A quick-release seal cap assembly for aircraft having a water ditching capability

Abstract

The application belongs to the technical field of helicopter structure, and discloses a quick-release sealing hatch cover assembly suitable for a model with water-landing function, which comprises a hatch cover body and a sealing rubber strip; the cross section of the hatch cover body is boat-shaped, that is, the center line of the rectangular plate-shaped structure is bent downward to form a convex rib shape, the direction of the center line is the heading, the sealing rubber strip is arranged at the outer edge of the hatch cover body, and the hatch cover body is connected with the helicopter structure through connecting devices at four corners. The hatch cover assembly has the ability to withstand the instantaneous rapid impact force of touching water while ensuring the convenient disassembly and sealing function of the hatch cover assembly, forms an electrically connected low impedance path with the adjacent metal structure to ensure the safety of the aircraft when suffering lightning strike, has reliable sealing performance, does not damage the integrity of the sealing rubber strip and the structure of the sealing hatch cover assembly, and the bending of the edge strip and the positioning pin plays a limiting role on the sealing rubber strip, so that the structure sealing function is reliable and can be used in the marine environment.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of helicopter structure, and relates to a helicopter hatch cover assembly, in particular to a quick-release sealing hatch cover assembly suitable for a model with water-landing function. BACKGROUND

[0002] The hatch cover refers to a structural element fixed at an opening on the surface of the fuselage for maintaining the aerodynamic shape of the fuselage, and the hatch cover needs to have quick-release capability matching the maintenance frequency to meet the installation, maintenance and use requirements of the equipment inside the fuselage; when the hatch cover is located at the bottom of the fuselage belly and the aircraft needs to have water-landing capability, the hatch cover also needs to withstand the rapid impact force on the structure generated by the surface tension of water at the moment of touching water; when the hatch cover is located on the surface of the fuselage, the hatch cover assembly needs to participate in the formation of the lightning current path on the surface of the whole aircraft to ensure the safety of the aircraft when the helicopter needs to perform a flight task in a thunderstorm or is struck by lightning in a ground parking state; due to the harshness of the marine environment of the helicopter, the hatch cover assembly needs to have environmental corrosion resistance.

[0003] The existing detachable sealing hatch cover assembly of the helicopter often adopts the structure form of a hatch frame, a hatch cover, fasteners and compressed rubber type rubber strips, and the fasteners often adopt bolts, screws or quick-release nails, and the deficiencies are that: the hatch frame is directly connected with the hatch cover, bolt holes need to be opened at the hatch frame and the hatch cover, and in actual use, the connection holes make the hatch frame be in a high stress area, and the hatch frame is prone to cracks and structural damage; the sealing rubber strip cannot maintain the integrity of its own structure due to the opening of the fastener passing holes, thereby affecting the sealing performance; when the size of the hatch cover is large, a large number of fasteners need to be arranged, and the disassembly is time-consuming and inconvenient; the existing hatch cover assembly often acts as a non-load-bearing component and has weak load-bearing capacity, and cannot meet the demand of bearing the rapid impact force of touching water. SUMMARY

[0004] The purpose of the application is to solve the above problems, and the application provides a quick-release sealing hatch cover assembly suitable for a model with water-landing function, which provides a new hatch cover assembly form for a helicopter that needs to perform a water-landing task, has the ability to support water-landing, and can prevent lightning strikes and corrosion.

[0005] The technical scheme of the application is as follows:

[0006] A quick-release sealing hatch cover assembly suitable for a model with water-landing function, comprising a hatch cover body and a sealing rubber strip, the cross section of the hatch cover body is boat-shaped, that is, the center line of the rectangular plate-shaped structure is bent downward to form a convex rib shape, the direction of the center line is the heading direction, the sealing rubber strip is arranged at the outer edge of the hatch cover body, and the hatch cover body is connected with the helicopter structure through connecting devices at four corners.

[0007] Further, the cover body comprises an upper panel, a lower panel and an aluminum honeycomb, the upper panel is pasted on the upper surface of the aluminum honeycomb, the lower panel is pasted on the lower surface of the aluminum honeycomb, and the edge portions of the upper panel and the lower panel are provided with glass cloth edge seals on the side surfaces of the aluminum honeycomb.

