CN107869813A - A kind of nacelle anti-condensation method of spacecraft transfer - Google Patents
A kind of nacelle anti-condensation method of spacecraft transfer Download PDFInfo
- Publication number
- CN107869813A CN107869813A CN201711030263.7A CN201711030263A CN107869813A CN 107869813 A CN107869813 A CN 107869813A CN 201711030263 A CN201711030263 A CN 201711030263A CN 107869813 A CN107869813 A CN 107869813A
- Authority
- CN
- China
- Prior art keywords
- spacecraft
- nacelle
- temperature
- radome fairing
- dew
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F5/00—Air-conditioning systems or apparatus not covered by F24F1/00 or F24F3/00, e.g. using solar heat or combined with household units such as an oven or water heater
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F13/00—Details common to, or for air-conditioning, air-humidification, ventilation or use of air currents for screening
- F24F13/22—Means for preventing condensation or evacuating condensate
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F13/00—Details common to, or for air-conditioning, air-humidification, ventilation or use of air currents for screening
- F24F13/22—Means for preventing condensation or evacuating condensate
- F24F2013/221—Means for preventing condensation or evacuating condensate to avoid the formation of condensate, e.g. dew
Abstract
The present invention relates to a kind of nacelle anti-condensation method of spacecraft transfer, including：S1. transhipment day is selected, calculates the dew-point temperature of the nacelle of spacecraft；S2. the spacecraft placement space is heated up, the temperature of the placement space is higher than the dew-point temperature；S3. to parcel cage on the outside of the nacelle of the spacecraft；Or spacecraft described in S4. is located in radome fairing, and the inner space of the radome fairing is aerated.By carrying out heating control to the placement space of spacecraft, so that the nacelle temperature of space flight increases, it is higher than dew-point temperature so as to be advantageous to the temperature on the nacelle surface of spacecraft, so as to avoid condensation of the water vapor in air on nacelle surface, so as to solve the problems, such as that spacecraft cabin surface condenses in placement space.
Description
Technical field
The present invention relates to a kind of nacelle anti-condensation method of anti-condensation method, more particularly to a kind of spacecraft transfer.
Background technology
Wenchang, hainan launching site belongs to tropical marine climate, has the characteristics of high temperature, high humidity, high salt, long-term mean temperature
More than 20 DEG C, relative humidity is more than 80%, concentration of saline fog 0.0225mg/m3.If spacecraft is directly exposed in this environment,
Optical lens, cell piece, thermal control coating of the installation of spacecraft surface etc. can then be adversely affected.
In order to avoid launching site hot and humid environment is to the sensitive equipment such as accurate electromechanical equipment, optical device on spacecraft
Influence, the work such as the general assembly of spacecraft, test is carried out in clean room.According to launching site techniqueflow, spacecraft is not
With work such as factory building general assembly, test and docking, and spacecraft needs to be transported to launch site and launched.Due to each factory building it
Between, a certain distance between factory building and launch site be present, the relatively low spacecraft of surface temperature can be exposed to height in transport process
In warm high humidity environment, the risk of surface sweating be present, and then endanger the safety of spacecraft.
The content of the invention
It is an object of the invention to provide a kind of nacelle anti-condensation method of spacecraft, solves spacecraft transfer process middle deck
The problem of body condenses.
For achieving the above object, the present invention provides a kind of nacelle anti-condensation method of spacecraft transfer, including：
S1. transhipment day is selected, calculates the dew-point temperature of the nacelle of spacecraft；
S2. the spacecraft placement space is heated up, the temperature of the placement space is higher than the dew-point temperature；
S3. to parcel cage on the outside of the nacelle of the spacecraft；Or
S4. the spacecraft is located in radome fairing, and the inner space of the radome fairing is aerated.
According to an aspect of the present invention, it is described in the step of wrapping up cage to the outside of the nacelle of the spacecraft
Cage uses foam heat insulating material.
According to an aspect of the present invention, the spacecraft is located in radome fairing, and the inner space of the radome fairing is entered
In the step of row ventilation, the inner space of the radome fairing is aerated using caisson or air-conditioning device.
According to an aspect of the present invention, the inner space of the radome fairing is aerated using caisson, makes institute
The pressure of the inner space of radome fairing is stated higher than the pressure outside the radome fairing.
According to an aspect of the present invention, the inner space of the radome fairing is aerated using air-conditioning device, makes institute
The temperature of the inner space of radome fairing is stated at 15~25 DEG C, is less than or equal to the relative humidity of the inner space of the radome fairing
50%.
According to an aspect of the present invention, select transhipment day, the step of the dew-point temperature for the nacelle for calculating spacecraft in wrap
Include：
S11. the temperature and relative humidity of transhipment day is obtained；
S12. according to the temperature and the relative humidity calculation nacelle of spacecraft dew-point temperature.
According to an aspect of the present invention, the spacecraft placement space is heated up, makes the temperature of the placement space
In the step of degree is higher than the dew-point temperature, the time heated up to the spacecraft placement space at least shifts to an earlier date day than transhipment
Two days.
According to an aspect of the present invention, the spacecraft placement space is heated up, makes the temperature in the space high
In the step of dew-point temperature, the initial temperature of the placement space is less than 20 DEG C, initial RH 40%.
According to the scheme of the present invention, by carrying out heating control to the placement space of spacecraft, so that space flight
Nacelle temperature increases, and is higher than dew-point temperature so as to be advantageous to the temperature on the nacelle surface of spacecraft, so as to avoid air
Condensation of the middle vapor on nacelle surface, so as to which efficiently solve that spacecraft cabin surface condenses in placement space asks
Topic.
According to the scheme of the present invention, spacecraft is wrapped up wherein by using cage, so as to be risen to spacecraft
Protective effect is arrived.Meanwhile kept apart spacecraft and external environment by the effect of cage, avoid in external environment
Vapor contacts with the nacelle of spacecraft, further avoid condensation of the vapor in the nacelle of spacecraft, reduces space flight
The possibility that device condenses in transport process middle deck external surface.
According to the scheme of the present invention, divulged information, made to the radome fairing inner space where spacecraft by caisson
The pressure inside radome fairing where spacecraft is more than the pressure of the external environment outside radome fairing, avoids in external environment and contains
The air of a large amount of vapor enters inside radome fairing, is tied so as to avoid the vapor in external environment on spacecraft cabin surface
The phenomenon of dew.
According to the scheme of the present invention, the mistake divulged information by air-conditioning device to the radome fairing inner space where spacecraft
Cheng Zhong, the temperature for making the radome fairing inner space where spacecraft are 15~25 DEG C, and relative humidity is less than or equal to 50%.Radome fairing
Temperature Humidity Sensor is set, in real time humiture environment in measurement cover, so as to control the ventilation of air-conditioning to supply state.Filled by air-conditioning
The temperature and humidity state on active control spacecraft cabin surface is put, further avoid the dew condensation phenomenon on spacecraft surface.
Brief description of the drawings
Fig. 1 schematically shows the step block diagram of the nacelle anti-condensation method according to the present invention.
Embodiment
, below will be to embodiment in order to illustrate more clearly of embodiment of the present invention or technical scheme of the prior art
In the required accompanying drawing used be briefly described.It should be evident that drawings in the following description are only some of the present invention
Embodiment, for those of ordinary skills, on the premise of not paying creative work, can also be according to these
Accompanying drawing obtains other accompanying drawings.
When being described for embodiments of the present invention, term " longitudinal direction ", " transverse direction ", " on ", " under ", " preceding ",
" rear ", "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", the orientation expressed by " outer " or position relationship are to be based on phase
Orientation shown in the drawings or position relationship are closed, it is for only for ease of the description present invention and simplifies description, rather than instruction or dark
Show that the device of meaning or element there must be specific orientation, with specific azimuth configuration and operation, therefore above-mentioned term can not
It is interpreted as limitation of the present invention.
The present invention is described in detail with reference to the accompanying drawings and detailed description, embodiment can not go to live in the household of one's in-laws on getting married one by one herein
State, but therefore embodiments of the present invention are not defined in implementation below.
As shown in figure 1, according to a kind of nacelle anti-condensation method of spacecraft transfer of the present invention, including：
S1. transhipment day is selected, calculates the dew-point temperature of the nacelle of spacecraft；
S2. spacecraft placement space is heated up, the temperature of placement space is higher than dew-point temperature；
S3. to parcel cage on the outside of the nacelle of spacecraft；Or
S4. the spacecraft is located in radome fairing, and the inner space of the radome fairing is aerated.
According to one embodiment of the present invention, select and transport day, in the dew-point temperature step for the nacelle for calculating spacecraft
Including：
S11. the temperature and relative humidity of transhipment day is obtained.In the present embodiment, choose transhipment in the future, obtain transhipment day
Data of weather forecast.The temperature and relative humidity data of transhipment day is obtained according to data of weather forecast.
S12. the dew-point temperature of the nacelle of spacecraft is calculated according to the temperature data of acquisition and relative humidity data.
According to one embodiment of the present invention, because the humiture of external environment is than warm and humid in spacecraft assembling workshop
Degree is high, and spacecraft placement space is heated up before transhipment.In the present embodiment, spacecraft is positioned in assembling workshop,
According to the dew-point temperature of calculating, to carrying out heating control in assembling workshop.Needed at least when being heated up in assembling delivery room
Shift to an earlier date two day than transhipment to carry out, ensure that during being heated up in assembling delivery room, it is too fast to avoid temperature change
Influence to parts in spacecraft, the safety and reliability of spacecraft is ensure that, further ensure the use of spacecraft
Life-span.In the present embodiment, the initial temperature of the placement space of spacecraft is less than 20 DEG C, initial RH 40%.
In above-mentioned placement space, the condensation of the nacelle dry tack free anhydrous steam of spacecraft.When being transported through to spacecraft, spacecraft
Contacted with external environment, to avoid vapor from being condensed on nacelle surface, therefore heating control is carried out to the placement space of spacecraft
Temperature after system is greater than the dew-point temperature on the nacelle surface of spacecraft.By carrying out heating control to the placement space of spacecraft
System, so that the nacelle temperature of space flight increases, is higher than dew-point temperature so as to be advantageous to the temperature on the nacelle surface of spacecraft,
So as to avoid condensation of the water vapor in air on nacelle surface, sky is being placed so as to efficiently solve spacecraft cabin surface
Between middle condensation the problem of.
According to one embodiment of the present invention, during transporting spacecraft, to parcel on the outside of the nacelle of spacecraft every
From cover.In the present embodiment, cage uses foam heat insulating material.Spacecraft is wrapped up wherein by using cage,
So as to serve protective effect to spacecraft.Meanwhile kept apart spacecraft and external environment by the effect of cage, avoid
Vapor in external environment contacts with the nacelle of spacecraft, and it is solidifying in the nacelle of spacecraft to further avoid vapor
Knot, reduces the possibility that spacecraft condenses in transport process middle deck external surface.
According to another embodiment of the invention, spacecraft is assembled into radome fairing, during spacecraft is transported,
Radome fairing inner space where spacecraft is aerated.In the present embodiment, using caisson or air-conditioning device
Divulged information to the radome fairing inner space where spacecraft.In the present embodiment, phase is chosen according to the distance to spacecraft transfer
The draft type answered.If the transhipment of spacecraft chooses caisson pair apart from short (for example, being transported between adjacent composing room)
The inner space of radome fairing is aerated.If the transhipment distance (for example, being transported between composing room and launching site) of spacecraft,
Air-conditioning device is then chosen to be aerated the inner space of radome fairing.Flexibly chosen by transporting distance to radome fairing inner space
The mode of ventilation, make the transport process of spacecraft flexible, and can flexibly choose transhipment route, save transhipment time
With improve transport efficacy.
In the present embodiment, transhipment distance is near, and the inner space of radome fairing is aerated using caisson.Right
During spacecraft is transported through, caisson is installed on transit vehicle.Caisson is by the bottom of spacecraft to whole
Divulged information in stream cover.When being ventilated by caisson into radome fairing, the pressure in radome fairing is set to be more than the external world outside radome fairing
The pressure of environment.By above-mentioned setting, it ensure that the gas of the inner space of radome fairing is provided by caisson, avoid the external world
The air containing a large amount of vapor enters inside radome fairing in environment, so as to avoid the vapor in external environment in spacecraft
Nacelle surface sweating phenomenon.In the present embodiment, divulged information using caisson to the nacelle inner space of spacecraft, storage
What is stored in device of air mixes gas for dry nitrogen or sky.
In the present embodiment, transhipment distance is remote, and the inner space of radome fairing is aerated using air-conditioning device.At this
In embodiment, during being transported after spacecraft is combined with carrier, air-conditioning device is used on transferring platform to spacecraft
The radome fairing inner space at place is aerated.The mistake divulged information by air-conditioning device to the radome fairing inner space where spacecraft
Cheng Zhong, it is 15~25 DEG C to make the temperature in radome fairing, and relative humidity is less than or equal to 50%.Temperature and humidity sensing is set in radome fairing
Device, the temperature and humidity of environment in cover is measured in real time, so as to control the ventilation of air-conditioning to supply state, it is ensured that humiture meets will
Ask, so as to avoid phenomenon of the vapor in external environment in the nacelle surface sweating of spacecraft.
The above is only enumerating for the concrete scheme of the present invention, should for the equipment and structure of wherein not detailed description
When being interpreted as taking the existing common apparatus in this area and universal method to be practiced.
The scheme of the present invention is the foregoing is only, is not intended to limit the invention, for the technology of this area
For personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (8)
1. a kind of nacelle anti-condensation method of spacecraft transfer, including：
S1. transhipment day is selected, calculates the dew-point temperature of the nacelle of spacecraft；
S2. the spacecraft placement space is heated up, the temperature of the placement space is higher than the dew-point temperature；
S3. to parcel cage on the outside of the nacelle of the spacecraft；Or
S4. the spacecraft is located in radome fairing, and the inner space of the radome fairing is aerated.
2. nacelle anti-condensation method according to claim 1, it is characterised in that wrapped to the outside of the nacelle of the spacecraft
In the step of wrapping up in cage, the cage uses foam heat insulating material.
3. nacelle anti-condensation method according to claim 1, it is characterised in that the spacecraft is located in radome fairing, right
In the step of inner space of the radome fairing is aerated, using caisson or air-conditioning device in the radome fairing
Portion space is aerated.
4. nacelle anti-condensation method according to claim 2, it is characterised in that using caisson to the radome fairing
Inner space is aerated, and makes the pressure of inner space of the radome fairing higher than the pressure outside the radome fairing.
5. nacelle anti-condensation method according to claim 2, it is characterised in that using air-conditioning device to the radome fairing
Inner space is aerated, and makes the temperature of inner space of the radome fairing at 15~25 DEG C, makes the inside of the radome fairing empty
Between relative humidity be less than or equal to 50%.
6. nacelle anti-condensation method according to claim 3, it is characterised in that selected transhipment day, calculate the cabin of spacecraft
The step of dew-point temperature of body, includes：
S11. the temperature and relative humidity of transhipment day is obtained；
S12. according to the temperature and the relative humidity calculation nacelle of spacecraft dew-point temperature.
7. nacelle anti-condensation method according to claim 1, it is characterised in that risen to the spacecraft placement space
Temperature, in the step of making the temperature of the placement space be higher than the dew-point temperature, the spacecraft placement space is heated up
Time than transhipment day at least shift to an earlier date two days.
8. nacelle anti-condensation method according to claim 1, it is characterised in that risen to the spacecraft placement space
Temperature, in the step of making the temperature in the space be higher than the dew-point temperature, the initial temperature of the placement space is less than 20 DEG C, just
Beginning relative humidity is 40%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711030263.7A CN107869813A (en) | 2017-10-27 | 2017-10-27 | A kind of nacelle anti-condensation method of spacecraft transfer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201711030263.7A CN107869813A (en) | 2017-10-27 | 2017-10-27 | A kind of nacelle anti-condensation method of spacecraft transfer |
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| CN107869813A true CN107869813A (en) | 2018-04-03 |
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| CN201711030263.7A Pending CN107869813A (en) | 2017-10-27 | 2017-10-27 | A kind of nacelle anti-condensation method of spacecraft transfer |
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Citations (6)
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|---|---|---|---|---|
| RU2183799C2 (en) * | 2000-08-28 | 2002-06-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева" | Method of removal of condensate from moisture receiver of heat exchanger-condenser with hydrophilic material and device for realization of this method |
| CN101196333A (en) * | 2007-12-13 | 2008-06-11 | 中冶南方工程技术有限公司 | Anti-dew ventilation method and facilities for main factory building of cold rolling factory |
| JP2009190539A (en) * | 2008-02-14 | 2009-08-27 | Japan Aerospace Exploration Agency | Thermal control system |
| CN101663196A (en) * | 2007-02-23 | 2010-03-03 | 空中客车运营有限公司 | Fuselage of an aircraft or spacecraft and corresponding aircraft or spacecraft |
| CN104270830A (en) * | 2014-09-28 | 2015-01-07 | 任红 | Workshop following type environmental parameter monitoring system based on wireless sensor networks |
| CN106016513A (en) * | 2016-04-29 | 2016-10-12 | 中国水利水电建设工程咨询中南有限公司 | Damp-proof anti-condensation method for hydropower plant |
-
2017
- 2017-10-27 CN CN201711030263.7A patent/CN107869813A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2183799C2 (en) * | 2000-08-28 | 2002-06-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева" | Method of removal of condensate from moisture receiver of heat exchanger-condenser with hydrophilic material and device for realization of this method |
| CN101663196A (en) * | 2007-02-23 | 2010-03-03 | 空中客车运营有限公司 | Fuselage of an aircraft or spacecraft and corresponding aircraft or spacecraft |
| CN101196333A (en) * | 2007-12-13 | 2008-06-11 | 中冶南方工程技术有限公司 | Anti-dew ventilation method and facilities for main factory building of cold rolling factory |
| JP2009190539A (en) * | 2008-02-14 | 2009-08-27 | Japan Aerospace Exploration Agency | Thermal control system |
| CN104270830A (en) * | 2014-09-28 | 2015-01-07 | 任红 | Workshop following type environmental parameter monitoring system based on wireless sensor networks |
| CN106016513A (en) * | 2016-04-29 | 2016-10-12 | 中国水利水电建设工程咨询中南有限公司 | Damp-proof anti-condensation method for hydropower plant |
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Application publication date: 20180403 |