CN113531125B - Inflatable sealing structure of aircraft canopy fuselage opening frame and assembly method thereof - Google Patents
Inflatable sealing structure of aircraft canopy fuselage opening frame and assembly method thereof Download PDFInfo
- Publication number
- CN113531125B CN113531125B CN202110887608.0A CN202110887608A CN113531125B CN 113531125 B CN113531125 B CN 113531125B CN 202110887608 A CN202110887608 A CN 202110887608A CN 113531125 B CN113531125 B CN 113531125B
- Authority
- CN
- China
- Prior art keywords
- silica gel
- gel hose
- canopy
- mounting groove
- natural
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/46—Sealings with packing ring expanded or pressed into place by fluid pressure, e.g. inflatable packings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Architecture (AREA)
- Fluid Mechanics (AREA)
- Sealing Material Composition (AREA)
- Specific Sealing Or Ventilating Devices For Doors And Windows (AREA)
Abstract
The application belongs to the technical field of the sealed design of aircraft canopy fuselage oral cavity frame, concretely relates to aircraft canopy fuselage oral cavity frame inflatable seal structure, include: a frame of the machine body opening; the canopy is connected to the opening frame of the machine body, and the edge of the canopy is provided with an installation groove; the bottom wall is provided with an opening; the natural-color fine plain cloth is bonded in the mounting groove and is provided with an opening; the silica gel hose is laid in the mounting groove, is bonded on the natural-color fine plain cloth and is provided with an inflation hole; the charging connector is connected in inflating the hole, passes the trompil on mounting groove diapire, the thin plain cloth of true qualities, inserts passenger cabin vent line to can fill the gassing to the silica gel hose, make the silica gel hose have: in the inflation state, the silica gel hose is inflated and expanded, and is filled between the canopy cover and the fuselage opening frame after the canopy cover is closed; and in the air leakage state, the silica gel hose is deflated and contracted, and a gap is reserved between the silica gel hose and the opening frame of the airplane body after the cabin cover is closed. In addition, the application relates to a method for assembling the inflatable sealing structure of the aircraft cabin cover fuselage opening frame.
Description
Technical Field
The application belongs to the technical field of sealing design of an airplane canopy fuselage opening frame, and particularly relates to an inflatable sealing structure of the airplane canopy fuselage opening frame and an assembling method thereof.
Background
A sealing structure is designed between the aircraft cockpit cover fuselage opening frames to prevent gas leakage at the position when an aircraft flies, and at present, the sealing structure between the aircraft cockpit cover fuselage opening frames has the following defects:
1) the rubber is made of natural rubber, has poor wear resistance, is easy to wear, has poor cold resistance, is subject to low-temperature environment and is easy to lose efficacy.
2) In order to ensure the sealing property between the canopy and the frame at the opening of the airplane body, the sealing structure is extruded between the canopy and the frame at the opening of the airplane body, and the canopy is opened and closed, the sealing structure is easy to scratch and rub, so that the sealing structure is damaged;
3) the sealing structure is connected to the cabin cover, so that the connection is not reliable enough and is easy to fall off, thereby causing dangerous accidents.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an inflatable sealing structure for an aircraft canopy fuselage aperture frame and method of assembly thereof that overcomes or mitigates at least one of the technical disadvantages known to exist.
The technical scheme of the application is as follows:
one aspect provides an aircraft canopy fuselage aperture frame inflatable seal structure, including:
a frame of the machine body opening;
the canopy is connected to the opening frame of the machine body, and the edge of the canopy is provided with an installation groove; the bottom wall of the mounting groove is provided with an opening;
the natural color fine plain cloth is bonded in the mounting groove and is provided with an opening;
the silica gel hose is laid in the mounting groove, is bonded on the natural-color fine plain cloth and is provided with an inflation hole;
the charging connector is connected in inflating the hole, passes the trompil on mounting groove diapire, the thin plain cloth of true qualities, inserts passenger cabin vent line to can fill the gassing to the silica gel hose, make the silica gel hose have:
in the inflation state, the silica gel hose is inflated and expanded, and is filled between the canopy cover and the fuselage opening frame after the canopy cover is closed;
and in the air leakage state, the silica gel hose is deflated and contracted, and a gap is reserved between the silica gel hose and the opening frame of the airplane body after the cabin cover is closed.
