Capsule body of flexible aircraft, flexible aircraft and capsule body splicing method

Abstract

The invention discloses a capsule body of a flexible aircraft, the flexible aircraft and a capsule body splicing method, and relates to the technical field of flexible aircrafts. The bag body comprises a force bearing fabric layer and a gas barrier film. The bearing fabric layer is a biaxial warp knitting layer and comprises warp yarns, weft yarns and knitting yarns which are perpendicular to one another. The warp yarn layer and the weft yarn layer are overlapped in the thickness direction of the force bearing fabric layer, and the weaving yarn is woven between the warp yarn layer and the weft yarn layer. And the gas barrier film is compounded on the outer surface of the bearing fabric layer through lamination. The weaving yarns comprise thermoplastic yarns which can be melted at high temperature to fill gaps of the fabric. The gas barrier film includes a thermoplastic polyurethane film and / or a polyester film. Therefore, the low-cost high-performance flexible aircraft capsule material can be produced, and the low-cost requirement of the high-performance capsule material is met.

Description

Technical Field

[0001] The present invention relates to the technical field of flexible aircraft, and in particular to a capsule of a flexible aircraft and a method for splicing the flexible aircraft and the capsule. Background Art

[0002] High-performance flexible aircraft include various platforms such as stratospheric airships, heavy-load airships, high-altitude balloons, inflatable drones, and floating wind power generation systems. This type of aircraft has the advantages of strong load capacity, long hovering time, and low cost, and has unique application value in many fields.

[0003] At present, the capsule materials of high-performance flexible aircraft are mostly made of multifunctional materials, which are obtained through a laminated composite (coating or lamination) process. That is, gas barrier materials, weather-resistant materials and other functional materials are laminated on the surface of the load-bearing fabric through adhesives to form a complete and coordinated flexible composite material. This flexible composite material has the characteristics of high strength, light weight, high gas barrier and high weather resistance.

[0004] Among them, the bearing strength and gas barrier properties of the capsule material are the key properties of the flexible aircraft capsule, which determine the performance and use cost of the aircraft.

[0005] Therefore, improving the specific strength of load-bearing fabrics and the barrier properties of gas barrier films have become the main methods for current high-performance flexible aircraft capsule materials. For example, to improve the specific strength of load-bearing fabrics, high-performance fibers with high specific strength, such as Vectran fibers, aramid fibers, polyester fibers, and poly-p-phenylenebenzobisoxazole fibers (Poly-p-phenylenebenzobisoxazole, referred to as PBO fibers), can be used to replace polyester and nylon fibers. For example, to improve the air tightness of the capsule, the gas barrier film can use a high-barrier film, such as polyvinylidene fluoride film (PVDF film), polyamide film (PA), EVOH film or its co-extruded film, to replace polyurethane film or polyester film. This technical approach can indeed improve the performance of capsule materials to a certain extent, but it also brings about a substantial increase in the cost of material production, limiting the widespread application and technological development of flexible aircraft.

[0006] Moreover, this method of improving the performance of functional materials does not effectively solve the problem of insufficient airtightness of the aircraft capsule after processing and molding. Experiments have shown that using conventional overlapping or docking methods, the buoyant gas in the capsule can quickly leak out through the fiber gaps between the joints, resulting in the flexible aircraft's hovering time not meeting the requirements and the aircraft's use cost being higher than expected.

[0007] Therefore, developing low-cost, high-performance bladder materials with good molding process performance and solving the problem of air leakage in the seams of bladder panels have become urgent needs for flexible aircraft to enter into widespread engineering applications. Summary of the invention

[0008] The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, the present invention proposes a flexible aircraft capsule, which improves the layer structure of the capsule material to make it low-cost and have good molding process performance, and can solve the problem of air leakage in the splicing seams of the capsule panels.

[0009] The invention also provides a method for splicing a capsule of a flexible aircraft.

[0010] The present invention also provides a flexible aircraft having the capsule.

[0011] According to the capsule of the flexible aircraft of the first embodiment of the invention, the capsule comprises a load-bearing fabric layer and a gas barrier film. The load-bearing fabric layer is a biaxial warp knitted layer, and comprises: warp yarns, a plurality of the warp yarns are laid flat to form a warp yarn layer; weft yarns, a plurality of the weft yarns are laid flat to form a weft yarn layer, the weft yarns are perpendicular to the warp yarns, the warp yarn layer and the weft yarn layer are stacked along the thickness direction of the load-bearing fabric layer; and braided yarns, the braided yarns are woven between the warp yarn layer and the weft yarn layer.

[0012] The gas barrier film is laminated and compounded on the outer surface of the load-bearing fabric layer.

[0013] Wherein, the braided yarn comprises thermoplastic yarn, and the braided yarn comprises polyurethane yarn and / or polyvinyl chloride yarn.

[0014] The yarn bundles of the warp yarn and the weft yarn are both larger than the yarn bundles of the braiding yarn, the fineness of the warp yarn and the weft yarn are both larger than the fineness of the braiding yarn, and the melting points of the warp yarn and the weft yarn are both higher than the melting point of the braiding yarn.

[0015] The gas barrier film includes a thermoplastic polyurethane film and / or a polyester film.

[0016] According to the capsule of the flexible aircraft according to the embodiment of the present invention, the capsule in the present application has the advantages of simple structure, convenient processing and low cost, and can be widely used in highly airtight, leak-proof flexible capsules or flexible composite material structures.

[0017] That is, based on the load-bearing fabric layer of the biaxial warp knitting structure, low-cost load-bearing fibers can be used to obtain high-performance load-bearing fabrics, and thick, low-cost thermoplastic polyurethane films and / or polyester films can be used as gas barrier films for the capsule material to improve the gas barrier properties of the capsule material. By using thermoplastic fibers as weaving yarns, the problem of air leakage in the joints during the welding process of the capsule material can also be solved, and the air tightness of the flexible aircraft capsule can be improved, which has significant economic value and technical benefits. The above innovative points are interdependent and inseparable, and together constitute a low-cost, high-performance flexible aircraft capsule material of the present invention, which solves the demand for low-cost high-performance capsule materials.

