Aircraft emergency slide cover system

Abstract

The present application discloses an emergency escape chute surrounding cloth system for an airplane, which comprises a surrounding cloth connected between a body of the airplane and the escape chute. The surrounding cloth comprises an outer layer and a capsule layer. The outer layer surrounds the capsule layer, and the capsule layer is filled with aerogel particles. The system comprises a gas control device for controlling the flow of gas in the capsule layer relative to the ambient environment. The gas control device is configured to cause the gas in the capsule layer to flow out of the capsule layer to compress the capsule layer after the escape chute is deployed. The emergency escape chute surrounding cloth system for an airplane according to the present application utilizes the capsule layer of aerogel particles to adjust the softness and hardness of the surrounding cloth. The surrounding cloth is soft enough when the escape chute is stowed, and the surrounding cloth has sufficient hardness to support the escape chute after the escape chute is deployed.

Description

Technical Field

[0001] This invention relates to the field of aircraft cabin equipment, and more specifically, to an aircraft emergency slide enclosure system. Background Technology

[0002] Emergency slides are essential auxiliary equipment for emergency evacuation from civil aircraft. Their main structure is an inflatable airbag with a central slide track. The airbag is supplied with gas from high-pressure cylinders. To meet the requirements of evacuation in dark environments, emergency slides are also equipped with power supplies and lights, typically powered by battery packs. Before deployment, the airbag is empty. Figure 1 As shown, slide 1 is installed in the aircraft cabin in a packaged state; after being thrown and deployed, the gas in the high-pressure cylinder enters the airbag, forming an evacuation channel from the aircraft cabin to the ground.

[0003] One end of the apron is attached to the slide, and the other end is wrapped around the pre-positioning rod. For example... Figure 2 As shown, when the protective covering 2 is pre-positioned along with the slide, the pre-positioning rod wrapped in the covering will be locked in the aircraft fuselage floor clamps. At this time, the covering serves to connect the aircraft and the slide airbag. During emergency evacuation, personnel can evacuate from the aircraft cabin to the ground along the slide. When the slide is released from its pre-positioning position, the pre-positioning rod wrapped in the covering will leave the floor clamps and retract to the bottom of the cabin door. At this time, the covering no longer serves to connect the aircraft and the slide airbag. In summary, the protective covering is mainly used in two scenarios: first, to establish the connection between the airbag and the aircraft when the slide is needed for emergency evacuation; and second, to move along with the pre-positioning rod during the pre-positioning and release of the aircraft when the slide is not in use.

[0004] Civil aircraft protective covers are typically made of polyurethane tape, which must meet multiple requirements such as being lightweight, high-strength, and flame-retardant. Considering its intended use, the cover material cannot be too soft, especially in windy conditions, where it needs to provide stronger restraint on the slide structure. Insufficient restraint may cause the slide to bend or deflect due to wind before full deployment, preventing evacuation. Conversely, the cover material cannot be too stiff, as its shape changes during the aircraft door's pre-positioning and de-positioning process before deployment; therefore, the cover needs to be relatively flexible to accommodate these shape changes.

[0005] There are two main traditional methods: one is to thicken the material in the areas requiring reinforcement, making the local area harder; the other is to add metal or high-hardness composite material sandwich panels, making the local area harder. Both methods will reduce the smoothness of the slide's pre-positioning / de-positioning. If the hardness is increased too much, it will also affect the slide's packaging.

[0006] Therefore, the existing emergency slide enclosure needs to be improved to adapt to the softness and hardness requirements of different scenarios. Summary of the Invention

[0007] To overcome the shortcomings of the prior art, the present invention provides an aircraft emergency slide enclosure system including an enclosure connected between the aircraft body and the slide. The enclosure includes an outer layer and a bladder layer, the outer layer surrounding the bladder layer, and the bladder layer being filled with aerogel particles. The system includes a gas control device for controlling the flow of gas in the bladder layer relative to the external environment. The gas control device is configured such that when the slide is deployed, the gas control device causes the gas in the bladder layer to flow out of the bladder layer to compress the bladder layer.

[0008] According to another aspect of the invention, the capsule layer comprises a plurality of capsules, each capsule comprising a bag body made of a breathable membrane material and aerogel particles filled in the bag body.

[0009] According to another aspect of the invention, when the airflow in the capsule layer is not flowing out or when the surrounding fabric is closed, the porosity of the aerogel in the capsule is not less than 95%.

[0010] According to another aspect of the invention, the gas control device includes: a sensor for sensing whether an emergency slide has been launched or whether a protective covering has been deployed; a vacuum pump that, when activated after the slide has been launched, draws gas from the bladder layer; and a normally open valve that communicates with the bladder layer and closes when the vacuum pump is activated.

[0011] According to another aspect of the invention, an aircraft emergency slide enclosure system includes a flexible wire connected to a vacuum pump, the flexible wire being embedded in the outer layer of the enclosure.

[0012] According to another aspect of the invention, the sensor includes a wind pressure sensor for sensing external wind pressure, the wind pressure sensor being disposed on the outer layer of the enclosure, and a vacuum pump being activated in a controlled manner when the wind pressure measured by the wind pressure sensor is greater than a set threshold.

[0013] According to another aspect of the invention, the gas control device includes a valve device disposed on the outer layer, the valve device being configured to open as the surrounding fabric unfolds, so as to allow the bladder layer to communicate with external gas.

[0014] According to another aspect of the invention, the valve device includes a valve body and a plug, the valve body having a valve opening formed thereon, the plug being configured to open or close relative to the valve opening, one end of the plug being connected to a surrounding fabric, and the other end of the plug being connected to the valve body of the valve device, the plug being opened when the slide is thrown.

[0015] According to another aspect of the invention, the capsule layer is locally arranged in the surrounding fabric to form a locally reinforced region.

[0016] The aircraft emergency slide enclosure system according to the present invention utilizes the aerogel particle encapsulation layer to adjust the softness and hardness of the enclosure, so that the enclosure is sufficiently soft when the emergency slide is retracted, and has sufficient hardness to provide support after the emergency slide is deployed. Attached Figure Description

[0017] For a more complete understanding of the invention, reference can be made to the following description of exemplary embodiments taken in conjunction with the accompanying drawings, in which:

[0018] Figure 1 The diagram shows the state of the aircraft enclosure when the slide is not deployed.

[0019] Figure 2 The diagram shows the state of the aircraft enclosure when the slide is deployed.

[0020] Figure 3 A schematic diagram of an aircraft emergency slide in the deployment state according to the present invention is shown, including the enclosure system according to the present invention.

[0021] Figure 4 A schematic diagram of a sandwich fabric suitable for an aircraft emergency slide enclosure according to the present invention is shown.

[0022] Figure 5 A schematic diagram of an aerogel bladder suitable for an aircraft emergency slide enclosure according to the present invention is shown.

[0023] Figure 6 A schematic diagram of an aircraft emergency slide enclosure system according to a first embodiment of the present invention is shown.

[0024] Figure 7 It shows Figure 6 The control flowchart of the enclosure control system is shown.

[0025] Figure 8 A schematic diagram of an aircraft emergency slide enclosure system according to a second embodiment of the present invention is shown.

[0026] Figure 9 It shows Figure 8 The diagram shows the aircraft emergency slide enclosure system in its deactivated state.

[0027] Figure 10 It shows Figure 8 The diagram shows the control flow chart of the aircraft emergency slide enclosure system.

[0028] List of reference numerals

[0029] 1 emergency slide

[0030] 2. Enclosure

[0031] 10, 20 enclosure system

[0032] 11. Envelope

[0033] 110 outer layer

[0034] 115 capsule layers

[0035] 116 pouches

[0036] 117 aerogel particles

[0037] 16 prepositioning rods

[0038] 12 vacuum pumps

[0039] 13 Wind pressure sensors

[0040] 14 Normally open valves

[0041] 15 power supply

[0042] 21 Valve Device

[0043] 211 Valve Body

[0044] 212 valve opening

[0045] 213 plug

[0046] 30 cabin doors

[0047] 40 slides Detailed Implementation

[0048] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0049] Figure 3 A schematic diagram of an aircraft emergency slide according to the present invention is shown. The emergency slide 1 is deployed outside the fuselage and in an inflated state. In a preferred embodiment of the present invention, the enclosure system of the emergency slide 1 mainly includes an enclosure 11 and a gas control device for controlling the softness and hardness of the aerogel bladder layer 115 inside the enclosure 11. The enclosure 11 is connected between the fuselage and the slide body 40. Figure 3 As shown, one edge of the enclosure 11 is connected to the fuselage below the aircraft door 30 via a pre-positioning rod 16, and the opposite edge of the enclosure 11 is connected to the upper edge of the slide body 40. The enclosure 11 fills the gap between the slide body 40 and the fuselage, providing an entrance passage connecting the aircraft door 30 and the slide body 40, guiding and supporting passengers, and maintaining the stability of the slide.

[0050] In particular, in the fabric system according to the present invention, the stiffness of the fabric 11 is variable, and the change in stiffness is achieved by the gas control device in the fabric system controlling the inflow and outflow of gas.

[0051] First, refer to Figure 4 and Figure 5 Explain the structure of the surrounding fabric 11. Figure 4 A schematic diagram of the interlayer fabric used to make the sheath 11 is shown. The interlayer fabric making the sheath 11 includes two opposing outer layers 110 and an aerogel bladder layer 115 disposed within the outer layers 110. The outer layers 110 of the sheath can be made of abrasion-resistant materials with a certain mechanical strength. For example, preferably, the outer layers 110 of the sheath can be made of an airtight polyurethane sheet, which is typically composed of a polyurethane coating and a base fabric. Gas can be sealed inside the outer layer of the sheath 11, and the airtightness of the outer layer ensures that gas will not leak out through the gaps between the fibers of the base fabric.

[0052] Figure 5 The structure of the aerogel capsule layer 115 is schematically illustrated. Preferably, the aerogel capsule layer 115 includes a plurality of capsules 116. The capsules 116 are flat and can be made of a breathable but leak-proof film material that prevents leakage of aerogel particles 117. For example, the capsules 116 can be made of flexible TPU (thermoplastic polyurethane elastomer), and then the aerogel particles 117 are filled into these capsules 116, which are then arranged in an array to form the capsule layer 115. There may be a certain spacing between adjacent capsules 116. The capsules 116 can be fixed to the inner surface of the outer layer 110 by stitching or adhesive processes. In other alternative embodiments, a breathable and soft inner layer can also be added specifically for fixing the plurality of capsules 116, and then the inner layer with the capsules 116 fixed thereto is sewn inside the outer layer.

[0053] Preferably, the particle size of the aerogel particles 117 applicable to the present invention can be in the range of 50~200μm, and in the initial state, that is, in the state where the surrounding fabric 11 is closed, the porosity of the aerogel is not less than 95%. The aerogel particles are nanoporous structures made of silica.

[0054] The pleated layer 115 in the sheath 11 can be arranged on a portion of the sheath 11, thereby forming a locally reinforceable region within the sheath 11. For example... Figure 3As shown, the reinforced area of ​​the fabric 11 with the aerogel layer 115 is a rectangular frame, while other areas of the fabric 11 (the middle area and the four sides) do not have the aerogel layer 115. Changes in the amount of gas in the aerogel within the aerogel layer 115 cause changes in the hardness of the fabric 11. When the gas is expelled from the aerogel layer 115, the aerogel particles 117 lose some gas, causing the spacing between the particles to decrease and they to compress each other, making the overall material structure denser and thus harder. When the gas flows back into the aerogel layer 115, the aerogel particles 117 return to their original looser state, and the fabric 11 softens.

[0055] The draping system according to the invention also includes a gas control device for controlling the flow of gas in the bladder layer 115. Figure 6 An aircraft emergency slide enclosure system 10 including a gas control device according to a first embodiment of the present invention is shown. The gas control device includes a vacuum pump 12, a normally open valve 14, and sensors. The power supplies 15 of the various devices in the gas control device can share the existing power supply of the emergency slide. Both the vacuum pump 12 and the normally open valve 14 are gas-flow-through connected to the plenum 115 of the enclosure 11. The vacuum pump 12 is configured to extract gas from the plenum 115. The sensors are used to sense whether the emergency slide is being launched or whether the enclosure is unfolding, thereby controlling the operation of the vacuum pump 12 and the normally open valve 14.

[0056] The sensor is preferably a wind pressure sensor 13 disposed on the surface of the outer layer 110 of the enclosure 11, for sensing changes in external wind pressure. The signal sensed by the wind pressure sensor 13 is used to control the vacuum pump 12 and the normally open valve 14.

[0057] In one embodiment, a normally open wind pressure sensor 13 can be used. When the wind pressure sensed by the wind pressure sensor 13 is greater than a set threshold (e.g., the wind pressure value corresponding to a wind speed of 10 m / s), the wind pressure sensor 13 closes internally, and the entire circuit loop is connected. The current from the power supply 15 flows to the vacuum pump 12 to start the vacuum pump 12 and close the normally open valve 14. When the wind pressure sensed by the wind pressure sensor 13 is not greater than the set threshold, the wind pressure sensor 13 disconnects internally, the circuit loop is broken, the vacuum pump 12 loses its current supply and stops operating, and the normally open valve 14 returns to its normally open state.

[0058] In another alternative embodiment, a controller can be added. The signal from the wind pressure sensor 13 is transmitted to the controller, which controls the vacuum pump 12 and the normally open valve 14 to open / close. When the wind pressure sensed by the wind pressure sensor 13 is greater than a set threshold, the controller controls the normally open valve 14 to close, allowing airflow to flow out of the capsule 115. When the wind pressure sensed by the wind pressure sensor 13 is not greater than the set threshold, the signal from the wind pressure sensor 13 is transmitted to the controller, which controls the vacuum pump 12 to close and the normally open valve 14 to open, allowing airflow to flow into the capsule 115 through the normally open valve 14.

[0059] The wind pressure sensor suitable for this invention can be a piezoelectric wind pressure sensor 13. This sensor utilizes the piezoelectric effect, containing piezoelectric material inside. When subjected to wind pressure, an electric charge is generated on the surface of the material, the amount of which is proportional to the wind pressure. The wind pressure sensor 13 converts the sensed wind pressure into an electrical signal, the voltage or current value of which corresponds to the wind pressure intensity. When the aircraft emergency slide is deployed, the wind pressure sensor 13 is exposed to the external wind field, thereby generating the corresponding signal.

[0060] The wires for transmitting electrical signals connecting the various devices in the gas control device can be built into the outer layer 110 of the cover 11, for example, they can be built into the outer fabric 110. The wires can be flexible wires, so as to transmit signals stably while ensuring that the cover 11 can be folded.

[0061] Figure 7 A control flowchart of the enclosure system 10 according to a first embodiment of the present invention is shown. In an emergency evacuation scenario, when the emergency slide is deployed, the enclosure 11 structure is fully exposed to the external wind field environment. At this time, the wind pressure sensor 13 installed on the enclosure 11 begins to monitor wind pressure changes in real time. When the wind pressure exceeds a preset threshold, the wind pressure sensor 13 immediately triggers a response mechanism: first, it closes the normally open valve 14 to block the gas passage, and simultaneously starts the vacuum pump 12 to quickly extract the gas from the aerogel bladder layer 115. As the gas is extracted, the aerogel particles undergo a phase change, and the enclosure 11 structure gradually hardens, thereby enhancing the structural stability of the enclosure 11 in strong wind environments. If the wind pressure drops to below the safety threshold and remains stable (typically when the slide is moved indoors), the enclosure 11 is no longer exposed to the wind field, and the system immediately opens the normally open valve 14 to restore the gas supply. As the gas is re-injected, the aerogel material returns to its initial state, the enclosure 11 gradually softens, and the slide and enclosure 11 can be retracted, ready for the next use.

[0062] In the first embodiment, the airflow control device is an active airflow control device including a vacuum pump 12. It should be understood that other devices or mechanisms can also be used to control the vacuum pump 12, such as other types of sensors that can detect whether the emergency slide has been launched, such as mechanical position sensors that directly monitor the position of mechanical components linked to the launch of the slide, or pressure sensors that detect whether the interior of the emergency slide is inflated. In addition, the normally open valve 14 can be manually or automatically forced open when the emergency slide needs to be retracted.

[0063] Figure 8 A schematic diagram of an aircraft emergency slide enclosure system 20 according to a second embodiment of the present invention is shown. Figure 9 It shows Figure 8 The diagram shows the aircraft emergency slide enclosure system 20 retracted below the cabin door. The structure of the enclosure 11 in the second embodiment is the same as that in the first embodiment, and will not be described again here.

[0064] The second embodiment's enclosure system 20 employs a passive gas control device. Specifically, the gas control device includes a valve device 21 that is opened as the slide is launched. Figure 8 As shown, a valve device 21 is disposed on the outer layer 110 of the surrounding fabric 11. The valve device 21 includes a valve body 211 and a plug 213. A valve opening 212 is formed on the valve body 211, and the plug 213 is configured to open or close relative to the valve opening 212. One end of the plug 213 is connected to the surrounding fabric 11, and the other end of the plug 213 is connected to the valve body 211. When the slide is in such a state... Figure 9 When the slide is in the retracted state, the plug 213 closes the valve opening 212. When the slide is launched, the surrounding cloth 11 unfolds. The movement of the surrounding cloth 11 pulls one end of the plug 213, causing the plug 213 to move out of its original closed position and opening the valve opening 212. This creates air holes on the outer layer 110 of the surrounding cloth 11. When the airflow outside the surrounding cloth 11 is fast, based on Bernoulli's principle, the faster the flow, the lower the pressure. A pressure difference is formed between the external gas and the gas inside the bladder layer 115, causing some of the gas in the bladder layer 115 to flow out. The structure of the surrounding cloth 11 gradually hardens, enhancing the structural stability of the surrounding cloth 11 in strong wind environments.

[0065] The gas control device of the second embodiment may include a plurality of valve devices 21, which are arranged spaced apart from each other on the outer layer 110 of the cover 11, and the valve openings 212 are all in communication with the inner layer 115 of the cover 11. The provision of a plurality of valve devices 21 can accelerate the speed at which the airflow flows out of the inner layer 115 when the slide is thrown, ensuring that the cover 11 can harden in a short time.

[0066] Figure 10A control flowchart of the enclosure system 20 according to the second embodiment is shown. In an emergency evacuation scenario, when the slide begins to be deployed, the enclosure 11 is fully exposed to the external wind field environment. As the enclosure 11 unfolds, one end of the plug 213 of the valve device 21 is pulled by the enclosure 11, the valve opening 212 is opened, the vent is exposed to the wind field, allowing gas to flow out of the aerogel capsule layer 115. The aerogel material undergoes a phase change, and the structure of the enclosure 11 gradually hardens, thereby enhancing the structural stability of the enclosure 11 in strong wind environments. If the wind pressure drops to below the safety threshold and remains stable (typically when the slide is moved indoors), the enclosure 11 is no longer exposed to the wind field, and the outside gas will flow back to the capsule layer 115 through the valve opening 212. As the gas is re-injected, the aerogel material returns to its initial state, the enclosure 11 gradually softens, and the slide and enclosure 11 can be retracted.

[0067] The aircraft emergency slide enclosure system provided by this invention achieves dynamic adjustment of the enclosure's softness and hardness through an innovative aerogel bladder layer structure and gas control device, significantly improving the safety and reliability during emergency evacuation.

[0068] In other alternative embodiments, the enclosure system may include both the active airflow control device of the first embodiment and the passive airflow control device of the second embodiment. Having two sets of passive airflow control devices provides a dual protection mechanism, ensuring that hardening can still be achieved through Bernoulli's principle of the valve device in the event of power failure, thus improving the reliability of the enclosure system.

[0069] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit them. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the above embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. An aircraft emergency slide enclosure system, the system comprising an enclosure connected between the aircraft body and the slide. characterized in that The surrounding fabric includes an outer layer and a capsule layer, the outer layer surrounding the capsule layer, and the capsule layer being filled with aerogel particles. The system includes a gas control device for controlling the flow of gas in the capsule layer relative to the external environment. The gas control device is configured such that, when the slide is launched, the gas control device causes the gas in the capsule layer to flow out of the capsule layer to compress the capsule layer. The capsule layer includes multiple capsules, each capsule comprising a bag body made of a breathable membrane material and aerogel particles filled in the bag body. When the airflow in the capsule layer is not flowing out or when the surrounding fabric is retracted, the porosity of the aerogel particles in the capsule is not less than 95%.

2. The aircraft emergency slide enclosure system as described in claim 1, characterized in that, The gas control device includes: The sensor is used to sense whether the emergency slide has been launched or whether the enclosure has been unfolded; A vacuum pump, activated when the slide is launched, draws gas from the capsule layer; and A normally open valve is connected to the bladder layer, and the normally open valve closes when the vacuum pump is started.

3. The aircraft emergency slide enclosure system as described in claim 2, characterized in that, The aircraft emergency slide enclosure system includes flexible wires connected to the vacuum pump, the flexible wires being embedded in the outer layer of the enclosure.

4. The aircraft emergency slide enclosure system as described in claim 2, characterized in that, The sensor includes a wind pressure sensor for sensing external wind pressure. The wind pressure sensor is disposed on the outer layer of the enclosure. When the wind pressure measured by the wind pressure sensor is greater than a set threshold, the vacuum pump is started in a controlled manner.

5. The aircraft emergency slide containment system as described in claim 1, characterized in that, The gas control device includes a valve device disposed on the outer layer, the valve device being configured to open as the covering fabric unfolds, thereby allowing the bladder layer to communicate with external gas.

6. The aircraft emergency slide containment system as described in claim 5, characterized in that, The valve device includes a valve body and a plug. A valve opening is formed on the valve body, and the plug is configured to open or close relative to the valve opening. One end of the plug is connected to the surrounding fabric, and the other end of the plug is connected to the valve body of the valve device. When the slide is thrown, the plug is opened.

7. The aircraft emergency slide containment system as described in claim 1, characterized in that, The capsule layer is locally arranged within the surrounding fabric to form a locally reinforced area.

8. The aircraft emergency slide enclosure system as described in claim 1, characterized in that, The aerogel particles include silica aerogel particles.

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