According to at least one embodiment of the application, in the inflatable sealing structure of the aircraft canopy fuselage opening frame, the natural-color fine plain cloth covers the bottom wall and two side walls of the mounting groove;
the outer wall of the silica gel hose is provided with:
each side wall bonding surface is correspondingly bonded on the bonding part of the natural-color fine plain cloth and one side wall of the mounting groove;
and the bottom wall bonding surface is positioned between the two side wall bonding surfaces and is bonded on the bonding part of the natural-color fine plain cloth and the bottom wall of the mounting groove.
According to at least one embodiment of the application, in the inflatable sealing structure of the aircraft canopy fuselage aperture frame, the outer side wall surface of the silicone hose is provided with a protruding part which protrudes out of the mounting groove and is in sealing contact with the fuselage aperture frame after the canopy is closed when the silicone hose is in an inflated state.
According to at least one embodiment of the application, in the inflatable sealing structure of the aircraft canopy fuselage opening frame, the inflation nozzle penetrates through the bottom wall of the installation groove and the upper screw joint of the opening on the natural-color fine plain cloth to be provided with the locking nut, so that the inflation nozzle is fixed on the canopy, and the silica gel hose is prevented from falling off from the installation groove.
According to at least one embodiment of the application, in the inflatable sealing structure of the aircraft canopy fuselage aperture frame of the aircraft, a plurality of inflation nozzles and corresponding inflation holes thereof, the openings in the canopy, the openings in the natural-color fine plain cloth, and the locking nuts are distributed along the edge of the canopy.
According to at least one embodiment of the application, in the above-mentioned inflatable sealing structure for the aircraft canopy fuselage opening frame, the inflatable sealing structure further includes:
the rubber plate is bonded on the bottom wall of the mounting groove and bonded with the natural-color fine plain cloth, and is provided with an opening for the inflation nozzle to pass through.
According to at least one embodiment of the application, in the inflatable sealing structure of the aircraft canopy fuselage opening frame, the outer side wall surface of the silica gel hose is coated with talcum powder.
In another aspect, an assembly method for an inflatable sealing structure of a fuselage aperture frame of an aircraft canopy is provided, which includes:
manufacturing a process sample section of the silica gel hose;
selecting a rubber plate with proper thickness to be adhered to the mounting groove, and matching the rubber plate with the process sample section in the mounting groove to enable the bulge part on the process sample section to bulge out of the mounting groove by a preset size;
taking out the process sample section, and cleaning the surface of the mounting groove by using absorbent cotton dipped with industrial alcohol;
trial assembling the silica gel hose in the mounting groove, and taking out the silica gel hose after making a positioning mark at the corner part;
bonding natural-color fine plain cloth in the mounting groove;
wiping the natural color fine plain cloth and the silica gel hose with absorbent cotton dipped with gasoline;
coating an adhesive on the natural-color fine plain cloth, drying the natural-color fine plain cloth to form a glue film, and coating the adhesive on the glue film again;
coating an adhesive on the outer wall surface of the silica gel hose, airing, and adhering the silica gel hose to the natural-color fine plain cloth section by section according to the positioning mark; the inflating nozzle passes through the rubber plate, the natural color fine plain cloth and the opening on the bottom wall of the mounting groove and is connected to the cabin vent pipeline;
coating talcum powder on the outer side wall surface of the silica gel hose;
closing the canopy, and inflating the silica gel hose to enable the silica gel hose to be in an inflated state and keep the silica gel hose in a set time;
and (4) deflating the silica gel hose to enable the silica gel hose to be in an air leakage state and keep the set time.
