Aircraft float connection structure and fixed-wing aircraft having the same

Abstract

The present invention discloses a connection structure of an aircraft float and a fixed-wing aircraft having the same, and relates to the technical field of aircraft floats, including: a connection assembly, the connection assembly includes: a fuselage force dispersion plate assembly, a float force dispersion plate assembly and a quick-release connection assembly; the fuselage force dispersion plate assembly and the float force dispersion plate assembly are arranged relatively; the fuselage force dispersion plate assembly is fixed to the fuselage shell; the float force dispersion plate assembly is fixed to the float shell; the quick-release connection assembly includes a connector 1 and a connector 2, the connector 1 and the connector 2 are quickly released, the free end of the connector 1 is fixedly connected to the fuselage force dispersion plate assembly, and the free end of the connector 2 is fixedly connected to the float force dispersion plate assembly to form a quick-release connection structure between the aircraft fuselage and the float. The connection structure of the aircraft float of the present invention can realize the rapid disassembly and assembly of the float, and the stress generated by the connection structure is easier to disperse, and has the characteristics of simple overall structure, stability and durability.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft floats, in particular to a connecting structure of an aircraft float and a fixed-wing aircraft having the same. Background Art

[0002] Amphibious aircraft can take off and land on both land and water, and their floats are generally installed at the lower part of the wing. The floats of existing amphibious aircraft are generally installed at the lower end of the wing through a wing box structure or a combined beam structure, and the two ends of the connection structure are respectively connected to the wing structure and the float cylinder structure. This connection structure has the disadvantages of complex structural assembly, large mass, and poor corrosion resistance. In addition, the floats of existing manned sports fixed-wing aircraft are mostly fixed or non-detachable, which has the disadvantage that they cannot or are difficult to be removed during pure land takeoff and landing, thereby generating unnecessary weight and resistance during flight.

[0003] Therefore, how to develop a connection structure for aircraft pontoons and a fixed-wing aircraft having the same, which can achieve rapid disassembly and assembly of pontoons, more easily disperse the stress generated by the connection structure, and have the characteristics of simple overall structure, stability and durability is an urgent problem to be solved by technical personnel in this field. Summary of the invention

[0004] In view of this, the present invention proposes a connection structure for aircraft floats and a fixed-wing aircraft having the same, aiming to solve the problem that when the above-mentioned existing aircraft with floats take off and land purely on land, the floats are fixed and cannot be disassembled or are difficult to disassemble, resulting in unnecessary load and resistance during flight.

[0005] In order to achieve the above object, the present invention adopts the following technical solution:

[0006] One aspect of the present invention provides a connection structure for an aircraft float, comprising:

[0007] A connection assembly, the connection assembly comprising: a fuselage force dispersion plate assembly, a buoy force dispersion plate assembly and a quick-release connection assembly;

[0008] The fuselage force dispersion plate assembly and the buoy force dispersion plate assembly are arranged relatively to each other; the fuselage force dispersion plate assembly is fixed to the fuselage shell; the buoy force dispersion plate assembly is fixed to the buoy shell;

[0009] The quick-release connection assembly includes a connector 1 and a connector 2, wherein the connector 1 and the connector 2 are quickly released and connected, the free end of the connector 1 is fixedly connected to the fuselage force dispersion plate assembly, and the free end of the connector 2 is fixedly connected to the pontoon force dispersion plate assembly to form a quick-release connection structure between the aircraft fuselage and the pontoon.

[0010] It can be known from the above technical solutions that, compared with the prior art, the connection structure of the aircraft pontoon disclosed in the present invention adopts a quick-release pontoon design, and realizes the rapid disassembly and assembly of the aircraft and the pontoon through the quick-release connection assembly; the pontoon can be quickly disassembled as needed, thereby reducing the weight and flight resistance of the aircraft during flight; in order to prevent the aircraft and the pontoon from being damaged by local force, the connection force between the two is first transmitted to the fuselage force dispersion plate assembly and the pontoon force dispersion plate assembly through the quick-release connection assembly, and then transmitted to the corresponding aircraft fuselage and pontoon by the fuselage force dispersion plate assembly and the pontoon force dispersion plate assembly, respectively, to realize the step-by-step divergence of the connection force. The present invention can realize the rapid disassembly and assembly of the pontoon, and the stress generated by the connection structure is easier to disperse, and has the characteristics of simple overall structure, stability and durability.