[0008] Further, the edge of the aluminum honeycomb is provided with a step, so that the upper surface of the aluminum honeycomb is slightly smaller than the lower surface of the aluminum honeycomb; the position of the glass cloth edge seal includes all the step surfaces.

[0009] Further, it further comprises n edge sealing strips, the edge sealing strip is a long strip structure with an L-shaped cross section, the L-shaped edge sealing strip is attached to the upper surface of the cover body and the vertical surface of the step and is detachably fixed, and the n edge sealing strips are respectively installed on the edges of the cover body and press the sealing rubber strips; the number n is determined according to the length of a single edge sealing strip, the area of the cover body and the spacing distance between adjacent edge sealing strips.

[0010] Further, the inner side of the sealing rubber strip has a bent edge, and a gap is provided between the edge sealing strip and the vertical surface and the horizontal surface of the step of the cover body, and the bent edge is clamped into the gap.

[0011] Further, the fixed mounting structure of the edge sealing strip is that a blind hole is arranged on the upper surface of the cover body near the edge portion of the step, an embedded part is arranged in the blind hole and is solidified with the cover body, a threaded blind hole is arranged on the embedded part, and the upper edge of the edge sealing strip is connected with the threaded blind hole of the embedded part through a screw.

[0012] Further, when the cover body is installed on a helicopter, the steps on the edges of the cover body are arranged in the upper frame of the body structure of the helicopter, the steps and the upper frame of the body structure form a square groove for accommodating the sealing rubber strip, and the sealing rubber strip is circumferentially attached between the step surface and the surface of the upper frame of the body structure to complete the sealing.

[0013] Further, the sealing rubber strip is an O-shaped sealing ring with multiple contact points, specifically, the main body of the O-shaped sealing ring, at least two protruding lines are arranged along the ring of the O-shaped sealing ring, and the last protruding line of the outer ring part of the O-shaped sealing ring is the highest protruding line.

[0014] Further, at the position close to the body metal structure of the cover body, a conductive structure is arranged, and the conductive structure is connected with the conductive device of the body metal structure through a lead-out wire.

[0015] Further, the edge sealing strips on the front and rear of the cover body are replaced by positioning pin assemblies, the positioning pin assembly comprises a positioning base plate and a positioning pin, the positioning base plate is of the same structure as the edge sealing strip but is bent to match the bent protruding rib shape of the cover body, the positioning base plate is provided with a hole for aligning the positioning hole of the fuselage, and the positioning pin is inserted into the positioning hole and the hole of the positioning base plate.

[0016] The beneficial effects of the present application are as follows:

[0017] 1. The position of the cover assembly of the present application is greater than 1m in outer dimension due to the requirement of the helicopter to hang cargo, therefore the present application has the ability to withstand the instantaneous rapid impact force of touching water while ensuring the convenience of disassembling and sealing function of the cover assembly through reasonable structure design.

[0018] 2. The cover assembly of the present application forms an electrically connected low impedance path with the adjacent metal structure to ensure the safety of the aircraft when subjected to lightning.

[0019] 3 In addition, the cover assembly selects reasonable surface protection measures to meet the corrosion resistance requirements of marine environment or other harsh environment flight.

[0020] 4. The sealing performance of the present application is reliable: the integrity of the sealing cover assembly and the sealing rubber strip is not damaged, the bending of the edge strip and the positioning pin plays a limiting role on the sealing rubber strip, and the two make the structure sealing function reliable.

[0021] 5. The cover assembly of the present application is simple to install and convenient to maintain: the structure is detachable, the number of quick-release locks is small, the cover assembly is easy to install and maintain; the edge strip is detachable, and the sealing rubber strip is easy to install and replace.