Drawings
FIG. 1 is a schematic view of an inflatable sealing structure of a fuselage aperture frame of an aircraft canopy provided in an embodiment of the present application;
FIG. 2 is a partial structural schematic view of an inflatable sealing structure of a fuselage aperture frame of an aircraft canopy according to an embodiment of the present application;
FIG. 3 is a schematic diagram of a process section of a silicone hose in a sealing structure of a fuselage aperture frame of an aircraft canopy according to an embodiment of the present application, in which a rubber plate is fitted in a mounting groove;
wherein:
1-a frame of the machine body; 2-a canopy; 3-natural color fine plain cloth; 4-a silica gel hose; 5-an inflating valve; 6-a rubber plate; 7-process section.
For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be described in detail with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are used for explaining the present application and not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of any other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1 to 3.
One aspect provides an aircraft canopy fuselage oral cavity frame inflatable seal structure, includes:
a machine body opening frame 1;
the canopy 2 is connected to the fuselage mouth frame 1, and the edge of the canopy is provided with an installation groove; the bottom wall of the mounting groove is provided with an opening;
the natural color fine plain cloth 3 is bonded in the mounting groove and is provided with an opening;
the silica gel hose 4 is laid in the mounting groove, is bonded on the natural-color fine plain cloth 3 and is provided with an inflation hole;
charging connector 5 is connected in aerifing the hole, passes the trompil on mounting groove diapire, the thin plain cloth of true qualities 3, inserts passenger cabin vent line to can fill the gassing to silica gel hose 4, make silica gel hose 4 have:
in the inflation state, the silica gel hose 4 is inflated and expanded, and is filled between the canopy 2 and the fuselage opening frame 1 after the canopy 2 is closed;
in the air leakage state, the silica gel hose 4 is deflated and contracted, and a gap is reserved between the closed cockpit cover 2 and the frame 1 of the opening of the airplane body.
For the inflatable sealing structure of the aircraft canopy fuselage mouth frame disclosed in the above embodiment, it can be understood by those skilled in the art that the inflatable sealing structure is designed to inflate the silicone hose 4 through the inflation nozzle 5 after the canopy 2 is closed, so that the silicone hose 4 is inflated to fill the space between the canopy 2 and the fuselage mouth frame 1, thereby forming a seal between the canopy 2 and the fuselage mouth frame 1 of the aircraft, and effectively preventing the gas leakage at the position when the aircraft flies.
For the inflatable sealing structure of the aircraft canopy fuselage aperture frame disclosed in the above embodiment, it can be further understood by those skilled in the art that the silicone hose 4 is made of a silicone material, so that the silicone hose has good wear resistance, is not easily worn, has good cold resistance, and can maintain good performance under low temperature conditions.
For the inflatable sealing structure of the aircraft canopy fuselage mouth frame disclosed in the above embodiment, it can be further understood by those skilled in the art that the silicone hose 4 can be set in an air leakage state during the closing or opening process of the canopy 2, at this time, a gap exists between the silicone hose 4 and the aircraft fuselage mouth frame 1 due to contraction of the silicone hose 4, so that rubbing with the aircraft fuselage mouth frame 1 can be avoided, the silicone hose 4 is protected from being damaged, after the canopy 2 is closed, the silicone hose 4 is set in an inflatable state, and the silicone hose 4 expands to be filled between the canopy 2 and the aircraft fuselage mouth frame 1, so as to form sealing between the aircraft canopy 2 and the aircraft fuselage mouth frame 1.
For the inflatable sealing structure of the aircraft canopy fuselage mouth frame disclosed in the above embodiment, a person skilled in the art can also understand that the silica gel hose 4 made of a silica gel material is difficult to be reliably and directly bonded in the installation groove, and the natural-color fine flat cloth 3 is designed to be matched with the adhesive to bond between the silica gel hose 4 and the installation groove, so that a strong bonding force can be formed between the silica gel hose 4 and the installation groove, and the silica gel hose 3 is prevented from falling off from the installation groove.
In some optional embodiments, in the above-mentioned inflatable sealing structure for the aircraft canopy fuselage aperture frame, the natural-color fine plain cloth 3 covers the bottom wall and two side walls of the installation groove;
the outer wall of the silica gel hose 4 is provided with:
each side wall bonding surface is correspondingly bonded on the bonding part of the natural color fine plain cloth 3 and one side wall of the mounting groove;
and the bottom wall bonding surface is positioned between the two side wall bonding surfaces and is bonded on the bonding part of the natural-color fine plain cloth 3 and the bottom wall of the mounting groove.