[0018] Due to the use of a load-bearing fabric layer with high specific strength, under the same material surface density requirements, the gas barrier film can use a thicker thermoplastic polyurethane film or polyester film with better barrier properties, thereby obtaining a flexible aircraft capsule with better airtightness.

[0019] In some specific embodiments, the warp yarns and the weft yarns independently include at least one of ultra-high molecular weight polyethylene fibers, polyester fibers, and nylon fibers.

[0020] In some specific embodiments, a polyurethane adhesive or a polyester adhesive is coated between the gas barrier film and the load-bearing fabric layer, and the gas barrier film is compositely connected to the load-bearing fabric layer by lamination.

[0021] In some specific embodiments, the gas barrier film is a thermoplastic polyurethane film, and the thermoplastic polyurethane film is formed on the outer surface of the load-bearing fabric layer by coating.

[0022] Optionally, the weaving yarn includes a plurality of yarn knots and weaving threads connected between two adjacent yarn knots, a yarn knot is arranged between each two adjacent warp yarns and the intersecting two adjacent weft yarns, and at the intersection of each warp yarn and each weft yarn, a weaving thread is connected between two yarn knots located at a diagonal position, and another weaving thread is connected between two yarn knots located at another diagonal position, and the two weaving threads clamp the warp yarn and the weft yarn located at the intersection.

[0023] According to the second embodiment of the present invention, a method for splicing a flexible aircraft capsule includes the following steps:

[0024] After the two pieces of the capsule are butt-jointed, a welding tape is used to weld the two pieces at the joint seams to connect the two pieces;

[0025] Wherein, the cut piece is a component of the capsule body, and the cut piece includes a load-bearing fabric layer and a gas barrier film;

[0026] The load-bearing fabric layer is a biaxial warp knitted layer, and comprises:

[0027] Warp yarns, a plurality of the warp yarns are laid flat to form a warp yarn layer;

[0028] Weft yarns, a plurality of the weft yarns are laid flat to form a weft yarn layer, the weft yarns are perpendicular to the warp yarns, and the warp yarn layer and the weft yarn layer are stacked along the thickness direction of the load-bearing fabric layer;

[0029] a braiding yarn woven between the warp yarn layer and the weft yarn layer;

[0030] The gas barrier film is laminated and compounded on the outer surface of the load-bearing fabric layer;

[0031] wherein the braided yarn comprises thermoplastic yarn, and the braided yarn comprises polyurethane yarn and / or polyvinyl chloride yarn;

[0032] The yarn bundles of the warp yarn and the weft yarn are larger than the yarn bundles of the braiding yarn, the fineness of the warp yarn and the weft yarn are larger than the fineness of the braiding yarn, and the melting points of the warp yarn and the weft yarn are higher than the melting point of the braiding yarn;

[0033] The gas barrier film is a thermoplastic polyurethane film or a polyester film;

[0034] The structure of the welding belt is the same as that of the cutting piece, and the welding belt is located on the inner surface of the cutting piece, the load-bearing fabric layer of the welding belt is in contact with the load-bearing fabric layer of the cutting piece, the welding belt and the woven yarn on the cutting piece are hot-melted to form an adhesive film, and a part of the adhesive film is filled in the fabric gaps of the load-bearing fabric layer.

[0035] Optionally, the welding strip is connected to the cut piece by hot pressing welding or high frequency welding.

[0036] Optionally, a hot melt adhesive film is provided between the welding belt and the cut piece.

[0037] Furthermore, vertical projections of the hot-melt adhesive film and the welding belt on the cut piece overlap, and the thickness of the hot-melt adhesive film ranges from 0.01 mm to 0.1 mm.

[0038] The bladder of the flexible aircraft according to the embodiment of the third aspect of the invention is manufactured by using the splicing method of the bladder of the flexible aircraft according to the above embodiment of the invention.

[0039] The flexible aircraft according to the embodiment of the fourth aspect of the invention comprises the capsule of the flexible aircraft as described in the above embodiment.

[0040] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0042] Figure 1 A schematic diagram of the layer structure of a flexible aircraft capsule in the prior art;

[0043] Figure 2 A schematic diagram of the layer structure of a flexible aircraft capsule according to an embodiment of the present invention;

[0044] Figure 3 A schematic diagram of the layer structure of a biaxial warp knitted 0° / 90° weave of a load-bearing fabric layer in some embodiments;

[0045] Figure 4 A schematic diagram of the layer structure of the biaxial warp knitted ±45° weaving of the load-bearing fabric layer in some embodiments;

[0046] Figure 5 Schematic diagram of the joint seam structure of the capsule in some embodiments.

[0047] Reference numerals:

[0048] Figure 1 Middle markings: fabric layer 10', conventional warp yarn 11', conventional weft yarn 12', conventional air barrier film 30', weather-resistant film 20', heat-sealed film 40';

[0049] The remaining figures are marked:

[0050] Capsule 100,

[0051] Load-bearing fabric layer 10,

[0052] Warp yarn layer 110, warp yarn 101,

[0053] Weft yarn layer 120, weft yarn 102,

[0054] Weaving yarn 103,

[0055] Yarn knot 1031, weaving thread 1032,

[0056] Gas barrier film 20,

[0057] Adhesive film 300 , welding tape 400 , and cut piece 500 . DETAILED DESCRIPTION

[0058] 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 only used to explain the present invention, and cannot be understood as limiting the present invention.

[0059] In the description of the present invention, it is to be understood that a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0060] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" 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 it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0061] At present, there are obvious technical deficiencies in the capsule materials of high-performance flexible aircraft. On the one hand, the capsule layer structure is complex and requires high material costs. On the other hand, the capsule material has poor molding processability and insufficient air tightness.