[0022] 6. At present, the cover assembly has been implemented on the aircraft, and the actual effect is good. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 is a structure diagram of the sealing cover assembly of the present application;

[0024] Figure 2 is a schematic diagram of the cross-sectional shape of the cover of the present application;

[0025] Figure 3 is a schematic diagram of the main structure of the cover of the present application;

[0026] Figure 4 is a schematic diagram of the sealing function of the cover of the present application;

[0027] Figure 5 is a schematic diagram of the installation of the positioning pin of the present application;

[0028] Figure 6 is a schematic diagram of the structure of the positioning pin of the present application;

[0029] Figure 7 is a schematic diagram of the installation structure of the butterfly lock of the present application;

[0030] Figure 8 is a schematic diagram of the installation structure of the butterfly lock of the present application;

[0031] Figure 9 is a schematic diagram of the installation structure of the butterfly lock of the present application;

[0032] Figure 10It is lightning protection iron access diagram of the present application;

[0033] 1 - cover body, 2 - sealing strip, 3 - positioning pin, 4 - sealing rubber strip, 5 - sealing butterfly lock, 6 - upper panel, 7 - lower panel, 8 - aluminum honeycomb, 9 - glass cloth, 10 - J-97 medium temperature adhesive film, 11 - J-96 medium temperature adhesive film, 12 - J-95 medium temperature adhesive film, 13 - screw, 14 - embedded part, 15 - upper frame of body structure, 16 - sealing washer, 17 - body positioning hole, 18 - bent edge, 19 - 3M glue, 20 - body lock seat, 21 - bolt, 22 - lock tongue, 23 - disc type hole, 24 - handle, 25 - cover assembly iron bolt, 26 - cover assembly iron washer, 27 - cover assembly iron nut, 28 - body metal structure, 29 - body metal structure iron washer, 30 - iron wire, 31 - body metal structure iron bolt, 32 - body metal structure iron nut. DETAILED DESCRIPTION

[0034] This part is the embodiment of the present application, which is used to explain and illustrate the technical scheme of the present application. In the case of no conflict, the embodiments of the present application and the features in the embodiments can be combined with each other.

[0035] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship as given in the drawings, which are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or the case must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second" and the like are only for the purpose of description and cannot be understood as indicating or implying relative importance or implying the number of the indicated technical features. Therefore, the features defined as "first", "second" and the like can explicitly or implicitly include more features. In the description of the present application, unless otherwise stated, the meaning of "a plurality of" is two or more.

[0036] In the description of the present application, it should be noted that unless otherwise specified and limited, the terms "mounting", "connection", "connection" should be interpreted broadly, for example, it can be fixed connection, or detachable connection or integrated connection, it can be mechanical connection, or point connection, it can be direct connection, or indirect connection through intermediate medium, it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0037] The quick-release seal cover assembly is suitable for a water-landing helicopter, comprising a cover body 1 and a sealing rubber strip 4. The cross section of the cover body 1 is boat-shaped, i.e. the center line of the rectangular plate structure is bent downward to form a convex ridge. The sealing rubber strip 4 is arranged on the outer edge of the cover body 1. The cover body 1 is connected to the helicopter structure through the connecting devices at the four corners.

[0038] The cover body 1 comprises an upper panel 6, a lower panel 7 and an aluminum honeycomb 8. The upper panel 6 is attached to the upper surface of the aluminum honeycomb 8, and the lower panel 7 is attached to the lower surface of the aluminum honeycomb 8. The edge portions of the upper panel 6 and the lower panel 7 are provided with glass cloth 9 sealing edges on the side surfaces of the aluminum honeycomb 8.

[0039] The edge of the aluminum honeycomb 8 is provided with a step, so that the upper surface of the aluminum honeycomb 8 is slightly smaller than the lower surface of the aluminum honeycomb 8. The positions of the glass cloth 9 sealing edges include all the step surfaces.

[0040] The quick-release seal cover assembly further comprises n sealing strips 2. The sealing strip 2 is an L-shaped long strip structure. The L-shaped sealing strip 2 is attached to the upper surface of the cover body 1 and the vertical step surface outside and can be detachably fixed. The n sealing strips 2 are respectively installed on the edges of the cover body 1 and press the sealing rubber strip 4. The number n is determined according to the length of the single sealing strip 2, the area of the cover body 1 and the interval distance between adjacent sealing strips 2.

[0041] The inner side of the sealing rubber strip 4 has a bent edge 18. The sealing strip 2 and the vertical step surface and the horizontal step surface of the cover body 1 are provided with a gap. The bent edge 18 is clamped into the gap.