With respect to the inflatable sealing structure of the aircraft canopy fuselage aperture frame disclosed in the above embodiments, it will be understood by those skilled in the art that, the two side wall bonding surfaces and the bottom wall bonding surface of the outer wall of the silica gel hose 4 are bonded on the corresponding parts of the natural color fine plain cloth 3 covering the two side walls and the bottom wall of the installation groove, namely, the three outer wall surfaces are adhered to the wall surface of the mounting groove, the bonding area is larger, the bonding is reliable, and the deformation of the silica gel hose 4 in the directions of the two side walls and the bottom wall of the mounting groove can be limited, and the silica gel hose can only deform towards the outer side of the mounting groove so as to ensure that after the cabin cover 2 is closed, the silicone hose 4 is inflated through the inflation nozzle 5, so that the silicone hose 4 expands outwards and is easily in sealing contact with the outer fuselage mouth frame 1 to fill the space between the canopy 2 and the fuselage mouth frame 1, and sealing is formed between the canopy 2 and the fuselage mouth frame 1 of the airplane.
In some alternative embodiments, in the inflatable sealing structure of the aircraft canopy fuselage aperture frame, the outer side wall surface of the silicone hose 4 has a protruding portion protruding from the mounting groove, and the protruding portion is in sealing contact with the fuselage aperture frame 1 after the canopy 2 is closed when the silicone hose 4 is in an inflated state.
For the inflatable sealing structure of the aircraft canopy fuselage mouth frame disclosed in the above embodiment, it can be understood by those skilled in the art that the outer side wall surface of the silicone hose 4 is designed to have a protruding portion protruding out of the installation groove, so that the protruding portion can be easily abutted to the fuselage mouth frame 1 by setting the silicone hose 4 in an inflated state after the canopy 2 is closed, and a seal is formed between the canopy 2 and the fuselage mouth frame 1, in addition, in order to avoid the silicone hose 4 from being scratched and rubbed with the fuselage mouth frame 1 in the closing or opening process of the canopy 2, when the canopy 2 is closed and the silicone hose 4 is in an air leakage state, the height of the protruding portion protruding out of the installation groove is not more than 3mm, and the distance between the protruding portion and the fuselage mouth frame 1 is not less than 1.5 mm.
In some optional embodiments, in the above-mentioned inflatable sealing structure for the aircraft canopy fuselage aperture frame, the inflation nozzle 5 penetrates through the bottom wall of the installation groove, and the upper part of the opening of the natural-color fine plain cloth 3 is screwed with a lock nut, so as to fix the inflation nozzle 5 on the canopy 2 and prevent the silicone hose 4 from falling off from the installation groove.
In some optional embodiments, in the above-mentioned inflatable sealing structure for the aircraft canopy fuselage aperture frame of the aircraft canopy, a plurality of inflation nozzles 5 and their corresponding inflation holes, the openings in the canopy 2, the openings in the natural-color fine plain cloth 3, and the lock nuts are distributed along the edge of the canopy 2, so that the silicone hose 4 has a faster inflation/deflation speed, and the silicone hose 4 can be rapidly switched between an inflation state and a deflation state, and the silicone hose 4 can be reliably positioned in the installation slot, thereby preventing the silicone hose 4 from falling off from the installation slot.
In some optional embodiments, in the above-mentioned inflatable sealing structure for the aircraft canopy fuselage aperture frame, further includes:
and the rubber plate 6 is bonded on the bottom wall of the mounting groove, is bonded with the natural-color fine plain cloth 3 and is provided with an opening through which the inflating nozzle 5 passes.
For the inflatable sealing structure of the aircraft canopy fuselage mouth frame disclosed in the above embodiment, a person skilled in the art can understand that the rubber plate 6 is bonded on the bottom wall of the installation groove, and the gap between the bottom wall of the installation groove and the silicone hose 4 can be filled by designing the thickness of the rubber plate 6, and adjusting the height of the protruding part of the silicone hose 4 protruding out of the installation groove.