[0011] As a further improvement of the above technical solution, the quick-release connection assembly further includes a plug-in and pull-out pin;

[0012] The connector 1 and the connector 2 are provided with a first plug hole and a second plug hole at opposite ends thereof respectively;

[0013] The first plug hole is coaxially arranged with the second plug hole, and the plug-in pin movably penetrates the first plug hole and the second plug hole to detachably connect the first connector and the second connector together.

[0014] The connector 1 and the connector 2 of the present invention are connected by a latch to form a quick-release structure, which is simple and convenient to operate.

[0015] As a further improvement of the above technical solution, there are two connectors one, and the two connectors one are arranged at intervals along the height direction of the aircraft; the connector two is located between the two connectors one, and the socket two of the connector two is coaxial with the sockets one of the two connectors one; the plug-in pin is inserted into the two sockets one and the socket two.

[0016] By arranging the connector 2 between the two connectors 1, stable constraint of the connector 2 is achieved, thereby improving the reliability of the connection structure.

[0017] As a further improvement of the above technical solution, there are two connectors 2, and the two connectors 2 are arranged at intervals along the height direction of the aircraft; the two connectors 2 are located between the two connectors 1, and the sockets 2 of the two connectors 2 are coaxial with the sockets 1 of the two connectors 1; the plug-in pin is inserted into the two sockets 1 and the two sockets 2.

[0018] By connecting two connectors 2 arranged at intervals with the corresponding two connectors 1, the stress points are spaced apart to prevent excessive stress concentration, which can further improve the stress stability of the connection structure between the float and the fuselage.

[0019] As a further improvement of the above technical solution, a stopper is fixed on the top of the plug-in pin, which can prevent the plug-in pin from falling out of the socket.

[0020] As a further improvement of the above technical solution, the fuselage force dispersion plate assembly includes a first dispersion plate and a second dispersion plate, the first dispersion plate and the second dispersion plate are both in two pieces; the two first dispersion plates are both located inside the fuselage shell, and are respectively arranged corresponding to the two sides of the fuselage bulkhead plate in the fuselage shell; the two second dispersion plates are respectively located at the outer ends of the two first dispersion plates in the opposite direction; the two first dispersion plates and the two second dispersion plates are fixedly connected by fasteners to be fastened to the fuselage bulkhead plate;

[0021] The buoy force dispersion plate assembly includes a third dispersion plate and a fourth dispersion plate, and the third dispersion plate and the fourth dispersion plate are both in two pieces; the two third dispersion plates are both located inside the buoy shell, and are respectively arranged on both sides of the buoy ribs in the buoy shell; the two fourth dispersion plates are respectively located at the outer ends of the two third dispersion plates in opposite directions; the two third dispersion plates and the two fourth dispersion plates are fixedly connected by fasteners to be fastened to the buoy ribs;

[0022] One end of the connector 1 away from the socket 1 is located between the two first dispersion plates, and is fixedly connected to the two first dispersion plates and the two second dispersion plates by fasteners; one end of the connector 2 away from the socket 2 is located between the two third dispersion plates, and is fixedly connected to the two third dispersion plates and the two fourth dispersion plates by fasteners.

[0023] The first dispersion plate, the second dispersion plate, the third dispersion plate and the fourth dispersion plate play the role of dispersing the connection tension between the aircraft and the pontoon in multiple stages; the fuselage bulkhead plate is clamped and fixed by the first dispersion plate and the second dispersion plate, the pontoon rib plate is clamped and fixed by the third dispersion plate and the fourth dispersion plate, and the connector 1 and the connector 2 are built between the corresponding connection plates and clamped and fixedly connected, achieving the technical effect of a firm connection. Each dispersion plate is located inside the fuselage shell or the pontoon shell, which can not only reduce the windward resistance and corrosion of the external environment, but also make the appearance clean and beautiful.

[0024] As a further improvement of the above technical solution, the connector 1 includes a connecting arm 1 and a shaft sleeve 1, one end of the connecting arm 1 is fixed to the outer wall of the shaft sleeve 1, and a hole of the shaft sleeve is the plug hole 1;

[0025] The second connector includes a second connecting arm and a second shaft sleeve; one end of the second connecting arm is fixed to the outer wall of the second shaft sleeve, and the second sleeve hole is the second plug hole; the axis lines of the first plug hole and the second plug hole are arranged along the height direction of the aircraft;

[0026] The connecting arm 1 is located inside the fuselage shell; the sleeve 1, the connecting arm 2 and the sleeve 2 are all located inside the float shell; an avoidance hole is provided at the top of the float shell corresponding to the socket 1 and the socket 2; the plug-in pin is inserted into the avoidance hole from the top of the float shell and passes downward through the socket 1 and the socket 2.

