CN204998798U - Close on spacecraft and hot accuse system thereof - Google Patents
Close on spacecraft and hot accuse system thereof Download PDFInfo
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- CN204998798U CN204998798U CN201520776812.5U CN201520776812U CN204998798U CN 204998798 U CN204998798 U CN 204998798U CN 201520776812 U CN201520776812 U CN 201520776812U CN 204998798 U CN204998798 U CN 204998798U
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- utricule
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- near space
- heat
- radiation coating
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Abstract
The utility model discloses a close on spacecraft and hot accuse system thereof. The utility model discloses close on the hot accuse system of spacecraft including set up on closing on spacecraft casing surface having the inflation contraction work can the shrink utricule the shrink utricule for with that closes on the outer surface contact face of spacecraft casing still is equipped with the phase transition heat -sink device on the surface, the phase transition heat -sink device is used for absorbing close on the radiation heat of spacecraft under -deck still be equipped with first radiation coating on the outside of phase transition heat -sink device, first radiation coating absorbs close on the radiation heat of spacecraft under -deck and conduct extremely the phase transition heat -sink device. The utility model discloses it is relatively stable that hot accuse system can guarantee to close on spacecraft under -deck temperature, and its structure is succinct, and hot prosecutor formula is simple. The utility model discloses closing on spacecraft and adopting passive heat accuse cost little, the temperature that can effectively guarantee to close on the spacecraft under -deck is invariable relatively for ware under -deck equipment can normal work.
Description
Technical field
The utility model belongs near space vehicle technical field, particularly relates to the heat control system of near space vehicle and the near space vehicle containing this heat control system.
Background technology
Near space is the new space of human economy exploitation, and following near space vehicle will reside in this region for a long time.The pacing factor that can the equipment compartment of aircraft provide metastable temperature environment to determine below deck equipment normally to work.
The problem that night temperatures is excessively cold, likely appears that day temperature is too high, in the combined action that the interior ambient temperature be subject to due to indoor environment temperature near space of aircraft closed cabin body, solar radiation, infrared radiation and sun reflection and below deck equipment generate heat.Be difficult to the external environment condition of discharging at the heat of electronic machine, need to take actv. thermal control measure, to ensure that electronic machine temperature is within the temperature of safety.For the long-time supersonic aircraft in endoatmosphere flight, aircraft always to add heat large, thermal environment is comparatively severe, and narrow space and heat seal better performances in cabin, indoor environment temperature is also higher or lower, and heat is difficult to be dispersed into air environment or be difficult to absorb heat.The relative constancy of indoor environment temperature cannot be kept, be difficult to effective guarantee below deck equipment and normally work.
The current thermal control measure to aircraft is divided into passive thermal control method and Active thermal control method usually, but be subject to the impact of Flight Vehicle Structure up till now, energy resource system load is restricted, and should not adopt the strategy of active temperature control, therefore proposes new requirement to the thermal control of equipment compartment.
Wherein, passive thermal control method installs simple, dependable performance, lightweight, cost is low, commonality is good.Passive scheme mainly through change instrument installation form, increase heat insulating mattress, increase phase-change material, temperature control cover be installed and paste aluminium foil etc., to suppress closed cabin body heat environment to the heat effect of instrument and equipment, to realize controlling the temperature of the electronic machine that works long hours.Tradition passive thermal control method generally only takes thermal control measure for electronic machine, and for inner complicated, narrow and small and there is the high-temperature closed of multiple electronic machine, take thermal control measure one by one, will bring larger thermal control cost to Single Electron equipment.With whole cabin body for thermal control object, to take at many levels, thermal control mode step by step, suppress the heat importing electronic machine.Thermal control measure is taked to closed cabin housing, the heat importing cabin body into is reduced from source, and be subject to thermal property and constructional feature for the difference of electronic machine, adopt different thermal control measures or multiple thermal control measure associating, suppress the heat being entered electronic machine by heat conduction, radiation and free convection heating, control with the temperature realized for complicated cabin body inner electronic equipment.Therefore, these passive temperature control measures are complicated at present, and still bring larger thermal control cost.