In some alternative embodiments, in the above-mentioned inflatable sealing structure of the aircraft canopy fuselage aperture frame, the outer side wall surface of the silicone hose 4 is coated with talc powder to protect the silicone hose 4 from being damaged.
In the prior art scheme, the process for bonding the hose with the silica gel as the main material is not mature, the problems of complex process, low bonding strength, poor reliability and the like exist, in order to reliably connect the silica gel hose 4 in the sealing structure of the aircraft canopy fuselage mouth frame to the mounting groove on the canopy 1, the application provides an assembling method of the aircraft canopy fuselage mouth frame inflatable sealing structure on the other hand, and the assembling method comprises the following steps:
manufacturing a process sample section 7 of the silica gel hose 4, wherein the process sample section 7 and the silica gel hose 4 have the same cross section;
selecting a rubber plate 6 with proper thickness to be adhered to the installation groove, matching the rubber plate 6 with the process sample section 7 in the installation groove, and enabling a protruding part on the process sample section 7 to protrude out of the installation groove by a preset size, wherein as shown in fig. 3, A can be not less than 1.5mm, and B is not more than 3 mm;
taking out the process sample section 7, and cleaning the surface of the mounting groove by using absorbent cotton dipped with industrial alcohol;
the silicone hose 4 is trial-installed in the installation groove, and is taken out after the corner part is marked with a positioning mark, in the process, in order to facilitate operation, the canopy 2 can be detached from the machine body and placed on the support, so that the opening of the installation groove is upward;
bonding the natural color fine plain cloth 3 in the mounting groove;
wiping the natural color fine plain cloth 3 and the silica gel hose 4 clean by using absorbent cotton dipped with gasoline;
coating an adhesive on the natural-color thin flat cloth 3, airing to form a glue film, and coating the adhesive on the glue film again to make fingers touch the glue film with a sticky feeling;
coating an adhesive on the outer wall surface of the silica gel hose 4, airing, and adhering the silica gel hose to the natural-color fine plain cloth 3 section by section according to the positioning marks; the inflating nozzle 5 passes through the rubber plate 6, the natural color fine plain cloth 3 and an opening on the bottom wall of the mounting groove to be connected to a cabin vent pipeline;
the outer side wall surface of the silica gel hose 4 is coated with talcum powder;
closing the canopy 2, and inflating the silica gel hose 4 to enable the silica gel hose 4 to be in an inflated state, and keeping the pressure for a set time, specifically 2 hours, so as to form stable pressure among the silica gel hose 4, the natural-color fine flat cloth 3 and the mounting groove, and keeping the pressure for the set time, specifically 2 hours, so as to ensure reliable bonding among the silica gel hose 4, the natural-color fine flat cloth 3 and the mounting groove;
deflating the silica gel hose 4, making the silica gel hose 4 be in the state of leaking air, keeping reaching the set time, specifically can be 2 hours, this in-process keeps canopy 2 to be in the closed condition to it is reliable to make the silica gel hose 4 bond in the mounting groove.
For the assembling method of the aircraft canopy fuselage mouth frame inflatable sealing structure disclosed in the above embodiment, it is used to implement the assembling of the aircraft canopy fuselage mouth frame inflatable sealing structure disclosed in the above embodiment, and the technical effects that can be obtained by the assembling method can refer to the technical effects of the relevant parts of the aircraft canopy fuselage mouth frame inflatable sealing structure, and are not described herein again.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (1)
1. An assembly method of an inflatable sealing structure of a fuselage aperture frame of an aircraft canopy is used for realizing the assembly of the inflatable sealing structure of the fuselage aperture frame of the aircraft canopy, and the inflatable sealing structure of the fuselage aperture frame of the aircraft canopy comprises the following steps:
a body opening frame (1);
the canopy (2) is connected to the fuselage mouth frame (1), and the edge of the canopy is provided with an installation groove; the bottom wall of the mounting groove is provided with an opening;
the natural-color fine plain cloth (3) is bonded in the mounting groove and is provided with an opening;
the silica gel hose (4) is laid in the mounting groove, is adhered to the natural-color fine plain cloth (3) and is provided with an inflation hole;
charging connector (5), connect in the inflation hole, pass the mounting groove diapire trompil on the thin plain cloth of true qualities (3) inserts passenger cabin vent line, with can be right silica gel hose (4) fill the gassing, make silica gel hose (4) have:
in an inflation state, the silica gel hose (4) is inflated and expanded, and is filled between the canopy cover (2) and the fuselage mouth frame (1) after the canopy cover (2) is closed;
in the air leakage state, the silica gel hose (4) is deflated and contracted, and a gap is reserved between the silica gel hose and the fuselage mouth frame (1) after the canopy (2) is closed;
the natural color fine plain cloth (3) covers the bottom wall and two side walls of the mounting groove;
the outer wall of the silica gel hose (4) is provided with:
each side wall bonding surface is correspondingly bonded on the bonding part of the natural color fine plain cloth (3) and one side wall of the mounting groove;
the bottom wall bonding surface is positioned between the two side wall bonding surfaces and is bonded on the bonding part of the natural-color fine plain cloth (3) and the bottom wall of the mounting groove;
the outer side wall surface of the silica gel hose (4) is provided with a protruding part which protrudes out of the mounting groove, and when the silica gel hose (4) is in the inflation state, the silica gel hose is in sealing contact with the fuselage mouth frame (1) after the canopy (2) is closed;
the inflation nozzle (5) penetrates through the bottom wall of the mounting groove, and a locking nut is screwed on the opening on the natural-color fine plain cloth (3) so as to fix the inflation nozzle (5) on the canopy cover (2) and prevent the silica gel hose (4) from falling off from the mounting groove;
the number of the inflating nozzles (5) and the corresponding inflating holes thereof, the openings on the canopy cover (2), the openings on the natural-color fine plain cloth (3) and the locking nuts are multiple, and the inflating nozzles are distributed along the edge of the canopy cover (2);
the inflatable sealing structure for the engine base hatch cover body opening frame further comprises:
the rubber plate (6) is bonded on the bottom wall of the mounting groove, is bonded with the natural-color fine plain cloth (3), and is provided with an opening through which the inflating nozzle (5) passes;
talcum powder is smeared on the outer side wall surface of the silica gel hose (4);
the assembling method of the inflatable sealing structure of the aircraft canopy fuselage opening frame is characterized by comprising the following steps:
manufacturing a process sample section (7) of the silica gel hose (4);
selecting a rubber plate (6) with proper thickness to be adhered to the installation groove, and matching the rubber plate (6) with the process sample section (7) in the installation groove to ensure that the protruding part on the process sample section (7) protrudes out of the installation groove by a preset size;
taking out the process sample section (7), and cleaning the surface of the mounting groove by using absorbent cotton dipped with industrial alcohol;
trial assembling the silica gel hose (4) in the installation groove, and taking out the silica gel hose after making a positioning mark at the corner part;
the natural-color fine plain cloth (3) is adhered in the mounting groove;
wiping the natural color fine plain cloth (3) and the silica gel hose (4) by using absorbent cotton dipped with gasoline;