[0042] The fixed installation structure of the sealing strip 2 is that a blind hole is arranged on the upper surface of the cover body 1 near the step edge portion. An embedded part 14 is installed in the blind hole and is solidified with the cover body 1. The embedded part 14 is provided with a threaded blind hole. The upper edge of the sealing strip 2 is connected to the threaded blind hole of the embedded part 14 through a screw 13.

[0043] When the cover body 1 is installed on the helicopter, the steps on the edges of the cover body 1 are arranged in the upper frame 15 of the helicopter structure. The steps and the upper frame 15 of the helicopter structure form a square groove for accommodating the sealing rubber strip 4. The sealing rubber strip 4 is circumferentially attached between the step surface and the surface of the upper frame 15 of the helicopter structure to complete the sealing.

[0044] The sealing rubber strip 4 is an O-shaped sealing ring with multiple contact points. Specifically, the sealing rubber strip 4 is an O-shaped sealing ring. At least two protruding lines are arranged along the ring of the O-shaped sealing ring. The last protruding line of the outer ring part of the O-shaped sealing ring is the highest protruding line.

[0045] At the position of the cover body 1 near the metal structure of the helicopter, a conductive structure is arranged. The conductive structure is connected to the conductive device of the metal structure of the helicopter through a lead wire.

[0046] The sealing strips 2 at the front and rear of the main body 1 of the cover are replaced with positioning pin components 3. The positioning pin components 3 include a positioning base plate and a positioning pin. The positioning base plate has the same structure as the sealing strip 2, but is bent to match the bending convex shape of the main body 1 of the cover. The positioning base plate is provided with a hole that aligns with the positioning hole 17 of the fuselage. The positioning pin is inserted into the positioning hole 17 and the hole of the positioning base plate.

[0047] Another embodiment of the present invention will now be described with reference to the accompanying drawings.

[0048] A large, quick-release sealing cap assembly that is lightning-proof, corrosion-resistant, and can withstand the pressure of forced descent on water, such as... Figure 1 As shown, it consists of a cover body 1, a sealing strip 2, a positioning pin 3, a sealing strip 4, and a sealing butterfly lock 5.

[0049] Step 1, Design the main body of the cap 1:

[0050] like Figure 2 As shown, the main body of the canopy 1 has a boat-shaped cross-section, which can buffer the impact force of water contact during a forced descent on water.

[0051] like Figure 3 As shown, the main body 1 of the cover adopts an aluminum panel and aluminum honeycomb structure. The upper panel 6 and the lower panel 7 are both 2A12 aluminum alloy plates with a thickness of 0.5mm. The aluminum honeycomb 8 is made of aluminum honeycomb core material -53-4-0.05(Ⅱ)-δ25HB5443, with a height of 25mm and a density of 53kg / mm3. Aluminum honeycomb has better moisture resistance and impact resistance than paper honeycomb. J-96 medium-temperature adhesive 11+ is used between the upper panel 6 and the aluminum honeycomb 8, and between the lower panel 7 and the aluminum honeycomb 8. J-95 medium-temperature adhesive film 12 is used for bonding; before bonding, the upper panel 6 and the lower panel 7 are surface treated with phosphoric acid anodizing; the main body 1 of the cover is sealed with J-97 medium-temperature adhesive film 10 with a sealing thickness of 2mm; after sealing, two layers of glass cloth 9 are used for edge wrapping with a wrapping length of 30mm; the edge wrapping glass cloth 9 and the cover are bonded with J-96 medium-temperature base adhesive 11 + J-95 medium-temperature adhesive film 12; the main body 1 of the cover is heated in the furnace for bonding and molding, and after molding, the surface is sprayed with H06-27 anti-corrosion primer.

[0052] Step 2, design edge banding strip 2:

[0053] like Figure 1 As shown, the edge sealing strip 2 is arranged around the main body 1 of the cover, and it serves as a functional component for fixing the adhesive strip.

[0054] like Figure 4As shown, the edge sealing strip 2 has an L-shaped cross-section and is treated with borosilicate anodizing + H06-27 anti-corrosion primer. It is connected to the cap body 1 by screws 13 with a diameter of 4mm. The upper panel 6 of the cap body 1 has a hole of Ф4.2mm and the aluminum honeycomb 8 has a hole of Ф15mm. J-97 medium-temperature adhesive film 10 is used to fix the insert 14. The insert 14 is put into the oven for curing together with the cap body 1. The screws 13 are screwed into the insert 14, and the diameter of the insert 14 corresponds to the diameter of the screw 13. In order to withstand the clamping force of the sealing strip on the edge sealing strip 2 when the cap assembly is installed, the screws 13 are evenly distributed around the perimeter at a spacing of about 120mm, while ensuring that the screw threading distance d meets the condition of l≥(2*d+1)mm.

[0055] Step 3, Design positioning pin 3:

[0056] like Figure 5 As shown, the positioning pin 3 is made of 7050 aluminum alloy, and the surface treatment is borosilicate anodizing + H06-27 anti-corrosion primer; one is located on each side of the main body 1, one forward and one backward, aligned with the positioning hole 17 on the fuselage. When installing the main body assembly, the positioning pin 3 acts as a guide, and the fuselage positioning hole 17 acts as a limiting device; the installation method of the positioning pin 3 on the main body of the main body is the same as that of the edge sealing strip 2; as... Figure 6 As shown, the positioning pin 3 has an L-shaped cross-section, and the L-shaped bend serves to limit the sealing strip; the end of the positioning pin 3 is tapered, which makes the cap assembly easier to install and guide.

[0057] Step 4, Design sealing strip 4:

[0058] like Figure 4 As shown, the sealing strip 4 adopts an O-ring with a multi-contact design. The O-ring strip has good compression performance, and compared with other cross-sectional strips, it can reduce the locking force while ensuring the same compression amount. After the strip is compressed, one contact point can form a sealing line, and multiple contacts form multiple sealing lines. The last long contact point forms a rolled-up waterproof ridge after being squeezed, making the sealing strip more reliable. The sealing strip 4 with the bent edge 18 fits into the gap formed by the sealing strip 2 and the cap body 1, enhancing the reliability of the strip installation. The contact surface between the sealing strip 4 and the cap body 1 is designed to be flat. The sealing strip 4 is bonded to the cap body 1 with 193M adhesive, thereby further fixing the strip to the cap body 1.

[0059] Step 5, install the sealing butterfly lock 5:

[0060] like Figure 1 As shown, the sealed butterfly lock 5 is arranged on the four corners of the cover body 1. The butterfly lock 5 controls the movement of the locking tongue 22 by turning the handle 24. The locking tongue 22 is fixed on the lock seat 20 of the body.

[0061] like Figure 7As shown, the sealing type butterfly lock 5 is fixed on the cover body 1 by 4 bolts 21 with a diameter of 5 mm, and 4 corresponding diameter inserts are embedded in the cover body 1 corresponding to the positions of the 4 bolts, the fixing mode of the inserts is the same as that of the insert 14, the upper panel 6 has a Ф14.3 mm hole, and the aluminum honeycomb 8 has a Ф18 mm hole;

[0062] As shown in Figure 8 , Figure 9 To install the sealing type butterfly lock 5, the butterfly lock realizes sealing between the lock and the structure by using the sealing washer 16; the lower panel 7 and the aluminum honeycomb 8 have a saucer-shaped hole 23, the size of the saucer-shaped hole 23 should avoid interference with the butterfly lock, and the honeycomb is sealed with a J-97 medium temperature adhesive film 10 with a sealing thickness of 3 mm;

[0063] Step 6, design lightning protection grounding path:

[0064] As shown in Figure 7 On the cover body 1, try to arrange 1 set of cover assembly iron bolts 25, cover assembly grounding washer 26 and cover assembly grounding nut 27 near the metal structure of the machine body

[0065] As shown in Figure 10 On the metal structure 28 of the machine body, select a position as close as possible to the cover assembly iron bolt 25, and arrange 1 set of metal structure grounding nut 32, metal structure grounding washer 29 and metal structure grounding bolt 31;

