CN112287462A - Design method of pressure emergency lifesaving system for manned spacecraft sealed cabin - Google Patents
Design method of pressure emergency lifesaving system for manned spacecraft sealed cabin Download PDFInfo
- Publication number
- CN112287462A CN112287462A CN202011210305.7A CN202011210305A CN112287462A CN 112287462 A CN112287462 A CN 112287462A CN 202011210305 A CN202011210305 A CN 202011210305A CN 112287462 A CN112287462 A CN 112287462A
- Authority
- CN
- China
- Prior art keywords
- scheme
- cabin
- rescue system
- lifesaving
- sealed cabin
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Abstract
The invention relates to a design method of a pressure emergency rescue system for a manned spacecraft sealed cabin, which comprises the following steps: s1, obtaining an intra-cabin structure scheme of a sealed cabin of a manned spacecraft and an intra-cabin layout scheme of the sealed cabin; s2, generating a rescue system structure scheme of a rescue system which can be unfolded and stored in the sealed cabin based on the cabin structure scheme, and generating an interface design scheme of the rescue system by combining the cabin layout scheme and the rescue system structure scheme; and S3, generating a use mode scheme for deploying and storing the lifesaving system based on the lifesaving system structure scheme and the interface design scheme. The pressure emergency disposal of the manned spacecraft in the pressure emergency state is solved, and the life safety of the spacecraft is effectively ensured. In addition, a normal task and a pressure emergency device or material reuse design principle is carried out, so that the resource cost of the whole device can be reduced to the maximum extent, and the safety level is higher.
Description
Technical Field
The invention relates to the field of spaceflight, in particular to a design method of a pressure emergency lifesaving system for a manned spacecraft sealed cabin.
Background
With the continuous progress of manned space technology in China, the development task of the space station is comprehensively developed, the launching number of manned spacecrafts in China is remarkably increased, and manned deep space exploration is inevitably a trend. The manned spacecraft is in the risk of decompression of a sealed cabin caused by space debris, micro-planet impact and the like during space flight, and how to ensure the safety of the spaceman till the safety returns for as long as possible under the condition of decompression of the sealed cabin is one of important contents of research and design of the manned spacecraft emergency lifesaving system.
Disclosure of Invention
The invention aims to provide a design method of a rescue system for pressure emergency of a manned spacecraft sealed cabin, which is used for emergency rescue of the spacecraft sealed cabin.
In order to achieve the above object, the present invention provides a design method of a rescue system for pressure emergency of a manned spacecraft capsule, comprising:
s1, obtaining an intra-cabin structure scheme of a sealed cabin of a manned spacecraft and an intra-cabin layout scheme of the sealed cabin;
s2, generating a rescue system structure scheme of a rescue system which can be unfolded and stored in the sealed cabin based on the cabin structure scheme, and generating an interface design scheme of the rescue system by combining the cabin layout scheme and the rescue system structure scheme;
and S3, generating a use mode scheme for deploying and storing the lifesaving system based on the lifesaving system structure scheme and the interface design scheme.
According to one aspect of the invention, in the lifesaving system structure scheme, the lifesaving system is provided as a detachable and assembled flexible bag structure for realizing the expansion and the storage in the sealed cabin.
According to one aspect of the invention, the step of generating a structural scheme of a rescue system deployable and stowable in the sealed capsule based on the structural scheme in the capsule comprises:
selecting a molding material of the lifesaving system;
the lifesaving system is arranged into a shapeable flexible bag structure matched with the inner shape and size of the sealed cabin;
splitting the flexible bladder structure into a plurality of petal-shaped components that are detachably connected to one another;
and arranging a connecting structure of the petal-shaped assembly.
According to one aspect of the invention, the connecting structure is a containment zipper.
According to one aspect of the invention, the step of generating the interface design scheme of the lifesaving system by combining the cabin layout scheme and the lifesaving system structure scheme comprises the following steps:
generating a multiplexing scheme of equipment or materials in the spacecraft in a normal task and emergency state;
designing a mounting interface for mounting the petal-shaped assembly in the sealed cabin based on the cabin layout scheme, the lifesaving system structure scheme and the multiplexing scheme;
and designing the folding mode and the unfolding mode of the petal-shaped assembly.
