frame installation structure. In the fastening structure of the present invention, no screw holes are provided on the transparent part, the internal stress balance of the transparent part itself will not be destroyed, and there is no stress weak point; a circle of prestressed frame is formed around the transparent part to form a The overall force-bearing structure of the transparent part with the prestressed buffer function and the body can effectively transfer the pressure difference and bird strike loads on the transparent part to the fuselage through the frame, ensuring the stability of the structure; the sealant, etc. The wrapping of the components makes it more firmly and permanently bonded to the edge of the transparent part, which greatly increases the service life of the sealant and polyurethane interlayer, protects the conductive strips in the laminated transparent parts, and prevents them from arcing or even breaking; reduce The replacement frequency of transparent parts reduces the cost of use.

Description

technical field [0001] The invention relates to various civil aviation aircraft such as passenger planes, cargo planes and trainer planes, in particular to a fastening structure and fastening method for transparent window parts of civil aviation planes. Background technique [0002] Civil aviation aircraft mainly include passenger planes, cargo planes and trainer planes. In addition to commercial aviation such as passenger and cargo regular routes and business flights, civil aviation also plays a role in different fields such as aerial surveying, physical prospecting, sowing, fertilization, spraying pesticides and aerial forest protection. play an important role. [0003] The transparent parts of civil aviation aircraft windows generally include transparent parts of front windshield, transparent parts of side windshield and transparent parts of portholes. As an important optical structural part of the aircraft, the transparent window parts of civil aviation aircraft must ha...

AI Technical Summary

Problems solved by technology

[0005] 1. If Figure 1-Figure 2 As shown, when installing the transparent part 2, since the sealant 1 is made of elastic material and the tightening force of each bolt is different, when the bolts are tightened, the aluminum alloy frame will be pressed to deform the sealant 1, and then the edge of the sealant 1 will be torn A gap is formed between the sealant 1 and the transparent part 2, making it easier for moisture to penetrate into the transparent part 2, corroding the transparent organic material interlayer (hereinafter referred to as the organic interlayer) 21 and the internal structure of the transparent part 2, accelerating its aging and failure, and This will lead to the degradation and cracking of the internal interlayer, and even the separation of the glass and the interlayer, posing a major safety hazard

[0006] 2. If Figure 1-Figure 3 , Figure 5 As shown, opening a hole on the organic interlayer 21 of the transparent part 2 has already destroyed the initial internal stress balance of the interlayer, and the vicinity of the hole becomes a weak link in strength, coupled with possible superimposed processing defects and assembly stress, the interlayer is very easy. Cracks are generated. Once encountering foreign object impact or aerodynamic load and body vibration during use, it may cause the interlayer crack to expand or even completely rupture, causing the cabin to lose its security and cause danger.

[0007] 3. If Figure 4 As shown, although the installation structure avoids the internal stress balance damage and stress concentration problems caused by the interlayer punching of the transparent part 2, the transparent part 2 cannot be firmly installed on the fuselage frame. When the transparent part 2 is subjected to a pressure difference When factors such as temperature difference change or external impact are affected, the structural adhesive 1 becomes its only stable guarantee. As the structural adhesive 1 continues to age, it will be difficult to withstand the above loads, and the transparent part 2 will fall off from the fuselage frame, resulting in accidents.

Under the condition of such severe pressure difference and temperature difference of transparent part 2, coupled with the joint action of aerodynamic load, vibration and fatigue load, any tiny residual stress or assembly stress near the interlayer hole can easily be extended into cracks, or even Flight accidents such as explosion of transparent part 2 due to cracks

[0009] 5. During the flight, due to the continuous increase of the internal and external pressure difference, the transparent part 2 will produce outward arching deformation and directly tear the edge of the sealant 1, so that there will be a gap between the edge of the sealant 1 and the transparent part 2. As the number of flights continues to accumulate, the gap between the edge of the sealant 1 and the transparent part 2 will gradually expand until the sealant 1 fails, which will cause moisture to continuously penetrate into the interior of the transparent part 2, corrode its internal structural adhesive, and accelerate its aging; and fix the transparent The bolts of part 2 will also loosen due to repeated deformation of transparent part 2, which will reduce the service life of transparent part 2 and become a great safety hazard

[0010] 6. When the polyurethane interlayer on the edge of the laminated transparent part 2 is eroded, it will change from transparent to milky white translucent, even yellow, cracked and delaminated, resulting in the conductive strips in the interlayer being stripped from the glass surface or even At the same time, an arc occurs at the junction between the inner edge of the conductive strip and the heating film. The local overheating generated by the arc will cause the conductive strip to change color and the anti-icing heating system to fail. In more serious cases, the outer transparent part 2 will be broken.

[0011] 7. If Figure 2-Figure 4 As shown, a metal part 3 is added during installation to increase the fastness of the installation structure of the transparent part 2. After the deformation of the part 2, the metal part will become a lever fulcrum to destroy the internal stress state of the edge of the transparent part 2, causing cracks on the edge of the transparent part 2 and even directly causing damage to the edge of the transparent part 2

If there is no effective solution to the above problems, it will be difficult to overcome related technical problems such as the rapid aging of the sealant on the transparent parts of civil aviation aircraft windows, short service life, difficult unit detection, and unstable moisture-proof sealing performance. The above problems still exist , the fastening and installation structure of the window transparent parts of civil aviation aircraft has also become a major problem for relevant technical personnel

[0032] However, with the progress of the times, the professional technologies of all walks of life are constantly being updated, and people's 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 aviation aircraft windows has not yet been solved.

For such important problems affecting people's lives and property safety, there is no reasonable solution at present, and the present invention fills the gap in this field

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