[0062] by Figure 1 Taking the layer structure of a flexible aircraft capsule as an example, its main load-bearing fabric layer 10' is made of plain woven fabric. The fabric layer 10' is woven from conventional warp yarns 11' and conventional weft yarns 12'. The conventional warp yarns 11' and conventional weft yarns 12' are in a bent state. When bearing loads, the yarns of the conventional warp yarns 11' and conventional weft yarns 12' are first bent and then straightened. The fabric has large deformation, low strength, low elastic modulus, poor shear resistance and interlayer performance. When bearing tearing force, a single yarn is continuously stressed, and the tearing resistance is poor. The fiber strength performance in the woven fabric cannot be fully exerted.

[0063] In this example, the outer surface of the fabric layer 10' is provided with a conventional gas barrier film 30' and a weather resistant film 20' in sequence, and the inner surface of the fabric layer 10' is provided with a heat sealing film 40'. The multi-layer film structure complements the strength of the capsule and realizes the gas barrier and weather resistance of the capsule.

[0064] In order to solve the problem of insufficient bladder strength of flexible aircraft in the prior art, the present application proposes a new bladder structure to obtain a low-cost, high-performance bladder material for flexible aircraft.

[0065] The following describes a bladder 100 of a flexible aircraft according to a first embodiment of the present invention with reference to the accompanying drawings.

[0066] Reference Figure 2 The bladder 100 includes a load-bearing fabric layer 10 and a gas barrier film 20 , wherein the former is used to provide the bladder 100 with high specific strength, and the latter is used to provide the bladder 100 with gas barrier properties.

[0067] Specifically, Figure 3 and Figure 4 As shown, the load-bearing fabric layer 10 is a biaxial warp knitted layer. The load-bearing fabric layer 10 comprises: warp yarns 101 , weft yarns 102 and weaving yarns 103 , and the warp yarns 101 and weft yarns 102 are load-bearing fibers of the load-bearing fabric layer 10 .

[0068] Among them, a plurality of warp yarns 101 are laid flat to form a warp yarn layer 110, a plurality of weft yarns 102 are laid flat to form a weft yarn layer 120, the weft yarns 102 are perpendicular to the warp yarns 101, the warp yarn layer 110 and the weft yarn layer 120 are stacked along the thickness direction of the load-bearing fabric layer 10, the braiding yarn 103 is woven between the warp yarn layer 110 and the weft yarn layer 120, and the braiding yarn 103 braids the warp yarns 101 and the weft yarns 102, so that the load-bearing fabric layer 10 has anti-slip properties. In other words, the warp yarns 101 and the weft yarns 102 are not intertwined with each other, and can be stretched parallel to form two yarn sheet layers, which are stacked and combined in a flat form and tied together by the braiding yarn 103. Therefore, the capsule material using this woven fabric can maximize the body strength of the load-bearing fiber and achieve lightweight capsule material by avoiding the strength loss caused by bending of fiber weaving.

[0069] The load-bearing fabric layer 10 obtained by biaxial warp knitting overcomes the shortcomings of easy deformation and poor creep resistance of the warp yarn 101 and the weft yarn 102 in conventional weaving methods, and can provide excellent tear resistance and a stable overall structure for the bladder material. The load-bearing fabric layer 10 obtained by biaxial warp knitting effectively improves the strength utilization rate of the load-bearing fibers, and obtains a high-specific-strength, high-performance bladder material.

[0070] In the present application, the braiding yarn 103 is a thermoplastic fiber yarn. The yarn bundles of the warp yarn 101 and the weft yarn 102 are larger than the yarn bundles of the braiding yarn 103, the fineness of the warp yarn 101 and the weft yarn 102 are larger than the fineness of the braiding yarn 103, and the melting points of the warp yarn 101 and the weft yarn 102 are higher than the melting point of the braiding yarn 103.

[0071] Here, selecting the yarn bundle and fineness of the weaving yarn 103 within a lower range can reduce the mechanical strength of the weaving yarn 103 and have less impact on the overall mechanical properties of the biaxial warp knitted fabric. It mainly provides a certain strength in the thickness direction to maintain the stability of the warp yarn 101 and the weft yarn 102.

[0072] The braided yarn 103 is set as a thermoplastic yarn, so that when the pieces of the capsule 100 are spliced ​​and connected, solder can be used to weld at the splicing seam. In this way, the braided yarn 103 of the load-bearing fabric layer 10 can be quickly melted at high temperature, infiltrated and filled between the fibers and fiber bundles in the form of a fluid. The braided yarn 103 in the splicing seam area melts at high temperature to form a flowing resin, which is filled between the fibers and fiber bundles, avoiding gas leakage from the fiber gaps between the splicing seams, thereby improving the air tightness of the capsule 100 after molding.

[0073] Here, the braiding yarn 103 can be a thermoplastic polyurethane yarn, or other thermoplastic, low-melting-point yarns. Of course, the selection of other yarns also requires that the braiding yarn 103 has a lower melting point.

[0074] It should be noted that thermoplastic polyurethane is a linear block copolymer consisting of a soft segment and a hard segment. The soft segment is usually composed of a long-chain polyol (such as polyester or polyether diol), which provides elasticity and flexibility; the hard segment is generally generated by the reaction of diisocyanate and a short-chain chain extender, which gives the material strength and rigidity. This unique structure gives thermoplastic polyurethane yarn the processing properties of thermoplastics and the elasticity of rubber, so that it can melt and fill the gap, and can also achieve elastic deformation of the gap after filling, thereby improving the sealing and softness of the joints.

[0075] Furthermore, the braided yarn 103 may be other types of low-melting-point fibers produced by melt spinning, such as modified low-melting-point polyester fibers.

[0076] Reference Figure 2 The gas barrier film 20 is laminated on the outer surface of the load-bearing fabric layer 10. Since the load-bearing fabric layer 10 has obtained a high specific strength, the strength requirements of other film layers can be reduced. At this time, the gas barrier film 20 can be selected from materials with good gas barrier properties but low cost, thereby reducing the overall cost of the capsule 100. Specifically, the gas barrier film 20 is a thermoplastic polyurethane film or a polyester film. The application of this low-cost raw material in the manufacture of the capsule material significantly reduces the production cost of the high-performance capsule material.