According to one aspect of the invention, in the step of designing the installation interface for installing the petal-shaped assembly in the sealed cabin based on the cabin layout scheme, the lifesaving system structure scheme and the multiplexing scheme, collision risk analysis is performed on the sealed cabin, and according to the result of the collision risk analysis, the petal-shaped assembly is folded and arranged around the cabin wall with the collision risk exceeding the preset condition.
According to one aspect of the invention, the flap assembly is connected to the bulkhead using a seal or mechanical fastening.
According to one aspect of the invention, the usage mode schemes comprise a pressure emergency preparation sub-scheme, a lifesaving system deployment and state setting sub-scheme, and a lifesaving system withdrawal and state setting sub-scheme before returning; wherein the content of the first and second substances,
in the pressure emergency preparation sub-scheme, after the on-track pressure emergency is judged, emergency setting is carried out on non-bearing equipment in a sealed cabin;
in the sub-scheme of the expansion and state setting of the lifesaving system, the lifesaving system is expanded, and pressure maintaining and leakage detecting are carried out until the lifesaving system can be maintained normal;
in the sub scheme of the rescue system withdrawal and state setting before returning, the rescue system is fixedly stored, and the equipment in the sealed cabin is set in the state before returning.
According to the scheme provided by the invention, the pressure emergency disposal of the manned spacecraft in the pressure emergency state is solved, and the life safety of the astronaut is effectively ensured. In addition, a normal task and a pressure emergency device or material reuse design principle is carried out, so that the resource cost of the whole device can be reduced to the maximum extent, and the safety level is higher.
According to one scheme of the emergency lifesaving system, the shaped flexible bag matched with the internal interface of the sealed cabin is arranged, so that the emergency lifesaving system is ensured to be accommodated and unfolded. Meanwhile, the flexible bag is subjected to interface design with other devices in the cabin, so that the emergency problem of the pressure of the manned spacecraft sealed cabin in the orbit is solved at a low resource cost, and particularly the emergency return time is long when the pressure of the manned spacecraft is in emergency in deep space exploration.
According to the scheme of the invention, the lifesaving system is split into the plurality of petal-shaped structures, so that the space occupation of the lifesaving system in a narrow space is effectively solved, and the improvement on the utilization rate of the space in the whole sealed cabin is facilitated.
According to one scheme of the invention, the assembly connection of the lifesaving system is carried out by adopting the sealing zipper, so that the connection is convenient and quick, and the quick arrangement of the lifesaving system in an emergency state is facilitated.
According to one scheme of the invention, the petal-shaped components of the split lifesaving system are arranged around the position which is easy to be impacted, so that the arrangement position can be found in time when danger occurs, and the arrangement of the whole lifesaving system is facilitated.
Drawings
Fig. 1 is a block diagram schematically illustrating steps of a method of designing a rescue system according to an embodiment of the invention;
fig. 2 is a schematic diagram schematically illustrating an on-track use mode of the lifesaving system according to an embodiment of the invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
Referring to fig. 1 and 2, according to one embodiment of the invention, the design method of the rescue system for manned spacecraft capsule pressure emergency comprises the following steps:
s1, obtaining an intra-cabin structure scheme of a sealed cabin of a manned spacecraft and an intra-cabin layout scheme of the sealed cabin;
s2, generating a rescue system structure scheme of a rescue system which can be unfolded and stored in the sealed cabin based on the cabin structure scheme, and generating an interface design scheme of the rescue system by combining the cabin layout scheme and the rescue system structure scheme;
and S3, generating a use mode scheme for deploying and storing the lifesaving system based on the structural scheme and the interface design scheme of the lifesaving system.
According to one embodiment of the invention, in the lifesaving system structure scheme, the lifesaving system is provided as a detachable and assembled flexible bag structure for realizing the expansion and the storage in the sealed cabin.
According to one embodiment of the invention, the step of generating a structural scheme of a rescue system of the rescue system which can be deployed and stored in a sealed cabin based on the structural scheme in the cabin comprises the following steps:
selecting a molding material of the lifesaving system. In the present embodiment, a material having high airtightness and good compatibility, such as 210 oxford cloth, is selected.
The lifesaving system is arranged into a shapeable flexible bag structure matched with the inner shape and size of the sealed cabin; in the embodiment, the lifesaving system is designed into a flexible bag which can be shaped in the sealed cabin according to the structural form and the size in the sealed cabin of the manned spacecraft.
The flexible bladder structure is split into a plurality of mutually detachably connected petal-like assemblies. In the embodiment, the designed lifesaving system is split into a plurality of petal-shaped assemblies according to the shape and the structure of the lifesaving system. In this embodiment, the life saving system can be disassembled into 2 to 3 pieces. In this embodiment, the petal-shaped elements may be petal-shaped structures.
A connection structure of the petal-shaped components is arranged. In this embodiment, the sealed connection is achieved by arranging adjacent flap assemblies in a configuration that provides a containment zipper in the connected position, the containment zipper having an operating force that is required to meet ergonomic requirements.
According to one embodiment of the invention, the step of generating the interface design scheme of the lifesaving system by combining the cabin layout scheme and the lifesaving system structure scheme comprises the following steps:
generating a multiplexing scheme of equipment or materials in the spacecraft in a normal task and emergency state; in this embodiment, a design of multiplexing a normal task with a pressure emergency device or materials is required. The design of the flexible bag and the spacecraft interface is synchronously developed by combining the design of the layout scheme in the manned spacecraft cabin, so that the lifesaving system can be well shaped with the inner wall of the sealed cabin when being unfolded for use on track, instruments, lighting, living goods and the like are wrapped in the lifesaving system as far as possible, and the original function and design state of the airship are kept. Meanwhile, the function of carrying articles in and out of the lifesaving system is designed by matching with pressure clothes in the cabin, so that the requirement of carrying the articles in a sudden manner is met.
And designing an installation interface for installing the petal-shaped assembly in the sealed cabin based on an in-cabin layout scheme, a lifesaving system structure scheme and a multiplexing scheme. In the present embodiment, collision risk analysis is performed on the sealed cabin, and the flap assembly is folded and disposed around the cabin wall where the collision risk exceeds a preset condition according to the result of the collision risk analysis. The installation position is convenient for the operation of astronauts and meets the requirement of ergonomics.
And designing the folding mode and the unfolding mode of the petal-shaped assembly. In the embodiment, the influence of the crease generated after long-term folding on the material performance is eliminated through the folding and unfolding design of the lifesaving system, and the on-orbit unfolding time of the astronaut is ensured to meet the requirement. The related operations should meet ergonomic requirements.
According to one embodiment of the invention, the flap assembly is connected to the bulkhead by means of a seal or mechanical fastening.
According to one embodiment of the invention, the use mode scheme comprises a pressure emergency preparation sub-scheme, a life-saving system deployment and state setting sub-scheme and a life-saving system withdrawal and state setting sub-scheme before returning; in the pressure emergency preparation sub-scheme, after the on-orbit judgment of the pressure emergency, the astronaut immediately sets non-pressure-bearing equipment in the cabin in an emergency mode and wears pressure clothes in the cabin. Referring to fig. 2, in the present embodiment, the pressure emergency preparation needs to be completed within 10 minutes. The emergency setting step of the non-pressure-bearing equipment in the cabin specifically comprises the following steps: the pressure relief valve is arranged at a pressure relief gear; closing the gas and oxygen supply valve; closing the fan; closing the condensed water storage tank; the pressure suit is worn and leakage is detected.
In the sub-scheme of the expansion and state setting of the lifesaving system, the lifesaving system is expanded, and pressure maintaining and leakage detecting are carried out until the lifesaving system can be maintained normal. In the embodiment, the articles required to work and be used in life in the life-saving system are transferred according to the list, the flexible bag is unfolded, the zipper is closed, an independent closed environment is established, then air is supplied to the astronaut to achieve the pressure for life, and after the pressure maintaining and leakage detecting are qualified, the flexible bag can work normally. The astronaut takes off the pressure suit in the capsule and works and lives in the flexible bag. Referring to fig. 2, in the present embodiment, the deployment and state setting of the rescue system is completed within 60 minutes. The method specifically comprises the following steps: transferring the articles; unlocking the flexible cabin inner bag and fixing the package; the unfolded flexible bag is adhered with the hasp; connecting the flexible crusty pancake with a power supply and communication interface of an airship in place; closing the zipper, and bonding by using a 3M adhesive tape; setting a state, supplying gas and maintaining pressure; leak rate, etc.
In the sub-scheme of the recovery and state setting of the rescue system before returning, the rescue system is stored and fixed, and the state setting before returning is carried out on equipment in the sealed cabin. In this embodiment, before returning, the flexible bag needs to be unlocked, stored, and fixed, and the cabin interior equipment needs to be set in a state before returning. The astronaut sits in the seat in the cabin and waits for return according to the ground requirements. Referring to fig. 2, in the present embodiment, it specifically includes: removing the comprehensive display of the collection emergency, the manual control command board and the like, and fixing the diet bag and the like; setting the state of equipment in the cabin according to the step of pressure emergency preparation; withdrawing and fixing the flexible cabin inner bag according to the steps; the astronaut sits in the seat in the cabin and waits for return according to the ground requirements.
The foregoing is merely exemplary of particular aspects of the present invention and devices and structures not specifically described herein are understood to be those of ordinary skill in the art and are intended to be implemented in such conventional ways.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The design method of the lifesaving system for the pressure emergency of the manned spacecraft sealed cabin comprises the following steps:
s1, obtaining an intra-cabin structure scheme of a sealed cabin of a manned spacecraft and an intra-cabin layout scheme of the sealed cabin;
s2, generating a rescue system structure scheme of a rescue system which can be unfolded and stored in the sealed cabin based on the cabin structure scheme, and generating an interface design scheme of the rescue system by combining the cabin layout scheme and the rescue system structure scheme;
and S3, generating a use mode scheme for deploying and storing the lifesaving system based on the lifesaving system structure scheme and the interface design scheme.
2. The method of claim 1, wherein the rescue system is configured as a detachable and assembled flexible bag structure for deployment and storage in the sealed capsule in the rescue system structure scheme.
3. The method of claim 2, wherein the step of generating a structural scheme of a rescue system for a rescue system deployable and stowable in the capsule based on the structural scheme of the capsule comprises:
selecting a molding material of the lifesaving system;
the lifesaving system is arranged into a shapeable flexible bag structure matched with the inner shape and size of the sealed cabin;
splitting the flexible bladder structure into a plurality of petal-shaped components that are detachably connected to one another;
and arranging a connecting structure of the petal-shaped assembly.
4. A method of designing a rescue system according to claim 3, wherein the attachment structure is a containment zipper.
5. The method of claim 4, wherein the step of generating the interface design scheme of the rescue system by combining the cabin layout scheme and the rescue system structure scheme comprises:
generating a multiplexing scheme of equipment or materials in the spacecraft in a normal task and emergency state;
designing a mounting interface for mounting the petal-shaped assembly in the sealed cabin based on the cabin layout scheme, the lifesaving system structure scheme and the multiplexing scheme;
and designing the folding mode and the unfolding mode of the petal-shaped assembly.
6. The rescue system design method according to claim 5, wherein in the step of designing the installation interface for installing the petal assembly in the capsule based on the cabin layout scheme, the rescue system structure scheme and the multiplexing scheme, the capsule is subjected to collision risk analysis, and the petal assembly is folded and arranged around the cabin wall with a collision risk exceeding a preset condition according to the result of the collision risk analysis.
7. The method of claim 6, wherein the flap assembly is attached to the bulkhead with a seal or mechanical fastening.
8. The life saving system design method of claim 7, wherein the usage pattern scheme comprises a pressure emergency preparation sub-scheme, a life saving system deployment and status setting sub-scheme, a life saving system withdrawal and status setting sub-scheme before returning; wherein the content of the first and second substances,
in the pressure emergency preparation sub-scheme, after the on-track pressure emergency is judged, emergency setting is carried out on non-bearing equipment in a sealed cabin;
in the sub-scheme of the expansion and state setting of the lifesaving system, the lifesaving system is expanded, and pressure maintaining and leakage detecting are carried out until the lifesaving system can be maintained normal;
in the sub scheme of the rescue system withdrawal and state setting before returning, the rescue system is fixedly stored, and the equipment in the sealed cabin is set in the state before returning.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011210305.7A CN112287462A (en) | 2020-11-03 | 2020-11-03 | Design method of pressure emergency lifesaving system for manned spacecraft sealed cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011210305.7A CN112287462A (en) | 2020-11-03 | 2020-11-03 | Design method of pressure emergency lifesaving system for manned spacecraft sealed cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112287462A true CN112287462A (en) | 2021-01-29 |
Family
ID=74351389
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011210305.7A Pending CN112287462A (en) | 2020-11-03 | 2020-11-03 | Design method of pressure emergency lifesaving system for manned spacecraft sealed cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112287462A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2006134153A (en) * | 2006-09-25 | 2008-03-27 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" (RU) | EMERGENCY RESCUE SPACE DECK FOR A VEHICLE |
| US20080087770A1 (en) * | 2006-10-11 | 2008-04-17 | Christopher A. Rygaard | Conformal airlock assembly and method |
| CN106379562A (en) * | 2015-12-16 | 2017-02-08 | 北京空间技术研制试验中心 | Control method for harmful gas in on-orbit flying manned spacecraft cabin |
| US20190286762A1 (en) * | 2018-03-19 | 2019-09-19 | Northwest Instrument Inc. | Method and System for Space Design |
| CN110963088A (en) * | 2019-11-15 | 2020-04-07 | 北京空间机电研究所 | Pressure protection device under emergent decompression condition of manned spacecraft sealed cabin |
-
2020
- 2020-11-03 CN CN202011210305.7A patent/CN112287462A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2006134153A (en) * | 2006-09-25 | 2008-03-27 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" (RU) | EMERGENCY RESCUE SPACE DECK FOR A VEHICLE |
| US20080087770A1 (en) * | 2006-10-11 | 2008-04-17 | Christopher A. Rygaard | Conformal airlock assembly and method |
| CN106379562A (en) * | 2015-12-16 | 2017-02-08 | 北京空间技术研制试验中心 | Control method for harmful gas in on-orbit flying manned spacecraft cabin |
| US20190286762A1 (en) * | 2018-03-19 | 2019-09-19 | Northwest Instrument Inc. | Method and System for Space Design |
| CN110963088A (en) * | 2019-11-15 | 2020-04-07 | 北京空间机电研究所 | Pressure protection device under emergent decompression condition of manned spacecraft sealed cabin |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5350138A (en) | Low-cost shuttle-derived space station | |
| US6467221B1 (en) | Spacecraft sleeping berth | |
| WO2007106096A2 (en) | Modular spacecraft | |
| US8122646B1 (en) | Method and apparatus for an inflatable shell | |
| CN107651218A (en) | The dual airtight protection manned lunar surface's lander of symmetrical expression cockpit layout | |
| CN110963088B (en) | Pressure protection device under emergent decompression condition of manned spacecraft sealed cabin | |
| CN111619827A (en) | Inflatable expansion type living cabin for spacecraft | |
| KR20080077974A (en) | Airliftable tank for storing a product that is to be jettisoned during flight | |
| US6293500B1 (en) | Integrated translation tube assembly for a space module | |
| Litteken et al. | Design of a microgravity hybrid inflatable airlock | |
| CN112287462A (en) | Design method of pressure emergency lifesaving system for manned spacecraft sealed cabin | |
| US20210347469A1 (en) | Aircraft provided with a buoyancy system, and a buoyancy method | |
| WO2007062440A8 (en) | Collapsible space shuttle | |
| US3520503A (en) | Omnidirectional multiple impact landing system | |
| Litteken et al. | Development of an inflatable airlock for deep space exploration | |
| Gardinier et al. | Design and testing of the K-1 reusable launch vehicle landing system airbags | |
| CN106080487A (en) | The most floating riding car buoyancy escape system is can guarantee that before water logging does not has | |
| Howard | A Two-Chamber Multi-Functional Airlock for a Common Habitat Architecture | |
| Valle et al. | System Integration Comparison Between Inflatable and Metallic Spacecraft Structures | |
| EP2185411B1 (en) | Flotation systems | |
| RU2263613C1 (en) | System of controllable descent and landing of flying vehicle in emergency situation (versions) | |
| Campbell et al. | Advanced inflatable airlock system for EVA | |
| Kennedy et al. | Inflatable Structures Technology Handbook | |
| Bell | Hybrid Deployable Habitat Structures for Orbital and Lunar/Planetary Applications | |
| Mary | EVA Vehicle Interfaces |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |