Emergency exhaust device of aerostat and aerostat with emergency exhaust device

Abstract

The invention provides an emergency exhaust device of an aerostat and the aerostat with the emergency exhaust device, and the emergency exhaust device comprises an exploder which is installed on the top surface of a bag body of the aerostat, and the bag body is filled with floating gas; the cutting rope is connected with the exploder, the interior of the cutting rope is filled with combustible materials so that the cutting rope can be detonated after the exploder is detonated, the cutting rope cuts the bag body under the action of the blasting force, the buoyancy lift gas is discharged from the interior of the bag body, and therefore the aerostat falls to the ground.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aerostats, and more particularly, to an emergency exhaust device of an aerostat and an aerostat having the emergency exhaust device. Background Art

[0002] Aerostats generally refer to soft-structured aircraft that are lighter than air and rely on atmospheric buoyancy to rise. Aerostats are composed of airbags made of polymer composite materials and various equipment and payloads arranged on the airbag body. The airbag is filled with a buoyancy gas with a density lower than that of air. The density difference between the gas inside and outside the airbag provides the buoyancy of the aerostat, thereby completing the launch of the aerostat. Aerostats generally include balloons and airships. Aerostats take off from the ground, and after reaching a certain height, they begin to stay at high altitudes, cruise in the region, and conduct scientific experiments. Depending on the type of aerostat and the test requirements, the altitude of the aerostat is generally 0-30km, generally in the troposphere or stratosphere. At this altitude, there are many other aircraft performing high-altitude operations. If an aerostat loses control unexpectedly, it needs emergency treatment to land quickly to avoid interference with other aircraft and prevent threats to the flight safety of other aircraft. Therefore, the aerostat itself must be equipped with an emergency response processing device. When it loses control or an accident occurs, the emergency response processing device can be used to quickly discharge the buoyancy gas in the bladder, allowing the aerostat to land quickly, keeping the aerostat under control at all times and minimizing risks.

[0003] At present, emergency response processing devices include large-caliber or large number of exhaust valves on the bladder. In an emergency, the valve is opened to discharge the floating gas in the bladder. However, the exhaust area of ​​the exhaust valve is small and the exhaust speed is slow, which cannot achieve the purpose of quickly exhausting the airship to the ground. In addition, since the airship resides in the troposphere or stratosphere, the ambient temperature, atmospheric pressure and solar radiation in this area are low. Long-term low temperature and low pressure will affect the electronic components in the exhaust valve, and the lubrication of the transmission mechanism in the exhaust valve will also be affected. There is a risk of leakage in the exhaust valve, which cannot play the role of safety control emergency. Summary of the invention

[0004] To solve at least one of the technical problems in the prior art, the embodiments of the present disclosure provide an emergency exhaust device for an aerostat and an aerostat having the emergency exhaust device, which can expand the exhaust area, increase the exhaust speed, and achieve rapid landing of the aerostat.

[0005] An embodiment of the present disclosure provides an emergency exhaust device for an airship, comprising: a detonator installed on the top surface of the bladder of the airship, the bladder being filled with buoyancy gas; a cutting rope connected to the detonator, the interior of the cutting rope being filled with combustibles to detonate after the detonator is detonated, the cutting rope cuts the bladder under the action of the explosive force, so that the buoyancy gas is discharged from the interior of the bladder, thereby causing the airship to land.

[0006] According to some embodiments of the present disclosure, a support surface is provided on the top surface of the capsule, and the detonator comprises: a mounting frame mounted on the support surface; an igniter provided on the mounting frame, and the igniter detonates in response to an electric current input from the outside.

[0007] According to some embodiments of the present disclosure, the cutting rope includes: a rope body connected to one end of the igniter; a cutting portion arranged on a side of the rope body close to the bag body, and the cutting portion is configured to have a containing space to contain the combustible material; wherein, after the igniter ignites the combustible material, the cutting portion cuts the bag body under the action of the explosive force.

[0008] According to some embodiments of the present disclosure, the rope body is made of any one of silver and lead.

[0009] According to some embodiments of the present disclosure, the cutting rope forms a preset pattern on the support surface, so that after the cutting portion is detonated, the capsule is cut along the edge of the preset pattern.

[0010] According to some embodiments of the present disclosure, the above-mentioned preset graphic is any one of a circle, a triangle and a polygon.