[0077] The capsule 100 in the present application has the advantages of simple structure, convenient processing and low cost, and can be widely used in highly airtight, leak-proof flexible capsules or flexible composite material structures.

[0078] That is, based on the load-bearing fabric layer 10 of the biaxial warp knitted structure, low-cost load-bearing fibers can be used to obtain high-performance load-bearing fabrics, and thick, low-cost thermoplastic polyurethane film or polyester film can be used as the gas barrier film 20 of the capsule material to improve the gas barrier performance of the capsule material. By using thermoplastic fibers as the weaving yarn 103, the problem of air leakage in the joints during the welding process of the capsule material can also be solved, and the air tightness of the flexible aircraft capsule can be improved, which has significant economic value and technical benefits. The above innovative points are interdependent and inseparable, and together constitute a low-cost and high-performance flexible aircraft capsule material of the present invention, which solves the demand for low-cost high-performance capsule materials.

[0079] Due to the use of a load-bearing fabric layer 10 with high specific strength, under the same material surface density requirements, the gas barrier film 20 can use a thicker thermoplastic polyurethane film or polyester film with better barrier properties, thereby obtaining a flexible aircraft capsule 100 with better air tightness.

[0080] In some specific embodiments, the warp yarn 101 is made of ultra-high molecular weight polyethylene fiber, and the weft yarn 102 is made of ultra-high molecular weight polyethylene fiber.

[0081] Specifically, ultrahigh molecular weight polyethylene fiber (UHMWPE fiber for short) is a synthetic fiber spun from polyethylene with a molecular weight of 1 million to 5 million. It is a high-performance fiber with many excellent properties.

[0082] Ultra-high molecular weight polyethylene fiber has high strength and high modulus. The strength of some ultra-high molecular weight polyethylene fibers is 15 times that of high-quality steel, 4 times that of glass and nylon materials, 2.6 times that of carbon fiber, and 1.7 times that of aramid fiber. It can be said that the specific strength of ultra-high molecular weight polyethylene fiber is at a high level among chemical fiber materials, and its specific modulus is second only to special-grade carbon fiber. It can play an important role in scenarios with extremely high requirements for material strength and stiffness.

[0083] The density of ultra-high molecular weight polyethylene fiber is low, and some ultra-high molecular weight polyethylene fiber has a density of only 0.97 grams per cubic centimeter. It is a fiber with a density of less than 1 among high-performance fibers and can float on the water. This makes the products made of it have high performance and light weight.

[0084] Ultra-high molecular weight polyethylene fiber has good impact resistance. When impacted, the fiber can disperse and dissipate the impact energy through its own deformation and energy absorption mechanism, thereby protecting the protected object. Its impact resistance can reach 3.6 times that of aramid armor structure.

[0085] Ultra-high molecular weight polyethylene fiber has strong wear resistance and corrosion resistance, and can maintain good surface condition and performance during long-term use. At the same time, it has strong chemical corrosion resistance and can remain stable in harsh chemical environments and seawater environments, and is not prone to chemical reactions such as rust or hydrolysis.

[0086] Ultra-high molecular weight polyethylene fiber is resistant to low temperatures and can still maintain good flexibility and mechanical properties in low temperature environments.

[0087] Ultra-high molecular weight polyethylene fiber has good light resistance. After being exposed to sunlight for 1500 hours, its strength can still be maintained at more than 80%. It can be used in outdoor environments for a long time with stable performance.

[0088] In other specific embodiments, without changing the weaving method of the load-bearing fabric layer 10, other fibers such as polyester fibers and nylon fibers may be used instead of ultra-high molecular weight polyethylene fibers as the warp yarns 101 and the weft yarns 102 to achieve similar or similar performance.

[0089] In some specific embodiments, according to the configuration of the capsule 100 of the flexible aircraft, the density of the warp yarn 101 and the weft yarn 102 can be designed as required.

[0090] For example, for a spherical capsule 100 , the density ratio of the warp yarn 101 to the weft yarn 102 can be selected as 1:1. For example, for an ellipsoidal or cylindrical capsule 100 , the density ratio of the warp yarn 101 to the weft yarn 102 can be selected as 1:2.

[0091] In some specific embodiments, polyurethane adhesive or polyester adhesive is coated between the gas barrier film 20 and the load-bearing fabric layer 10 , and the gas barrier film 20 is compositely connected to the load-bearing fabric layer 10 by lamination.

[0092] Here, the lamination connection between the gas barrier membrane 20 and the load-bearing fabric layer 10 has many advantages. First, through the lamination process, different membrane layers can be tightly combined to form a whole, and the connection strength between the membranes is greatly improved, which can effectively resist the pulling and squeezing of external forces, and ensure the stability of the membrane structure under various use environments. Lamination can make the stress evenly distributed on the connection interface to avoid damage to the connection parts caused by local stress concentration. The membrane lamination connection can make the fit between the membrane layers very high, thus forming a flat and smooth surface. The laminated membrane structure can form a good seal to isolate the internal membrane layer from erosion by external environmental factors such as air, moisture, and dust.

[0093] In some other specific embodiments, the gas barrier film 20 is a thermoplastic polyurethane film, which is formed on the outer surface of the load-bearing fabric layer 10 by coating.

[0094] It is understandable that the film connection formed by coating and pressing can make the gas barrier film 20 and the load-bearing fabric layer 10 fit tightly together. During the coating and pressing process, the coating or adhesive can fill the microscopic pores and uneven surfaces under pressure, so that the gas barrier film 20 and the load-bearing fabric layer 10 are tightly combined, reducing the air gap and enhancing the connection effect. For objects with complex shapes, the coating and pressing process can be well adapted. Whether it is a curved surface or a part with an irregular shape, as long as the fluidity of the coating or adhesive and the coating and pressing method are properly selected, a uniform film connection can be achieved. During the coating and pressing process, the coating or adhesive can penetrate into the surface structure of the connected material to form a mechanical interlock. When the coating is cured, this interlocking structure can greatly enhance the connection strength between the film layer and the substrate. Compared with some other film layer connection methods, the coatings and adhesives used in coating and pressing are usually lower in cost.

