CN113944827A - Airplane design test heat preservation sealing system and parameter optimization method thereof - Google Patents
Airplane design test heat preservation sealing system and parameter optimization method thereof Download PDFInfo
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- CN113944827A CN113944827A CN202111577023.5A CN202111577023A CN113944827A CN 113944827 A CN113944827 A CN 113944827A CN 202111577023 A CN202111577023 A CN 202111577023A CN 113944827 A CN113944827 A CN 113944827A
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- air duct
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/12—Arrangements for supporting insulation from the wall or body insulated, e.g. by means of spacers between pipe and heat-insulating material; Arrangements specially adapted for supporting insulated bodies
- F16L59/121—Arrangements for supporting insulation from the wall or body insulated, e.g. by means of spacers between pipe and heat-insulating material; Arrangements specially adapted for supporting insulated bodies for pipes passing through walls or partitions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L5/00—Devices for use where pipes, cables or protective tubing pass through walls or partitions
- F16L5/02—Sealing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/02—Shape or form of insulating materials, with or without coverings integral with the insulating materials
- F16L59/028—Composition or method of fixing a thermally insulating material
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/02—Shape or form of insulating materials, with or without coverings integral with the insulating materials
- F16L59/029—Shape or form of insulating materials, with or without coverings integral with the insulating materials layered
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/12—Arrangements for supporting insulation from the wall or body insulated, e.g. by means of spacers between pipe and heat-insulating material; Arrangements specially adapted for supporting insulated bodies
- F16L59/13—Resilient supports
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A20/00—Water conservation; Efficient water supply; Efficient water use
- Y02A20/20—Controlling water pollution; Waste water treatment
Abstract
The invention relates to the technical field of airplane design and discloses a heat-insulating sealing system for an airplane design test and a parameter optimization method thereof, wherein the system comprises a warehouse plate, a large-section air duct penetrating through the warehouse plate and a heat-insulating sealing structure connecting the warehouse plate and the large-section air duct; the storehouse plate is provided with a through hole; the heat-insulation sealing structure comprises a glass fiber reinforced plastic frame body arranged on the crossing port and heat-insulation fillers filled between the glass fiber reinforced plastic frame body and the large-section air duct; the parameter optimization method comprises the following steps: s1, determining the shape and size of the through opening; s2, designing the shape and size of the glass fiber reinforced plastic frame body to be matched with the through port; s3, controlling the thicknesses of the heat-insulating filler, the polyurethane perfusion foaming layer, the rubber heat-insulating layer and the flexible silicone rubber layer; the invention can solve the problem of poor sealing safety of the air duct and the warehouse board interface in an extreme environment of an aircraft climate laboratory, and ensures that the contact area of the air duct and the warehouse board interface is well sealed in an extreme temperature and severe vibration environment.
Description
Technical Field
The invention relates to the technical field of airplane design, in particular to a heat-preservation sealing system for an airplane design test and a parameter optimization method thereof.
Background
The design and manufacture of the airplane are important guarantees of national safety and economic independence, and the large airplane is a high-integration control point of aviation science and technology in the jet era and is a key strategic technology for keeping military deterrence capacity and international influence in China; the whole process of airplane design and development generally comprises five stages of pre-development, engineering development, detailed design, comprehensive trial production, airworthiness evidence obtaining and the like, and each stage is of great importance; various experiments are often performed on the aircraft in the comprehensive trial-manufacturing stage, wherein the experiments include simulation experiments performed on the trial-manufactured aircraft in an extreme environment so as to ensure normal operation of the aircraft in an extreme climatic environment after the aircraft is really lifted off; generally, the large-section air duct needs a cabin warehouse board penetrating through a climate simulation laboratory to control the climate environment of the climate simulation laboratory.
The large-section air duct passes through the heat-insulation cabin body, and a hole with the section area of about 6m multiplied by 1.5m is usually required to be formed on a cabin plate of the cabin body so that the air duct passes through the hole, and the air duct and the hole are required to be well sealed. When the airplane is tested in the heat preservation cabin body in high and low temperature, snowfall and other extreme environments, the temperature in the air duct ranges from minus 60 ℃ to plus 90 ℃, the humidity ranges from 5% to 95%, meanwhile, large temperature and humidity differences exist between the inside and the outside of the air duct and the inside and the outside of the heat preservation cabin body, strong vibration is caused by huge air speed in the air duct, and a sealing structure at the joint of a warehouse board and the air duct needs to be tested in a severe environment. If the sealing treatment at the interface is not good, the vibration of the air duct can damage the integrity of the window, the conditions of icing, leakage and the like occur at the sealing part, and the working environment of the heat-insulating cabin is damaged.
At present, in the field of aircraft design in China, particularly in aircraft climate environment laboratories, a method for heat preservation and sealing of a large-section air duct passing through a reservoir plate in an extreme environment does not exist, so that the method needs to be established to solve the problem of leakage of sealing of an interface in the extreme environment, and meanwhile, the method has good performances of vibration reduction, sealing, freezing prevention and the like, and has the advantages of safety, reliability, aging resistance, corrosion resistance and strong environmental adaptability.
Disclosure of Invention
The technical problem solved by the invention is as follows: in the prior art, the air duct and the storehouse plate interface under the extreme environment have poor sealing safety, no damping function and poor heat preservation durability in an airplane design test.
The technical scheme of the invention is as follows: a heat-insulation sealing system for an aircraft design test comprises a warehouse plate, a large-section air duct penetrating through the warehouse plate, and a heat-insulation sealing structure connecting the warehouse plate and the large-section air duct;
the storehouse plate is provided with a through hole;
the heat-insulation sealing structure comprises a glass fiber reinforced plastic frame body arranged on the through opening, a heat-insulation filler filled between the glass fiber reinforced plastic frame body and the large-section air duct, an external sealing structure arranged on the periphery of the large-section air duct at the outer side end of the heat-insulation filler, and a flexible silicone rubber layer for blocking the inner side end of the heat-insulation filler;
the external sealing structure comprises a rubber insulating layer, a polyurethane perfusion foaming layer and a fixing structure, wherein the rubber insulating layer is arranged around the periphery of the large-section air duct in a surrounding manner and is in contact with the outer side end of the insulating filler;
the fixing structure comprises a protective cover plate on the outer side of the polyurethane perfusion foaming layer and a fixing flange plate connected with the protective cover plate;
the fixed flange plate connects two ends of the protective cover plate with the glass fiber reinforced plastic frame body and the side wall of the large-section air duct through self-tapping bolts;
the joints of the fixed flange plate, the glass fiber reinforced plastic frame body and the large-section air duct are coated with a layer of weather-resistant silicone sealant;
ethylene propylene diene monomer waterproof coiled materials are adhered to the joint of the fixed flange plate and the large-section air duct;
a butyl adhesive tape covers the self-tapping bolt at the joint of the fixed flange plate and the glass fiber reinforced plastic frame body;
and a flexible air-insulating waterproof material is arranged between the rubber heat-insulating layer and the large-section air duct.
Further, the heat-insulating filler is hydrophobic glass silk floss; the hydrophobic glass silk floss has good water resistance and heat preservation performance, can effectively enhance the heat preservation performance of the large-section air duct and the warehouse board, reduces the internal and external heat exchange caused by the warehouse board with the through opening, and keeps the temperature in the heat preservation cabin formed by the warehouse board constant.
Furthermore, the whole protective cover plate is made of stainless steel; the protective cover plate comprises a corner protective plate covering the polyurethane pouring foaming layer and an edge protective plate covering the edge of the polyurethane pouring foaming layer; the protective cover plate can carry out rigid protection on the polyurethane perfusion foaming layer, and prevent the polyurethane perfusion foaming layer from being damaged and losing efficacy in the air due to long-time exposure; in addition, the contact area between the air duct and the wall plate can be increased, and the stability of the contact area is improved.
Furthermore, the glass fiber reinforced plastic frame body is formed by enclosing U-shaped glass fiber reinforced plastic bars clamped on the crossing port. The glass fiber reinforced plastic has the advantages of light weight, high strength, corrosion resistance and the like, the U-shaped inner wall of the U-shaped glass fiber reinforced plastic can clamp and protect the edge of the crossing hole, and the arrangement mode can effectively improve the stability of the warehouse plate crossing hole.
