CN104071327B - The parallel temperature controlling system of stratospheric airship and control method - Google Patents
The parallel temperature controlling system of stratospheric airship and control method Download PDFInfo
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- CN104071327B CN104071327B CN201410247741.XA CN201410247741A CN104071327B CN 104071327 B CN104071327 B CN 104071327B CN 201410247741 A CN201410247741 A CN 201410247741A CN 104071327 B CN104071327 B CN 104071327B
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- temperature
- cabin
- pipeline
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Abstract
The invention discloses the parallel temperature controlling system of a kind of stratospheric airship and control method, described control system comprises the first temperature control subsystem in parallel and the second temperature control subsystem; First temperature control subsystem comprises high pressure gas holder, be installed in dirigible cabin and with relevant device and connect or close cold drawing, be installed on the heat exchanger in dirigible cabin, near the first fan of heat exchanger, be communicated with high pressure gas holder and cold drawing and gas drawn first pipeline in cabin, and connection high pressure gas holder and heat exchanger gas is drawn second pipeline in cabin; Second temperature control subsystem comprises blower fan, is communicated with blower fan and cold drawing and gas is drawn the 3rd pipeline in cabin, being arranged at the exhaust apparatus in cabin above relevant device, and the 4th pipeline of connection exhaust apparatus and blower fan.Consumption of current of the present invention is less, quality is light, relatively low to the sealing requirements of pipeline; Can prevent dirigible single low-temperature receiver when very hot weather low latitude from can not meet the adverse effect of refrigeration demand.
Description
Technical field
The present invention relates to stratospheric airship environmental control system and method, be particularly useful for the parallel control system and the method that control temperature in cabin.
Background technology
Compared with other aerospace vehicles, stratospheric airship has unique advantage in fields such as communication, supervision, defence, and in military and civilian, development is comparatively quick.
A key issue of stratospheric airship design is exactly the thermal control problem of engine room facilities:
First, the operating altitude of stratospheric airship is generally 20km, and its ambient temperature is minimum reaches-56.5 DEG C, and if do not taked adequate measures, the equipment in cabin comprises electronic machine, communication apparatus etc. and all cannot work.
Secondly, face subaerial ambient temperature if run in dirigible lift-off process or decline process higher, when ambient temperature is greater than the permissive temperature of equipment, also can affect the in-use performance of equipment.
Therefore need a kind of new system of design to solve the problems referred to above.
Summary of the invention
Goal of the invention: provide that a kind of structure is simple, power consumption is little, the good cabin atmosphere control system of controllability and method, for the overall thermal control of stratospheric airship provides Technical Reference.
Technical scheme: the parallel temperature controlling system of a kind of stratospheric airship, comprises the first temperature control subsystem in parallel and the second temperature control subsystem;
Described first temperature control subsystem comprises high pressure gas holder, be installed in dirigible cabin and with relevant device and connect or close cold drawing, be installed on the heat exchanger in dirigible cabin, near the first fan of heat exchanger, be communicated with described high pressure gas holder and cold drawing and gas drawn first pipeline in cabin, and be communicated with described high pressure gas holder and heat exchanger and gas drawn second pipeline in cabin;
Described second temperature control subsystem comprises blower fan, is communicated with blower fan and cold drawing and gas is drawn the 3rd pipeline in cabin, being arranged at the exhaust apparatus in cabin above relevant device, and the 4th pipeline of connection exhaust apparatus and blower fan.
Described first pipeline, the second pipeline, the 3rd pipeline and the 4th pipeline are provided with valve.Described cold drawing comprises the cover plate of formation one hollow accommodation space and connects with cover plate inwall and form the coil pipe of fold-line-shaped air flue, and coil pipe has the admission port and air extractor duct that stretch out cover plate outside.The present invention also comprises the electrical heating wire being arranged on nacelle interior wall.
In a further embodiment, the present invention also comprises temperature acquisition disposal system, described temperature acquisition disposal system comprises the first temperature sensor be arranged on relevant device, the touch switch be electrically connected with electrical heating wire, the second temperature sensor being arranged at dirigible nacelle interior wall, be fixed on dirigible bulkhead and the data trap stretching out three-temperature sensor outside bulkhead, be connected with the second temperature sensor and three-temperature sensor, and the control housing connected with data trap, the first temperature sensor, touch switch and each valve.