[0095] In some optional embodiments, the gas barrier film 20 may be a thermoplastic polyurethane film or a polyester film with a thickness of 0.05 mm to 0.2 mm, which has good barrier properties against conventional buoyant gases such as helium and hydrogen.

[0096] In some embodiments, Figure 3 and Figure 4 As shown, the load-bearing fabric layer 10 is a biaxial warp knitted fabric, and the warp yarn 101 and the weft yarn 102 are laid at angles such as 0° / 90° or ±45°. According to the special tear resistance and impact resistance design requirements of the bladder material, the warp yarn 101 and the weft yarn 102 can also be laid at other angles.

[0097] In some specific embodiments, Figure 3 As shown, the load-bearing fabric layer 10 is woven by biaxial warp knitting 0° / 90°. The woven yarn 103 includes a plurality of yarn knots 1031 and weaving threads 1032 connected between two adjacent yarn knots 1031. A yarn knot 1031 is arranged between each two adjacent warp yarns 101 and the intersecting two adjacent weft yarns 102. At the intersection of each warp yarn 101 and each weft yarn 102, a weaving thread 1032 is connected between two yarn knots 1031 at a diagonal position, and another weaving thread 1032 is connected between two yarn knots 1031 at another diagonal position. The weaving threads 1032 at two locations clamp the warp yarn 101 and the weft yarn 102 at the intersection. In this way, each intersection of the warp yarn 101 and the weft yarn 102 has four yarn knots 1031 at four corners, which are clamped by the weaving threads 1032 on both sides in the thickness direction, and the stability is very strong.

[0098] In other specific embodiments, Figure 4 As shown, the load-bearing fabric layer 10 is biaxially warp knitted at ±45°. No yarn knots 1031 are formed on the knitting yarns 103, but each intersection of the warp yarns 101 and the weft yarns 102 is clamped by two knitting yarns 103 on both sides, which is also very stable.

[0099] The following describes a method for splicing a capsule 100 of a flexible aircraft according to a second embodiment of the present invention with reference to the accompanying drawings.

[0100] Specifically, the splicing of the bladder body 100 includes the following steps: after the two cut pieces 500 of the bladder body 100 are butt-jointed, a welding tape 400 is used to weld the two cut pieces 500 at the splicing seam to connect the two cut pieces 500 .

[0101] The cut piece 500 is a component of the bladder body 100 , and the cut piece 500 includes a load-bearing fabric layer 10 and a gas barrier film 20 .

[0102] The load-bearing fabric layer 10 is a biaxial warp knitted layer. The load-bearing fabric layer 10 includes: warp yarn 101, weft yarn 102 and braiding yarn 103. The warp yarn 101 and weft yarn 102 are the load-bearing fibers of the load-bearing fabric layer 10. Among them, multiple warp yarns 101 are laid flat to form a warp yarn layer 110, and multiple weft yarns 102 are laid flat to form a weft yarn layer 120. The weft yarn 102 is perpendicular to the warp yarn 101. The warp yarn layer 110 and the weft yarn layer 120 are stacked along the thickness direction of the load-bearing fabric layer 10. The braiding yarn 103 is woven between the warp yarn layer 110 and the weft yarn layer 120. The braiding yarn 103 weaves the warp yarn 101 and the weft yarn 102, so that the load-bearing fabric layer 10 has anti-slip properties. The gas barrier film 20 is laminated on the outer surface of the load-bearing fabric layer 10.

[0103] Among them, the yarn bundles of the warp yarn 101 and the weft yarn 102 are larger than the yarn bundles of the weaving yarn 103, the fineness of the warp yarn 101 and the weft yarn 102 is larger than the fineness of the weaving yarn 103, and the melting points of the warp yarn 101 and the weft yarn 102 are higher than the melting point of the weaving yarn 103.

[0104] The gas barrier film 20 is a thermoplastic polyurethane film or a polyester film.

[0105] The structure of the welding tape 400 is the same as that of the cutting piece 500 , and the welding tape 400 is located on the inner surface of the cutting piece 500 , the load-bearing fabric layer 10 of the welding tape 400 is in contact with the load-bearing fabric layer 10 of the cutting piece 500 , and the woven yarn 103 on the welding tape 400 and the cutting piece 500 is hot-melted to form an adhesive film 300 .

[0106] In some optional embodiments, the yarn bundle of the braided yarn 103 ranges from 12K to 24K, the fineness ranges from 50D to 400D, and the braided yarn 103 is a thermoplastic fiber with a melting point of 100°C to 130°C.

[0107] That is to say, the structure of the flexible aircraft bladder 100 obtained in the second embodiment is substantially the same as that of the flexible aircraft bladder 100 obtained in the first embodiment. The difference is that in the second embodiment, it is further defined that a welding belt 400 having the same structure as the cut piece 500 of the bladder 100 is used and welded at the joint seam of the cut piece 500.

[0108] In this way, when the bladder 100 splices and connects the cut pieces 500, the braided yarns 103 on the cut pieces 500 and the welding belt 400 can melt. That is, the braided yarns 103 of the load-bearing fabric layers 10 on the cut pieces 500 and the welding belt 400 can melt quickly at high temperatures, infiltrate and fill between the fibers and fiber bundles in the form of fluid. The braided yarns 103 in the splicing seam area melt at high temperatures to form a flowing resin, which fills between the fibers and fiber bundles, avoiding gas leakage from the fiber gaps between the splicing seams, thereby improving the air tightness of the bladder 100 after molding.

[0109] The capsule 100 obtained by this processing method can not only double fill and seal the gap at the joint seam, but also use the material of the capsule 100 itself as the welding belt 400, which can effectively control the processing cost.

[0110] Specifically, the bladder material is used as the welding belt 400, which is used for welding the cut pieces 500 of the bladder material. After welding, the load-bearing fabric layer 10 of the cut pieces 500 is brought into contact and welded with the load-bearing fabric layer 10 of the welding belt 400. Here, the gas barrier film 20 of the cut pieces 500 is located on the outer surface of the final product of the bladder 100, and the gas barrier film 20 of the welding belt 400 is located on the inner surface of the final product of the bladder 100.

[0111] In some specific embodiments, the welding tape 400 is connected to the cut piece 500 by heat-compression welding.

[0112] It can be understood that hot press welding is to diffuse and fuse the molecules on the surfaces of the materials to be connected by heating and pressurizing. In this process, the interface of the materials gradually disappears, forming a continuous whole. This molecular-level bonding makes the connection strength very high, able to withstand large external forces such as tension and pressure, and effectively avoid separation of the connection parts. Hot press welding can form a very tight connection, effectively preventing the leakage of gas and liquid.

[0113] From a microscopic perspective, hot press welding can fill tiny pores and gaps on the surface of materials. When the materials soften due to heat and squeeze each other under pressure, these microscopic unevenness are filled to form a seamless connection. It can prevent tiny particles such as dust and moisture from entering the interior of the component, improving the reliability and service life of the product.

[0114] In some specific embodiments, the welding tape 400 is connected to the cut piece 500 by high frequency welding.

[0115] It is understandable that high-frequency welding uses a high-frequency generator to generate a high-frequency electric field. Under the action of the high-frequency electric field, the molecules of the woven yarn 103 material on the welding belt 400 and the cut piece 500 generate high-frequency vibrations. The molecules of the woven yarn 103 material generate intense friction and movement due to the high-frequency vibrations and quickly heat up and transform from a solid state to a molten state of the adhesive film 300. Under the action of external pressure, the two layers of adhesive film 300 are tightly bonded together, thereby achieving rapid welding of the materials. This method can complete the connection process in a very short time, usually only a few seconds or even shorter. Since high-frequency welding is fast and can be precisely controlled by automated equipment, it is very suitable for large-scale, high-efficiency industrial production.

[0116] High-frequency welding is based on heating and fusion at the molecular level of materials. Under the action of the high-frequency electric field, the material molecules obtain enough energy, diffuse and interweave with each other, so that the molecular structure of the connection part is tightly combined. This close combination between molecules makes the connection strength of the welded material high and can withstand greater tension, pressure and shear force. The high-frequency electric field can act evenly on the surface and inside of the material to be welded, so that the whole material is heated evenly, thereby achieving a uniform welding effect.

[0117] In summary, under the action of the high-temperature mold, the woven yarn 103 in the load-bearing fabric layer 10 in the welding band 400 area melts quickly to form an adhesive film 300 to connect the welding band 400 and the cut piece 500, and the molten adhesive simultaneously fills the fabric gaps in the welding area.

[0118] In some embodiments, a hot melt adhesive film is disposed between the welding tape 400 and the cutting piece 500 .

[0119] Specifically, the hot melt adhesive film will melt after being heated, filling the tiny gap between the cut piece 500 and the welding strip 400, and will form a very strong bond after being cooled and solidified. This bonding force can effectively resist the pulling, shearing and peeling of external forces, ensuring that the cut piece 500 and the welding strip 400 are tightly connected.

[0120] After being heated and melted, the hot melt adhesive film will be evenly spread on the contact surface between the cut piece 500 and the welding belt 400, and there will be no situation where the local bonding is too strong or too weak. This makes the bonding quality between the cut piece 500 and the welding belt 400 more stable and reliable.

[0121] In some embodiments, the vertical projections of the hot melt adhesive film and the welding tape 400 on the cut piece 500 overlap, that is, the coverage area of ​​the hot melt adhesive film and the welding tape 400 on the cut piece 500 overlaps. This can reduce adhesive omissions and improve connection reliability.

[0122] Specifically, the thickness of the hot melt adhesive film is in the range of 0.01 mm to 0.1 mm, so as to avoid the adhesive film being too thick and affecting the flow of the braided yarn 103 solution.

[0123] The bladder 100 of the flexible aircraft according to the third embodiment of the present invention is manufactured by using the splicing method of the bladder 100 of the flexible aircraft according to the second embodiment.

[0124] The flexible aircraft according to the embodiment of the third aspect of the present invention comprises the capsule 100 of the flexible aircraft described in all the above embodiments.

[0125] The embodiments of the present application are described in detail below. It should be noted that the embodiments described below are exemplary and are only used to explain the present application, and should not be construed as limiting the present application. In addition, unless otherwise explicitly stated, all reagents used in the following embodiments are commercially available or can be synthesized according to this article or known methods, and the reaction conditions not listed are also easily available to those skilled in the art.

[0126] Example 1

[0127] This embodiment provides a capsule 100 , which includes a load-bearing fabric layer 10 and a gas barrier film 20 . The load-bearing fabric layer 10 is a biaxial warp knitted layer, and includes warp yarns 101 , weft yarns 102 and braiding yarns 103 .

[0128] The material and parameter selection of the warp yarn 101 are: ultra-high molecular weight polyethylene fiber, fineness 400D, 8 yarns / cm.

[0129] The material and parameter selection of the weft yarn 102 are: ultra-high molecular weight polyethylene fiber, fineness 400D, 8 yarns / cm.

[0130] The material and parameter selection of the braiding yarn 103: thermoplastic polyurethane yarn, melting point 100°C to 120°C.

[0131] The material and parameter selection of the gas barrier film 20 are: polyester film, helium permeability <0.1 L / m2·24h·atm.

[0132] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 995 kN·m / kg, helium permeability <0.1 L / m2·24h·atm.

[0133] Example 2

[0134] This embodiment provides a capsule 100. The structure of this embodiment is basically the same as that of the capsule 100 in Embodiment 1, except that:

[0135] The fineness of warp yarn 101 is 200D, 16 yarns / cm;

[0136] The fineness of the weft yarn 102 is 200D, 16 yarns / cm;

[0137] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 990 kN·m / kg, helium permeability <0.1 L / m2·24h·atm.

[0138] Example 3

[0139] This embodiment provides a capsule 100. The structure of this embodiment is basically the same as that of the capsule 100 in Embodiment 1, except that:

[0140] Warp yarn 101, fineness 100D, 35 yarns / cm;

[0141] Weft yarn 102, fineness 100D, 35 yarns / cm;

[0142] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 992 kN·m / kg, helium permeability <0.1 L / m2·24h·atm.

[0143] Example 4

[0144] This embodiment provides a capsule 100. The structure of this embodiment is basically the same as that of the capsule 100 in Embodiment 1, except that:

[0145] The material and parameter selection of the warp yarn 101 are: nylon fiber, fineness 300D, 15 yarns / cm;

[0146] The material and parameter selection of the weft yarn 102 are: nylon fiber, fineness 300D, 15 yarns / cm;

[0147] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 150 kN·m / kg, helium permeability <0.1 L / m2·24h·atm.

[0148] Example 5

[0149] This embodiment provides a capsule 100. The structure of this embodiment is basically the same as that of the capsule 100 in Embodiment 1, except that:

[0150] The material and parameter selection of the warp yarn 101: polyester fiber, fineness 300D, 15 yarns / cm;

[0151] The material and parameter selection of the weft yarn 102: polyester fiber, fineness 300D, 15 yarns / cm;

[0152] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 175 kN·m / kg, helium permeability <0.1 L / m2·24h·atm.

[0153] Example 6

[0154] This embodiment provides a capsule 100. The structure of this embodiment is basically the same as that of the capsule 100 in Embodiment 1, except that:

[0155] The material and parameter selection of the gas barrier film 20: thermoplastic polyurethane film, helium permeability <2.5L / m2·24h·atm;

[0156] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 983 kN·m / kg, helium permeability <2.5 L / m2·24h·atm.

[0157] Example 7

[0158] This embodiment provides a capsule 100. The structure of this embodiment is basically the same as that of the capsule 100 in Embodiment 1, except that:

[0159] The material and parameter selection of the warp yarn 101 are: nylon fiber, fineness 300D, 15 yarns / cm;

[0160] The material and parameter selection of the weft yarn 102 are: nylon fiber, fineness 300D, 15 yarns / cm;

[0161] Material and parameter selection of gas barrier film 20: thermoplastic polyurethane film, helium permeability <2.5L / m2·24h·atm

[0162] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 135 kN·m / kg, helium permeability <2.5 L / m2·24h·atm.

[0163] Example 8

[0164] This embodiment provides a capsule 100. The structure of this embodiment is basically the same as that of the capsule 100 in Embodiment 1, except that:

[0165] The material and parameter selection of the warp yarn 101: polyester fiber, fineness 300D, 15 yarns / cm;

[0166] The material and parameter selection of the weft yarn 102: polyester fiber, fineness 300D, 15 yarns / cm;

[0167] Material and parameter selection of gas barrier film 20: thermoplastic polyurethane film, helium permeability <2.5L / m2·24h·atm

[0168] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 160 kN·m / kg, helium permeability <2.5 L / m2·24h·atm.

[0169] Example 9

[0170] This embodiment provides a capsule 100. The structure of this embodiment is basically the same as that of the capsule 100 in Embodiment 1, except that:

[0171] The material and parameter selection of the warp yarn 101: ultra-high molecular weight polyethylene fiber, fineness 400D, 10 yarns / cm;

[0172] The material and parameter selection of the weft yarn 102: ultra-high molecular weight polyethylene fiber, fineness 400D, 8 yarns / cm;

[0173] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 995 kN·m / kg, helium permeability <0.1 L / m2·24h·atm.

[0174] Example 10

[0175] This embodiment provides a capsule 100. The structure of this embodiment is basically the same as that of the capsule 100 in Embodiment 1, except that:

[0176] The material and parameter selection of the warp yarn 101: ultra-high molecular weight polyethylene fiber, fineness 400D, 10 yarns / cm;

[0177] The material and parameter selection of the weft yarn 102: ultra-high molecular weight polyethylene fiber, fineness 400D, 8 yarns / cm;

[0178] The material and parameter selection of the gas barrier film 20: thermoplastic polyurethane film, helium permeability <2.5L / m2·24h·atm;

[0179] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 983 kN·m / kg, helium permeability <2.5 L / m2·24h·atm.

[0180] Comparative Example 1

[0181] This comparative example provides a capsule 100, which has a substantially similar structure to the capsule 100 of Example 1, except that:

[0182] The load-bearing fabric layer is a plain weave fabric layer, with 10 warp yarns / cm and 10 weft yarns / cm;

[0183] The material and parameter selection of the gas barrier film 20: polyester film, helium permeability <4.5L / m2·24h·atm;

[0184] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 870 kN·m / kg, helium permeability <4.5 L / m2·24h·atm.

[0185] Comparative Example 2

[0186] This comparative example provides a capsule 100, which has a substantially similar structure to the capsule 100 of Example 1, except that:

[0187] The material and parameter selection of the warp yarn 101 are: nylon fiber, fineness 300D, 15 yarns / cm;

[0188] The material and parameter selection of the weft yarn 102 are: nylon fiber, fineness 300D, 15 yarns / cm;

[0189] The load-bearing fabric layer is a plain woven fabric layer;

[0190] The material and parameter selection of the gas barrier film 20: polyester film, helium permeability <4.5L / m2·24h·atm;

[0191] The performance parameter characteristics of the capsule 100 obtained in this way are: specific strength 100 kN·m / kg, helium permeability <4.5 L / m2·24h·atm.

[0192] The specific strength and helium permeability tests were performed on the capsules 100 of Examples 1-10 and Comparative Examples 1-2, respectively. The results are shown in Table 1.