Furthermore, the U-shaped glass steel bar and the warehouse plate are provided with communicated fixed connecting holes;
a connecting rod is arranged in the fixed connecting hole;
the two ends of the connecting rod are provided with a pressing sealing piece connected with the side wall of the U-shaped glass steel bar; through the connecting rod, compress tightly sealing member can closely paste U type glass billet and storehouse board tightly, make big cross-section wind channel and U type glass billet's outer wall can the steady contact to guarantee whole stability of crossing the contact surface.
Furthermore, the cross port and the side line of the through section of the large-section air duct are in a shape of a sawtooth or a wave which can be matched with each other; the zigzag or wavy design can effectively increase the contact area between the large-section air duct and the U-shaped glass steel bars, thereby further improving the stable sealing performance and preventing the problem of sealing leakage at the crossing port caused by severe vibration of the air duct.
Further, the cross sections of the through opening and the large-section air duct are circular or rectangular; the flat rectangular through holes are beneficial to reducing the construction height of the heat-insulation cabin body, are convenient for arranging the warehouse boards and have low construction cost; the circular large-section air duct passes through the through opening of the warehouse plate, so that the stability can be improved, the stress concentration is prevented, and the local leakage caused by long-time vibration is avoided.
Furthermore, damping devices connected with the warehouse board are uniformly arranged on the periphery of the large-section air duct; the vibration energy of the air duct can be effectively absorbed through the damping device, and the influence of the vibration on the heat-insulation sealing structure is reduced.
Furthermore, the damping device comprises a first connecting lug arranged on the large-section air duct, a second connecting lug arranged on the warehouse board, and a damping rod, wherein one end of the damping rod is hinged with the first connecting lug, and the other end of the damping rod is hinged with the second connecting lug;
the shock absorption rod comprises a telescopic damping rod and a shock absorption spring arranged on the damping rod; through being the setting of triangle-shaped bracing with the damping rod, not only can absorb the vibration energy in large cross-section lateral wall wind channel, can also provide the stable supporting effect, ensure that heat preservation seal structure's sealing performance is not destroyed.
A parameter optimization method for an airplane design test heat-preservation sealing system comprises the following steps:
s1, determining the shape and size of the through opening; the shape of the through opening is rectangular or circular;
the rectangular through opening is 5.5-7 m long and 1.3-1.6 m high, and the diameter of the circular through opening is 2.9-3.5 m;
s2, designing the shape and the size of the glass fiber reinforced plastic frame body according to the shape and the size of the through opening determined in the step S1 to enable the glass fiber reinforced plastic frame body to be matched with the through opening, wherein the thickness of the glass fiber reinforced plastic frame body is 22-36 mm;
s3, controlling the thickness of the heat-insulating filler to be 55-75 mm, controlling the thickness of the polyurethane perfusion foaming layer to be 200-250 mm, controlling the thickness of the rubber heat-insulating layer to be 55-75 mm, and controlling the thickness of the flexible silicone rubber layer to be 25-40 mm.
The invention has the beneficial effects that: according to the heat-insulation sealing system for the airplane design test and the parameter optimization method thereof, the glass fiber reinforced plastic frame body is arranged on the crossing port, and heat-insulation fillers, the flexible silicone rubber layer and the rubber heat-insulation layer are filled between the glass fiber reinforced plastic frame body and the air duct, so that good flexible sealing heat insulation is realized, and the temperature exchange at the crossing port is effectively prevented; the arrangement of the polyurethane injection foaming layer not only increases the contact area between the air duct and the storage plate, but also can enhance the air tightness; the waterproof heat-insulating material has excellent sealing, heat-insulating and waterproof performances and strong cohesiveness, thereby forming secondary protection; the glass fiber reinforced plastic frame body and the side wall of the air duct are connected through the protective cover plate to implement rigid protection on the polyurethane perfusion foaming layer, so that the safety performance is improved; the indoor environment is effectively guaranteed not to be affected by the outside, and the normal use of the heat-preservation cabin formed by the warehouse board in various extreme environments is met; the vibration energy of the air duct can be absorbed through the damping device, and the sealing structure is made of flexible materials, so that the vibration damping device has good vibration damping performance and can effectively weaken the vibration of the air duct caused by high-speed circulating air; the structure practicality is strong, can effectively ensure going on smoothly of aircraft design test.
Drawings
FIG. 1 is a flow chart of a parameter optimization method of an aircraft design test insulation sealing system according to the present invention;
FIG. 2 is a schematic structural view of the whole of embodiment 1 of the present invention;
FIG. 3 is a schematic structural view of a flexible silicone rubber layer according to example 1 of the present invention;
FIG. 4 is a schematic structural view of a heat-insulating sealing structure in embodiment 1 of the present invention;
FIG. 5 is a schematic structural view of embodiment 2 of the present invention;
FIG. 6 is a schematic structural view of embodiment 4 of the present invention;
the air-conditioning and heat-insulating composite material comprises, by weight, 1-warehouse board, 2-large-section air duct, 3-heat-insulating sealing structure, 30-glass fiber reinforced plastic frame body, 31-heat-insulating filler, 32-external sealing structure, 33-flexible silicone rubber layer, 320-rubber heat-insulating layer, 321-polyurethane pouring foaming layer, 322-protective cover plate, 323-fixed flange plate, 324-ethylene propylene diene monomer waterproof coiled material, 325-flexible air-isolating waterproof material, 326-corner protective plate, 327-edge protective plate, 300-fixed connecting hole, 301-connecting rod, 302-pressing sealing piece, 4-damping device, 40-first connecting lug, 41-second connecting lug and 42-damping rod.
Detailed Description
Example 1
As shown in fig. 2, the insulation sealing system for the aircraft design test comprises a warehouse plate 1, a large-section air duct 2 penetrating through the warehouse plate 1, and an insulation sealing structure 3 connecting the warehouse plate 1 and the large-section air duct 2;
a through opening is arranged on the storehouse plate 1;
as shown in fig. 3, the heat-insulating sealing structure 3 includes a glass fiber reinforced plastic frame 30 disposed on the through opening, a heat-insulating filler 31 filled between the glass fiber reinforced plastic frame 30 and the large-section air duct 2, an external sealing structure 32 disposed at the outer end of the heat-insulating filler 31 and around the large-section air duct 2, and a flexible silicone rubber layer 33 sealed at the inner end of the heat-insulating filler 31;
as shown in fig. 4, the external sealing structure 32 includes a rubber insulating layer 320 surrounding the large-section air duct 2 and contacting the outer end of the insulating filler 31, a polyurethane perfusion foam layer 321 wrapping the rubber insulating layer 320, and a fixing structure disposed outside the polyurethane perfusion foam layer 321;
the fixing structure comprises a protective cover plate 322 on the outer side of a polyurethane pouring foaming layer 321, and a fixing flange plate 323 connected with the protective cover plate 322;
the fixed flange plate 323 connects two ends of the protective cover plate 322 with the glass fiber reinforced plastic frame 30 and the side wall of the large-section air duct 2 through self-tapping bolts;
the joints of the fixed flange plate 323, the glass fiber reinforced plastic frame body 30 and the large-section air duct 2 are coated with a layer of weather-resistant silicone sealant;
ethylene propylene diene monomer waterproof coiled materials 324 are adhered to the joint of the fixed flange plate 323 and the large-section air duct 2;
a butyl adhesive tape covers the self-tapping bolt at the joint of the fixed flange plate 323 and the glass fiber reinforced plastic frame body 30;
a flexible air-insulating waterproof material 325 is arranged between the rubber insulating layer 320 and the large-section air duct 2;
the heat-insulating filler 31 is hydrophobic glass wool;
the whole of the shield plate 322 is made of stainless steel; the shielding cover plate 322 includes a corner shielding plate 326 covering the polyurethane injection foam layer 321, and an edge shielding plate 327 covering an edge of the polyurethane injection foam layer 321;
the glass fiber reinforced plastic frame 30 is formed by enclosing a U-shaped glass fiber reinforced plastic bar clamped on the through opening.
Example 2
The difference from the embodiment 1 is that, as shown in fig. 5, the glass fiber reinforced plastic frame 30 is formed by enclosing a U-shaped glass fiber reinforced plastic bar clamped on the through opening;
the U-shaped glass steel bar and the warehouse plate 1 are provided with communicated fixed connecting holes 300;
a connecting rod 301 is arranged in the fixed connecting hole 300;
the two ends of the connecting rod 301 are provided with a pressing sealing piece 302 connected with the side wall of the U-shaped glass steel strip.
Compared to example 1: this embodiment has set up fixed connection hole 300 on glass steel framework 30, storehouse board 1, compresses tightly the bolt through connecting rod 301, compress tightly sealing member 302 to U type glass steel strip and storehouse board 1 and connect, effectively increases heat preservation seal structure 3's stability.
Example 3:
the difference from the embodiment 1 is that the cross port and the cross section 2 of the large section air duct have matched wave shapes.
Compared to example 1: the cross port and the cross section 2 of the air duct are in a matched wave shape; the linear type of the crossing port edge line is changed into the wave shape, so that the contact area between the side wall of the air duct and the warehouse board can be effectively increased, the filling amount of the heat-insulating filler and the rubber heat-insulating layer is increased, and the stability of the heat-insulating sealing structure 3 is favorably improved.
Example 4
As shown in fig. 6, the difference from embodiment 1 is that the large-section air duct 2 is uniformly provided with damping devices 4 connected with the warehouse board 1 around;
the damping device 4 comprises a first connecting lug 40 arranged on the large-section air duct 2, a second connecting lug 41 arranged on the storehouse plate 1, and a damping rod 42, one end of which is hinged with the first connecting lug 40, and the other end of which is hinged with the second connecting lug 41;
the shock-absorbing lever 42 includes a telescopic damping lever, and a shock-absorbing spring provided on the damping lever.
Compared to example 1: the damping rods 42 of the inclined struts are uniformly arranged on the side wall of the air duct, so that vibration energy of the air duct with the large-section side wall can be absorbed, a stable supporting effect can be provided, the sealing performance of the heat-insulation sealing structure is guaranteed not to be damaged, and the anti-seismic performance is enhanced.
Example 5
The parameter optimization method applied to the airplane design test heat preservation sealing system in the embodiment 1 comprises the following steps:
s1, determining the shape and size of a through opening, wherein the shape of the through opening is rectangular;
the length of the rectangular through opening is 5.5m, and the height of the rectangular through opening is 1.3 m;
s2, designing the shape and the size of the glass fiber reinforced plastic frame body 30 according to the shape and the size of the through opening determined in the step S1 to enable the shape and the size to be matched with the through opening, wherein the thickness of the glass fiber reinforced plastic frame body 30 is 22 mm;
s3, controlling the thickness of the heat-insulating filler 31 to be 55mm, controlling the thickness of the polyurethane pouring foaming layer 321 to be 200mm, controlling the thickness of the rubber heat-insulating layer 320 to be 55mm, and controlling the thickness of the flexible silicone rubber layer 33 to be 25 mm.
Example 6
The parameter optimization method applied to the airplane design test heat preservation sealing system in the embodiment 2 comprises the following steps:
s1, determining the shape and size of a through opening, wherein the shape of the through opening is rectangular;
the length of the rectangular through opening is 7m, and the height of the rectangular through opening is 1.6 m;
s2, designing the shape and the size of the glass fiber reinforced plastic frame body 30 according to the shape and the size of the through opening determined in the step S1 to enable the shape and the size to be matched with the through opening, wherein the thickness of the glass fiber reinforced plastic frame body 30 is 36 mm;
s3, controlling the thickness of the heat-insulating filler 31 to be 75mm, controlling the thickness of the polyurethane pouring foaming layer 321 to be 250mm, controlling the thickness of the rubber heat-insulating layer 320 to be 75mm, and controlling the thickness of the flexible silicone rubber layer 33 to be 40 mm.
Example 7
The parameter optimization method applied to the airplane design test heat preservation sealing system in the embodiment 3 comprises the following steps:
s1, determining the shape and size of a through opening, wherein the through opening is circular;
the diameter of the round through opening is 2.9 m;
s2, designing the shape and the size of the glass fiber reinforced plastic frame body 30 according to the shape and the size of the through opening determined in the step S1 to enable the shape and the size to be matched with the through opening, wherein the thickness of the glass fiber reinforced plastic frame body 30 is 29 mm;
s3, controlling the thickness of the heat-insulating filler 31 to be 65mm, controlling the thickness of the polyurethane pouring foaming layer 321 to be 225mm, controlling the thickness of the rubber heat-insulating layer 320 to be 65mm, and controlling the thickness of the flexible silicone rubber layer 33 to be 32 mm.
Example 8
The parameter optimization method applied to the airplane design test heat preservation sealing system in the embodiment 4 comprises the following steps:
s1, determining the shape and size of a through opening, wherein the through opening is circular;
the diameter of the round through opening is 3.5 m;
s2, designing the shape and the size of the glass fiber reinforced plastic frame body 30 according to the shape and the size of the through opening determined in the step S1 to enable the shape and the size to be matched with the through opening, wherein the thickness of the glass fiber reinforced plastic frame body 30 is 29 mm;
s3, controlling the thickness of the heat-insulating filler 31 to be 65mm, controlling the thickness of the polyurethane pouring foaming layer 321 to be 225mm, controlling the thickness of the rubber heat-insulating layer 320 to be 65mm, and controlling the thickness of the flexible silicone rubber layer 33 to be 32 mm.
Claims (10)
1. The heat-insulation sealing system for the airplane design test is characterized by comprising a warehouse plate (1), a large-section air duct (2) penetrating through the warehouse plate (1), and a heat-insulation sealing structure (3) connecting the warehouse plate (1) and the large-section air duct (2);
a through opening is formed in the storehouse plate (1);
the heat-insulation sealing structure (3) comprises a glass fiber reinforced plastic frame body (30) arranged on the crossing port, a heat-insulation filler (31) filled between the glass fiber reinforced plastic frame body (30) and the large-section air duct (2), an external sealing structure (32) arranged on the periphery of the large-section air duct (2) at the outer side end of the heat-insulation filler (31), and a flexible silicone rubber layer (33) sealed at the inner side end of the heat-insulation filler (31);
the external sealing structure (32) comprises a rubber insulating layer (320) which is arranged around the periphery of the large-section air duct (2) and is in contact with the outer end of the insulating filler (31), a polyurethane pouring foaming layer (321) which is wrapped on the periphery of the rubber insulating layer (320), and a fixing structure which is arranged on the outer side of the polyurethane pouring foaming layer (321);
the fixing structure comprises a protective cover plate (322) on the outer side of a polyurethane pouring foaming layer (321), and a fixing flange plate (323) connected with the protective cover plate (322);
the fixed flange plate (323) connects two ends of the protective cover plate (322) with the glass fiber reinforced plastic frame body (30) and the side wall of the large-section air duct (2) through self-tapping bolts;
the joint of the fixed flange plate (323) and the glass fiber reinforced plastic frame body (30) and the large-section air duct (2) is coated with a layer of weather-resistant silicone sealant;
ethylene propylene diene monomer waterproof coiled materials (324) are attached to the joint of the fixed flange plate (323) and the large-section air duct (2);
a butyl adhesive tape covers the self-tapping bolt at the joint of the fixed flange plate (323) and the glass fiber reinforced plastic frame body (30);
and a flexible air-insulating waterproof material (325) is arranged between the rubber heat-insulating layer (320) and the large-section air duct (2).
2. The aircraft design test insulation sealing system according to claim 1, wherein the insulation filler (31) is hydrophobic glass wool.
3. The aircraft design test heat preservation sealing system of claim 1, characterized in that the protective cover plate (322) is made of stainless steel material as a whole; the shielding plate (322) includes a corner shielding plate (326) covering the polyurethane injection foam layer (321), and an edge shielding plate (327) covering an edge of the polyurethane injection foam layer (321).
4. The aircraft design test heat preservation sealing system of claim 1, characterized in that the glass fiber reinforced plastic frame body (30) is enclosed by a U-shaped glass fiber reinforced plastic bar clamped on the through opening.
5. The insulation sealing system for the airplane design test is characterized in that a fixing connecting hole (300) is formed in the U-shaped glass steel bar and the warehouse board (1) and communicated with each other;
a connecting rod (301) is arranged in the fixed connecting hole (300);
and two ends of the connecting rod (301) are provided with a pressing sealing piece (302) connected with the side wall of the U-shaped glass steel rod.
6. The aircraft design test heat preservation sealing system of claim 1, characterized in that the cross port and the cross section air duct (2) cross section cross section line are in the shape of a matched sawtooth or wave.
7. The aircraft design test heat preservation sealing system of claim 1, characterized in that the cross-sectional shapes of the crossing port and the large-section air duct (2) are circular or rectangular.
8. The insulation sealing system for the airplane design test is characterized in that damping devices (4) connected with the warehouse board (1) are uniformly arranged on the periphery of the large-section air duct (2).
9. The aircraft design test heat insulation sealing system according to claim 8, wherein the shock absorption device (4) comprises a first connecting lug (40) arranged on the large-section air duct (2), a second connecting lug (41) arranged on the warehouse board (1), and a shock absorption rod (42) with one end hinged with the first connecting lug (40) and the other end hinged with the second connecting lug (41);
the shock-absorbing rod (42) comprises a telescopic damping rod and a shock-absorbing spring arranged on the damping rod.
10. The parameter optimization method for the airplane design test heat preservation sealing system according to any one of claims 1 to 9, characterized by comprising the following steps:
s1, determining the shape and size of the through opening; the shape of the through opening is rectangular or circular;
the rectangular through opening is 5.5-7 m long and 1.3-1.6 m high, and the diameter of the circular through opening is 2.9-3.5 m;
s2, designing the shape and the size of the glass fiber reinforced plastic frame body (30) according to the shape and the size of the through opening determined in the step S1 to enable the shape and the size to be matched with the through opening, wherein the thickness of the glass fiber reinforced plastic frame body (30) is 22-36 mm;
s3, controlling the thickness of the heat-insulating filler (31) to be 55-75 mm, controlling the thickness of the polyurethane perfusion foaming layer (321) to be 200-250 mm, controlling the thickness of the rubber heat-insulating layer (320) to be 55-75 mm, and controlling the thickness of the flexible silicone rubber layer (33) to be 25-40 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111577023.5A CN113944827A (en) | 2021-12-22 | 2021-12-22 | Airplane design test heat preservation sealing system and parameter optimization method thereof |
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| US4086736A (en) * | 1976-12-16 | 1978-05-02 | Daniel International Corporation | Fire and liquid seals for pipes and conduits and method of forming same |
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| CN105546222A (en) * | 2016-02-26 | 2016-05-04 | 南京大学 | Sealing device for large-depth underwater vehicle cable-penetrating pressure-proof shell |
| CN207486341U (en) * | 2017-10-25 | 2018-06-12 | 海洋石油工程股份有限公司 | For the air hose insulation construction of adverse circumstances |
| CN211039945U (en) * | 2019-08-08 | 2020-07-17 | 江西胜达暖通设备有限公司 | Building engineering air pipe mounting structure |
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| CN212223976U (en) * | 2020-04-23 | 2020-12-25 | 新兴华北(北京)建设工程有限公司 | Old district basement wall pipe's mounting structure convenient to construction |
| CN112211259A (en) * | 2020-10-12 | 2021-01-12 | 福建省锦秋建筑工程有限公司 | Connection module of water supply and drainage system of green building and construction method thereof |
| CN113819310A (en) * | 2021-09-15 | 2021-12-21 | 上海外高桥造船海洋工程有限公司 | Bulkhead penetration structure |
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| US4086736A (en) * | 1976-12-16 | 1978-05-02 | Daniel International Corporation | Fire and liquid seals for pipes and conduits and method of forming same |
| US20010001355A1 (en) * | 1998-04-17 | 2001-05-24 | J. Rodman Steele, Jr. Akerman, Senterfitt & Eidson, P.A. | Partition passage and method of installing |
| CN105546222A (en) * | 2016-02-26 | 2016-05-04 | 南京大学 | Sealing device for large-depth underwater vehicle cable-penetrating pressure-proof shell |
| CN207486341U (en) * | 2017-10-25 | 2018-06-12 | 海洋石油工程股份有限公司 | For the air hose insulation construction of adverse circumstances |
| CN211039945U (en) * | 2019-08-08 | 2020-07-17 | 江西胜达暖通设备有限公司 | Building engineering air pipe mounting structure |
| CN211901864U (en) * | 2020-01-14 | 2020-11-10 | 王欢 | Wall-penetrating pipeline waterproof device for building construction |
| CN212223976U (en) * | 2020-04-23 | 2020-12-25 | 新兴华北(北京)建设工程有限公司 | Old district basement wall pipe's mounting structure convenient to construction |
| CN112211259A (en) * | 2020-10-12 | 2021-01-12 | 福建省锦秋建筑工程有限公司 | Connection module of water supply and drainage system of green building and construction method thereof |
| CN113819310A (en) * | 2021-09-15 | 2021-12-21 | 上海外高桥造船海洋工程有限公司 | Bulkhead penetration structure |
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