DK179553B1 - A lighter-than-air vehicle with a hull, a laminate for such hull and a method of production of such laminate - Google Patents

Abstract

A lighter-than-air vehicle comprising a hull of a laminate material with a reinforcing fibre layer, for example Zylon®, and a first, and optionally second, Ethylene Vinyl Alcohol film melt-bonded into the fibre layer. A weathering layer protects the fibres against UV degradation.

Description

Weathering Layer

Adhesive + Gas Barrier Layer Load Bearing Layers (FR)

Adhesive + Gas Barrier Layer

Primary Gas Barrier Layer

A lighter-than-air vehicle with a hull, a laminate for such hull and a method of production of such laminate

FIELD OF THE INVENTION

The present invention relates to a lighter-than-air vehicle with a hull, a laminate for such hull and a method of production of such laminate. Especially, it relates to a multi-functional laminate with a reinforcing fibre layer and a gas barrier film.

BACKGROUND OF THE INVENTION

Lighter-than-air vehicles have a flexible hull that is filled with a gas, typically Helium. In case that the vehicle does not have an internal structural framework, it is also called a blimp, where the shape of the airship, typically elongate shape, is maintained by internal pressure. The hull has to be made of a laminate that is stable enough to not burst and which also functions as a gas barrier, typically for Helium, He, inside the hull.

Hull material for high-altitude lighter-than-air vehicles is subject to a number of requirements. It must be light-weight while at the same time provide mechanical stability. It has to chemically resist the aggressive atmosphere at high altitude, especially the ozone content in the air. It must also be UV resistant and be stable and flexible at high and low temperature. Although, materials are known for each of these requirements, the combination thereof implies a severe challenge for the development of hull materials.

US patent No. 7,354,636 by Lavan et al, assigned to Lockheed Martin Corporation, discloses a laminate with a liquid crystal polymer fibre layer, for example Vectran®, a polyimide (PI) layer secured to the liquid crystal polymer fibre layer; and a polyvinylidene fluoride (PVDF) layer secured to the PI layer. The layers are secured to one another with a polyurethane (PU) adhesive. Adjacent laminates may be secured to one another by a PVDF cover tape on the exterior surfaces and a structural tape on the interior surfaces. The structural tape includes a liquid crystal polymer fibre layer and a PI layer to ensure the integrity of the vehicle. An alternative material may include a liquid crystal polymer fibre layer and a PVDF layer disposed on both sides of the liquid crystal polymer fibre layer. The weight is around 5 ounces per square yard (170 grams /square meter). The tensile strength is around 240 lbs per inch, corresponding to 420 N/cm.

Seeing that the payload capacity is directly related to the weight of the hull, it would be desirable to reduce the weight while keeping or even increasing the strength.

A better weight to strength ratio is found in the article “Tear propagation of a Highperformance Airship Envelope Material” published by Maekawa and Yoshino in Journal of Aircraft Vol. 45, No. 5, Sept-Oct. 2008. The disclosed material had a weight of 157 g/m² and a tensile strength of 997 N/cm. The laminate comprises Zylon® fibres for its base fabric. Zylon® is a trademark name of Toyobo Corporation for rigid-rod lyotropic liquid crystal polymer. In more detail, it is a thermoset liquidcrystalline polyoxazole, poly(p-phenylene-2,6-benzobisoxazole), also called PBO.

Zylon® (PBO) has a high specific strength as compared to other commercially available high performance fibres. Zylon® yarns also have high resistance to creep elongation and are therefore useful for fibre reinforcement (FR) in the laminate material. However, PBO is also known to be very susceptible to photo-degradation not only by UV but also by visible light. The presence of moisture and oxygen has been found to accelerate the photo-degradation. For these reasons, despite the apparent advantages in terms of high strength and low creep, other challenges go along with this fibre material when used for stratospheric airships.

Another hull material is disclosed in US patents US6074722 by Cuccias et al. assigned to Lockheed Martin, wherein the laminate is made of a fibrous layer laminated to plastic resin material. The fibrous layer is either a woven material or a multilayer of unidirectional filamentary material. Laminates with woven fabrics for airships are also disclosed in US7713890 by Vogt et al. assigned to Milliken & Company. Integration of electronic components in the hull layer is disclosed in US8152093 by Liggett et al. assigned to Lockheed Martin Corporation.

Various hull materials are discussed in the article “Material challenges for LighterThan-Air Systems in High Altitude Applications” by Zhai and Euler, published by the American Institute of Aeronautics and Astronautics at the AIAA 5^lh Aviation, Technology, Integration, and Operations Conference (ATIO) 26-28 Sept. 2005, Arlington California. This article discusses various materials for lighter-than-air ballonet materials, in particular materials for the gas retention layer as well as for the load-bearing woven structural layer, which takes up the load/stress. These layers are bonded to each other by an adhesive layer. Adhesive bonding is described with reference to polyurethane, epoxy and acrylic. For the gas retention layer, the article states low temperature flexibility as the most important parameter among various desirable properties, which also includes low gas permeability, minimal weight, good bondability, abrasion resistance, and ozone resistance. In table 5 of this article, ethylene vinyl alcohol copolymer (EVOH) is mentioned as having poor low temperature flexibility, indicating that EVOH is not suitable as ballonet or hull material for lighter-than-air airships at low temperatures, which are typically found at high altitudes. For this apparent reason, this article mentions instead polyolefin, polyurethane, ethylene propylene diene monomer (EPDM) rubber, and silicone rubber as the most promising polymeric materials for the gas retention layer.

Although, the article by Zhai and Euler indicates EVOH as not useful for high-altitude airships, indications are found that EVOH is useful when used in a sandwich layer together with polyurethanes, which are also regarded as promising material in the above article. Reference is made in this respect to the sales brochure of Eval Europe NV, a subsidiary of Kuraray Co. Ltd., the brochure being found on the Internet site http://eval-americas.com/media/l5453/eval%20industrial%20application.pdf. In this brochure, great flexibility and excellent gas barriers are mentioned in addition to suitability at frigid atmospheric conditions for a coextruded film structure where EVOll resin (Eval™) is sandwiched between layers of thermoplastic polyurethane (TPU), the sandwich in short described as TPU/Eval™/TPU. One of the proposed uses of this sandwich film is as material for stratospheric dirigibles. This brochure indicates that a sandwiching of EVOH between two TPU films overcomes the disadvantage of the poor low-temperature flexibility of EVOH itself. However, for a light-weight hull material, which is essential for suitable lifting capacity of airships, the sandwiching of EVOH between TPU layers disadvantageously adds weight to the hull without optimizing the strength of the final hull material.

EVOH is generally proposed as moisture barrier for packaging in US2011/0171489. For a barrier composite film for balloons, US5853862 proposes EVOH as a possible ingredient in a non-crystalline thermoplastic polymer layer coated on a base film layer, where examples for the material of the base layer includes polypropylene or polyamide. A flexible multilayer material suitable for a blimp is disclosed in US2010/0239797. The multi-layer material, for example made with 5 layers, comprises an EVOH layer and a layer of Ultra High Molecular Weight PolyEthylene (UHMWPE), for example Dyneema or Spectra fibres. For a balloon, US2009/0229I9 discloses EVOH as a barrier layer in a multilayer material with a polyester core layer,

Accordingly, it appears that an optimum solution for a hull material has not yet been found. As a conclusion, although, numerous proposals are found in the prior art for airship hulls, there is still a steady need for improvements and optimization.

DESCRIPTION / SUMMARY OF THE INVENTION

It is therefore an objective of the invention to provide an improvement in the art. It is a further objective to provide a lighter-than-air vehicle with an improved hull. Specifically, the improved laminate hull is optimized with respect to weight relatively to strength as well as minimised gas permeability. These objectives are achieved with a lighter-than-air vehicle having a hull that comprises a laminate as described in more detail in the following.

The following abbreviations are used:

ypi (yarns per inch), I inch = 2.54 cm, 1 ypi = 1/(2.54) yarns per cm tpi (twist per inch); tpm (twists per meter); 1 tpi=39 tpm gsm (grams per square meter) sqm (square meter)

UV-Vis weathering - degradation by exposure to UV radiation and/or visible light

The laminate for the hull comprises a laminate material as a gas barrier and load bearing structure, the laminate comprising a reinforcing fibre layer and a first Ethylene Vinyl Alcohol, EVOH, film melt-bonded into the fibre layer on one side of the fibre layer, wherein the EVOH is in direct contact with the reinforcing fibre layer.

The term “direct contact” implies that no layer of other material is disposed between the EVOH layer and the fibre layer. Especially, the EVOH film is not provided as part of a composite film, where the EVOH is sandwiched between two TPU layers prior to melt-bonding it to the fibre layer.

Optionally, the laminate comprises a second EVOl I film melt-bonded into the fibre layer on an opposite side of the fibre layer, wherein also the EVOH of the second EVOH film is in direct contact with the reinforcing fibre layer. In this case, the reinforcing fibre layer is sandwiched between a first and second film made of Ethylene Vinyl Alcohol, EVOH, which is melted into the fibre layer on either side.

EVOH has very low gas permeability for Helium, which is highly useful, ft is UV stable and ozone resistant. Furthermore, it is heat sealable. The prior art statement of poor low temperature flexibility was experimentally not found as a problem when used alone or when used in the laminates that were provided with EVOH as gas barrier layer.

For the hull material, a first EVOH film melt-bonded onto and at least partially into the fibre layer from one side, and optionally a second EVOH film is melt-bonded onto and at least partially into the fibre layer from the opposite side of the fibre layer. Such melt bonding is achieved by heat-pressing the layers together. As an example, a temperature in the range of 175-18CTC is useful. In the laminate as described in the following paragraphs, the EVOH film not only serves as an adhesive for bonding the layers to each other, but also acts gas barrier. Thus, it serves as a multi-functional layer.

In order to provide high strength and light weight of the fibre reinforcement (FR) layer, liquid crystal fibres is a good candidate, for example Poly [p-phenylene-2, 6benzobisoxazole], PBO. Such fibres are marketed as Zylon® fibres, as already explained in the introduction.

In order to optimize strength and/or uniformity, it is advantageous in some cases to include at least one of twisted fibres, sized fibres and fibres that are both sized and twisted. Optionally, the sized fibres assist in additional bonding between the layers, especially if the sized material is compatible with the adhesive layer. Examples of sized material are certain PVA (poly-vinyl-acetate) fibres. Another example is fibres marketed under the trade name Exceval. For example sizing of the fibres is achieved by applying the sizing material as a spin finish to the fibres.

A suitable sizing agent is polyvinyl alcohol. Such agent is commercially available, for example from the Japanese company Kuraray® Co, Ltd. A hydrophobically modified polyvinyl alcohol with the trade name Exceval™ from Kuraray® has also been used experimentally with good results. Such sizing agents based on polyvinyl alcohol are highly elastic, chemically resistant and turned out to be compatible with EVOH. It was shown experimentally that the polyvinyl alcohol strengthened Zylon® yarns. It also provided better adhesion between the fabric and the EVOH.

For example, a first set of fibres in the fibre layer, optionally liquid crystal fibres, are twisted, whereas a second set of fibres in the fibre layer, optionally liquid crystal fibres, is not twisted.

In some embodiments, the two sets of fibres are arranged in different directions. For example, a first set of the fibres oriented in a first direction are twisted and a second set of fibres oriented in a second direction are not twisted. For example, the first and the second direction have an angle between the directions of at least 30 degrees, for example 45 degrees, optionally perpendicular. Good results have been achieved with twisted fibres that comprise a twist of between 30 and 50 twists per meter.

Both balanced and unbalanced fibrous layers are potentially useful. In some embodiments, the fibres in the second set of fibres are at least two times thicker than the first set of fibres. In some embodiments, the first set of fibres has a first thread density and the second set of fibres has a second thread density that differs from the first thread density by at least a factor of two.

For a lighter-than-air vehicle, where weight is crucial, experimental results were obtained for a fibre layer with a weight of between 40 and 70 g per sqm.

For example, the thickness of the EVOH layer is between IO and 20 microns.

Advantageously, the laminate comprises a multi-functional weathering layer meltbonded to the first EVOH layer, wherein the weathering layer comprises a metallized polymer film, having a single metal layer on only one side or, alternatively, on both sides of the polymer film. In case that the weathering layer has only a single metal layer, it is advantageously oriented with the metal layer towards the EVOH and meltbonded onto the first EVOH film layer. This way, it is protected by the outwardsdirected polymer, for example polyimide, of the weathering layer. Such weathering layer has to protect the hull against the reactive Ozone and other chemical attacks as well as protect the reinforcing fibre layer against UV radiation. As discussed initially, PBO, for example Zylon® degrades very quickly in UV light. In addition, it functions as an additional gas barrier. A good candidate for the polymer in the weathering layer is polyimide, Pl. An examples of an alternative material for this purpose is polyvinyl fluoride, PVF. For example, the thickness of the weathering layer is between IO and 20 microns.

It is pointed out that the outwards-directed polymer layer also is useful for creating strong seems between adjacent laminates.

Although, EVOH is a good gas barrier, the gas tightness can be improved by adding a metallized gas barrier layer to the laminate on the inner side of the hull, which is opposite to the weathering layer. For this purpose the metallised gas barrier is optionally melt-bonded onto the second EVOH film. A candidate for the metallised polymer film layer is a polyethylene terephthalate, PET; for example a PET layer with a thickness of between 4 and 8 microns.

In experiments, it has been shown, as will also be described in greater detail below, that a gas tight and stable laminate could be made with a weight in the range between 90 and I IO gsm. For example, the tenacity-to-weight ratio for the laminate was experimentally found to above 890 kNm/kg.

In some embodiments, the fibre layer is a woven layer with a warp and a weft. For elongate blimps, the necessary strength in transverse direction of the hull is higher than in the longitudinal direction. Accordingly, the warp and weft, optionally, have filaments of different thickness and/or density. When using a non-crimp fibre layer, it is composed of a plurality of layers with unidirectional filaments, the different layers having different filament directions, for example perpendicular directions. Also in this case, the filaments in one direction are advantageously thicker and/or denser than in the second direction in order to optimise the strength without adding unnecessary weight.

It was found that both balanced and unbalanced structures were useful. Selection of balanced or unbalanced structures depends on the purpose. For example a higher strength may be desired in one direction as compared to the other. This is relevant for shape stability of the hull as well as minimization of weight, as unbalanced structures typically have a higher potential for optimized strength/weight ratios, seeing that the force on the fabric due to the elongate hull shape differs in the longitudinal the transverse direction.

As it appears from the above, the laminate includes a numerous layers, the combination of which is multi-functional. The functionality includes protection against UV radiation, visible light, ozone, singlet oxygen, and heat. The outermost layer also provides thermal management by having a low emissivity.

For ranges between a first and a second value, the forst and second values are optionally included.

SI IORT DESCRIPTION OF THE DRAWINGS

The invention will be explained in more detail with reference to the drawing, where

FIG. I illustrates a principle sketch for the laminate of the hull material;

FIG. 2 illustrates an alternative principle sketch for the laminate of the hull material;

FIG. 3 illustrates a fibre re-enforcement (FR) layer a) non-crimp 2 ply cross-ply and

b) woven; c) non-crimp 3 ply;

FIG. 4 Prototype P3, a) schematic design and b) photographs of outside and inside;

FIG. 5 Prototype P4, a) schematic design and b) photographs of outside and inside;

FIG. 6 Prototype P9, a) schematic design and b) photographs of outside and inside;

FIG. 7 Prototype PIO, a) schematic design and b) photographs of outside and inside;

FIG. 8 Comparison of the strength and weight of the new laminate prototypes and laminate materials developed in other studies;

FIG. 9 Comparison of the strength-to-weight ratio of the new laminate prototypes and laminate materials developed in other studies;

FIG. IO Comparison of tensile strength of prototypes before and after thermal exposure and accelerated UV-Vis weathering;

FIG. 11 Strength loss after thermal exposure and accelerated UV-Vis weathering;

FIG. 12 Schematic diagram of a cut-slit tear specimen;

FIG. 13 Load extension curve of prototype P4 subjected to a constant load of 1250 N;

FIG. 14 Prototype Pl2, schematic design;

FIG. 15 Prototype P13, schematic design;

FIG. 16 Prototype Pl4, schematic design;

FIG. 17 illustrates DMA measurements performed for a) EVOH film, b) Mylar film,

c) Pl film, d) the warp of prototype P4.

DETAILED DESCRIPTION I PREFERRED EMBODIMENT

In order to provide a thin and light-weight hull material laminate, which at the same time is gas tight, UV resistant, heat-resistant, and chemically resistant, especially ίο against singlet oxygen and ozone, the following basic scheme was used, which is exemplified in FIG. I. A load-bearing fibrous re-enforcing (FR) layer is sandwiched between two adhesive layers, which are used to bond the FR to further layers, for example, an outer hull layer, in the following called weathering layer, and a potential inner hull layer as a gas barrier. In particular, the adhesive layers are configures as efficient gas barrier with low gas permeability. For example, the adhesive layers are main gas barrier layers such that the total gas permeability of the adhesive layers is less than the gas permeability of the remaining layers. This combination of functions of adhesivity and low gas permeability is unconventional. In contrast thereto, in the prior art, there are specific main gas-barrier layers different from the adhesive layers, where the main gas barriers have a lower gas permeability than the adhesive layers. In this context gas permeability concerns the gas inside the hull, typically Helium or Hydrogen gas.

As an example, illustrated in more detail in FIG. I, a fibrous load bearing layer is sandwiched between two EVOH layers, which not only work as gas barriers but are also used to take the role of adhesive for potential further layers, especially an outer hull layer, in the following called weathering layer, and a potential inner hull layer as a further gas barrier. Further functions of the layers, especially the weathering layer are protection against UV radiation, visible light, ozone, singlet oxygen, and heat.

Although, two EVOH film layers have been used in the optimization process, it is believed that a single EVOH layer melt-bonded into the fibre layer also would be more advantageous than the laminate systems of the prior art.

A variation of the design concept of FIG. I is shown in FIG. 2. In this case, the laminate material does not have any separate inner primary gas barrier layer. Instead the inner surface of the laminate is metallized after the laminate formation. Use of EVOH as an adhesive material with low gas permeability and the metallization of the inner surface yield excellent gas barrier properties of the laminate material. Elimination of the gas barrier layer reduces the overall laminate weight, while the tensile strength of the laminate is not affected.

In the following, materials as well as production methods are discussed in relation to experiments that were performed in optimising the hull laminate material.

Yarn selection

In order to simultaneously optimize low weight and high strength, high strength fibres are advantageously used. An example of an advantageous material for the fibrous load-bearing layer was found in crystalline PBO (crystalline polyoxazole, poly(pphenylene-2,6-benzobisoxazole) fibres, especially of the brand Zylon® because these fibres have a very high strength and specific modulus among the commercially available high performance fibres. These yarns also have high resistance to creep elongation. Zylon® yams were therefore selected for the fibre reinforcement in the laminate material used in experiments. However, PBO is known to be very susceptible to photo-degradation. The presence of moisture and oxygen has been accelerates photodegradation, why a protection mechanism had to be found.

For the fibre reinforcement layer, both balanced and unbalanced structures can be used. In some embodiments, an unbalanced construction was chosen to provide the different strength required in the longitudinal and the hoop direction of the LTA airship.

Zylon® yams with 99 denier, 150 denier, and 250 denier yam counts were provided by Toyobo Co., Ltd. The supplied yarns, which had zero-twist (non-twisted), were tested for their tensile strength. The average tensile strengths of non-twisted 99 denier and 250 denier yams were 35.5 gf/denier (4.8% cv ; cv-coefficient of variation) and 34.9 gf/denier (3.0% cv), respectively. Recognizing the fact that adding an optimum degree of twist (twist factor) to a yam provides its highest tensile strength, a series of tests were conducted to determine the optimum twist factor and the corresponding highest tensile strength achievable in 99 denier and 250 denier Zylon® yams. The Twist Factor (TF), which depends on both the amount of twist (twists per inch, tpi ; twists per meter, tpm ; 1 tpi=39 tpm), and the yam count are calculated using the formula TF = 0.124 tpi · dtex”⁵ where dtex is the unit for count, also called yarn linear density (1 denier is equal to 0.9 dtex).

The yams with 99 denier (110 dtex) and 250 denier (278 dtex) were twisted with various amount of twist (tpi, tpm) and tested for their tensile strength. The results tabulated in Table 1 show that the tensile strength of both 99 denier and 250 denier yams are highest for the Twist Factor of 10 which corresponds to 7.69 tpi (or 303 twists per meter, tpm) for the 99 denier yam and 4.84 tpi (or 190 tpm) for the 250 denier yam.

Twist Factor	Yam count. denier	turns per inch, tpi	Tenacity, gf/denier	Strain @ peak load. %
avg. cv%	avg.	cv%
10.00	99	7.69	40.6 3.3	3.9	9.6
13.21	99	10.16	39.9 3.1	3.8	2.1
9.19	250	4.45	37.5 2.7	3.6	~ 0
10.00	250	4.84	39.0 1.5	3.7	3.0
11.55	250	5.59	38.0 3.5	3.7	3.7
13.13	250	6.35	38.9 1.4	3.8	~0

Table 1

Fibre reinforcement configuration

In experiments, for the load bearing layer, several principles were applied. One was a non-crimp 2 ply cross-ply fibre reinforcement layer as illustrated in FIG. 3a and another a woven fibre reinforcement layer as illustrated in FIG. 3b. A third principle with 90/±45 degree plies is illustrated in FIG. 3c.

Film selection for lamination

EVOH (Ethylene Vinyl alcohol copolymer) has a very low permeability with respect to gas, especially He, which is why it is a good candidate for the adhesive layer.

A good candidate for the outer weathering layer against the outer atmosphere was found in Pl (polyimide), although also other polymers are possible, for example polyvinyl fluoride (PVF). Advantageously, the outer weathering layer was metallised, in order to repel radiation and heat. In order to protect the metal against damages, the metal coating was directed inwards, which is between the polymer of the weathering layer and the EVOH. This way, the polymer protects the metal against the corrosive environment in the stratosphere.

Alternatively, the weathering layer is metallized on both sides. If the weathering layer is metallized on both sides or has a metalized side that is exposed to the environment, it is advantageously protected by a corrosion resistance coating.

In some embodiments, an inner gas barrier was added to the opposite side of the multilayer as compared to the weathering layer, where the inner gas barrier layer was a metallised polyethylene terephthalate (PET) film, for example Mylar®.

Lamination was done for laminates with a size of 7.5 inch x 7.5 inch (19 cm x 19 cm) under pressure at 285 psi = 1965 kPa between two stationary aluminium plates with a temperature of 175-178’C for 15 minutes, the upper end of the temperature interval showing the best lamination results. These samples for used for tests of various kinds as described in the following.

However, different combinations of temperature and dwell time are possible. In other experiments, a lower pressure and lower dwell time at higher temperature in the range of 180-200°C was successful. For example, a temperature of 196°C was used for 2 seconds at a pressure of 60 psi = 414 kPa.

Strength measurements

Tensile strength measurements were performed according to the Standard Test Method for Breaking Force and Elongation of Textile Fabrics (Strip Method) ASTM D5O35. The tensile strength values are reported in the units of N/cm and gf/denier (mN/tex = 88.3 gf/den). Tensile strength in N/cm represents the sample tenacity per unit width in cm. Tensile strength in gf/denier represents the sample tenacity per total denier of yams in the loading direction. Tensile strength in gf/denier is used as a normalized metric to determine how of much of yam strength is translated to laminated/n on-lamina ted fibre reinforcement strength.

I4

For unbalanced structures, as explained in the following in detail, estimated tensile strengths (calculated based on the yarn strength and fibre reinforcement construction parameters) were 1033 N/cm and 516 N/cm in the warp and weft directions, respectively. In general, the warp direction tensile strength of all the samples (except laminated woven fibre reinforcements) were found to be close to 1000 N/cm, while the weft of all samples were found to be greater than 500 N/cm. Corresponding parameter values in terms of gf/den were in the range of 31 -35.

Experiments were also performed for balanced fabric structures based on Zylon® yam in the fabric. Low twisted (3-5 tpi) Zylon® yams of 99 denier and with a density of 46-50 ypi (approximately 18-20 yam per cm) were used for both the warp and the weft in a plain weave. The Zylon® yam was sized with polyvinyl alcohol. Tensile strengths were measures in the range of 520 to 615 N/cm and 28 to 34 gf/den in the warp and weft directions, and an elongation at break of 2.9-3.2%. This results are also very good for the purpose, seing that this were values for the fabric and not the entire laminate. In more detail the following data were measured.

As a conclusion, it has been demonstrated that both balanced and unbalanced structures with high-strength yams are very useful.

Example 1 - P3

FIG. 4a shows a specific embodiment of the principle sketch of FIG. 2. On the left in the figure, the weight of each layer is shown in unit of grams per square meter (gsm), and the thickness in microns is shown to the right. Photographs of the produced laminates are shown in FIG. 4b.

The schematic design of this laminate prototype, in the experiment termed P3, comprises an unbalanced cross-ply (two-ply) non crimp fabric as the fibre reinforcement. The fabric has 250 denier Zylon® yams in 90-degree and 0-degree directions. The basis weight of the fabric is 48 gsm with yam density of 30 ypi (30 yams per inch are approximately 12 yams per cm) in 90-degree direction and 15 ypi (approximately 6 yarns per cm) in 0-degree direction, thus, yielding more strength in the 90-degree direction than in the 0-degree direction. The prototype design includes three layers of

EVOH film which provide excellent adhesion and gas barrier properties. The estimated and measured weight of this laminate prototype was found to be 111 gsm and 109 gsm, respectively.

Example 2 - P4

FIG. 5a shows a specific embodiment of the principle sketch of FIG . 1. On the left in the figure, the weight of each layer is shown in unit of grams per square meter (gsm), and the thickness is shown to the right. Photographs of the produced laminates are shown in FIG. 5b.

The schematic design of this laminate prototype, in the experiment termed P4, comprises an unbalanced cross-ply (two-ply) non crimp fabric as the fibre reinforcement. The fabric has 250 denier PBO yams in longitudinal and cross directions. The basis weight of the fabric is 48 gsm with yam density of 30 ypi (approximately 12 yams per cm) in 90-degree direction and 15 ypi (approximately 6 yams per cm) in 0-degree direction. In order to achieve lower laminate weight, the design uses two layers of EVOH film and a bottom layer of a lightweight metallized PET film (Mylar®) which serves as the primary gas barrier layer. The estimated and measured weight of this laminate prototype is 103 gsm.

Example 3 - P9

FIG. 6a shows a specific embodiment of the principle sketch of FIG. 1. On the left in the figure, the weight of each layer is shown in unit of grams per square meter (gsm), and the thickness is shown to the right. Photographs of the produced laminates are shown in FIG. 6b.

The schematic design of this laminate prototype, in the experiment termed P9, comprises an unbalanced woven fabric as the fibre reinforcement. The woven fabric has 99 denier Zylon® yarns with 40 tpm twist in warp direction and non-twisted 250 denier Zylon® yarns in weft directions, respectively. The basis weight of the fabric is 50 gsm with yam density of 40 ypi (approximatelyl6 yams per cm) in warp direction and 30 ypi (approximately 12 yams per cm) in weft direction. Like prototype P4, the bottom layer is a lightweight metallized PET film (Mylar®) which serves as the primary gas barrier layer. Although the lamination temperature of 175°C produced satisfactory adhesion between the layers, increasing the lamination temperature to 178°C improved the adhesion between layers. The estimated and measured weights of this laminate prototype were found to be 105 gsm.

Example 4 - PIO

FIG. 7a shows a specific embodiment of the principle sketch of FIG, 1. On the left in the figure, the weight of each layer is shown in unit of grams per square meter (gsm), and the thickness is shown to the right. Photographs of the produced laminates are shown in FIG. 7b.

The schematic design of this laminate prototype, in the experiment termed PIO, comprises an unbalanced woven fabric as the fibre reinforcement. Unlike the prototype P9, prototype PIO uses woven fabric with 99 denier Zylon® yams with 40 tpm twist in warp direction and non-twisted 99 denier Zylon® yams in weft directions, respectively. The basis weight of the fabric is 50 gsm with yam density of 40 ypi (approximately 16 yams per cm) in warp direction and 75 ypi (30 yams per cm) in weft direction. The higher ypi (yams per inch) in the weft direction is expected to form a more stable fabric structure with smoother surface texture. In the initial trails, a lamination temperature of 175°C was used, however, this resulted in poor lamination quality with weak adhesion of the metallized PI film. Increasing the lamination temperature to 178 C improved the lamination quality, but the adhesion was not as good as prototype P9 but still satisfactory. The estimated and measured weight of this laminate prototype was found to 105 gsm.

Gas barrier performance

Helium permeability test results (Table 2) shows that while both the laminate prototypes P3 and P4 have much lower helium permeability than the target value of 132 cc/m2.day.atm, laminate prototype P4 has significantly lower helium permeability compared to that of prototype P3. The lower permeability of prototype P4 is attributed to the presence of the metallized Mylar® layer which also reduced the overall weight of the prototype P4.

Laminate Prototype	Laminate Weight,	Gas (He) Permeability, cc/m2.day. atm
P3	109	23
P4	103	8

Table 2

Given the same layering schemes, helium permeability values of prototypes P9 and PIO were expected to be same as that of prototype P4, which with respect to gas tightness were favoured over P3.

Laminate Strength

The warp and weft direction tensile strength of laminate prototypes P4, P9, and PIO are shown in Table 3. The tensile strength of one specimen of prototype P3 was found to be 1086 N/cm.

Laininale Prototype	1 .»nil note Weight,	Tensile Strength. N/cm	Ten sile St ren« til. gf/ctenier	Elongation/» (d break
Warp	Weft	Warp	Weft	Wa rp	Weft
Avg.	ev%	Avg.	cv%	Avg.	ev%	Avg.	cv%	Avg.	ev%	Avg.	ev%
P4	103	045.4	5.5	5O7.X	7.9	32.1	5.7	35.3	5.0	3.17	7.3	2.9!	5.0
P9	105	4X6.9	6.0	970.8	3.7	32.0	5.5	32.9	4.5	3.01	7.8	3.29	8.8
PIO	105	476.8	-	956.4	-	30.7	-	33.3	-	2.68	-	3.41	-

Table 3

The estimated tensile strengths, calculated based on the yam strength and fibre reinforcement construction parameters, are 1033 N/cm and 516 N/cm in the two directions. The measured tensile strength of the prototypes was slightly lower than the estimated values. The lower tensile strengths compared to the estimated tensile strength is attributed to manual experimental preparation of laminate prototypes which causes lack of complete alignment of yarns and non-uniform tension in the yarns. These imperfections result in non-uniform load sharing among the load-bearing yarns which

I8 ultimately causes pre-mature rupture of specimens during the tensile test. It is believed that the tensile strengths improve and are similar to theoretical values when the laminates are produced in a dedicated large scale production facility. However, it is pointed out that the experimental values are deviating by less than 10% from the theoretical values, which is a very satisfactory result.

Comparison with other studies

A comparison of the strength and weight of the new laminate prototypes and laminate materials developed in other studies in the literature is shown in FIG. 8. The references are found at the end of this section in relation to Table 4.

Comparison of strength-to-weight ratio of the new laminate with the laminates developed by other studies is shown in FIG. 9. The new laminate prototypes are not only significantly lighter than any other laminates with similar tensile strength, but also significantly stronger than any laminate with the similar weight. The strength-toweight ratios of the new laminate prototypes are higher than all the laminates developed in other studies.

As it is seen in this comparison, the strength of the laminates P3, P4, P9, and PIO is very high as compared to the weight, making them highly suitable for use in lighter than air vehicles. However, it is pointed out that the superior Tenacity-to-weight ratio, as illustrated in FIG. 9, is believed to be scalable to thicker laminates, which favours the exemplified laminates also over those laminates that have an overall higher tenacity in FIG. 8.

I9

#	Organi/ation / Study	Remarks	Material Description	Tenacity, \/cm	Weight, gsm	Tenacity toWeight Ratio, kX.m/kg
Al	Development of High Specific Strength Envelope Material1	”Z5()0-)(>()’’ means 5()0d Zylon fiber is used & 10Ü gsm	Z5ÜÜ-100PU- XL	1300	244	533
Λ2	Z25Ü-94PU-XL	1240	235	52X
Λ 3	Z250-79PU-XL	1100	226	4X7
Λ4	Z250-47PU-XL	615	193	319
A5	Z250-47PU	610	164	372
Λ6	Z25(M0PU	510	154	331
Bl	Development of High Specific Strength Envelope Material 1	B3, B5 are developed. Bl, B2. B4 are off the shelf; V:Vectran, PU:Polyurethane, PE: Polyethylene. XL:EVOH. XLAiAluminum stuck EVOH	V-PU-XL	610	1%	30X
B2	V100-3 IP E- XLA	620	150	413
B3	V-PU-XL	350	111	315
B4	V200-102PUXL	1060	274	3X7
Cl	Development of High Specific Strength Envelope Material 1	Λ1-Λ6 are modified into this category; TA:Tcdlar with Aluminiumdeposit, T: Tedlar, Z: Zylon, PUA: Polyurethane with Aluminum deposit	ΤΛ-Ζ250110PU	1327	19«	670
C2	T-Z25O-110PU	1313	225	5X4
Dl	Development of High Specific Strength Envelope Material1	Z25Ü-110PLIAXLD	1337	163	X20
D2	Z250H0PU- XLD	1350	171	7X9
El	Development of High Specific Strength En\ elope Material 1	for internal gas bug or light weight use; N:Nylon. K: Kevlar, JEHydrel; Ml: Mictron	N3O-4OPU- XLD	105	7«	135
E2	K200-H-MI	450	130	346
E3	V-H-Ml	500	104	4X1
E4	Z-H-Ml	440	117	376

Fl	Development of High Specific Strength Envelope Material1	Thick Zylon fibers arc sandwiched by two Mylar films	Z5OO-37M	680	!6l	422
12	Z1000-74M	1220	198	616
1’3	Z1500-11 IM	1800	236	763
F4	Z1000-44M	770	170	453
F5	Z1500-67M	1090	193	565
F6	Z2000-89M	1400	210	667
Gl	Japan Aerospace Exploration Agency (JAXA)	Suitable for Operational Airship (overall length: 250 m)	AL-PVF + PL·' + Zylon fabric + PL	1310	203	645
Hl	Japan Aerospace Exploration Agency (JAXA) 4.5.6	T cchnology Demostrator Airship (overall length: 150 m)	AL-PVF + PL’ + Zylon fabric + PL	993	157	632
.11	Cubic Tech Corp 7	Heavy Zylon Noncrimp fabric	Zylon FR (349 gsm)	2833	-	-
J2	Cubic Tech Corp 7	Medium Vcctran Noncrimp Fabric	Vcctran FR (139 gsm)	916	-	-
KI	Kang et al 2006	Vcctran woven Fabric	Vcctran FR {109)+PL coating + PVF + PL film	883	220	401
LI	Gn 2007 9	Lindstrand HALE Airship Envelope	Vcctran FR	1460	295	495
L2	tin 2007 9	Envelope of Stratospheric Airship (overall length 200 m)	na	1360	210	648
Ml	C ao & Gao 2(109 10	Zylon plain weave (Warp)	PBO FR (87) + PVF(52) + PL’(25*2) + PL coating (58)	1013	189	536
Zylon plain weave (Weft)	12X1	678
Nl	Lietal. 201011	Zylon plain weave (Warp)	990 denier P13O (78) + PET (40) + PVF (30) +PL ¢30)	1578	178	887
Zylon plain weave (Weft)	1356	762

Table 4

References to Table 4:

l. Kamatsu, K, Sano, Μ., and Kakuta, Y., Development of High Specific Strength Envelope Material, ΑΑΙΑ 3rd Annual Aviation Technology, Integration, and Operations (ATIO) Tech, Nov 17-18 2003, Denver, Colorado.

2. Sasaki Y., Eguchi, K, Kono T, and Maekawa, S, “Scenario for Development of the SPF Airship Technology Demostrator, The Fifth Stratospheric Platform Systems

Workshop, Feb 23-24, 2005, Tokyo, Japan.

3. Maekawa S, On the Design Issue of a Stratospheric Platform Airship Structure NAL TM-722, National Aerospace Laboratory of Japan, May 2003.

2l

4. Maekawa, S and Yoshino, T, Tear propagation of a High-Performance Airship Envelope Material, Journal of Aircraft, 45 (5), Sept-Oct 2008.

5. Nkadate, Μ., Maekawa, S., Maeda ,T, Hiyoshi, Μ., Kitada, T., and Segawaö, S. Reinforcement of an Opening for High Strength and Light Weight Envelop Material Zylon 18th AIAA Lighter-Than-Air Systems Technology Conference, May 4-7 2009, Seattle, Washington, USA.

6. Nakadate, Μ., Maekawa, S., Shibasaki, K, Kurose, T. Kitada, T, and Segawa, S., “Development of High Strength and Light Weight Envelop Material Zylon 7th International Airship Convention 2008, Friedrichshafen Germany, Oct 9-11 2008.

7. High Strength-to-Weight Ratio Non-Woven Technical Fabrics for Aerospace Applications Cubic Tech Corp, 2009, Mesa, Arizona.

8. Kang, W, Suh, Y, and Woo, K.., Mechanical property characterization of filmfabric laminate for stratospheric airship envelope Composite Structures, 75, pp. 151— 155, 2006.

9. Gu Z., Research of Stratospheric Airships Skin Material' Spacecraft Recovery& Remote Sensing, 28( I), pp.62-66,2007.

10. Cao, X, and Gao, C. Fabrication and Investigation of Envelope Materials for Stratospheric Aircraft with PBO Fabric as Load-carriers High-tech Fibre & Application, 34(4), pp.0-5, 2009.

11. Li B, Xing L, Zhou Z, Jiang S, and Chen X., Study on Mechanical Properties of High Performance Envelope Materials Material Engineering, pp. 1-5,2010.

Effect of thermal and UV-Vis weathering

Laminate prototypes P4, P9, and P10 were subjected to two different weathering conditions. In one weathering exposure the prototypes were subjected to thermal exposure for 24 hours in an oven at 80°C. The other weathering exposure involved the accelerated exposure to UV and Visible light (UV-Vis) spectrum of -275 to 700 nm for a duration of 170 hours (- 60 days of real time exposure at an altitude of 10 km). The prototypes were exposed in an Atlas Ci 3000+ Weather-Ometer (www. atlas-mts.com) with the irradiance level of l.l Watts/m2 at 340 nm. During the UV-Vis weathering, the temperature of the prototypes was maintained at about 80°C. For UV-Vis weathering the specimens were mounted on metal frames and the inner side (Mylar® side) of the samples was covered with two layers of black card paper to prevent any exposure to the inner side. The frames were then mounted on round rails inside the weathering chamber of Atlas Ci 3000+ Weather-Ometer such that the outside of the specimens were facing towards the UV and visible light source.

The tensile strength of the prototypes after each weathering exposure was tested. The strength loss in percentage was as defined as follows:

Strength Loss% = ^{Tensile Strenth} before exposure -Tensile Strength_{after exposure} Tensile Stren^th^_e^_ore exposure

This was used as a metric to evaluate thermal and photo-degradation.

The average tensile strength before and after thermal exposure and UV-Vis weathering were found to be statistically the same (statistical analysis was performed using ttest at 95% confidence level). It can therefore be concluded that there is negligible degradation caused by thermal and UV-Vis weathering. It is important to notice that the specimens tested before and after weathering exposures were taken from different replicas of the same prototype. Due to the manual preparation of the prototypes, there are inherent variations within a replica as well as variations among the different replicas of the same prototype. Some of the samples exposed to heat showed higher strength compared to corresponding unexposed samples which strongly points to the variability in the specimens within a sample. A graphical comparison of tensile strengths of prototypes P4, P9, and PIO before and after thermal exposure and UV-Vis weathering is shown in FIG. IO.

Strength loss % in prototypes P4, P9 and PIO after thermal exposure and accelerated UV-Vis weathering is shown in FIG. 11.

The average tensile strength before and after thermal exposure and UV-Vis weathering were found to be statistically same (statistical analysis was performed suing t-test at 95% confidence level). It can therefore be concluded that there is negligible degradation caused by thermal and UV-Vis weathering. It is important to note that the specimens tested before and after weathering exposures were taken from different replicas of the same prototype. Due to the manual preparation of the prototypes, there are inherent variations within a replica as well as variations among the different replicas of the same prototype. Some of the samples exposed to heat showed higher strength compared to corresponding unexposed samples which strongly points to the variability in the specimens within a sample.

Tear strength measurements

The tear strength of prototype P4 and P9 were measured using the cut-slit tear test method MIL-C-21189. Schematic diagram of a tear specimen is shown in FIG. 12. A 1.25 inch cut slit is made at the centre of the specimen perpendicular to the direction of test. The specimens are 4 inch wide with a test gauge length of 3 inch between the grips.

Tear strength of a specimen was calculated by averaging the 5 highest peak loads during a tear test. Three specimens per sample were tested in warp and weft directions. The tear strength results of prototype P4 and P9 are shown in Table 5.

Laminate Prototype	Tear Strength, N
Warp	Weft
Avg.	cv%	Avg.	cv%
P4	330.7	9.5	403.5	9.7
P9	290.0	6.6	533.7	5.2

Table 5

The reason for the higher tear in warp direction of prototype P4 compared to prototype P9 is due to the difference in warp yam denier used to construct the two structures. In prototype P4, 250 denier yam was used, while in prototype P9, 99 denier was used. It is well established in the literature that the tear load increases by increasing the yam braking load.

Resistance to creep elongation

A 1-inch wide specimen of prototype P4 was subject to a constant load of 1250 N for a duration of 1 day on a MTS Load frame (www.mts.com) with the load frame running in load control mode. The gauge length of the test specimen was 3 inch (76 mm).

The load extension curve of the test is shown in FIG. 13. After an instantaneous extension of 1.6%, the P4 specimen showed a very small creep extension of 0.02%.

Alternative laminates

FIG. 14 and FIG. 15 show specific light-weight embodiments of the principle sketch of FIG.2.

The schematic design of the laminate prototype, experimentally termed Pl2, illustrated in FIG. 14 uses an unbalanced cross-ply non-crimp fabric or an unbalanced woven fabric as the fibre reinforcement. The 48 gsm fabric is made of PBO yarns. The inner surface of the laminate (adhesive layer) is metallized after the laminate formation. The estimated basis weight of the laminate prototype is 96 gsm.

Using a three-ply non-crimp fabric instead was expected to not only further reduce the fibre reinforcement weight but also increase the tensile strength of the laminate. An example of laminate prototype with three-ply fibre reinforcement is described below in relation to FIG. 15. The schematic design of this laminate prototype, experimentally termed P13, illustrated in FIG. 15, uses a three-ply fabric (250 denier yam) with 15 ypi (approximately 6 yams per cm) in 90° direction, and 11 ypi (approximately 4 yarns per cm) in +/- 45° directions. The three ply is arranged as in FIG. 3c. The fibre reinforcement weight is equal to 41 gsm. Similar to prototype Pl2, the inner surface of the laminate (adhesive layer) is metallized after the lamination process. The estimated weight the laminate is expected to be 89 gsm. The estimated tensile strength of the laminate prototype P13 is estimated to be higher than 1000 N/cm.

The schematic design of laminate prototype, experimentally termed P14 illustrated in FIG. 16 uses a three-ply fabric (250 denier yam) with 22 ypi (approximately 9 yarns per cm) tn 90° direction, and 16 ypi (approximately 6 yams per cm) in +/- 45° directions. The fibre reinforcement weight is equal to 59 gsm. The three ply is arranged as in FIG. 3c. Similar to prototype Pl 2, the inner surface of the laminate (adhesive layer) is metallized after the lamination process. The estimated weight the laminate is expected to be 107 gsm. The estimated tensile strength of the laminate prototype Pl 3 is estimated to be higher than 1550 N/cm. The strength-to-weight ratio is estimated to be close to 1400 kN.m/Kg, which is vastly higher than all laminate materials developed in other studies.

Temperature stability measurements

Dynamic Mechanical Analysis (DMA) was made on a number of samples for a large temperature range in order to elucidate whether low temperatures could become a problem for the flexibility of the material. The temperature range was from -60°C to l00°C. In this interval, the loss modulus, related to the inelastic properties and the energy dissipation, and the storage modulus, related to the elastic properties, were measured in units of MPa with a Q800 DMA measurement device commercially provided by TA Instruments, New Castle, DE 19720, USA (www.TAlnstruments.com). In addition, the ratio between the two parameters, also called Tan Delta, was calculated. Measurements are illustrated in FIG. 17a, 17b and 17c.

The measurements are illustrated in

FIG. 17a for a sample of EVOH film with a size of20 x 7 x 0.0130 mm,

FIG. 17b for a sample of Mylar film with a size of 22 x 7 x 0.0050 mm,

FIG. 17c for a sample for a sample of polyimide (PI) film with a size of 23 x 7 x 0.0130 min,

FIG. 17d for a sample of the P4 Warp tensile 3 with a size of 19 x 6 x 0.1020 mm.

The measurements showed that the EVOH, Mylar and Pl films are stable at low temperatures without indicating low temperature weakness. For the EVOH film, this is surprising in view of the Zhai and Euler article discussed in the introdction. The Tan Delta curve indicates phase transitions, which for the films at low temperatures seem not to occur. For the laminates of Prototype P4, no evidence of delamination and neither physical damage was observed. It is believed that the heating of the fabric to 180°C during processing leads to a cross-link the polymers into their final state in the fabric, which is advantageous for the stability.

Conclusions

Light weight laminate materials for the hull of high altitude lighter than air vehicles were developed, which have improved properties. The new laminate prototypes are not only significantly lighter than prior art laminates with similar tensile strength, but also significantly stronger than prior art laminates with the similar weight. The specific strength (strength-to-weight ratio) of the laminate prototypes is significantly higher than the current state-of-the-art. The laminates prototypes also have excellent re5 sistance to thermal degradation, photo degradation, chemical resistance, especially against singlet oxygen and ozone, excellent gas barrier properties, and excellent resistance to creep elongation. Furthermore, the outermost film/layer also provide excellent thermal management, including low emissivity. Accordingly, the layered material has multi-functional properties at high level. The laminate design concept can be used IO to adjust the laminate materials to lower or higher weight while largely keeping the strength-to-weight ratio.

Claims (23)

An aircraft lighter than air comprising a hull, the hull comprising a laminate material as a gas barrier and supporting structure, the laminate material comprising a reinforcing fiber layer and a first film of ethylene vinyl alcohol, EVOH, melt-bonded into the fiber layer on one side of the fiber layer, wherein EVOH is in direct contact with the reinforcing fiber layer, the reinforcing fiber layer comprising fibers made of liquid crystal. The aircraft of claim 1, wherein a second EVOH film is melt bonded into the fiber layer on an opposite side of the fiber layer, said EVOH of the second EVOH film being in direct contact with the reinforcing fiber layer. An aircraft according to any one of the preceding claims, wherein the liquid crystal is poly [p-phenylene-2,6-benzobisoxazole], PBO. The aircraft of claim 3, wherein at least some of the liquid crystal fibers are twisted. An aircraft according to claim 4, wherein the twisted fibers of liquid crystal comprise a twist of between 30 and 50 per meters. An aircraft according to claim 4 or 5, wherein the fiber layer comprises at least a first set of fibers and a second set of fibers, wherein the fibers in the first set of fibers are twisted fibers of liquid crystal and oriented in a first direction, and wherein the fibers in the second set fibers are non-twisted fibers of liquid crystal and oriented in a second direction which is different from the first direction. An aircraft according to claim 6, wherein the first and second directions have an angle between the directions of at least 30 degrees. An aircraft according to claim 6 or 7, wherein the first and second directions are perpendicular. An aircraft according to any one of claims 6-8, wherein the first set of fibers has a first density of threads and the second set of fibers has a second density of threads which differs from the first density of threads by a factor of at least two. An aircraft according to any one of the preceding claims, wherein the weight of the fiber layer is between 40 and 70 g / m 2. An aircraft according to any one of the preceding claims, wherein the thickness of the first EVOH film is between 10 and 20 micrometers. An aircraft according to any one of the preceding claims, wherein the thickness of the second EVOH film is between 10 and 20 micrometers. An aircraft according to any one of the preceding claims, wherein the laminate comprises a weather-exposed layer melt-bonded to the first EVOH film, the weather-exposed layer comprising a metallized polymer film. The aircraft of claim 13, wherein the metallized polymer film comprises a metal layer melt-bonded at and on the first EVOH film layer. An aircraft according to claim 13 or 14, wherein the thickness of the weather-exposed layer is between 10 and 20 micrometers. An aircraft according to any one of the preceding claims, wherein the laminate comprises a metallized gas barrier layer melt-bonded to the second EVOH film on the opposite side of the laminate relative to the weathered layer. The aircraft of claim 16, wherein the metallized gas barrier layer comprises a metallized polymer film that is melt bonded to the second EVOH film with a metal layer on the opposite side of the metallized polymer film relative to the second EVOH film. The aircraft of claim 17, wherein the metallized polymer film layer is a layer of polyethylene terephthalate, PET, having a thickness of between 2 and 6 micrometers. An aircraft according to any one of the preceding claims, wherein the laminate has a weight of between 85 and 120 g / m 2. An aircraft according to any one of the preceding claims, wherein the strength / weight ratio of the laminate is above 890 kNm / kg. A method of making an aircraft laminate material lighter than air according to any one of the preceding claims, which method comprises providing a reinforcing fiber layer and a first EVOH film on one side of the fiber layer or a first and second EVOH film on each side of the fiber layer, and compressing the layers with heat at a temperature of between 175 ° C and 200 ° C for melt bonding, the reinforcing fiber layer consisting of fibers made of liquid crystal. A laminate material for an aircraft lighter than air according to claim 2 and any one of claims 3-20 depending on claim 2, wherein the laminate material has a weight of between 85 and 120 g / m 2 and comprises a reinforcing fiber layer made of Poly [pphenylene -2,6-benzobisoxazole] fibers, where the weight of the fiber layer is between 40 and 70 g / m2, and a first and second 10-15 micrometer thick EVOH film are melt-bonded into the fiber layer on each side of the fiber layer, as well as a 10- 15 micrometer thick polyimide film having a metallized side melt bonded to the first EVOH layer. A laminate according to claim 22, further comprising a 4-12 micrometer thick metallized polymer film layer fused on top of the second EVOH film on the opposite side of the laminate material relative to the weathered layer.