Ultraviolet-proof covering cloth for nose and fuselage of airplane

Abstract

The utility model relates to the technical field of covering cloth, in particular to ultraviolet-proof covering cloth for a nose and a fuselage of an airplane, which comprises a protective component used for covering the airplane, side surrounding cloth is arranged on the periphery of the protective component, the protective component is sequentially provided with waterproof cloth, ultraviolet-proof cloth, a drying layer, heat insulation cloth and a cotton cloth layer from top to bottom, and the side surrounding cloth is in a circular ring shape; according to the anti-ultraviolet covering cloth for the aircraft nose and fuselage, waterproof matching of the upper portion is achieved by arranging the waterproof cloth, the erosion influence of rainwater weather on the lower portion is reduced, and damage caused by long-time exposure and ultraviolet irradiation to metal parts of the outer wall of the aircraft on the lower portion is reduced through installation of the anti-ultraviolet cloth; under the cooperation of the drying layer, the corrosion influence of moisture on the outer wall during the attaching contact with the outer wall of the airplane is reduced, under the cooperation of the heat insulation cloth with the vacuum layer, the damage influence of sunlight temperature transfer on the lower covering airplane is reduced, and under the cooperation of the cotton cloth layer, the friction damage influence on the outer wall of the airplane is reduced. And the side surrounding cloth is matched with the fixing piece, so that the whole body can be stably fixed and covered on the airplane.

Description

Technical Field

[0001] The utility model relates to the technical field of cover cloths, in particular to an anti-ultraviolet cover cloth used for the nose and fuselage of an aircraft. Background Art

[0002] Ultraviolet light is a general term for radiation with a frequency of 750THz to 30PHz in the electromagnetic spectrum, corresponding to a wavelength of 400nm to 10nm in a vacuum. It cannot cause visual disturbances in people. It is invisible light with a higher frequency than blue-violet light. Long-term exposure of the aircraft nose and fuselage to ultraviolet light can easily cause adverse effects on metal parts. Therefore, aircraft that have been out of service for a long time need to be covered and shielded with anti-ultraviolet light.

[0003] The utility model with the publication number CN210501746U discloses an anti-ultraviolet tarpaulin, which comprises a tarpaulin base, an elastic layer is arranged on the tarpaulin base, an anti-ultraviolet layer is arranged on the elastic layer, an absorption layer is arranged on the anti-ultraviolet layer, a waterproof layer is arranged on the absorption layer, a wear-resistant layer is arranged under the tarpaulin base, edge sealing layers covering the tarpaulin are arranged on both sides of the wear-resistant layer, fixing holes are arranged on the edge sealing layers, a fireproof asbestos layer is arranged in the elastic layer, and a light reflecting layer is arranged on the waterproof layer;

[0004] In the above technical solution, the anti-ultraviolet layer can slow down the aging speed of the tarpaulin and extend its service life; the setting of the wear-resistant layer increases the wear resistance of the tarpaulin and avoids damage to the inner lining; the elastic layer can increase the elasticity of the tarpaulin so that it can be used to cover different areas or volumes; the design of the light reflection layer can reflect light, and cooperate with the anti-ultraviolet layer to enhance the strength of anti-ultraviolet; however, the anti-ultraviolet cover cloth used for aircraft is not convenient for quickly fitting and covering the aircraft, and the cover cloth does not have a heat-insulating effect, which reduces the damage to the aircraft parts below due to exposure to the sun. Utility Model Content

[0005] The purpose of the utility model is to provide an anti-ultraviolet tarpaulin for the nose and fuselage of an aircraft, so as to solve the problem that the anti-ultraviolet tarpaulin with the authorization publication number CN210501746U proposed in the above background technology is not convenient for the anti-ultraviolet tarpaulin used for aircraft to quickly fit and cover the aircraft, and the tarpaulin does not have a heat-insulating effect, thereby reducing the damage to the aircraft components below due to exposure to the sun.

