Low heat radiation self-adapting cover for aircraft

Abstract

The utility model belongs to the field of aviation protection technology, and the plane low heat radiation self -adaptation cover cloth includes cloth cover outer layer, cloth cover inner layer and temperature control interlayer, uses, through the adsorbing disc of cloth cover inner layer and fuselage adhesion, cooperation drawstring hole drawstring fixed, makes the cover cloth stable cover fuselage. Temperature sensor real -time monitoring ambient temperature, triggers each structure cooperative work: high temperature, the phase change material unit of temperature control interlayer heat absorption buffer temperature, shape memory alloy ventilation adjustment channel (35 DEG C to 40 DEG C phase change) temperature expansion, inside spring auxiliary increase ventilation volume, while miniature rotary mechanism drives the rotation of reflector, enhances heat radiation reflection. Low temperature, the phase change material unit heat preservation, ventilation passage contraction reduces heat loss, the angle of reflector adjustment reduces the heat dissipation. The universal joint of support framework adapts fuselage curved surface, telescopic damping buffer deformation stress, maintains cloth cover inner and outer layer stable gap, realizes all temperature domain self -adaptation low heat radiation protection.

Description

Technical Field

[0001] This utility model belongs to the field of aviation protection technology, specifically an aircraft low-heat radiation adaptive covering. Background Technology

[0002] When an aircraft is parked or in transport, its surface covering needs to cope with complex temperature environments: under high temperatures and direct sunlight, the surface of the covering is prone to a sudden temperature rise due to heat radiation accumulation, which not only affects the stability of aircraft equipment but may also accelerate the aging of fuselage materials and increase the risk of being detected by enemy infrared reconnaissance equipment; in low-temperature environments, if the covering cannot effectively maintain the internal temperature, condensation may form or equipment may be difficult to start. Existing aircraft coverings mostly adopt a single insulation layer design, which can block heat conduction to a certain extent, but lacks the ability to dynamically respond to ambient temperature and is difficult to maintain stable thermal protection performance over a wide temperature range. Moreover, the support structure of traditional coverings is mostly a rigid mesh, which cannot adapt to the deformation requirements of the fuselage curved surfaces or edges, and is prone to problems such as localized over-tight fit or uneven gaps, weakening the heat insulation effect and even potentially leading to serious safety accidents such as wind and water accretion causing equipment damage.

[0003] The patent application No. 202422045494.7, entitled "A Long-Life Sunscreen Cover for Military Aircraft," improves the durability of the cover by optimizing the fabric material and strengthening the edge stitching process, and focuses on solving the problems of easy aging and short life of traditional covers. However, this design still has limitations: First, sun protection and heat insulation rely on static material properties and do not have an active adjustment structure, so it cannot optimize heat radiation reflection or ventilation efficiency according to real-time temperature changes, and the heat insulation performance is prone to saturation in high-temperature environments; Second, the support structure adopts a rigid frame, which improves the overall strength, but lacks a buffer mechanism, making it difficult to cope with the stress caused by vibration or thermal expansion and contraction when military aircraft are parked in uncertain areas, and it does not dynamically control the gap between the inner and outer layers of the cover, resulting in an unstable heat conduction path and failing to meet the refined requirements of low heat radiation. Utility Model Content

[0004] To address the problems mentioned in the background art, this utility model provides an aircraft low-heat radiation adaptive fabric to solve the problem that aircraft fabric cannot adaptively control temperature and dynamically adjust heat radiation.

[0005] To achieve the above objectives, this utility model provides the following technical solution: an adaptive low-heat-radiation fabric for aircraft, characterized in that it comprises an outer fabric layer, an inner fabric layer, and a temperature-controlled interlayer. The outer and inner fabric layers are rectangular, and the temperature-controlled interlayer is disposed inside the outer fabric layer. The temperature-controlled interlayer includes phase change material units and elastic connectors. The phase change material units and elastic connectors are arrayed and fixed on the inner side of the outer fabric layer. The phase change material units are square, and the elastic connectors are cross-shaped and connected to the phase change material units. Multiple support frames are provided at the connection gaps of the elastic connectors. The outer and inner fabric layers are interconnected through ventilation adjustment channels. The ventilation adjustment channel array is fixed on the long side of the outer and inner fabric layers. A micro-rotating mechanism and a reflective sheet are installed on the outer side of the outer fabric layer, and a temperature sensor is provided on the outer fabric layer.

[0006] Optionally, the ventilation regulating channel is configured as a rectangular tube and the material is a shape memory alloy, the phase change temperature is set to 35℃-40℃, and a spring is installed inside the ventilation regulating channel.

[0007] Optionally, the support frame adopts a universal joint that can rotate in all directions, and telescopic dampers are installed at both ends of the support frame, with the telescopic dampers connecting the outer layer of the fabric cover and the inner layer of the fabric cover.

[0008] Optionally, the micro-rotating mechanism includes a micro-motor, a driving wheel, a driven rod, a rotating rod, and a base. The rotating rod is mounted on the base. Multiple micro-motors are arranged in a circular array on the base with the rotating rod as the center. The driving wheel is rotatably connected to the micro-motor. The bottom of the driven rod is gear-shaped and meshes with the driving wheel and is rotatably connected to the rotating rod. One end of the rotating rod is connected to the top of the driven rod, and the other end of the rotating rod is connected to a turntable. A reflector is fixed on the turntable.

[0009] Optionally, multiple mounting seats are arranged in an array on the inner side of the inner layer of the cover, and suction cups are rotatably connected to the mounting seats.

[0010] Optionally, the outer and inner layers of the fabric cover are provided with an array of drawstring holes along their wide edges.

[0011] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0012] This invention achieves a synergistic effect of low thermal radiation and adaptive temperature control. Through the array design of square phase change material units and cross-shaped elastic connectors in the temperature control interlayer, uniform temperature control is achieved across the entire fabric covering. The phase change material can buffer temperature changes by absorbing or releasing heat when the temperature fluctuates. In conjunction with the micro-rotating mechanism and reflective sheet on the outer layer of the fabric cover, the reflective sheet can dynamically optimize the thermal radiation reflection efficiency by adjusting the angle under the trigger of the temperature sensor, significantly reducing the thermal radiation intensity on the surface of the fabric covering.

[0013] This invention improves structural stability and gap controllability. The support frame adopts a universal joint structure with telescopic damping at both ends. The universal joint can adapt to the deformation requirements of the curved surface and corners of the fuselage through omnidirectional rotation, while the telescopic damping buffers the stress generated by the thermal expansion and contraction of the fabric, avoiding local tearing. At the same time, the combination of universal joint and telescopic damping can stably maintain the air gap between the outer and inner layers of the fabric cover, solving the problem of unstable gap in rigid frame design and further reducing the range of gap fluctuation.

[0014] This invention enables automatic ventilation adjustment to enhance environmental adaptability. The rectangular ventilation channel is made of shape memory alloy material, which can expand and contract autonomously at a phase change temperature of 35℃-40℃. Combined with the internal spring structure, the channel expands at high temperatures to increase ventilation and contracts at low temperatures to reduce heat loss, thus achieving adaptive adjustment of ventilation and enabling the fabric to maintain stable performance in environments ranging from -30℃ to 80℃.

[0015] This invention optimizes installation adaptability. The suction cup and rotating mounting base design of the inner layer of the cover can flexibly adapt to different machine body surfaces, enhancing the stability of the fit between the cover and the machine body. Attached Figure Description

[0016] Figure 1 This is a front view of the overall structure of this utility model;

[0017] Figure 2 This is a bottom view of the overall structure of this utility model;

[0018] Figure 3 This is a front view of the inner side of the outer layer of the fabric cover in this utility model;

[0019] Figure 4 This is a schematic diagram of the micro-rotating mechanism in this utility model;

[0020] Figure 5 This is a schematic diagram of the supporting frame structure in this utility model;

[0021] In the picture:

[0022] 1. Outer layer of fabric cover; 2. Inner layer of fabric cover; 3. Phase change material unit; 4. Elastic connector; 5. Support frame; 6. Ventilation adjustment channel; 7. Miniature rotating mechanism; 8. Reflector; 9. Spring; 10. Telescopic damping; 11. Miniature motor; 12. Drive wheel; 13. Driven rod; 14. Rotating rod; 15. Base; 16. Rotating rod; 17. Turntable; 18. Mounting base; 19. Suction cup; 20. Pull cord hole; 21. Temperature sensor. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] like Figures 1 to 5 As shown, this utility model provides an adaptive low-heat radiation fabric for aircraft, characterized in that it includes an outer fabric layer 1, an inner fabric layer 2, and a temperature-controlled interlayer. The outer fabric layer 1 and the inner fabric layer 2 are rectangular. The temperature-controlled interlayer is disposed inside the outer fabric layer 1. The temperature-controlled interlayer includes a phase change material unit 3 and an elastic connector 4. The phase change material unit 3 and the elastic connector 4 are arrayed and fixed on the inner side of the outer fabric layer 1. The phase change material unit 3 is square. The elastic connector 4 is cross-shaped and connects to the phase change material unit 3. Multiple support frames 5 are provided at the connection gaps of the elastic connector 4. The outer fabric layer 1 and the inner fabric layer 2 are interconnected by ventilation adjustment channels 6. The ventilation adjustment channels 6 are arrayed and fixed on the long side of the outer fabric layer 1 and the inner fabric layer 2. A micro-rotating mechanism 7 and a reflector 8 are installed on the outer side of the outer fabric layer 1. A temperature sensor 21 is provided on the outer fabric layer 1.

[0025] Specifically, this invention achieves a combination of low thermal radiation and adaptive temperature control. Through the array design of square phase change material units 3 and cross-shaped elastic connectors 4 in the temperature control interlayer, uniform temperature control is achieved across the entire fabric covering. The phase change material can buffer temperature changes by absorbing or releasing heat when the temperature fluctuates. In conjunction with the micro-rotating mechanism 7 and reflective sheet 8 on the outer layer of the fabric cover, under the triggering of the temperature sensor 21, the reflective sheet 8 can dynamically optimize the thermal radiation reflection efficiency by adjusting the angle, significantly reducing the thermal radiation intensity on the surface of the fabric covering.

[0026] The ventilation regulating channel 6 is configured as a rectangular tube and is made of shape memory alloy. The phase change temperature is set to 35℃-40℃. A spring 9 is installed inside the ventilation regulating channel 6.

[0027] Specifically, this utility model can realize automatic ventilation adjustment to enhance environmental adaptability. The rectangular tube-shaped ventilation adjustment channel 6 is made of shape memory alloy material, which can expand and contract autonomously at a phase change temperature of 35℃-40℃. With the internal spring 9 structure, the channel expands at high temperatures to increase ventilation volume and contracts at low temperatures to reduce heat loss, realizing adaptive adjustment of ventilation volume, so that the covering cloth can maintain stable performance in an environment of -30℃ to 80℃.

[0028] The support frame 5 adopts a universal joint that can rotate in all directions. The support frame 5 is equipped with telescopic dampers 10 at both ends, and the telescopic dampers 10 connect the outer layer 1 and the inner layer 2 of the fabric cover.

[0029] Specifically, this utility model can improve structural stability and gap controllability. The support frame 5 adopts a universal joint structure and is equipped with telescopic dampers 10 at both ends. The universal joint can adapt to the deformation requirements of the curved surface and corners of the body through all-round rotation, and the telescopic dampers 10 can buffer the stress generated by the thermal expansion and contraction of the fabric to avoid local tearing. At the same time, the combination of universal joint and telescopic damper 10 can stably maintain the air gap between the outer layer 1 and the inner layer of the fabric cover, solve the problem of unstable gap in rigid frame design, and further reduce the range of gap fluctuation.

[0030] The micro-rotating mechanism 7 includes a micro motor 11, a driving wheel 12, a driven rod 13, a rotating rod 14, and a base 15. A rotating rod 16 is provided on the base 15. Multiple micro motors 11 are provided and arranged in a circular array on the base 15 with the rotating rod 16 as the center. The driving wheel 12 is rotatably connected to the micro motor 11. The bottom of the driven rod 13 is gear-shaped and meshes with the driving wheel 12 and is rotatably connected to the rotating rod 16. One end of the rotating rod 14 is connected to the top of the driven rod 13, and the other end of the rotating rod 14 is connected to a turntable 17. A reflector 8 is fixed on the turntable 17.

[0031] Multiple mounting bases 18 are arranged in an array on the inner side of the inner layer 2 of the fabric cover, and suction cups 19 are rotatably connected to the mounting bases 18.

[0032] Specifically, this utility model can achieve optimized installation adaptability. The suction cup 19 and rotating mounting base 18 of the inner layer of the cover can be flexibly adapted to different machine body surfaces, enhancing the adhesion stability between the cover and the machine body.

[0033] The outer layer 1 and the inner layer 2 of the fabric cover are provided with an array of drawstring holes 20 along their wide edges.

[0034] The working principle and usage process of this utility model are as follows: During use, the suction cup 19 of the inner layer of the cover adheres to the machine body, and the pull rope through the pull rope hole 20 secures the cover, ensuring stable coverage of the machine body. The temperature sensor 21 monitors the ambient temperature in real time, triggering coordinated operation of various structures: At high temperatures, the phase change material unit 3 of the temperature control layer absorbs heat to buffer the temperature, the shape memory alloy ventilation regulating channel 6 (35℃-40℃ phase change) expands due to temperature, and the internal spring 9 assists in increasing ventilation; simultaneously, the micro-rotating mechanism 7 drives the reflector 8 to rotate, enhancing heat radiation reflection. At low temperatures, the phase change material unit 3 releases heat to maintain insulation, the ventilation channel contracts to reduce heat loss, and the reflector 8 adjusts its angle to reduce heat dissipation. The universal joint of the supporting frame 5 adapts to the curved surface of the machine body, and the telescopic damping 10 buffers deformation stress, maintaining a stable gap between the inner and outer layers of the cover, achieving adaptive low-heat radiation protection across the entire temperature range.

[0035] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0036] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An aircraft low-heat-radiation adaptive fabric, characterized in that, The device includes an outer cloth cover (1), an inner cloth cover (2), and a temperature control interlayer. The outer cloth cover (1) and the inner cloth cover (2) are rectangular. The temperature control interlayer is disposed inside the outer cloth cover (1). The temperature control interlayer includes a phase change material unit (3) and an elastic connector (4). The phase change material unit (3) and the elastic connector (4) are arrayed and fixed on the inner side of the outer cloth cover (1). The phase change material unit (3) is square, and the elastic connector (4) is cross-shaped. Furthermore, the phase change material unit (3) is connected, and multiple support frames (5) are provided at the connection gap of the elastic connector (4). The outer layer (1) and the inner layer (2) of the cloth cover are connected to each other through ventilation adjustment channels (6). The ventilation adjustment channels (6) array is fixed at the long side of the outer layer (1) and the inner layer (2) of the cloth cover. A micro rotating mechanism (7) and a reflective sheet (8) are installed on the outer side of the outer layer (1). A temperature sensor (21) is provided on the outer layer (1).

2. The aircraft low-heat-radiation adaptive fabric according to claim 1, characterized in that, The ventilation regulating channel (6) is configured as a rectangular tube and the material is a shape memory alloy. The phase change temperature is set to 35℃-40℃. A spring (9) is installed inside the ventilation regulating channel (6).

3. The aircraft low-heat-radiation adaptive fabric according to claim 1, characterized in that, The support frame (5) adopts a universal joint that can rotate in all directions. The support frame (5) is equipped with telescopic dampers (10) at both ends. The telescopic dampers (10) connect the outer layer (1) of the cover and the inner layer (2) of the cover.

4. The aircraft low-heat-radiation adaptive fabric according to claim 1, characterized in that, The micro-rotating mechanism (7) includes a micro motor (11), a driving wheel (12), a driven rod (13), a rotating rod (14), and a base (15). A rotating rod (16) is provided on the base (15). Multiple micro motors (11) are arranged in a circular array on the base (15) with the rotating rod (16) as the center. The driving wheel (12) is rotatably connected to the micro motor (11). The bottom of the driven rod (13) is gear-shaped and meshes with the driving wheel (12) and is rotatably connected to the rotating rod (16). One end of the rotating rod (14) is connected to the top of the driven rod (13), and the other end of the rotating rod (14) is connected to a turntable (17). A reflector (8) is fixed on the turntable (17).

5. The aircraft low-heat-radiation adaptive fabric according to claim 1, characterized in that, Multiple mounting bases (18) are arranged in an array on the inner side of the inner layer (2) of the cloth cover, and suction cups (19) are rotatably connected to the mounting bases (18).

6. The aircraft low-heat-radiation adaptive fabric according to claim 1, characterized in that, Pull cord holes (20) are arranged in an array along the wide edge of the outer layer (1) and inner layer (2) of the fabric cover.

Images