[0193] Table 1

[0194]

[0195]

[0196] It can be seen from Table 1 that compared with comparative example 1, example 1 of the present invention has higher specific strength and lower helium permeability; the specific strength of examples 1, 9 and 10 in which the load-bearing layer fabric of the high molecular polyethylene fiber is biaxial warp knitted is higher than that of the plain weave fabric; the capsule material using high barrier polyester film as the barrier layer has low helium permeability and good barrier performance.

[0197] Compared with Comparative Example 2, Example 4 of the present invention has higher specific strength and lower helium permeability; the specific strength of Example 4 and Example 7 in which the bearing layer fabric of nylon fiber is biaxial warp knitted is higher than that of plain fabric; the bladder material using high barrier polyester film as the barrier layer has low helium permeability and good barrier performance.

[0198] In the description of this specification, the description with reference to the terms "embodiment", "example", 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 representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0199] Although the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. A capsule of a flexible aircraft, characterized in that: The capsule comprises a load-bearing fabric layer and a gas barrier film; The load-bearing fabric layer is a biaxial warp knitted layer, and comprises: Warp yarns, a plurality of the warp yarns are laid flat to form a warp yarn layer; Weft yarns, a plurality of the weft yarns are laid flat to form a weft yarn layer, the weft yarns are perpendicular to the warp yarns, and the warp yarn layer and the weft yarn layer are stacked along the thickness direction of the load-bearing fabric layer; a braiding yarn woven between the warp yarn layer and the weft yarn layer; The gas barrier film is laminated and compounded on the outer surface of the load-bearing fabric layer; wherein the braided yarn comprises thermoplastic yarn, and the braided yarn comprises polyurethane yarn and / or polyvinyl chloride yarn; The yarn bundles of the warp yarn and the weft yarn are larger than the yarn bundles of the braiding yarn, the fineness of the warp yarn and the weft yarn are larger than the fineness of the braiding yarn, and the melting points of the warp yarn and the weft yarn are higher than the melting point of the braiding yarn; The gas barrier film includes a thermoplastic polyurethane film and / or a polyester film.

2. The capsule of the flexible aircraft according to claim 1, characterized in that: The warp yarns and the weft yarns independently include at least one of ultra-high molecular weight polyethylene fibers, polyester fibers, and nylon fibers.

3. The capsule of the flexible aircraft according to claim 1, characterized in that: The weaving yarn includes a plurality of yarn knots and weaving threads connected between two adjacent yarn knots, wherein a yarn knot is arranged between each two adjacent warp yarns and the intersecting two adjacent weft yarns, and at the intersection of each warp yarn and each weft yarn, a weaving thread is connected between two yarn knots located at a diagonal position, and another weaving thread is connected between two yarn knots located at another diagonal position, and the weaving threads at two locations clamp the warp yarn and the weft yarn located at the intersection.

4. The capsule of the flexible aircraft according to claim 1, characterized in that: A polyurethane adhesive or a polyester adhesive is coated between the gas barrier film and the load-bearing fabric layer, and the gas barrier film is compositely connected with the load-bearing fabric layer by lamination; Alternatively, the gas barrier film is a thermoplastic polyurethane film, and the thermoplastic polyurethane film is formed on the outer surface of the load-bearing fabric layer by coating.

5. A method for splicing a capsule of a flexible aircraft, characterized in that: The steps include: After the two pieces of the capsule are butt-jointed, a welding tape is used to weld the two pieces at the joint seams to connect the two pieces; Wherein, the cut piece is a component of the capsule body, and the cut piece includes a load-bearing fabric layer and a gas barrier film; The load-bearing fabric layer is a biaxial warp knitted layer, and comprises: Warp yarns, a plurality of the warp yarns are laid flat to form a warp yarn layer; Weft yarns, a plurality of the weft yarns are laid flat to form a weft yarn layer, the weft yarns are perpendicular to the warp yarns, and the warp yarn layer and the weft yarn layer are stacked along the thickness direction of the load-bearing fabric layer; a braiding yarn woven between the warp yarn layer and the weft yarn layer; The gas barrier film is laminated and compounded on the outer surface of the load-bearing fabric layer; wherein the braided yarn comprises thermoplastic yarn, and the braided yarn comprises polyurethane yarn and / or polyvinyl chloride yarn; The yarn bundles of the warp yarn and the weft yarn are larger than the yarn bundles of the braiding yarn, the fineness of the warp yarn and the weft yarn are larger than the fineness of the braiding yarn, and the melting points of the warp yarn and the weft yarn are higher than the melting point of the braiding yarn; The gas barrier film comprises a thermoplastic polyurethane film and / or a polyester film; The structure of the welding belt is the same as that of the cutting piece, and the welding belt is located on the inner surface of the cutting piece. The load-bearing fabric layer of the welding belt is in contact with the load-bearing fabric layer of the cutting piece. The welding belt and the woven yarn on the cutting piece form an adhesive film through hot melting, and a part of the adhesive film is filled in the fabric gaps of the load-bearing fabric layer.

6. The method for splicing the capsule of a flexible aircraft according to claim 5, characterized in that: The welding belt is connected to the cut piece by hot pressing welding or high frequency welding.

7. The method for splicing a capsule of a flexible aircraft according to claim 5, characterized in that: A hot melt adhesive film is provided between the welding belt and the cutting piece.

8. The method for splicing the capsule of a flexible aircraft according to claim 7, characterized in that: The vertical projections of the hot melt adhesive film and the welding belt on the cut piece overlap, and the thickness of the hot melt adhesive film ranges from 0.01 mm to 0.1 mm.

9. A capsule of a flexible aircraft, characterized in that: The flexible aircraft is manufactured by the splicing method of the capsule of any one of claims 5-8.

10. A flexible aircraft, characterized in that: A bladder comprising the flexible flying machine according to any one of claims 1 to 4, or a bladder comprising the flexible flying machine according to claim 9.

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