[0027] The connecting arm 1, the connecting arm 2, the shaft sleeve 1 and the shaft sleeve 2 are all built into the corresponding shell, which further reduces the wind resistance and the corrosion of the external environment and improves the durability and safety of the connection structure.

[0028] As a further improvement of the above technical solution, the first dispersion plate and the third dispersion plate are both carbon fiber plates; the second dispersion plate and the fourth dispersion plate are both aluminum alloy plates, and the plate surfaces are both provided with weight-reducing holes; the plug-in pin, the connector one and the connector two are all made of titanium alloy.

[0029] The connector is made of titanium alloy with high structural strength, light weight and good corrosion resistance, the second dispersion plate and the fourth dispersion plate are made of lightweight and corrosion-resistant aluminum alloy plates, and the first dispersion plate and the third dispersion plate are made of lightweight, high modulus and corrosion-resistant carbon fiber plates; the stress generated by the connection between the connectors is transmitted step by step through the aluminum alloy plates and the carbon fiber plates to the fuselage bulkhead plates in the fuselage shell and the buoy rib plates in the buoy shell, thereby solving the problem that the connection between composite materials and metal parts is easily damaged due to stress concentration, greatly reducing the stress concentration between the buoy and the fuselage, and improving the stability and durability of the connection structure.

[0030] As a further improvement of the above technical solution, there are more than two connecting assemblies, and the more than two connecting assemblies are arranged at intervals along the length direction of the buoy shell.

[0031] More than two connection assemblies can be adapted to buoys of different lengths, further increasing the stability of the connection structure.

[0032] Another aspect of the present invention provides a fixed-wing aircraft, including the connection structure of the aircraft float; the outer wall of the float shell of the fixed-wing aircraft is provided with a pressure regulating port connected to the closed inner cavity of the float; the pressure regulating port is installed with a flexible sealing membrane.

[0033] The pressure of the gas in the closed inner cavity of the float will change when the temperature changes, which will cause the sealed hard shell structure of the float to expand or contract. In order to prevent this phenomenon from affecting or damaging the float shell, a flexible sealing membrane is designed and installed on the outer wall of the float shell. The bulge or depression of the flexible sealing membrane can balance the pressure difference between the gas in the inner cavity of the float and the external atmosphere, thereby avoiding structural deformation of the float shell and increasing its service life.

[0034] It can be seen from the above technical solutions that, compared with the prior art, the present invention discloses a connection structure for aircraft floats, which has the following advantages and beneficial effects:

[0035] 1. The connection structure of the aircraft buoy provided by the present invention adopts a latch-positioned connection form, which realizes the rapid combination or separation between the buoy and the fuselage and is easy to operate.

[0036] 2. The connection structure of the aircraft buoy provided by the present invention has a connection assembly placed inside the buoy and the fuselage, which can reduce wind resistance and corrosion from the external environment while making the appearance clean and beautiful.

[0037] 3. The aircraft buoy connection structure provided by the present invention greatly reduces the deadweight of the structure while ensuring the structural strength and function. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0039] Figure 1 A three-dimensional schematic diagram of the connection structure of the aircraft float of the present invention;

[0040] Figure 2 A schematic diagram of the internal structure of the connection structure of the aircraft float of the present invention;

[0041] Figure 3 A schematic diagram of the structure of the quick-release connection assembly of the connection structure of the aircraft buoy of the present invention;

[0042] Figure 4 A schematic diagram of the assembly of another form of quick-release connection components of the connection structure of the aircraft float of the present invention;

[0043] Figure 5 A schematic diagram of a quick-release connection assembly structure of another form of the connection structure of the aircraft float of the present invention;

[0044] Figure 6 A schematic diagram of the connecting body structure of another form of the quick-release connecting assembly of the connecting structure of the aircraft float of the present invention;

[0045] Figure 7 A schematic diagram of the assembly state of the quick-release connection assembly of the present invention on a fixed-wing aircraft;

[0046] Figure 8 A schematic diagram of the fixed-wing aircraft and the buoy assembly state of the present invention;

