CN104076834A - Spacecraft sealed cabin humidity control system and method used for vacuum hot test - Google Patents
Spacecraft sealed cabin humidity control system and method used for vacuum hot test Download PDFInfo
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- CN104076834A CN104076834A CN201410322874.9A CN201410322874A CN104076834A CN 104076834 A CN104076834 A CN 104076834A CN 201410322874 A CN201410322874 A CN 201410322874A CN 104076834 A CN104076834 A CN 104076834A
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Abstract
The invention discloses a spacecraft sealed cabin humidity control system and method used for a vacuum hot test. The spacecraft sealed cabin humidity control system comprises a dehumidifying subsystem, a constant humidity injecting subsystem, a temperature, humidity and pressure measuring subsystem and a control subsystem. The dehumidifying subsystem is used for dehumidifying a spacecraft sealed cabin. The constant humidity injection subsystem is used for injecting gas constant in humidity into the spacecraft sealed cabin. The temperature, humidity and pressure measuring subsystem is used for measuring the actual humidity and pressure of the spacecraft sealed cabin. The control subsystem is used for controlling the humidity of the gas which is injected into the spacecraft sealed cabin by the constant humidity injecting subsystem based on the actual humidity of the spacecraft sealed cabin and target humidity which is set by a shunt humidity generator in the constant humidity injecting subsystem. According to the spacecraft sealed cabin humidity control system and method used for the vacuum hot test, through regulating the humidity of the gas which is injected into the sealed cabin by the constant humidity injecting subsystem, it is ensured that pressure in the sealed cabin is within the required range, and the humidity in the cabin meets the requirements for working conditions of the vacuum hot test.
Description
Technical field
The present invention relates to a kind of space capsule environmental test technical field, be specifically related to a kind of vacuum thermal test space capsule moisture control system and control method.
Background technology
With the spacecraft of pressurized capsule section, while carrying out vacuum thermal test, due to the heat exchange state of wanting under virtual space state of flight, need to pressurized capsule internal pressure be regulated and be controlled.When completing the control of pressurized capsule internal pressure, after finding that cabin internal pressure arrives 200Pa left and right, almost be difficult to reduce again, to be mainly that in cabin, moisture is excessive cause for this, these moisture are because spacefarer enters the water vapour that cabin training process is brought on the one hand, that in these cabins, moisture has following characteristic due to the water vapour that in below deck equipment installation, debug process, operating personnel bring on the other hand:
A) the most of surface that is adsorbed on material and equipment by Van der Waals for of hydrone, there is similar part with the liquefaction of gas, the surface molecule structure variation being adsorbed is little, and the hydrone being therefore adsorbed and the chemical property of absorption surface all remain unchanged, and belong to physisorption;
B) air humidity in pressurized capsule is larger, and relative humidity may reach more than 90%.
For ensureing in pressurized capsule each electronic equipment of moisture sensitivity in normal duty, guarantee that heat test carries out every test of process and complete smoothly, before heat test, need pressurized capsule to dewater, in heat test process, need the water cut in pressurized capsule to control, the follow-up model vacuum thermal test that is about to carry out, overall thermal control has proposed concrete requirement to the control of humidity in gas test process in pressurized capsule especially first, be that pressurized capsule dewaters after end, require to be filled with the pure air of constant dew point.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of vacuum thermal test space capsule moisture control system and control method, completes smoothly with every test of guaranteeing space capsule vacuum thermal test process.
For solving the problems of the technologies described above, the invention provides a kind of vacuum thermal test space capsule moisture control system.This space capsule moisture control system comprises: dehumidifying subsystem, for space capsule is dehumidified; Constant humidity injects subsystem, for described space capsule being injected to the gas of constant humidity; Humiture and pressure survey subsystem, for measuring actual humidity and the actual pressure of described space capsule; And inject with dehumidifying subsystem, constant humidity the control subsystem that subsystem, humiture and pressure survey subsystem are connected respectively, it injects the target humidity of the described space capsule that subsystem arranges for the actual humidity based on described space capsule and described constant humidity, control described constant humidity and inject subsystem and inject the humidity of gas in described space capsule.
The present invention also provides one to utilize moisture control system to carry out vacuum thermal test space capsule humidity control method.This space capsule humidity control method comprises the following steps: step 1: space capsule is dehumidified; Step 2: the gas that described space capsule is injected to constant humidity; Step 3: the target humidity of the described space capsule arranging in the actual humidity based on described space capsule and described moisture control system, control the humidity of injecting gas in described space capsule.
Vacuum thermal test provided by the invention passes through dehumidifying subsystem by humidity in space capsule by space capsule moisture control system and control method, be that water partial pressure is reduced to 100Pa (now in cabin dewpoint temperature should lower than-20 DEG C), inject subsystem to the gas that injects constant humidity in pressurized capsule by constant humidity, humiture and pressure survey subsystem Real-Time Monitoring space capsule internal pressure, humidity situation of change, control subsystem according to space capsule internal pressure, humidity feedback, the gas humidity that constant humidity is injected in subsystem injection space capsule regulates and controls, when final guarantee space capsule internal pressure reaches claimed range, in cabin, humidity meets the requirement of vacuum thermal test operating mode.
Brief description of the drawings
Below, by the description in conjunction with its accompanying drawing to some embodiments of the present invention, can further understand object of the present invention, specific structural features and advantage, wherein the similar assembly of similar symbology.
Fig. 1 is space capsule moisture control system schematic diagram of the present invention.
Fig. 2 is the structural representation of humiture and pressure survey subsystem in space capsule moisture control system of the present invention.
Fig. 3 is the structural representation of subsystem of dehumidifying in space capsule moisture control system of the present invention.
Fig. 4 is the structural representation that in space capsule moisture control system of the present invention, constant humidity injects subsystem.
Fig. 5 is space capsule humidity control method process flow diagram of the present invention.
In figure, 1 for controlling subsystem, 2 is vacuum meter, 3.1 for wearing container electric connector, 3.2 is crossing cabin electric connector, 3.3 for wearing additional reservoir electric connector, 4.1 is pressure survey communication cable, 4.2 is temperature and humidity measurement communication cable, 5 is Temperature Humidity Sensor, 6 is space capsule, 7 is additional reservoir, 8 is vacuum gauge, 9.1 is space simulator interior conduit, 9.2 is the outer common conduit of space simulator, 9.3 is dehumidifying subsystem pipeline, 9.4 is constant humidity injection subsystem pipeline, 9.5 is connecting tube, 10 is constant humidity injection subsystem, 11.1 is dehumidifying subsystem valve, 11.2 is constant humidity injection subsystem valve, 12 is vacuum pump group, 13 is shunting humidity generator, 14 is dry gas generator, 20 is humiture and pressure survey subsystem, 30 is dehumidifying subsystem, 40 is supervisory control comuter, 50 is control station.
Embodiment
Below the specific embodiment of the present invention is elaborated: the specific embodiment of the present invention is implemented under taking technical solution of the present invention as prerequisite; provided detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
Figure 1 shows that space capsule moisture control system schematic diagram of the present invention.Vacuum thermal test of the present invention comprises that by space capsule moisture control system humiture and pressure survey subsystem 20 (as shown in Figure 2), dehumidifying subsystem 30 (as shown in Figure 3), constant humidity inject subsystem 10 (as shown in Figure 4) and control subsystem 1.Control subsystem 1 and mainly comprise supervisory control comuter 40, control station 50, communication cable etc., the various parameters that supervisory control comuter 40 notifies control station 50 Receiving & control ground station 50 to return via communication cable by serial communication user's various operations, control station 50 injects subsystem 10 and humiture and pressure survey subsystem 20 with dehumidifying subsystem 30, constant humidity respectively and is electrically connected.
The control station of controlling in subsystem 1 comprises PLC controller, serial server, expansion module and relay.PLC controller is received and is carried out the various instructions that supervisory control comuter sends by serial ports; And gather Temperature Humidity Sensor signal by the analog input module in expansion module, and the actual temperature of collection, humidity are carried out to conversion process, be uploaded to supervisory control comuter 40 simultaneously; Gather by serial server the pressure value that in humiture and pressure survey subsystem, vacuum meter 2 shows, be uploaded to supervisory control comuter 40 simultaneously; By digital output module, digital quantity input module and relay in expansion module dehumidify respectively the switch control of subsystem 30 intermediate pump groups 12, dehumidifying subsystem valve 11.1 and the switch control that constant humidity injects subsystem valve 11.2; By operation pid algorithm, the desired value that the real time data that humiture and pressure survey subsystem 20 are provided and constant humidity inject the space capsule that subsystem 10 shunting humidity generators 13 arrange (for example, the target humidity of space capsule) compare, regulate in real time the humidity of injecting gas in space capsule.In the time that the actual humidity of space capsule is less than the target humidity of space capsule, increase constant humidity and inject subsystem 10 and inject the humidity of gas in space capsule; In the time that the actual humidity of space capsule is greater than the target humidity of space capsule, reduce constant humidity and inject subsystem 10 and inject the humidity of gas in space capsule; In the time that the actual humidity of space capsule equals the target humidity of space capsule, the humidity that makes constant humidity injection subsystem 10 inject gas in space capsule remains unchanged; When the actual pressure of space capsule and actual humidity meet the requirement of vacuum thermal test, constant humidity injects subsystem 10 and stops injecting to space capsule the gas of constant humidity.
Figure 2 shows that the structural representation of humiture and pressure survey subsystem 20 in space capsule moisture control system of the present invention, wherein, this humiture and pressure survey subsystem 20 are for measuring actual temperature, actual humidity and the actual pressure of space capsule.Humiture and pressure survey subsystem 20 comprise vacuum meter 2, wear container electric connector 3.1, crossing cabin electric connector 3.2, wear additional reservoir electric connector 3.3, pressure survey communication cable 4.1, temperature and humidity measurement communication cable 4.2, vacuum gauge 8, Temperature Humidity Sensor 5, additional reservoir 7.Vacuum gauge 8, Temperature Humidity Sensor 5 are positioned at additional reservoir 7, and additional reservoir 7 is arranged in space capsule 6, and its inside remains the state of 1 atmospheric pressure and normal temperature.For the vacuum gauge 8 of actual pressure of measuring space capsule by pressure survey communication cable 4.1, wear additional reservoir electric connector 3.3, crossing cabin electric connector 3.2, wear container electric connector 3.1 and be connected with vacuum meter 2, vacuum meter 2 is connected with control subsystem 1 by communication cable; For measure the actual temperature of space capsule and the Temperature Humidity Sensor of humidity 5 by temperature and humidity measurement communication cable 4.2, wear additional reservoir electric connector 3.3, crossing cabin electric connector 3.2, wear container electric connector 3.1 and be connected with control subsystem 1.
Figure 3 shows that the structural representation of the subsystem 30 that dehumidifies in space capsule moisture control system of the present invention, wherein, dehumidifying subsystem 30 is for dehumidifying to space capsule.Dehumidifying subsystem 30 comprises vacuum pump group 12, dehumidifying subsystem valve 11.1, dehumidifying subsystem pipeline 9.3.Vacuum pump group 12 is connected with space capsule 6 by dehumidifying subsystem pipeline 9.3, the outer common conduit 9.2 of space simulator, space simulator interior conduit 9.1, on dehumidifying subsystem pipeline 9.3, be provided with dehumidifying subsystem valve 11.1, to control, space capsule dehumidified.Space simulator interior conduit 9.1 is wound around wrapped multiple insulating assembly behind heating tape, and when the number of plies of this insulating assembly is 10 layers, effect of heat insulation is very good.
Figure 4 shows that the structural representation of constant humidity injection subsystem 10 in space capsule moisture control system of the present invention, wherein, constant humidity injects subsystem 10 for space capsule being injected to the gas of constant humidity.This constant humidity injects subsystem 10 and comprises that dry gas generator 14, shunting humidity generator 13, connecting tube 9.5, constant humidity inject subsystem pipeline 9.4, constant humidity injects subsystem valve 11.2.Shunting humidity generator 13 injects common conduit 9.2, space simulator interior conduit 9.1 outside subsystem pipeline 9.4, space simulator by constant humidity and is connected with space capsule 6, inject on subsystem pipeline 9.4 and be provided with constant humidity injection subsystem valve 11.2 at constant humidity, to control the output of constant humidity injection subsystem constant humidity gas.Dry gas generator 14 is connected with shunting humidity generator 13 by connecting tube 9.5.
Figure 5 shows that vacuum thermal test of the present invention space capsule humidity control method process flow diagram.It will be understood by those skilled in the art that, although disclose concrete step in Fig. 5, but these steps are only used for explanation as example, that is to say, the vacuum thermal test of the embodiment of the present invention with space capsule humidity control method can also carry out multiple other step or execution graph 5 in the shift step of step.Particularly, the embodiment of the present invention comprises the steps:
In step 101, space capsule is dehumidified; Particularly,
The first step, opens dehumidifying subsystem valve 11.1, confirms that constant humidity injects subsystem valve 11.2 in closed condition simultaneously;
Second step, starts vacuum pump group 12, adopts the mode of step-down to dehumidify to space capsule;
The 3rd step, the humidity of measuring in space capsule changes, and when the actual humidity of space capsule, when water partial pressure is better than 100Pa, stops dehumidifying.
In step 102, space capsule is injected to the gas of constant humidity; Particularly,
The first step, opens constant humidity and injects subsystem valve 11.2, confirms that dehumidifying subsystem valve 11.1 is in closed condition simultaneously;
Second step, the shunting humidity generator 13 that injects subsystem 10 at the constant humidity of moisture control system arranges the target humidity of space capsule, starts constant humidity and injects subsystem 10, to the gas of inputting constant humidity in space capsule.
In step 103, the humidity of gas in space capsule is injected in the space capsule target humidity control arranging in the actual humidity based on space capsule and shunting humidity generator 13, thereby regulates the humidity in space capsule; Particularly,
The first step, measures actual humidity and the actual pressure of space capsule in real time;
Second step, compares the space capsule target humidity arranging in the actual humidity of space capsule and shunting humidity generator 13, injects the humidity of gas in space capsule to regulate in real time constant humidity to inject subsystem 10.
In the time that the actual humidity of space capsule is less than the target humidity of space capsule, increase constant humidity and inject subsystem 10 and inject the humidity of gas in space capsule; In the time that the actual humidity of space capsule is greater than the target humidity of space capsule, reduce constant humidity and inject subsystem 10 and inject the humidity of gas in space capsule; In the time that the actual humidity of space capsule equals the target humidity of space capsule, the humidity that makes constant humidity injection subsystem 10 inject gas in space capsule remains unchanged; When the actual pressure of space capsule and actual humidity meet the requirement of vacuum thermal test, close constant humidity and inject subsystem valve 11.2, to stop injecting to space capsule the gas of constant humidity.
Although above the embodiment of this patent has been given to describe in detail and explanation; but what should indicate is; we can carry out various equivalences to above-mentioned embodiment according to the conception of patent of the present invention and change and amendment; when its function producing does not exceed spiritual that instructions and accompanying drawing contain yet, all should be within the protection domain of this patent.
Claims (11)
1. a vacuum thermal test space capsule moisture control system, is characterized in that, described space capsule moisture control system comprises:
Dehumidifying subsystem, for dehumidifying to space capsule;
Constant humidity injects subsystem, for described space capsule being injected to the gas of constant humidity;
Humiture and pressure survey subsystem, for measuring actual humidity and the actual pressure of described space capsule;
Control subsystem, injecting subsystem and described humiture and pressure survey subsystem with described dehumidifying subsystem, described constant humidity is respectively connected, described control subsystem is injected the target humidity of the described space capsule that subsystem arranges for actual humidity based on described space capsule and described constant humidity, control described constant humidity and inject subsystem and inject the humidity of gas in described space capsule.
2. vacuum thermal test as claimed in claim 1 space capsule moisture control system, it is characterized in that, described dehumidifying subsystem is injected subsystem with described constant humidity and is connected with described space capsule with space simulator interior conduit by the outer common conduit of space simulator, wherein, described space simulator interior conduit is wound around wrapped multiple insulating assembly behind heating tape.
3. vacuum thermal test as claimed in claim 2 space capsule moisture control system, it is characterized in that, described dehumidifying subsystem comprises vacuum pump group, dehumidifying subsystem valve, dehumidifying subsystem pipeline, wherein, vacuum pump group is connected with described space capsule with described space simulator interior conduit by described dehumidifying subsystem pipeline, the outer common conduit of described space simulator, described dehumidifying subsystem valve is set on described dehumidifying subsystem pipeline, to control, space capsule is dehumidified.
4. vacuum thermal test as claimed in claim 2 space capsule moisture control system, it is characterized in that, described constant humidity injects subsystem and comprises dry gas generator, shunting humidity generator, connecting tube, constant humidity injects subsystem valve and constant humidity injects subsystem pipeline, wherein, described shunting humidity generator is connected with described dry gas generator by described connecting tube, described shunting humidity generator also injects subsystem pipeline by described constant humidity, the outer common conduit of described space simulator is connected with described space capsule with described space simulator interior conduit, on described constant humidity injection subsystem pipeline, be provided with constant humidity and inject subsystem valve, inject the output of subsystem constant humidity gas to control constant humidity.
5. vacuum thermal test as claimed in claim 1 space capsule moisture control system, is characterized in that, described humiture and pressure survey subsystem comprise:
Vacuum gauge, for measuring the actual pressure of described space capsule;
Temperature Humidity Sensor, for measuring actual humidity and the temperature of described space capsule;
Wherein, described vacuum gauge and described Temperature Humidity Sensor are positioned at additional reservoir, and described additional reservoir is arranged in described space capsule, and its inside remains the state of 1 atmospheric pressure and normal temperature;
Described vacuum gauge by pressure survey communication cable, wear additional reservoir electric connector, crossing cabin electric connector, wear container electric connector and be connected with vacuum meter, described vacuum meter is connected with described control subsystem by communication cable;
Described Temperature Humidity Sensor by temperature and humidity measurement communication cable, wear additional reservoir electric connector, crossing cabin electric connector, wear container electric connector with control subsystem be connected.
6. vacuum thermal test as claimed in claim 1 space capsule moisture control system, it is characterized in that, described control subsystem mainly comprises supervising device, control station, communication cable, described supervising device is notified described control station via described communication cable by serial communication by user's various operations and is received the various parameters that described control station returns, and described control station injects subsystem and described humiture and pressure survey subsystem with described dehumidifying subsystem, described constant humidity respectively and is electrically connected.
7. vacuum thermal test as claimed in claim 6 space capsule moisture control system, it is characterized in that, described control station comprises PLC controller, serial server, expansion module and relay, wherein, PLC controller, carries out for receiving by serial ports the various instructions that described supervising device sends; And gather Temperature Humidity Sensor signal by the analog input module in described expansion module, and the actual temperature of collection, humidity are carried out to conversion process, be uploaded to described supervising device simultaneously; Gather by described serial server the pressure value that in described humiture and pressure survey subsystem, vacuum meter shows, be uploaded to described supervising device simultaneously; By the digital output module in expansion module, digital quantity input module and described relay dehumidify respectively the switch control of subsystem intermediate pump group, dehumidifying subsystem valve and the switch control that constant humidity injects subsystem valve; By operation pid algorithm, the target humidity that the actual humidity of the described space capsule that described humiture and pressure survey subsystem are provided and described constant humidity inject the described space capsule of subsystem shunting humidity generator setting compares, to regulate in real time the humidity of injecting gas in described space capsule.
8. vacuum thermal test as claimed in claim 7 space capsule moisture control system, it is characterized in that, in the time that the actual humidity of described space capsule is less than the target humidity of described space capsule, increase the humidity of gas in described constant humidity injection subsystem injection space capsule;
In the time that the actual humidity of described space capsule is greater than the target humidity of described space capsule, reduce the humidity of gas in described constant humidity injection subsystem injection space capsule;
In the time that the actual humidity of described space capsule equals the target humidity of described space capsule, the humidity that makes described constant humidity inject gas in subsystem injection space capsule remains unchanged;
When the actual pressure of described space capsule and actual humidity meet the requirement of vacuum thermal test, described constant humidity injects subsystem and stops injecting to described space capsule the gas of constant humidity.
9. utilize moisture control system to carry out a vacuum thermal test space capsule humidity control method, it is characterized in that, described space capsule humidity control method comprises the following steps:
Step 1: space capsule is dehumidified;
Step 2: the gas that described space capsule is injected to constant humidity;
Step 3: the target humidity of the described space capsule arranging in the actual humidity based on described space capsule and described moisture control system, control the humidity of injecting gas in described space capsule.
10. space capsule humidity control method as claimed in claim 9, is characterized in that,
Step 1 comprises the following steps:
A. open dehumidifying subsystem valve, confirm that constant humidity injects subsystem valve in closed condition simultaneously;
B. start vacuum pump group, adopt the mode of step-down to dehumidify to pressurized capsule;
C, the humidity of measuring in described space capsule changes, and when the actual humidity of described space capsule, when water partial pressure is reduced to 100Pa in pressurized capsule, stops dehumidifying;
Step 2 comprises the following steps:
A. open described constant humidity and inject subsystem valve, confirm that described dehumidifying subsystem valve is in closed condition simultaneously;
B., the target humidity of described space capsule is set in described moisture control system, starts constant humidity and inject subsystem, to the gas of inputting constant humidity in described space capsule;
Step 3 comprises the following steps:
A. measure in real time actual humidity and the actual pressure of described space capsule;
B. the target humidity of the described space capsule arranging in the actual humidity of described space capsule and described moisture control system is compared, to regulate in real time the humidity of injecting gas in described space capsule.
11. space capsule humidity control methods as claimed in claim 10, it is characterized in that, in the time that the actual humidity of described space capsule is less than the target humidity of described space capsule, increase the humidity of gas in described constant humidity injection subsystem injection space capsule;
In the time that the actual humidity of described space capsule is greater than the target humidity of described space capsule, reduce the humidity of gas in described constant humidity injection subsystem injection space capsule;
In the time that the actual humidity of described space capsule equals the target humidity of described space capsule, the humidity that makes described constant humidity inject gas in subsystem injection space capsule remains unchanged;
When the actual pressure of described space capsule and actual humidity meet the requirement of vacuum thermal test, stop injecting to described space capsule the gas of constant humidity.
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| CN201410322874.9A CN104076834A (en) | 2014-03-18 | 2014-07-08 | Spacecraft sealed cabin humidity control system and method used for vacuum hot test |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20141001 |