CN104071327A - Parallel type temperature control system and control method for stratospheric airship - Google Patents
Parallel type temperature control system and control method for stratospheric airship Download PDFInfo
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- CN104071327A CN104071327A CN201410247741.XA CN201410247741A CN104071327A CN 104071327 A CN104071327 A CN 104071327A CN 201410247741 A CN201410247741 A CN 201410247741A CN 104071327 A CN104071327 A CN 104071327A
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Abstract
The invention discloses a parallel type temperature control system and a control method for a stratospheric airship. The control system comprises a first temperature control subsystem and a second temperature control subsystem which are connected in parallel, wherein the first temperature control subsystem comprises a high-pressure gas tank, a cold plate which is mounted in an airship cabin and is linked with relevant equipment or is close to the relevant equipment, a heat exchanger which is mounted in the airship cabin, a first fan which is close to the heat exchanger, a first pipeline which is communicated with the high-pressure gas tank and the cold plate and is used for guiding gas out of the cabin, and a second pipeline which is communicated with the high-pressure gas tank and the heat exchanger and is used for guiding the gas out of the cabin; and the second temperature control subsystem comprises a fan, a third pipeline which is communicated with the fan and the cold plate and is used for guiding the gas out of the cabin, an air outlet device which is arranged above the relevant equipment in the cabin, and a fourth pipeline which is communicated with the air outlet device and the fan. The control system has the advantages of less power consumption, light weight, and relative lower requirements for the sealing of the pipelines. Through the adoption of the control system and the control method, the adverse effect that a single cold source cannot meet the requirements of refrigeration when the airship is in a low altitude in extremely hot weather, can be avoided.
Description
Technical field
The present invention relates to stratospheric airship environmental control system and method, be particularly useful for controlling parallel control system and the method for temperature in cabin.
Background technology
Compare with other aerospace vehicles, stratospheric airship has unique advantage in fields such as communication, supervision, defence, and aspect military and civilian, development is comparatively quick.
The thermal control problem that a key issue of stratospheric airship design is exactly engine room facilities:
First, the operating altitude of stratospheric airship is generally 20km, and its ambient temperature is minimum reaches-56.5 ℃, and if do not taked adequate measures, the equipment in cabin comprises that electronic machine, communication apparatus etc. all cannot work.
Secondly, if run into, face subaerial ambient temperature higher in dirigible lift-off process or decline process, when ambient temperature is greater than the permissive temperature of equipment, also can affect the in-use performance of equipment.
Therefore need to design a kind of new system, solve the problems referred to above.
Summary of the invention
Goal of the invention: provide a kind of simple in structure, power consumption is little, the good cabin atmosphere control system of controllability and method, for the whole 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 and the second temperature control subsystem in parallel;
Described the first temperature control subsystem comprises high pressure gas holder, be installed in dirigible cabin and with relevant device and connect or approaching cold drawing, be installed on the heat exchanger in dirigible cabin, the first fan near heat exchanger, be communicated with described high pressure gas holder and cold drawing and gas drawn to first pipeline in cabin, and be communicated with described high pressure gas holder and heat exchanger and gas drawn to second pipeline in cabin;
Described the second temperature control subsystem comprises blower fan, is communicated with blower fan and cold drawing and gas is drawn to the 3rd pipeline in cabin, is arranged at the exhaust apparatus above relevant device cabin in, and the 4th pipeline of connection exhaust apparatus and blower fan.
On described the first pipeline, the second pipeline, the 3rd pipeline and the 4th pipeline, be provided with valve.Described cold drawing comprises and forms the cover plate of a hollow accommodation space and connect and form the coil pipe of fold-line-shaped air flue with cover plate inwall, and coil pipe has admission port and the air extractor duct that stretches out cover plate outside.The present invention also comprises the electrical heating wire that is arranged on cabin inwall.
In a further embodiment, the present invention also comprises temperature acquisition disposal system, described temperature acquisition disposal system comprises the first temperature sensor being arranged on relevant device, the touch switch being electrically connected to electrical heating wire, the second temperature sensor that is arranged at dirigible cabin inwall, is fixed on dirigible bulkhead and stretches out the three-temperature sensor in bulkhead outside, the data trap being connected with three-temperature sensor with the second temperature sensor, and the control housing connecting with data trap, the first temperature sensor, touch switch and each valve.
Control method based on the parallel temperature controlling system of above-mentioned stratospheric airship, comprises the steps:
When dirigible is during from the higher low latitude upward movement of ambient temperature, the first temperature control subsystem is opened, and the cold air in high pressure gas holder is delivered to cold drawing, cooling connection with it or close equipment; Meanwhile, cold air is delivered to heat exchanger, and the first fan blows other parts to cabin by near air heat exchanger, forms airflow circulating;
When dirigible rises to certain altitude, temperature is out of my cabin during lower than the highest permissive temperature of below deck equipment, and the second temperature control subsystem is opened, the cold air outside cabin is transported in cabin and cold drawing in;
When dirigible after operation a period of time, when temperature drops to the permissive temperature of equipment, stops the first temperature control subsystem and the second temperature control subsystem at advection layer;
Temperature in dirigible during lower than the minimum permissive temperature of below deck equipment, is opened electrical heating wire heating, opens the second fan simultaneously, forms airflow circulating in cabin;
When dirigible declines, first open the second temperature control subsystem and carry out coolingly, when it can not meet the demands, open the first temperature control subsystem.
Beneficial effect: the present invention has advantages of that consumption of current is less, quality is light, relatively low to the sealing requirements of pipeline; Can prevent that 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 the advantages such as compact conformation, quality are light, low price, controllability is good, safety is high in addition.
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.
The specific embodiment
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 and the second temperature control subsystem in parallel, and dirigible cabin sidewall is made by warming plate 1.
The 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 cooling for the integral body in cabin.
Particularly, the first temperature control subsystem comprises high pressure gas holder 11, cold drawing 12, heat exchanger 13, the first fans 14, and the first pipeline 17, the second pipeline 18, the first valve 15 and the second valve 16 etc.
Cold drawing 12 is installed on and in dirigible cabin and with relevant device, connects or approach, for carry out interchange of heat with it, to reduce the temperature of equipment; Heat exchanger 13 is installed in dirigible cabin, for cabin in air carry out interchange of heat, to reduce the temperature in cabin; The first fan 14 is near heat exchanger, for the air of surroundings being blown to other places in cabin, forms circulating air, strengthens heat transfer effect; The first pipeline 17 is for being communicated with high pressure gas holder and cold drawing and gas being drawn to cabin, to be formed for the first circulating path of cooling below deck equipment; The second pipeline 18 is for being communicated with high pressure gas holder and heat exchanger and gas being drawn to cabin, for temperature in cooling cabin.
And the second temperature control subsystem comprises blower fan 21, be communicated with blower fan and cold drawing and gas drawn to the 3rd pipeline 23 in cabin, be arranged at the exhaust apparatus 22 above relevant device cabin in, and the 4th pipeline 24 of connection exhaust apparatus and blower fan.On the first pipeline, the second pipeline, the 3rd pipeline and the 4th pipeline, be provided with valve.
In a further embodiment, cold drawing comprises and forms the cover plate 121 of a hollow accommodation space and the coil pipe 124 that connects and form fold-line-shaped air flue with cover plate inwall, and coil pipe has admission port 123 and the air extractor duct 122 that stretches out cover plate outside.Be arranged on the electrical heating wire of cabin inwall.
In a further embodiment, control process is undertaken by temperature acquisition disposal system, described temperature acquisition disposal system comprises the first temperature sensor 41 being arranged on relevant device, the touch switch 46 being electrically connected to electrical heating wire, be arranged at the second temperature sensor 42 of dirigible cabin inwall, be fixed on dirigible bulkhead and stretch out the three-temperature sensor 43 in bulkhead outside, the data trap 44 being connected with three-temperature sensor 43 with the second temperature sensor 42, and and data trap, the first temperature sensor 41, the control housing 45 that touch switch and each valve connect.
Wherein, the first temperature sensor is used for surveying the temperature of electronic machine, and the second temperature sensor is used for surveying the ambient temperature in dirigible equipment compartment, and three-temperature sensor is used for surveying 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 during from the higher low latitude upward movement of ambient temperature, the first temperature control subsystem is opened, and the cold air in high pressure gas holder is delivered to cold drawing, cooling connection with it or close equipment; Meanwhile, cold air is delivered to heat exchanger, and the first fan blows other parts to cabin by near air heat exchanger, forms airflow circulating;
When dirigible rises to certain altitude, temperature is out of my cabin during lower than the highest permissive temperature of below deck equipment, and the second temperature control subsystem is opened, the cold air outside cabin is transported in cabin and cold drawing in;
When dirigible after operation a period of time, when temperature drops to the permissive temperature of equipment, stops the first temperature control subsystem and the second temperature control subsystem at advection layer;
Temperature in dirigible during lower than the minimum permissive temperature of below deck equipment, is opened electrical heating wire heating, opens the second fan simultaneously, forms airflow circulating in cabin;
When dirigible declines, first open the second temperature control subsystem and carry out coolingly, 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 second temperature control subsystem occur over just on fan and blower fan the demand of power supply, have the additional demand of compressor to electric power, so its consumption of current are relatively less unlike vaporization cycle.The parts that simultaneously need than fluid circuit cooling system are few, and in this system, related cooling media does not have corrosive property, relatively low to the seal request of pipeline, thus 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 characterictic described in the above-mentioned specific embodiment, in reconcilable situation, can combine by any suitable mode.For fear of unnecessary repetition, the present invention is to the explanation no longer separately of various possible array modes.
Claims (6)
1. the parallel temperature controlling system of stratospheric airship, is characterized in that, comprises the first temperature control subsystem and the second temperature control subsystem in parallel;
Described the first temperature control subsystem comprises high pressure gas holder (11), be installed in dirigible cabin and with relevant device and connect or approaching cold drawing (12), be installed on the heat exchanger (13) in dirigible cabin, the first fan (14) near heat exchanger, be communicated with described high pressure gas holder and cold drawing and gas drawn to first pipeline (17) in cabin, and be communicated with described high pressure gas holder and heat exchanger and gas drawn to second pipeline (18) in cabin;
Described the second temperature control subsystem comprises blower fan (21), be communicated with blower fan and cold drawing and gas drawn to the 3rd pipeline (23) in cabin, be arranged at the exhaust apparatus (22) of relevant device top in cabin, and the 4th pipeline (24) that is communicated with exhaust apparatus and blower fan.
2. the parallel temperature controlling system of stratospheric airship as claimed in claim 1, is characterized in that, on described the first pipeline, the second pipeline, the 3rd pipeline and the 4th pipeline, is 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 and forms the cover plate (121) of a hollow accommodation space and connect and form the coil pipe (124) of fold-line-shaped air flue with cover plate inwall, and coil pipe has admission port (123) and the air extractor duct (122) that stretches 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 comprises the electrical heating wire that is arranged on cabin inwall.
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) being arranged on relevant device, the touch switch being electrically connected to electrical heating wire (46), be arranged at second temperature sensor (42) of dirigible cabin inwall, be fixed on dirigible bulkhead and stretch out the three-temperature sensor (43) in bulkhead outside, the data trap (44) being connected with three-temperature sensor (43) with the second temperature sensor (42), and and data trap, the first temperature sensor (41), the control housing (45) that touch switch and each valve connect.
6. the control method based on the parallel temperature controlling system of stratospheric airship claimed in claim 4, is characterized in that, comprises the steps:
When dirigible is during from the higher low latitude upward movement of ambient temperature, the first temperature control subsystem is opened, and the cold air in high pressure gas holder is delivered to cold drawing, cooling connection with it or close equipment; Meanwhile, cold air is delivered to heat exchanger, and the first fan blows other parts to cabin by near air heat exchanger, forms airflow circulating;
When dirigible rises to certain altitude, temperature is out of my cabin during lower than the highest permissive temperature of below deck equipment, and the second temperature control subsystem is opened, the cold air outside cabin is transported in cabin and cold drawing in;
When dirigible after operation a period of time, when temperature drops to the permissive temperature of equipment, stops the first temperature control subsystem and the second temperature control subsystem at advection layer;
Temperature in dirigible during lower than the minimum permissive temperature of below deck equipment, is opened electrical heating wire heating, opens the second fan simultaneously, forms airflow circulating in cabin;
When dirigible declines, first open the second temperature control subsystem and carry out coolingly, 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 true CN104071327A (en) | 2014-10-01 |
| CN104071327B CN104071327B (en) | 2016-03-30 |
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| CN201410247741.XA Expired - Fee Related CN104071327B (en) | 2014-06-05 | 2014-06-05 | The parallel temperature controlling system of stratospheric airship and control method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104608906A (en) * | 2014-12-05 | 2015-05-13 | 中国航空工业集团公司第六三一研究所 | Stratospheric airship task control subsystem |
| CN105485834A (en) * | 2015-11-30 | 2016-04-13 | 上海宇航系统工程研究所 | Temperature control system of near space sealed cabin |
| CN106184693A (en) * | 2016-07-18 | 2016-12-07 | 江苏科技大学 | A kind of stratospheric airship balloonet air-charging and air-discharging system and method |
| CN110422311A (en) * | 2019-07-25 | 2019-11-08 | 南京航空航天大学 | A kind of stratospheric airship equipment compartment temperature control system |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106184693A (en) * | 2016-07-18 | 2016-12-07 | 江苏科技大学 | A kind of stratospheric airship balloonet air-charging and air-discharging system and method |
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| CN110422311A (en) * | 2019-07-25 | 2019-11-08 | 南京航空航天大学 | A kind of stratospheric airship equipment compartment temperature control system |
| 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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| Publication number | Publication date |
|---|---|
| CN104071327B (en) | 2016-03-30 |
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Granted publication date: 20160330 Termination date: 20190605 |