Buoyancy airbag assembly for aerospace craft recovery, recovery system and aerospace craft

Abstract

The invention relates to the technical field of aerospace craft water recovery, and provides a buoyancy air bag assembly for aerospace craft recovery, a recovery system and an aerospace craft, the aerospace craft comprises the recovery system, the recovery system comprises a buoyancy air bag assembly and a mounting part, and the buoyancy air bag assembly comprises a buoyancy air bag and a push-out air bag; the push-out air bag penetrates through and is fixedly connected to the installation opening of the buoyancy air bag, the first end of the push-out air bag is located in the buoyancy air bag, the second end of the push-out air bag is located outside the buoyancy air bag, and the push-out air bag is used for pushing the buoyancy air bag in the first direction during inflation. When the aerospace craft is recycled, the push-out air bag in the buoyancy air bag assembly pushes the buoyancy air bag and the mounting piece in the inflating process, the buoyancy air bag is pushed out of the mounting piece, the buoyancy air bag can be smoothly and safely popped out, the buoyancy air bag is prevented from being clamped, the buoyancy air bag is rapidly inflated under the condition that the buoyancy air bag is smoothly and safely popped out, and the safety of the aerospace craft is improved. The bursting risk of the buoyancy air bag is reduced, and smooth work of the buoyancy air bag is guaranteed.

Description

Technical Field

[0001] The present application relates to the technical field of aerospace vehicle water recovery, and in particular to a buoyancy airbag assembly, a recovery system and aerospace vehicle for aerospace vehicle recovery. Background Art

[0002] Spacecraft such as rockets can carry a variety of products for flight tests or special missions, such as high-altitude atmospheric parameter detectors, small satellites, radiation protection devices, etc. For some mission modes, the cabin carrying the flight payload device needs to be recovered in order to conduct further analysis of the payload data.

[0003] As a recovery method for spacecraft, sea parachute recovery has the following advantages: the impact force of water impact is smaller than that of landing, and the spacecraft does not need to install a landing cushion system, which reduces the weight of the spacecraft; sea parachute recovery can avoid natural hazards such as gullies and trees on land, which is conducive to the safe recovery of spacecraft, and can also avoid landing in densely populated areas, causing harm to personnel and buildings, and leading to unnecessary economic losses. When the spacecraft's to-be-recovered cabin lands on the sea, a buoyancy device is needed to increase the buoyancy of the to-be-recovered cabin to ensure that the to-be-recovered cabin can float on the sea, making it easier for salvage personnel to quickly find the to-be-recovered cabin.

[0004] The buoyancy airbag is a buoyancy device. The method of using the buoyancy airbag is to use a gas generator to instantly generate a large amount of gas to fill the buoyancy airbag. The buoyancy airbag is fixedly connected to the cabin to be recovered, providing a certain amount of buoyancy for the cabin to be recovered, so that it floats on the sea. However, in the prior art, the buoyancy airbag needs to be installed in the airbag installation tube through a complex folding process. When the buoyancy airbag is inflated quickly, the buoyancy airbag may be stuck inside the airbag installation tube and cannot be ejected smoothly, which poses a risk of bursting the buoyancy airbag or damaging the airbag installation tube. Summary of the invention

[0005] The present application provides a buoyancy airbag assembly, a recovery system and a spacecraft for recovering a spacecraft. When recovering the spacecraft, the ejection airbag in the buoyancy airbag assembly can push the buoyancy airbag out of the mounting part to prevent the buoyancy airbag from being stuck in the mounting part, thereby ensuring that the buoyancy airbag is ejected smoothly and safely.

[0006] In order to achieve the above objectives, this application adopts the following technical solutions: The first aspect of the present application provides a buoyancy airbag assembly for spacecraft recovery, comprising: A buoyancy air bag having a mounting port; The push-out airbag is passed through and fixedly connected to the installation port, the first end of the push-out airbag is located inside the buoyancy airbag, the second end of the push-out airbag is located outside the buoyancy airbag, the second end has an air inlet, and the push-out airbag is used to push the buoyancy airbag along a first direction when inflated.

[0007] In some possible implementations, when the push-out airbag is filled with gas, the push-out airbag extends along a first direction.

[0008] In some possible implementations, when the push-out airbag is filled with gas, the air inlet is located in the first direction.

[0009] In some possible implementations, the first end of the ejection airbag is provided with an exhaust port, and the ejection airbag is sealingly connected to the mounting port.

