Composite flexible skin for inflatable aircraft

Abstract

The utility model relates to a composite flexible skin for an inflatable aircraft. The composite flexible skin comprises an outer layer part, a flexible bonding substrate and an inner layer part, the flexible bonding substrate is filled between the outer layer part and the inner layer part and is used for connecting the outer layer part and the inner layer part; a first memory alloy wire braid layer and a first temperature sensor are embedded in the outer layer part, and the first temperature sensor is adjacent to the first memory alloy wire braid layer; a second memory alloy wire braid layer and a second temperature sensor are embedded in the inner layer part, and the second temperature sensor is adjacent to the second memory alloy wire braid layer; the warp and weft direction of the first memory alloy wire woven layer is consistent with the warp and weft direction of the second memory alloy wire woven layer.

Description

Technical Field

[0001] The utility model relates to the field of aerospace, in particular to a composite flexible skin for an inflatable aircraft. Background Art

[0002] For an airship, during the flight, under the combined action of complex and harsh multiple high-altitude environmental factors on the flexible skin thin film composite material of the floating airbag, on the one hand, the mesoscopic structure of each component inside the skin thin film material will age and be damaged, and the original function of the thin film will deteriorate; on the other hand, the alternating high and low temperatures will cause stress alternating fatigue damage to the flexible skin thin film of the floating airbag. The dual coupling effect of these damage mechanisms directly leads to a sharp decline in the load-bearing performance and service life of the flexible thin film composite material, and may even cause catastrophic blasting consequences to the near-space airship. Therefore, it is of great practical significance to monitor and track the temperature and stress conditions of the flexible skin thin film composite material.

[0003] At present, the shape memory alloy that has been studied more is a material composed of two or more metal elements that has a shape memory effect through thermoelasticity and martensitic phase transformation and its reverse transformation. Moreover, the shape memory alloy is the material with the best shape memory performance among shape memory materials. In addition, due to the existence of phase transformation, the shape memory alloy has a unique thermal-force-resistance curve. Therefore, how to utilize this characteristic of the shape memory alloy to realize the temperature and pressure intelligent perception of the flexible skin thin film composite material of the floating airbag has become a direction that can be further studied. Content of the Utility Model

[0004] The purpose of the utility model is to provide a composite flexible skin for an inflatable aircraft.

[0005] To achieve the above-mentioned utility model purpose, the utility model provides a composite flexible skin for an inflatable aircraft, including: an outer layer part, a flexible bonding substrate, and an inner layer part;

[0006] The flexible bonding substrate is filled between the outer layer part and the inner layer part and is used to connect the outer layer part and the inner layer part;

[0007] The outer layer part is embedded with a first memory alloy wire braided layer and a first temperature sensor, and the first temperature sensor is arranged adjacent to the first memory alloy wire braided layer;

[0008] The inner layer part is embedded with a second memory alloy wire braided layer and a second temperature sensor, and the second temperature sensor is arranged adjacent to the second memory alloy wire braided layer;

[0009] The warp and weft directions of the first memory alloy wire braided layer are arranged to be consistent with the warp and weft directions of the second memory alloy wire braided layer.

[0010] According to one aspect of the present utility model, a third shape memory alloy wire braided layer is embedded in the outer layer portion;

[0011] Along the direction from the outer layer portion to the inner layer portion, the third shape memory alloy wire braided layer and the first shape memory alloy wire braided layer are arranged at intervals in sequence.

[0012] According to one aspect of the present utility model, the diameter of the alloy wire of the third shape memory alloy wire braided layer is smaller than the diameter of the alloy wire of the first shape memory alloy wire braided layer.

[0013] According to one aspect of the present utility model, the warp and weft directions of the third shape memory alloy wire braided layer are arranged in a staggered manner with respect to the warp and weft directions of the first shape memory alloy wire braided layer.

[0014] According to one aspect of the present utility model, the outer layer portion further includes: a protective structure layer, a first heat conduction layer, and a second heat conduction layer;

[0015] Along the direction from the outside to the inside of the composite flexible skin, the protective structure layer, the first heat conduction layer, and the second heat conduction layer are arranged in sequence;

[0016] The third shape memory alloy wire braided layer is arranged between the protective structure layer and the first heat conduction layer;

[0017] The first shape memory alloy wire braided layer is arranged between the first heat conduction layer and the second heat conduction layer;

[0018] The first temperature sensor is attached to the side where the second heat conduction layer is in contact with the first shape memory alloy wire braided layer.

[0019] According to one aspect of the present utility model, the protective structure layer includes: a reflective anti-aging layer, a sealing layer, and a first heat insulation layer;

[0020] Along the direction from the outside to the inside of the composite flexible skin, the reflective anti-aging layer, the sealing layer, and the first heat insulation layer are arranged in a stacked manner in sequence.

[0021] According to one aspect of the present utility model, the first shape memory alloy wire braided layer includes: a first warp alloy wire and a first weft alloy wire;

[0022] The third shape memory alloy wire braided layer includes: a third warp alloy wire and a third weft alloy wire;

[0023] The extending direction of the third warp alloy wire is arranged at an angle with respect to the extending direction of the first warp alloy wire;

[0024] The extending direction of the third zonal alloy wire is set to have an included angle with the extending direction of the first zonal alloy wire.

[0025] According to one aspect of the present invention, the inner layer portion further includes: a third heat conducting layer and a second heat insulating layer;

[0026] Along the direction from the outside to the inside of the composite flexible skin, the third heat conducting layer and the second heat insulating layer are arranged in sequence;

[0027] The second shape memory alloy wire braided layer is arranged between the third heat conducting layer and the second heat insulating layer;

[0028] The second temperature sensor is attached to the side where the third heat conducting layer is in contact with the second shape memory alloy wire braided layer.

[0029] According to one aspect of the present invention, the second shape memory alloy wire braided layer includes: second warp alloy wires and second weft alloy wires;

[0030] The extending direction of the second warp alloy wires is the same as that of the first warp alloy wires;

[0031] The extending direction of the second weft alloy wires is the same as that of the first weft alloy wires;

[0032] The diameters of the second warp alloy wires are set to be the same as those of the first warp alloy wires;

[0033] The diameters of the second weft alloy wires are set to be the same as those of the first weft alloy wires.

[0034] According to a solution of the present invention, by setting the outside of the composite flexible skin of the present invention as a composite structure layer, the outside structure of the present invention is made more firm and reliable, and it can conveniently and effectively guarantee the reliable change of the shape of the composite flexible skin. In addition, by setting an anti-aging layer on the outermost layer, the overall reliability of the composite flexible skin is further effectively improved, so that the aircraft adopting the present invention can have good flight performance in different environments. In addition, by further setting a sealing layer and a first heat insulating layer, the overall waterproof and heat insulating effect is realized, effectively avoiding the intrusion of water, heat, etc. in the external environment, and thus being beneficial to ensuring the stability, reliability and accurate control of the entire composite flexible skin.

[0035] According to a solution of the present utility model, the inner layer part is arranged as a heat-conducting layer plus a heat-insulating layer, which effectively simplifies the structure of the inner layer part, thereby being more beneficial to the thin and light setting of the entire composite flexible skin and reducing the overall mass of the composite flexible skin. In addition, by arranging the heat-insulating layer on the inner side, the influence of the internal environmental temperature on the composite flexible skin is effectively avoided, and the control accuracy and reliability of the present utility model for the composite flexible skin are effectively ensured.

[0036] According to a solution of the present utility model, the method of setting different diameters of the alloy wires of the third shape memory alloy wire braided layer and the first shape memory alloy wire braided layer can cause different changes in the electrical signals of the third shape memory alloy wire braided layer and the first shape memory alloy wire braided layer. Furthermore, the deformation state of the composite flexible skin can be obtained more accurately based on the different changes of the third shape memory alloy wire braided layer and the first shape memory alloy wire braided layer. In addition, by setting the third shape memory alloy wire braided layer with a smaller diameter, its electrical signal change is more sensitive, and it is arranged closer to the outer side of the composite flexible skin, so that the minute changes of the composite flexible skin can be obtained more accurately and reliably. In addition, by combining the oblique arrangement of the third shape memory alloy wire braided layer, the distribution range thereof is different from that of the first shape memory alloy wire braided layer, and thus the entire composite flexible skin can be more effectively controlled and measured accurately in each area through the third shape memory alloy wire braided layer and the first shape memory alloy wire braided layer. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 is a schematic structural diagram of a composite flexible skin showing an embodiment according to the present utility model;

[0038] Figure 2 is a schematic side view of a composite flexible skin showing an embodiment according to the present utility model. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0039] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0040] When describing the embodiments of the present utility model, the orientation or positional relationship expressed by the terms "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" is based on the orientation or positional relationship shown in the relevant drawings. This is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, the above terms should not be construed as limiting the present utility model.

[0041] The following will describe the present utility model in detail with reference to the drawings and specific embodiments. The embodiments cannot be elaborated one by one here, but the embodiments of the present utility model are not limited to the following embodiments.

[0042] Combined Figure 1 and Figure 2 As shown, according to an embodiment of the present utility model, a composite flexible skin for an inflatable aircraft includes: an outer layer portion 11, a flexible adhesive substrate 12, and an inner layer portion 13; wherein, the flexible adhesive substrate 12 is filled between the outer layer portion 11 and the inner layer portion 13 and is used to connect the outer layer portion 11 and the inner layer portion 13. In addition, through the provided flexible adhesive substrate 12, based on its flexibility, the deformation of the outer layer portion 11 and the inner layer portion 13 on the opposite sides is conducted to achieve the controlled deformation of the entire composite flexible skin.

[0043] In this embodiment, a first shape memory alloy wire braided layer 11a and a first temperature sensor 11b are embedded in the outer layer portion 11; a second shape memory alloy wire braided layer 13a and a second temperature sensor 13b are embedded in the inner layer portion 13; wherein, by embedding the shape memory alloy wire braided layers in the outer layer portion 11 and the inner layer portion 13, the energization control of the inner and outer sides of the composite flexible skin can be realized, so as to realize the flexible and accurate control of the shape of the composite flexible skin. Through the provided temperature sensors, the temperature of the inner and outer sides of the composite flexible skin can be accurately and timely detected, which is more conducive to realizing the accurate control of the whole composite flexible skin.

[0044] In this embodiment, the warp and weft directions of the first shape memory alloy wire braided layer 11a are set to be consistent with the warp and weft directions of the second shape memory alloy wire braided layer 13a. By setting the warp and weft directions of the first shape memory alloy wire braided layer 11a and the second shape memory alloy wire braided layer 13a to be the same, the unified deformation control of the outer layer portion 11 and the inner layer portion 13 can be effectively ensured, which is beneficial to ensuring the control accuracy of the composite flexible skin.

[0045] Combined Figure 1 and Figure 2As shown, according to an embodiment of the present utility model, a third shape memory alloy wire braided layer 11c is embedded in the outer layer portion 11; in this embodiment, the third shape memory alloy wire braided layer 11c and the first shape memory alloy wire braided layer 11a are arranged at intervals; wherein, along the direction from the outer layer portion 11 to the inner layer portion 13, the third shape memory alloy wire braided layer 11c and the first shape memory alloy wire braided layer 11a are arranged at intervals in sequence.

[0046] In this embodiment, the diameter of the alloy wire of the third shape memory alloy wire braided layer 11c is smaller than the diameter of the alloy wire of the first shape memory alloy wire braided layer 11a.

[0047] Through the above settings, the method of setting the diameters of the alloy wires of the third shape memory alloy wire braided layer 11c and the first shape memory alloy wire braided layer 11a differently can cause different changes in the electrical signals of the third shape memory alloy wire braided layer 11c and the first shape memory alloy wire braided layer 11a. Furthermore, the deformation state of the composite flexible skin can be obtained more accurately according to the different changes of the third shape memory alloy wire braided layer 11c and the first shape memory alloy wire braided layer 11a. In addition, by setting the third shape memory alloy wire braided layer 11c with a smaller diameter, its electrical signal changes more sensitively, and it is arranged closer to the outer side of the composite flexible skin, so that the minute changes of the composite flexible skin can be obtained more accurately and reliably. In addition, by combining the obliquely arranged third shape memory alloy wire braided layer 11c, the distribution range thereof is different from that of the first shape memory alloy wire braided layer 11a, so that the third shape memory alloy wire braided layer 11c and the first shape memory alloy wire braided layer 11a can more effectively control and measure each area of the entire composite flexible skin accurately and effectively.

[0048] Combined with Figure 1 and Figure 2 As shown, according to an embodiment of the present utility model, the warp and weft directions of the third shape memory alloy wire braided layer 11c are arranged in a staggered manner with respect to the warp and weft directions of the first shape memory alloy wire braided layer 11a. Among them, the warp and weft directions of the third shape memory alloy wire braided layer 11c and the warp and weft directions of the first shape memory alloy wire braided layer 11a present a state of being obliquely arranged with an included angle, so that the third shape memory alloy wire braided layer 11c can pass through the grid area of the first shape memory alloy wire braided layer 11a in the projection direction.

[0049] Combined with Figure 1 and Figure 2As shown, according to an embodiment of the present utility model, the outer layer part 11 further includes: a protective structure layer 111, a first heat-conducting layer 112, and a second heat-conducting layer 113; wherein, along the direction from the outside to the inside of the composite flexible skin, the protective structure layer 111, the first heat-conducting layer 112, and the second heat-conducting layer 113 are arranged in sequence. In this embodiment, the third shape memory alloy wire braided layer 11c is arranged between the protective structure layer 111 and the first heat-conducting layer 112; the first shape memory alloy wire braided layer 11a is arranged between the first heat-conducting layer 112 and the second heat-conducting layer 113. In this embodiment, the first temperature sensor 11b is attached to the side where the second heat-conducting layer 113 contacts the first shape memory alloy wire braided layer 11a.

[0050] Combined with Figure 1 and Figure 2 As shown, according to an embodiment of the present utility model, the protective structure layer 111 includes: a reflective anti-aging layer 111a, a sealing layer 111b, and a first heat-insulating layer 111c; wherein, along the direction from the outside to the inside of the composite flexible skin, the reflective anti-aging layer 111a, the sealing layer 111b, and the first heat-insulating layer 111c are arranged in a stacked manner in sequence.

[0051] Through the above settings, by arranging the outside of the composite flexible skin of the present utility model as a composite structure layer, the outside structure of the present utility model is made more firm and reliable, and it can conveniently and effectively guarantee the reliable change of the shape of the composite flexible skin. In addition, by setting an anti-aging layer on the outermost layer, the overall reliability of the composite flexible skin can be further effectively improved, so that the aircraft using the present utility model can have good flight performance in different environments. In addition, further by setting the sealing layer 111b and the first heat-insulating layer 111c, the overall waterproof and heat-insulating effect is realized, effectively avoiding the intrusion of water, heat, etc. in the external environment, and thus being beneficial to ensuring the stability, reliability and accurate control of the entire composite flexible skin.

[0052] Combined with Figure 1 and Figure 2 As shown, according to an embodiment of the present utility model, the first shape memory alloy wire braided layer 11a includes: a first warp alloy wire 11a1 and a first weft alloy wire 11a2; the third shape memory alloy wire braided layer 11c includes: a third warp alloy wire 11c1 and a third weft alloy wire 11c2; wherein, the extending direction of the third warp alloy wire 11c1 has an included angle with the extending direction of the first warp alloy wire 11a1; the extending direction of the third weft alloy wire 11c2 has an included angle with the extending direction of the first weft alloy wire 11a2.

[0053] Combined with Figure 1 and Figure 2As shown, according to an embodiment of the present utility model, the inner layer portion 13 further includes: a third heat-conducting layer 131 and a second heat-insulating layer 132; wherein, along the direction from the outside to the inside of the composite flexible skin, the third heat-conducting layer 131 and the second heat-insulating layer 132 are arranged in sequence; the second shape memory alloy wire braided layer 13a is arranged between the third heat-conducting layer 131 and the second heat-insulating layer 132. In this embodiment, the second temperature sensor 13b is attached to the side where the third heat-conducting layer 131 contacts the second shape memory alloy wire braided layer 13a.

[0054] Through the above arrangement, the inner layer portion 13 is set in the form of a heat-conducting layer plus a heat-insulating layer, effectively simplifying the structure of the inner layer portion 13, thereby being more beneficial to the thin and light setting of the entire composite flexible skin and reducing the overall mass of the composite flexible skin. In addition, by arranging the heat-insulating layer on the inner side, the influence of the internal environmental temperature on the composite flexible skin is effectively avoided, effectively ensuring the control accuracy and reliability of the present utility model for the composite flexible skin.

[0055] Combined Figure 1 and Figure 2 As shown, according to an embodiment of the present utility model, the second shape memory alloy wire braided layer 13a includes: second warp alloy wires 13a1 and second weft alloy wires 13a2. In this embodiment, the extending directions of the second warp alloy wires 13a1 and the first warp alloy wires 11a1 are the same; the extending directions of the second weft alloy wires 13a2 and the first weft alloy wires 11a2 are the same. In this embodiment, the diameters of the second warp alloy wires 13a1 are set to be the same as those of the first warp alloy wires 11a1; the diameters of the second weft alloy wires 13a2 are set to be the same as those of the first weft alloy wires 11a2.

[0056] According to an embodiment of the present utility model, the composite flexible skin of the present utility model for an inflatable aircraft further includes: a yarn bundle braided layer, wherein the yarn bundle braided layer is embedded in the flexible adhesive substrate 12. The flexibility of the flexible adhesive substrate 12 is effectively enhanced by the arranged yarn bundle braided layer, making the structure of the present utility model more reliable.

[0057] Combined Figure 1 and Figure 2 As shown, according to an embodiment of the present utility model, the thickness of the composite flexible skin is less than or equal to 0.7 mm.

[0058] The above content is only an example of the specific solution of the present utility model. For the equipment and structures not described in detail therein, it should be understood that the existing general equipment and general methods in the art are adopted for implementation.

[0059] The above is only one solution of the present utility model and is not intended to limit the present utility model. For those skilled in the art, the present utility model can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A composite flexible skin for an inflatable aircraft, characterized in that, Comprising: An outer layer portion (11), a flexible adhesive substrate (12), and an inner layer portion (13); The flexible adhesive substrate (12) is filled between the outer layer portion (11) and the inner layer portion (13), and is used to connect the outer layer portion (11) and the inner layer portion (13); The outer layer portion (11) is embedded with a first shape memory alloy wire braided layer (11a) and a first temperature sensor (11b), and the first temperature sensor (11b) is disposed adjacent to the first shape memory alloy wire braided layer (11a); The inner layer portion (13) is embedded with a second shape memory alloy wire braided layer (13a) and a second temperature sensor (13b), and the second temperature sensor (13b) is disposed adjacent to the second shape memory alloy wire braided layer (13a); The warp and weft directions of the first shape memory alloy wire braided layer (11a) are arranged to be consistent with the warp and weft directions of the second shape memory alloy wire braided layer (13a).

2. The composite flexible skin for an inflatable aircraft according to claim 1, wherein The outer layer portion (11) is embedded with a third shape memory alloy wire braided layer (11c); Along the direction from the outer layer portion (11) to the inner layer portion (13), the third shape memory alloy wire braided layer (11c) and the first shape memory alloy wire braided layer (11a) are arranged at intervals in sequence.

3. The composite flexible skin for an inflatable aircraft according to claim 2, wherein, The alloy wire diameter of the third shape memory alloy wire braided layer (11c) is smaller than the alloy wire diameter of the first shape memory alloy wire braided layer (11a).

4. The composite flexible skin for an inflatable aircraft according to claim 3, characterized in that, The warp and weft directions of the third shape memory alloy wire braided layer (11c) are arranged in a staggered manner with the warp and weft directions of the first shape memory alloy wire braided layer (11a).

5. The composite flexible skin for an inflatable aircraft according to claim 4, characterized in that, The outer layer portion (11) further includes: a protective structure layer (111), a first heat conducting layer (112), and a second heat conducting layer (113); Along the direction from the outside to the inside of the composite flexible skin, the protective structure layer (111), the first heat conducting layer (112), and the second heat conducting layer (113) are arranged in sequence; The third shape memory alloy wire braided layer (11c) is disposed between the protective structure layer (111) and the first heat conducting layer (112); The first shape memory alloy wire braided layer (11a) is disposed between the first heat conducting layer (112) and the second heat conducting layer (113); The first temperature sensor (11b) is attached to the side where the second heat conducting layer (113) contacts the first shape memory alloy wire braided layer (11a).

6. The composite flexible skin for an inflatable aircraft according to claim 5, characterized in that, The protective structure layer (111) includes: a reflective anti-aging layer (111a), a sealing layer (111b), and a first heat insulation layer (111c); Along the direction from the outside to the inside of the composite flexible skin, the reflective anti-aging layer (111a), the sealing layer (111b), and the first heat insulation layer (111c) are stacked in sequence; 7. The composite flexible skin for an inflatable aircraft according to claim 6, characterized in that, The first shape memory alloy wire braided layer (11a) includes: a first warp alloy wire (11a1) and a first weft alloy wire (11a2); The third shape memory alloy wire braided layer (11c) includes: a third warp alloy wire (11c1) and a third weft alloy wire (11c2); The extending direction of the third meridional alloy wire (11c1) is set at an angle with the extending direction of the first meridional alloy wire (11a1); The extending direction of the third latitudinal alloy wire (11c2) is set at an angle with the extending direction of the first latitudinal alloy wire (11a2).

8. The composite flexible skin for an inflatable aircraft according to claim 7, characterized in that, The inner layer portion (13) further includes: a third heat conduction layer (131) and a second heat insulation layer (132); In the direction from the outside to the inside of the composite flexible skin, the third heat conduction layer (131) and the second heat insulation layer (132) are arranged in sequence; The second shape memory alloy wire braided layer (13a) is arranged between the third heat conduction layer (131) and the second heat insulation layer (132); The second temperature sensor (13b) is attached to the side where the third heat conduction layer (131) is in contact with the second shape memory alloy wire braided layer (13a).

9. The composite flexible skin for an inflatable aircraft according to claim 8, characterized in that, The second shape memory alloy wire braided layer (13a) includes: a second meridional alloy wire (13a1) and a second latitudinal alloy wire (13a2); The extending direction of the second meridional alloy wire (13a1) is the same as that of the first meridional alloy wire (11a1); The extending direction of the second latitudinal alloy wire (13a2) is the same as that of the first latitudinal alloy wire (11a2); The diameter of the second meridional alloy wire (13a1) is set to be the same as that of the first meridional alloy wire (11a1); The diameter of the second latitudinal alloy wire (13a2) is set to be the same as that of the first latitudinal alloy wire (11a2).

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