[0011] According to some embodiments of the present disclosure, the emergency exhaust device of the aerostat further includes: a plurality of installation clamps arranged at intervals on the support surface, the plurality of installation clamps being configured to fix the cutting rope on the support surface so that the cutting portion fits the support surface.

[0012] According to some embodiments of the present disclosure, the detonator further includes: a short-circuit protector connected to the other end of the igniter, the short-circuit protector being configured to disconnect or connect the igniter by plugging in or separating the igniter; wherein, when the airship is transported, the short-circuit protector is plugged in with the igniter to short-circuit the igniter; and when the airship is in working condition, the short-circuit protector is separated from the igniter to connect the igniter to an external electrical connection component, thereby allowing the igniter to receive the current.

[0013] According to some embodiments of the present disclosure, the short-circuit protector includes a limiter, and the limiter is snap-connected to the igniter.

[0014] According to some embodiments of another aspect of the present disclosure, there is provided an airship with an emergency exhaust device, comprising: a bladder filled with buoyancy gas; the emergency exhaust device of the airship arranged on the top surface of the bladder; a pod installed below the bladder; and an electrical connection assembly arranged in the pod to supply power to the emergency exhaust device of the airship.

[0015] According to an emergency exhaust device of an airship and an airship having the emergency exhaust device according to an embodiment of the present disclosure, a detonator is installed on the top surface of the bladder of the airship, the bladder is filled with buoyancy gas, a cutting rope is connected to the detonator, the interior of the cutting rope is filled with combustible materials to detonate after the detonator is detonated, and the cutting rope cuts the bladder under the action of the explosive force, so that the buoyancy gas is discharged from the interior of the bladder, which can expand the exhaust area, increase the exhaust speed, and realize the rapid landing of the airship. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 is a side view of a conventional emergency response processing device;

[0017] Figure 2 is a perspective view of an emergency exhaust device of an aerostat according to an exemplary embodiment of the present disclosure;

[0018] Figure 3 is a schematic diagram of the installation position of an emergency exhaust device on the bladder of an aerostat according to an exemplary embodiment of the present disclosure;

[0019] Figure 4 is a cross-sectional view of a cutting cable located on a bladder according to an exemplary embodiment of the present disclosure;

[0020] Figure 5 is a top view of a cutting rope in a circle according to an exemplary embodiment of the present disclosure.

[0021] In the drawings, the meanings of the reference numerals are as follows:

[0022] 100. Valve body;

[0023] 200, valve cover;

[0024] 300. Electric control unit;

[0025] 400, tie rod;

[0026] 1. Short circuit protector;

[0027] 2. Ignition device;

[0028] 3. Mounting frame;

[0029] 4. Cutting rope;

[0030] 41. Rope body;

[0031] 42. Cutting part;

[0032] 43. Combustibles;

[0033] 5. Install the fixture;

[0034] 6. Cyst;

[0035] A. Support surface. DETAILED DESCRIPTION

[0036] Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the present disclosure. In the following detailed description, for ease of explanation, many specific details are set forth to provide a comprehensive understanding of the embodiments of the present disclosure. However, it is apparent that one or more embodiments may also be implemented without these specific details. In addition, in the following description, descriptions of known structures and technologies are omitted to avoid unnecessary confusion of the concepts of the present disclosure.

[0037] The terms used herein are only for describing specific embodiments and are not intended to limit the present disclosure. The terms "comprise", "include", etc. used herein indicate the existence of the features, steps, operations and / or components, but do not exclude the existence or addition of one or more other features, steps, operations or components.

[0038] All terms (including technical and scientific terms) used herein have the meanings commonly understood by those skilled in the art unless otherwise defined. It should be noted that the terms used herein should be interpreted as having a meaning consistent with the context of this specification and should not be interpreted in an idealized or overly rigid manner.

[0039] In the case of using expressions such as "at least one of A, B, and C, etc.", it should generally be interpreted in accordance with the meaning of the expression generally understood by those skilled in the art (for example, "a system having at least one of A, B, and C" should include but is not limited to a system having A alone, B alone, C alone, A and B, A and C, B and C, and / or A, B, C, etc.). In the case of using expressions such as "at least one of A, B, or C, etc.", it should generally be interpreted in accordance with the meaning of the expression generally understood by those skilled in the art (for example, "a system having at least one of A, B, or C" should include but is not limited to a system having A alone, B alone, C alone, A and B, A and C, B and C, and / or A, B, C, etc.).

[0040] Figure 1 It is a side view of a conventional emergency response processing device.

[0041] The traditional emergency response device is an exhaust valve, such as Figure 1 As shown, the exhaust valve comprises a valve body 100, a valve cover 200, an electric control unit 300 and a pull rod 400. The exhaust valve relies on the electric control unit 300 to drive the pull rod 400 to open and close the valve. When an emergency occurs, the electric control unit 300 receives an emergency processing signal, and the electric control unit 300 drives the pull rod 400 to move. The pull rod 400 and the valve cover 200 are fixedly connected. Under the action of the driving force, the valve cover 200 moves away from the valve body 100, the exhaust valve opens, the buoyant gas is discharged, and the aerostat descends.

[0042] However, there are two main problems with this exhaust valve. On the one hand, the exhaust area of ​​the exhaust valve is small and the weight of the exhaust valve is large. Since the exhaust valve contains many electric units and metal structures, the valve body, transmission mechanism, sealing mechanism, support mechanism, opening and closing mechanism, etc. are all composed of metal parts. The structure and principle are similar to those of industrial electric valves. An exhaust valve weighing about 8kg has an exhaust area of ​​only 300cm 2, there are problems such as heavy weight, small exhaust area, slow exhaust speed, slow landing speed of the airship, and long landing time of the airship. It is impossible to achieve the purpose of rapid exhaust and landing of the airship, with poor safety and narrow application. On the other hand, the exhaust valve has poor reliability and there is a risk of leakage. Since the aerostat resides in the troposphere or stratosphere, the ambient temperature, atmospheric pressure and solar radiation in this area are low. Long-term low temperature and low pressure will affect the electronic components in the exhaust valve, the lubrication of the transmission mechanism will also be affected, the rubber material will age and become brittle, and the overall sealing performance will be greatly reduced. The exhaust valve is exposed to the air for a long time and will encounter rain and snow. Once ice or movement is stuck, the reliability of the exhaust valve cannot be guaranteed. The exhaust valve relies on rubber and other materials for sealing. In severe weather conditions, the exhaust valve cannot be opened and cannot play a role in safety control and emergency response.

[0043] In order to solve the problems of small exhaust area, slow exhaust speed and exhaust valve leakage, according to the inventive concept of one aspect of the present disclosure, a detonator is installed on the top surface of the bladder of the airship, the bladder is filled with buoyancy gas, the cutting rope is connected to the detonator, the interior of the cutting rope is filled with combustible materials to detonate after the detonator is detonated, and the cutting rope cuts the bladder under the action of the blasting force, so that the buoyancy gas is discharged from the interior of the bladder, which can expand the exhaust area, increase the exhaust speed, and realize the rapid landing of the airship.

[0044] Figure 2 is a perspective view of an emergency exhaust device of an aerostat according to an exemplary embodiment of the present disclosure.

[0045] According to an embodiment of the present disclosure, an emergency exhaust device for an aerostat is provided, such as Figure 2 As shown, it includes a detonator and a cutting rope 4. The detonator is installed on the top surface of the capsule 6 of the aerostat, and the capsule 6 is filled with buoyancy gas. The cutting rope 4 is connected to the detonator, and the interior of the cutting rope 4 is filled with a combustible 43 to be detonated after the detonator is detonated. The cutting rope 4 cuts the capsule 6 under the action of the explosive force, so that the buoyancy gas is discharged from the interior of the capsule 6, thereby causing the aerostat to land.

[0046] According to an embodiment of the present disclosure, the buoyancy gas is a gas with a density less than that of air, such as helium.

[0047] According to the embodiments of the present disclosure, the detonator is a blunt detonator, which meets the relevant standard of 1A1W5min non-fire, the detonation mode of the detonator is current detonation, the detonation current is not less than 5A, and the self-resistance of the detonator is 1Ω.

[0048] According to an embodiment of the present disclosure, the cutting rope 4 is sealed and fixed to the detonator, and the interior of the cutting rope 4 is filled with a combustible material 43, which may be gunpowder.

[0049] According to an embodiment of the present disclosure, a detonator is installed on the top surface of the capsule 6 of the airship, the capsule 6 is filled with buoyancy gas, the cutting rope 4 is connected to the detonator, the interior of the cutting rope 4 is filled with combustible material 43, so as to be detonated under the conduction action of the detonator, and the cutting rope 4 cuts the capsule 6 under the action of the explosive force, so that the buoyancy gas is discharged from the interior of the capsule 6, which can expand the exhaust area, increase the exhaust speed, and realize the rapid landing of the airship.

[0050] Figure 3 It is a schematic diagram of the installation position of the emergency exhaust device on the bladder of the aerostat according to an exemplary embodiment of the present disclosure.

[0051] According to the embodiments of the present disclosure, Figure 3 As shown, the top surface of the capsule 6 is provided with a support surface A, and the detonator comprises a mounting frame 3 and an igniter 2, wherein the mounting frame 3 is mounted on the support surface A. The igniter 2 is arranged on the mounting frame 3, and the igniter 2 detonates in response to an electric current input from the outside.

[0052] According to an embodiment of the present disclosure, the connection between the mounting frame 3 and the support surface A may be threaded or riveted to ensure the stability of the mounting frame 3 and the support surface A.

[0053] In an illustrative embodiment, a through hole is provided on the mounting frame 3, and the mounting frame 3 is fixed on the supporting surface A by screws and bolts.

[0054] Figure 4 is a cross-sectional view of a cutting cable located on a bladder according to an exemplary embodiment of the present disclosure.

[0055] According to the embodiments of the present disclosure, Figure 4 As shown, the cutting rope 4 includes a rope body 41 and a cutting portion 42. The rope body 41 is connected to one end of the igniter 2. The cutting portion 42 is arranged on a side of the rope body 41 close to the capsule 6, and the cutting portion 42 is configured to have a receiving space to receive the combustible material 43. After the igniter 2 ignites the combustible material 43, the cutting portion 42 cuts the capsule 6 under the action of the blasting force.

[0056] According to the embodiment of the present disclosure, the cutting rope 4 is a disposable pyrotechnic product, and there are no electronic components inside the cutting rope 4. After the igniter 2 ignites the combustible material 43, an explosive force is generated, and the explosive force acts in the direction of the capsule 6. The cutting part 42 cuts the capsule 6 under the action of the explosive force. Exhausting the capsule 6 in this way reduces the weight of the emergency exhaust device (the weight of the emergency exhaust device is approximately 200g). It is simple and reliable, can be started at any time, has a fast response speed, and a long service life. It can quickly release the buoyant gas in the capsule 6 to achieve the timely landing of the aerostat. In addition, the cutting rope 4 is not affected by the height of the troposphere or stratosphere and the low temperature and low pressure environment, can adapt to various severe weather conditions, has low energy consumption, and always keeps the aerostat test under control, reducing the test risk to a minimum.

[0057] According to an embodiment of the present disclosure, the rope body 41 is made of any one of silver and lead.

[0058] According to an embodiment of the present disclosure, the material of the rope body 41 is preferably silver, which can enhance the flexibility of the rope body 41 .

[0059] According to an embodiment of the present disclosure, the cutting rope 4 forms a preset pattern on the support surface A, so that after the cutting portion 42 is detonated, the capsule 6 is cut along the edge of the preset pattern.

[0060] According to the embodiments of the present disclosure, the selected position of the support surface A is preferably the highest point on the top of the capsule 6. Since the buoyant gas in the capsule 6 rises naturally, it will gather at the top of the capsule 6. The pressure at the highest point on the top of the capsule 6 is the largest. When the detonator detonates the combustible material 43 in the cutting portion 42, under the action of the blasting force, the cutting portion 42 cuts the capsule 6 along the edge of a preset pattern, and the buoyant gas is discharged from the inside of the capsule 6. Due to the natural diffusion and convection of gas molecules, the buoyant gas gathered at the highest point on the top of the capsule 6 will first move to the outside of the capsule 6 due to the pressure difference, and the exhaust speed is the fastest. Selecting the position of the support surface A at the highest point on the top of the capsule 6 can quickly and effectively discharge the buoyant gas from the capsule 6.

[0061] According to an embodiment of the present disclosure, the support surface A may also be selected to be located at a position close to the highest point of the top of the capsule 6 .

[0062] According to an embodiment of the present disclosure, the length of the cutting wire 4 is determined based on the exhaust area of ​​the buoyancy gas and the flying altitude of the aerostat.

[0063] According to an embodiment of the present disclosure, the preset shape is any one of a circle, a triangle and a polygon.

[0064] According to an embodiment of the present disclosure, the polygon may be any one of a square, a rectangle, a pentagon, and a hexagon.

[0065] According to the embodiment of the present disclosure, the cutting rope 4 is enclosed into a closed shape, which can increase the discharge area of ​​the buoyancy gas, increase the discharge speed of the buoyancy gas, and achieve rapid landing of the aerostat.

[0066] Figure 5 is a top view of a cutting rope in a circle according to an exemplary embodiment of the present disclosure.

[0067] According to the embodiments of the present disclosure, Figure 5 As shown, the preset pattern is preferably a circle, and the diameter of the circle is preferably 3m. When the length of the cutting rope 4 is a fixed value, the cutting rope 4 is enclosed in a circle. When the detonator detonates the combustible material 43 in the cutting part 42, under the action of the blasting force, the area of ​​the capsule 6 cut by the cutting part 42 is the largest. If the preset pattern is a polygon, the area of ​​the capsule 6 cut by the cutting part 42 is smaller than when the preset pattern is a circle. If the preset pattern is a triangle, the area of ​​the capsule 6 cut by the cutting part 42 is smaller than when the preset pattern is a polygon, that is, when the length of the cutting rope 4 is a fixed value, the area of ​​the triangle is the smallest.

[0068] According to the embodiments of the present disclosure, Figure 5 As shown, the emergency exhaust device of the aerostat further comprises a plurality of mounting fixtures 5. The plurality of mounting fixtures 5 are arranged on the support surface A at intervals, and the plurality of mounting fixtures 5 are configured to fix the cutting rope 4 on the support surface A so that the cutting portion 42 fits the support surface A.

[0069] According to an embodiment of the present disclosure, the connection between the multiple installation fixtures 5 and the support surface A can be threaded, riveted or bonded to ensure the stability of the multiple installation fixtures 5 and the support surface A.

[0070] In an illustrative embodiment, each mounting fixture 5 is provided with a mounting hole, and each mounting fixture 5 is fixed on the supporting surface A by screws and bolts.

[0071] According to the embodiment of the present disclosure, a plurality of mounting clamps 5 are arranged at intervals on the support surface A, and the cutting rope 4 is fixed on the support surface A by using the plurality of mounting clamps 5. There is no need to open the surface of the bladder 6, and no impact is caused on the material of the bladder 6. It can ensure that the bladder 6 of the airship maintains good sealing, which is conducive to the long-term airborne stay of the airship.

[0072] According to an embodiment of the present disclosure, the detonator further includes a short-circuit protector 1, which is connected to the other end of the igniter 2, and the short-circuit protector 1 is configured to disconnect or connect the igniter 2 by plugging or separating the igniter 2. When the aerostat is transported, the short-circuit protector 1 is plugged into the igniter 2 to short-circuit the igniter 2. When the aerostat is in operation, the short-circuit protector 1 is separated from the igniter 2 to connect the igniter 2 to an external electrical connection component, so that the igniter 2 receives current.

[0073] According to the embodiments of the present disclosure, the short-circuit protector 1 can monitor the current in the circuit in real time and can identify abnormal situations. When transporting or storing the aerostat, the short-circuit protector 1 is plugged into the igniter 2 to short-circuit the internal circuit of the igniter 2, and the circuit is disconnected in time to prevent the igniter 2 from being detonated due to electrostatic interference or erroneous operation, thereby protecting the igniter 2 and avoiding potential fire risks or electrical failures. When the aerostat is in a working state during a formal test, the short-circuit protector 1 is separated from the igniter 2, so that the igniter 2 is connected to the external electrical connection component, so that the igniter 2 receives current and detonates.

[0074] According to the embodiments of the present disclosure, the short-circuit protector 1 and the igniter 2 can be locked by means of a threaded connection, a wedge connection or a snap connection.

[0075] According to the embodiment of the present disclosure, if the short-circuit protector 1 and the igniter 2 are locked by threaded connection, the operator needs to rotate the short-circuit protector 1 so that the external thread set on the surface of the short-circuit protector 1 is engaged with the internal thread of the igniter 2, thereby achieving a tight connection between the short-circuit protector 1 and the igniter 2. The operator rotates the short-circuit protector 1 in the opposite direction to separate the short-circuit protector 1 from the igniter 2.

[0076] According to an embodiment of the present disclosure, if the short-circuit protector 1 and the igniter 2 are locked by a wedge-shaped connection, when the operator inserts the short-circuit protector 1 into the igniter 2, the wedge-shaped mechanism will rise as the insertion depth increases. When the short-circuit protector 1 is fully inserted, the wedge-shaped mechanism is locked to prevent the short-circuit protector 1 from falling off.

[0077] According to an embodiment of the present disclosure, if the short-circuit protector 1 and the igniter 2 are locked by a snap-fit ​​connection, the short-circuit protector 1 includes a limiter, and the limiter is snap-fitted to the igniter 2 .

[0078] According to the embodiment of the present disclosure, when the operator inserts the short-circuit protector 1 into the igniter 2, the operator presses or slides the limiter to cause the limiter to deform and shrink. When the short-circuit protector 1 is fully inserted, the limiter pops out from the hole set on the igniter 2 to achieve automatic locking. When the short-circuit protector 1 needs to be pulled out of the igniter 2, the limiter is pressed or slid to cause the limiter to deform and shrink again, thereby achieving unlocking, so that the short-circuit protector 1 can be pulled out of the igniter 2.

[0079] According to another embodiment of the present disclosure, an aerostat with an emergency exhaust device is provided, comprising a capsule 6, the emergency exhaust device of the aerostat, a pod and an electrical connection assembly. The capsule 6 is filled with buoyancy gas, and the emergency exhaust device of the aerostat is arranged on the top surface of the capsule 6. The pod is installed below the capsule 6, and the electrical connection assembly is arranged in the pod to supply power to the emergency exhaust device of the aerostat.

[0080] According to an embodiment of the present disclosure, the electrical connection component includes a relay and a power supply component, and the power supply component can select a battery pack. The power supply component is connected to the input end of the relay, and then the output end of the relay is connected to the input end of the igniter 2. By operating the external control circuit, a low-voltage, low-current signal is sent to the relay to close the contacts of the relay. After the relay contacts are closed, the high voltage and high current of the power supply component are transmitted to the igniter 2 through the relay. After receiving sufficient high voltage and high current, the igniter 2 generates sparks to ignite the combustible material 43 in the cutting part 42 of the emergency exhaust device of the airship, thereby completing the detonation process.

[0081] According to the embodiment of the present disclosure, an emergency exhaust device is arranged on the supporting surface of the top surface of the sac 6, and the combustible material 43 inside the cutting rope 4 is detonated under the conduction action of the detonator. The cutting rope 4 cuts the sac 6 under the action of the blasting force, so that the buoyant gas is discharged from the inside of the sac 6, which can expand the exhaust area. At the same time, it is simple and reliable, can be started at any time, has a long service life, can quickly release the buoyant gas in the sac 6, and realize the timely landing of the airship. In addition, the cutting rope 4 is not affected by the height of the troposphere or the stratosphere and the low temperature and low pressure environment, can adapt to various severe weather conditions, has low energy consumption, and always keeps the airship test under control, reducing the test risk to a minimum.

[0082] It will be appreciated by those skilled in the art that the features described in the various embodiments and / or claims of the present disclosure may be combined or coupled in a variety of ways, even if such combinations or couplings are not explicitly described in the present disclosure. In particular, the features described in the various embodiments and / or claims of the present disclosure may be combined or coupled in a variety of ways without departing from the spirit and teachings of the present disclosure. All of these combinations and / or couplings fall within the scope of the present disclosure.

[0083] It should also be noted that the directional terms mentioned in the embodiments, such as "upper", "lower", "front", "back", "left", "right", etc., are only reference directions of the drawings and are not intended to limit the scope of protection of the present disclosure. Throughout the drawings, the same elements are represented by the same or similar reference numerals. Conventional structures or configurations will be omitted when they may cause confusion in the understanding of the present disclosure, and the shapes and sizes of the components in the drawings do not reflect the actual size and proportion, but only illustrate the contents of the embodiments of the present disclosure.

[0084] Unless otherwise indicated, the numerical parameters in this specification and the appended claims are approximate values ​​and can be changed according to the desired properties obtained by the content of the present disclosure. Specifically, all numbers used in the specification and claims to express the content of the composition, reaction conditions, etc., should be understood to be modified by the term "about" in all cases. In general, the meaning of the expression is to include changes in some embodiments of ±10%, in some embodiments of ±5%, in some embodiments of ±1%, and in some embodiments of ±0.5% by a specific number.

[0085] The ordinal numbers used in the specification and claims, such as "first", "second", "third", etc., to modify the corresponding elements, do not themselves mean that the elements have any ordinal numbers, nor do they represent the order of one element and another element, or the order in the manufacturing method. The use of these ordinal numbers is only used to clearly distinguish a component with a certain name from another component with the same name.

[0086] In addition, unless the steps are specifically described or must occur in sequence, the order of the above steps is not limited to the above list, and can be changed or rearranged according to the required design. And the above embodiments can be mixed and matched with each other or with other embodiments based on design and reliability considerations, that is, the technical features in different embodiments can be freely combined to form more embodiments.

[0087] The embodiments of the present disclosure are described above. However, these embodiments are only for illustrative purposes and are not intended to limit the scope of the present disclosure. Although the embodiments are described above separately, this does not mean that the measures in the various embodiments cannot be used in combination to advantage. The scope of the present disclosure is defined by the attached claims and their equivalents. Without departing from the scope of the present disclosure, those skilled in the art may make a variety of substitutions and modifications, which should all fall within the scope of the present disclosure.

Claims

1. An emergency exhaust device for an aerostat, wherein: include: A detonator is mounted on the top surface of the capsule of the aerostat, and the capsule is filled with buoyancy gas; A cutting rope is connected to the detonator. The interior of the cutting rope is filled with combustible materials so as to explode after the detonator is detonated. The cutting rope cuts the capsule under the action of the explosive force, so that the buoyancy gas is discharged from the interior of the capsule, thereby causing the airship to land.

2. The emergency exhaust device of an aerostat according to claim 1, wherein: The top surface of the capsule is provided with a support surface, and the detonator comprises: A mounting frame, mounted on the supporting surface; An igniter is arranged on the mounting frame, and the igniter is detonated in response to an electric current input from the outside.

3. The emergency exhaust device of an aerostat according to claim 2, wherein: The cutting rope comprises: A rope body connected to one end of the igniter; A cutting portion, arranged on a side of the rope body close to the bag body, wherein the cutting portion is configured to have a containing space to contain the combustible; After the igniter ignites the combustible, the cutting part cuts the capsule under the action of the explosive force.

4. The emergency exhaust device of an aerostat according to claim 3, wherein: The material of the rope body is any one of silver and lead.

5. The emergency exhaust device of an aerostat according to claim 3, wherein: The cutting rope forms a preset pattern on the support surface, so that after the cutting part is detonated, the capsule body is cut along the edge of the preset pattern.

6. The emergency exhaust device of an aerostat according to claim 5, wherein: The preset shape is any one of a circle, a triangle and a polygon.

7. The emergency exhaust device of an aerostat according to claim 5, wherein: Also includes: A plurality of mounting fixtures are arranged at intervals on the support surface, and the plurality of mounting fixtures are configured to fix the cutting rope on the support surface so that the cutting portion fits the support surface.

8. The emergency exhaust device of an aerostat according to claim 2, wherein: The detonator also includes: A short circuit protector is connected to the other end of the igniter, and the short circuit protector is configured to disconnect or connect the igniter by plugging or separating the igniter; Wherein, when transporting the aerostat, the short-circuit protector is plugged into the igniter to cause the igniter to short-circuit; When the aerostat is in working state, the short circuit protector is separated from the igniter, so that the igniter is connected to an external electrical connection component, thereby enabling the igniter to receive the current.

9. The emergency exhaust device of an aerostat according to claim 8, wherein: The short circuit protector comprises a limiting member, and the limiting member is snap-connected with the igniter.

10. An aerostat with an emergency exhaust device, wherein: include: A capsule filled with a buoyancy gas; The emergency exhaust device of the aerostat according to any one of claims 1 to 9, arranged on the top surface of the bladder; A pod, installed below the capsule; An electrical connection assembly is arranged in the nacelle to supply power to the emergency exhaust device of the aerostat.

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