[0010] In some possible implementations, a pressure relief valve is provided on the buoyancy airbag, and the pressure relief valve is a one-way valve. When the air pressure in the buoyancy airbag is higher than a preset value, the gas is discharged through the pressure relief valve.

[0011] A second aspect of the present application provides a recovery system for aerospace vehicle recovery, the recovery system comprising: The buoyancy airbag assembly described in the first aspect above; A mounting member, the mounting member comprises a body and a connection cover connected to the body, the body and the connection cover enclose a mounting space, and the connection cover is located in a first direction; The buoyancy airbag assembly is placed in the installation space, and the push-out airbag is used to push the buoyancy airbag and the connection cover along a first direction when inflated. When the connection cover is separated from the body, the push-out airbag pushes the buoyancy airbag out of the installation space.

[0012] In some possible implementations, when the push-out airbag is filled with gas, the length of the push-out airbag along the first direction is L; the length of the mounting member along the first direction is M; wherein L>M.

[0013] In some possible implementations, the ejection airbag is placed along a first direction in the installation space.

[0014] In some possible implementations, the connection cover is provided with a weak portion, and the connection cover is connected to the body via the weak portion.

[0015] In some possible implementations, the recovery system also includes a guide member, which is installed on the main body of the installation member. The guide member is provided with a guide channel. The air inlet end of the guide channel is used to connect with the air supply device, and the exhaust end of the guide channel is connected with the air inlet of the ejection airbag; the cross-sectional area of ​​the guide channel gradually increases from the air inlet end to the exhaust end.

[0016] A third aspect of the present application provides a spacecraft, the spacecraft comprising the recovery system described in the second aspect, and the recovery system is installed in a cabin of the spacecraft.

[0017] It can be seen from the above technical solution that the present application has at least the following beneficial effects: The present application provides a buoyancy airbag assembly, a recovery system and a spacecraft for recovering a spacecraft. When recovering the spacecraft, the push-out airbag in the buoyancy airbag assembly pushes the buoyancy airbag and the mounting part in a first direction when inflated, and pushes the buoyancy airbag out of the mounting part, so that the buoyancy airbag can be ejected smoothly and safely, and the buoyancy airbag is prevented from being stuck in the mounting part. The buoyancy airbag is quickly inflated when it is ejected smoothly and safely, reducing the risk of squeezing and bursting of the buoyancy airbag, and ensuring that the buoyancy airbag can work smoothly; and when the buoyancy airbag assembly is installed in the mounting part, no complicated folding process is required, which saves installation time and improves installation efficiency; further, the problem of large size design of the mounting part for installing the buoyancy airbag assembly is solved, and the mounting part can be designed in size according to the design space of the cabin section of the spacecraft, saving corresponding assembly space for the cabin section of the spacecraft, which is beneficial to reducing the weight of the spacecraft and improving the energy utilization rate of the spacecraft, and the mounting part can be designed into a special shape, which can further save corresponding assembly space for the cabin section of the spacecraft.

[0018] It should be understood that the description of technical features, technical solutions, beneficial effects or similar language in this application does not imply that all features and advantages can be realized in any single embodiment. On the contrary, it is understood that the description of features or beneficial effects means that specific technical features, technical solutions or beneficial effects are included in at least one embodiment. Therefore, the description of technical features, technical solutions or beneficial effects in this specification does not necessarily refer to the same embodiment. Furthermore, the technical features, technical solutions and beneficial effects described in the present embodiment can also be combined in any appropriate manner. Those skilled in the art will understand that the embodiment can be realized without one or more specific technical features, technical solutions or beneficial effects of a specific embodiment. In other embodiments, additional technical features and beneficial effects can also be identified in a specific embodiment that does not embody all embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A schematic diagram of the structure of a buoyancy airbag assembly for spacecraft recovery provided in an embodiment of the present application, wherein the buoyancy airbag and the ejection airbag are filled with gas; Figure 2 A schematic diagram of the structure of a recovery system for aerospace vehicle recovery provided in an embodiment of the present application, wherein the buoyancy airbag and the ejection airbag are in an uninflated state in the mounting member; Figure 3 A schematic diagram of the structure of a recovery system for a spacecraft recovery provided in an embodiment of the present application when in use, wherein the buoyancy airbag is outside the mounting member, and the buoyancy airbag and the ejection airbag are filled with gas.

[0020] Figure markings: 10-buoyancy airbag assembly; 1-push-out airbag; 11-first end; 12-second end; 13-air inlet; 14-exhaust port; 2-buoyancy airbag; 3-pressure relief valve; 20-mounting piece; 21-main body; 22-connecting cover; 23-installation space; 30-flow guide; 31-inlet end; 32-exhaust end; 33-filter; 40-air supply device; X-first direction; Y-second direction. DETAILED DESCRIPTION

[0021] The terms "first", "second", "third", etc. in the specification of this application and the accompanying drawings are used to distinguish different objects rather than to limit a specific order.

[0022] In the embodiments of the present application, words such as "exemplary" or "for example" are used to indicate examples, illustrations or descriptions. Any embodiment or design described as "exemplary" or "for example" in the embodiments of the present application should not be interpreted as being more preferred or more advantageous than other embodiments or designs. Specifically, the use of words such as "exemplary" or "for example" is intended to present related concepts in a specific way.

[0023] Spacecraft are aircraft used in aerospace engineering. Spacecraft include rockets, manned spacecraft, etc. Take rockets as an example. As a carrier, rockets can carry a wide variety of products for flight tests or special missions, such as high-altitude atmospheric parameter detectors, small satellites, radiation protection devices, etc. For some mission modes, it is necessary to recover the cabin carrying the flight payload device in order to conduct further analysis of the payload data.

[0024] When recovering a spacecraft, it can be recovered on land or on water. Water recovery can make the spacecraft reusable and reduce the cost of space launch. The common way of water recovery is sea recovery. In addition, water recovery can also be carried out on lakes.

[0025] Taking offshore recovery as an example, offshore recovery can be divided into offshore platform recovery and offshore parachute recovery. Offshore platform recovery means that after the spacecraft completes its mission, it will fly autonomously to the offshore platform according to the set trajectory through its own control system and power device. Offshore parachute recovery is to slow down the spacecraft to a certain speed through a parachute, and the spacecraft will splash directly onto the sea surface, and then be found and recovered by sea search and rescue ships and helicopters. Developing offshore parachute recovery technology based on the existing parachute deceleration technology in land recovery technology is a good choice for realizing the recovery of spacecraft at sea. Moreover, offshore parachute recovery has high reliability and low loss of carrying capacity. Countries around the world have been conducting related research for a long time.

[0026] Compared with land recovery, sea parachute recovery has the following advantages: the impact force of water impact is smaller than that of landing, and the spacecraft does not need to install a landing cushion system, which reduces the weight of the spacecraft; sea parachute recovery can avoid natural hazards such as gullies and trees on land, which is conducive to the safe recovery of spacecraft, and can also avoid landing in densely populated areas, causing harm to people and buildings, and leading to unnecessary economic losses; the physical properties of the sea surface change less, and the sea area selection is relatively easy, which enhances the adaptability of spacecraft to various inclination orbits.

[0027] Based on the safety considerations of marine recovery, the salvage and rescue ship needs to be on duty outside the landing zone safety zone. Only after the spacecraft's waiting compartment has completely fallen into the water can it enter the safety zone for search and rescue. It usually takes at least 4 to 6 hours for the salvage and rescue ship to reach the landing zone. In order to ensure that the spacecraft's waiting compartment can float on the water after it falls into the water, so that the search and rescue personnel can quickly find the spacecraft's waiting compartment, it is necessary to use a buoyancy device to increase the buoyancy of the fallen compartment. Commonly used buoyancy devices include floats, electric push rod buoyancy devices, buoyancy airbags, etc.

[0028] Among them, the commonly used buoyancy device with high technical reliability and low cost is the buoyancy airbag, which is used by using a gas generator to instantly generate a large amount of gas to inflate the buoyancy airbag. The inflated buoyancy airbag is fixedly connected to the compartment to be recovered, providing a certain buoyancy for the compartment to be recovered, so that it floats on the sea.

[0029] The gas generating device has the characteristics of fast gas production speed (gas production time is, for example, about 100ms), fast gas flow rate (for example, 400m / s), high gas production temperature (for example, 300°C), and large gas production volume, and can quickly inflate the buoyancy airbag.

[0030] In the prior art, the buoyancy airbag needs to be installed in the metal tube of the airbag through a complex folding process. When the buoyancy airbag is inflated quickly, high-temperature and high-speed combustion gas is directly filled into the buoyancy airbag, and the buoyancy airbag may be stuck inside the airbag installation tube and cannot be ejected smoothly, which poses a risk of bursting the buoyancy airbag or damaging the airbag installation tube. Moreover, in order to reduce the risk of buoyancy airbag bursting, the internal space size of the airbag installation tube needs to be designed to be relatively large, which occupies a large internal space of the compartment to be recovered in the aerospace vehicle. In addition, for some buoyancy airbag devices with large-volume airbags, the inflated volume of the buoyancy airbag far exceeds the maximum size of the compartment to be recovered, and the internal space of the compartment to be recovered is limited. The internal space design of the airbag installation tube is also greatly restricted, and the risk of buoyancy airbag bursting when inflated is higher.

[0031] In view of this, the embodiments of the present application provide a buoyancy airbag assembly, a recovery system and a spacecraft for recovering a spacecraft. When recovering the spacecraft, the push-out airbag in the buoyancy airbag assembly pushes the buoyancy airbag and the mounting member in a first direction when inflated, and pushes the buoyancy airbag out of the mounting member, so that the buoyancy airbag can be ejected smoothly and safely, and the buoyancy airbag is prevented from being stuck in the mounting member. The buoyancy airbag is quickly inflated when it is ejected smoothly and safely, reducing the risk of squeezing and bursting of the buoyancy airbag, and ensuring that the buoyancy airbag can work smoothly; and when the buoyancy airbag assembly is installed in the mounting member, no complicated folding process is required, which saves installation time and improves installation efficiency; further, the problem of large size design of the mounting member for installing the buoyancy airbag assembly is solved, and the mounting member can be designed in size according to the design space of the cabin section of the spacecraft, saving corresponding assembly space for the cabin section of the spacecraft, which is beneficial to reducing the weight of the spacecraft and improving the energy utilization rate of the spacecraft, and the mounting member can be designed into a special shape, which can further save corresponding assembly space for the cabin section of the spacecraft.

[0032] In the first aspect, the buoyancy airbag assembly 10 for spacecraft recovery provided in the embodiment of the present application is introduced. Figure 1 As shown, the buoyancy airbag assembly 10 includes a buoyancy airbag 2 and a push-out airbag 1, the buoyancy airbag 2 has a mounting port; the push-out airbag 1 is passed through and fixedly connected to the mounting port, the first end 11 of the push-out airbag 1 is located inside the buoyancy airbag 2, the second end 12 of the push-out airbag 1 is located outside the buoyancy airbag 2, the second end 12 has an air inlet 13, and the push-out airbag 1 is used to push the buoyancy airbag 2 along a first direction X when inflated.

[0033] like Figure 1 As shown, when the buoyancy airbag 2 and the push-out airbag 1 are both filled with gas, the first end 11 of the push-out airbag 1 is located inside the buoyancy airbag 2 , and the second end 12 of the push-out airbag 1 extends outside the buoyancy airbag 2 through the installation opening of the buoyancy airbag 2 .

[0034] The buoyancy airbag assembly 10 is used in the recovery of a spacecraft. The spacecraft includes a cabin and a recovery system installed in the cabin; the recovery system includes the buoyancy airbag assembly 10, a mounting member 20 and an air supply device 40, the buoyancy airbag assembly 10 is installed in the mounting member 20, and the air supply device 40 is connected to the air inlet 13 of the push-out airbag 1 of the buoyancy airbag assembly 10.

[0035] The module of a spacecraft may be a return module, a control module, a fairing or other modules that need to be recovered.

[0036] When the cabin of the spacecraft is recovered on water, the air supply device 40 supplies air to the ejection airbag 1, and the gas enters from the air inlet 13 to quickly inflate the ejection airbag 1. During this process, the ejection airbag 1 pushes the buoyancy airbag 2 along the first direction X, and pushes the buoyancy airbag 2 out of the mounting member 20, so that the buoyancy airbag 2 is smoothly and safely ejected from the mounting member 20. The buoyancy airbag 2 is quickly inflated in the case of being smoothly and safely ejected. After the inflation is completed, the buoyancy airbag 2 provides buoyancy to the cabin of the spacecraft, so that the cabin of the spacecraft floats on the water surface.

[0037] When the buoyancy airbag assembly 10 provided in the embodiment of the present application is used to recover the cabin section of the aerospace vehicle, the push-out airbag 1 in the buoyancy airbag assembly 10 pushes the buoyancy airbag 2 and the mounting member 20 along the first direction X when inflated, and pushes the buoyancy airbag 2 out of the mounting member 20, so that the buoyancy airbag 2 can be ejected smoothly and safely, and the buoyancy airbag 2 is prevented from being stuck in the mounting member 20. The buoyancy airbag 2 is quickly inflated when it is ejected smoothly and safely, reducing the risk of squeezing and bursting of the buoyancy airbag 2, and ensuring that the buoyancy airbag 2 can work smoothly; moreover, the push-out airbag 1 is used to push the buoyancy airbag 2 to the outside of the mounting member 20, and the buoyancy airbag assembly 10 When inserting into the mounting part 20, no complicated folding process is required, which saves installation time and improves installation efficiency; furthermore, the buoyancy airbag 2 can be ejected smoothly and safely, solving the problem of large size design of the mounting part 20 for installing the buoyancy airbag assembly 10. The mounting part 20 for installing the buoyancy airbag assembly 10 can be designed in size according to the design space of the cabin of the spacecraft, saving corresponding assembly space for the cabin of the spacecraft, which is beneficial to reducing the weight of the spacecraft and improving the energy utilization rate of the spacecraft, and the mounting part 20 can be designed to be special-shaped, which can further save corresponding assembly space for the cabin of the spacecraft.

[0038] In a specific embodiment, when the push-out airbag 1 is filled with gas, the push-out airbag 1 extends along the first direction X. In this configuration, when the uninflated push-out airbag 1 is inflated, the push-out airbag 1 expands along the first direction X, and the push-out airbag 1 pushes the buoyancy airbag 2 along the first direction X.

[0039] like Figure 1In the embodiment shown, when the push-out airbag 1 is filled with gas, the push-out airbag 1 is a columnar structure extending along the first direction X; when the uninflated push-out airbag 1 is inflated, the push-out airbag 1 expands along the first direction X, and the inflated push-out airbag 1 is similar to a columnar push rod. The first end 11 of the push-out airbag 1 contacts the inner surface of the buoyancy airbag 2, and the push-out airbag 1 pushes the buoyancy airbag 2 along the first direction X.

[0040] In a specific embodiment, Figure 1 As shown, the push-out airbag 1 and the buoyancy airbag 2 are both inflated with gas, and the push-out airbag 1 and the buoyancy airbag 2 are coaxially arranged along the first direction X.

[0041] Such an arrangement is conducive to pushing out the airbag 1 along the first direction X to stably and quickly push the buoyancy airbag 2 to the outside of the mounting member 20 .

[0042] Specifically, the volume of the push-out airbag 1 is smaller than that of the buoyancy airbag 2 , that is, the push-out airbag 1 is a small-volume airbag. After the push-out airbag 1 is loaded into the mounting member 20 , due to its small volume, no wrinkles or bends will be formed, and thus no large flow resistance will be formed after being loaded into the mounting member 20 .

[0043] Specifically, Figure 1 As shown, when the ejection airbag 1 is filled with gas, the gas inlet 13 is located in the first direction X.

[0044] With such a configuration, the gas entering from the air inlet 13 can fill the push-out airbag 1 along the first direction X more quickly, which is beneficial to increasing the expansion speed of the push-out airbag 1 along the first direction X.

[0045] In a specific embodiment, the first end 11 of the ejection airbag 1 is provided with an exhaust port 14 , and the ejection airbag 1 is sealed and connected to the installation port.

[0046] When in use, gas enters from the air inlet 13 of the push-out airbag 1, quickly inflating the push-out airbag 1, and the push-out airbag 1 pushes the buoyancy airbag 2. When the push-out airbag 1 is inflated, the buoyancy airbag 2 is outside the mounting member 20, and the gas flows into the buoyancy airbag 2 through the exhaust port 14 at the first end 11 of the push-out airbag 1, quickly inflating the buoyancy airbag 2, and finally making both the push-out airbag 1 and the buoyancy airbag 2 fully inflated.

[0047] In the present embodiment, the push-out airbag 1 can not only push the buoyancy airbag 2, but also the gas can flow to the buoyancy airbag 2 through the push-out airbag 1, so that the buoyancy airbag assembly 10 only needs to have one air inlet 13, and the structure is simple; moreover, the gas flows from the push-out airbag 1 into the buoyancy airbag 2, and the gas pressure is reduced, thus avoiding the situation where the buoyancy airbag 2 is burst due to excessive gas pressure.

[0048] The push-out airbag 1 can be bonded and sealed with the buoyancy airbag 2, which not only realizes a fixed connection between the two, but also realizes a sealed connection between the two; or, the push-out airbag 1 and the buoyancy airbag 2 are sealed by other sealing connection methods.

[0049] There may be multiple exhaust ports 14 .

[0050] Specifically, Figure 1 As shown, the exhaust port 14 is arranged in the second direction Y, which is conducive to the rapid expansion of the push-out airbag 1 along the first direction X. The second direction Y may be the width direction of the push-out airbag 1 .

[0051] In a specific embodiment, Figure 1 As shown, a pressure relief valve 3 is provided on the buoyancy airbag 2, and the pressure relief valve 3 is a one-way valve. When the air pressure in the buoyancy airbag 2 is higher than a preset value, that is, the buoyancy airbag 2 is in a high-pressure state, the gas in the buoyancy airbag 2 is discharged through the pressure relief valve 3 to protect the buoyancy airbag 2 from being burst.

[0052] The preset value may be a preset value of the pressure that the buoyancy airbag 2 can withstand.

[0053] When the buoyancy airbag 2 is not inflated, the pressure relief valve 3 is in a closed state, and the buoyancy airbag 2 is a sealed airbag; when the buoyancy airbag 2 is fully inflated, if the pressure exceeds the maximum pressure that the pressure relief valve 3 can withstand, the pressure relief valve 3 switches from a closed state to an open state, so that the gas in the buoyancy airbag 2 is discharged through the pressure relief valve 3, thereby ensuring the inflation safety of the buoyancy airbag 2.

[0054] Specifically, the pressure relief valve 3 can be assembled onto the buoyancy airbag 2 through a threaded connection, and the threaded interface is a cone-ball seal to ensure the tightening torque.

[0055] In a second aspect, the present application provides a recovery system for aerospace vehicle recovery, such as Figure 2 As shown, the recovery system includes a mounting member 20 and the buoyancy airbag assembly 10 in the above-mentioned first aspect; the mounting member 20 includes a main body 21 and a connecting cover 22 connected to the main body 21, the main body 21 and the connecting cover 22 enclose an installation space 23, and the connecting cover 22 is located in the first direction X; wherein, the buoyancy airbag assembly 10 is placed in the installation space 23, and the push-out airbag 1 is used to push the buoyancy airbag 2 and the connecting cover 22 along the first direction X when inflated, and when the connecting cover 22 is separated from the main body 21, the push-out airbag 1 pushes the buoyancy airbag 2 out of the installation space 23.

[0056] When the push-out airbag 1 is inflated, the push-out airbag 1 expands rapidly, and the push-out airbag 1 pushes the buoyancy airbag 2 and the connecting cover 22 along the first direction X. The connecting cover 22 will be separated from the main body 21 under the action of the thrust, and the buoyancy airbag 2 is pushed by the push-out airbag 1 and brought to the outside of the mounting member 20, so that the buoyancy airbag 2 is placed in a free state outside the mounting member 20, that is, under the action of the push-out airbag 1, the buoyancy airbag 2 can be smoothly and safely popped out from the mounting member 20, avoiding the buoyancy airbag 2 from being stuck in the mounting member 20, and the buoyancy airbag 2 is quickly inflated when it is smoothly and safely popped out, reducing the risk of squeezing and bursting of the buoyancy airbag 2, and ensuring that the buoyancy airbag 2 can work smoothly.

[0057] Specifically, Figure 3 As shown, when the push-out airbag 1 is filled with gas, the length of the push-out airbag 1 along the first direction X is L; the length of the mounting member 20 along the first direction X is M; wherein L>M.

[0058] With such arrangement, when the push-out airbag 1 is filled with gas, the second end 12 of the push-out airbag 1 is located inside the mounting member 20 , and the first end 11 of the push-out airbag 1 extends outside the mounting member 20 , so that the push-out airbag 1 pushes and completely brings the buoyancy airbag 2 outside the mounting member 20 .

[0059] Specifically, when the airbag 1 is filled with gas, the cross-sectional area of ​​the airbag 1 along the second direction Y is smaller than the cross-sectional area of ​​the installation space 23 along the second direction Y. Therefore, when the airbag 1 is filled with gas, the airbag 1 will not interfere with the installation member 20 .

[0060] In a specific embodiment, the ejection airbag 1 is placed along the first direction X in the installation space 23 .

[0061] When the push-out airbag 1 is inflated, since the push-out airbag 1 is placed along the first direction X in the installation space 23, the push-out airbag 1 expands more smoothly along the first direction X, and the push-out airbag 1 pushes the buoyancy airbag 2 and the connection cover 22 of the installation member 20 more smoothly along the first direction X.

[0062] Specifically, Figure 2 As shown, the buoyancy airbag assembly 10 is piled up in a wrinkled state along the first direction X in the installation space 23 . The buoyancy airbag assembly 10 does not need to be complicatedly folded, which saves the time of installing the buoyancy airbag assembly 10 into the installation space 23 and improves the installation efficiency of the buoyancy airbag assembly 10 .

[0063] In order to improve the accuracy of the push-out airbag 1 in pushing the buoyancy airbag 2 and the connecting cover 22 of the mounting member 20 along the first direction X when inflated, the push-out airbag 1 and the buoyancy airbag 2 are coaxially arranged along the first direction X with the mounting member 20 when both are filled with gas.

[0064] In a specific embodiment, the connection cover 22 is provided with a weak portion, and the connection cover 22 is connected to the body 21 via the weak portion.

[0065] When the airbag 1 is pushed out to push the connection cover 22 , the weak portion is destroyed under the action of the thrust, so that the connection cover 22 and the body 21 are separated.

[0066] The weak part may be a connecting plate with a smaller thickness; or, the weak part may be a weakening groove through which the screw passes to connect with the main body 21; or, the material of the weak part may be a material with lower strength, such as polytetrafluoroethylene.

[0067] In other embodiments, the entire connection cover 22 is made of a material with relatively low strength, such as polytetrafluoroethylene.

[0068] In a specific embodiment, Figure 2 As shown, the recovery system also includes a guide member 30, which is installed on the main body 21 of the mounting member 20. The guide member 30 is provided with a guide channel. The air inlet end 31 of the guide channel is used to communicate with the air supply device 40, and the exhaust end 32 of the guide channel is connected to the air inlet 13 of the ejection airbag 1; from the air inlet end 31 to the exhaust end 32, the cross-sectional area of ​​the guide channel gradually increases.

[0069] As the gas flows from the air inlet end 31 to the exhaust end 32 of the guide channel, the cross-sectional area of ​​the guide channel gradually increases from the air inlet end 31 to the exhaust end 32, thereby reducing the gas flow rate through the guide channel; after the gas flow rate is reduced, it enters and pushes out the airbag 1, reducing the risk of the gas bursting and pushing out the airbag 1.

[0070] Wherein, the guide channel can be a tapered channel.

[0071] Specifically, a filter screen 33 is provided in the flow guiding channel, and the filter screen 33 is used to filter the gas passing through the flow guiding channel.

[0072] Specifically, the guide member 30 is a metal member. When the gas passes through the guide member 30 , the guide member 30 can absorb the heat of the gas, thereby reducing the risk of high-temperature gas directly entering the ejection airbag 1 and causing damage to the ejection airbag 1 .

[0073] Specifically, the recovery system further includes a gas supply device 40 , which is communicated with the guide channel of the guide member 30 , and is used for providing gas.

[0074] The gas supply device 40 may be a gas generating device; or, the gas supply device 40 may be other devices capable of quickly generating gas.

[0075] In a third aspect, an embodiment of the present application provides a spacecraft, which includes the recovery system in the second aspect, and the recovery system is installed in a cabin of the spacecraft.

[0076] like Figure 2-3 As shown, the installation of the buoyancy airbag assembly 10 and the working process of the recovery system when recovering the cabin section of the spacecraft are described as follows: A centrifuge is connected to the air inlet 13 of the push-out airbag 1, and the centrifuge is turned on to evacuate the air in the push-out airbag 1 and the buoyancy airbag 2. After evacuation, the push-out airbag 1 and the buoyancy airbag 2 are in a flat state.

[0077] Close and disassemble the centrifuge, connect the air inlet 13 of the push-out airbag 1 to the exhaust end 32 of the guide member 30, and ensure the interface is sealed at the connection; install the push-out airbag 1 and the buoyancy airbag 2 into the body 21 of the mounting member 20, so that the buoyancy airbag assembly 10 is piled up in a folded state along the first direction X, such as Figure 2 ; Use screws to connect the connecting cover 22 to the main body 21.

[0078] The gas supply device 40 is connected to the gas inlet end 31 of the guide member 30, and the interface is sealed, wherein the gas supply device 40 is a gas generating device.

[0079] The gas generating device works and generates a large amount of gas quickly. The gas enters the ejection airbag 1 through the guide member 30 and quickly fills up. The ejection airbag 1 pushes the buoyancy airbag 2 and the connecting cover 22 along the first direction X. The connecting cover 22 is separated from the main body 21 under the action of the thrust. The buoyancy airbag 2 is pushed by the ejection airbag 1 and brought to the outside of the mounting member 20, so that the buoyancy airbag 2 is placed in a free state outside the mounting member 20, that is, the buoyancy airbag 2 is ejected smoothly and safely.

[0080] The gas flows into the buoyancy airbag 2 through the exhaust port 14 of the push-out airbag 1, and quickly fills up the entire buoyancy airbag assembly 10. Figure 3 As shown, the buoyancy airbag assembly 10 provides buoyancy to the cabin of the aerospace vehicle, so that the cabin floats on the water surface.

[0081] The guide member 30 is a metal member, and a filter screen 33 is arranged in the guide channel of the guide member 30. When the gas passes through the guide member 30, the gas absorbs heat, and the filter screen 33 filters the debris carried by the gas.

[0082] After the push-out airbag 1 is fully inflated, the gas flows into the buoyancy airbag 2 through the exhaust port 14 of the push-out airbag 1. At this time, the gas temperature and pressure will be significantly reduced. When the buoyancy airbag 2 is inflated, the gas will not heat and damage the buoyancy airbag 2, thereby protecting the inflation safety of the buoyancy airbag 2.

[0083] For example, when the push-out airbag 1 is rapidly inflated, the portion of the push-out airbag 1 located inside the buoyancy airbag 2 cannot withstand the impact of the high-temperature, high-speed combustion gas, causing its strength to reach its limit and become damaged. Since the portion of the push-out airbag 1 located outside the buoyancy airbag 2 is sealed and fixedly connected to the buoyancy airbag 2, the combustion gas can still enter from the air inlet 13 of the push-out airbag 1 and eventually flow into the buoyancy airbag 2, without affecting the normal operation of the buoyancy airbag 2.

[0084] The above description is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present application should be included in the protection scope of the present application.

Claims

1. A buoyancy airbag assembly for spacecraft recovery, characterized in that: include: A buoyancy air bag having a mounting port; The ejection airbag is passed through and fixedly connected to the installation port, the first end of the ejection airbag is located inside the buoyancy airbag, the second end of the ejection airbag is located outside the buoyancy airbag, the second end has an air inlet, and the ejection airbag is used to push the buoyancy airbag along a first direction when inflated.

2. The buoyancy airbag assembly according to claim 1, characterized in that: When the ejection airbag is filled with gas, the ejection airbag extends along the first direction.

3. The buoyancy airbag assembly according to claim 1, characterized in that: When the ejection airbag is filled with gas, the air inlet is located in the first direction.

4. The buoyancy airbag assembly according to claim 1, characterized in that: The first end of the ejection airbag is provided with an exhaust port, and the ejection airbag is sealingly connected to the installation port.

5. The buoyancy airbag assembly according to claim 1, characterized in that: The buoyancy airbag is provided with a pressure relief valve, which is a one-way valve. When the air pressure in the buoyancy airbag is higher than a preset value, the gas is discharged through the pressure relief valve.

6. A recovery system for aerospace vehicle recovery, characterized in that: The recovery system comprises: The buoyancy airbag assembly according to any one of claims 1 to 5; A mounting member, the mounting member comprising a body and a connection cover connected to the body, the body and the connection cover enclose a mounting space, and the connection cover is located in a first direction; Wherein, the buoyancy airbag assembly is placed in the installation space, and the push-out airbag is used to push the buoyancy airbag and the connection cover along the first direction when inflated. When the connection cover is separated from the body, the push-out airbag pushes the buoyancy airbag out of the installation space.

7. The recovery system according to claim 6, characterized in that: When the ejection airbag is filled with gas, the length of the ejection airbag along the first direction is L; The length of the mounting member along the first direction is M; Among them, L>M.

8. The recovery system according to claim 6, characterized in that: The ejection airbag is placed in the installation space along the first direction.

9. The recovery system according to claim 6, characterized in that: The connection cover is provided with a weak portion, and the connection cover is connected to the body through the weak portion.

10. The recovery system according to claim 6, characterized in that: The recovery system further comprises a guide member, the guide member is mounted on the body of the mounting member, the guide member is provided with a guide channel, the air inlet end of the guide channel is used to communicate with the air supply device, and the air outlet end of the guide channel is communicated with the air inlet of the ejection airbag; In a direction from the air inlet end to the air outlet end, the cross-sectional area of ​​the flow guide channel gradually increases.

11. A spacecraft, characterized in that: The aerospace vehicle comprises the recovery system according to any one of claims 6 to 10, and the recovery system is installed in a cabin of the aerospace vehicle.

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