Based on the control method of the parallel temperature controlling system of above-mentioned stratospheric airship, comprise the steps:
When dirigible is from the low latitude upward movement that ambient temperature is higher, the first temperature control subsystem is opened, and the cold air in high pressure gas holder is delivered to cold drawing, and cooling connects with it or close equipment; Meanwhile, cold air is delivered to heat exchanger, and the air near heat exchanger is blown other parts to cabin by the first fan, forms airflow circulating;
When dirigible rises to certain altitude, during the high permissive temperature of temperature out of my cabin lower than below deck equipment, the second temperature control subsystem is opened, and is transported to by the cold air outside cabin in cabin and in cold drawing;
When dirigible is after advection layer runs a period of time, when temperature drops to the permissive temperature of equipment, stop the first temperature control subsystem and the second temperature control subsystem;
When the minimum permissive temperature of the temperature in dirigible lower than below deck equipment, open electrical heating wire heating, open the second fan simultaneously, in cabin, form airflow circulating;
When dirigible declines, first open the second temperature control subsystem and cool, when it can not meet the demands, open the first temperature control subsystem.
Beneficial effect: the advantage that the present invention has that consumption of current is less, quality is light, relatively low to the sealing requirements of pipeline; Can prevent dirigible single low-temperature receiver when very hot weather low latitude from can not meet the adverse effect of refrigeration demand; System of the present invention has compact conformation in addition, quality is light, low price, controllability are good, safety advantages of higher.
Accompanying drawing explanation
Fig. 1 is the structural representation of one embodiment of the present invention.
Fig. 2 is the structural representation of cold drawing of the present invention.
Fig. 3 is the structural representation of another preferred embodiment of the present invention.
Detailed description of the invention
As depicted in figs. 1 and 2, the parallel temperature controlling system of stratospheric airship of the present invention mainly comprises the first temperature control subsystem in parallel and the second temperature control subsystem, and dirigible cabin sidewall is made up of warming plate 1.
First temperature control subsystem and the second temperature control subsystem all have two-way delivery pipe, and wherein a road is used for the cooling of heat-producing device, and another road is used for the entirety cooling in cabin.
Particularly, the first temperature control subsystem comprises high pressure gas holder 11, cold drawing 12, heat exchanger 13, the first fan 14, and the first pipeline 17, second pipeline 18, first valve 15 and the second valve 16 etc.
Cold drawing 12 is installed on and connects in dirigible cabin and with relevant device or close, for carrying out interchange of heat with it, to reduce the temperature of equipment; Heat exchanger 13 is installed in dirigible cabin, for carrying out interchange of heat with the air in cabin, to reduce the temperature in cabin; First fan 14 is near heat exchanger, local for being blown by the air of surroundings to other in cabin, forms circulating air, strengthens heat transfer effect; First pipeline 17 is for being communicated with high pressure gas holder and cold drawing and gas being drawn cabin, to form the first circulating path for cooling below deck equipment; Second pipeline 18 is for being communicated with high pressure gas holder and heat exchanger and gas being drawn cabin, for cooling temperature in cabin.
And the second temperature control subsystem comprises blower fan 21, be communicated with blower fan and cold drawing and gas drawn the 3rd pipeline 23 in cabin, being arranged at the exhaust apparatus 22 in cabin above relevant device, and the 4th pipeline 24 of connection exhaust apparatus and blower fan.First pipeline, the second pipeline, the 3rd pipeline and the 4th pipeline are provided with valve.
In a further embodiment, cold drawing comprises the cover plate 121 of formation one hollow accommodation space and connects with cover plate inwall and form the coil pipe 124 of fold-line-shaped air flue, and coil pipe has the admission port 123 and air extractor duct 122 that stretch out cover plate outside.Be arranged on the electrical heating wire of nacelle interior wall.
In a further embodiment, control process is undertaken by temperature acquisition disposal system, described temperature acquisition disposal system comprises the first temperature sensor 41 be arranged on relevant device, the touch switch 46 be electrically connected with electrical heating wire, be arranged at the second temperature sensor 42 of dirigible nacelle interior wall, be fixed on dirigible bulkhead and stretch out the three-temperature sensor 43 outside bulkhead, the data trap 44 be connected with the second temperature sensor 42 and three-temperature sensor 43, and and data trap, first temperature sensor 41, the control housing 45 that touch switch and each valve connect.
Wherein, the first temperature sensor is used for detecting the temperature of electronic machine, and the second temperature sensor is used for detecting the ambient temperature in dirigible equipment compartment, and three-temperature sensor is used for detecting the ambient temperature of dirigible outside, and touch switch is used for switch electrical heating wire.
Control method based on the parallel temperature controlling system of above-mentioned stratospheric airship mainly comprises the steps:
When dirigible is from the low latitude upward movement that ambient temperature is higher, the first temperature control subsystem is opened, and the cold air in high pressure gas holder is delivered to cold drawing, and cooling connects with it or close equipment; Meanwhile, cold air is delivered to heat exchanger, and the air near heat exchanger is blown other parts to cabin by the first fan, forms airflow circulating;
When dirigible rises to certain altitude, during the high permissive temperature of temperature out of my cabin lower than below deck equipment, the second temperature control subsystem is opened, and is transported to by the cold air outside cabin in cabin and in cold drawing;
When dirigible is after advection layer runs a period of time, when temperature drops to the permissive temperature of equipment, stop the first temperature control subsystem and the second temperature control subsystem;
When the minimum permissive temperature of the temperature in dirigible lower than below deck equipment, open electrical heating wire heating, open the second fan simultaneously, in cabin, form airflow circulating;
When dirigible declines, first open the second temperature control subsystem and cool, when it can not meet the demands, open the first temperature control subsystem.
In the above-described embodiments, the first temperature control subsystem and the demand of the second temperature control subsystem to power supply occur over just on fan and blower fan, and unlike vaporization cycle, there is the additional demand of compressor to electric power, therefore its consumption of current is relatively less.The parts simultaneously needed than fluid circuit cooling system are few, and cooling media involved in this system does not have corrosive property, relatively low to the seal request of pipeline, therefore its reliability and safety higher.
More than describe the preferred embodiment of the present invention in detail; but the present invention is not limited to the detail in above-mentioned embodiment, within the scope of technical conceive of the present invention; can carry out multiple equivalents to technical scheme of the present invention, these equivalents all belong to protection scope of the present invention.
It should be noted that in addition, each the concrete technical characteristic described in above-mentioned detailed description of the invention, in reconcilable situation, can be combined by any suitable mode.In order to avoid unnecessary repetition, the present invention illustrates no longer separately to various possible array mode.
Claims (6)
1. the parallel temperature controlling system of stratospheric airship, is characterized in that, comprises the first temperature control subsystem in parallel and the second temperature control subsystem;
Described first temperature control subsystem comprises high pressure gas holder (11), be installed in dirigible cabin and with relevant device and connect or close cold drawing (12), be installed on the heat exchanger (13) in dirigible cabin, near first fan (14) of heat exchanger, be communicated with described high pressure gas holder and cold drawing and gas drawn first pipeline (17) in cabin, and be communicated with described high pressure gas holder and heat exchanger and gas drawn second pipeline (18) in cabin;
Described second temperature control subsystem comprises blower fan (21), be communicated with blower fan and cold drawing and gas drawn the 3rd pipeline (23) in cabin, be arranged at the exhaust apparatus (22) in cabin above relevant device, and be communicated with the 4th pipeline (24) of exhaust apparatus and blower fan.
2. the parallel temperature controlling system of stratospheric airship as claimed in claim 1, is characterized in that, described first pipeline, the second pipeline, the 3rd pipeline and the 4th pipeline are provided with valve.
3. the parallel temperature controlling system of stratospheric airship as claimed in claim 1 or 2, it is characterized in that, described cold drawing comprises the cover plate (121) of formation one hollow accommodation space and connects with cover plate inwall and form the coil pipe (124) of fold-line-shaped air flue, and coil pipe has the admission port (123) and air extractor duct (122) that stretch out cover plate outside.
4. the parallel temperature controlling system of stratospheric airship as claimed in claim 1 or 2, is characterized in that, also comprise the electrical heating wire being arranged on nacelle interior wall.
5. the parallel temperature controlling system of stratospheric airship as claimed in claim 4, it is characterized in that, also comprise temperature acquisition disposal system, described temperature acquisition disposal system comprises the first temperature sensor (41) be arranged on relevant device, the touch switch (46) be electrically connected with electrical heating wire, be arranged at second temperature sensor (42) of dirigible nacelle interior wall, be fixed on dirigible bulkhead and stretch out the three-temperature sensor (43) outside bulkhead, the data trap (44) be connected with the second temperature sensor (42) and three-temperature sensor (43), and and data trap, first temperature sensor (41), the control housing (45) that touch switch and each valve connect.
6. based on a control method for the parallel temperature controlling system of stratospheric airship according to claim 4, it is characterized in that, comprise the steps:
When dirigible is from the low latitude upward movement that ambient temperature is higher, the first temperature control subsystem is opened, and the cold air in high pressure gas holder is delivered to cold drawing, and cooling connects with it or close equipment; Meanwhile, cold air is delivered to heat exchanger, and the air near heat exchanger is blown other parts to cabin by the first fan, forms airflow circulating;
When dirigible rises to certain altitude, during the high permissive temperature of temperature out of my cabin lower than below deck equipment, the second temperature control subsystem is opened, and is transported to by the cold air outside cabin in cabin and in cold drawing;
When dirigible is after advection layer runs a period of time, when temperature drops to the permissive temperature of equipment, stop the first temperature control subsystem and the second temperature control subsystem;
When the minimum permissive temperature of the temperature in dirigible lower than below deck equipment, open electrical heating wire heating, open the second fan simultaneously, in cabin, form airflow circulating;
When dirigible declines, first open the second temperature control subsystem and cool, when it can not meet the demands, open the first temperature control subsystem.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410247741.XA CN104071327B (en) | 2014-06-05 | 2014-06-05 | The parallel temperature controlling system of stratospheric airship and control method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410247741.XA CN104071327B (en) | 2014-06-05 | 2014-06-05 | The parallel temperature controlling system of stratospheric airship and control method |
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| CN104071327A CN104071327A (en) | 2014-10-01 |
| CN104071327B true CN104071327B (en) | 2016-03-30 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104608906B (en) * | 2014-12-05 | 2017-01-18 | 中国航空工业集团公司第六三一研究所 | Stratospheric airship task control subsystem |
| CN105485834B (en) * | 2015-11-30 | 2019-04-05 | 上海宇航系统工程研究所 | A kind of temperature control system of near space sealed compartment |
| CN106184693B (en) * | 2016-07-18 | 2018-03-06 | 江苏科技大学 | A kind of stratospheric airship balloonet air-charging and air-discharging system and method |
| CN110422311B (en) * | 2019-07-25 | 2024-03-19 | 南京航空航天大学 | Stratospheric airship equipment compartment temperature control system |
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| US7472865B2 (en) * | 2005-09-15 | 2009-01-06 | Lockheed Martin Corporation | Dehumidification system for an airship |
| CN101832619A (en) * | 2009-03-09 | 2010-09-15 | 北京航空航天大学 | Novel low-temperature and low-pressure wind speed environment control system |
| CN102179140A (en) * | 2011-01-27 | 2011-09-14 | 中国商用飞机有限责任公司 | Drying system used in airplane |
| CN203012558U (en) * | 2012-12-27 | 2013-06-19 | 西安飞豹科技发展公司 | Airplane nacelle sealed cabin environment control system |
| CN103486696A (en) * | 2013-09-30 | 2014-01-01 | 广东申菱空调设备有限公司 | Rapid cooling type aircraft ground air conditioning unit and control method thereof |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7055777B2 (en) * | 2002-06-25 | 2006-06-06 | 21St Century Airships Inc. | Airship and method of operation |
| US7228793B2 (en) * | 2002-11-25 | 2007-06-12 | Fizzy Fruit, LLC | Carbonation system for enhancing the flavor of fruits and vegetables |
| US7708222B2 (en) * | 2007-04-27 | 2010-05-04 | Stratocomm Corporation | Long mission tethered aerostat and method of accomplishing |
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2014
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7472865B2 (en) * | 2005-09-15 | 2009-01-06 | Lockheed Martin Corporation | Dehumidification system for an airship |
| CN101832619A (en) * | 2009-03-09 | 2010-09-15 | 北京航空航天大学 | Novel low-temperature and low-pressure wind speed environment control system |
| CN102179140A (en) * | 2011-01-27 | 2011-09-14 | 中国商用飞机有限责任公司 | Drying system used in airplane |
| CN203012558U (en) * | 2012-12-27 | 2013-06-19 | 西安飞豹科技发展公司 | Airplane nacelle sealed cabin environment control system |
| CN103486696A (en) * | 2013-09-30 | 2014-01-01 | 广东申菱空调设备有限公司 | Rapid cooling type aircraft ground air conditioning unit and control method thereof |
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