[0047] In the figure: 1. Fuselage force dispersion plate assembly; 11. First dispersion plate; 12. Second dispersion plate; 2. Float force dispersion plate assembly; 21. Third dispersion plate; 22. Fourth dispersion plate; 3. Quick-release connection assembly; 31. Plug-in pin; 311. Stopper; 32. Connecting body one; 321. Connecting arm one; 322. Bushing one; 3221. Socket one; 33. Connecting body two; 331. Connecting arm two; 332. Bushing two; 3321. Socket two; 4. Fuselage shell; 41. Fuselage bulkhead; 5. Float shell; 51. Float rib; 52. Avoidance hole; 53. Pressure regulating port; 54. Flexible sealing membrane; 6. Fasteners. DETAILED DESCRIPTION

[0048] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0049] In the description of the present invention, it is necessary to understand that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0050] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0051] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0052] like Figures 1 to 8As shown, this embodiment provides a connection structure for aircraft pontoons, wherein two pontoon shells 5 of the aircraft are symmetrically arranged on both sides of a fuselage shell 4, and include:

[0053] The connection assembly comprises: a fuselage force dispersion plate assembly 1, a buoy force dispersion plate assembly 2 and a quick-release connection assembly 3.

[0054] The fuselage force dispersion plate assembly 1 and the buoy force dispersion plate assembly 2 are arranged relatively to each other; the fuselage force dispersion plate assembly 1 is fixed to the fuselage shell 4; and the buoy force dispersion plate assembly 2 is fixed to the buoy shell 5.

[0055] The quick-release connection assembly 3 includes a connector 1 32 and a connector 2 33, which are quickly released and connected. The free end of the connector 1 32 is fixedly connected to the fuselage force distribution plate assembly 1, and the free end of the connector 2 33 is fixedly connected to the buoy force distribution plate assembly 2 to form a quick-release connection structure between the aircraft fuselage and the buoy.

[0056] The connection structure of the aircraft pontoon provided in this embodiment adopts a quick-release pontoon design, and realizes the rapid disassembly and assembly of the aircraft and the pontoon through the quick-release connection component 3; the pontoon can be quickly disassembled as needed, thereby reducing the aircraft weight and flight resistance during flight; in order to prevent the aircraft and the pontoon from being damaged by local force, the connection force between the two is first transmitted to the fuselage force dispersion plate component 1 and the pontoon force dispersion plate component 2 through the quick-release connection component 3, and then transmitted to the corresponding aircraft fuselage and pontoon by the fuselage force dispersion plate component 1 and the pontoon force dispersion plate component 2, respectively, to realize the step-by-step divergence of the connection force. The present invention can not only realize the rapid disassembly and assembly of the pontoon, but also reduce the structural weight under the premise of ensuring the structural strength and function, and the structure is simple and stable.

[0057] In some embodiments, the quick-release connection assembly 3 further includes a plug-in pin 31;

[0058] The connector 1 32 and the connector 2 33 are respectively provided with a first plug hole 3221 and a second plug hole 3321 at opposite ends thereof;

[0059] The first plug hole 3221 and the second plug hole 3321 are coaxially arranged, and the plug-in pin 31 movably penetrates the first plug hole 3221 and the second plug hole 3321 to detachably connect the first connector 32 and the second connector 33 together.

[0060] The connector 1 32 and the connector 2 33 are connected by a latch to form a quick-release structure, which is easy and convenient to operate.

[0061] In some embodiments, there are two connectors 32, and the two connectors 32 are arranged at intervals along the height direction of the aircraft; the connector 2 33 is located between the two connectors 32, and the second socket 3321 of the connector 2 33 is coaxial with the first socket 3221 of the two connectors 32; the plug-in pin 31 is inserted into the two sockets 1 3221 and the socket 2 3321.

[0062] By arranging the second connector 33 between the two first connectors 32, stable constraint of the second connector 33 is achieved, thereby improving the reliability of the connection structure.

[0063] In some embodiments, there are two connectors 33, and the two connectors 33 are arranged at intervals along the height direction of the aircraft; the two connectors 33 are located between the two connectors 32, and the two sockets 3321 of the two connectors 33 are coaxial with the sockets 1 3221 of the two connectors 1 32; the plug-in pin 31 is inserted into the two sockets 1 3221 and the two sockets 2 3321.

[0064] The two connectors 2 33 arranged at intervals are connected to the corresponding two connectors 1 32 so that the stress points are spaced apart to prevent excessive stress concentration, thereby further improving the stress stability of the connection structure between the buoy and the fuselage.