Utility model content
The purpose of this utility model is to overcome above-mentioned the deficiencies in the prior art, provides a kind of near space vehicle and heat control system thereof, which solves current complicated to the passive temperature control measure of near space vehicle, and brings the technical matters of larger thermal control cost.
For achieving the above object, the technical solution adopted in the utility model is:
A kind of near space vehicle heat control system, comprise the contraction utricule with contractile function be arranged near space vehicle housing outer surface, described contraction utricule relative to the surface of described near space vehicle housing outer surface contact surface on be also provided with decalescence parts, described decalescence parts, for absorbing the radiations heat energy in described near space vehicle cabin, the outside of described decalescence parts are also provided with the first radiation coating; Described first radiation coating absorbs the radiations heat energy in described near space vehicle cabin and conducts to described decalescence parts.
Preferably, described near space vehicle heat control system also comprises Chu Liuxiang, and described storage stream case is communicated with described contraction utricule by heat-conducting fluid passage, realizes the circulation of heat-conducting fluid between described storage stream case and described contraction utricule.
Particularly, described storage stream case be arranged on described contraction utricule relative to on the surface of described near space vehicle housing outer surface contact surface.
Further preferably, described contraction utricule comprises the first contraction utricule and second and shrinks utricule, described first cavity shrinking utricule communicates with the described second cavity shrinking utricule, described decalescence parts be arranged on described first shrink utricule relative to on the surface of described near space vehicle housing outer surface contact surface, described storage stream case be arranged on described second shrink utricule relative to on the surface of described near space vehicle housing outer surface contact surface, and described storage stream case passes through described heat-conducting fluid passage and described second shrinks utricule and be communicated with.
Further preferably, described first shrink utricule relative to the surface of described near space vehicle housing outer surface contact surface on be also provided with the second radiation coating stoping described decalescence parts to radiations heat energy in described near space vehicle cabin.
Particularly, the thickness of described second radiation coating is 50-150 micron.
Further preferably, described first shrink utricule relative to described first radiation coating contact surface on be also provided with the 3rd radiation coating being beneficial to and absorbing radiations heat energy in described near space vehicle cabin.
Particularly, the thickness of described 3rd radiation coating is 50-150 micron.
Further preferably, the described second outside face shrinking utricule is also coated with the 4th radiation coating being beneficial to and shrinking the heat-conducting fluid radiations heat energy in utricule to described second.
Particularly, the thickness of described 4th radiation coating is 50-150 micron.
Preferably, the outside face of described storage stream case is also provided with the 5th radiation coating for preventing the outside radiations heat energy of described heat-conducting fluid in described storage stream case.
Further preferably, the THICKNESS CONTROL of described 5th radiation coating is 50-150 micron.
Further preferably, the described first cavity shrinking utricule and/or the second contraction utricule is divided to be separated with several compartments, and wherein, described first several compartments shunk in utricule communicate with each other or several compartments shunk in utricule communicate with second respectively; Described second several compartments shunk in utricule communicate with each other or several compartments flow case by described heat-conducting fluid channel connection with described storage respectively.
Preferably, the THICKNESS CONTROL of described first radiation coating is 50-150 micron.
And a kind of near space vehicle, it comprises near space vehicle heat control system described in the utility model.
Compared with prior art, the utility model provides near space vehicle heat control system by arranging contraction utricule near space vehicle housing outer surface, and decalescence parts are set shrinking on the surface that utricule deviates near space vehicle housing outer surface, the first radiation coating is utilized to absorb the radiations heat energy in described near space vehicle cabin and conduct to described decalescence parts, the radiations heat energy making the generation of decalescence parts near space vehicle below deck equipment and sunshine be passed to decalescence parts carries out absorption and stores, meanwhile, the Swelling and contraction shrinking utricule generation also effectively can absorb the radiations heat energy produced near space vehicle cabin, thus keep the temperature relative constancy near space vehicle cabin.Therefore, the utility model near space vehicle heat control system adopts passive thermal control mode that the temperature near space vehicle cabin can be made relatively stable, for the normal work of near space vehicle below deck equipment provides guarantee, and it is simple for structure, and thermal control mode is simple.