coating an adhesive on the natural-color fine plain cloth (3), airing to form an adhesive film, and coating the adhesive on the adhesive film again;
coating an adhesive on the outer wall surface of the silica gel hose (4), airing, and adhering the silica gel hose to the natural-color fine plain cloth (3) section by section according to the positioning mark; the inflating nozzle (5) passes through the rubber plate (6), the natural color fine plain cloth (3) and the opening on the bottom wall of the mounting groove to be connected with the cabin vent pipeline;
talcum powder is smeared on the outer side wall surface of the silica gel hose (4);
closing the canopy cover (2), and inflating the silica gel hose (4) to enable the silica gel hose (4) to be in an inflated state and keep the inflated state for a set time;
and (4) deflating the silica gel hose (4) to enable the silica gel hose (4) to be in an air leakage state and keep the set time.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110887608.0A CN113531125B (en) | 2021-08-03 | 2021-08-03 | Inflatable sealing structure of aircraft canopy fuselage opening frame and assembly method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110887608.0A CN113531125B (en) | 2021-08-03 | 2021-08-03 | Inflatable sealing structure of aircraft canopy fuselage opening frame and assembly method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113531125A CN113531125A (en) | 2021-10-22 |
| CN113531125B true CN113531125B (en) | 2022-08-30 |
Family
ID=78090324
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110887608.0A Active CN113531125B (en) | 2021-08-03 | 2021-08-03 | Inflatable sealing structure of aircraft canopy fuselage opening frame and assembly method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113531125B (en) |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2823525A1 (en) * | 2001-04-12 | 2002-10-18 | Louis Paul Banzet | Watertight sectional door for flood protection comprises vertical watertight metal track guides with inflated rubber tubes held by wedge and seating ring |
| CN2647750Y (en) * | 2003-09-23 | 2004-10-13 | 佟宝义 | Full automatic air compacting sealing door |
| CN201115090Y (en) * | 2007-10-12 | 2008-09-10 | 艾默生网络能源有限公司 | Outdoor cabinet door |
| CN201891841U (en) * | 2010-12-10 | 2011-07-06 | 苏州江南航天机电工业有限公司 | Inflatable sealing structure of extended cabinet |
| CN203684982U (en) * | 2014-01-06 | 2014-07-02 | 台山平安五金制品有限公司 | Large air gate and sealing device thereof |
| CN210617827U (en) * | 2019-09-25 | 2020-05-26 | 河南华润电力首阳山有限公司 | Vehicle and carriage door plant sealing device thereof |
| CN111511150A (en) * | 2020-06-02 | 2020-08-07 | 飞潮(上海)环境技术有限公司 | Dustproof and waterproof sealing strip for electric appliance cabinet |
| CN213144323U (en) * | 2020-10-28 | 2021-05-07 | 乐金显示光电科技(中国)有限公司 | Sealing chamber |
-
2021
- 2021-08-03 CN CN202110887608.0A patent/CN113531125B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN113531125A (en) | 2021-10-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108597375B (en) | Method for attaching special-shaped curved surface cover plate to flexible screen | |
| US4613102A (en) | Pneumatic deicers with template | |
| JP5432164B2 (en) | Member constituting a holder for the apparatus and tire having such a member | |
| US4917646A (en) | Self-sealing valve, a self-sealing, non-latex balloon, and a method for producing such a balloon | |
| JP5530930B2 (en) | Tire and flexible member assembly | |
| CN111251177B (en) | Bearing head and polishing device with same | |
| CN111086315B (en) | Laminating device and laminating frock of curved surface apron | |
| CN113531125B (en) | Inflatable sealing structure of aircraft canopy fuselage opening frame and assembly method thereof | |
| CN101189127A (en) | Method for production of a curved screen arrangement for a vehicle | |
| JP2005297963A (en) | Holding pocket for electronic detector | |
| CA1236445A (en) | Pneumatic deicer and deicing method | |
| CN113581445A (en) | Aircraft cockpit cover fuselage opening frame sealing structure and assembly method | |
| CN108634698A (en) | A kind of inflatable air cushion and its manufacturing method | |
| US2699580A (en) | Canopy seal and process for making the same | |
| CN210566513U (en) | Inflation connector and inflation cushion | |
| JP2003001839A (en) | Apparatus for sustaining/recovering ink jet recoding head | |
| US2855014A (en) | Repair patch for rubber and rubberized articles | |
| NL2025440B1 (en) | Shielding screen with inflatable edge body | |
| US3410508A (en) | Inflatable seal | |
| EP0791536A2 (en) | Pneumatic deicing system with drain valve | |
| CN113829642B (en) | Hollow surface fabric sealing piece and forming die and method thereof | |
| ES2398149T3 (en) | Sealing tape | |
| CN216068753U (en) | Shell of cladding equipment | |
| CN219035542U (en) | Concrete impermeability appearance | |
| CN213108292U (en) | A inflatable frock and equipment for special-shaped apron laminating |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |