CN109178357B - Space life support device - Google Patents
Space life support device Download PDFInfo
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- CN109178357B CN109178357B CN201810999237.3A CN201810999237A CN109178357B CN 109178357 B CN109178357 B CN 109178357B CN 201810999237 A CN201810999237 A CN 201810999237A CN 109178357 B CN109178357 B CN 109178357B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Abstract
The invention discloses a space life support device, comprising: the cabin body comprises a cylinder body and an end cover for installing an opening of the cylinder body, and a closed space is formed by enclosing; the cover plate is arranged in the cylinder body to divide the closed space into an upper part and a lower part; the upper space is internally provided with a vertical plate along the axial direction, and the upper space is divided into a left part and a right part; the lower space is communicated with the left space and the right space; the ventilation device is arranged on the vertical plate; the temperature control device comprises a heater, a temperature measuring element and a temperature control circuit; the heater and the temperature measuring element are arranged in the lower space; the temperature control circuit is positioned in the right space, the input end of the temperature control circuit is connected with the temperature measuring element, and the output end of the temperature control circuit is connected with the heater; the pneumatic control device comprises an oxygen supply pipeline, a pneumatic control circuit and a pressure release valve which are connected in sequence; the input end of the pneumatic control circuit is connected with the measuring element. The problem that life support device is bulky has been solved to this scheme, is suitable for near space and reduces the volume, and accessible aircraft carries on and gets into near space.
Description
Technical Field
The invention relates to the technical field of life support of adjacent space, in particular to a space life support device.
Background
The near space is an airspace 20-100 kilometers from the ground. Since the flight altitude of a commercial aviation aircraft is about 10 km from the ground, and the operating altitude of an aerospace satellite is more than 200 km from the ground, the adjacent space is a space combination of aviation and aerospace.
The adjacent space belongs to an atmosphere stratosphere, and the weather is stable and is not influenced by severe weather. Therefore, the adjacent space carrying has feasibility and wide development prospect. However, at present, only life support devices for the ground and the outer space are available, but no life support device for the adjacent space is available, the life support device for the outer space is generally complex in structure and large in size, is usually launched to the outer space by a rocket, and is not suitable for being carried on an aircraft; the ground life support device is suitable for ground air pressure and temperature and is not suitable for animal survival in the low-temperature and low-pressure environment in the adjacent space.
In order to solve the problems, the scheme provides the life support device for the near space, which is used as a carrying device of an aircraft, so that an animal can safely lift off and return along with the aircraft.
Disclosure of Invention
The invention provides a space life support device which is used for overcoming the defects of large volume, inconvenience in carrying and the like in the prior art, is small in size, is suitable for being used in an adjacent space and is convenient for carrying an aircraft.
To achieve the above object, the present invention provides a space life support device, comprising:
the cabin body comprises a cylinder body with an opening at one end and an end cover arranged at the opening end of the cylinder body, and the cylinder body and the end cover are enclosed to form a closed space; a cover plate is transversely arranged in the cylinder body and divides the closed space into an upper part and a lower part; a vertical plate is axially arranged in the upper space and divides the upper space into a left part and a right part; the lower space is communicated with the left space and the right space;
the ventilation device is arranged on the vertical plate, and the gas in the closed space circularly flows in a channel formed by the left space, the lower space and the right space under the action of the ventilation device;
the temperature control device comprises a heater, a temperature measuring element and a temperature control circuit; the heater and the temperature measuring element are arranged in the lower space; the temperature control circuit is positioned in the right space, the input end of the temperature control circuit is connected with the temperature measuring element, and the output end of the temperature control circuit is connected with the heater and used for controlling the working state of the heater according to the signal output by the temperature measuring element and the set temperature;
the pneumatic control device comprises an oxygen supply pipeline, a pneumatic control circuit and a pressure release valve which are connected in sequence; the input end of the pneumatic control circuit is connected with a measuring element for measuring the internal environmental parameters of the closed space; the pneumatic control circuit controls the working states of the oxygen supply pipeline and the pressure release valve according to the output signal of the measuring element and a set threshold value; and the pressure release valve, the oxygen supply pipeline and the connecting pipe between the oxygen bottles are all arranged on the cabin body.
According to the space life support device provided by the invention, the cabin body is divided into four spaces through the cover plate and the vertical plate, wherein the lower space is used for providing a moving space for organisms, the other three spaces form a ventilation channel, meanwhile, the cover plate and the vertical plate provide a bearing basis for the measurement and control element, the heater and the temperature control device are used for providing a temperature suitable for life survival for the space, and the ventilation device and the air control device are used for providing a gas atmosphere suitable for life survival for the space.
Drawings
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 description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a perspective view of a space life support device provided by an embodiment of the invention;
FIG. 2 is an exploded perspective view of FIG. 1;
FIG. 3 is a partially exploded perspective view of FIG. 2;
FIG. 4 is a perspective view of FIG. 3 from another perspective;
FIG. 5 is a schematic longitudinal cross-sectional view of FIG. 3;
fig. 6 is a schematic diagram of the pneumatic control device of fig. 1.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
The invention provides a space life support device.
Example one
Referring to fig. 1 to 4, the present invention provides a space life support device, including: the device comprises a cabin body 1, a ventilation device 2, a temperature control device and an air control device 4;
referring to fig. 5, the cabin 1 includes a cylinder 11 with an opening at one end and an end cover 12 installed at the opening end of the cylinder 11 through a bolt assembly, and the cylinder 11 and the end cover 12 enclose a closed space 10; a cover plate 13 is transversely arranged in the cylinder 11, and the cover plate 13 divides the closed space 10 into an upper space 101 and a lower space 102; an upright plate 14 is axially arranged in the upper space 101, and the upright plate 14 divides the upper space 101 into a left space 101a and a right space 101 b; the lower space 102 is communicated with the left space 101a and the right space 101b (for forming an air duct for air circulation);
a sealing structure is arranged between the end cover 12 and the cylinder body 11 so as to form a closed space 10 in the cylinder body, and the cover plate 13 is arranged along the cross section direction of the cylinder body 11 and is connected with a step structure on the inner wall of the cylinder body 11 through a connecting piece; the vertical plate 14 (for mounting each test element and the circuit board) is perpendicular to the cover plate 13 and fixed to the column extending from the bottom of the cylinder 11 to the cover plate 13 through at least two connectors, the edge of the left half of the cover plate 13 is provided with a plurality of air supply holes 131 to communicate the lower space 102 with the left space 101a, and the edge of the right half of the cover plate 13 is provided with a plurality of air return holes 132 to communicate the lower space 102 with the right space 101 b.
The cabin body 1 is made of light materials, and structural design satisfies withstand pressure about 0.9 ~ 1.0 standard atmospheric pressure, in order to guarantee the temperature requirement of cabin body 1 inside, set up the heat preservation in cabin body 1 outside, the heat preservation includes heat preservation sleeve 15 and heat preservation lid 16, barrel 11 is installed in heat preservation sleeve 15, end cover 12 is installed on the opening of barrel 11, heat preservation lid 16 is installed on heat preservation sleeve 15's opening, and cover end cover 12, encapsulate cabin body 1 that forms with barrel 11 and end cover 12 connection inside.
The ventilating device 2 is arranged on the vertical plate 14, and the gas in the closed space 10 circularly flows in a channel formed by the left space 101a, the lower space 102 and the right space 101b under the action of the ventilating device 2;
the temperature control device comprises a heater 31, a temperature measuring element 32 and a temperature control circuit 33; the heater 31 and the temperature measuring element 32 are installed in the lower space 102; the temperature control circuit 33 is positioned in the right space 101b, has an input end connected with the temperature measuring element 32 and an output end connected with the heater 31, and is used for controlling the working state of the heater 31 according to the signal output by the temperature measuring element 32 and the set temperature;
in this embodiment, the ventilation device 2 includes a blower or a fan, and the heater 31 includes a heating module 311 (mainly for heating the circulating air) installed at an air outlet of the blower and an electric heating plate 312 (mainly for heating the position of the animal) installed at the bottom of the lower space 102; the gas in the closed space 10 is heated from the upper and lower ends respectively, the internal heat exchange process is accelerated, the temperature measuring element 32 is installed on the cover plate 13, and comprises a long temperature measuring rod (for sensing the temperature of the electric heating plate 312) with a sensing end extending into the lower space 102 near the electric heating plate 312 and a short temperature measuring rod (for sensing the temperature of the space around the animal) extending into the upper part of the lower space 102, the temperature control circuit 33 controls the working state of the electric heating plate 312 according to the signal output by the long temperature measuring rod and the set temperature threshold thereof, and controls the working state of the heating module 311 according to the signal output by the short temperature measuring rod and the set temperature threshold thereof, the set temperature thresholds of the two temperature measuring rods can be the same or different, and in the same time, the working states of the heating module 311 and the electric heating plate 312 can be the same or. On one hand, the uniformity of ventilation and temperature in the biological protection cabin is ensured, and on the other hand, the air is heated to control the temperature in the biological protection cabin. Through fan, equipment fixing board, transparent cover plate, supply-air hole, return air hole, make the interior gas of cabin form an air current circulation, when the air current passes through heating module, realize thermal exchange, and then heat the air in the ecological protection cabin, make its temperature keep in appropriate range.
Referring to fig. 6, the pneumatic control device 4 includes an oxygen supply pipeline 41, a pneumatic control circuit 42 and a pressure release valve 43 connected in sequence; the input end of the pneumatic control circuit 42 is connected with a measuring element 44 for measuring the internal environmental parameters of the closed space; the pneumatic control circuit 42 controls the working states of the oxygen supply pipeline 41 and the pressure release valve 43 according to the output signal of the measuring element 44 and a set threshold value; the pressure release valve 43 and the connecting pipe between the oxygen supply pipeline 11 and the oxygen cylinder are both arranged on the cabin body 1.
In order to save space and simplify circuits and pipelines, a cabin body 1 is provided with a connector 17 for externally connecting an aircraft control system and an interface 18 for releasing and restoring cabin pressure, a temperature control circuit 33 and a pneumatic control circuit 42 are integrated on a circuit board (a controller, which can specifically adopt a chip), the controller is connected with the connector 17 and is used for monitoring various environmental parameters in the cabin by means of the aircraft control system in a ground monitoring system, in order to solve the condition of animals in a lower space 102, a camera 100 can be installed on a vertical plate 14 at a position right opposite to the lower space, a cover plate 13 is made of transparent materials, and one surface of the cover plate 13 facing the lower space 102 is provided with an LED lamp strip 200 so that the camera 100 can shoot the moving state of the animals through the cover plate 13. The camera 100 and the LED lamp strip 200 are both connected with the controller.
A plurality of high-pressure oxygen cylinders carry the required oxygen consumption of a flight task, and the one-level stop valve of every oxygen cylinder export installation, one-level relief pressure valve and inflation valve as an organic whole, this valve itself have an interface installation manometer, this interface is reformed transform to the accessible when the life insurance system uses, directly with high pressure sensor rather than the installation.
The outlet pressure of the primary pressure reducing valve is about 0.45MPa, and the pressure reducing valve from the gas cylinder to the primary pressure reducing valve is arranged outside the cabin body 1. Two gas cylinders are decompressed by a primary pressure reducing valve and then combined into one path through a tee joint to be connected with an inlet pipeline of a secondary pressure reducing box in the cabin body 1.
An air control device 42 collects the oxygen concentration value of a measuring point (a measuring element 44, specifically comprising an oxygen concentration measuring instrument) installed in a sealed cabin (the sealed space 10) by security personnel, once the value is lower than a set value of 20%, an electromagnetic valve of an oxygen supply pipeline 41 is driven to release oxygen into the sealed cabin, and once the value reaches a set value of 22%, the electromagnetic valve is closed, and the release of oxygen into the sealed cabin is stopped.
When the aircraft carrying the life support device ascends, the pressure difference between the inside and the outside of the cabin is detected through the measuring element 44 (the pressure sensor), and when the pressure difference between the inside and the outside of the cabin exceeds 0.9 atmospheric pressure, the air control device 42 drives the pressure release valve 43 to open, so that the pressure in the cabin needs to be released to about 0.9 atmospheric pressure. When returning to the ground, in order to open the cabin end cover 12, the pressure relief valve 43 needs to be opened to restore the pressure in the cabin to the local atmospheric pressure; the action of the pressure release valve 43 in pressure return can be automatically driven by the pneumatic control circuit 42 (when the pressure difference between the inside and the outside reaches 0.1 atmosphere), and can also be realized by a manual valve arranged outside the cabin.
Preferably, a platform 103 is arranged at one end of the lower space 102 far away from the cover plate 13, and a fence 104 is arranged between the cover plate 13 and the bottom wall of the lower space 102 and surrounds the platform 103 for one circle; the annular space formed between the fence 104 and the peripheral side wall of the cabin body is internally provided with a cushion; the bottom of the cushion is arranged on the bottom wall of the cabin body, a ventilation space 300 is arranged between the top of the cushion and the cover plate 13, and the part of the cover plate 13, which is opposite to the ventilation space 300, is provided with ventilation holes (namely a ventilation hole 131 and a return air inlet 132); the part of the fence 104, which is opposite to the ventilation space 300, is also provided with a ventilation hole, and the inside of the cushion can adsorb liquid media.
The living things can move on the platform 103, the air flow in the cabin enters the heating module 311 from the upper part of the right space 101b through the fan, is heated, then is blown into the left space 101a through the air inlet at the top of the standing plate 14, passes through the air supply hole 131 on the cover plate 13, enters the ventilation space 300 of the lower space 102, enters the living things moving space through the air vent at the upper part of the fence 104, then passes through the air return hole 132 on the cover plate 13 upwards after passing through the air vent at the upper part of the fence and the fence 104, and returns to the right space 101b, thus completing a cycle.
For easy to assemble, the pad floats and falls into two parts to install: first pad floats 105a, second pad floats 105b, and the material that can adsorb water or other liquid medium is specifically adopted to the pad floats, plays the buffering damping effect on the one hand, and on the other hand adsorptivity is stronger, can adsorb the moisture that overflows from rail 104 when carrying aquatic animals, prevents to get into and erodees the circuit in the right part space 101b of top.
The living thing survival guarantee comprises a living thing moving platform, water, a fence, a cushion, a transparent cover plate, an electric heating plate and a temperature measuring rod, and the water temperature is controlled in a proper range through the control of the electric heating plate and the temperature measuring rod, so that living things have a comfortable living environment. The living thing survivorship guarantee module is also a temperature control backup at the same time, when the temperature in the device can not be controlled within a set range, the living thing can be guaranteed to have a proper temperature living environment through the module, and when the device is not controlled by air pressure, water can play a pressure maintaining role on the living thing. In addition, the water has the buffering capacity, and plays a certain role in buffering and protecting living objects when the aircraft descends and collides with the ground.
Preferably, the temperature control circuit 33 and the pneumatic control circuit 42 are integrated on a circuit board (controller), and the controller is installed on the vertical plate 14; the controller, the measuring element 44 and the ventilation device 2 are all located in the right space 101a and isolated from the lower space 102, in order to further prevent moisture, dust and the like from entering the right space 101a, a lower cover plate, a protective cover 600 and an upper cover plate 700 can be respectively arranged on the right side of the vertical plate 14, the controller is installed in a space surrounded by the upper cover plate 700, the lower cover plate and the protective cover 600, a water blocking structure 500 is installed on the lower cover plate at a position close to the cover plate 13, and a sealing structure 400 is arranged between the water blocking structure 500 and the cover plate 13. Protected by a cushion floating structure, a sealing structure 400, a water-blocking structure 500 and a protective cover 600.
The temperature measuring element 32 extends into the space surrounded by the fence 104 from the right space 101b through the cover plate 13; a fence 106 is arranged at one end of the interior of the fence 104 close to the temperature measuring element 32, the top of the fence 106 is connected with the cover plate 13, the bottom of the fence 106 is connected with the bottom wall of the cabin, and the platform 103 and the temperature measuring element 32 are respectively positioned at two sides of the fence 106; preventing vibration or shock from damaging the temperature sensing element 32. The control end of the temperature measuring element 32 for outputting a signal extends into the right space 101b through the cover plate 13, and is protected by the sealing structure 400.
The electric heating plate 312 is installed at the bottom of the platform 103 for heating the platform 103.
Preferably, an image acquisition module and a data transmission module (a component of the controller, not shown) are further integrated on the circuit board; the cover plate 13 is made of a transparent material, the vertical plate 14 is provided with a camera 100, and the camera 100 is located in the left space; the cover plate 13 is provided with an LED lamp for illuminating the lower space; the output end of the camera 100 is connected with the image acquisition module; the data transmission module is used for being connected with a ground control system through a wireless network. The activity and vital signs of the living beings located in the layer can be monitored by means of the aircraft control system via a ground control system. The control and data transmission module realizes power supply and control of the fan, the heating module, the electric heating plate and the illuminating lamp, collects parameters such as the running state, the temperature, the air pressure, the water temperature and the oxygen concentration of equipment in the cabin and transmits the parameters to the ground of the central control system. And the image acquisition and transmission module acquires the activity state of the living objects in the cabin in real time and transmits the activity state to the image processing central system.
Preferably, referring to fig. 6, the oxygen supply line 41 includes:
an automatic circuit including a first pipe 411a, and a first shut-off valve 411b, a first pressure reducing valve 411c, a first solenoid valve 411d, and a first low pressure sensor 41e sequentially connected to the first pipe 411 a; the inlet end of the first conduit 411a is used for connecting an oxygen cylinder outside the cabin; the outlet end of the first duct 411a is located in the right space 101 b; and the control end of the first electromagnetic valve 421d is connected with the output end of the pneumatic control circuit 42. The pipeline structure has reliable action, simple structure and small occupied space.
Preferably, the automatic pipeline further comprises an inlet end connected in parallel with the automatic pipeline:
a manual line including a second pipe 412a, and a second cut-off valve 412b, a second pressure reducing valve 412c, and a second low pressure sensor sequentially connected to the second pipe 412 a; the inlet end of the second pipeline 412a is used for connecting an oxygen cylinder outside the cabin; the outlet end of the second pipe 412a is located in the right space 101 b.
The first and second pipes 411a and 412a are connected to one pipe at the oxygen inlet end, and the pipe penetrates the outside of the cabin to connect two oxygen cylinders located outside the cabin, and the first and second pipes 411a and 412a are supplied with oxygen through the oxygen cylinders.
In the normal mode, the second stop valve 412b at the outlet of the manual pipeline is closed, and when the valve of the automatic control pipeline is not opened or the pressure reducing valve fails, the first stop valve 411b of the automatic control pipeline is closed, and the second stop valve 412b of the manual pipeline is opened, so that the switching control of the oxygen supply system is realized. To simplify the structure of the cabin 1 and to facilitate the operation, all pressure relief valves 43 and the pipes connected to the outside are connected to the interface 18.
Preferably, the pressure relief valve 43 comprises a second solenoid valve 431, the second solenoid valve 431 is installed on a first branch pipe penetrating through the cabin 1, and a control end of the second solenoid valve 431 is connected with the pneumatic control circuit 42. The first branch is connected to a connection 18 for cabin pressure relief. The action of the pressure relief valve 43 is automatically controlled.
Preferably, the pressure relief valve 43 further comprises a first manual valve 432 located in the chamber, the first manual valve 432 being mounted on a second branch pipe extending through the chamber 1; the second branch is connected to a connection 18 for cabin pressure relief.
Preferably, the pressure relief valve 43 further comprises a second manual valve 433 positioned outside the cabin 1, and the second manual valve 433 is installed on a third branch pipe penetrating through the cabin 1. The third branch is connected to a connection 18 for cabin pressure relief.
To account for system redundancy and safety, manual and automatic modes are set, respectively. Manual mode: a stop valve and a plug (which is arranged on the same side of the cabin body as the stop valve) are respectively arranged inside and outside the cabin. The ground can be operated by personnel in the cabin or ground workers.
Preferably, the measuring unit 44 includes at least three oxygen concentration measuring instruments 441 installed at different positions in the enclosed space 10 and at least three pressure sensors 442 installed at different positions in the enclosed space 10;
the pneumatic control circuit 42 controls the first electromagnetic valve 421d to complete oxygen supply to the enclosed space 10 according to the average value of the signals output by all the oxygen concentration measuring instruments 441;
the pneumatic control circuit 42 controls the second solenoid valve 412c to complete the pressure relief of the enclosed space 10 according to the average value of the signals output by all the pressure sensors 442.
In order to reduce the error between the measured values and the actual values of the oxygen concentration measuring instrument 441 and the pressure sensor 442 at a single measuring point, a plurality of measuring points are taken to be averaged, and the error caused by uneven distribution of oxygen and air pressure is reduced.
The external structure of the life support device comprises a heat insulation layer, a cabin body, a flange cover plate, a cabin penetrating aviation plug, a repressing valve and the like, wherein the heat insulation layer plays a role in heat insulation, a closed space formed by the cabin body and the flange cover plate plays a role in isolation and pressure maintaining, the cabin penetrating aviation plug is used for power supply and communication of the life support cabin, and the repressing valve is used for air pressure recovery in the life support cabin. Life support device inner structure mainly comprises life support equipment and measurement and control equipment, including electric plate, temperature measurement pole, movable platform, heating module, fan, controller, sensor, lamp strip, camera etc. these equipment all install through equipment fixing board, later wholly again with the passenger cabin installation fixed.
The design of adopting above-mentioned structure has the advantage:
1. the side wall of the cabin body is not required to be welded with equipment for installing a supporting column and the like, so that the cabin body is simplified to process;
2. the installation and the test of partial equipment can be carried out outside the cabin, the operation is convenient, the test is flexible, and the winding of the line is avoided;
3. the equipment mounting plate, the upper cover plate, the lower cover plate and the inner wall of the cabin body form a waterproof closed space, and the waterproof closed space can protect electrical equipment such as a controller and a fan;
4. the equipment installation space is separated from the animal activity space, the activity space is large, and the functional design is convenient to carry out.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (9)
1. A space life support device, comprising:
the cabin body comprises a cylinder body with an opening at one end and an end cover arranged at the opening end of the cylinder body, and the cylinder body and the end cover are enclosed to form a closed space; a cover plate is transversely arranged in the cylinder body and divides the closed space into an upper part and a lower part; a vertical plate is axially arranged in the upper space and divides the upper space into a left part and a right part; the lower space is communicated with the left space and the right space;
the ventilation device is arranged on the vertical plate, and the gas in the closed space circularly flows in a channel formed by the left space, the lower space and the right space under the action of the ventilation device;
the temperature control device comprises a heater, a temperature measuring element and a temperature control circuit; the heater and the temperature measuring element are arranged in the lower space; the temperature control circuit is positioned in the right space, the input end of the temperature control circuit is connected with the temperature measuring element, and the output end of the temperature control circuit is connected with the heater and used for controlling the working state of the heater according to the signal output by the temperature measuring element and the set temperature;
the pneumatic control device comprises an oxygen supply pipeline, a pneumatic control circuit and a pressure release valve which are connected in sequence; the input end of the pneumatic control circuit is connected with a measuring element for measuring the internal environmental parameters of the closed space; the pneumatic control circuit controls the working states of the oxygen supply pipeline and the pressure release valve according to the output signal of the measuring element and a set threshold value; the pressure release valve, the oxygen supply pipeline and the connecting pipe between the oxygen bottles are all arranged on the cabin body;
a platform at one end far away from the cover plate in the lower space, and a fence is arranged between the cover plate and the bottom wall of the lower space and surrounds the platform for one circle;
the annular space formed between the fence and the peripheral side wall of the cabin body is internally provided with a cushion; the bottom of the cushion is arranged on the bottom wall of the cabin body, a ventilation space is formed between the top of the cushion and the cover plate, and ventilation holes are formed in the part of the cover plate, which is over against the ventilation space, and the part of the fence, which is over against the ventilation space;
the inside of the cushion float is filled with a liquid medium.
2. The space life support device of claim 1, wherein the temperature control circuit and the gas control circuit are integrated on a circuit board and mounted on the vertical plate; the measuring element and the ventilation device are both positioned in the right space;
the temperature measuring element extends into the space surrounded by the fence from the right space through the cover plate;
a fence is arranged at one end, close to the temperature measuring element, in the fence, the top of the fence is connected with the cover plate, the bottom of the fence is connected with the bottom wall of the cabin body, and the platform and the temperature measuring element are respectively positioned at two sides of the fence;
the heater is installed at the bottom of the platform.
3. The space life support device of claim 2, wherein an image acquisition module and a data transmission module are further integrated on the circuit board;
the cover plate is made of transparent materials, a camera is mounted on the vertical plate, and the camera is located in the left space;
the cover plate is provided with an LED lamp for illuminating the lower space;
the output end of the camera is connected with the image acquisition module;
the data transmission module is used for being connected with a ground control system through a wireless network.
4. The space life support apparatus of claim 1, wherein the oxygen supply line comprises:
the automatic pipeline comprises a first pipeline, and a first stop valve, a first pressure reducing valve, a first electromagnetic valve and a first low-pressure sensor which are sequentially connected to the first pipeline;
the inlet end of the first pipeline is used for connecting an oxygen bottle outside the cabin;
the outlet end of the first conduit is located in the right space;
and the control end of the first electromagnetic valve is connected with the output end of the pneumatic control circuit.
5. The space life support device of claim 4, further comprising an inlet end in parallel with said automated conduit:
the manual pipeline comprises a second pipeline, and a second stop valve, a second pressure reducing valve and a second low-pressure sensor which are sequentially connected to the second pipeline;
the inlet end of the second pipeline is used for connecting an oxygen bottle outside the cabin;
the outlet end of the second conduit is located in the right space.
6. The space life support device of claim 4, wherein said pressure relief valve comprises a second solenoid valve mounted on a first branch pipe extending through said cabin, a control end of said second solenoid valve being connected to said pneumatic control circuit.
7. The space life support apparatus of claim 6, wherein said pressure relief valve further comprises a first manual valve positioned within said chamber, said first manual valve mounted on a second manifold extending through said chamber;
the pressure release valve further comprises a second manual valve located outside the cabin, and the second manual valve is installed on a third branch pipe penetrating through the cabin body.
8. The space life support device of claim 7, wherein said measuring elements include at least three oxygen concentration meters installed at different locations within the enclosed space and at least three pressure sensors installed at different locations within the enclosed space;
the air control circuit controls the first electromagnetic valve to complete oxygen supply to the closed space according to the average value of the signals output by all the oxygen concentration measuring instruments;
and the air control circuit controls the second electromagnetic valve to complete the pressure relief of the closed space according to the average value of the signals output by all the pressure sensors.
9. The space life support device of any one of claims 1 to 8, wherein the outer wall of the cabin body is provided with a heat insulation sleeve, and the heat insulation sleeve comprises a heat insulation sleeve arranged on the outer wall of the barrel body and a heat insulation cover arranged on an opening of the heat insulation sleeve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810999237.3A CN109178357B (en) | 2018-08-30 | 2018-08-30 | Space life support device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810999237.3A CN109178357B (en) | 2018-08-30 | 2018-08-30 | Space life support device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109178357A CN109178357A (en) | 2019-01-11 |
| CN109178357B true CN109178357B (en) | 2020-09-11 |
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| EP0588739A1 (en) * | 1992-09-14 | 1994-03-23 | AEROSPATIALE Société Nationale Industrielle | Procedure and device for the thermomechanical testing through simulation of a heat shield or the like |
| US9812925B2 (en) * | 2014-07-18 | 2017-11-07 | Microsoft Technology Licensing, Llc | Closed loop data center and organic life ecosystem |
| CN107861548A (en) * | 2017-12-08 | 2018-03-30 | 北京强度环境研究所 | A kind of control system for low-oxygen environment experiment |
| CN207488868U (en) * | 2017-12-08 | 2018-06-12 | 北京强度环境研究所 | A kind of control system for low-oxygen environment experiment |
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| EP0588739A1 (en) * | 1992-09-14 | 1994-03-23 | AEROSPATIALE Société Nationale Industrielle | Procedure and device for the thermomechanical testing through simulation of a heat shield or the like |
| US9812925B2 (en) * | 2014-07-18 | 2017-11-07 | Microsoft Technology Licensing, Llc | Closed loop data center and organic life ecosystem |
| CN107861548A (en) * | 2017-12-08 | 2018-03-30 | 北京强度环境研究所 | A kind of control system for low-oxygen environment experiment |
| CN207488868U (en) * | 2017-12-08 | 2018-06-12 | 北京强度环境研究所 | A kind of control system for low-oxygen environment experiment |
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