[0006] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0007] An anti-ultraviolet cover cloth for an aircraft nose and fuselage comprises a protective assembly for covering the aircraft, the outer periphery of the protective assembly is provided with side cloths, the protective assembly is provided with waterproof cloth, anti-ultraviolet cloth, a drying layer, a heat-insulating cloth and a cotton cloth layer in sequence from top to bottom, the side cloths are in a circular ring shape, and the bottom of the side cloths are provided with a plurality of fixings for overall traction and fixing, the fixings comprising a fixing seat and a connecting ring.

[0008] Preferably, the lower surface of the waterproof cloth is bonded and fixed to the upper surface of the anti-ultraviolet cloth, and the width of the outer wall of the anti-ultraviolet cloth is matched with the width of the outer wall of the waterproof cloth.

[0009] In the utility model, the waterproof cloth is arranged to increase the waterproofness of the top of the protective component, reduce the influence of rainwater erosion in rainy weather, and stably cooperate with the anti-ultraviolet cloth below for protection.

[0010] Preferably, the lower surface of the anti-ultraviolet cloth is bonded and fixed to the upper surface of the drying layer, and the width of the outer wall of the drying layer is matched with the width of the outer wall of the anti-ultraviolet cloth.

[0011] In the utility model, the anti-ultraviolet cloth is arranged to increase the overall anti-ultraviolet function, reduce the damage to the metal components of the aircraft covered below by long-term ultraviolet radiation, and the anti-ultraviolet cloth is closely attached to the drying layer to increase the stability of the installation.

[0012] Preferably, the lower surface of the drying layer is bonded and fixed to the upper surface of the insulation cloth, and the width of the outer wall of the insulation cloth is matched with the width of the outer wall of the drying layer. The hollow area between the inner wall and the outer wall of the insulation cloth is a vacuum layer, and the vacuum layer is provided with dividing strips arranged in a cross shape.

[0013] In the utility model, the drying layer is made of dry cotton cloth to reduce the influence of moisture when it is attached to the outer wall of the aircraft, and the heat insulation cloth is used to reduce the damage to the aircraft caused by long-term exposure to the sun. The vacuum layer on the heat insulation cloth reduces the influence of heat conduction from above, and the interior of the vacuum layer is evenly divided by multiple dividing strips, which helps to stabilize the heat insulation.

[0014] Preferably, the lower surface of the thermal insulation cloth is bonded and fixed to the upper surface of the cotton cloth layer, the width of the outer wall of the cotton cloth layer is matched with the width of the outer wall of the thermal insulation cloth, and a plurality of silicone balls are provided on the lower surface of the cotton cloth layer. The silicone balls are hemispherical, and the tops of the silicone balls are bonded and fixed to the bottom of the cotton cloth layer.

[0015] In the utility model, the cotton cloth layer cooperates to reduce friction damage to the outer wall of the aircraft covered below, and at the same time, the silicone balls distributed in a matrix cooperate to increase the friction with the outer wall of the aircraft, which helps to achieve overall stable covering cooperation.

[0016] Preferably, a guide cloth is provided on the lower surface of the cotton cloth layer near the left end, the top of the guide cloth is sewn and fixed to the cotton cloth layer by connecting nylon thread, a sleeve corresponding to the nose of the aircraft is provided in the middle of the guide cloth, the sleeve and the guide cloth are an integrally formed structure, and the sleeve is plugged into and matched with the nose of the aircraft.

[0017] In the utility model, the guide cloth is provided to help the protective assembly cover the top of the aircraft. The nose of the aircraft is plugged into and matched with the corresponding sleeve under the cooperation of the guide cloth, so as to achieve overall stable coverage above the aircraft and provide stable protective cooperation for the nose and fuselage of the aircraft.

[0018] Preferably, the fixing parts are distributed at equal intervals, and the bottom of the fixing seat is welded and fixed to the top of the connecting ring, and the fixing seat is snap-fitted with the side cloth.

[0019] In the utility model, the cooperation of multiple fixing parts helps to fix the side cloth and the protective assembly above the covered aircraft, and the external traction rope is pulled and fixed to the external fixing column through the connecting ring, thereby reducing the protective assembly from falling due to external force and affecting the protection coordination above the aircraft.

[0020] Compared with the prior art, the beneficial effects of the utility model are:

[0021] 1. The utility model realizes waterproof coordination on the upper side by arranging a waterproof cloth, reduces the erosion effect of rainy weather on the lower side, installs anti-ultraviolet cloth to reduce the damage to the metal parts of the lower aircraft outer wall caused by long-term exposure to ultraviolet rays, cooperates with the dry layer to reduce the erosion effect of moisture on the outer wall when in contact with the outer wall of the aircraft, cooperates with the heat-insulating cloth with a vacuum layer, reduces the damage effect of the temperature transfer from the sun on the lower covered aircraft, and cooperates with the cotton cloth layer to reduce the friction damage effect on the outer wall of the aircraft. The fixing parts on the side cloth help to stably fix the overall cover on the aircraft.

[0022] 2. The utility model increases the friction with the outer wall of the aircraft and reduces the friction damage to the outer wall of the aircraft by arranging multiple silicone balls. A plurality of cross-distributed dividing strips are arranged in the vacuum layer to evenly divide the vacuum layer, which is helpful for heat insulation protection. The fixing part is equipped with a connecting ring to help the external traction rope to be wound around, thereby achieving overall position traction and fixation. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0024] Figure 2 It is an overall bottom view schematic diagram of the utility model;

[0025] Figure 3 This is a schematic diagram of the structure of the protection component of the utility model;

[0026] Figure 4 This is a schematic diagram of the explosion structure of the protection component of the utility model;

[0027] Figure 5 It is a bottom view schematic diagram of the side cloth of the utility model;

[0028] Figure 6 It is a schematic diagram of the overall cross-sectional structure of the utility model;

[0029] Figure 7 This is a schematic diagram of the structure of the heat insulation cloth of the utility model.

[0030] The meaning of each number in the figure is:

[0031] Protection components; 10, waterproof cloth; 11, anti-ultraviolet cloth; 12, drying layer; 13, heat insulation cloth; 130, vacuum layer; 131, separator strip; 14, cotton cloth layer; 140, silicone ball; 15, guide cloth; 150, sleeve;

[0032] Side cloth;

[0033] Fixing piece; 30. Fixing seat; 31. Connecting ring. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0035] See also Figure 1-Figure 7 , this embodiment provides a technical solution:

[0036] An anti-ultraviolet covering cloth for an aircraft nose and fuselage, comprising a protective component 1 for covering the aircraft, a side cloth 2 being arranged on the periphery of the protective component 1, and a waterproof cloth 10, an anti-ultraviolet cloth 11, a drying layer 12, a heat-insulating cloth 13 and a cotton cloth layer 14 being arranged in sequence from top to bottom of the protective component 1;

[0037] The lower surface of the waterproof cloth 10 is bonded and fixed to the upper surface of the anti-ultraviolet cloth 11 , and the width of the outer wall of the anti-ultraviolet cloth 11 is matched with the width of the outer wall of the waterproof cloth 10 .

[0038] In the utility model, the waterproof cloth 10 is provided to increase the waterproofness of the top of the protective component 1, reduce the influence of rainwater erosion in rainy weather, and stably protect the anti-ultraviolet cloth 11 below.

[0039] The lower surface of the anti-ultraviolet cloth 11 is bonded and fixed to the upper surface of the drying layer 12 , and the width of the outer wall of the drying layer 12 is matched with the width of the outer wall of the anti-ultraviolet cloth 11 .

[0040] In the utility model, the anti-ultraviolet cloth 11 is provided to increase the overall anti-ultraviolet function, reduce the damage to the metal components of the aircraft covered below by long-term ultraviolet radiation, and the anti-ultraviolet cloth 11 is closely fitted with the drying layer 12 to increase the stability of the installation.

[0041] The lower surface of the drying layer 12 is bonded and fixed to the upper surface of the insulation cloth 13, and the width of the outer wall of the insulation cloth 13 is adapted to the width of the outer wall of the drying layer 12. The hollow area between the inner wall and the outer wall of the insulation cloth 13 is a vacuum layer 130, and the vacuum layer 130 is provided with dividing strips 131 arranged in a cross shape.

[0042] In the present invention, the drying layer 12 is made of dry cotton cloth to reduce the influence of moisture when it is attached to the outer wall of the aircraft, and the heat insulation cloth 13 is used to reduce the damage to the aircraft caused by long-term exposure to the sun. The vacuum layer 130 on the heat insulation cloth 13 reduces the influence of heat conduction from above, and multiple dividing strips 131 are used to evenly divide the interior of the vacuum layer 130, which helps to stabilize the heat insulation.

[0043] The lower surface of the insulation cloth 13 is bonded and fixed to the upper surface of the cotton cloth layer 14. The width of the outer wall of the cotton cloth layer 14 is matched with the width of the outer wall of the insulation cloth 13. A plurality of silicone balls 140 are provided on the lower surface of the cotton cloth layer 14. The silicone balls 140 are hemispherical, and the tops of the silicone balls 140 are bonded and fixed to the bottom of the cotton cloth layer 14.

[0044] In the utility model, the cotton cloth layer 14 reduces the friction damage to the outer wall of the aircraft covered below, and at the same time, the silicone balls 140 distributed in a matrix increase the friction with the outer wall of the aircraft, which helps to ensure the overall stable covering cooperation.

[0045] A guide cloth 15 is provided on the lower surface of the cotton cloth layer 14 near the left end. The top of the guide cloth 15 is sewn and fixed to the cotton cloth layer 14 by connecting nylon thread. A sleeve 150 corresponding to the nose of the aircraft is provided in the middle of the guide cloth 15. The sleeve 150 and the guide cloth 15 are an integrally formed structure, and the sleeve 150 is plugged into and matched with the nose of the aircraft.

[0046] In the utility model, the guide cloth 15 is provided to help the protective assembly 1 to cover the top of the aircraft. The nose of the aircraft can be plugged into and matched with the corresponding sleeve 150 under the cooperation of the guide cloth 15, so as to achieve overall stable coverage above the aircraft and provide stable protective cooperation for the nose and fuselage of the aircraft.

[0047] The side cloth 2 is in a circular ring shape, and a plurality of fixing members 3 for overall traction and fixing are disposed at the bottom of the side cloth 2 . The fixing members 3 include a fixing seat 30 and a connecting ring 31 .

[0048] The fixing members 3 are distributed at equal intervals, and the bottom of the fixing seat 30 is welded and fixed to the top of the connecting ring 31 , and the fixing seat 30 is snap-fitted with the side cloth 2 .

[0049] In the utility model, the cooperation of multiple fixing parts 3 helps to fix the side cloth 2 and the protective assembly 1 above the covered aircraft, and the external traction rope is pulled and fixed to the external fixing column through the connecting ring 31, thereby reducing the protective assembly 1 from falling due to external force and affecting the protection coordination above the aircraft.

[0050] When using the anti-ultraviolet cover cloth for the nose and fuselage of an aircraft of this embodiment, the user first glues the waterproof cloth 10 and the anti-ultraviolet cloth 11 together, connects the anti-ultraviolet cloth 11 and the heat-insulating cloth 13 with the drying layer 12, and then glues the cotton cloth layer 14 with the silicone balls 140 and the heat-insulating cloth 13 together, fixes the guide cloth 15 with the sleeve 150 on one end of the cotton cloth layer 14, and finally connects the side cloth 2 with the fixing part 3 to the protective component 1, and the top of the side cloth 2 is glued to the edge of the waterproof cloth 10, and the side end of the side cloth 2 is glued to the anti-ultraviolet cloth 13. The wire cloth 11, the dry layer 12, and the cotton cloth layer 14 are sewn together with nylon thread. When it is necessary to cover the top of the aircraft, the whole is dragged above the aircraft, and the nose of the aircraft is correspondingly plugged into the sleeve 150, and the external traction fixing rope is wound through the corresponding connecting ring 31. With the cooperation of the fixing part 3, the position of the side cloth 2 and the protective component 1 is pulled and fixed. The waterproof cloth 10 isolates the rain from the top and the direct contact erosion is affected. The anti-ultraviolet cloth 11 reduces the damage to the external metal components of the aircraft due to long-term exposure to ultraviolet rays.