[0065] In some embodiments, a stopper 311 is fixed to the top of the plug-in pin 31. The stopper 311 can prevent the plug-in pin 31 from falling out of the socket.

[0066] In some embodiments, the fuselage force dispersion plate assembly 1 includes a first dispersion plate 11 and a second dispersion plate 12, and the first dispersion plate 11 and the second dispersion plate 12 are both two pieces; the two first dispersion plates 11 are both located inside the fuselage shell 4, and are respectively arranged on both sides of the fuselage bulkhead plate 41 in the fuselage shell 4; the two second dispersion plates 12 are respectively located at the outer ends of the two first dispersion plates 11 in opposite directions; the two first dispersion plates 11 and the two second dispersion plates 12 are fixedly connected by fasteners 6 to be fastened to the fuselage bulkhead plate 41.

[0067] The buoy force dispersion plate assembly 2 includes a third dispersion plate 21 and a fourth dispersion plate 22, and the third dispersion plate 21 and the fourth dispersion plate 22 are both two pieces; the two third dispersion plates 21 are both located inside the buoy shell 5, and are respectively arranged on both sides of the buoy ribs 51 in the buoy shell 5; the two fourth dispersion plates 22 are respectively located at the outer ends of the two third dispersion plates 21 in relative directions; the two third dispersion plates 21 and the two fourth dispersion plates 22 are fixedly connected by fasteners 6 to be fastened to the buoy ribs 51.

[0068] One end of the connector 32 away from the socket 1 3221 is located between the two first dispersion plates 11, and is fixedly connected to the two first dispersion plates 11 and the two second dispersion plates 12 by fasteners 6; one end of the connector 33 away from the socket 2 3321 is located between the two third dispersion plates 21, and is fixedly connected to the two third dispersion plates 21 and the two fourth dispersion plates 22 by fasteners 6.

[0069] The first dispersion plate 11 and the second dispersion plate 12, the third dispersion plate 21 and the fourth dispersion plate 22 play the role of dispersing the connection tension between the aircraft and the pontoon in multiple stages; the fuselage bulkhead plate 41 is clamped and fixed by the first dispersion plate 11 and the second dispersion plate 12, the pontoon rib plate 51 is clamped and fixed by the third dispersion plate 21 and the fourth dispersion plate 22, and the connector 1 32 and the connector 2 33 are built between the corresponding connecting plates and are clamped and fixedly connected, achieving the technical effect of a firm connection. Each dispersion plate is located inside the fuselage shell or the pontoon shell, which can not only reduce the windward resistance and corrosion of the external environment, but also make the appearance clean and beautiful.

[0070] Specifically, the buoy rib 51 is fixed inside the buoy shell 5 ; and the fuselage bulkhead plate 41 is fixed inside the fuselage shell 4 .

[0071] In some embodiments, the connector 32 includes a connector arm 321 and a sleeve 322, one end of the connector arm 321 is fixed to the outer wall of the sleeve 322, and the sleeve hole of the sleeve 322 is the plug hole 3221;

[0072] The second connector 33 includes a second connecting arm 331 and a second sleeve 332; one end of the second connecting arm 331 is fixed to the outer wall of the second sleeve 332, and the sleeve hole of the second sleeve 332 is a second plug hole 3321; the axis lines of the first plug hole 3221 and the second plug hole 3321 are arranged along the height direction of the aircraft.

[0073] The connecting arm 1 321 is located inside the fuselage shell 4; the shaft sleeve 1 322, the connecting arm 2 331 and the shaft sleeve 2 332 are all located inside the buoy shell 5; the top of the buoy shell 5 corresponds to the socket 1 3221 and the socket 2 3321. An avoidance hole 52 is provided; the plug-in pin 31 is inserted into the avoidance hole 52 from the top of the buoy shell 5 and passes through the socket 1 3221 and the socket 2 3321 downward.

[0074] The connecting arm 1 321, the connecting arm 2 331, the shaft sleeve 1 322, and the shaft sleeve 2 332 are all built inside the corresponding shell, which further reduces the wind resistance and corrosion of the external environment and improves the durability and safety of the connection structure.

[0075] In some embodiments, the first dispersion plate 11 and the third dispersion plate 21 are both carbon fiber plates; the second dispersion plate 12 and the fourth dispersion plate 22 are both aluminum alloy plates, and the plate surfaces are provided with weight-reducing holes; the plug-in pin 31, connector one 32 and connector two 33 are all made of titanium alloy.

[0076] The connector is made of a titanium alloy material with high structural strength, light weight and good corrosion resistance; the second dispersion plate 12 and the fourth dispersion plate 22 are made of a lightweight and corrosion-resistant aluminum alloy plate; the first dispersion plate 11 and the third dispersion plate 21 are made of a lightweight, high modulus and corrosion-resistant carbon fiber plate; the stress generated by the connection between the connectors is transmitted step by step through the aluminum alloy plate and the carbon fiber plate to the fuselage bulkhead plate 41 in the fuselage shell and the buoy rib plate 51 in the buoy shell, thereby solving the problem that the connection between the composite material and the metal parts is easily damaged due to stress concentration, greatly reducing the stress concentration between the buoy and the fuselage, and improving the stability and durability of the connection structure.

[0077] In some embodiments, there are two connecting assemblies, which are arranged at intervals along the length direction of the buoy shell 5 and correspond to two ends of the buoy shell 5 respectively.

[0078] More than two connection components may be provided, and the more than two connection components may be adapted to floats of different lengths, thereby further increasing the stability of the connection structure.

[0079] The embodiment of the present invention further provides a fixed-wing aircraft, including a connection structure of an aircraft pontoon; the outer wall of the pontoon shell 5 of the fixed-wing aircraft is provided with a pressure regulating port 53 connected to the closed inner cavity of the pontoon; the pressure regulating port 53 is installed with a flexible sealing membrane 54.

[0080] Specifically, the flexible sealing membrane 54 can be a rubber membrane; the flexible sealing membrane 54 covers the pressure regulating port 53, and a pressure ring is used to press and fix the flexible sealing membrane 54 at the pressure regulating port 53 to close the pressure regulating port 53; the pressure ring is fixed to the outer wall of the float shell 5 with bolts; the ring hole of the pressure ring corresponds to the pressure regulating port 53 and the shape and size are adapted.

[0081] The pressure of the gas in the closed inner cavity of the float will change when the temperature changes, which will cause the sealed hard shell structure of the float to expand or contract. In order to prevent this phenomenon from affecting or damaging the float shell, a flexible sealing membrane 54 is designed and installed on the outer wall of the float shell 5. The bulge or depression of the flexible sealing membrane 54 can be used to balance the pressure difference between the gas in the inner cavity of the float and the external atmosphere, thereby avoiding structural deformation of the float shell and increasing its service life.

[0082] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine different embodiments or examples described in this specification.

[0083] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. The connection structure of an aircraft buoy is characterized in that: include: A connection assembly, the connection assembly comprising: a fuselage force dispersion plate assembly (1), a buoy force dispersion plate assembly (2) and a quick-release connection assembly (3); The fuselage force dispersion plate assembly (1) and the buoy force dispersion plate assembly (2) are arranged relative to each other; the fuselage force dispersion plate assembly (1) is fixed to the fuselage shell (4); the buoy force dispersion plate assembly (2) is fixed to the buoy shell (5); The quick-release connection assembly (3) comprises a connector 1 (32) and a connector 2 (33), wherein the connector 1 (32) and the connector 2 (33) are quickly-released and connected, wherein the free end of the connector 1 (32) is fixedly connected to the fuselage force dispersion plate assembly (1), and the free end of the connector 2 (33) is fixedly connected to the buoy force dispersion plate assembly (2), so as to form a quick-release connection structure between the aircraft fuselage and the buoy; The quick-release connection assembly (3) further comprises a plug-in and pull-out pin (31); The connecting body 1 (32) and the connecting body 2 (33) are respectively provided with a first plug hole (3221) and a second plug hole (3321) at opposite ends thereof; The first plug hole (3221) and the second plug hole (3321) are coaxially arranged, and the plug-in pin (31) movably penetrates the first plug hole (3221) and the second plug hole (3321) to detachably connect the first connector (32) and the second connector (33); The fuselage force dispersion plate assembly (1) comprises a first dispersion plate (11) and a second dispersion plate (12), wherein the first dispersion plate (11) and the second dispersion plate (12) are both two pieces; the two first dispersion plates (11) are both located inside the fuselage shell (4) and are respectively arranged corresponding to the two sides of the fuselage bulkhead plate (41) inside the fuselage shell (4); the two second dispersion plates (12) are respectively located at the outer ends of the two first dispersion plates (11) in the opposite direction; the two first dispersion plates (11) and the two second dispersion plates (12) are fixedly connected by fasteners (6) to be fastened to the fuselage bulkhead plate (41); The buoy force dispersion plate assembly (2) comprises a third dispersion plate (21) and a fourth dispersion plate (22), wherein the third dispersion plate (21) and the fourth dispersion plate (22) are both two pieces; the two third dispersion plates (21) are both located inside the buoy shell (5), and are respectively arranged on both sides of the buoy rib (51) inside the buoy shell (5); the two fourth dispersion plates (22) are respectively located at the outer ends of the two third dispersion plates (21) in opposite directions; the two third dispersion plates (21) and the two fourth dispersion plates (22) are fixedly connected by fasteners (6) to be fastened to the buoy rib (51); One end of the connector 1 (32) away from the insertion hole 1 (3221) is located between the two first dispersion plates (11), and is fixedly connected to the two first dispersion plates (11) and the two second dispersion plates (12) via fasteners (6); one end of the connector 2 (33) away from the insertion hole 2 (3321) is located between the two third dispersion plates (21), and is fixedly connected to the two third dispersion plates (21) and the two fourth dispersion plates (22) via fasteners (6).

2. The connection structure of the aircraft float according to claim 1, characterized in that: There are two connectors (32), and the two connectors (32) are arranged at intervals along the height direction of the aircraft; the connector (33) is located between the two connectors (32), and the second plug hole (3321) of the connector (33) is coaxial with the first plug holes (3221) of the two connectors (32); the plug-in pin (31) is inserted into the two first plug holes (3221) and the second plug hole (3321).

3. The connection structure of the aircraft float according to claim 2, characterized in that: There are two connectors (33) and the two connectors (33) are arranged at intervals along the height direction of the aircraft; the two connectors (33) are located between the two connectors (32), and the second plug holes (3321) of the two connectors (33) are coaxial with the first plug holes (3221) of the two connectors (32); the plug-in pin (31) is inserted into the two first plug holes (3221) and the two second plug holes (3321).

4. The connection structure of the aircraft float according to claim 3, characterized in that: A stopper (311) is fixed on the top end of the plug-pull pin (31).

5. The connection structure of the aircraft float according to claim 1, characterized in that: The connecting body 1 (32) comprises a connecting arm 1 (321) and a shaft sleeve 1 (322), one end of the connecting arm 1 (321) is fixed to the outer wall of the shaft sleeve 1 (322), and the sleeve hole of the shaft sleeve 1 (322) is the insertion hole 1 (3221); The second connector (33) comprises a second connecting arm (331) and a second shaft sleeve (332); one end of the second connecting arm (331) is fixed to the outer wall of the second shaft sleeve (332), and the sleeve hole of the second shaft sleeve (332) is the second plug hole (3321); the axis lines of the first plug hole (3221) and the second plug hole (3321) are arranged along the height direction of the aircraft; The connecting arm 1 (321) is located inside the fuselage shell (4); the shaft sleeve 1 (322), the connecting arm 2 (331) and the shaft sleeve 2 (332) are all located inside the buoy shell (5); the top end of the buoy shell (5) is provided with an avoidance hole (52) corresponding to the plug hole 1 (3221) and the plug hole 2 (3321); the plug-in pin (31) is inserted into the avoidance hole (52) from the top end of the buoy shell (5) and passes through the plug hole 1 (3221) and the plug hole 2 (3321) downwards.

6. The connection structure of the aircraft float according to claim 1, characterized in that: The first dispersion plate (11) and the third dispersion plate (21) are both carbon fiber plates; the second dispersion plate (12) and the fourth dispersion plate (22) are both aluminum alloy plates, and the plate surfaces are both provided with weight-reducing holes; the plug-in pin (31), the connector one (32) and the connector two (33) are all made of titanium alloy.

7. The connection structure of the aircraft float according to claim 1, characterized in that: There are more than two connection assemblies, and the more than two connection assemblies are arranged at intervals along the length direction of the buoy shell (5).

8. A fixed-wing aircraft, characterized in that: It comprises the connection structure of the aircraft float according to any one of claims 1 to 7; the outer wall of the float shell (5) is provided with a pressure regulating port (53) connected to the closed inner cavity of the float; the pressure regulating port (53) is installed with a flexible sealing membrane (54).

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