[0066] Arrange the grounding wire 30, one end of which is installed between the metal structure grounding washer 29 and the metal structure grounding nut 32, and the other end is installed between the cover assembly grounding washer 26 and the cover assembly grounding nut 27;

[0067] The cover body 1 has a through hole at the cover assembly grounding bolt 25, and the aluminum honeycomb uses a J-97 medium temperature adhesive film 10 to seal the edge with a sealing thickness of 3 mm;

[0068] The contact area between the head of the cover assembly grounding bolt 25 and the lower panel 7 is removed to expose the metal; the contact area between the cover assembly grounding nut 27 and the grounding wire 30 is removed to expose the metal; the contact area between the head of the metal structure grounding bolt 31 and the metal structure 28 is removed to expose the metal; the contact area between the metal structure grounding nut 32 and the grounding wire 30 is removed to expose the metal;

[0069] Current transmission path: cover body lower panel 7→ cover assembly grounding bolt 25→ cover assembly grounding bolt 27→ cover assembly grounding washer 26→ grounding wire 30→ metal structure grounding washer 29→ metal structure grounding bolt 32→ metal structure 28→ machine body grounding point.

[0070] The key point of the present application is:

[0071] 1. The present application maintains the structural integrity of the port cover, port frame and sealing rubber strip, and the structural sealing performance is reliable;

[0072] 2. The present application uses a boat-shaped port cover to reduce the impact force when the aircraft is forced to land on water;

[0073] 3. The present application uses high-density and high-thickness aluminum honeycomb for the port cover body, which has strong load-bearing capacity;

[0074] 4. The present application uses edge sealing strips to limit the sealing rubber strip;

[0075] 5. The edge sealing strips in the present application can be detached, making the installation and removal of the sealing rubber strip simple and ensuring the interchangeability of the sealing rubber strip in the port cover assembly;

[0076] 6. The present application uses positioning pins, which have a guiding effect to make the installation of large port covers simple;

[0077] 7. The positioning pins used in the present application have a bending edge, which limits the sealing rubber strip;

[0078] 8. The present application uses O-shaped cross-section and multi-contact sealing rubber strips, making the structural sealing performance of the aircraft more reliable;

[0079] 9. The present application uses a sealing type butterfly lock, which has greater locking force than ordinary quick-release locks, ensuring reliable installation of the port cover;

[0080] 10. The butterfly lock used in the present application has a sealing washer, which ensures the sealing performance of the butterfly lock through hole on the port cover body;

[0081] 11. The present application uses a small number of butterfly locks, which ensures that the large port cover assembly is simple and fast to disassemble;

[0082] 12. The present application is designed with a lightning protection strap passage to ensure the safety of the aircraft after being struck by lightning;

[0083] 13. The present application selects appropriate materials and surface protection measures for the parts exposed to the external environment to avoid environmental corrosion problems.

[0084] The advantages of the present application are:

[0085] 1) Wide application range: this design method can be used in any large port cover assembly that needs to perform water landing tasks and ensure structural sealing performance;

[0086] 2) Reliable sealing performance: the sealing port cover assembly does not damage the structural integrity and sealing rubber strip, and the bending edges of the edge sealing strips and positioning pins limit the sealing rubber strip, making the structural sealing function reliable;

[0087] 3) reliable corrosion resistance: reasonable surface protection measures are adopted, so that the structure has reliable environmental corrosion resistance;

[0088] 4) reliable lightning protection performance: the lightning protection grounding path is designed, the grounding path is simple and has high conductivity, so that the safety of the aircraft is reliable;

[0089] 5) reliable carrying capacity: the cross-sectional form of the door cover assembly and the use of aluminum honeycomb make the carrying capacity reliable;

[0090] 6) simple installation and convenient maintenance: the structure is detachable, the number of quick-release locks is small, the door cover assembly is easy to install and maintain; the sealing edge strip is detachable, and the sealing rubber strip is easy to install and replace.

[0091] The above is only a specific embodiment of the present application, and the present application is described in detail, and the part not described in detail is a conventional technology. However, the protection scope of the present application is not limited to this, any skilled person in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application. The protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A quick-release sealing cap assembly suitable for aircraft models with water landing capability, characterized in that, Includes a main body of the cap (1) and a sealing strip (4). The cross-section of the main body of the cap (1) is boat-shaped, that is, the center line of the rectangular plate structure is bent downward to form a convex ridge. The direction of the center line is the heading. The sealing strip (4) is located on the outer edge of the main body of the cap (1). The main body of the cap (1) is connected to the helicopter structure through the connecting devices at the four corners. The main body of the cap (1) includes an upper panel (6), a lower panel (7) and an aluminum honeycomb (8). The upper panel (6) is pasted on the upper surface of the aluminum honeycomb (8), and the lower panel (7) is pasted on the lower surface of the aluminum honeycomb (8). The edges of the upper panel (6) and the lower panel (7) are sealed with glass cloth (9) on the side of the aluminum honeycomb (8). The edges of the aluminum honeycomb (8) are stepped, so that the upper surface of the aluminum honeycomb (8) is slightly smaller than the lower surface of the aluminum honeycomb (8); the glass cloth (9) seals the edges, including all the stepped surfaces; It also includes n edge sealing strips (2), which are long strip structures with an L-shaped cross section. The L-shape of the edge sealing strip (2) fits the upper surface of the cap body (1) and the outside of the step vertical surface and is detachably fixed. The n edge sealing strips (2) are respectively installed on the edge of the cap body (1) and press the sealing strip (4) tightly. The number of n is determined according to the length of a single edge sealing strip (2), the area of ​​the cap body (1) and the spacing between adjacent edge sealing strips (2). The inner side of the sealing strip (4) has a bent edge (18), and there is a gap between the sealing strip (2) and the vertical and horizontal surfaces of the steps of the main body of the cover (1), and the bent edge (18) is inserted into the gap; It also includes a sealed butterfly lock (5), which is arranged on the four corners of the main body of the cover (1). The sealed butterfly lock (5) controls the movement of the latch (22) by turning the handle (24). The latch (22) is fixed to the fuselage lock seat (20) of the helicopter.

2. A quick-release sealing cap assembly for aircraft with water landing capability as described in claim 1, characterized in that, The fixed installation structure of the edge sealing strip (2) is as follows: a blind hole is set on the upper surface of the cap body (1) near the edge of the step, an insert (14) is inserted into the blind hole and cured together with the cap body (1), the insert (14) is provided with a threaded blind hole, and the upper edge of the edge sealing strip (2) is connected to the threaded blind hole of the insert (14) by a screw (13).

3. A quick-release sealing cap assembly for aircraft with water landing capability as described in claim 1, characterized in that, When the main body of the cover (1) is installed on the helicopter, the steps on the edge of the main body of the cover (1) are all located inside the upper frame (15) of the helicopter's fuselage structure. The steps and the upper frame (15) of the fuselage structure form a square groove to accommodate the sealing strip (4). The sealing strip (4) is circumferentially attached between the step surface and the surface of the upper frame (15) of the fuselage structure to complete the seal.

4. A quick-release sealing cap assembly for aircraft with water landing capability as described in claim 1, characterized in that, The sealing strip (4) is an O-ring with multiple contacts, specifically the main body of the O-ring. It has at least two raised lines along the circumferential direction of the O-ring, and the last raised line on the outer ring of the O-ring is the line with the highest protrusion.

5. A quick-release sealing cap assembly for aircraft with water landing capability as described in claim 1, characterized in that, The sealing strips (2) at the front and rear of the main body of the cover (1) are replaced with positioning pin assemblies (3). The positioning pin assembly (3) includes a positioning base plate and a positioning pin. The positioning base plate has the same structure as the sealing strip (2) but is bent to match the bending convex shape of the main body of the cover (1). The positioning base plate has a hole that aligns with the positioning hole (17) of the fuselage. The positioning pin is inserted into the positioning hole (17) and the hole of the positioning base plate.

6. A quick-release sealing cap assembly for aircraft with water landing capability as described in claim 1, characterized in that, A conductive structure is provided on the main body of the mouth cover (1) near the metal structure of the machine body. The conductive structure is connected to the conductive device of the metal structure of the machine body through lead wires.

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