Claims

1. An anti-ultraviolet drape for an aircraft nose and fuselage, comprising a protective component (1) for covering the aircraft, wherein the protective component (1) is provided with side cloth (2) on its periphery, and characterized in that: The protective assembly (1) is provided with a waterproof cloth (10), an anti-ultraviolet cloth (11), a drying layer (12), a heat-insulating cloth (13) and a cotton cloth layer (14) in order from top to bottom; the side cloth (2) is in a circular ring shape, and a plurality of fixing members (3) for overall traction and fixing are provided at the bottom of the side cloth (2); the fixing members (3) include a fixing seat (30) and a connecting ring (31).

2. The anti-ultraviolet ray cover for aircraft nose and fuselage according to claim 1, characterized in that: The lower surface of the waterproof cloth (10) is bonded and fixed to the upper surface of the anti-ultraviolet cloth (11), and the width of the outer wall of the anti-ultraviolet cloth (11) is matched to the width of the outer wall of the waterproof cloth (10).

3. The anti-ultraviolet ray cover for aircraft nose and fuselage according to claim 2, characterized in that: The lower surface of the anti-ultraviolet cloth (11) is bonded and fixed to the upper surface of the drying layer (12), and the width of the outer wall of the drying layer (12) is matched to the width of the outer wall of the anti-ultraviolet cloth (11).

4. The anti-ultraviolet ray cover for aircraft nose and fuselage according to claim 3, characterized in that: The lower surface of the drying layer (12) is bonded and fixed to the upper surface of the heat insulating cloth (13), and the width of the outer wall of the heat insulating cloth (13) matches the width of the outer wall of the drying layer (12). The hollow area between the inner wall and the outer wall of the heat insulating cloth (13) is a vacuum layer (130), and the vacuum layer (130) is provided with dividing strips (131) arranged in a cross shape.

5. The anti-ultraviolet ray cover for aircraft nose and fuselage according to claim 4, characterized in that: The lower surface of the heat insulating cloth (13) is bonded and fixed to the upper surface of the cotton cloth layer (14); the width of the outer wall of the cotton cloth layer (14) matches the width of the outer wall of the heat insulating cloth (13); a plurality of silicone balls (140) are provided on the lower surface of the cotton cloth layer (14); the silicone balls (140) are hemispherical; and the tops of the silicone balls (140) are bonded and fixed to the bottom of the cotton cloth layer (14).

6. The anti-ultraviolet ray cover for aircraft nose and fuselage according to claim 5, characterized in that: A guide cloth (15) is provided on the lower surface of the cotton cloth layer (14) near the left end; the top of the guide cloth (15) is sewn and fixed to the cotton cloth layer (14) by connecting nylon thread; a sleeve (150) corresponding to the nose of the aircraft is provided in the middle of the guide cloth (15); the sleeve (150) and the guide cloth (15) are an integrally formed structure; and the sleeve (150) is plug-fitted to the nose of the aircraft.

7. The anti-ultraviolet ray cover for aircraft nose and fuselage according to claim 1, characterized in that: The fixing members (3) are distributed at equal intervals, and the bottom of the fixing seat (30) is welded and fixed to the top of the connecting ring (31), and the fixing seat (30) is snap-fitted with the side surrounding cloth (2).

Images