The utility model near space vehicle is owing to have employed above-mentioned the utility model near space vehicle heat control system, therefore, adopt passive thermal control cost little near space vehicle, effectively can ensure the temperature relative constancy near space vehicle cabin, device below deck equipment can normally be worked.
Accompanying drawing explanation
Fig. 1 is the near space vehicle heat control system structural representation that the utility model embodiment provides;
Fig. 2 is the vesicula contractilles body structure enlarged diagram in the near space vehicle heat control system that provides of the utility model embodiment.
Detailed description of the invention
In order to make the purpose of this utility model, technical scheme and advantage clearly understand, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the utility model, and be not used in restriction the utility model.
It should be noted that, when an element is described on " being fixed on " or " being arranged at " another element, it can directly on another element or may there is centering elements simultaneously.Be described to be " connection " another element when an element, it can be directly connect another element or may there is centering elements simultaneously.
Also it should be noted that, the orientation term such as left and right, upper and lower, the top in the present embodiment, end, is only relative concept or be reference with the normal operating condition of product each other, and should not be regarded as have restrictive.
It is little that the utility model embodiment provides a kind of thermal control cost, effectively can keep the passive thermal control system of temperature relative constancy near space vehicle cabin.This near space vehicle heat control system structure as shown in Figure 1, 2, it comprises the contraction utricule 20 be arranged near space vehicle housing 4 outside face, described contraction utricule 20 relative to the surface in the outer 4 surface contact faces of described near space vehicle housing on be also provided with decalescence parts 10.
Wherein, decalescence parts 10 are containing decalescence material, therefore, have the effect of heat absorption store heat and heat release heat.In one embodiment, the decalescence material in decalescence parts 10 can be inorganic phase-changing material or organic phase change material or compound that is inorganic and organic phase change material.In a particular embodiment, inorganic phase-changing material can select the inorganic matters such as crystalline hydrate salt, fuse salt, metal alloy; Organic phase change material can select the organic matters such as paraffin, carboxylic acid, ester, polyalcohol.Therefore, in one embodiment, these decalescence parts 10 can be phase-change material Rotating fields or the utricule structures of those phase-change materials formation.
In order to make decalescence parts 1 can effectively decalescence and heat release, in one embodiment, in the outside of decalescence parts 10, table be provided with the first radiation coating 11.The setting of the first radiation coating 11, can to absorb in described near space vehicle cabin and sunshine radiations heat energy and conduct to described decalescence parts 10, make the phase transformation of decalescence material carry out heat storage.This first radiation coating 11 is preferably painting and is located on the whole surface of decalescence parts 10.
In order to improve the effect of the radiation-absorbing heat of the first radiation coating 11, in one embodiment, this the first radiation coating 11 material is the radiative material with high radiation coefficient, the radiative material of this high radiation coefficient can select the high radiation coefficient material of this area routine, as in a particular embodiment, this high radiation coefficient material selection SiC, metallic oxide, boride, sulfide, selenide etc.
In another embodiment, the THICKNESS CONTROL of described first radiation coating 11 is 50-150 micron.
One surface of above-mentioned contraction utricule 20 contacts with the first radiation coating 11 on above-mentioned decalescence parts 10, and contacting with near space vehicle housing outer surface relative to the surface of the first radiation coating 11 contact surface of utricule 20 is shunk in its another surface namely.Like this, when after the first radiation coating 11 radiation-absorbing heat, as the radiations heat energy that the heat near space environment and near space vehicle below deck equipment 5 produce, particularly daytime sunshine radiations heat energy after, heat is directly passed to decalescence parts 10 and carries out phase transformation heat storage.Meanwhile, in the process of the first radiation coating 11 radiation-absorbing heat, shrink utricule 20 and also can play its expansion characteristics because of the radiations heat energy absorbed, the radiations heat energy realizing near space vehicle below deck equipment 5 generation transmits to decalescence parts 10, and avoid extraneous heat to transmit near space vehicle cabin, avoid excessive temperature near space vehicle cabin to raise, keep temperature near space vehicle cabin relatively stable.
When near space ambient temperature is too low, particularly during night, now near space vehicle cabin, temperature also can reduce suddenly.In the process, shrink utricule 20 volume in low temperature environment can shrink, like this, decalescence parts 10 also can be close to described near space vehicle housing 4 because of shrinking of utricule 20 of contraction, and the thermal radiation effect of the first radiation coating 11 by decalescence parts 10 surface, radiations heat energy near space vehicle cabin, makes the temperature near space vehicle cabin keep relative stability.
In one embodiment, the described dilation function of shrinking utricule 20 is realized by the heat-conducting fluid be filled in described contraction utricule.In certain embodiments, the heat-conducting fluid that this heat-conducting fluid can select this area conventional, as in a particular embodiment, this heat-conducting fluid selects alcohols etc.Select those heat-conducting fluids can play good conductive force and/or cold and hot contraction.
In one embodiment, the cavity shrinking utricule 20 point is separated with several compartments 23, and communicates between several compartments 23 or several compartments 23 are flowed case 30 be communicated with by described heat-conducting fluid passage 24 with described storage respectively, as shown in Figure 2.The cavity shrinking utricule 20 is separated into some compartments 23, heat-conducting fluid can be uniformly filled in and shrinks in utricule 20 cavity, also can avoid shrinking utricule 20 and locally overinflation occur and be out of shape or reduce the service life of shrinking utricule 20.
In a further embodiment, above-mentioned near space vehicle heat control system also comprises storage stream case 30, and this storage stream case 30 is communicated with contraction utricule 20 by heat-conducting fluid passage 24.This storage stream case 30 is for storing heat-conducting fluid, when heat-conducting fluid is by radiations heat energy, this heat-conducting fluid expands is filled in the cavity of contraction utricule 20 by heat-conducting fluid passage 24, make to shrink utricule 20 expand and launch, or buffering shrinks the expansion that in the cavity of utricule 20, heat-conducting fluid occurs.In one embodiment, storage stream case 30 be arranged on shrink utricule 20 relative to on the surface in described near space vehicle housing 4 exterior surface face, certainly, this storage stream case 30 can also need to be arranged on other positions adjacent with shrinking utricule 20 according to installation.
In order to avoid or reduce and be stored in the outside radiations heat energy of heat-conducting fluid flowed in case 30, in one embodiment, also be provided with the 5th radiation coating 31 at the outside face of described storage stream case 30, it effectively can prevent the outside radiations heat energy of described heat-conducting fluid in described storage stream case 30.
In order to reduce the 5th radiation coating 31 outwards radiations heat energy effect, in one embodiment, 5th radiation coating 31 material is the radiative material with low-E, the radiative material of this low-E can be the low-E material of this area routine, as in one embodiment, low-E coating or low-E metal powder etc.In another embodiment, the THICKNESS CONTROL of described 5th radiation coating 31 is 50-150 micron.
On the above-mentioned near space vehicle heat control system embodiment basis including storage stream case 30, in one embodiment, above-mentioned contraction utricule 20 comprises the first contraction utricule 21 and second and shrinks utricule 22, and the first cavity shrinking utricule 21 communicates with the described second cavity shrinking utricule 22.Now, in one embodiment, decalescence parts 10 be arranged on described first shrink utricule 21 relative to on the surface in described near space vehicle housing 4 exterior surface face, described storage stream case 30 be arranged on described second shrink utricule 22 relative to on the surface in described near space vehicle housing 4 exterior surface face, and described storage is flowed case 30 and is shunk utricule 22 by heat-conducting fluid passage 24 and second and be communicated with.Communicate by contraction utricule 20 being arranged to cavity first shrinks utricule 21 and second shrinks utricule 22, conveniently can carry out regional processing to the surface of shrinking utricule 20, radiations heat energy to be optimized near space vehicle cabin to decalescence parts 10 radiation delivery, thus improve the relative stability of temperature near space vehicle cabin.
As in one embodiment, first shrink utricule 21 relative to the surface in described near space vehicle housing 4 exterior surface face on be also coated with the second radiation coating 211, the surface contacted with decalescence parts 10 that is to say the first contraction utricule 21 is also coated with the second radiation coating 211.The setting of this second radiation coating 211, at needs by when near space vehicle cabin, radiations heat energy is outwards derived, as hot environment on daytime, decalescence parts 10 can continue the impact being subject to external heat source, constant temperature raises, likely there is the trend of its heat absorbed to radiation near space vehicle cabin, and the existence of this second radiation coating 211, the heat of outside or decalescence parts 10 effectively can be avoided near space vehicle cabin to carry out radiation and cause the harmful effect that in cabin, temperature raises.
Therefore, in a particular embodiment, this second radiation coating 211 material is the material with low-E, and the radiative material of this low-E can be the low-E material of this area routine, as in one embodiment, low-E coating or low-E metal powder etc.In another specific embodiment, the THICKNESS CONTROL of described second radiation coating 211 is 50-150 micron.By regulating this second radiation coating 211 material and thickness, improve the effect of external high temperature environment to radiations heat energy near space vehicle cabin that it stops decalescence parts 10 or near space.
Or in another embodiment, first shrink utricule 21 relative to the surface in the first radiation coating 11 surface contact face on be also coated with the 3rd radiation coating 212, that is to say the first contraction utricule 21 with the surface in described near space vehicle housing 4 exterior surface face on be also coated with the 3rd radiation coating 212.During daytime, first shrinks heat-conducting fluid in utricule 21 and the second contraction utricule 22 is expanded by after radiations heat energy, after first contraction utricule 21 and the second contraction utricule 22 are filled, the 3rd radiation coating 212 that first contraction utricule 21 surface is coated with can continue to absorb the radiations heat energy produced near space vehicle cabin, and is passed to decalescence parts 10.
In a particular embodiment, 3rd radiation coating 212 material is the material with high radiation coefficient, the radiative material of this high radiation coefficient can select the high radiation coefficient material of this area routine, as in a particular embodiment, this high radiation coefficient material selection SiC, metallic oxide, boride, sulfide, selenide etc.In another specific embodiment, the THICKNESS CONTROL of described 3rd radiation coating 212 is 50-150 micron.By regulating the 3rd radiation coating 212 material and thickness, improve the effect that the 3rd radiation coating 212 absorbs the radiations heat energy that near space vehicle below deck equipment 5 produces in the course of the work.
In a preferred embodiment, first shrink utricule 21 while the second radiation coating 211 is set, first shrink utricule 21 relative to the surface in the first radiation coating 11 surface contact face on the 3rd radiation coating 212 is set.Such first shrinks utricule 21 can effectively prevent the external high temperature environment of decalescence parts 10 or near space to while radiations heat energy near space vehicle cabin, radiations heat energy near space vehicle cabin can be conducted to decalescence parts 10, improve the stability of temperature near space vehicle cabin.
In one embodiment, the above-mentioned second outside face shrinking utricule 22 is also coated with the 4th radiation coating 221 being beneficial to and shrinking the heat-conducting fluid radiations heat energy in utricule 22 to described second.4th radiation coating 221 is preferably painting and is located on the second whole surface of contraction utricule 22.
In a particular embodiment, 4th radiation coating 221 material is the material with high radiation coefficient, the radiative material of this high radiation coefficient can select the high radiation coefficient material of this area routine, as in a particular embodiment, this high radiation coefficient material selection SiC, metallic oxide, boride, sulfide, selenide etc.In another specific embodiment, the THICKNESS CONTROL of described 4th radiation coating 221 is 50-150 micron.
On the basis of the various embodiments described above, in one embodiment, above-mentioned first cavity shrinking utricule 21 or the second contraction utricule 22 is divided to be separated with several compartments 23, or the first cavity shrinking utricule 21 and the second contraction utricule 22 is all divided to be separated with several compartments 23, and several compartments 23 wherein in the first contraction utricule 21 communicate with each other or several compartments 23 shunk with second in utricule 22 communicate respectively; Second several compartments 23 shunk in utricule 22 communicate with each other or several compartments 23 are flowed case 30 be communicated with by described heat-conducting fluid passage 24 with described storage respectively, and the second contraction utricule 22 structure as shown in Figure 2.The cavity and the second cavity shrinking utricule 22 that shrink utricule 21 by first are separated into some compartments 23, heat-conducting fluid can be uniformly filled in shrink in utricule 20 cavity, the cavity of the first contraction utricule 21 and second also can be avoided to shrink utricule 22 and locally overinflation occur and be out of shape or reduce the service life of shrinking utricule 20.
Therefore, near space vehicle heat control system in the various embodiments described above is by its decalescence parts 10 arranged and shrink utricule 20 or the further storage stream case 30 arranged, make the utility model embodiment near space vehicle heat control system can ensure that the temperature near space vehicle cabin is relatively stable, and it is simple for structure, thermal control mode is simple.
Correspondingly, on the basis of near space vehicle heat control system above, the utility model embodiment still provides near space vehicle, and it comprises utility model embodiment near space vehicle heat control system mentioned above.Therefore, adopt passive thermal control cost little near space vehicle, effectively can ensure the temperature relative constancy near space vehicle cabin, device below deck equipment 5 can normally be worked.
The foregoing is only preferred embodiment of the present utility model; not in order to limit the utility model; all do within spirit of the present utility model and principle any amendment, equivalent to replace or improvement etc., all should be included within protection domain of the present utility model.
Claims (15)
1. a near space vehicle heat control system, it is characterized in that: comprise the contraction utricule with dilation function be arranged near space vehicle housing outer surface, described contraction utricule relative to the surface of described near space vehicle housing outer surface contact surface on be also provided with decalescence parts, described decalescence parts, for absorbing the radiations heat energy in described near space vehicle cabin, the outside of described decalescence parts are also provided with the first radiation coating; Described first radiation coating absorbs the radiations heat energy in described near space vehicle cabin and conducts to described decalescence parts.
2. near space vehicle heat control system as claimed in claim 1, it is characterized in that: also comprise Chu Liuxiang, described storage stream case is communicated with described contraction utricule by heat-conducting fluid passage, realizes the circulation of heat-conducting fluid between described storage stream case and described contraction utricule.
3. near space vehicle heat control system as claimed in claim 2, is characterized in that: described storage stream case be arranged on described contraction utricule relative to on the surface of described near space vehicle housing outer surface contact surface.
4. near space vehicle heat control system as claimed in claim 3, it is characterized in that: described contraction utricule comprises the first contraction utricule and second and shrinks utricule, described first cavity shrinking utricule communicates with the described second cavity shrinking utricule, described decalescence parts be arranged on described first shrink utricule relative to on the surface of described near space vehicle housing outer surface contact surface, described storage stream case be arranged on described second shrink utricule relative to on the surface of described near space vehicle housing outer surface contact surface, and described storage stream case shrinks utricule by described heat-conducting fluid passage and described second is communicated with.
5. near space vehicle heat control system as claimed in claim 4, is characterized in that: described first shrink utricule relative to the surface of described near space vehicle housing outer surface contact surface on be also provided with the second radiation coating stoping described decalescence parts to radiations heat energy in described near space vehicle cabin.
6. near space vehicle heat control system as claimed in claim 5, is characterized in that: the thickness of described second radiation coating is 50-150 micron.
7. near space vehicle heat control system as claimed in claim 4, is characterized in that: described first shrink utricule relative to described first radiation coating contact surface on be also provided with the 3rd radiation coating being beneficial to and absorbing radiations heat energy in described near space vehicle cabin.
8. near space vehicle heat control system as claimed in claim 7, is characterized in that: the thickness of described 3rd radiation coating is 50-150 micron.
9. near space vehicle heat control system as claimed in claim 4, is characterized in that: the outside face of described second contraction utricule is also coated with the 4th radiation coating being beneficial to and shrinking the heat-conducting fluid radiations heat energy in utricule to described second.
10. near space vehicle heat control system as claimed in claim 9, is characterized in that: the thickness of described 4th radiation coating is 50-150 micron.
11. as arbitrary in claim 2-10 as described near space vehicle heat control system, it is characterized in that: the outside face of described storage stream case is also provided with the 5th radiation coating of the outside radiations heat energy of described heat-conducting fluid for preventing in described storage stream case.
12. near space vehicle heat control systems as claimed in claim 11, is characterized in that: the THICKNESS CONTROL of described 5th radiation coating is 50-150 micron.
13. as arbitrary in claim 4-10 as described near space vehicle heat control system, it is characterized in that: the described first cavity shrinking utricule and/or the second contraction utricule is divided to be separated with several compartments, wherein, several compartments in described first contraction utricule communicate with each other or several compartments shunk in utricule communicate with second respectively; Described second several compartments shunk in utricule communicate with each other or several compartments flow case by described heat-conducting fluid channel connection with described storage respectively.
14. as arbitrary in claim 1-10 as described near space vehicle heat control system, it is characterized in that: the THICKNESS CONTROL of described first radiation coating is 50-150 micron.
15. 1 kinds of near space vehicles, it comprise as arbitrary in claim 1-14 as described near space vehicle heat control system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520776812.5U CN204998798U (en) | 2015-09-30 | 2015-09-30 | Close on spacecraft and hot accuse system thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520776812.5U CN204998798U (en) | 2015-09-30 | 2015-09-30 | Close on spacecraft and hot accuse system thereof |
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| CN204998798U true CN204998798U (en) | 2016-01-27 |
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| CN201520776812.5U Withdrawn - After Issue CN204998798U (en) | 2015-09-30 | 2015-09-30 | Close on spacecraft and hot accuse system thereof |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184825A (en) * | 2016-09-18 | 2016-12-07 | 电子科技大学 | A kind of method improving fast respone space moonlet thermal control ability |
| CN106304778A (en) * | 2016-08-12 | 2017-01-04 | 上海卫星工程研究所 | The integrated thermal control method of space big heat consumption transient working unit |
| CN106553772A (en) * | 2015-09-30 | 2017-04-05 | 东莞前沿技术研究院 | Near space vehicle and its heat control system |
| CN106741811A (en) * | 2017-01-10 | 2017-05-31 | 东莞前沿技术研究院 | Aerostatics gondola, aerostatics |
-
2015
- 2015-09-30 CN CN201520776812.5U patent/CN204998798U/en not_active Withdrawn - After Issue
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106553772A (en) * | 2015-09-30 | 2017-04-05 | 东莞前沿技术研究院 | Near space vehicle and its heat control system |
| CN106553772B (en) * | 2015-09-30 | 2023-08-04 | 东莞前沿技术研究院 | Near space vehicle and thermal control system thereof |
| CN106304778A (en) * | 2016-08-12 | 2017-01-04 | 上海卫星工程研究所 | The integrated thermal control method of space big heat consumption transient working unit |
| CN106184825A (en) * | 2016-09-18 | 2016-12-07 | 电子科技大学 | A kind of method improving fast respone space moonlet thermal control ability |
| CN106184825B (en) * | 2016-09-18 | 2018-04-06 | 电子科技大学 | A kind of method for improving fast respone space moonlet thermal control ability |
| CN106741811A (en) * | 2017-01-10 | 2017-05-31 | 东莞前沿技术研究院 | Aerostatics gondola, aerostatics |
| WO2018129880A1 (en) * | 2017-01-10 | 2018-07-19 | 东莞前沿技术研究院 | Aerostat nacelle and aerostat |
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Effective date of registration: 20230630 Address after: Room 501, Building D2, Songshan Lake International Innovation and Entrepreneurship Community, Songshan Lake High tech Industrial Development Zone, Dongguan City, Guangdong Province, 523000 Patentee after: Dongguan Dongguan Institute of Science and Technology Innovation Address before: 523000 Room 502, 5th floor, building 1, innovation and Technology Park, Songshanhu high tech Industrial Development Zone, Dongguan City, Guangdong Province Patentee before: DONGGUAN FRONTIER TECHNOLOGY INSTITUTE Patentee before: SHENZHEN KUANG-CHI SPACE TECH. Co.,Ltd. |
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Granted publication date: 20160127 Effective date of abandoning: 20230804 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20160127 Effective date of abandoning: 20230804 |